NASA/TM—2009–215902

July 2009

Using the Saturn V and Titan III 

Vibroacoustic Databanks for Random 

Vibration Criteria Development

R.C. Ferebee

Marshall Space Flight Center, Marshall Space Flight Center, Alabama
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i

NASA/TM—2009–215902

Using the Saturn V and Titan III 

Vibroacoustic Databanks for Random 

Vibration Criteria Development

R.C. Ferebee

Marshall Space Flight Center, Marshall Space Flight Center, Alabama

July 2009

National Aeronautics and

Space Administration

Marshall Space Flight Center • MSFC, Alabama 35812
ii

Available from:

NASA Center for AeroSpace Information

7115 Standard Drive

Hanover, MD 21076 –1320

443–757–5802

This report is also available in electronic form at

<https://www2.sti.nasa.gov>

Acknowledgments

This is an update to TN D–7159 “Development and Application of Vibroacoustic Structural Data Banks 

in Predicting Vibration Design and Test Criteria for Rocket Vehicle Structures,” which was originally published 

in 1973. Errors in the original publication were corrected, and additional data from the Titan program 

are also included. Some guidelines for calculating vibration criteria were also added.

Special thanks to Phillip Harrison, Rajinder Mehta, Andrew Smith, and Lowery Duvall 

from the Marshall Space Flight Center for their technical review.

TRADEMARKS

Trade names and trademarks are used in this report for identification only. This usage does not constitute an official

endorsement, either expressed or implied, by the National Aeronautics and Space Administration. 
iii

TABLE OF CONTENTS

1. INTRODUCTION ........................................................................................................... 1

2. VIBROACOUSTIC STRUCTURAL DATABANKS ...................................................... 3

2.1 Structural Characteristics ........................................................................................... 3

2.2 Vibration and Acoustic Data ...................................................................................... 3

2.3 Statistical Analysis ...................................................................................................... 4

2.4 Normalization Method ............................................................................................... 7

3. SATURN V AND TITAN III FLIGHT DATABANKS ................................................. 9

3.1 Saturn V Databank ..................................................................................................... 9

3.2 Honeycomb Databank ............................................................................................... 9

3.3 Titan III Databank ..................................................................................................... 9

4. APPLICATION OF VIBROACOUSTIC DATABANKS ................................................ 14

4.1 Utilization of Vibroacoustic Databanks ..................................................................... 14

4.2 Component Weight and Frequency Scaling ................................................................ 15

4.3 Components Mounted to Rocket Engines .................................................................. 16

5. TEST CRITERIA DEVELOPMENT .............................................................................. 17

5.1 Test Duration ............................................................................................................. 17

5.2 Test Amplitude ........................................................................................................... 19

5.3 Acceptance Test Criteria ............................................................................................. 21

6. CONCLUSIONS AND RECOMMENDATIONS .......................................................... 23

APPENDIX A—SATURN V VIBRATION AND ACOUSTIC DATA ............................... 24

APPENDIX B—TITAN III VIBRATION AND ACOUSTIC DATA .................................. 132

REFERENCES ..................................................................................................................... 191
iv

LIST OF FIGURES

 1. Reference acoustic spectrum ..................................................................................... 2

 2. Typical Space Shuttle solid rocket booster mission profile ........................................ 17

 3. S–N curve for aluminum ........................................................................................... 18

 4. Scaled vibration data enveloped by criteria ............................................................... 20

 5. Comparison of reference and new acoustic spectra .................................................. 21

 6. Illustration of tolerance stack-up ............................................................................. 22

 7. Saturn V zones .......................................................................................................... 24

 8. S-IVB stage forward skirt external acoustic measurement location ........................... 25

 9. Zone 15: S-IVB stage forward skirt external and internal acoustic 

measurement location ............................................................................................... 26

10. S-IVB stage forward skirt vibration measurement locations ..................................... 27

11. S-IVB stage forward skirt vibration measurement locations ..................................... 28

12. Ring frame PSD, longitudinal, liftoff, 2 lb/ft2 ........................................................... 29

13. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), liftoff ............... 30

14. Ring frame PSD, longitudinal, Mach 1, 2 lb/ft2 ........................................................ 31

15. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), Mach 1 ............ 32

16. Ring frame PSD, longitudinal, Max Q, 2 lb/ft2 ......................................................... 33

17. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), Max Q ............. 34

18. Ring frame PSD, longitudinal, Mach 1/Max Q, 2 lb/ft2 ............................................ 35

19. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), transonic .......... 36
v

LIST OF FIGURES (Continued)

20. Skin-stringer PSD, tangential, liftoff, 2 lb/ft2 ............................................................ 37

21. Skin-stringer PSD, tangential, Mach 1, 2 lb/ft2 ......................................................... 38

22. Ring frame PSD, tangential, Max Q, 2 lb/ft2 ............................................................ 39

23. Ring frame PSD, tangential, Mach 1/Max Q, 2 lb/ft2 ............................................... 40

24. Ring frame PSD, radial, liftoff, 2 lb/ft2 ..................................................................... 41

25. Ring frame PSD, radial, Mach 1, 2 lb/ft2 .................................................................. 42

26. Ring frame PSD, radial, Max Q, 2 lb/ft2 ................................................................... 43

27. Ring frame PSD, radial, Mach 1/Max Q, 2 lb/ft2 ...................................................... 44

28. Zone 11: S-II stage forward skirt external acoustic measurement location ................ 45

29. S-II stage forward skirt vibration measurement locations ......................................... 46

30. Ring frame PSD, longitudinal, liftoff, 3.3 lb/ft2 ........................................................ 47

31. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), liftoff ................... 48

32. Ring frame PSD, longitudinal, Mach 1, 3.3 lb/ft2 ..................................................... 49

33. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Mach 1 ............... 50

34. Ring frame PSD, radial, liftoff, 3.3 lb/ft2 .................................................................. 51

35. Ring frame PSD, radial, Mach 1, 3.3 lb/ft2 ............................................................... 52

36. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Mach 1 ................ 53

37. S-II stage forward skirt vibration measurement location .......................................... 54

38. S-II stage forward skirt vibration measurement locations ......................................... 55

39. S-II stage S-IC/S–II interstage, and S-II aft skirt vibration 

measurement locations ............................................................................................. 56

40. Ring frame PSD, radial, liftoff, 1.1–1.5 lb/ft2 ............................................................ 57
vi

LIST OF FIGURES (Continued)

41. Ring frame PSD, radial, Mach 1, 1.1–1.5 lb/ft2 ........................................................ 58

42. Ring frame PSD, radial, Max Q, 1.1–1.5 lb/ft2 ......................................................... 59

43. Saturn V acoustic spectrum, S-II forward/aft skirt, Max Q ...................................... 60

44. Ring frame PSD, radial, Mach 1/Max Q, 1.1–1.5 lb/ft2 ............................................ 61

45. Saturn V acoustic spectrum, S-II forward/aft skirt, transonic ................................... 62

46. S-IC forward skirt rings measurement locations ....................................................... 63

47. Ring frame PSD, radial, static, 9.2 lb/ft2 ................................................................... 64

48. Saturn V acoustic spectrum, S-IC forward skirt, static test ....................................... 65

49. Zone 9: S-II stage thrust cone acoustic measurement location .................................. 66

50. S-II thrust cone ring frames measurement locations ................................................. 67

51. Ring frame PSD, parallel, static, 4.7–8.0 lb/ft2 .......................................................... 68

52. Saturn V acoustic spectrum, S-II thrust cone (subzone 9-2-1), static test .................. 69

53. Ring frame PSD, normal, static, 13.9 lb/ft2 ............................................................... 70

54. Saturn V acoustic spectrum, S-II thrust cone (subzone 9-2-1), static test .................. 71

55. S-IC stage intertank ring vibration measurement location ........................................ 72

56. Ring frame PSD, longitudinal, liftoff, 6.2 lb/ft2 ........................................................ 73

57. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), liftoff .................. 74

58. Ring frame PSD, longitudinal, Mach 1, 6.2 lb/ft2 ..................................................... 75

59. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), Mach 1 ............... 76

60. Ring frame PSD, longitudinal, Max Q, 6.2 lb/ft2 ...................................................... 77

61. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), Max Q ................ 78
vii

LIST OF FIGURES (Continued)

62. Ring frame PSD, longitudinal, Mach 1/Max Q, 6.2 lb/ft2 ......................................... 79

63. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), transonic ............. 80

64. Ring frame PSD, radial, liftoff, 6.2 lb/ft2 .................................................................. 81

65. Ring frame PSD, radial, Mach 1, 6.2 lb/ft2 ............................................................... 82

66. Ring frame PSD, radial, Max Q, 6.2 lb/ft2 ................................................................ 83

67. Ring frame PSD, radial, Mach 1/Max Q, 6.2 lb/ft2 ................................................... 84

68. Zone 2: S-IC stage heat shield frame internal acoustic measurement location .......... 85

69. S-IC stage external acoustic measurement locations ................................................. 86

70. S-IC stage upper thrust ring vibration measurement location ................................... 87

71. Ring frame PSD, longitudinal, liftoff, 25.6 lb/ft2 ...................................................... 88

72. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), liftoff ............. 89

73. Ring frame PSD, longitudinal, Mach 1, 25.6 lb/ft2 ................................................... 90

74. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), Mach 1 .......... 91

75. Ring frame PSD, longitudinal, Mach 1/Max Q, 25.6 lb/ft2 ....................................... 92

76. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), transonic ........ 93

77. Ring frame PSD, radial, liftoff, 25.6 lb/ft2 ................................................................ 94

78. Ring frame PSD, radial, Mach 1, 25.6 lb/ft2 ............................................................. 95

79. Ring frame PSD, radial, Max Q, 25.6 lb/ft2 .............................................................. 96

80. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), Max Q ........... 97

81. Ring frame PSD, radial, Mach 1/Max Q, 25.6 lb/ft2 ................................................. 98

82. S-II stage forward skirt vibration measurement locations ......................................... 99
viii

LIST OF FIGURES (Continued)

 83. Skin-stringer PSD, normal, liftoff, 3.3 lb/ft2 ......................................................... 100

 84. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), liftoff ............... 101

 85. Skin-stringer PSD, longitudinal, liftoff, 1.5 lb/ft2 ................................................. 102

 86. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), liftoff ............... 103

 87. Skin-stringer PSD, longitudinal, Mach 1, 1.5 lb/ft2 .............................................. 104

 88. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Mach 1 ............ 105

 89. Skin-stringer PSD, longitudinal, Max Q, 1.5 lb/ft2 ............................................... 106

 90. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Max Q ............. 107

 91. Skin-stringer PSD, longitudinal, Mach 1/Max Q, 1.5 lb/ft2 .................................. 108

 92. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), transonic ......... 109

 93. Skin-stringer PSD, tangential, liftoff, 1.5 lb/ft2 ..................................................... 110

 94. Skin-stringer PSD, tangential, Mach 1, 1.5 lb/ft2 .................................................. 111

 95. Skin-stringer PSD, tangential, Max Q, 1.5 lb/ft2 ................................................... 112

 96. Skin-stringer PSD, tangential, Mach 1/Max Q, 1.5 lb/ft2 ...................................... 113

 97. Skin-stringer PSD, radial, liftoff, 1.5 lb/ft2 ........................................................... 114

 98. Skin-stringer PSD, radial, Mach 1, 1.5 lb/ft2 ........................................................ 115

 99. Zone 9: S-II stage aft skirt external acoustic measurement location ..................... 116

100. Zone 9: S-II/S-IC interstage external acoustic measurement location ................... 117

101. S-II stage aft skirt vibration measurement locations ............................................. 118

102. S–II aft skirt skin/stringer vibration measurement locations ................................. 119

103. S-II aft skirt skin/stringer vibration measurement locations ................................. 120
ix

LIST OF FIGURES (Continued)

104. Skin-stringer PSD, longitudinal, static, 2.8 lb/ft2 .................................................. 121

105. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), static test ................... 122

106. Skin-stringer PSD, radial, Mach 1, 2.8 lb/ft2 ........................................................ 123

107. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), Mach 1 ...................... 124

108. Skin-stringer PSD, radial, Max Q, 2.8 lb/ft2 ......................................................... 125

109. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), Max Q ....................... 126

110. Skin-stringer PSD, radial, Mach 1/Max Q, 2.8 lb/ft2 ............................................ 127

111. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), transonic ................... 128

112. Skin-stringer PSD, radial, static, 2.8 lb/ft2 ............................................................ 129

113. Honeycomb PSD, radial, static, 1.1 lb/ft2 ............................................................. 130

114. Saturn V acoustic spectrum, payload shroud, static test ....................................... 131

115. Titan IIIC vehicle compartment and station designations .................................... 132

116. Compartment 3A measurement locations ............................................................ 133

117. Compartment 3A instrumentation and guidance truss measurement locations .... 134

118. Vibration measurements 2562 and 2563, compartment 3A, 

at mounting point of attitude control nozzles, station 130 .................................... 135

119. P/L truss vibration PSD, longitudinal, Mach 1/Max Q, 2.28 lb/ft2 ....................... 136

120. P/L truss vibration PSD, radial, Mach 1/Max Q, 2.28 lb/ft2 ................................. 137

121. Ring frame vibration PSD, longitudinal, liftoff, 2.49 lb/ft2 ................................... 138

122. Ring frame vibration PSD, longitudinal, Mach 1, 2.49 lb/ft ................................. 139

123. Ring frame vibration PSD, radial, liftoff, 2.49 lb/ft .............................................. 140

124. Ring frame vibration PSD, radial, Mach 1, 2.49 lb/ft ........................................... 141
x

LIST OF FIGURES (Continued)

125. Skin-stringer vibration PSD, longitudinal, liftoff, 2.49 lb/ft .................................. 142

126. Skin-stringer vibration PSD, longitudinal, Mach 1, 2.49 lb/ft ............................... 143

127. Skin-stringer vibration PSD, radial, liftoff, 2.49 lb/ft ............................................ 144

128. Skin-stringer vibration PSD, radial, Mach 1, 2.49 lb/ft ......................................... 145

129. Titan III acoustic spectrum, compartment 3A, liftoff .......................................... 146

130. Titan III acoustic spectrum, compartment 3A, Mach 1 ........................................ 147

131. Titan III acoustic spectrum, compartment 3A, Max Q ......................................... 148

132. Compartment 2B measurement locations ............................................................. 149

133. Vibration measurements 2519 and 2520, compartment 2B, station 360 ................ 150

134. Skin-stringer vibration PSD, radial, liftoff, 2.7 lb/ft .............................................. 151

135. Skin-stringer vibration PSD, tangential, liftoff, 2.7 lb/ft ....................................... 152

136. Skin-stringer vibration PSD, tangential, Mach 1, 2.7 lb/ft .................................... 153

137. Titan III acoustic spectrum, compartment 2B, liftoff ........................................... 154

138. Titan III acoustic spectrum, compartment 2B, Mach 1/Max Q ............................ 155

139. Compartment 2C measurement locations ............................................................. 156

140. Vibration measurements 2602, 2603, and 2604, compartment 2C, station 473 ...... 157

141. Vibration measurements 2566 and 2567, compartment 2C, station 493 ................ 158

142. Skin-stringer vibration PSD, radial, liftoff, 3.06 lb/ft2 .......................................... 159

143. Skin-stringer vibration PSD, radial, Mach 1, Max Q, 3.06 lb/ft2 .......................... 160

144. Skin-stringer vibration PSD, radial, transonic, 3.06 lb/ft2 ..................................... 161

145. Skin-stringer vibration PSD, longitudinal, liftoff, 3.06 lb/ft .................................. 162
xi

LIST OF FIGURES (Continued)

146. Skin-stringer vibration PSD, tangential, liftoff, 3.06 lb/ft2 .................................... 163

147. Titan III acoustic spectrum, compartment 2C, liftoff ........................................... 164

148. Titan III acoustic spectrum, compartment 2C, Mach 1/Max Q ............................ 165

149. Compartment 1A measurement locations ............................................................ 166

150. Skin-stringer vibration PSD, radial, Mach 1, 4.52 lb/ft2 ....................................... 167

151. Skin-stringer vibration PSD, radial, liftoff, 4.67 lb/ft2 .......................................... 168

152. Skin-stringer vibration PSD, radial, transonic, 4.67 lb/ft2 ..................................... 169

153. Skin-stringer vibration PSD, tangential, liftoff, 4.67 lb/ft2 .................................... 170

154. Vibration measurements 2610 and 2611, compartment 1A, station 508 ................ 171

155. Vibration measurements 2526 and 2527, compartment 1A, station 508 ................ 172

156. Skin-stringer vibration PSD, longitudinal, liftoff, 4.67 lb/ft2 ................................ 173

157. Skin-stringer vibration PSD, radial, liftoff, 4.67 lb/ft2 .......................................... 174

158. Titan III acoustic spectrum, compartment 1A, liftoff .......................................... 175

159. Titan III acoustic spectrum, compartment 1A, Mach 1 ........................................ 176

160. Titan III acoustic spectrum, compartment 1A, Max Q ......................................... 177

161. Compartment 1C measurement locations ............................................................. 178

162. Compartment 1C acoustic measurement, station 1219 ......................................... 179

163. Vibration measurements 2540 and 2541, compartment 1C, station 1214 .............. 180

164. Skin-stringer vibration PSD, longitudinal, liftoff, 8.4 lb/ft2 .................................. 181

165. Skin-stringer vibration PSD, radial, liftoff, 8.4 lb/ft2 ............................................ 182

166. Skin-stringer vibration PSD, radial, liftoff, 12.08 lb/ft2 ......................................... 183
xii

LIST OF FIGURES (Continued)

167. Skin-stringer vibration PSD, radial, transonic, 12.08 lb/ft2 ................................... 184

168. Skin-stringer vibration PSD, tangential, liftoff, 12.08 lb/ft2 .................................. 185

169. Skin-stringer vibration PSD, longitudinal, liftoff, 27.9 lb/ft2 ................................ 186

170. Skin-stringer vibration PSD, radial, liftoff, 27.9 lb/ft2 .......................................... 187

171. Skin-stringer vibration PSD, radial, transonic, 27.9 lb/ft2 ..................................... 188

172. Titan III acoustic spectrum, compartment 1C, liftoff ........................................... 189

173. Titan III acoustic spectrum, compartment 1C, Mach 1 ........................................ 190
xiii

LIST OF TABLES

1. Tolerance factors for various probability levels .......................................................... 7

2. Saturn V flight accelerometer data ............................................................................. 10

3. Titan III flight accelerometer data .............................................................................. 12

4. Titan III acoustic measurements ................................................................................ 13

5. Structural parameters ................................................................................................. 19
xiv

LIST OF ACRONYMNS

BW bandwidth

dB decibels

MARL Mobile Acoustic Research Laboratory

Max Q maximum dynamic pressure

MEFL Maximum Expected Flight Level

MSFC Marshall Space Flight Center

OASPL overall sound pressure level

P/L payload

PL Probability Level

PSD Power Spectral Density

psi pounds (force) per square inch

rms root-mean-square

SRB Solid Rocket Booster

Sta. station

TM Technical Memorandum
xv

NOMENCLATURE

f frequency of vibration, Hz

fi the ith center frequency, Hz

g acceleration due to cyclic motion divided by the acceleration of gravity

g2/Hz acceleration power spectral density of vibration structure (in terms 

of acceleration)

Gi(97.5% PL) 97.5% probability level of Gi(f) corrected for nonstandard 

normal distribution

GL(f ) normalized acceleration power spectral density as a function 

of frequency, g2/Hz

GM(f ) measured acceleration power spectral density as a function 

of frequency, g2/Hz

GN(f ) new vehicle acceleration power spectral density as a function 

of frequency, g2/Hz

GR(f ) data bank acceleration power spectral density as a function 

of frequency, g2/Hz

Ki(97.5%) factor for positively skewed function

MN mass per unit area of the new vehicle’s structure

MR mass per unit area of the data bank structure

N number of gi(f) or acceleration power spectral density spectra 

PL(f ) reference acoustic pressure as a function of frequency, psirms

PM(f ) measured acoustic pressure as a function of frequency, psirms

PN(f ) new vehicle measured or predicted acoustic pressure as a function 

of frequency, psirms
xvi

NOMENCLATURE (Continued)

PR(f ) reference acoustic pressure as a function of frequency, psirms

Si skewness, a measure of how symmetrical a distribution is with respect 

to the mean

Xi the mean or average of all values

Xi the ith input value, g2/Hz or g/10 Hz bandwidth

σi standard deviation or measure of dispersion of data points around their 

mean value

σi

2 variance or square of the standard deviation
1

TECHNICAL MEMORANDUM

USING THE SATURN V AND TITAN III VIBROACOUSTIC DATABANKS 

FOR RANDOM VIBRATION CRITERIA DEVELOPMENT

1. INTRODUCTION

This is an update to TN D–7159, “Development and Application of Vibroacoustic Structural Data Banks in Predicting Vibration Design and Test Criteria for Rocket Vehicle Structures,” 

which was originally published in 1973.1 There was an error in the processing of the data in the 

original report that has been corrected in this version. Originally, the data were normalized before 

statistics were calculated, which tended to introduce errors into the finished product. The original 

Saturn data2,3 were reprocessed and this time the normalization was done after statistics were calculated. The revised process is described in section 2 of this document.

This study presents a comprehensive and accurate semi-empirical method of predicting 

the acoustically induced broadband random vibration criteria for component installations located 

on space vehicles. Vibroacoustic structural databanks were developed from the more than 1285 

vibration and acoustic measurements taken on static firings and flights of the Saturn and Titan III 

vehicles and from the Mobile Acoustic Research Laboratory (MARL) testing program.

The MARL was a 12.19 m (40 ft) platform on wheels. Various large flight and development structures, such as instrument units, skirts, and interstages, were installed on the MARL and 

located in the acoustic near- and mid-fields and subjected to static firings of the various Saturn 

stages and engines at Marshall Space Flight Center (MSFC) and the Mississippi Test Facility. The 

MARL test structures were instrumented and vibration and acoustic data were recorded during the 

static firings.

A vibroacoustic structural databank is a statistical compilation of vibration and acoustic 

data, which are categorized according to definite structural configurations, such as skin stringer, 

ring frame, and honeycomb. Simply stated, a vibroacoustic databank indicates the vibration level 

for a given sound pressure level acting on a particular structural configuration.

An extensive examination of structural drawings for the Saturn vehicles and MARL test 

structures was made to define the structural parameters for the various databanks. The structural 

categories studied were ring frames, skin stringer, and honeycomb.

Vibration and acoustic data obtained during static firings and flights of the vehicles, as well 

as MARL data, were recorded on data summarization sheets. Information, such as data validity, 
2

slice time, and other elucidative information necessary for development of the databanks, is contained on these sheets.

For a particular databank, each of the vibration spectra with its associated acoustic spectrum was normalized to the reference acoustic spectrum shown on figure 1. The reference acoustic 

spectrum has no special meaning other than that it is a typical Saturn V liftoff acoustic spectrum. 

All vibration spectra were categorized according to structural zone, flight condition, and measurement direction; then, they were statistically analyzed to determine the mean and the 97.5% probability level spectra. The databanks were developed for both the liftoff and transonic environments, 

which consider the differences in the spatial correlation of the random acoustic pressure fields.

150

145

140

135

130

125

120

10 100 1,000

Frequency (Hz)

1/3 Octave Band Sound Pressure Level in dBRE 2 

× 10–5 Newton Meter2

Figure 1. Reference acoustic spectrum.

In utilizing these databanks for determining vibration criteria for a new vehicle structure, 

the databank that is closest to the new vehicle structural configuration is selected. The proper mass 

and sound pressure level adjustments are made to determine the vibration criteria for the unloaded 

new vehicle structure. Component vibration criteria for varying weight ranges are then determined 

from conventional mass attenuation techniques.
3

2. VIBROACOUSTIC STRUCTURAL DATABANKS

2.1 Structural Characteristics

The Saturn and Titan launch vehicles have a complex structural definition consisting of ring 

frames, skin stringers, tanks, structural beams, etc. This Technical Memorandum (TM) is concerned with those structures that respond to acoustic and aerodynamic forcing functions. Therefore, vibroacoustic databanks were developed only for those categories falling under the structural 

definition of ring frame, skin stringer, and honeycomb panels.

• Ring frame: This type of structure is not directly susceptible to acoustic forcing functions, but 

receives motion from adjacent panels.

• Skin stringer: This type of structure responds to acoustic forcing functions. The stiffener 

(stringer) response depends directly on the motion of the skin.

• Honeycomb: This type of structure is directly excited by acoustic forcing functions. The Saturn 

stages and MARL test structures were structurally defined by reviewing a large number of structural assembly drawings. 

Physical dimensions, such as skin thickness, ring frame dimensions, stringer dimensions, 

honeycomb core density, and other pertinent structural definitions, were assembled into structural 

configuration books. These books represent an exhaustive accumulation of structural information 

that was invaluable in defining the vibroacoustic structural databank categories. The structural 

information along with the locations of the vibration and acoustic measurements were recorded 

on data summarization sheets. These data sheets were used to develop the vibroacoustic structural 

databanks. 

2.2 Vibration and Acoustic Data

Vibration and acoustic data from static firings and flights of the Saturn and Titan launch 

vehicles and from MARL were assembled and categorized. Using the measurement location structural description, the data were divided into the three structural categories described in section 2.1. 

Each measurement number with the measurement direction, measurement location, zone number, 

data sequence number, slice time, test number, frequency range, data validity, and flight condition 

(liftoff, Mach 1, and Max Q) were listed on the data summarization sheets. Both valid and invalid 

data were listed to maintain a permanent record of all the data obtained from static firings and 

flights of the launch vehicles and MARL tests. All valid vibration and acoustic measurements 

located on ring frame, skin stringer, or honeycomb structure were utilized in the vibroacoustic databanks with the exception of measurements located on component loaded structures. Component 

loaded structures were not considered in this study for the simple reason that any small change in 
4

the load would change the response of the structure. Measurements located on engines, fuel lines, 

brackets, loaded panels, and beams were not used to derive the vibroacoustic databanks in this 

report. However, the vibration measurements in each structural category were evaluated individually to determine if they actually represented a ring frame, skin stringer, or honeycomb response. 

This close evaluation was necessary since some vibration measurements were located on the skin 

near a ring and could be more representative of a ring frame response, rather than a skin-stringer 

response. The acoustic measurements were also summarized according to source variations, such 

as static firing, liftoff, and transonic flight. Other pertinent information similar to that recorded for 

the vibration measurement locations was also recorded for each acoustic measurement. The vibration data for numerous flight vehicle and static test locations have varied acoustic forcing functions. 

Each of the vibration spectra with its associated acoustic spectrum was normalized to a reference 

acoustic spectrum.

2.3 Statistical Analysis

Vibration and acoustic data from data retention at MSFC were retrieved from the storage 

tapes and assembled into vibroacoustic databanks for statistical analysis. A mean and 97.5% probability level spectra are derived for each structural category specified by the structural characteristics 

in section 2.1. The specific structural categories are divided into individual subdivisions depending 

on dimensional variations of the ring frames, skin stringer, and honeycomb panels. Each group or 

vibroacoustic databank consists of N spectral density spectra, each composed of 398 input values, 

covering the range from 20 to 2000 Hz in 5-Hz increments.

These 398 input values of Xi (power spectral density, g2/Hz) for each spectrum were defined 

at center frequencies of fi (Hz). The mean value Xi is the average of all values. In equation form, 

the mean is as follows:

Χ i i

i

= X

=

∑ 1

1 N

N

. (1)

The mean square value is the average of the squared values. The variance is the mean 

squared value about the mean. In equation form, the variance is the following:

σ i i i

i

X X 2 2

1

1

1 = −

=

∑ N

N

− ( ) . (2)

The standard deviation is the positive square root of the variance. The standard deviation is 

as follows:

σ i

i i

i

X X = − 













 =

∑ ( ) .

2

1

1

2

N 1

N

− (3)
5

To determine the probability level, it is necessary to determine the skewness. Most statistical distributions are not symmetrical with respect to their mean and are therefore classified to be 

skewed. In equation form, the skewness is as follows:

S

N N

N

X X

N

X X

N

i

i i

i

N

i i

i

= ( ) 

 

−

−

=

=

∑ −

−

1

2

1

2

3

1

2

( )

( )

1

3

N

∑





















. (4)

For a collection of data samples, the probability level in reference 4 can be used to determine Gi

 (97.5% PL):

G X i i i i ( ) 97. %5 PL = + Κ σ , (5)

where:

Gi(97.5% PL) = 97.5 percentile probability level in the ith frequency increment.

Xi = mean of the data samples in the ith frequency increment.

	 σi = the standard deviation of the data samples in the ith frequency increment.

Ki = the K factor of the ith frequency increment.

The effects on the Ki factor of higher moments are ignored. For a positively skewed function, the factor Ki

 can be found from 

Ki(97.5) = 1.96 exp (0.2055 Si – 0.0155 Si

2) , (6)

where Si is the skewness as defined by

S

N N

N

X X

N

X X

N

i

i i

i

N

i i

i

= ( ) 

 

−

−

=

=

∑ −

−

1

2

1

2

3

1

2

( )

( )

1

3

N

∑





















. (7)

The vibroacoustic databank normalized vibration data samples were statistically analyzed 

using the above equations. The results of this analysis are plots of the 97.5% probability level 

power spectral density (g2/Hz) versus frequency from 20 to 2000 Hz. The 97.5% probability level 

composites were also calculated and are presented with the individual vibroacoustic databank 

parametric listings. The composite values were calculated by the following:
6

g g f

i

i

rms BW Hz = ( ) =

∑ 1 2

1

398

, (8)

where BW is equal to 5 Hz.

An alternative to the above procedure is to assume that the measured data is log–normally

distributed, which presumes that the logarithms of the data points fit a normal distribution. 

Equation 5 can be used to calculate the 97.5 % PL using the Ki factors in table 1. For comparison, 

95% PL levels are shown. The equation used to derive these numbers is:5

K p

Z f Z f f

Z

n p p

,γ

γ

( ) =

( ) − ( ) − − − ( ) −

( ) −





1 1 1

2 1

2 2 2

2

+ 









 −





































( ) − −

Z

Z

n

f

Z

p

2

2

1

2

2 1

γ

γ

2

2 1 ( ) n −

 . (9)

where:

p = desired probability level with γ confidence.

f = 1

4 1 ( ) n − .

Zp = Prob(Z ≤ Zp) from standard tables, e.g., Zp = 1.96 for 97.5% PL.

Zγ = Prob(Z ≤ Zγ) from standard tables, e.g., Zγ = 0 for 50% confidence.

n = number of samples.
7

Table 1. Tolerance factors for various probability levels.

n

95%PL, 

50% Confidence

K–Factor

97.5%PL,

50% Confidence

K–Factor

2

3

4

5

6

7

8

9

10

11

12

13

14

15

20

25

30

40

50

60

70

100

∞

2.193

1.880

1.794

1.755

1.731

1.716

1.706

1.698

1.692

1.687

1.683

1.680

1.677

1.675

1.667

1.662

1.659

1.655

1.653

1.652

1.651

1.649

1.645

2.613

2.240

2.138

2.091

2.063

2.045

2.033

2.023

2.016

2.010

2.006

2.002

1.998

1.996

1.986

1.981

1.977

1.973

1.970

1.968

1.967

1.965

1.960

2.4 Normalization Method

To generate the vibroacoustic databanks, it is necessary to make all measured data compatible. Compatibility is achieved by normalizing all the measured vibration spectra and their acoustic 

spectra to the common acoustic forcing function shown in figure 1. After normalization, the only 

acoustic spectra needed to scale the acceleration are the reference and new spectra. The reference 

acoustic spectrum has no special meaning other than that it is a typical Saturn liftoff acoustic spectrum.

The normalization was performed by the following equation:

G f G f P f

P f L M

L

M

( ) = ( ) ( )

( )

















2

, (10)

where

GL(f) = Normalized power spectral density (g2/Hz) as a function of frequency f.

PL(f) = Reference acoustic pressure (psirms) as a function of frequency f.

GM(f) = Measured power spectral density (g2/Hz) as a function of frequency f.

PM(f) = Measured acoustic pressure (psirms) as a function of frequency f.
8

* This is the difference with the original publication. In reference 1, statistics were calculated after 

normalization, which affected the calculated standard deviation, and, ultimately, the 97.5% PL.

Statistics were calculated (mean and 97.5% PL) for all vibration spectra before they were 

normalized.* The output of the normalization program is power spectral density plots normalized 

to the reference acoustic spectrum. These individual plots are given a normalized vibration measurement number for identification and assembled into structural categories.
9

3. SATURN V AND TITAN III FLIGHT DATABANKS

Excel® spreadsheets containing all of these data are available upon request from the author.

3.1 Saturn V Databank

The Saturn V vibroacoustic databanks summarized in appendix A have been arranged 

into vehicle diameter categories of 6.71 m (22 ft) and 10.06 m (33 ft). Individual ring frame, skin 

stringer, and honeycomb structural categories are defined under each vehicle diameter. Each structural category is subdivided into longitudinal, radial, and tangential directions and into subdivisions based on structural dimensions. The databanks are further subdivided into conditions of 

static firing, liftoff, Mach 1, and maximum dynamic pressure. A condition representing combined 

conditions of liftoff and static firing was developed. Also, a transonic condition representing the 

combined conditions of Mach 1 and maximum dynamic pressure was developed. Each vibration 

measurement is presented with the 97.5% probability level acoustic measurement in the measurement zone. All acoustic spectra are shown in 1/3-octave band decibels. Structural characteristics, 

which came from reference 1, are summarized in table 2.

3.2 Honeycomb Databank

One honeycomb vibroacoustic databank was developed from the available vibration and 

acoustic data. The honeycomb databank consists of a parametric listing and power spectral density 

of the 97.5% probability levels. Appendix A, figure 133 shows the honeycomb databank.

3.3 Titan III Databank

The Titan III databanks in appendix B were compiled from data in reference 6 and have 

been arranged from lightest to heaviest surface density. Adding the weights of the skin, stringer, 

and ring frames and dividing by an area that includes at least two rings and stringers was used to 

calculate surface density. These databanks were compiled from data contained in reference 6. Structural characteristics are summarized in table 3 and a list of acoustic spectra is shown in table 4.

Caution should be applied when using the Titan databanks because individual spectra for 

each flight were often not available. Consequently, 97.5% probability levels were supplied in the 

reference documentation rather than the individual measurements, so the normalization was not 

done on each spectrum as in the Saturn V databank. Therefore, it is difficult to show that a vibration spectrum was the result of a particular acoustic spectrum; instead the vibration statistics are a 

result of acoustic statistics.
10Table 2. Saturn V flight accelerometer data.

Page

Source 

(Ref. 1) Type Meas. Dir.

Flight 

Condition

Skin 

Thickness 

(in)

Vehicle 

Diameter 

(ft)

Ring Wt. 

(lb/ft)

Stringer 

Wt. (lb/ft)

Surface 

Wt.(lb/ft2)

Composite 

(grms)

Source 

Meas.

29 A1 Ring Fr. Long Liftoff 0.032 22 0.95 0.47 2.0 3.18 E93–411

E96–411 31 A3 Ring Fr. Long Mach 1 0.032 22 0.95 0.47 2.0 13.84

33 A5 Ring Fr. Long Max Q 0.032 22 0.95 0.47 2.0 11.3235 A7 Ring Fr. Long Mach 1/Max Q 0.032 22 0.95 0.47 2.0 13.4137 A9 Ring Fr. Tangent Liftoff 0.032 22 0.95 0.47 2.0 3.69 E95–411

E98–411 38 A11 Ring Fr. Tangent Mach 1 0.032 22 0.95 0.47 2.0 26.17

39 A13 Ring Fr. Tangent Max Q 0.032 22 0.95 0.47 2.0 22.7240 A15 Ring Fr. Tangent Mach 1/Max Q 0.032 22 0.95 0.47 2.0 25.8041 A17 Ring Fr. Radial Liftoff 0.032 22 0.95 0.47 2.0 10.25 E94–411

E97–411 42 A19 Ring Fr. Radial Mach 1 0.032 22 0.95 0.47 2.0 34.06

43 A21 Ring Fr. Radial Max Q 0.032 22 0.95 0.47 2.0 45.2544 A23 Ring Fr. Radial Mach 1/Max Q 0.032 22 0.95 0.47 2.0 34.3347 A25–1 Ring Fr. Long Liftoff 0.040 33 2.51 0.71 3.3 12.71 E88–21949 A25–2 Ring Fr. Long Mach 1 0.040 33 2.51 0.71 3.3 12.1551 A25 Ring Fr. Radial Liftoff 0.040 33 2.51 0.71 3.3 15.25 E87–21952 A27 Ring Fr. Radial Mach 1 0.040 33 2.51 0.71 3.3 14.5857 A29 Ring Fr. Radial Liftoff 0.04–0.07 33 1.09–1.49 0.71–1.0 1.1–1.5 42.13 E79–86–219

E344–200 58 A31 Ring Fr. Radial Mach 1 0.04–0.07 33 1.09–1.49 0.71–1.0 1.1–1.5 9.46

59 A33 Ring Fr. Radial Max Q 0.04–0.07 33 1.09–1.49 0.71–1.0 1.1–1.5 13.3361 A35 Ring Fr. Radial Mach 1/Max Q 0.04–0.07 33 1.09–1.49 0.71–1.0 1.1–1.5 5.8164 A37 Ring Fr. Radial STATIC 0.100 33 5.53 1.00 9.2 16.37 E19–12068 A39 Ring Fr. Parallel STATIC 0.08–0.13 25.2 4.67–7.95 1.04 4.7–8.0 0.61 WE229–20670 A41 Ring Fr. Normal STATIC 0.130 17.5 11.39 1.04 13.9 2.03 WE181–20673 A43 Ring Fr. Long Liftoff 0.185 33 4.75 N/A 6.2 5.10 E20–11875 A45 Ring Fr. Long Mach 1 0.185 33 4.75 N/A 6.2 17.3477 A47 Ring Fr. Long Max Q 0.185 33 4.75 N/A 6.2 26.3179 A49 Ring Fr. Long Mach 1/Max Q 0.185 33 4.75 N/A 6.2 28.39
11

Table 2. Saturn V flight accelerometer data (Continued).

Page

Source 

(Ref. 1) Type Meas. Dir.

Flight 

Condition

Skin 

Thickness 

(in)

Vehicle 

Diameter 

(ft)

Ring Wt. 

(lb/ft)

Stringer 

Wt. (lb/ft)

Surface 

Wt.(lb/ft2)

Composite 

(grms)

Source 

Meas.

81 A51 Ring Fr. Radial Liftoff 0.185 33 4.75 N/A 6.2 24.75 E21–11882 A53 Ring Fr. Radial Mach 1 0.185 33 4.75 N/A 6.2 25.0783 A55 Ring Fr. Radial Max Q 0.185 33 4.75 N/A 6.2 32.2784 A57 Ring Fr. Radial Mach 1/Max Q 0.185 33 4.75 N/A 6.2 32.2888 A73 Ring Fr. Long Liftoff 0.375 33 29.06 1.95 25.6 13.87 E23–11590 A65 Ring Fr. Long Mach 1 0.375 33 29.06 1.95 25.6 18.9492 A69 Ring Fr. Long Mach 1/Max Q 0.375 33 29.06 1.95 25.6 10.6094 A75 Ring Fr. Radial Liftoff 0.375 33 29.06 1.95 25.6 3.55 E24–11595 A77 Ring Fr. Radial Mach 1 0.375 33 29.06 1.95 25.6 12.1096 A79 Ring Fr. Radial Max Q 0.375 33 29.06 1.95 25.6 8.4598 A81 Ring Fr. Radial Mach 1/Max Q 0.375 33 29.06 1.95 25.6 6.75100 A87 Skin/Str. Normal Liftoff 0.040 33 N/A 1.41 3.3 21.87102 A89 Skin/Str. Long Liftoff 0.040 33 N/A 0.71 1.5 1.42 E326–219104 A91 Skin/Str. Long Mach 1 0.040 33 N/A 0.71 1.5 2.18 E329–219106 A93 Skin/Str. Long Max Q 0.040 33 N/A 0.71 1.5 1.91 E326–219108 A95 Skin/Str. Long Mach 1/Max Q 0.040 33 N/A 0.71 1.5 4.41110 A97 Skin/Str. Tangent Liftoff 0.040 33 N/A 0.71 1.5 2.09 E327–219

E329–219

111 A99 Skin/Str. Tangent Mach 1 0.040 33 N/A 0.71 1.5 4.63 E327–219112 A101 Skin/Str. Tangent Max Q 0.040 33 N/A 0.71 1.5 4.19113 A103 Skin/Str. Tangent Mach 1/Max Q 0.040 33 N/A 0.71 1.5 8.11114 A105 Skin/Str. Radial Liftoff 0.040 33 N/A 0.71 1.5 6.03 E325–219115 A107 Skin/Str. Radial Mach 1 0.040 33 N/A 0.71 1.5 4.25121 A109 Skin/Str. Long STATIC 0.071 33 N/A 0.86 2.8 9.03 WE146–206123 A111 Skin/Str. Radial Mach 1 0.071 33 N/A 0.86 2.8 56.49

E351–206 125 A113 Skin/Str. Radial Max Q 0.071 33 N/A 0.86 2.8 90.88

127 A115 Skin/Str. Radial Mach 1/Max Q 0.071 33 N/A 0.86 2.8 67.06129 A117 Skin/Str. Radial STATIC 0.071 33 N/A 0.86 2.8 39.77 E75–206

WE240–206E76–206WE239–206WE148–206

130 A119 Honeycomb Radial STATIC 0.030 22 N/A N/A 3.1 67.60
12Table 3. Titan III flight accelerometer data.

Page

Source 

(Ref. 6) Type

Meas.

Dir.

Flight 

Condition Mat’l

Skin 

Thickness 

(in)

Ring Wt. 

(lb/ft)

Stringer Wt. 

(lb/ft)

Surface Wt. 

(lb/ft2)

Composite 

(grms) Source Meas.

136 A192 P/L Truss Long Mach 1/Max Q 7178 AL 0.028 1.48 2.38 2.28 12.35 2727137 A193 P/L Truss Radial Mach 1/Max Q 7178 AL 0.028 1.48 2.38 2.28 14.04 2728138 A182 Ring Fr. Long Liftoff 7075 AL 0.028 1.48 0.24 2.49 6.94 2718/2721139 A190 Ring Fr. Long Mach 1 7075 AL 0.028 1.48 0.24 2.49 4.96 2718/2721140 A183 Ring Fr. Radial Liftoff 7075 AL 0.028 1.48 0.24 2.49 4.25 2719/2722141 A191 Ring Fr. Radial Mach 1 7075 AL 0.028 1.48 0.24 2.49 4.95 2719/2722142 A142 Skin/Str. Long Liftoff 2014 AL 0.028 0.84 0.38 2.49 4.92 2551/2563/2702143 A147 Skin/Str. Long Mach 1 2014 AL 0.028 0.84 0.38 2.49 11.85 2551/2653/2702144 A180 Skin/Str. Radial Liftoff 2014 AL 0.028 0.84 0.376 2.49 8.79 2552/2703/2654145 A149 Skin/Str. Radial Mach 1 2014 AL 0.028 0.84 0.38 2.49 23.26 2552/2703/2654151 A127 Skin/Str. Radial Liftoff 7075 AL 0.04 0.32–0.77 0.85 2.70 6.83 2519152 A128 Skin/Str. Tangent Liftoff 7075 AL 0.04 0.32–0.77 0.85 2.70 9.32 2530153 A129 Skin/Str. Tangent Mach 1 7075 AL 0.04 0.32–0.77 0.85 2.70 14.88 2530159 A104 Skin/Str. Radial Liftoff AL 0.04 0.55–0.65 0.86 3.06 9.95 2567/2603160 A106 Skin/Str. Radial Mach 1/Max Q AL 0.04 0.55–0.65 0.86 3.06 23.16 2566/2602/2603161 A109 Skin/Str. Radial Transonic AL 0.04 0.55–0.65 0.86 3.06 23.43 2567/2367162 A107 Skin/Str. Long Liftoff AL 0.04 0.55–0.65 0.86 3.06 3.42 2602/2566163 A108 Skin/Str. Tangent Liftoff AL 0.04 0.55–0.65 0.86 3.06 3.06 2604167 A88 Skin/Str. Radial Mach 1 7075 AL 0.241 1.8 1.06 4.52 26.40 2723168 A81 Skin/Str. Radial Liftoff 7075 AL 0.04 0.86–1.18 1.06 4.67 18.02 2527169 A83 Skin/Str. Radial Transonic 7075 AL 0.04 0.86–1.18 1.06 4.67 63.94 2527170 A90 Skin/Str. Tangent Liftoff 7075 AL 0.04 1.18 1.06 4.67 7.04 2612173 A79 Skin/Str. Long Liftoff 7075 AL 0.04 0.86–1.18 1.06 4.67 23.09 2610/2526174 A77 Skin/Str. Radial Liftoff 7075 AL 0.04 1.18 1.06 4.67 15.18 2611/2608/2723181 A40 Skin/Str. Long Liftoff 2014 AL 0.25 3.9–4.21 0.73 8.40 8.72 2540182 A49 Skin/Str. Radial Liftoff 2014 AL 0.07 3.9–4.21 0.84 8.40 23.02 2623183 A51 Skin/Str. Radial Liftoff 2014 AL 0.25 3.9–4.21 0.73 12.08 19.20 2541184 A50 Skin/Str. Radial Transonic 2014 AL 0.1 3.9–4.21 0.84 12.08 8.16 2623185 A51–2 Skin/Str. Tangent Liftoff 2014 AL 0.1 3.9–4.21 0.84 12.08 11.50186 A47 Skin/Str. Long Liftoff 7079 AL 0.07 4.21 0.84 27.9 19.77 2572187 A38 Skin/Str. Radial Liftoff 7079 AL 0.07 4.2 0.84 27.9 8.90 2573188 A48 Skin/Str. Radial Transonic 7079 AL 0.07 4.21 0.84 27.9 5.08 2573
13

Table 4. Titan III acoustic measurements.

Compartment Meas. ID Station Flight Condition Page

3A 2574

2628

124

124

Liftoff

Mach 1

Max Q

146

147

148

2B 2629

2724

380

380

Liftoff

Mach 1/Max Q

154

155

2C 2725 450 Liftoff

Mach 1/Max Q

164

165

1A 2630

2575

2726

567

567

559

Liftoff

Max Q

Mach 1

175

176

177

1C 2576

2631

1219

1219

Liftoff

Mach 1

189

190
14

4. APPLICATION OF VIBROACOUSTIC DATABANKS

4.1 Utilization of Vibroacoustic Databanks

The vibroacoustic databanks presented have been defined for vehicle diameter, flight conditions, static firings, and various parametric categories. The following procedures should be followed 

to determine vibration criteria for a new vehicle structure:

(1) Select a databank from the appendices that best represents the new vehicle local structural 

configuration. Tables 2 and 3 provide the databank structural parameters for making this selection. Liftoff and static firing acoustic spectra produce different vibration responses than the ascent 

spectra because the correlation for ascent is less efficient than the more reverberant field produced 

at liftoff. Be sure to use the correct conditions. It is prudent to select more than one databank spectrum to scale because that tends to average the structural differences between the reference and new 

vehicles and leads to a more representative sample.

(2) A ‘back–up area’ is chosen and the weight is smeared over that area to calculate the surface 

weight. Using a width of more than three times the ring separation is not advisable because aspect 

ratio then becomes important. When using the ring-frame data the length and width of the back-up

area is usually equal to the ring separation distance.

(3) When the most representative databank is selected, make necessary mass and acoustic 

pressure adjustments according to equation (11) to determine vibration criteria for unloaded new 

vehicle structure:

G f G f P f

P f

M

M N R

N

R

R

N

( ) ( ) ( )

( ) = , 































2

(11)

where:

GN(f ) = New vehicle power spectral density (g2/Hz) as a function of frequency f.

GR(f ) = Databank power spectral density (g2/Hz) as a function of frequency f.

PN(f ) = New vehicle measured or predicted acoustic pressure (psirms) as a function 

of frequency f.

PR(f ) = Reference acoustic pressure (psirms) as a function of frequency f.

MN = Mass per unit area of new structure.

MR = Mass per unit area of databank structure.

Dimensionally, the mass term should be squared; however, experience has shown that the 

measured data are better fit by not squaring the term. Alternatively, equation (11) can be re-written 

as follows:
15

G f G f

dB f dB f M

M N R

N R R

N

( ) ( ) ( ) ( ) =  −



















10 

10 









, (12)

where dB(f) are the reference and new acoustic spectra in decibels.

This technique assumes that structures respond linearly with acoustic amplitude. That 

assumption can only be carried so far since eventually the structure will hit its elastic limit and 

become non-linear. Extrapolation upward beyond 6–10 dB should be done with caution and 

backed up with test data. Scaling downward to lower levels can be done over a greater range, 

although the results will be conservative.

4.2 Component Weight and Frequency Scaling

If a heavy component is to be mounted to the scaled structure, equation (11) can be modified by the addition of a component mass scaling factor, resulting in the following7:

G f G f P f

P f

M

M

W

N R

N

R

R

N

( ) ( ) ( )

( ) = 































2

R

W W R C +

















 , (13)

where

WR = Weight of the reference structure backup area.

WC = Weight of the component.

Again, the weight term should be squared for dimensional accuracy, but the data support 

using the equation as written. When calculating criteria for various component weight ranges, use 

the lightest component weight in the range in equation 13 for conservatism. 

For predictions on cylindrical space vehicle structure, letting fR and fN denote the values 

along the frequency axes for the spectra of the high frequency vibration responses on the reference 

and new vehicle, respectively, the frequency axis of the spectrum is shifted for diameter from the 

reference to the new vehicle by

f

D

D f N

R

N

R , (14)

where DR and DN are the diameters for the reference and new vehicle, respectively. Above the fundamental ring frequency, the local structural characteristics predominate, and frequency shifting 

is not necessary.8 
16

4.3 Components Mounted to Rocket Engines

Although this document is concerned with acoustically induced vibration, reference 7 contains some excellent guidelines for developing vibration criteria for engine-mounted components. 

Scaling is based on relative thrust and exhaust velocity for similar engines.
17

5. TEST CRITERIA DEVELOPMENT

Test criteria specify how a component is tested in order to qualify it for flight. In general, 

the amplitudes of the vibration test criteria are the same as the environments, since they also represent the maximum environment. However, for simplicity, the criteria may represent an envelope 

of the maximum environment for several flight regimes. In presenting the criteria, the space vehicle 

and payload are divided into major structural zones, such as aft skirt, forward skirt, nose cone, 

payload rack, etc. Each of these major zones is further divided into subzones based on local structural configuration, such as ring frames, stringers, coldplates, etc. The subzones are further broken 

down based on component weight ranges and component population. In special cases, random 

vibration criteria are formulated for specific components. Since the criteria are used for design and 

testing of space vehicle components and experiments, they also include the time the environment is 

present.

5.1 Test Duration

Equivalent damage time is the time required to induce an amount of damage at a high test 

level equivalent to that induced by exposure to a varying stress level. Acoustically induced random 

vibration on launch vehicles is a non-stationary environment, i.e., its root-mean-square amplitude 

changes fairly rapidly over its duration. Figure 2 shows a typical acoustic time history for the Space 

Shuttle Solid Rocket Booster (SRB).

–10 40 90 140 190 240 290 340 390

170

165

160

155

150

145

140

135

130

OASPL (dB)

Time (s)

Liftoff Boost Reentry

Figure 2. Typical Space Shuttle solid rocket booster mission profile.

Space Shuttle SRB and External Tank random vibration criteria were derived for each flight 

regime: liftoff, boost, and reentry. The spectra and test durations are specified for each time frame. 

The spectra are based on the peak acceleration during the particular flight phase, and the test 
18

duration is calculated to produce the same amount of fatigue damage as seen during the entire 

flight phase. The profile shown above can be an aggregate of several flights, or profiles can be normalized to the maximum values and averaged. Another technique is simply to calculate the equivalent fatigue times for several measurements over different flights and use the maximum value.

The equivalent damage time is based on Miner’s rule:

W W

T

T

n

b

2 1

1

2

= 













 , (15)

where:

b = measure of slope of stress-cycles-to-failure (S–N) curve (as shown in figure 3). 

The value of b is in the range 3 to 25. However, a value of 9 is representative 

of many structural materials.9

n = damping-stress exponent. For viscoelastic damping n = 2. For low to intermediate 

stresses in elastic-plastic materials n = 2.4, and for high stresses n = 8.9

T1, W1 = duration and overall rms level of random vibration test 1.

T2, W2 = duration and overall rms level of random vibration test 2.

Note: When comparing individual PSD values of two spectra, divide n/b by 2.

100

10

b = slope

1×103 1×104 1×105 1×106 1×107

Stress, S, in KSI

Cycles (N)

Figure 3. S–N curve for aluminum.

Rearranging terms in equation (15) and summing over N cycles results in the following equation:
19

T T

W

W eq i

i

N

i

b

n

= 













 =

∑

1 max

, (16)

where

Wmax = maximum level during time period.

Teq = equivalent damage time at level Wmax.

Ti = time at level Wi .

Typical values of b/n are from four (for solder joints) to five (for aluminum structures).9

W can represent any dynamic profile, such as sound pressure level (fig. 2), dynamic pressure, 

or sinusoidal acceleration. When using equation (15) for test time equivalence, use the minimum 

difference between the individual PSD values of the two spectra, then calculate the time equivalence using the overall rms values. The equivalent time should be the minimum of the two results. 

The Space Shuttle program required that qualification duration should be four times the 

expected duration, which resulted in the following test durations for SRB hardware. A factor of 

two times the expected duration is put on the first test so that an article tested for only one flight 

gets plenty of margin. For liftoff this factor was increased to 50 s so that all items saw at least 60 s 

of vibration test.

Liftoff: Teq = 2.5 s, flight duration = 10 s/mission. Total test time 50 s, plus 10 s per mission.

Boost: Teq = 10 s, flight duration = 40 s/mission. Total test time 80 s, plus 40 s per mission.

Reentry: Teq = 7.5 s, flight duration = 30 s/mission. Total test time 60 s, plus 30 s per mission.

5.2 Test Amplitude

After the proper scaling techniques have been applied, test criteria are derived by enveloping 

the scaled data. There is considerable latitude allowed in the enveloping technique; in fact, if five 

people are given the same data to envelope, they will probably produce six different envelopes. 

In this example, Saturn V databank A75 was scaled to the Space Shuttle SRB forward skirt 

structural characteristics and acoustic environment. The following scale parameters were used:

Table 5. Structural parameters.

New Structure Reference Structure

Skin Thickness

Vehicle Diameter

Ring weight

Surface weight

Total weight (four square ft)

0.54 in.

12 ft.

9.1 lb/ft

12.4 lb/ft2

34.1 lb

0.375 in.

33 ft.

29.1 lb/ft

25.6 lb/ft2

81.4 lb
20

The result should look something like figure 4.

1

0.1

0.01

0.001

10 100 1,000

Frequency (Hz)

g2/Hz

Scaled Data 3.9 grms

Envelope 7.5 grms

Figure 4. Scaled vibration data enveloped by criteria.

Since the new structure is about one-third of the diameter of the reference structure, the 

envelope is shifted higher in frequency to cover the first two peaks in the spectrum, which will occur 

at about 90 and 270 Hz on the SRB. A plot of the two acoustic spectra shows that they meet the 

stipulation in section 4.1, except for the area below 40 Hz. Additional margin can be added to the 

low frequency portion of the criteria to compensate. Figure 5 demonstrates a comparison of reference and new acoustic spectra.

It is quite common for the envelope to clip peaks in the spectrum. Peaks can be clipped by 

3 dB if the half-power bandwidth of the peak is less than 10% of the center frequency. The rms 

value of the envelope is always much higher than that of the spectrum, even in the area where clipping occurs. The results are usually tabulated in a manner similar to that shown below: 

Radial Axis, 50 s plus 10 s per mission

20 Hz @ 0.01 g2/Hz

20 – 80 Hz @ +4 dB/octave

80 – 400 Hz @ 0.07 g2/Hz

400 – 2000 Hz @ –3.5 dB/octave

2000 Hz @ 0.01 g2/Hz

Composite = 7.9 grms
21

165

160

155

150

145

140

135

130

125

120

115

110

105

100

dB

10 100 1,000 10,000

Frequency (Hz)

Ref. Acoustic

New Acoustic

Figure 5. Comparison of reference and new acoustic spectra.

Slopes are calculated as a check for the shaker controller and they should usually be kept 

below 12–15 dB/octave because the controllers often have a difficult time controlling steep slopes. 

The slopes can be calculated by

m

PSD

PSD

f

f

= ( )





 











10 2 10

10

2

1

10

2

1

log

log

log







 , (17)

where

m = slope in dB/octave.

PSD = PSD values at frequencies f1 and f2.

5.3 Acceptance Test Criteria

Acceptance vibration tests can serve various purposes, depending upon the organization’s 

viewpoint. Some acceptance tests are used to verify that the component was assembled correctly, 

and others are used to certify the component for flight. Some organizations use a minimum level, 

which often requires a qualification test for the acceptance criteria. Others specify a level below the 

qualification level for acceptance test with no minimum. Reference 10 contains a very good description of acceptance tests that were conducted during the Apollo program and some of the experiences that they had with the tests. Regardless of the philosophy, a good acceptance test program is 

essential to ensuring that the hardware is fit to fly.
22

Some of the methods of calculating acceptance test criteria are as follows:

• Fixed margin between qualification and acceptance – The maximum predicted flight level is used 

to determine either the acceptance or qualification level. If the MPFL is the acceptance level, then 

qualification is done at a fixed margin above MPFL. Organizations that use the acceptance test to 

certify for flight tend to follow this philosophy. Others set the qualification at the MPFL and run 

acceptance tests at a fixed margin below that level. The qualification test is considered to be the certification test for flight, and the acceptance test is used strictly to screen out manufacturing defects. 

Defects may include loose electrical connections, loose nuts, cold solder joints, improper crimps, 

and wire fatigue due to routing. If enough margin exists between acceptance and qualification 

(usually at least 6 dB), then no qualification for acceptance test will have to be conducted. Duration 

of the test is usually determined by the amount of functional testing that must be completed during vibration, but is generally between 1 and 3 minutes.

• Minimum acceptance test – If either of the methods above is used to determine acceptance test 

levels, there is a possibility that the levels may end up being so low that the vibration test may not 

screen all of the manufacturing defects. Most organizations have set a minimum screening spectrum, usually around 6 grms, which all acceptance test levels must exceed. The qualification for the 

acceptance test must be at least as high as the acceptance spectrum plus any tolerance differences. 

Figure 6 illustrates this concept. In this case, the upper tolerance on the acceptance test is 3 dB and 

the lower tolerance on the qualification for acceptance test is –1.5 dB, requiring a minimum margin of 4.5 dB. Testing this way ensures that acceptance tests will never exceed the qualification test. 

Duration of the qualification test should ensure that all possible acceptance tests are covered.

Qualification for Acceptance

Acceptance

Lower Qualification Tolerance and 

Upper Acceptance Tolerance

1

0.1

0.01

10 100 1,000

Frequency (Hz)

g2/Hz

–1.5 dB

+3 dB

+4.5 dB

Figure 6. Illustration of tolerance stack-up.
23

6. CONCLUSIONS AND RECOMMENDATIONS

The vibroacoustic structural databanks that were developed herein represent an advancement in the method of predicting the structural response caused by an acoustic or aerodynamic 

forcing function. It is recommended that when using these vibroacoustic databanks, engineering 

judgment should be used in selecting the databank which best represents the new vehicle structure. 

This is necessary since an exact structural relationship between the databank structure and the new 

vehicle structure will more than likely not occur.

When implementing the techniques contained in this TM it becomes apparent that random 

vibration criteria development is not an exact science. Scaling different spectra with the same scaling parameters can give results that vary by a wide margin. The most important aspect of the component qualification process is that every design be given a vibration test with a spectrum that at 

least approximates the actual flight environment. Exact replication of the flight environment is not 

necessary, because the test will expose the weak points of the design and allow design fixes before 

it flies on the launch vehicle. Testing with this method on a shaker is conservative for the following 

reasons:

• Vibration criteria are broadband envelopes of fluctuating power spectra.

• Zonal vibration criteria are higher than criteria for a specific component.

– Zonal criteria are based on lightest component weight.

• The applicable vibration test durations are applied in each of three orthogonal axes.

• Components are generally tested on a rigid fixture versus the more flexible vehicle structure.

The Space Shuttle experience showed that a strong ground qualification test program is 

important. Development flight instrumentation from Space Shuttle flights revealed exceedances 

to the qualification test criteria; however, no failures occurred during flight, even though the component had a number of failures during qualification testing. This reinforced the point that the 

component test program is very important to mission success. In addition, using vibration test 

technology during the component acceptance tests helps to reveal manufacturing flaws that could 

otherwise have escaped detection.
24

APPENDIX A—SATURN V VIBRATION AND ACOUSTIC DATA

Figure 7. Saturn V zones.
25

Figure 8. S-IVB stage forward skirt external acoustic measurement location.
26

Figure 9. Zone 15: S-IVB stage forward skirt external and internal acoustic measurement location.
27

 Figure 10. S-IVB stage forward skirt vibration measurement locations.
28

Figure 11. S-IVB stage forward skirt vibration measurement locations.
29

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A1 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 3.18 grms

Measurements: E93-411 E96-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 12. Ring frame PSD, longitudinal, liftoff, 2 lb/ft2. 
30

Location: S-IVB Forward Skirt

Flight Condition: Liftoff

Source: TN D-7159/A1

OASPL: 154.3 dB

170

160

150

140

130

120

110

100

Sound Pressure Level in dB, re 0.0002 microbar

Frequency (Hz)

10 100 1,000 10,000

Figure 13. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), liftoff.
31

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A3 Meas. Direction: Longitudinal

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 13.84 grms

Measurements: E93-411 E96-412 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 14. Ring frame PSD, longitudinal, Mach 1, 2 lb/ft2.
32

Location: S-IVB Forward Skirt

Flight Condition: Mach 1

Source: TN D-7159/A3

OASPL: 144.8 dB

170

160

150

140

130

120

110

100

Sound Pressure Level in dB, re 0.0002 microbar

Frequency (Hz)

10 100 1,000 10,000

Figure 15. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), Mach 1.
33

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A5 Meas. Direction: Longitudinal

Flight Condition: Max Q Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 11.32 grms

Measurements: E93-411 E96-413 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 16. Ring frame PSD, longitudinal, Max Q, 2 lb/ft2.
34

170

160

150

140

130

120

110

100

Sound Pressure Level in dB, re 0.0002 microbar

Frequency (Hz)

10 100 1,000 10,000

Location: S-IVB Forward Skirt

Flight Condition: Max Q

Source: TN D-7159/A5

OASPL: 143.9 dB

Figure 17. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), Max Q.
35

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A7 Meas. Direction: Longitudinal

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 13.41 grms

Measurements: E93-411 E96-414 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 18. Ring frame PSD, longitudinal, Mach 1/Max Q, 2 lb/ft2.
36

170

160

150

140

130

120

110

100

Sound Pressure Level in dB, re 0.0002 microbar

Frequency (Hz)

10 100 1,000 10,000

Location: S-IVB Forward Skirt

Flight Condition: Transonic

Source: TN D-7159/A7

OASPL: 144.5 dB

Figure 19. Saturn V acoustic spectrum, S-IVB forward skirt (subzone 15-2-2), transonic.
37

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A9 Meas. Direction: Tangential

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 3.69 grms

Measurements: E95-411 E98-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 20. Skin-stringer PSD, tangential, liftoff, 2 lb/ft2.
38

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A11 Meas. Direction: Tangential

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 26.17 grms

Measurements: E95-411 E98-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 21. Skin-stringer PSD, tangential, Mach 1, 2 lb/ft2.
39

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A13 Meas. Direction: Tangential

Flight Condition: Max Q Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 22.72 grms

Measurements: E95-411 E98-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 22. Ring frame PSD, tangential, Max Q, 2 lb/ft2.
40

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A15 Meas. Direction: Tangential

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 25.80 grms

Measurements: E95-411 E98-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 23. Ring frame PSD, tangential, Mach 1/Max Q, 2 lb/ft2.
41

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A17 Meas. Direction: Radial

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 10.25 grms

Measurements: E94-411 E97-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 24. Ring frame PSD, radial, liftoff, 2 lb/ft2.
42

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A19 Meas. Direction: Radial

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 34.06 grms

Measurements: E94-411 E97-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 25. Ring frame PSD, radial, Mach 1, 2 lb/ft2.
43

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A21 Meas. Direction: Radial

Flight Condition: Max Q Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 45.25 grms

Measurements: E94-411 E97-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 26. Ring frame PSD, radial, Max Q, 2 lb/ft2.
44

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A23 Meas. Direction: Radial

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 22 ft Skin Thickness: 0.032 in

Ring Sep.: N/A Ring Wt.: 0.95 lb/ft

Stringer Sep.: 7.55 in Stringer Wt.: 0.47 lb/ft

Surface Wt.: 2 lb/ft2 Composite: 34.33 grms

Measurements: E94-411 E97-411 Subzone: 15-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 27. Ring frame PSD, radial, Mach 1/Max Q, 2 lb/ft2.
45

Figure 28. Zone 11: S-II stage forward skirt external acoustic measurement location.
46

Figure 29. S-II stage forward skirt vibration measurement locations.
47

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: A25-1 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: N/A Ring Wt.: 2.51 lb/ft

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 3.3 lb/ft2 Composite: 12.71 grms

Measurements: E87-219 E88-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 30. Ring frame PSD, longitudinal, liftoff, 3.3 lb/ft2.
48

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Liftoff

Source: TN D-7159/A25-1

OASPL: 148.6 dB

Figure 31. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), liftoff.
49

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: A25-2 Meas. Direction: Longitudinal

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: N/A Ring Wt.: 2.51 lb/ft

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 3.3 lb/ft2 Composite: 12.15 grms

Measurements: E87-219 E88-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 32. Ring frame PSD, longitudinal, Mach 1, 3.3 lb/ft2.
50

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Mach 1

Source: TN D-7159/A25-2

OASPL: 144.8 dB

Figure 33. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Mach 1.
51

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A25 Meas. Direction: Radial

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: N/A Ring Wt.: 2.51 lb/ft

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 3.3 lb/ft2 Composite: 15.25 grms

Measurements: E87-219 E88-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 34. Ring frame PSD, radial, liftoff, 3.3 lb/ft2.
52

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A27 Meas. Direction: Radial

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: N/A Ring Wt.: 2.51 lb/ft

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 3.3 lb/ft2 Composite: 14.58 grms

Measurements: E87-219 E88-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 35. Ring frame PSD, radial, Mach 1, 3.3 lb/ft2.
53

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Mach 1

Source: TN D-7159/A27

OASPL: 152.0 dB

Figure 36. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Mach 1.
54

Figure 37. S-II stage forward skirt vibration measurement location.
55

Figure 38. S-II stage forward skirt vibration measurement locations.
56

Figure 39. S-II stage S-IC/S–II interstage, and S-II aft skirt vibration measurement locations.
57

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A29 Meas. Direction: Radial

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.04–0.071 in

Ring Sep.: N/A Ring Wt.: 1.09–1.49 lb/ft

Stringer Sep.: 5.76-8.63 in Stringer Wt.: 0.71–1.0 lb/ft

Surface Wt.: 1.1–1.5 lb/ft2 Composite: 42.13 grms

Measurements: E79-86-219 E344-200 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 40. Ring frame PSD, radial, liftoff, 1.1–1.5 lb/ft2.
58

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A31 Meas. Direction: Radial

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.04–0.071 in

Ring Sep.: N/A Ring Wt.: 1.09–1.49 lb/ft

Stringer Sep.: 5.76–8.63 in Stringer Wt.: 0.71–1.0 lb/ft

Surface Wt.: 1.1–1.5 lb/ft2 Composite: 9.46 grms

Measurements: E79-86-219 E344-200 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 41. Ring frame PSD, radial, Mach 1, 1.1–1.5 lb/ft2.
59

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A33 Meas. Direction: Radial

Flight Condition: Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.04–0.07in

Ring Sep.: N/A Ring Wt.: 1.09–1.49 lb/ft

Stringer Sep.: 5.76–8.63 in Stringer Wt.: 0.71–1.0 lb/ft

Surface Wt.: 1.1–1.5 lb/ft2 Composite: 13.33 grms

Measurements: E79-86-219 E344-200 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 42. Ring frame PSD, radial, Max Q, 1.1–1.5 lb/ft2.
60

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward/Aft Skirt

Flight Condition: Max Q

Source: TN D-7159/A33

OASPL: 152.0 dB

Figure 43. Saturn V acoustic spectrum, S-II forward/aft skirt, Max Q.
61

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A35 Meas. Direction: Radial

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.04–0.07in

Ring Sep.: N/A Ring Wt.: 1.09–1.49 lb/ft

Stringer Sep.: 5.76–8.63 in Stringer Wt.: 0.71–1.0 lb/ft

Surface Wt.: 1.1–1.5 lb/ft2 Composite: 5.81 grms

Measurements: E79-86-219 E344-200 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 44. Ring frame PSD, radial, Mach 1/Max Q, 1.1–1.5 lb/ft2.
62

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward/Aft Skirt

Flight Condition: Transonic

Source: TN D-7159/A35

OASPL: 158.8 dB

Figure 45. Saturn V acoustic spectrum, S-II forward/aft skirt, transonic.
63

Figure 46. S-IC forward skirt rings measurement locations.
64

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A37 Meas. Direction: Radial

Flight Condition: Static Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.10 in

Ring Sep.: N/A Ring Wt.: 5.53 lb/ft

Stringer Sep.: 5.76 in Stringer Wt.: 1.0 lb/ft

Surface Wt.: 9.2 lb/ft2 Composite: 16.37 grms

Measurements: E19-120 Subzone: 7

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 47. Ring frame PSD, radial, static, 9.2 lb/ft2.
65

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Forward Skirt

Flight Condition: Static Test

Source: TN D-7159/A37

OASPL: 150.8 dB

Figure 48. Saturn V acoustic spectrum, S-IC forward skirt, static test.
66

Figure 49. Zone 9: S-II stage thrust cone acoustic measurement location.
67

Figure 50. S-II thrust cone ring frames measurement locations.
68

1

0.1

0.01

0.001

0.0001

0.00001

0.000001

Document/Page No.: 7159/A39 Meas. Direction: Parallel

Flight Condition: Static Material: AL

Vehicle Diameter: 25.2 ft Skin Thickness: 0.08–0.13in

Ring Sep.: N/A Ring Wt.: 4.67–70.95 lb/ft

Stringer Sep.: 4.85 in Stringer Wt.: 1.04 lb/ft

Surface Wt.: 4.7–8.0 lb/ft2 Composite: 0.61 grms

Measurements: WE229-206 Subzone: 9-2-1-1

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 51. Ring frame PSD, parallel, static, 4.7–8.0 lb/ft2.
69

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Thrust Cone

Flight Condition: Static Test

Source: TN D-7159/A39

OASPL: 171.5 dB

Figure 52. Saturn V acoustic spectrum, S-II thrust cone (subzone 9-2-1), static test.
70

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A41 Meas. Direction: Normal

Flight Condition: Static Material: AL

Vehicle Diameter: 17.5 ft Skin Thickness: 0.13 in

Ring Sep.: N/A Ring Wt.: 11.39 lb/ft

Stringer Sep.: 6.72 in Stringer Wt.: 1.04 lb/ft

Surface Wt.: 13.9 lb/ft2 Composite: 2.03 grms

Measurements: WE181-206 Subzone: 9-2-1-1

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 53. Ring frame PSD, normal, static, 13.9 lb/ft2.
71

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Thrust Cone

Flight Condition: Static Test

Source: TN D-7159/A41

OASPL: 162.7 dB

Figure 54. Saturn V acoustic spectrum, S-II thrust cone (subzone 9-2-1), static test.
72

Figure 55. S-IC stage intertank ring vibration measurement location.
73

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: A43 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 5.10 grms

Measurements: E20-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 56. Ring frame PSD, longitudinal, liftoff, 6.2 lb/ft2.
74

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Intertank Ring

Flight Condition: Liftoff

Source: TN D-7159/A43

OASPL: 158.4 dB

Figure 57. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), liftoff.
75

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A45 Meas. Direction: Longitudinal

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 17.34 grms

Measurements: E20-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 58. Ring frame PSD, longitudinal, Mach 1, 6.2 lb/ft2.
76

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Intertank Ring

Flight Condition: Mach 1

Source: TN D-7159/A45

OASPL: 136.7 dB

Figure 59. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), Mach 1.
77

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A47 Meas. Direction: Longitudinal

Flight Condition: Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 26.31 grms

Measurements: E20-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 60. Ring frame PSD, longitudinal, Max Q, 6.2 lb/ft2.
78

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Intertank Ring

Flight Condition: Max Q

Source: TN D-7159/A47

OASPL: 142.6 dB

Figure 61. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), Max Q.
79

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A49 Meas. Direction: Longitudinal

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 28.39 grms

Measurements: E20-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 62. Ring frame PSD, longitudinal, Mach 1/Max Q, 6.2 lb/ft2.
80

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Intertank Ring

Flight Condition: Transonic

Source: TN D-7159/A49

OASPL: 151.7 dB

Figure 63. Saturn V acoustic spectrum, S-IC intertank ring (subzone 5-2-2), transonic.
81

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A51 Meas. Direction: Radial

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 24.75 grms

Measurements: E21-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 64. Ring frame PSD, radial, liftoff, 6.2 lb/ft2.
82

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A53 Meas. Direction: Radial

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 25.07 grms

Measurements: E21-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 65. Ring frame PSD, radial, Mach 1, 6.2 lb/ft2.
83

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A55 Meas. Direction: Radial

Flight Condition: Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 32.27 grms

Measurements: E21-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 66. Ring frame PSD, radial, Max Q, 6.2 lb/ft2.
84

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A57 Meas. Direction: Radial

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.185 in

Ring Sep.: N/A Ring Wt.: 4.75 lb/ft

Stringer Sep.: 7.88 in Stringer Wt.: N/A

Surface Wt.: 6.2 lb/ft2 Composite: 32.28 grms

Measurements: E21-118 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 67. Ring frame PSD, radial, Mach 1/Max Q, 6.2 lb/ft2.
85

Figure 68. Zone 2: S-IC stage heat shield frame internal acoustic measurement location.
86

Figure 69. S-IC stage external acoustic measurement locations.
87

Figure 70. S-IC stage upper thrust ring vibration measurement location.
88

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A73 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.375 in

Ring Sep.: N/A Ring Wt.: 29.064 lb/ft

Stringer Sep.: 9.72 in Stringer Wt.: 1.94 lb/ft

Surface Wt.: 25.6 lb/ft2 Composite: 4.26 grms

Measurements: E23-115 Subzone: 2-5-4

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 71. Ring frame PSD, longitudinal, liftoff, 25.6 lb/ft2.
89

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Upper Thrust Ring

Flight Condition: Liftoff

Source: TN D-7159/A73

OASPL: 164.3 dB

Figure 72. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), liftoff.
90

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A65 Meas. Direction: Longitudinal

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.375 in

Ring Sep.: N/A Ring Wt.: 29.06 lb/ft

Stringer Sep.: 9.72 in Stringer Wt.: 1.95 lb/ft

Surface Wt.: 25.6 lb/ft2 Composite: 18.94 grms

Measurements: E23-115 Subzone: 2-5-4

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 73. Ring frame PSD, longitudinal, Mach 1, 25.6 lb/ft2.
91

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Upper Thrust Ring

Flight Condition: Mach 1

Source: TN D-7159/A65

OASPL: 141.3 dB

Figure 74. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), Mach 1.
92

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A69 Meas. Direction: Longitudinal

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.375 in

Ring Sep.: N/A Ring Wt.: 29.06 lb/ft

Stringer Sep.: 9.72 in Stringer Wt.: 1.95 lb/ft

Surface Wt.: 25.6 lb/ft2 Composite: 10.60 grms

Measurements: E23-115 Subzone: 2-5-4

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 75. Ring frame PSD, longitudinal, Mach 1/Max Q, 25.6 lb/ft2.
93

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Upper Thrust Ring

Flight Condition: Transonic

Source: TN D-7159/A69

OASPL: 147.6 dB

Figure 76. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), transonic.
94

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A75 Meas. Direction: Radial

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.375 in

Ring Sep.: N/A Ring Wt.: 29.06 lb/ft

Stringer Sep.: 9.72 in Stringer Wt.: 1.95 lb/ft

Surface Wt.: 25.6 lb/ft2 Composite: 3.55 grms

Measurements: E24-115 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 77. Ring frame PSD, radial, liftoff, 25.6 lb/ft2.
95

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A77 Meas. Direction: Radial

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.375 in

Ring Sep.: N/A Ring Wt.: 29.06 lb/ft

Stringer Sep.: 9.72 in Stringer Wt.: 1.95 lb/ft

Surface Wt.: 25.6 lb/ft2 Composite: 12.10 grms

Measurements: E24-115 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 78. Ring frame PSD, radial, Mach 1, 25.6 lb/ft2.
96

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A79 Meas. Direction: Radial

Flight Condition: Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.375 in

Ring Sep.: N/A Ring Wt.: 29.06 lb/ft

Stringer Sep.: 9.72 in Stringer Wt.: 1.95 lb/ft

Surface Wt.: 25.6 lb/ft2 Composite: 8.45 grms

Measurements: E24-115 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 79. Ring frame PSD, radial, Max Q, 25.6 lb/ft2.
97

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-IC Upper Thrust Ring

Flight Condition: Max Q

Source: TN D-7159/A79

OASPL: 145.7 dB

Figure 80. Saturn V acoustic spectrum, S-IC upper thrust ring (subzone 2-5-4), Max Q.
98

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A81 Meas. Direction: Radial

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.375 in

Ring Sep.: N/A Ring Wt.: 29.06 lb/ft

Stringer Sep.: 9.72 in Stringer Wt.: 1.95 lb/ft

Surface Wt.: 25.6 lb/ft2 Composite: 6.75 grms

Measurements: E24-115 Subzone: 5-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 81. Ring frame PSD, radial, Mach 1/Max Q, 25.6 lb/ft2.
99

Figure 82. S-II stage forward skirt vibration measurement locations.
100

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A87 Meas. Direction: Normal

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 19.0 in Ring Wt.: N/A

Stringer Sep.: 8.47 in Stringer Wt.: 10.41 lb/ft

Surface Wt.: 3.3 lb/ft2 Composite: 20.66 grms

Measurements: Unknown Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 83. Skin-stringer PSD, normal, liftoff, 3.3 lb/ft2.
101

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Liftoff

Source: TN D-7159/A87

OASPL: 153.9 dB

Figure 84. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), liftoff.
102

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A89 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 1.42 grms

Measurements: E326-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 85. Skin-stringer PSD, longitudinal, liftoff, 1.5 lb/ft2.
103

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Liftoff

Source: TN D-7159/A89

OASPL: 161.9 dB

Figure 86. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), liftoff.
104

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A91 Meas. Direction: Longitudinal

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 2.18 grms

Measurements: E326-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 87. Skin-stringer PSD, longitudinal, Mach 1, 1.5 lb/ft2.
105

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Mach 1

Source: TN D-7159/A91

OASPL: 158.1 dB

Figure 88. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Mach 1.
106

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A93 Meas. Direction: Longitudinal

Flight Condition: Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 1.91 grms

Measurements: E326-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 89. Skin-stringer PSD, longitudinal, Max Q, 1.5 lb/ft2.
107

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Max Q

Source: TN D-7159/A93

OASPL: 162.0 dB

Figure 90. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), Max Q.
108

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A95 Meas. Direction: Longitudinal

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 4.41 grms

Measurements: E326-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 91. Skin-stringer PSD, longitudinal, Mach 1/Max Q, 1.5 lb/ft2.
109

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Forward Skirt

Flight Condition: Transonic

Source: TN D-7159/A95

OASPL: 152.1 dB

Figure 92. Saturn V acoustic spectrum, S-II forward skirt (subzone 11-2-2), transonic.
110

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A97 Meas. Direction: Tangential

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 2.09 grms

Measurements: E327-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 93. Skin-stringer PSD, tangential, liftoff, 1.5 lb/ft2.
111

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A99 Meas. Direction: Tangential

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 4.63 grms

Measurements: E327-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 94. Skin-stringer PSD, tangential, Mach 1, 1.5 lb/ft2.
112

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A101 Meas. Direction: Tangential

Flight Condition: Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 4.19 grms

Measurements: E327-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 95. Skin-stringer PSD, tangential, Max Q, 1.5 lb/ft2.
113

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A103 Meas. Direction: Tangential

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 8.11 grms

Measurements: E327-219 E329-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 96. Skin-stringer PSD, tangential, Mach 1/Max Q, 1.5 lb/ft2.
114

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A105 Meas. Direction: Radial

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 6.03 grms

Measurements: E325-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 97. Skin-stringer PSD, radial, liftoff, 1.5 lb/ft2.
115

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A107 Meas. Direction: Radial

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.040 in

Ring Sep.: 36.0 in Ring Wt.: N/A

Stringer Sep.: 8.63 in Stringer Wt.: 0.71 lb/ft

Surface Wt.: 1.5 lb/ft2 Composite: 4.25 grms

Measurements: E325-219 Subzone: 11-2-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 98. Skin-stringer PSD, radial, Mach 1, 1.5 lb/ft2.
116

Figure 99. Zone 9: S-II stage aft skirt external acoustic measurement location.
117Figure 100. Zone 9: S-II/S-IC interstage external acoustic measurement location.
118

Figure 101. S-II stage aft skirt vibration measurement locations.
119Figure 102. S–II aft skirt skin/stringer vibration measurement locations.
120

Figure 103. S-II aft skirt skin/stringer vibration measurement locations.
121

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A109 Meas. Direction: Longitudinal

Flight Condition: Static Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.071 in

Ring Sep.: 27.0 in Ring Wt.: N/A

Stringer Sep.: 5.76 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 2.8 lb/ft2 Composite: 9.03 grms

Measurements: WE146-206 E74-206 Subzone: 9-3-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 104. Skin-stringer PSD, longitudinal, static, 2.8 lb/ft2.
122

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Aft Skirt

Flight Condition: Static Test

Source: TN D-7159/A109

OASPL: 160.3 dB

Figure 105. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), static test.
123

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A111 Meas. Direction: Radial

Flight Condition: Mach 1 Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.071 in

Ring Sep.: 27.0 in Ring Wt.: N/A

Stringer Sep.: 5.76 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 2.8 lb/ft2 Composite: 56.49 grms

Measurements: E351-206 E76-206 Subzone: 9-3-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 106. Skin-stringer PSD, radial, Mach 1, 2.8 lb/ft2.
124

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Aft Skirt

Flight Condition: Mach 1

Source: TN D-7159/A111

OASPL: 139.0 dB

Figure 107. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), Mach 1.
125

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A113 Meas. Direction: Radial

Flight Condition: Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.071 in

Ring Sep.: 27.0 in Ring Wt.: N/A

Stringer Sep.: 5.76 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 2.8 lb/ft2 Composite: 90.88 grms

Measurements: E351-206 E76-206 Subzone: 9-3-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 108. Skin-stringer PSD, radial, Max Q, 2.8 lb/ft2.
126

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Aft Skirt

Flight Condition: Max Q

Source: TN D-7159/A113

OASPL: 141.7 dB

Figure 109. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), Max Q.
127

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A115 Meas. Direction: Radial

Flight Condition: Mach 1/Max Q Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.071 in

Ring Sep.: 27.0 in Ring Wt.: N/A

Stringer Sep.: 5.76 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 2.8 lb/ft2 Composite: 67.06 grms

Measurements: E351-206 E76-206 Subzone: 9-3-2

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 110. Skin-stringer PSD, radial, Mach 1/Max Q, 2.8 lb/ft2.
128

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: S-II Aft Skirt

Flight Condition: Transonic

Source: TN D-7159/A115

OASPL: 143.1 dB

Figure 111. Saturn V acoustic spectrum, S-II aft skirt (subzone 9-3-2), transonic.
129

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A117 Meas. Direction: Radial

Flight Condition: Static Material: AL

Vehicle Diameter: 33 ft Skin Thickness: 0.071 in

Ring Sep.: 27.0 in Ring Wt.: N/A

Stringer Sep.: 5.76 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 2.8 lb/ft2 Composite: 39.77 grms

Measurements: E76-206 E75-206 WE240-206 Subzone: 9-3-2

E76-206 WE239-206 WE148-206 

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 112. Skin-stringer PSD, radial, static, 2.8 lb/ft2.
130

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: 7159/A119 Meas. Direction: Radial

Flight Condition: Static Material: AL Honeycomb

Vehicle Diameter: 22 ft Overall Thickness: 1.0 in

Core Density: 3.10 lb/ft3 Outer Plate Thickness: 0.030 in

Surface Wt.: 1.12 lb/ft2 Composite: 67.60 grms

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 113. Honeycomb PSD, radial, static, 1.1 lb/ft2.
131

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Payload Shroud

Flight Condition: Static

Source: TM X-53377

OASPL: 154.1 dB

Figure 114. Saturn V acoustic spectrum, payload shroud, static test.
132

APPENDIX B—TITAN III VIBRATION AND ACOUSTIC DATA

Figure 115. Titan IIIC vehicle compartment and station designations.
133

Figure 116. Compartment 3A measurement locations.
134

Figure 117. Compartment 3A instrumentation and guidance truss measurement locations.
135

2653 Longitudinal

2654 Radial

Figure 118. Vibration measurements 2562 and 2563, compartment 3A, 

at mounting point of attitude control nozzles, station 130.
136

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A192 Meas. Direction: Longitudinal

Flight Condition: Mach 1/Max Q Material: 7178 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 37 in Ring Wt.: 1.48 lb/ft

Stringer Sep.: 14.2 in Stringer Wt.: 2.38 lb/ft

Surface Wt.: 2.28 lb/ft2 Composite: 10.06 grms

Measurements: 2727 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 119. P/L truss vibration PSD, longitudinal, Mach 1/Max Q, 2.28 lb/ft2.
137

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A193 Meas. Direction: Radial

Flight Condition: Mach 1/Max Q Material: 7178 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 37 in Ring Wt.: 1.48 lb/ft

Stringer Sep.: 14.2 in Stringer Wt.: 2.38 lb/ft

Surface Wt.: 2.28 lb/ft2 Composite: 9.44 grms

Measurements: 2728 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 120. P/L truss vibration PSD, radial, Mach 1/Max Q, 2.28 lb/ft2.
138

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A182 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 37 in Ring Wt.: 1.48 lb/ft

Stringer Sep.: 16.3 in Stringer Wt.: 0.24 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 11.94 grms

Measurements: 2718, 2721 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 121. Ring frame vibration PSD, longitudinal, liftoff, 2.49 lb/ft2.
139

100

10

1

0.1

0.01

0.001

0.0001

0.00001

Document/Page No.: MCR75440/A190 Meas. Direction: Longitudinal

Flight Condition: Mach 1 Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 37 in Ring Wt.: 1.48 lb/ft

Stringer Sep.: 16.3 in Stringer Wt.: 0.24 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 2.23 grms

Measurements: 2718, 2721 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 122. Ring frame vibration PSD, longitudinal, Mach 1, 2.49 lb/ft2.
140

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A183 Meas. Direction: Radial

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 37 in Ring Wt.: 1.48 lb/ft

Stringer Sep.: 16.3 in Stringer Wt.: 0.24 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 7.49 grms

Measurements: 2719, 2722 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 123. Ring frame vibration PSD, radial, liftoff, 2.49 lb/ft2.
141

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A191 Meas. Direction: Radial

Flight Condition: Mach 1 Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 37 in Ring Wt.: 1.48 lb/ft

Stringer Sep.: 16.3 in Stringer Wt.: 0.24 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 2.25 grms

Measurements: 2719, 2722 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 124. Ring frame vibration PSD, radial, Mach 1, 2.49 lb/ft2.
142

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A142 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 19.6 in Ring Wt.: 0.84 lb/ft

Stringer Sep.: 11 in Stringer Wt.: 0.38 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 8.50 grms

Measurements: 2551, 2653, 2702 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 125. Skin-stringer vibration PSD, longitudinal, liftoff, 2.49 lb/ft2.
143

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A147 Meas. Direction: Longitudinal

Flight Condition: Mach 1 Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 19.6 in Ring Wt.: 0.84 lb/ft

Stringer Sep.: 11 in Stringer Wt.: 0.38 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 5.07 grms

Measurements: 2551, 2653, 2702 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 126. Skin-stringer vibration PSD, longitudinal, Mach 1, 2.49 lb/ft2.
144

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A180 Meas. Direction: Radial

Flight Condition: Liftoff Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 19.6 in Ring Wt.: 0.84 lb/ft

Stringer Sep.: 13 in Stringer Wt.: 0.376 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 15.41 grms

Measurements: 2552, 2703, 2654 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 127. Skin-stringer vibration PSD, radial, liftoff, 2.49 lb/ft2.
145

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A149 Meas. Direction: Radial

Flight Condition: Mach 1 Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.028 in

Ring Sep.: 19.6 in Ring Wt.: 0.84 lb/ft

Stringer Sep.: 11 in Stringer Wt.: 0.38 lb/ft

Surface Wt.: 2.49 lb/ft2 Composite: 10.48 grms

Measurements: 2552, 2703, 2654 Compartment: 3A, 3B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 128. Skin-stringer vibration PSD, radial, Mach 1, 2.49 lb/ft2.
146

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 3A

Flight Condition: Liftoff

Source: MCR75440/A196

OASPL: 148.4 dB

Figure 129. Titan III acoustic spectrum, compartment 3A, liftoff.
147

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 3A

Flight Condition: Mach 1

Source: MCR75440/A197

OASPL: 159.1 dB

Figure 130. Titan III acoustic spectrum, compartment 3A, Mach 1.
148

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 3A

Flight Condition: Max Q

Source: MCR75440/A198

OASPL: 152.2 dB

Figure 131. Titan III acoustic spectrum, compartment 3A, Max Q.
149

Figure 132. Compartment 2B measurement locations.
150

2519 Radial

2520 Tangential

Figure 133. Vibration measurements 2519 and 2520, compartment 2B, station 360.
151

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A127 Meas. Direction: Radial

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.040 in

Ring Sep.: 22 in Ring Wt.: 0.32–.77 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.85 lb/ft

Surface Wt.: 2.7 lb/ft2 Composite: 15.76 grms

Measurements: 2519 Compartment: 2B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 134. Skin-stringer vibration PSD, radial, liftoff, 2.7 lb/ft2.
152

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A128 Meas. Direction: Tangential

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.040 in

Ring Sep.: 22 in Ring Wt.: 0.32–.77 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.85 lb/ft

Surface Wt.: 2.7 lb/ft2 Composite: 18.07 grms

Measurements: 2520 Compartment: 2B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 135. Skin-stringer vibration PSD, tangential, liftoff, 2.7 lb/ft2.
153

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A129 Meas. Direction: Tangential

Flight Condition: Mach 1 Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.040 in

Ring Sep.: 22 in Ring Wt.: 0.32–.77 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.85 lb/ft

Surface Wt.: 2.7 lb/ft2 Composite: 7.78 grms

Measurements: 2520 Compartment: 2B

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 136. Skin-stringer vibration PSD, tangential, Mach 1, 2.7 lb/ft2.
154

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 2B

Flight Condition: Liftoff

Source: MCR75440/A133

OASPL: 148.4 dB

Figure 137. Titan III acoustic spectrum, compartment 2B, liftoff.
155

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 2B

Flight Condition: Mach 1/Max Q

Source: MCR75440/A134

OASPL: 161.3 dB

Figure 138. Titan III acoustic spectrum, compartment 2B, Mach 1/Max Q.
156

Figure 139. Compartment 2C measurement locations.
157

Longitudinal 2602

Radial 2603

Tangential 2604

Figure 140. Vibration measurements 2602, 2603, and 2604, compartment 2C, station 473.
158

Longitudinal 2566

Radial 2567

Figure 141. Vibration measurements 2566 and 2567, compartment 2C, station 493.
159

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A104 Meas. Direction: Radial

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 19 in Ring Wt.: 0.55–.65 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.86 LB/in

Surface Wt.: 3.06 lb/ft2 Composite: 19.22 grms

Measurements: 2567, 2603 Compartment: 2C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 142. Skin-stringer vibration PSD, radial, liftoff, 3.06 lb/ft2.
160

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A106 Meas. Direction: Radial

Flight Condition: Mach1/Max Q Material: AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 19 in Ring Wt.: 0.55–.65 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 3.06 lb/ft2 Composite: 9.12 grms

Measurements: 2567, 2603 Compartment: 2C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 143. Skin-stringer vibration PSD, radial, Mach 1, Max Q, 3.06 lb/ft2.
161

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A109 Meas. Direction: Radial

Flight Condition: Transonic Material: AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 19 in Ring Wt.: 0.55–.65 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 3.06 lb/ft2 Composite: 9.24 grms

Measurements: 2567, 2367 Compartment: 2C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 144. Skin-stringer vibration PSD, radial, transonic, 3.06 lb/ft2.
162

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A107 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 19 in Ring Wt.: 0.55–.65 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 3.06 lb/ft Composite: 6.23 grms

Measurements: 2566, 2602 Compartment: 2C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 145. Skin-stringer vibration PSD, longitudinal, liftoff, 3.06 lb/ft.
163

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A108 Meas. Direction: Tangential

Flight Condition: Liftoff Material: AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 19 in Ring Wt.: 0.55–.65 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.86 lb/ft

Surface Wt.: 3.06 lb/ft2 Composite: 6.96 grms

Measurements: 2604 Compartment: 2C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 146. Skin-stringer vibration PSD, tangential, liftoff, 3.06 lb/ft2.
164

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 2C

Flight Condition: Liftoff

Source: MCR75440/A113

OASPL: 153.5 dB

Figure 147. Titan III acoustic spectrum, compartment 2C, liftoff.
165

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 2C

Flight Condition: Mach 1/Max Q

Source: MCR75440/A114

OASPL: 162.6 dB

Figure 148. Titan III acoustic spectrum, compartment 2C, Mach 1/Max Q.
166

Figure 149. Compartment 1A measurement locations.
167

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A88 Meas. Direction: Radial

Flight Condition: Mach 1 Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.241 in

Ring Sep.: 20 in Ring Wt.: 1.8 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 1.06 lb/ft

Surface Wt.: 4.52 lb/ft2 Composite: 5.63 grms

Measurements: 2723 Compartment: 1A

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 150. Skin-stringer vibration PSD, radial, Mach 1, 4.52 lb/ft2.
168

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A81 Meas. Direction: Radial

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 15 in Ring Wt.: 0.86–1.18 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 1.06 lb/ft

Surface Wt.: 4.67 lb/ft2 Composite: 13.01 grms

Measurements: 2527 Compartment: 1A

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 151. Skin-stringer vibration PSD, radial, liftoff, 4.67 lb/ft2.
169

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A83 Meas. Direction: Radial

Flight Condition: Transonic Material: 7075 AL

Vehicle Diameter: 10 FT Skin Thickness: 0.04 in

Ring Sep.: 15 in Ring Wt.: 0.86–1.18 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 1.06 lb/ft

Surface Wt.: 4.67 lb/sq.ft Composite: 28.54 grms

Measurements: 2527 Compartment: 1A

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 152. Skin-stringer vibration PSD, radial, transonic, 4.67 lb/ft2.
170

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A90 Meas. Direction: Tangential

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 8–15 in Ring Wt.: 1.18 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 1.06 lb/ft

Surface Wt.: 4.67 lb/ft2 Composite: 5.06 grms

Measurements: 2612 Compartment: 1A

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 153. Skin-stringer vibration PSD, tangential, liftoff, 4.67 lb/ft2.
171

2610 Longitudinal

2611 Radial

Figure 154. Vibration measurements 2610 and 2611, compartment 1A, station 508.
172

2526 Longitudinal

2527 Lateral

Figure 155. Vibration measurements 2526 and 2527, compartment 1A, station 508.
173

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A79 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 15 in Ring Wt.: 0.86–1.18 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 1.06 lb/ft

Surface Wt.: 4.67 lb/ft2 Composite: 15.90 grms

Measurements: 2610, 2526 Compartment: 1A

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 156. Skin-stringer vibration PSD, longitudinal, liftoff, 4.67 lb/ft2.
174

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A77 Meas. Direction: Radial

Flight Condition: Liftoff Material: 7075 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.04 in

Ring Sep.: 8–15 in Ring Wt.: 1.18 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 1.06 lb/ft

Surface Wt.: 4.67 lb/ft2 Composite: 13.79 grms

Measurements: 2611, 2608, 2723 Compartment: 1A

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 157. Skin-stringer vibration PSD, radial, liftoff, 4.67 lb/ft2.
175

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 1A

Flight Condition: Liftoff

Source: MCR75440/A95

OASPL: 154.7 dB

Figure 158. Titan III acoustic spectrum, compartment 1A, liftoff.
176

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 1A

Flight Condition: Mach 1

Source: MCR75440/A96

OASPL: 168.1 dB

Figure 159. Titan III acoustic spectrum, compartment 1A, Mach 1.
177

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 1A

Flight Condition: Max Q

Source: MCR75440/A97

OASPL: 162.8 dB

Figure 160. Titan III acoustic spectrum, compartment 1A, Max Q.
178

Figure 161. Compartment 1C measurement locations.
179

2576 Acoustic

Figure 162. Compartment 1C acoustic measurement, station 1219.
180

2540 Longitudinal

2541 Lateral

Figure 163. Vibration measurements 2540 and 2541, compartment 1C, station 1214.
181

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A40 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.25 in

Ring Sep.: 20 in Ring Wt.: 3.9–4.21 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.732 lb/ft

Surface Wt.: 8.4 lb/ft2 Composite: 4.05 grms

Measurements: 2540 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 164. Skin-stringer vibration PSD, longitudinal, liftoff, 8.4 lb/ft2.
182

100

10

1

0.1

0.01

0.001

0.0001

0.00001

Document/Page No.: MCR75440/A49 Meas. Direction: Radial

Flight Condition: Liftoff Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.07 in

Ring Sep.: 20 in Ring Wt.: 3.9–4.21 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.84 lb/ft

Surface Wt.: 8.4 lb/ft2 Composite: 12.42 grms

Measurements: 2623 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 165. Skin-stringer vibration PSD, radial, liftoff, 8.4 lb/ft2.
183

100

10

1

0.1

0.01

0.001

0.0001

0.00001

Document/Page No.: MCR75440/A51-2 Meas. Direction: Radial

Flight Condition: Liftoff Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.25 in

Ring Sep.: 20 in Ring Wt.: 3.9–4.21 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.732 lb/ft

Surface Wt.: 12.08 lb/ft2 Composite: 10.79 grms

Measurements: 2541 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 166. Skin-stringer vibration PSD, radial, liftoff, 12.08 lb/ft2.
184

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A50 Meas. Direction: Radial

Flight Condition: Transonic Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.1 in

Ring Sep.: 20 in Ring Wt.: 3.9–4.21 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.84 lb/ft

Surface Wt.: 12.08 lb/ft2 Composite: 10.92 grms

Measurements: 2623 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 167. Skin-stringer vibration PSD, radial, transonic, 12.08 lb/ft2.
185

100

10

1

0.1

0.01

0.001

0.0001

0.00001

Document/Page No.: MCR75440/A51 Meas. Direction: Tangential

Flight Condition: Liftoff Material: 2014 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.1 in

Ring Sep.: 20 in Ring Wt.: 3.9–4.21 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.84 lb/ft

Surface Wt.: 12.08 lb/ft2 Composite: 4.83 grms

Measurements: 2541 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 168. Skin-stringer vibration PSD, tangential, liftoff, 12.08 lb/ft2.
186

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A47 Meas. Direction: Longitudinal

Flight Condition: Liftoff Material: 7079 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.070 in

Ring Sep.: 20 in Ring Wt.: 4.21 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.84 lb/ft

Surface Wt.: 27.9 lb/ft2 Composite: 11.45 grms

Measurements: 2572 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 169. Skin-stringer vibration PSD, longitudinal, liftoff, 27.9 lb/ft2.
187

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A38 Meas. Direction: Radial

Flight Condition: Liftoff Material: 7079 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.070 in

Ring Sep.: 20 in Ring Wt.: 4.2 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.84 lb/ft

Surface Wt.: 27.9 lb/ft2 Composite: 5.74 grms

Measurements: 2573 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 170. Skin-stringer vibration PSD, radial, liftoff, 27.9 lb/ft2.
188

100

10

1

0.1

0.01

0.001

0.0001

Document/Page No.: MCR75440/A48 Meas. Direction: Radial

Flight Condition: Transonic Material: 7079 AL

Vehicle Diameter: 10 ft Skin Thickness: 0.070 in

Ring Sep.: 20 in Ring Wt.: 4.2 lb/ft

Stringer Sep.: 10.5 in Stringer Wt.: 0.84 lb/ft

Surface Wt.: 27.9 lb/ft2 Composite: 7.81 grms

Measurements: 2573 Compartment: 1C

10 100 1,000 10,000

Frequency (Hz)

g2/ Hz

Figure 171. Skin-stringer vibration PSD, radial, transonic, 27.9 lb/ft2.
189

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 1C

Flight Condition: Liftoff

Source: MCR75440/A52

OASPL: 158.6 dB

Figure 172. Titan III acoustic spectrum, compartment 1C, liftoff.
190

170

160

150

140

130

120

110

100

1/3 Octave Band Sound Pressure Level (dB re 20 Pa)

Frequency (Hz)

10 100 1,000 10,000

Location: Compartment 1C

Flight Condition: Mach 1

Source: MCR75440/A55

OASPL: 151.8 dB

Figure 173. Titan III acoustic spectrum, compartment 1C, Mach 1.
191

REFERENCES

 1. Bandgren, H.J.; and Smith, W.C.: “Development and Application of Vibroacoustic Structural 

Databanks in Predicting Vibration Design and Test Criteria for Rocket Vehicle Structures,” 

NASA–TN–D–7159, Marshall Space Flight Center, AL, February 1973.

 2. “Saturn V Static Firing Vibration Data Zonal Statistical Analyses,” Boeing Document 

D5–17032–1, October 3, 1969.

 3. “Saturn V Flight Vibration Data Zonal Statistical Analyses,” Boeing Document D5–17032–2, 

October 10, 1969.

 4. Barrett, R.E.: “Statistical Techniques for Describing Localized Vibratory Environments 

of Rocket Vehicles,” NASA–TN–D–2158, Marshall Space Flight Center, July 1964.

 5. Link, C.L.: “An Equation for One-sided Tolerance Limits for Normal Distributions,” 

Forest Products Laboratory Research Paper FPL 458, August 1985.

 6. Baratono, J.; and Engelsgjerd, I.K.: “Development of Solid Rocket Motor Vibroacoustic 

Structural Databanks,” Martin-Marietta Report MCR–75–440, December 1975.

 7. Barrett, R.E.: “Techniques for Predicting Localized Vibratory Environments of Rocket Vehicles,” NASA–TN–D–1836, October 1963.

 8. “Dynamic Environmental Criteria,” NASA–HDBK–7005, Jet Propulsion Library, CA, 2001.

 9. Curtis, A.J.; Tinling, N.G.; and Abstein, H.T., Jr.: “Selection and Performance of Vibration 

Tests,” The Shock and Vibration Information Center, 1971.

10. Laubach, C.H.M.: “Apollo Experience Report: Environmental Acceptance Testing,” NASA–

TN–D–8271, Johnson Space Center, TX, June 1976.
192

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Standard Form 298 (Rev. 8-98)

Prescribed by ANSI Std. Z39-18

Using the Saturn V and Titan III Vibroacoustic Databanks 

for Random Vibration Criteria Development

R.C. Ferebee

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

National Aeronautics and Space Administration

Washington, DC 20546–0001

Unclassified-Unlimited

Subject Category 39

Availability: NASA CASI 443–757–5802

M–1261

Technical Memorandum July 2008–October 2008

NASA/TM—2009–215902

vibroacoustic criteria, random vibration criteria, flight vibration data

01-07-2009

UU 208

NASA

U U U

This is an update to TN D-7159, “Development and Application of Vibroacoustic Structural Data Banks 

in Predicting Vibration Design and Test Criteria for Rocket Vehicle Structures”, which was originally 

published in 1973. Errors in the original document have been corrected and additional data from the 

Titan III program have been included. Methods for using the vibroacoustic databanks for vibration test 

criteria development are shown, as well as all of the data with drawings and pictures of the measurement 

locations. An Excel spreadsheet with the data included is available from the author.

STI Help Desk at email: help@sti.nasa.gov

STI Help Desk at: 443-757-5802

National Aeronautics and

Space Administration

IS20

George C. Marshall Space Flight Center

Marshall Space Flight Center, Alabama

35812