C 01W021r8FPNED FOR RELEASE 

11 AUGUST 2015 

FINAL REPORT. 

BIT. MISSION 7052 

11 December 1964 
c 0 9p98FgoggVED FOR RELEASE 

1 AUGUST 2015 

V. 

' File No. H-1155 SPECIAL HANDLING 11 December 1964 

- page 1 - 

FINAL REPORT - BIT MISSION 7052 

1. **,1 MISSION SUMMARY. 

1.1 1"N Program Objectives. 

As part of the over-all problem of determining the vulnerability 

of the Agena satellites to Soviet radar detection and tracking, the 

objective of the BIT program is to determine if and when the radar 

system associated with the signal acquires and tracks the Agena 

vehicle. The BIT system, designed to fulfill this objective, covers 

the frequency range from 154 to 164 Mc and accepts only those signals 

which have characteristics similar to On those signals which 

qualify, the system will measure frequency, PRF, and signal amplitude 

along with the time of intercept to enable an analyst to identify the 

signal characteristics and to estimate a geographical area within which 

the emitter is located. 

1.2 Mission Highlights. 

No signals of interest were intercepted during the effective 

mission life which started with orbit 9 and lasted until orbit 63. A 

problem in the vehicle's data link prevented recovery of the data 

recorded prior to orbit 9 and a commutator.failure in the BIT system 

after orbit 63 prematurely terminated the mission which was programmed 

to last 160 orbits. The Signal Simulator and Activity Indicator in the, 

BIT showed that the system was functioning properly during the entire 

mission for, which data is available. 

1.3 Flight Summary. 

Vehicle Number "1173 

Launch Date 2 November 1964 

Launch Time 2134 GMT 

Inclination 80 degrees 

Apogee 246 nautical miles 

Perigee 99 nautical miles 

Period 90.8 minutes 

This Document Consists of 7 Pages. 

Copy No__51_ of__Y___Copies, Series EDL 

SPECIAL HANDLI1"' 
File No. H-1155 

0 11 December 1964 SPECIAL HANDLINr- 

- page 2 - 

C2 of ggVED FOR RELEASE 

1 AUGUST 2015 

2. DATA ANALYSIS. 

2. 1 TS).... System Coverage. 

The BIT system was programmed on during 34 orbits of the 

63 orbit mission life while the vehicle was over the'northern hemisphere 

with an emphasis on the coverage over Europe, the USSR and Asia. 

On six occasions, the unit was on throughout the period while the vehicle 

was over the southern hemisphere. 

The system monitors the 154- to 164-Mc frequency range with 

a receiver sensitivity of -54 dbm. With the inclusion of the antenna 

pattern, the over—all system sensitivity varies from approximately 

-44 dbm at the horizon to -52 dbm looking straight down. Signals 

intercepted by the system are rejected by qualification circuitry if 

the pulse widths are less than approximately 24 microseconds and 

if the PRFs do not fall within the 95- to 100-pps PRF acceptance 

band or harmonics of this band. The system measures amplitude, 

frequency, and PRF on those signals which qualify. If a signal has 

a power level at the receiver of -26 dbm or greater, it will also be 

fed into a high level channel which requires no qualification other 

than amplitude and which measures only the signal amplitude. 

2. 2 "Sk..._ Mission Results. 

2.2.1 164.. Qualified Intercepts. 

2. 2. 2 CS.) Non-Qualified Intercepts. 

SPECIAL-• HANDLING 
.'11•1•4: C05 • • 

VED FOR RELEASE 

2015 

ON. 

• 

File No. H-1155 

11 December 1964 SPEC:AL HANDLINr 

- page 3 - 

3. N SYSTEM PERFORMANCE EVALUATION.: 

3.1 TS). System Description. 

A block•diagram of the BIT system is shown in Figure 1 although 

it is labeled by its in-house name of FIRE BOX. It is basically a TRF 

(tuned radio frequency) receiver with video logic for signal recognition 

and circuits for parameter measurement. An intercepted signal which 

exceeds the Detector B threshold of -53 dbm is amplitude standardized 

in the video threshold circuit and then qualified. If the pulse width 

is greater than 24 microseconds, the signal will be passed to the 

Pulse Rate Counter (PRC) and the PRF Qualifier. The PRC counts 

the total number of pulses received during one commutator read-in 

cycle (400 milliseconds) and the PRF Qualifier examines the pulse 

train for a PRF of 95 to 100 pps or harmonics of this PRF range. If 

the PRF qualifies, a pulse-by-pulse gate pulse is generated which 

opens the two gates to permit the Peak Level Detectors (PLD) to read 

amplitude and frequency. The PLD's store the lowest frequency and 

the highest pulse amplitude intercepted during the 400-millisecond 

read-in period. If the signal level exceeds -26 dbm at the receiver, 

the signal amplitude will be read in the Detector A channel without 

qualification. A Time Reference Generator provides a parallel octal 

time code reference for the system. It is also used to trigger the 

Signal Simulator on for four seconds every 256 seconds. The Simulator 

generates a 98-pps signal at a frequency of 160 Mc and a power level 

of -28 dbm which is used to test the entire system for proper operation 

plus providing a one-point calibration check of the system. 

A Signal Activity Indicator, designated as PRC-B, has been 

added to the system to provide a check on the operational status of 

the antenna and the PRF input line. The circuit, which is connected 

to the output of the Video Threshold circuit, counts every pulse received 

regardless of pulse width or PRF. Since it is primarily intended to 

indicate the presence of actiyity and it is an "add on" modification, no 

attempt was made to achieve accurate pulse 'count measurements. 

A summary of the system specifications for the BIT system 

used in this mission is given below, and a plot of the system's detection 

sensitivity is shown in Figure 2. 

Minimum Detectable Signal -53 dbm (PLD-B) 

-26 dbm (PLD-A) 

PRC Minimum Acceptable 

Pulse Width 24 microseconds 

Frequency/Amplitude PLD 

Minimum Pulse Width 30 microseconds 

SPECIAL-HANDLING 
BOX SYSTEM 

LU 

LL. 

0 

Slm 

F O 

LLW L1 .

0 

• 

01 

7,1 

NI 1.0: 

O 

• 

COMP8'P,•0-VED FOR RELEASE • • 

1 AUGUST 2015 

File:Noi H-1155 

11 December 1964 

tttt" 

- page 4 - 

O. 

0 

vV 

Figure 1 
Figure 2 

- page 5 - 

Q 

0 

1 1 

0 

Cf 

6SVFIRifPfkIP-14.P.F55 

ST201 151 December 19f 

0.417. 

• • 

C 
co5528"egVED FOR RELEASE 

• 

1 AUGUST 2015 

File No. H-1155 

11 December 1964 

SPECIAL HANDLING 

- page 6 - 

3. 1 Continued. 

PRF Qualifier Acceptance Range 95-100 pps (fundamental) 

189-201 pps,(2nd harmonic) 

RF Passband at -50 dbm 154.7 to 163.7 Mc 

3. 2 14S4*,, System Performance. 

The BIT system performed as designed for the duration of the 

useful life of the mission. Comparison of the system's response to 

the Signal Simulator during the mission with its response prior to 

launch showed that the detection sensitivity and the calibrations for 

frequency, amplitude, and PRF maintained their original levels. 

The system's operating temperature was 74 degrees Fahrenheit during 

the mission. 

The major problem encountered was the failure of the commutator 

to, start when the system was turned on for the orbit 64 read in. Turn 

on commands on succeeding orbits failed to start the commutator 

so all data after orbit 63 were lost. A check of the commutator speed 

during the mission showed it to be running at the correct speed on 

orbit 16 and 12 to 18 per cent slow on orbits 33 and 63. The power 

supply voltage was 26 volts on orbit 16 and 24 volts on orbit 63. 

This is within the specified operating range of the commutator. The 

unit on Mission 7051 was still operating at the end of the flight when 

the supply voltage was approximately 18 volts. 

Since it is not possible to predict when a commutator will fail, 

succeeding BIT units, with the exception of those used on Missions 7053 

and 7054, will be modified so that the commutator will run during the 

entire mission rather than being switched on and off for each read in 

and read out operation. This will greatly reduce the chances for future 

commutator failures. 

4. COMMENTS COMMENTS AND RECOMMENDATIONS. 

4. 1 Receipt of Data. 

The first data available for analysis were received on 10 

November. The remaining data for the first 65 orbits were received 

by 17 November and information regarding'the condition of the commutator 

on orbit 160 was received on 1 December. In general, the receipt of 

the data was much improved over the first mission. 

--Sreeffe_r_, 

SPECIAL HANDLnvc 
co IfAtAIMMEI5D FOR RELEASE 

File No. H-1155 

11 December 1964 SPECIAL HANDLING - page 7 - 

4. 2 System Modifications. 

All BIT units with the exception of the one scheduled for use 

on Mission 7054 and the one used on Mission 7053 will be modified 

so that the commutator will operate off of continuous vehicle power 

rather than programmed power. This will eliminate the on-off 

switching which should improve the reliability of the commutator 

operation. 

A request was received from Lockheed representatives to 

isolate the signal grounds in the BIT system from the chassis ground • 

because the chassis in turn is grounded to the vehicle frame.. This 

is for the purpose of reducing the ground loops in the vehicle frame for 

it is desired that all equipment on the vehicle be grounded at one point. 

To comply with this request, an electrically insulated plate was bonded 

to the base of the BIT box which isolates the signal ground from the 

vehicle frame. All units starting with Mission 7054 will be isolated 

from the 'ground in this manner. 

The modification which provides for the addition of the 256-

second output from the Time Reference Generator to the recorded 

data was made in all units starting with Mission 7054. This modification 

was described in the report on Mission 7051. 

"~SeeltisT„ 

SPECIAL HANDLING