# Experimental Research on the Dynamic Response of Floating Structures with Coatings Subjected to Underwater Explosion

Authors: Feng Xiao; Yong Chen; Yu Wang; Hongxing Hua; Dawei Zhu
Journal: Shock and Vibration
 (2014)

---

## Abstract

This paper presents an experimental investigation into the dynamic response of three free floating stiffened metal boxes with protective coatings subjected to underwater explosion (UNDEX). One box was kept intact while the other two were, respectively, covered with monolithic coatings and chiral honeycomb coatings. Three groups of live fire tests with different attack angles and stand-off distances were conducted. The acceleration on the stiffener and strain peak on the bottom hull were selected as the major comparative criterions. Test results show that the impulse transmitted to the structure at the initial stage can be reduced, owing to the coating flexibility and fluid-structure interaction mechanism. Consequently, the acceleration peaks induced by both shock wave and bubble pulse were reduced. The shock environment can be more effectively improved by honeycomb coating when compared with monolithic coating. Most of the strain peaks decreased to a certain extent, but some of them were notably manifested, especially for honeycomb coating. The test affirms the fact that soft coating can cause stress concentration on the shell that is in direct contact with the coating due to the impedance mismatch between the interfaces of materials. A softer rubber coating induces a greater magnitude of strain.


---

## Body

## 1. Introduction

In naval warfare, warship and submarine will inevitably suffer from underwater explosions. Unlike contact explosion, noncontact explosion does not break ship’s hull, but shock wave and bubble pulse usually cause great impact to ship and result in the permanent deformation of hull plate, breakdown of onboard equipment and casualty of personnel.How to moderate the devastating damage is very important and of great interest to ship designers. Many efforts have been taken to enhance the warship’s blast resistance since World War I (WWI). Early measures include reinforcing the hull and building the multilayer hull, but very complex engineering constructions are needed and big volumes are occupied. Such inconvenience prevents a further use of these techniques in modern ships [1]. Furthermore, existing devices and units mounted on the ship cannot meet the needs of good shock and vibration isolation at the same time [2]. Moreover, these units cannot reduce the total shock wave energy transmitted to ship. In 1990s, US navy [3] studied the shock resistance of a ship covered with protective coating. Research at the Naval Postgraduate School continues in an effort to understand the dynamic response of coated structures subjected to shock waves. The coating is a shock protective layer that can be plastered onto the ship hull’s wet surface in resistance to noncontact underwater explosion. It is stable under normal water pressure but very flexible under high shock loading. The working mechanism is mainly based on the energy absorption of coating through large deformation with a very short time interval as well as the wave reflection between the interfaces of materials with great acoustic impedance mismatch. Elastomers or viscoelastic rubbers are often used owing to their low modulus, high damping, large extensibility, recoverable deformation, low costs, and short cycle for repairing. Simple building technique merit makes it become a good choice at least when applied to weak or medium shock environment. In particular, nowadays special cavities are set in the coating for acoustic functions.Sandwich structures are widely used in engineering fields, especially in marine environment. Sandwich plates and beams have higher shock resistance than monolithic counterpart of equal mass under shock loading in both air and water [4–13]. Based on these results, sandwich coating has drawn much attention to the blast protection of ship subjected to noncontact underwater explosion. Chen et al. [14, 15] explored the attenuating effects of sandwich coating with square core coated onto the scaled ship model subjected to water blasts. Experimental results showed that soft core substantially reduce the transmitted impulse and the structure shock responses induced by the first shock wave can be lowered greatly after the polymer layer is coated. Elastic protective coating technique with soft core can be applied to weak or medium shock environment.Meanwhile, the influence of soft coating on the shock response of submerged structures is concerned. Permanent structure deformation may be undesirable if the structure is to be used even after the blast. Rubber coatings appear to concentrate shock energy within the structure for longer time periods. The study conducted by US Navy [3] revealed that if a steel panel was covered with a low density layer of glass microspheres, the damage to the steel panel caused by underwater explosion would increase. The thickness, shear deformation modulus, and sound impedance of coating had a large effect on structure stress. Kwon et al. [16] numerically studied the effect of coatings on metal cylinders in the underwater explosion environment. The results showed that the coating can concentrate shock energy within the structure under certain impact conditions. In a particular application, the occurrence of energy concentration is determined by a threshold value, below which adverse dynamic responses of a coated cylinder will occur. Additional research by Brasek [17] about one-dimensional system has demonstrated that the threshold value may depend upon the geometry and material properties of both coating and structures. Experimental research by Chen et al. [18] on the response of neoprene coated cylinder subjected to underwater explosions showed that, after the rubber layer is coated, the strain on the outer hull is notably manifested, especially in the hoop direction. However, no effect of stress concentration on the hull was observed in the research on the protective effect of a sandwich layer coated on ship hull [14].Considering the fact that some periodic honeycomb structures have good energy absorption capability and acoustic insulation property, which is very helpful for the acoustic stealth of ship, honeycomb rubber coatings are proposed. To date, most researches about honeycomb structures concentrate upon metallic material and studies on the dynamic response of honeycomb rubber coatings have been very limited. A comparative investigation on the water blast attenuation performance and stress concentration of the submerged structures covered with solid rubber coating and honeycomb rubber coating has not been conducted. Further, the influence of attack angle is also not considered. The dynamic response of a structure subjected to underwater explosion is a very complicated problem due to the interaction between fluid and structure. The outermost hull of a ship comprises plates welded to an array of stiffeners and the water blast response of plate structure is the basis of warship’s blast resistance [19, 20]. This paper presents an experimental investigation on the water blast responses of a free floating stiffened box before and after coatings are covered onto its bottom hull with different attack angles and stand-off distances. The principal aim of the paper is to explore the advantages and disadvantages of honeycomb coating relative to solid coating of the same material and weight in terms of the attenuation effect of coatings and the stress concentration on the hull. The main outline of this paper is as follows. First, the stiffened metal box and coatings are introduced. Second, the relevant material characteristics and quasistatic compression performance of coatings are presented. Third, the experimental procedures are detailed, including both test method and measuring instruments. The free field water pressure, wall pressure, acceleration in the time domain and frequency domain, and strain are compared. Last, an overall conclusion is made.


## 2. Experimental Research

Many other methods such as impact test can be used to study the performance of coating, but live UNDEX test is the most authentic way to evaluate the actual effect of the coating as the transient response of the hull with rubber coating subjected to underwater explosion is a very complex process, such as shock wave incidence and reflection, large deformation, hull motion, and strain and strain rate dependent behavior.


### 2.1. Target Models

Three stiffened metal boxes of the same geometry were manufactured. For convenience, we name the box without coatings model I and name the box with monolithic solid coatings model II and name the box with chiral honeycomb coatings model III. The total mass of model I is about 300 kg and the mass of all coatings is 76 kg. The weight of monolithic coatings is the same as that of honeycomb coatings. The global dimensions of the stiffened metal box are 1.5 m × 1.2 m × 0.4 m, as shown in Figure1(a). Four side plates were welded at the bottom ends for a waterproof. The bottom and side plates were reinforced by three longitudinal stiffeners and four transverse stiffeners. The stiffeners are 0.075 m high. The spacing of the longitudinal stiffeners is 0.3 m and the spacing of the transverse stiffeners is 0.4 m. All the plates and stiffeners were made by 0.004 m thick steel plate except the side plates which are 0.02 m thick. The model was designed to be simple but strong enough to withstand the shock wave. The material used is common mild steelA4, with the yielding stress beyond 250 MPa. Altogether 97 pieces of the coatings were plastered onto the outer surface of bottom hull with epoxy resin glue piece by piece, as shown in Figure 1(b). The gaps between different pieces were filled and leveled up with asphalt. The sooty part indicated by the arrowhead is the coating. The practical shape and detailed dimension of a single honeycomb coating are shown in Figure 2. Its global dimensions are 200 mm × 50 mm × 95 mm. The coating is 50 mm thick. Honeycomb cavities cover 20.7% of the whole volume. The plane of the honeycomb shown in Figure 2(b) is perpendicular to the plane of the hull.Test model of the stiffened box: (a) stiffened box without coatings, (b) stiffened box with coatings.
(a)
(b)Chiral honeycomb coating: (a) geometry, (b) dimension.
(a)
(b)


### 2.2. Mechanical Property of the Coating

The basic material used in the study is neoprene [15, 21]. The neoprene is a kind of synthetic rubber with sound flexibility and wearability that is produced by polymerization of chloroprene. In order to characterize the material with different levels of hardness, some specimens were tested on an INSTRON universal material testing machine. For the restriction of conditions, the biaxial and volumetric test data were unavailable. Figure 3 shows the stress-strain curves of three kinds of neoprene with different levels of hardness. Both tensile and compressive behaviors were included. The materials exhibit excellent flexibility as the specimen can be elongated up to 300% without any visible damage. The difference in compressive stress of three kinds of neoprene increases with the strain and their tensile stress is similar. Considering coating’s bearing capacity and long service life, the neoprene with shore hardness number 65 is used.Figure 3
Stress-strain curve of the neoprene with different shore hardness.Material properties are listed in Table1. Acoustic speed can be estimated as C
=
E
/
ρ, where E is the modulus and ρ is the density. ρ
·
c is the acoustic wave impedance. The acoustic impedance of neoprene and air are much smaller and the wave speed is lower than that of common steel. When the blast wave reaches the interface, reflection and transmission occur. As cavities are air filled, the acoustic impedance of honeycomb coating is greatly changed. Therefore, there exist great impedance mismatches in the transmission of waves.Table 1
Material properties.
Water
Neoprene
Air
Steel
ρ
·
c
(kg·m−2·s−1
)
1400000
224720
438.6
40472212
C (m/s)
1400
212
340
5188In addition to the mechanical property of base material, knowledge about the dynamic compression behavior of coatings facilitates the comprehension on its performance in underwater explosion environment. A whole piece of coating is so large that it is very difficult to test directly on common material test machines. As a substitution, a small piece of coating is cut from the box after live fire tests have been finished. The dimensions of the cut specimen are 200 mm × 200 mm. The uniaxial compression test was performed on a 100 KN Zwick general material test machine. During tests, the specimen was clamped between two thick circular plates. Only quasistatic compression test was performed. The quasistatic compression velocity was selected as 10 mm/min and applied to the coating’s upper surface in Figure2(b). Figure 4 shows the comparison of the stress-strain curves of monolithic coating and honeycomb coating. The nominal stress of the structure is defined as the measured force divided by the cross-sectional area of samples. The nominal strain of the structure is the crushing distance divided by the initial thickness of samples. It can be seen that honeycomb coating has much larger compressibility than monolithic one. There is not a high initial peak on the curves. The stress of monolithic coating is higher and the densification takes place much earlier with the structural stiffness when compared with that of honeycomb coating. When the honeycomb coating is loaded, the energy is absorbed by cell buckling. Soft coating decreases the level of stress at the expense of total compression distance. Under the same compression distance, honeycomb coating absorbs less energy. As a result, it is easy to deform.Figure 4
Stress-strain curves of monolithic coating and honeycomb coating.


### 2.3. Underwater Explosion Test

#### 2.3.1. Test Event

All tests were conducted in China Ship Scientific Research Center. A semispherical lake is 15 meters in depth and 80 meters in diameter, as shown in Figure5. The test model was freely located in the middle of two interconnected floating platforms, which were supported by two buoyancy tanks and used to place instruments. Figure 6 shows the sketch of test system.D1 is the waterline depth of about 0.2 m. R is the stand-off distance between the explosive charge and the center of bottom surface. β is the attack angle.L2 is the distance between the explosive charge and the free field water pressure transducer (P2). The shock factor representing the shock energy is defined as SF
=
W
/
R [22]. The SF varies from 0.12 to 0.18. We chose to fix the explosive charge weight (W) and vary the loading intensity by the change of the stand-off distance and attack angle. All test events were listed in Table 2. Nine events were attempted, including three predetermined stand-off distances (4.39 m, 2.83 m, and 7.5 m) and two attack angles (30
°, 9
0
°). As long as equal blast loadings are guaranteed, assessments can be made. The charge weight in all events is 1 kg. Before normal tests, a trial explosion was done in advance to examine the instruments.Table 2
Test events.
Test event number
Model
W  (kg)
R (m)
L
1
(m)
β (°)
SF
1
I
1
4.39
7.00
30
0.12
2
II
1
4.39
7.00
30
0.12
3
III
1
4.39
7.00
30
0.12
4
I
1
2.83
4.30
30
0.18
5
II
1
2.83
4.30
30
0.18
6
III
1
2.83
4.30
30
0.18
7
I
1
7.50
−0.60
90
0.14
8
II
1
7.50
−0.60
90
0.14
9
III
1
7.50
−0.60
90
0.14Figure 5
Underwater explosion test.Figure 6
Sketch of test system.


#### 2.3.2. Test Position and Instrumentation

As indicated in Figure6, one wall pressure transducer (P1) to explore the fluid-structure interaction as well as the wave reflection characteristics with different targets is placed about 5 mm vertically distant from the center of the bottom hull. One free field water pressure transducer (P2) to distinguish blast loads is suspended at the water depth of 4 m. Figure 7 depicts the test positions, viewed from the bottom. Three accelerometers on the stiffeners and eight strain gauges on the inner bottom hull were used. All accelerometers were to measure the positive acceleration towards the sky.E1,E3,E5, andE7 are the transverse gauges.E2,E4,E6, andE8 are the longitudinal gauges.Figure 7
Locations of accelerometer and strain gauges.The instrumentation included transducers, preamplifiers, a data recording system, and some auxiliary devices. Two PCB 138A05 pressure transducers with linearity within 2% and range up to 35 MPa were used to monitor water pressure. The accelerometers used are B&K 4393 piezoelectric accelerometers that have a maximum operational shock range of ±25 000 g, with upper frequency limit 16.5 kHz. In order to avoid overloading, all accelerometers are fixed at aluminum adaptors that are used as mechanical filters, with cut-off frequency around 3 KHz. Strain responses were tested with eight strain meters and manifested with a DC amplifier (DH3842). All gauges are of resistance style, with 350 ohm resistance. A suit of 32-channel Odyssey high speed data recording device is used to record all electrical signals after detonation of the explosive. The pressure data are recorded with a maximum sampling frequency of 5 MHz/Ch (channel). The selected sampling rate is 50 KHz/Ch and 20 KHz/Ch for acceleration and strain records, respectively. The TNT (trinitrotoluene) is fabricated in the shape of a right cylinder formed by pressing it into a hollow tube constructed from PMMA (polymethyl methacrylate) and initiated with an exploding bridge wire detonator. The explosive device is fixed by the nylon cords that are fastened on the platforms. By adjusting the length of the cords, the explosive can be fixed at a scheduled position.


## 2.1. Target Models

Three stiffened metal boxes of the same geometry were manufactured. For convenience, we name the box without coatings model I and name the box with monolithic solid coatings model II and name the box with chiral honeycomb coatings model III. The total mass of model I is about 300 kg and the mass of all coatings is 76 kg. The weight of monolithic coatings is the same as that of honeycomb coatings. The global dimensions of the stiffened metal box are 1.5 m × 1.2 m × 0.4 m, as shown in Figure1(a). Four side plates were welded at the bottom ends for a waterproof. The bottom and side plates were reinforced by three longitudinal stiffeners and four transverse stiffeners. The stiffeners are 0.075 m high. The spacing of the longitudinal stiffeners is 0.3 m and the spacing of the transverse stiffeners is 0.4 m. All the plates and stiffeners were made by 0.004 m thick steel plate except the side plates which are 0.02 m thick. The model was designed to be simple but strong enough to withstand the shock wave. The material used is common mild steelA4, with the yielding stress beyond 250 MPa. Altogether 97 pieces of the coatings were plastered onto the outer surface of bottom hull with epoxy resin glue piece by piece, as shown in Figure 1(b). The gaps between different pieces were filled and leveled up with asphalt. The sooty part indicated by the arrowhead is the coating. The practical shape and detailed dimension of a single honeycomb coating are shown in Figure 2. Its global dimensions are 200 mm × 50 mm × 95 mm. The coating is 50 mm thick. Honeycomb cavities cover 20.7% of the whole volume. The plane of the honeycomb shown in Figure 2(b) is perpendicular to the plane of the hull.Test model of the stiffened box: (a) stiffened box without coatings, (b) stiffened box with coatings.
(a)
(b)Chiral honeycomb coating: (a) geometry, (b) dimension.
(a)
(b)


## 2.2. Mechanical Property of the Coating

The basic material used in the study is neoprene [15, 21]. The neoprene is a kind of synthetic rubber with sound flexibility and wearability that is produced by polymerization of chloroprene. In order to characterize the material with different levels of hardness, some specimens were tested on an INSTRON universal material testing machine. For the restriction of conditions, the biaxial and volumetric test data were unavailable. Figure 3 shows the stress-strain curves of three kinds of neoprene with different levels of hardness. Both tensile and compressive behaviors were included. The materials exhibit excellent flexibility as the specimen can be elongated up to 300% without any visible damage. The difference in compressive stress of three kinds of neoprene increases with the strain and their tensile stress is similar. Considering coating’s bearing capacity and long service life, the neoprene with shore hardness number 65 is used.Figure 3
Stress-strain curve of the neoprene with different shore hardness.Material properties are listed in Table1. Acoustic speed can be estimated as C
=
E
/
ρ, where E is the modulus and ρ is the density. ρ
·
c is the acoustic wave impedance. The acoustic impedance of neoprene and air are much smaller and the wave speed is lower than that of common steel. When the blast wave reaches the interface, reflection and transmission occur. As cavities are air filled, the acoustic impedance of honeycomb coating is greatly changed. Therefore, there exist great impedance mismatches in the transmission of waves.Table 1
Material properties.
Water
Neoprene
Air
Steel
ρ
·
c
(kg·m−2·s−1
)
1400000
224720
438.6
40472212
C (m/s)
1400
212
340
5188In addition to the mechanical property of base material, knowledge about the dynamic compression behavior of coatings facilitates the comprehension on its performance in underwater explosion environment. A whole piece of coating is so large that it is very difficult to test directly on common material test machines. As a substitution, a small piece of coating is cut from the box after live fire tests have been finished. The dimensions of the cut specimen are 200 mm × 200 mm. The uniaxial compression test was performed on a 100 KN Zwick general material test machine. During tests, the specimen was clamped between two thick circular plates. Only quasistatic compression test was performed. The quasistatic compression velocity was selected as 10 mm/min and applied to the coating’s upper surface in Figure2(b). Figure 4 shows the comparison of the stress-strain curves of monolithic coating and honeycomb coating. The nominal stress of the structure is defined as the measured force divided by the cross-sectional area of samples. The nominal strain of the structure is the crushing distance divided by the initial thickness of samples. It can be seen that honeycomb coating has much larger compressibility than monolithic one. There is not a high initial peak on the curves. The stress of monolithic coating is higher and the densification takes place much earlier with the structural stiffness when compared with that of honeycomb coating. When the honeycomb coating is loaded, the energy is absorbed by cell buckling. Soft coating decreases the level of stress at the expense of total compression distance. Under the same compression distance, honeycomb coating absorbs less energy. As a result, it is easy to deform.Figure 4
Stress-strain curves of monolithic coating and honeycomb coating.


## 2.3. Underwater Explosion Test

### 2.3.1. Test Event

All tests were conducted in China Ship Scientific Research Center. A semispherical lake is 15 meters in depth and 80 meters in diameter, as shown in Figure5. The test model was freely located in the middle of two interconnected floating platforms, which were supported by two buoyancy tanks and used to place instruments. Figure 6 shows the sketch of test system.D1 is the waterline depth of about 0.2 m. R is the stand-off distance between the explosive charge and the center of bottom surface. β is the attack angle.L2 is the distance between the explosive charge and the free field water pressure transducer (P2). The shock factor representing the shock energy is defined as SF
=
W
/
R [22]. The SF varies from 0.12 to 0.18. We chose to fix the explosive charge weight (W) and vary the loading intensity by the change of the stand-off distance and attack angle. All test events were listed in Table 2. Nine events were attempted, including three predetermined stand-off distances (4.39 m, 2.83 m, and 7.5 m) and two attack angles (30
°, 9
0
°). As long as equal blast loadings are guaranteed, assessments can be made. The charge weight in all events is 1 kg. Before normal tests, a trial explosion was done in advance to examine the instruments.Table 2
Test events.
Test event number
Model
W  (kg)
R (m)
L
1
(m)
β (°)
SF
1
I
1
4.39
7.00
30
0.12
2
II
1
4.39
7.00
30
0.12
3
III
1
4.39
7.00
30
0.12
4
I
1
2.83
4.30
30
0.18
5
II
1
2.83
4.30
30
0.18
6
III
1
2.83
4.30
30
0.18
7
I
1
7.50
−0.60
90
0.14
8
II
1
7.50
−0.60
90
0.14
9
III
1
7.50
−0.60
90
0.14Figure 5
Underwater explosion test.Figure 6
Sketch of test system.


### 2.3.2. Test Position and Instrumentation

As indicated in Figure6, one wall pressure transducer (P1) to explore the fluid-structure interaction as well as the wave reflection characteristics with different targets is placed about 5 mm vertically distant from the center of the bottom hull. One free field water pressure transducer (P2) to distinguish blast loads is suspended at the water depth of 4 m. Figure 7 depicts the test positions, viewed from the bottom. Three accelerometers on the stiffeners and eight strain gauges on the inner bottom hull were used. All accelerometers were to measure the positive acceleration towards the sky.E1,E3,E5, andE7 are the transverse gauges.E2,E4,E6, andE8 are the longitudinal gauges.Figure 7
Locations of accelerometer and strain gauges.The instrumentation included transducers, preamplifiers, a data recording system, and some auxiliary devices. Two PCB 138A05 pressure transducers with linearity within 2% and range up to 35 MPa were used to monitor water pressure. The accelerometers used are B&K 4393 piezoelectric accelerometers that have a maximum operational shock range of ±25 000 g, with upper frequency limit 16.5 kHz. In order to avoid overloading, all accelerometers are fixed at aluminum adaptors that are used as mechanical filters, with cut-off frequency around 3 KHz. Strain responses were tested with eight strain meters and manifested with a DC amplifier (DH3842). All gauges are of resistance style, with 350 ohm resistance. A suit of 32-channel Odyssey high speed data recording device is used to record all electrical signals after detonation of the explosive. The pressure data are recorded with a maximum sampling frequency of 5 MHz/Ch (channel). The selected sampling rate is 50 KHz/Ch and 20 KHz/Ch for acceleration and strain records, respectively. The TNT (trinitrotoluene) is fabricated in the shape of a right cylinder formed by pressing it into a hollow tube constructed from PMMA (polymethyl methacrylate) and initiated with an exploding bridge wire detonator. The explosive device is fixed by the nylon cords that are fastened on the platforms. By adjusting the length of the cords, the explosive can be fixed at a scheduled position.


## 2.3.1. Test Event

All tests were conducted in China Ship Scientific Research Center. A semispherical lake is 15 meters in depth and 80 meters in diameter, as shown in Figure5. The test model was freely located in the middle of two interconnected floating platforms, which were supported by two buoyancy tanks and used to place instruments. Figure 6 shows the sketch of test system.D1 is the waterline depth of about 0.2 m. R is the stand-off distance between the explosive charge and the center of bottom surface. β is the attack angle.L2 is the distance between the explosive charge and the free field water pressure transducer (P2). The shock factor representing the shock energy is defined as SF
=
W
/
R [22]. The SF varies from 0.12 to 0.18. We chose to fix the explosive charge weight (W) and vary the loading intensity by the change of the stand-off distance and attack angle. All test events were listed in Table 2. Nine events were attempted, including three predetermined stand-off distances (4.39 m, 2.83 m, and 7.5 m) and two attack angles (30
°, 9
0
°). As long as equal blast loadings are guaranteed, assessments can be made. The charge weight in all events is 1 kg. Before normal tests, a trial explosion was done in advance to examine the instruments.Table 2
Test events.
Test event number
Model
W  (kg)
R (m)
L
1
(m)
β (°)
SF
1
I
1
4.39
7.00
30
0.12
2
II
1
4.39
7.00
30
0.12
3
III
1
4.39
7.00
30
0.12
4
I
1
2.83
4.30
30
0.18
5
II
1
2.83
4.30
30
0.18
6
III
1
2.83
4.30
30
0.18
7
I
1
7.50
−0.60
90
0.14
8
II
1
7.50
−0.60
90
0.14
9
III
1
7.50
−0.60
90
0.14Figure 5
Underwater explosion test.Figure 6
Sketch of test system.


## 2.3.2. Test Position and Instrumentation

As indicated in Figure6, one wall pressure transducer (P1) to explore the fluid-structure interaction as well as the wave reflection characteristics with different targets is placed about 5 mm vertically distant from the center of the bottom hull. One free field water pressure transducer (P2) to distinguish blast loads is suspended at the water depth of 4 m. Figure 7 depicts the test positions, viewed from the bottom. Three accelerometers on the stiffeners and eight strain gauges on the inner bottom hull were used. All accelerometers were to measure the positive acceleration towards the sky.E1,E3,E5, andE7 are the transverse gauges.E2,E4,E6, andE8 are the longitudinal gauges.Figure 7
Locations of accelerometer and strain gauges.The instrumentation included transducers, preamplifiers, a data recording system, and some auxiliary devices. Two PCB 138A05 pressure transducers with linearity within 2% and range up to 35 MPa were used to monitor water pressure. The accelerometers used are B&K 4393 piezoelectric accelerometers that have a maximum operational shock range of ±25 000 g, with upper frequency limit 16.5 kHz. In order to avoid overloading, all accelerometers are fixed at aluminum adaptors that are used as mechanical filters, with cut-off frequency around 3 KHz. Strain responses were tested with eight strain meters and manifested with a DC amplifier (DH3842). All gauges are of resistance style, with 350 ohm resistance. A suit of 32-channel Odyssey high speed data recording device is used to record all electrical signals after detonation of the explosive. The pressure data are recorded with a maximum sampling frequency of 5 MHz/Ch (channel). The selected sampling rate is 50 KHz/Ch and 20 KHz/Ch for acceleration and strain records, respectively. The TNT (trinitrotoluene) is fabricated in the shape of a right cylinder formed by pressing it into a hollow tube constructed from PMMA (polymethyl methacrylate) and initiated with an exploding bridge wire detonator. The explosive device is fixed by the nylon cords that are fastened on the platforms. By adjusting the length of the cords, the explosive can be fixed at a scheduled position.


## 3. Results and Discussions

### 3.1. Pressure Records

#### 3.1.1. Free Field Pressure-Time Profiles

Figure8 shows the typical free field water pressure-time history ofP2 (event 1). The initial shock wave within 4 ms is magnified. It is seen that the pressure rises to a peak instantaneously upon the arrival of primary shock wave. Subsequently, it decreases at a nearly exponential rate. The reflected wave from the structure can also be distinguished, arriving at 6.53 ms after the shock wave passes. The secondary shock is subsequently experienced, due to the damped oscillation of the gas bubble that contains explosive products. The pressure peak of the shock wave is much higher and its duration is shorter compared with that of the bubble pulsation. The incident shock wave arrives instantaneously with a peak of 6.59 MPa and then decays rapidly within about 0.4 ms. The first bubble pulsation arrives at 218 ms, with a broader profile and a low peak of 1.025 MPa. The bubble pulse pressure peak is 15.5% of the shock wave peak.Free field water pressure-time history (event 1): (a) record within 400 ms, (b) shock wave within 4 ms.
(a)
(b)Accurate shock pressure loading is important. Table3 lists all the free field pressure peaks in the shock wave phase. Considering the broad profile characteristics of bubble pulse, no comparison of their peaks is made. The free field theoretical peaks were obtained by Cole’s empirical formula P
m
=
52.4
(
W
1
/
3
/
R
)
1.13 [23]. As stand-off changes from 2.83 m to 7.5 m, the free field test peak increases from 5.79 MPa to 12.02 MPa. The deviations between the theoretical peak and the test peak range from 0.6% (event 1 and event 8) to 5.3% (event 2). The deviation is within 5.5%, which indicates that the explosion processes guarantee the following comparisons are authentic.Table 3
Summary of free field water pressure, wall pressure, and impulse.
Event number
Model
L
2 (m)
Theoretical peak (MPa)
Test peak (MPa)
Deviation (%)
Wall pressure peak  (MPa)
Impulse (Pa*s)
1
I
6.2
6.63
6.59
−0.60
3.20
117.6
2
II
6.2
6.69
6.33
−5.3
2.16
59.4
3
III
6.9
5.91
5.79
−2.0
2.22
52.6
4
I
3.6
12.22
12.02
−1.6
8.12
215
5
II
3.7
12.02
11.9
−1.0
5.53
204
6
III
6.1
6.79
6.89
1.5
5.13
118
7
I
3.9
11.38
11.59
1.8
6.14
293.8
8
II
3.8
11.63
11.69
−0.60
6.31
269.3
9
III
4.0
10.96
11.1
1.3
4.45
117.8


#### 3.1.2. Wall Pressure-Time Profiles

The wall pressure-time profiles are very helpful in understanding the working mechanism of the coating. The wall pressure is the result of blast wave, divergent rarefaction wave, and reflected wave. Figure9 presents the comparison of the wall pressure-time histories. Several distinct phases can be observed, including incidence, reflection, and cavitation. The whole process begins with the direct shock wave from the explosive, which is immediately followed by the reflected wave and later a tension wave produced by the onset of the cavitation near the bottom hull. As the face sheet moves, the fluid-structure interaction changes and the reflection is significantly reduced. The subsequent broad pressure wave indicates the repeating elastic deformation of the hull.Comparison of the wall pressure-time histories: (a) 2.83 m stand-off, (b) 7.5 m stand-off.
(a)
(b)In Figure9(a), the first incident wave peaks of coated models are much smaller than that of uncoated model as listed in Table 3. The reflected wave of model II is obvious. Moreover, its reflected wave peak is larger and the pulse duration is longer than that of the other two. The reflected signals of model III are much fewer. The negative pressure of model I takes place early because the face sheet moves fast under the incident shock wave with a high pressure peak, but its duration is short. In Figure 9(b), the prominent discrepancies of the wall pressure waveform can be observed. The first incident wave peak of model III significantly decreases. The reflected wave peak of model I is the largest and its duration is very long. The reflected wave of model II is still obvious while the reflected signals of model III are faded. This is mainly due to the lower reflection characteristic of honeycomb coating. Another difference is that the cavitation for model III takes place much earlier than the other two, which results in a much narrower time span of the first incident shock wave. This should be attributed to the soft coating, which deforms much easier and faster when the shock wave impinges the face sheet.The impulse transmitted to main structure is considered as the primary parameter that will determine the response. We compare the total impulse with the time span of 0.4 ms as listed in Table4. The impulse was calculated by the time integration of the wall pressure-time history. For 4.39 m stand-off, the impulses of model II and model III are, respectively, reduced by 49% and 55% of the impulse of model I. For 2.83 m stand-off, the impulses of model II and model III are, respectively, reduced by 5% and 45%. For 7.5 m stand-off, the impulses of model II and model III are, respectively, reduced by 8% and 60%. The level of impulse reduction depends upon the time, the resistance to the motion of the front face sheet, and the cavitation after the shock reflection, which in turn is affected by the coating structure. As the front face is moving, a rarefaction wave is radiated back into the fluid from the front face. The dispersion of the incident pressure is enabled by sequential crush of the coating. In addition, the acoustic mismatch between the water and the hull enhances the fluid-structure interaction effect. These factors result in an impulse reduction. The attenuation effect becomes outstanding because the reduction in impulse is facilitated by soft coating. As a result, lower structure responses induced by shock wave are anticipated in the subsequent sections.Table 4
Acceleration peaks unit (g).
Event
A
1
A
4
A
5
Average
1
624
436
1741
933
2
443
394
1480
772
3
182
266
360
269
4
948
738
2672
1452
5
762
655
2727
1381
6
301
398
648
449
7
945
795
3841
1860
8
858
782
3433
1691
9
335
426
731
497


### 3.2. Acceleration Records

#### 3.2.1. Acceleration-Time Profiles

Figure10 shows the detailed acceleration histories at locationA5. Despite some differences in these records, basic trends are consistent. An abrupt jump of signal indicates that the target responds to the arrival of shock wave and bubble pulse. Moreover, there exist fewer high frequency components in the coated models’ records, which will be verified by later spectra analysis. It is attributed to the high viscoelastic characteristics of the coatings. Acceleration peaks are compared to evaluate the protective effect. As expected, the peak induced by the shock wave is much larger than that induced by the bubble pulse. The maximum acceleration of model I for the shock wave and the first bubble pulse, respectively, reaches 1740 g and 338 g. The maximum acceleration of model II for the shock wave and the first bubble pulse, respectively, reaches 1480 g and 303 g. The maximum acceleration of model III for the shock wave and the first bubble pulse, respectively, reaches 360 g and 82 g. The initial acceleration peak is reduced drastically after the coating is covered. The maximum response to the shock wave decreased from 1741 g to 360 g, and the maximum response to the bubble pulse decreased from 338 g to 82 g. Honeycomb coating has a potential advantage due to the possibility of controlling the transferred force.Acceleration histories at locationA5: (a) event 1, (b) event 2, and (c) event 3.
(a)
(b)
(c)As a general comparison, Table4 summarizes all the measured acceleration peaks in the shock wave phase. As the secondary shock waves have much smaller peaks and are usually much less damaging than the primary shock wave, the peaks caused by the bubble pulse are not given. Furthermore, the average peak of three test locations (A1,A4, andA5) corresponding to each event is presented. For 4.39 m stand-off, the average peaks of model II and model III are, respectively, reduced by 17.2% and 71.1% of the average peak of model I. For 2.83 m stand-off, the average peaks of model II and model III are, respectively, reduced by 4.9% and 69%. For 7.5 m stand-off, the average peaks of model II and model III are, respectively, reduced by 9.1% and 73.2%. Prominent attenuation effects of model III are revealed. It can also be seen that the attenuation effect is related to coating as well as stand-off. When the stand-off equals 4.39 m, the attenuation effect is significant.To evaluate the attenuation effect conveniently, the acceleration peak ratio is defined between coated model and uncoated model. If it is less than unity, the acceleration is reduced and vice versa. Figure11 shows the acceleration peak ratio. The stand-off of number 1~number 3 is 4.39 m. The stand-off of number 4~number 6 is 2.83 m. The stand-off of number 7~number 9 is 7.5 m. It can be seen that nearly all the peaks decrease after the coating is covered, and only one peak ratio (number 6) increases to 1.02. This fact indicates that the attenuation effects of the coatings are global in nature. When the stand-off equals 4.39 m, the maximum acceleration isolation of these coatings appears. The peak ratio of model II at locationA1 decreases to 0.7 (number 1) and 30% of the acceleration of model I is cut off. The ratio of model III at locationA5 decreases to 0.17 (number 3) and 83% of the acceleration of model I is cut off. From the minimum acceleration isolation, the ratio of model III atA4 decreases to 0.6 (number 2) and at least 40% of the acceleration of model I can be cut off.Figure 11
Acceleration peak ratio.In general, the attenuation effect of model III is much better than that of model II. The shock environment can be effectively improved by honeycomb coating. On one hand, due to the impedance mismatch, most of the incident shock energy is isolated by the coating. Meanwhile, when stress wave is transmitted from “hard” material into “soft” material, it will be reflected and turn into tensile wave, resulting in the wave decaying. On the other hand, as honeycomb cell walls provide structural support and regulate the stress to the back plate, they will deform and collapse sequentially when the coating is impinged by water blast wave. The cavities, like closed air chambers, can provide adequate space for the large deformation of cell walls and desired blast mitigation. The results show that the structure with low impedance and high energy absorption capacity should be used as the protective layer.


#### 3.2.2. Shock Response Spectrum

Shock response spectrum (SRS) is an effective method in understanding the frequency component of dynamic response of the structure subjected to shock input [3]. By comparing SRS curves of uncoated model and coated model, the influence of the coating on the transient response of the model can be partly revealed. As a comparison, the shock response spectrum from acceleration history of three models at locationA5 (7.5 m stand-off) is plotted in Figure 12.A5 test point is selected because the shock intensity is the highest and more structural modes can be excited. In spite of some differences between the SRS curves derived from different locations, common trend is similar. So other accelerometers are not presented. The analysis frequency band is between 1 Hz and 10 kHz.Figure 12
Shock response spectrums of three models (7.5 m stand-off,A5 test point).It can be seen that in the frequency range lower than 30 Hz and higher than 100 Hz, there is a distinct reduction of SRS value after the coatings are covered. The higher the frequency is, the more obvious the attenuation effect is. The protective effect of model III in high frequency range is better than that in low frequency range. At high frequencies, the spectrum curve is mainly controlled by local structural deformation and the energy decays rapidly as the damping effect predominates. Considering the zero drift of accelerometers, the response below 2 Hz is untrustworthy. The difference between two coated models at low frequencies is small, and the effect of model II is slightly better than that of model II. Comparing with high frequency range, the frequency band between 30 Hz and 80 Hz is the magnification region. Prominent peaks can be observed, which correspond to the global bending. The effects of coated models seem limited. Moreover, the response of model III is larger than that of model II.


### 3.3. Strain Records

Figure13 shows the detailed strain histories with 1500 ms atE7. Like acceleration records, the strain responses to both shock wave and several bubble pulses can be distinguished. The maximum strain response to the bubble pulse is much smaller than that to the shock wave. The strain peaks of coated models are attenuated, especially for the shock wave. High frequency signal decays and vibration dominates at low frequency. Owing to the high damping of the coatings, there exist fewer high frequency components for coated models.Strain histories at locationE7: (a) event 7, (b) event 8, and (c) event 9.
(a)
(b)
(c)Table5 lists all the measured strain peaks in the shock wave phase. Only tensile strain is considered, which is often selected as a failure criterion of ductility. It is difficult to evaluate the actual attention effect of the coating from only a few points, so we have to make an evaluation by a statistic method. The average strain exceptE4 corresponding to each event is listed in Table 4. For 4.39 m stand-off, the average peak ratios of model II and model III, respectively, decrease to 0.79 and 0.68 of the average peak of model I. For 2.83 m stand-off, the peak ratios of model II and model III, respectively, decrease to 0.87 and 0.77. For 7.5 m stand-off, the peak ratios of model II and model III are, respectively, closed to 1 and 0.76. Like acceleration records, when the stand-off is 4.39 m, the average peak ratio of coated models is the minimum. The average strain of coated model decreases to some extent, except for event 8. The peak ratios of model II range from 0.79 to 1, and the ratios of model III range from 0.68 to 0.77. The results prove that better overall strain attenuation can be obtained by the honeycomb coating.Table 5
Strain peaks (μ
ε).
Event
E
1
E
2
E
3
E
4
E
5
E
6
E
7
E
8
Average (exceptE
4)
1
844
666
752
—
970
718
887
595
776
2
598
563
789
545
835
457
646
424
616
3
839
513
369
178
362
345
475
825
532
4
985
861
1000
—
1472
1237
1261
622
1062
5
829
807
1229
1155
1306
686
1005
636
928
6
965
510
655
786
604
735
825
1434
818
7
1086
787
1377
—
1602
1343
1650
682
1218
8
1108
859
1647
1219
1512
1029
1556
840
1221
9
884
633
773
892
926
936
1081
1315
935Similarly, strain peak ratio is defined between coated model and uncoated model. Figure14 shows the transverse ratio and longitudinal ratio. The stand-off of number 1~number 4 is 4.39 m. The stand-off of number 5~number 8 is 2.83 m. The stand-off of number 9~number 12 is 7.5 m.Strain peak ratio: (a) transverse direction, (b) longitudinal direction.
(a)
(b)It can be seen that the strain attention effect is related to stand-off and test point. The large strain isolation of model II appears atE6 under three stand-offs. For 4.39 m stand-off, the large isolation of model III appears atE3 toE7. For 2.83 m stand-off, the large isolation of model III appears atE5 andE6. For 7.5 m stand-off, the large isolation of model III appears atE3 andE5.After the coating is covered, the strain peaks at most of the test points decrease in some degree. The minimum peak ratio of model III is 0.37 corresponding to number 3 of Figure14(a), and the minimum ratio of model II is 0.55 corresponding to number 7 of Figure 14(b). The maximum strain isolation of model III is larger than that of model II. However, the prominent strain enlargements of coated models at some test points are also presented. This fact indicates that no protective effects can be brought by coatings and the attenuation effects are restricted to local area. For model II, the strain enlargement exists in number 2, number 6, number 9, and number 10 of Figure 14(a) and number 8, number 9, and number 12 of Figure 14(b). The peak ratios range from 1.02 to 1.22. For model III, the strain enlargement exists in number 4, number 8, and number 12 of Figure 14(b). The peak ratios range from 1.39 to 2.39. Furthermore, in number 1 and number 5 of Figure 14(a) and number 4, number 7, number 8, and number 12 of Figure 14(b), model III sustains greater shock damage than model II under identical testing conditions. It indicates that the stress concentration is more evident for the coating with lower impedance. The strain can be manifested over two times at the most execrable locations. This should be attributed to the fact that the stress wave transmitted from water to steel shell via coating cannot be released outward timely for the impedance mismatch between hull and coating. Therefore, the shock energy is accumulated before it is dissipated by structural damping and the stress concentration takes place. As Kwon points out that, for the impedance mismatch between rubber and steel, when stress wave is transmitted into inner steel plate, the stress will concentrate when the impedance of rubber is lower than a certain limit. The softer elastic coating inhibits release of stress wave energy from the structure to the surrounding water. When stress wave is transmitted from “soft” material into “hard” material, the intensity of transmission wave will exceed that of incident wave. The excess energy is manifested in the form of higher stresses in the underlying structure. Therefore, a higher stress state accompanies a coating with smaller characteristic impedance. In addition, a noticeable phenomenon is that the strain of model II is manifested in both directions while the strain of model III only is manifested in the longitudinal direction. The discrepancy is due to the difference of wave length in two directions. Meanwhile, like the strain attention effect, the strain enlargement of the coating is related to stand-off and test point. When stand-off is 2.83 m, the strain enlargements of two coated models are the maximum. There exist four strain enlargement points (E1,E2,E3, andE8) for model II, while there is only one point (E8) for model III. When the test point is close to the explosive charge, its strain enlargement becomes evident.In general, the strain on the outer hull in direct contact with the coating is often manifested. The amplification factor should be related to stress wave type and direction as well as other factors such as the wave impedance mismatch between structure and coating. Results show that the stress concentration is a very complicated nonlinear phenomenon and affected by almost all kinds of factors in the whole underwater explosion process. Softer coating with low acoustic impedance generally tends to concentrate the stress wave energy in the hull. The stress concentration induced by the impedance mismatch cannot be neglected. Such a response may entail increased strains and internal energy causing plastic deformation and failure of the structure.


## 3.1. Pressure Records

### 3.1.1. Free Field Pressure-Time Profiles

Figure8 shows the typical free field water pressure-time history ofP2 (event 1). The initial shock wave within 4 ms is magnified. It is seen that the pressure rises to a peak instantaneously upon the arrival of primary shock wave. Subsequently, it decreases at a nearly exponential rate. The reflected wave from the structure can also be distinguished, arriving at 6.53 ms after the shock wave passes. The secondary shock is subsequently experienced, due to the damped oscillation of the gas bubble that contains explosive products. The pressure peak of the shock wave is much higher and its duration is shorter compared with that of the bubble pulsation. The incident shock wave arrives instantaneously with a peak of 6.59 MPa and then decays rapidly within about 0.4 ms. The first bubble pulsation arrives at 218 ms, with a broader profile and a low peak of 1.025 MPa. The bubble pulse pressure peak is 15.5% of the shock wave peak.Free field water pressure-time history (event 1): (a) record within 400 ms, (b) shock wave within 4 ms.
(a)
(b)Accurate shock pressure loading is important. Table3 lists all the free field pressure peaks in the shock wave phase. Considering the broad profile characteristics of bubble pulse, no comparison of their peaks is made. The free field theoretical peaks were obtained by Cole’s empirical formula P
m
=
52.4
(
W
1
/
3
/
R
)
1.13 [23]. As stand-off changes from 2.83 m to 7.5 m, the free field test peak increases from 5.79 MPa to 12.02 MPa. The deviations between the theoretical peak and the test peak range from 0.6% (event 1 and event 8) to 5.3% (event 2). The deviation is within 5.5%, which indicates that the explosion processes guarantee the following comparisons are authentic.Table 3
Summary of free field water pressure, wall pressure, and impulse.
Event number
Model
L
2 (m)
Theoretical peak (MPa)
Test peak (MPa)
Deviation (%)
Wall pressure peak  (MPa)
Impulse (Pa*s)
1
I
6.2
6.63
6.59
−0.60
3.20
117.6
2
II
6.2
6.69
6.33
−5.3
2.16
59.4
3
III
6.9
5.91
5.79
−2.0
2.22
52.6
4
I
3.6
12.22
12.02
−1.6
8.12
215
5
II
3.7
12.02
11.9
−1.0
5.53
204
6
III
6.1
6.79
6.89
1.5
5.13
118
7
I
3.9
11.38
11.59
1.8
6.14
293.8
8
II
3.8
11.63
11.69
−0.60
6.31
269.3
9
III
4.0
10.96
11.1
1.3
4.45
117.8


### 3.1.2. Wall Pressure-Time Profiles

The wall pressure-time profiles are very helpful in understanding the working mechanism of the coating. The wall pressure is the result of blast wave, divergent rarefaction wave, and reflected wave. Figure9 presents the comparison of the wall pressure-time histories. Several distinct phases can be observed, including incidence, reflection, and cavitation. The whole process begins with the direct shock wave from the explosive, which is immediately followed by the reflected wave and later a tension wave produced by the onset of the cavitation near the bottom hull. As the face sheet moves, the fluid-structure interaction changes and the reflection is significantly reduced. The subsequent broad pressure wave indicates the repeating elastic deformation of the hull.Comparison of the wall pressure-time histories: (a) 2.83 m stand-off, (b) 7.5 m stand-off.
(a)
(b)In Figure9(a), the first incident wave peaks of coated models are much smaller than that of uncoated model as listed in Table 3. The reflected wave of model II is obvious. Moreover, its reflected wave peak is larger and the pulse duration is longer than that of the other two. The reflected signals of model III are much fewer. The negative pressure of model I takes place early because the face sheet moves fast under the incident shock wave with a high pressure peak, but its duration is short. In Figure 9(b), the prominent discrepancies of the wall pressure waveform can be observed. The first incident wave peak of model III significantly decreases. The reflected wave peak of model I is the largest and its duration is very long. The reflected wave of model II is still obvious while the reflected signals of model III are faded. This is mainly due to the lower reflection characteristic of honeycomb coating. Another difference is that the cavitation for model III takes place much earlier than the other two, which results in a much narrower time span of the first incident shock wave. This should be attributed to the soft coating, which deforms much easier and faster when the shock wave impinges the face sheet.The impulse transmitted to main structure is considered as the primary parameter that will determine the response. We compare the total impulse with the time span of 0.4 ms as listed in Table4. The impulse was calculated by the time integration of the wall pressure-time history. For 4.39 m stand-off, the impulses of model II and model III are, respectively, reduced by 49% and 55% of the impulse of model I. For 2.83 m stand-off, the impulses of model II and model III are, respectively, reduced by 5% and 45%. For 7.5 m stand-off, the impulses of model II and model III are, respectively, reduced by 8% and 60%. The level of impulse reduction depends upon the time, the resistance to the motion of the front face sheet, and the cavitation after the shock reflection, which in turn is affected by the coating structure. As the front face is moving, a rarefaction wave is radiated back into the fluid from the front face. The dispersion of the incident pressure is enabled by sequential crush of the coating. In addition, the acoustic mismatch between the water and the hull enhances the fluid-structure interaction effect. These factors result in an impulse reduction. The attenuation effect becomes outstanding because the reduction in impulse is facilitated by soft coating. As a result, lower structure responses induced by shock wave are anticipated in the subsequent sections.Table 4
Acceleration peaks unit (g).
Event
A
1
A
4
A
5
Average
1
624
436
1741
933
2
443
394
1480
772
3
182
266
360
269
4
948
738
2672
1452
5
762
655
2727
1381
6
301
398
648
449
7
945
795
3841
1860
8
858
782
3433
1691
9
335
426
731
497


## 3.1.1. Free Field Pressure-Time Profiles

Figure8 shows the typical free field water pressure-time history ofP2 (event 1). The initial shock wave within 4 ms is magnified. It is seen that the pressure rises to a peak instantaneously upon the arrival of primary shock wave. Subsequently, it decreases at a nearly exponential rate. The reflected wave from the structure can also be distinguished, arriving at 6.53 ms after the shock wave passes. The secondary shock is subsequently experienced, due to the damped oscillation of the gas bubble that contains explosive products. The pressure peak of the shock wave is much higher and its duration is shorter compared with that of the bubble pulsation. The incident shock wave arrives instantaneously with a peak of 6.59 MPa and then decays rapidly within about 0.4 ms. The first bubble pulsation arrives at 218 ms, with a broader profile and a low peak of 1.025 MPa. The bubble pulse pressure peak is 15.5% of the shock wave peak.Free field water pressure-time history (event 1): (a) record within 400 ms, (b) shock wave within 4 ms.
(a)
(b)Accurate shock pressure loading is important. Table3 lists all the free field pressure peaks in the shock wave phase. Considering the broad profile characteristics of bubble pulse, no comparison of their peaks is made. The free field theoretical peaks were obtained by Cole’s empirical formula P
m
=
52.4
(
W
1
/
3
/
R
)
1.13 [23]. As stand-off changes from 2.83 m to 7.5 m, the free field test peak increases from 5.79 MPa to 12.02 MPa. The deviations between the theoretical peak and the test peak range from 0.6% (event 1 and event 8) to 5.3% (event 2). The deviation is within 5.5%, which indicates that the explosion processes guarantee the following comparisons are authentic.Table 3
Summary of free field water pressure, wall pressure, and impulse.
Event number
Model
L
2 (m)
Theoretical peak (MPa)
Test peak (MPa)
Deviation (%)
Wall pressure peak  (MPa)
Impulse (Pa*s)
1
I
6.2
6.63
6.59
−0.60
3.20
117.6
2
II
6.2
6.69
6.33
−5.3
2.16
59.4
3
III
6.9
5.91
5.79
−2.0
2.22
52.6
4
I
3.6
12.22
12.02
−1.6
8.12
215
5
II
3.7
12.02
11.9
−1.0
5.53
204
6
III
6.1
6.79
6.89
1.5
5.13
118
7
I
3.9
11.38
11.59
1.8
6.14
293.8
8
II
3.8
11.63
11.69
−0.60
6.31
269.3
9
III
4.0
10.96
11.1
1.3
4.45
117.8


## 3.1.2. Wall Pressure-Time Profiles

The wall pressure-time profiles are very helpful in understanding the working mechanism of the coating. The wall pressure is the result of blast wave, divergent rarefaction wave, and reflected wave. Figure9 presents the comparison of the wall pressure-time histories. Several distinct phases can be observed, including incidence, reflection, and cavitation. The whole process begins with the direct shock wave from the explosive, which is immediately followed by the reflected wave and later a tension wave produced by the onset of the cavitation near the bottom hull. As the face sheet moves, the fluid-structure interaction changes and the reflection is significantly reduced. The subsequent broad pressure wave indicates the repeating elastic deformation of the hull.Comparison of the wall pressure-time histories: (a) 2.83 m stand-off, (b) 7.5 m stand-off.
(a)
(b)In Figure9(a), the first incident wave peaks of coated models are much smaller than that of uncoated model as listed in Table 3. The reflected wave of model II is obvious. Moreover, its reflected wave peak is larger and the pulse duration is longer than that of the other two. The reflected signals of model III are much fewer. The negative pressure of model I takes place early because the face sheet moves fast under the incident shock wave with a high pressure peak, but its duration is short. In Figure 9(b), the prominent discrepancies of the wall pressure waveform can be observed. The first incident wave peak of model III significantly decreases. The reflected wave peak of model I is the largest and its duration is very long. The reflected wave of model II is still obvious while the reflected signals of model III are faded. This is mainly due to the lower reflection characteristic of honeycomb coating. Another difference is that the cavitation for model III takes place much earlier than the other two, which results in a much narrower time span of the first incident shock wave. This should be attributed to the soft coating, which deforms much easier and faster when the shock wave impinges the face sheet.The impulse transmitted to main structure is considered as the primary parameter that will determine the response. We compare the total impulse with the time span of 0.4 ms as listed in Table4. The impulse was calculated by the time integration of the wall pressure-time history. For 4.39 m stand-off, the impulses of model II and model III are, respectively, reduced by 49% and 55% of the impulse of model I. For 2.83 m stand-off, the impulses of model II and model III are, respectively, reduced by 5% and 45%. For 7.5 m stand-off, the impulses of model II and model III are, respectively, reduced by 8% and 60%. The level of impulse reduction depends upon the time, the resistance to the motion of the front face sheet, and the cavitation after the shock reflection, which in turn is affected by the coating structure. As the front face is moving, a rarefaction wave is radiated back into the fluid from the front face. The dispersion of the incident pressure is enabled by sequential crush of the coating. In addition, the acoustic mismatch between the water and the hull enhances the fluid-structure interaction effect. These factors result in an impulse reduction. The attenuation effect becomes outstanding because the reduction in impulse is facilitated by soft coating. As a result, lower structure responses induced by shock wave are anticipated in the subsequent sections.Table 4
Acceleration peaks unit (g).
Event
A
1
A
4
A
5
Average
1
624
436
1741
933
2
443
394
1480
772
3
182
266
360
269
4
948
738
2672
1452
5
762
655
2727
1381
6
301
398
648
449
7
945
795
3841
1860
8
858
782
3433
1691
9
335
426
731
497


## 3.2. Acceleration Records

### 3.2.1. Acceleration-Time Profiles

Figure10 shows the detailed acceleration histories at locationA5. Despite some differences in these records, basic trends are consistent. An abrupt jump of signal indicates that the target responds to the arrival of shock wave and bubble pulse. Moreover, there exist fewer high frequency components in the coated models’ records, which will be verified by later spectra analysis. It is attributed to the high viscoelastic characteristics of the coatings. Acceleration peaks are compared to evaluate the protective effect. As expected, the peak induced by the shock wave is much larger than that induced by the bubble pulse. The maximum acceleration of model I for the shock wave and the first bubble pulse, respectively, reaches 1740 g and 338 g. The maximum acceleration of model II for the shock wave and the first bubble pulse, respectively, reaches 1480 g and 303 g. The maximum acceleration of model III for the shock wave and the first bubble pulse, respectively, reaches 360 g and 82 g. The initial acceleration peak is reduced drastically after the coating is covered. The maximum response to the shock wave decreased from 1741 g to 360 g, and the maximum response to the bubble pulse decreased from 338 g to 82 g. Honeycomb coating has a potential advantage due to the possibility of controlling the transferred force.Acceleration histories at locationA5: (a) event 1, (b) event 2, and (c) event 3.
(a)
(b)
(c)As a general comparison, Table4 summarizes all the measured acceleration peaks in the shock wave phase. As the secondary shock waves have much smaller peaks and are usually much less damaging than the primary shock wave, the peaks caused by the bubble pulse are not given. Furthermore, the average peak of three test locations (A1,A4, andA5) corresponding to each event is presented. For 4.39 m stand-off, the average peaks of model II and model III are, respectively, reduced by 17.2% and 71.1% of the average peak of model I. For 2.83 m stand-off, the average peaks of model II and model III are, respectively, reduced by 4.9% and 69%. For 7.5 m stand-off, the average peaks of model II and model III are, respectively, reduced by 9.1% and 73.2%. Prominent attenuation effects of model III are revealed. It can also be seen that the attenuation effect is related to coating as well as stand-off. When the stand-off equals 4.39 m, the attenuation effect is significant.To evaluate the attenuation effect conveniently, the acceleration peak ratio is defined between coated model and uncoated model. If it is less than unity, the acceleration is reduced and vice versa. Figure11 shows the acceleration peak ratio. The stand-off of number 1~number 3 is 4.39 m. The stand-off of number 4~number 6 is 2.83 m. The stand-off of number 7~number 9 is 7.5 m. It can be seen that nearly all the peaks decrease after the coating is covered, and only one peak ratio (number 6) increases to 1.02. This fact indicates that the attenuation effects of the coatings are global in nature. When the stand-off equals 4.39 m, the maximum acceleration isolation of these coatings appears. The peak ratio of model II at locationA1 decreases to 0.7 (number 1) and 30% of the acceleration of model I is cut off. The ratio of model III at locationA5 decreases to 0.17 (number 3) and 83% of the acceleration of model I is cut off. From the minimum acceleration isolation, the ratio of model III atA4 decreases to 0.6 (number 2) and at least 40% of the acceleration of model I can be cut off.Figure 11
Acceleration peak ratio.In general, the attenuation effect of model III is much better than that of model II. The shock environment can be effectively improved by honeycomb coating. On one hand, due to the impedance mismatch, most of the incident shock energy is isolated by the coating. Meanwhile, when stress wave is transmitted from “hard” material into “soft” material, it will be reflected and turn into tensile wave, resulting in the wave decaying. On the other hand, as honeycomb cell walls provide structural support and regulate the stress to the back plate, they will deform and collapse sequentially when the coating is impinged by water blast wave. The cavities, like closed air chambers, can provide adequate space for the large deformation of cell walls and desired blast mitigation. The results show that the structure with low impedance and high energy absorption capacity should be used as the protective layer.


### 3.2.2. Shock Response Spectrum

Shock response spectrum (SRS) is an effective method in understanding the frequency component of dynamic response of the structure subjected to shock input [3]. By comparing SRS curves of uncoated model and coated model, the influence of the coating on the transient response of the model can be partly revealed. As a comparison, the shock response spectrum from acceleration history of three models at locationA5 (7.5 m stand-off) is plotted in Figure 12.A5 test point is selected because the shock intensity is the highest and more structural modes can be excited. In spite of some differences between the SRS curves derived from different locations, common trend is similar. So other accelerometers are not presented. The analysis frequency band is between 1 Hz and 10 kHz.Figure 12
Shock response spectrums of three models (7.5 m stand-off,A5 test point).It can be seen that in the frequency range lower than 30 Hz and higher than 100 Hz, there is a distinct reduction of SRS value after the coatings are covered. The higher the frequency is, the more obvious the attenuation effect is. The protective effect of model III in high frequency range is better than that in low frequency range. At high frequencies, the spectrum curve is mainly controlled by local structural deformation and the energy decays rapidly as the damping effect predominates. Considering the zero drift of accelerometers, the response below 2 Hz is untrustworthy. The difference between two coated models at low frequencies is small, and the effect of model II is slightly better than that of model II. Comparing with high frequency range, the frequency band between 30 Hz and 80 Hz is the magnification region. Prominent peaks can be observed, which correspond to the global bending. The effects of coated models seem limited. Moreover, the response of model III is larger than that of model II.


## 3.2.1. Acceleration-Time Profiles

Figure10 shows the detailed acceleration histories at locationA5. Despite some differences in these records, basic trends are consistent. An abrupt jump of signal indicates that the target responds to the arrival of shock wave and bubble pulse. Moreover, there exist fewer high frequency components in the coated models’ records, which will be verified by later spectra analysis. It is attributed to the high viscoelastic characteristics of the coatings. Acceleration peaks are compared to evaluate the protective effect. As expected, the peak induced by the shock wave is much larger than that induced by the bubble pulse. The maximum acceleration of model I for the shock wave and the first bubble pulse, respectively, reaches 1740 g and 338 g. The maximum acceleration of model II for the shock wave and the first bubble pulse, respectively, reaches 1480 g and 303 g. The maximum acceleration of model III for the shock wave and the first bubble pulse, respectively, reaches 360 g and 82 g. The initial acceleration peak is reduced drastically after the coating is covered. The maximum response to the shock wave decreased from 1741 g to 360 g, and the maximum response to the bubble pulse decreased from 338 g to 82 g. Honeycomb coating has a potential advantage due to the possibility of controlling the transferred force.Acceleration histories at locationA5: (a) event 1, (b) event 2, and (c) event 3.
(a)
(b)
(c)As a general comparison, Table4 summarizes all the measured acceleration peaks in the shock wave phase. As the secondary shock waves have much smaller peaks and are usually much less damaging than the primary shock wave, the peaks caused by the bubble pulse are not given. Furthermore, the average peak of three test locations (A1,A4, andA5) corresponding to each event is presented. For 4.39 m stand-off, the average peaks of model II and model III are, respectively, reduced by 17.2% and 71.1% of the average peak of model I. For 2.83 m stand-off, the average peaks of model II and model III are, respectively, reduced by 4.9% and 69%. For 7.5 m stand-off, the average peaks of model II and model III are, respectively, reduced by 9.1% and 73.2%. Prominent attenuation effects of model III are revealed. It can also be seen that the attenuation effect is related to coating as well as stand-off. When the stand-off equals 4.39 m, the attenuation effect is significant.To evaluate the attenuation effect conveniently, the acceleration peak ratio is defined between coated model and uncoated model. If it is less than unity, the acceleration is reduced and vice versa. Figure11 shows the acceleration peak ratio. The stand-off of number 1~number 3 is 4.39 m. The stand-off of number 4~number 6 is 2.83 m. The stand-off of number 7~number 9 is 7.5 m. It can be seen that nearly all the peaks decrease after the coating is covered, and only one peak ratio (number 6) increases to 1.02. This fact indicates that the attenuation effects of the coatings are global in nature. When the stand-off equals 4.39 m, the maximum acceleration isolation of these coatings appears. The peak ratio of model II at locationA1 decreases to 0.7 (number 1) and 30% of the acceleration of model I is cut off. The ratio of model III at locationA5 decreases to 0.17 (number 3) and 83% of the acceleration of model I is cut off. From the minimum acceleration isolation, the ratio of model III atA4 decreases to 0.6 (number 2) and at least 40% of the acceleration of model I can be cut off.Figure 11
Acceleration peak ratio.In general, the attenuation effect of model III is much better than that of model II. The shock environment can be effectively improved by honeycomb coating. On one hand, due to the impedance mismatch, most of the incident shock energy is isolated by the coating. Meanwhile, when stress wave is transmitted from “hard” material into “soft” material, it will be reflected and turn into tensile wave, resulting in the wave decaying. On the other hand, as honeycomb cell walls provide structural support and regulate the stress to the back plate, they will deform and collapse sequentially when the coating is impinged by water blast wave. The cavities, like closed air chambers, can provide adequate space for the large deformation of cell walls and desired blast mitigation. The results show that the structure with low impedance and high energy absorption capacity should be used as the protective layer.


## 3.2.2. Shock Response Spectrum

Shock response spectrum (SRS) is an effective method in understanding the frequency component of dynamic response of the structure subjected to shock input [3]. By comparing SRS curves of uncoated model and coated model, the influence of the coating on the transient response of the model can be partly revealed. As a comparison, the shock response spectrum from acceleration history of three models at locationA5 (7.5 m stand-off) is plotted in Figure 12.A5 test point is selected because the shock intensity is the highest and more structural modes can be excited. In spite of some differences between the SRS curves derived from different locations, common trend is similar. So other accelerometers are not presented. The analysis frequency band is between 1 Hz and 10 kHz.Figure 12
Shock response spectrums of three models (7.5 m stand-off,A5 test point).It can be seen that in the frequency range lower than 30 Hz and higher than 100 Hz, there is a distinct reduction of SRS value after the coatings are covered. The higher the frequency is, the more obvious the attenuation effect is. The protective effect of model III in high frequency range is better than that in low frequency range. At high frequencies, the spectrum curve is mainly controlled by local structural deformation and the energy decays rapidly as the damping effect predominates. Considering the zero drift of accelerometers, the response below 2 Hz is untrustworthy. The difference between two coated models at low frequencies is small, and the effect of model II is slightly better than that of model II. Comparing with high frequency range, the frequency band between 30 Hz and 80 Hz is the magnification region. Prominent peaks can be observed, which correspond to the global bending. The effects of coated models seem limited. Moreover, the response of model III is larger than that of model II.


## 3.3. Strain Records

Figure13 shows the detailed strain histories with 1500 ms atE7. Like acceleration records, the strain responses to both shock wave and several bubble pulses can be distinguished. The maximum strain response to the bubble pulse is much smaller than that to the shock wave. The strain peaks of coated models are attenuated, especially for the shock wave. High frequency signal decays and vibration dominates at low frequency. Owing to the high damping of the coatings, there exist fewer high frequency components for coated models.Strain histories at locationE7: (a) event 7, (b) event 8, and (c) event 9.
(a)
(b)
(c)Table5 lists all the measured strain peaks in the shock wave phase. Only tensile strain is considered, which is often selected as a failure criterion of ductility. It is difficult to evaluate the actual attention effect of the coating from only a few points, so we have to make an evaluation by a statistic method. The average strain exceptE4 corresponding to each event is listed in Table 4. For 4.39 m stand-off, the average peak ratios of model II and model III, respectively, decrease to 0.79 and 0.68 of the average peak of model I. For 2.83 m stand-off, the peak ratios of model II and model III, respectively, decrease to 0.87 and 0.77. For 7.5 m stand-off, the peak ratios of model II and model III are, respectively, closed to 1 and 0.76. Like acceleration records, when the stand-off is 4.39 m, the average peak ratio of coated models is the minimum. The average strain of coated model decreases to some extent, except for event 8. The peak ratios of model II range from 0.79 to 1, and the ratios of model III range from 0.68 to 0.77. The results prove that better overall strain attenuation can be obtained by the honeycomb coating.Table 5
Strain peaks (μ
ε).
Event
E
1
E
2
E
3
E
4
E
5
E
6
E
7
E
8
Average (exceptE
4)
1
844
666
752
—
970
718
887
595
776
2
598
563
789
545
835
457
646
424
616
3
839
513
369
178
362
345
475
825
532
4
985
861
1000
—
1472
1237
1261
622
1062
5
829
807
1229
1155
1306
686
1005
636
928
6
965
510
655
786
604
735
825
1434
818
7
1086
787
1377
—
1602
1343
1650
682
1218
8
1108
859
1647
1219
1512
1029
1556
840
1221
9
884
633
773
892
926
936
1081
1315
935Similarly, strain peak ratio is defined between coated model and uncoated model. Figure14 shows the transverse ratio and longitudinal ratio. The stand-off of number 1~number 4 is 4.39 m. The stand-off of number 5~number 8 is 2.83 m. The stand-off of number 9~number 12 is 7.5 m.Strain peak ratio: (a) transverse direction, (b) longitudinal direction.
(a)
(b)It can be seen that the strain attention effect is related to stand-off and test point. The large strain isolation of model II appears atE6 under three stand-offs. For 4.39 m stand-off, the large isolation of model III appears atE3 toE7. For 2.83 m stand-off, the large isolation of model III appears atE5 andE6. For 7.5 m stand-off, the large isolation of model III appears atE3 andE5.After the coating is covered, the strain peaks at most of the test points decrease in some degree. The minimum peak ratio of model III is 0.37 corresponding to number 3 of Figure14(a), and the minimum ratio of model II is 0.55 corresponding to number 7 of Figure 14(b). The maximum strain isolation of model III is larger than that of model II. However, the prominent strain enlargements of coated models at some test points are also presented. This fact indicates that no protective effects can be brought by coatings and the attenuation effects are restricted to local area. For model II, the strain enlargement exists in number 2, number 6, number 9, and number 10 of Figure 14(a) and number 8, number 9, and number 12 of Figure 14(b). The peak ratios range from 1.02 to 1.22. For model III, the strain enlargement exists in number 4, number 8, and number 12 of Figure 14(b). The peak ratios range from 1.39 to 2.39. Furthermore, in number 1 and number 5 of Figure 14(a) and number 4, number 7, number 8, and number 12 of Figure 14(b), model III sustains greater shock damage than model II under identical testing conditions. It indicates that the stress concentration is more evident for the coating with lower impedance. The strain can be manifested over two times at the most execrable locations. This should be attributed to the fact that the stress wave transmitted from water to steel shell via coating cannot be released outward timely for the impedance mismatch between hull and coating. Therefore, the shock energy is accumulated before it is dissipated by structural damping and the stress concentration takes place. As Kwon points out that, for the impedance mismatch between rubber and steel, when stress wave is transmitted into inner steel plate, the stress will concentrate when the impedance of rubber is lower than a certain limit. The softer elastic coating inhibits release of stress wave energy from the structure to the surrounding water. When stress wave is transmitted from “soft” material into “hard” material, the intensity of transmission wave will exceed that of incident wave. The excess energy is manifested in the form of higher stresses in the underlying structure. Therefore, a higher stress state accompanies a coating with smaller characteristic impedance. In addition, a noticeable phenomenon is that the strain of model II is manifested in both directions while the strain of model III only is manifested in the longitudinal direction. The discrepancy is due to the difference of wave length in two directions. Meanwhile, like the strain attention effect, the strain enlargement of the coating is related to stand-off and test point. When stand-off is 2.83 m, the strain enlargements of two coated models are the maximum. There exist four strain enlargement points (E1,E2,E3, andE8) for model II, while there is only one point (E8) for model III. When the test point is close to the explosive charge, its strain enlargement becomes evident.In general, the strain on the outer hull in direct contact with the coating is often manifested. The amplification factor should be related to stress wave type and direction as well as other factors such as the wave impedance mismatch between structure and coating. Results show that the stress concentration is a very complicated nonlinear phenomenon and affected by almost all kinds of factors in the whole underwater explosion process. Softer coating with low acoustic impedance generally tends to concentrate the stress wave energy in the hull. The stress concentration induced by the impedance mismatch cannot be neglected. Such a response may entail increased strains and internal energy causing plastic deformation and failure of the structure.


## 4. Conclusion

This paper experimentally investigated the water blast attenuation effect and dynamic response of a free floating stiffened box with rubber coatings covered onto the bottom hull subjected to UNDEX. The comparison of wall pressure histories indicates that attenuation effects primarily originate from the fact that the coatings can substantially reduce the incident impulse at the initial fluid-structure interaction stage, which is very beneficial for the protection of underwater structures. The attenuation effect of honeycomb coating is significantly enhanced by local cavitation. The acceleration responses of inner structures to both shock wave and bubble pulse can be greatly lowered, especially for the shock wave. The relative benefit of honeycomb coating is significantly enhanced over its solid counterpart under the same shock condition. Rubber coatings provide additional damping for reducing high frequency response of the structure. Strain results have exhibited two types of effects. Due to the impedance mismatch between the interfaces of materials, stress concentration takes place mainly on the outer shell that directly contacts the coating. A softer rubber coating concentrates the stress wave within the structure, which contributes to increased stress magnitudes and induces a greater magnitude of strain. The strain enlargement is related to the coating structure, attack angle, stand-off, and location of strain recorded.



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*Source: 705256-2014-03-27.xml*