An electronic device high-g impact characteristic test evaluation apparatus and method

Abstract

The application relates to the field of impact dynamics tests, and particularly discloses an electronic instrument high-g-value impact characteristic test evaluation device and method. The device comprises an adapting section, a pulse shaper, and a base. The adapting section is coaxially connected with the tail of a high-speed gas gun launch tube to form a radially constrained loading channel and is movably connected with an impact mass. The pulse shaper is arranged in the adapting section. The base is slidably connected in the adapting section and located behind the pulse shaper, and is used for bearing the load transmitted by the impact mass when the impact mass hits the pulse shaper. The base has a front cavity and a rear cavity, and the rear cavity contains a measuring body. A diaphragm pressure gauge is arranged on the front end impact surface of the base, a base accelerometer is arranged in the front cavity, and a multi-parameter sensor is arranged in the measuring body. The device can accurately obtain an excitation load, realize distributed synchronous measurement of multiple physical quantities, has reliable signal line protection and kinetic energy absorption mechanism, and improves the accuracy and reliability of performance evaluation of electronic instruments and protective components of the electronic instruments under a high-g-value impact environment.

Description

Technical Field

[0001] This invention relates to the field of impact dynamics testing, and in particular to a device and method for testing and evaluating the high-g impact characteristics of electronic instruments. Background Technology

[0002] During launch and penetration of hard targets, missile-borne electronic instruments under test (DUTs) are subjected to high-g impact environments, reaching tens of thousands of g. To evaluate the mechanical response and reliability of their internal structural layout, connection methods, potting materials, and buffer components under impact loads, ground-based simulation tests are necessary. Currently, high-velocity gas guns are a commonly used method for high-g impact testing. Their basic principle involves launching an impact mass block at high speed to strike a simulated base, generating a pulse load that applies to the DUT installed inside the base. The acceleration signal of the base is measured as the excitation, and the acceleration signal inside the instrument is measured as the response to evaluate its protective performance.

[0003] However, existing technical solutions have the following limitations in practical applications: 1) Limitations of Base Acceleration Measurement Technology: Under impact loads, the base undergoes high-speed motion. Current methods primarily employ wireless storage testing devices, requiring the integration of sensors, data acquisition circuits, and power supplies within the base. This approach has significant drawbacks: complex device structure and high cost; limited effective testing space within the base, resulting in a very small number of measurement channels per test; and the need to disassemble the module to retrieve data after each test, leading to low testing efficiency. While wired measurement can address these issues, the signal lines are highly susceptible to damage under inertial shear loads, and there is currently a lack of targeted line protection technology.

[0004] 2) Severe acceleration signal coupling interference: The acceleration measured by missile-borne instruments such as the fuze during penetration consists of three parts: the rigid body acceleration of the projectile, the structural response of the missile-guided system, and the response of the accelerometer to the excitation signal. These three parts exhibit a progressive characteristic. Specifically, the resistance of the target being penetrated generates rigid body acceleration (1-4 kHz) on the projectile. When this acceleration is transmitted through the missile-guided system (using threaded connections, pre-tightened clamping, etc.), it is superimposed with the high-frequency vibration response of the missile-guided system (10 kHz). 1 -10 2The overload information peak value sensed by the fuze is much higher than that of the rigid body acceleration (kHz). When this signal is further transmitted to the accelerometer through the fuze structure (shell, potting compound, mounting structure, etc.), it is coupled with the high-frequency resonant response of the measuring body vibration response and the sensor mounting structure. Therefore, the actual measured acceleration has undergone three layers of information superposition. The rigid body acceleration is mainly used to assess the overload level, calculate the penetration depth in real time, and calibrate the detonation time. However, the high-frequency interference signal seriously affects the interpretation of the initial excitation signal, resulting in inaccurate interpretation of the peak value and pulse width. However, current evaluation tests mostly use the acceleration of a certain measuring point on the base as the excitation signal and the internal acceleration of the electronic instrument under test as the response signal to evaluate the protective effectiveness of the potting material or buffer pad. This lacks a comprehensive evaluation method involving multiple parts and multiple physical quantities. The overall rigid acceleration of the base, which serves as the system input excitation, is coupled with the vibration response of the base and its measuring parts in actual measurement, introducing a large amount of high-frequency interference, resulting in inaccurate acquisition of input parameters and affecting the reliability of the protective effectiveness evaluation.

[0005] 3) Defects in recovery and testing environment: After impact acceleration, the base often adopts an elastic recovery method, but the rebound can easily generate secondary collisions that interfere with the measurement signal. In addition, existing safety protection for high-speed collisions of large masses often uses open target chambers, which have problems such as large size and low testing efficiency; there is a lack of effective control over the residual kinetic energy of the base, and the collision between the mass block and the base in the open space can easily generate radial displacement, affecting the measurement results; the entire collision system lacks axial linear motion constraints.

[0006] Therefore, it is necessary to propose a new device and method for testing and evaluating the high-g impact characteristics of electronic instruments. Summary of the Invention

[0007] To address the problems existing in the prior art, this invention provides a device and method for testing and evaluating the high-g impact characteristics of electronic instruments. It can accurately acquire the excitation load, support distributed synchronous measurement of multiple physical quantities, and has reliable signal line protection and efficient kinetic energy absorption mechanism, so as to more comprehensively and accurately evaluate the performance of the electronic instrument under test and its protective components in extreme impact environments.

[0008] As a first aspect of the present invention, the present invention provides a device for testing and evaluating the high-g impact characteristics of electronic instruments. This device can realize distributed synchronous measurement of multiple physical quantities, characterize the impact response of key components, and is suitable for mechanical response testing and impact resistance evaluation of components such as electronic instruments under test, potting materials, and buffer materials under high-g overload environments.

[0009] The device includes: an adapter section for coaxial connection with the tail of a high-speed gas cannon's launch tube to form a radially constrained loading channel, wherein an impact mass block is movably connected within the adapter section; a pulse shaper disposed within the adapter section at the front end of the base in the impact direction; a base slidably connected within the adapter section, located behind the pulse shaper, for bearing the impact load transmitted from the impact mass block striking the pulse shaper; the base having a front cavity and a rear cavity, the rear cavity for accommodating a measuring body; and a measuring system including a thin-film pressure gauge disposed on the impact surface at the front end of the base, a base accelerometer disposed in the front cavity, and a multi-parameter sensor disposed within the measuring body.

[0010] Optionally, the multi-parameter sensor includes at least one of an accelerometer, a strain gauge, a pressure gauge, and a thermometer.

[0011] Optionally, the diaphragm pressure gauge is attached to the interface between the front end cover of the base and the pulse shaper.

[0012] Optionally, the thin-film pressure gauge is an array-type piezoelectric thin-film pressure sensor with a high-frequency response, measuring frequency response up to the GHz level, used to capture the complex high-frequency component signals contained in the impact load, and reflect the true excitation spectrum characteristics that the electronic instrument under test and its internal structure may withstand.

[0013] Optionally, the adapter section is a thick-walled circular tube structure with an inner diameter consistent with the inner diameter of the high-speed air gun's firing tube; a side line groove is provided on the tube wall of the adapter section along the axial direction, and the side line groove extends along the axial direction of the adapter section to accommodate the signal line led out from the base.

[0014] Optionally, a limiting slider is provided on the outer side of the base, and the protrusion of the limiting slider is embedded in the side groove to restrict the circumferential rotation of the base and guide its axial sliding.

[0015] Optionally, a buffer layer is provided between the base and the measuring body, and the buffer layer is an elastic damping material or a plastic crushable energy-absorbing material.

[0016] Optionally, the high-g impact characteristic testing and evaluation device for electronic instruments further includes a kinetic energy trap disposed within the adapter section. The kinetic energy trap is located behind the base to absorb the residual kinetic energy of the base. The kinetic energy trap includes an energy-absorbing block, an intermediate slider, and a brake arranged sequentially along the impact direction. The energy-absorbing block is made of a crushable plastic energy-absorbing material. The brake is filled with a viscous medium to decelerate the intermediate slider to a stop.

[0017] Optionally, the mass of the intermediate slider is greater than 30 times the mass of the base assembly.

[0018] As a second aspect of the present invention, the present invention provides a method for testing and evaluating the high-g impact characteristics of electronic instruments, based on the high-g impact characteristic testing and evaluation device for electronic instruments described in the first aspect above, the method comprising the following steps: Assemble the test system: Place the measuring body, which is equipped with the electronic instrument and sensor to be tested, into the base, attach the thin film pressure gauge to the front end of the base, and place the base, pulse shaper and kinetic energy trap into the adapter section in sequence; Perform impact loading: drive the impact mass block to strike the pulse shaper, and apply a high g-value impact load to the base; Synchronous data acquisition: The impact interface pressure is measured by the thin-film pressure gauge, the base response acceleration is measured by the base accelerometer, and the response physical quantity of the electronic instrument under test is measured by the multi-parameter sensor; Data processing and evaluation: Based on the pressure data measured by the thin-film pressure gauge and the mass of the base assembly, the rigid body acceleration of the base is calculated as the input excitation; the response signals measured by the base accelerometer and the multi-parameter sensor are compared and analyzed with the input excitation to evaluate the performance of the electronic instrument under test or its protective components under high g-value impact.

[0019] As can be seen from the above technical solution, this invention constructs a radially constrained loading channel by coaxially connecting the adapter section with the high-speed gas cannon launch tube, and sequentially setting a pulse shaper and a sliding base within it, thus creating an axially stable and tightly constrained impact transmission path. By directly placing a thin-film pressure gauge on the impact surface at the front end of the base to measure the impact interface pressure, and simultaneously acquiring the response signal using an accelerometer inside the base, accurate acquisition of the impact excitation load and direct observation of the response behavior are achieved. This structural design makes the transmission of impact load more concentrated and the waveform more controllable, effectively avoiding the data distortion problems caused by vibration coupling and signal line damage in traditional measurements, thereby significantly improving the accuracy and reliability of performance evaluation of electronic instruments under test and their protective components under high-g impact environments. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the overall structure of the high-g impact characteristic testing and evaluation device for electronic instruments proposed in this embodiment of the invention; Figure 2This is a schematic diagram of the adapter segment in an embodiment of the present invention; Figure 3 This is a schematic diagram of the overall structure of the base in an embodiment of the present invention; Figure 4 This is a schematic diagram showing the structural details of the base in an embodiment of the present invention; Figure 5 This is a schematic diagram of the overall structure of the measuring body in an embodiment of the present invention; Figure 6 This is a schematic diagram showing the structural details of the measuring body in an embodiment of the present invention; Figure 7 This is a schematic diagram of the energy absorption system in an embodiment of the present invention; Figure 8 This is a schematic diagram of the impact mass block in an embodiment of the present invention; Figure 9 The acceleration curves for the excitation and target response generated in this embodiment are shown.

[0022] Reference numerals: 1. Adapter section; 11. Adapter flange; 12. Observation window; 13. Side line groove; 2. Impact mass block; 3. Pulse shaper; 4. Base; 41. Diaphragm pressure gauge; 42. Front end cover; 43. Base accelerometer; 44. Front cavity; 45. Wire groove; 46. Rear cavity; 47. Height adapter block; 48. Rear end cover; 49. Limiting slider; 5. Measuring body; 51. Measuring body end cover; 52. Encapsulating material; 53. Multi-parameter sensor; 54. Electronic instrument under test; 55. Wiring hole; 56. Measuring body shell; 57. Buffer pad; 6. Kinetic energy trap; 61. Energy absorption block; 62. Intermediate slider; 63. Brake. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] To address the problems of high cost, low efficiency, inaccurate excitation load, and complex target chamber protection structure in existing high-g impact testing and evaluation devices based on air cannons, this invention provides a high-g impact characteristic testing and evaluation device for electronic instruments. This device uses an air cannon to drive an impact mass block, which collides with a base under radial constraint, thereby generating a high-g overload with a specific pulse width and amplitude, achieving precise loading of the base.

[0025] This invention also provides a more accurate method for acquiring excitation loads and a method for measuring various mechanical response parameters within electronic instruments. Through targeted circuit protection design and the use of wired measurement, the utilization rate of the internal space of the base is effectively improved. This device can comprehensively evaluate the operating characteristics of key components, structural layout, potting components, and external buffer energy-absorbing components of the electronic instrument under test.

[0026] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0027] Example 1 Reference Figures 1 to 9 As shown, Embodiment 1 of the present invention provides a device for testing and evaluating the high-g impact characteristics of electronic instruments. This device can perform multi-physical quantity, distributed, synchronous testing and comprehensive evaluation of the mechanical response characteristics of the electronic instrument under test 54, potting material 52, buffer pad 57, etc. under high-g impact environment.

[0028] In this embodiment, the device includes an impact loading system, an energy absorption system, and a measurement system, specifically, as follows: Figure 1 As shown, the device consists of structural components such as an adapter section 1, an impact mass block 2, a pulse shaper 3, a base 4, a measuring body 5, and a kinetic energy trap 6. These structural components are arranged sequentially along the impact direction to form a complete impact loading system and energy absorption system.

[0029] The adapter section 1 connects to the tail end of the air cannon launcher and maintains the same inner diameter to ensure that the impact mass block 2 enters the adapter section 1 without deceleration after being launched from the launcher. Along the firing direction, the adapter section 1 contains, in sequence, a pulse shaper 3, a base 4, and a kinetic energy trap 6. The pulse shaper 3 is flush with the front end of the base 4; the base 4 contains a front cavity 44 and a rear cavity 46, with the measuring body 5 nested within the rear cavity 46. The kinetic energy trap 6 consists of a front energy-absorbing block 61, a middle slider 62, and a rear braking mechanism.

[0030] A certain gap is reserved between the tail end of the base 4 and the energy-absorbing block 61 at the front end of the kinetic energy trap 6, which serves as the free sliding stroke of the base 4 during the loading process of the measuring body 5. After loading is completed, the kinetic energy trap 6 absorbs the residual kinetic energy of the base 4 to prevent it from rebounding and causing a secondary impact.

[0031] The measurement system of this embodiment includes a thin-film pressure gauge 41 (for measuring the input excitation load) disposed on the impact surface at the front end of the base 4, a base accelerometer 43 (for measuring the acceleration response of the base 4) inside the front cavity 44 of the base 4, and at least one multi-parameter sensor 53 inside the measurement body 5 (for measuring the mechanical response characteristics of the electronic instrument under test 54 and its internal components, i.e., the output response signal of the object under test).

[0032] In one specific embodiment, such as Figure 1 and Figure 2 As shown, the adapter section 1 serves as the main body for bearing and constraining the entire device. It is fixedly connected to the tail end of the high-speed air gun's launch tube via the adapter flange 11, ensuring that the inner diameters of the two are strictly consistent, forming a smooth, coaxial launch and impact channel.

[0033] Based on the above embodiments, the adapter section 1 is further constructed as a thick-walled circular tube using high-strength alloy steel (e.g., 4340 or high-strength gun steel) to ensure its structural strength and dimensional stability under high-speed impact. Its length is typically no less than 1000 mm, its inner diameter matches the inner diameter of the connected air cannon tube (e.g., 100 mm), its wall thickness is no less than 20 mm, and its inner wall is mirror-finished to reduce frictional resistance of moving parts.

[0034] Based on the above embodiments, two pairs of functional windows are further provided on the wall of the adapter section 1 at 90° intervals along the circumference. One pair is an observation window 12, sealed with a high-strength transparent material (such as polycarbonate or bulletproof glass), with a width of not less than 50 mm and a length of approximately 50% of the total length of the tube body, used for high-speed photographic observation and assembly of internal components during the test. The other pair is a side line groove 13, with a width of approximately 20 mm and a length of approximately 70% of the total length of the tube body, used to guide and protect all measurement signal lines led out from the base 4, preventing them from being sheared by inertial forces during high-speed movement. At the same time, the cylindrical sections of the limiting sliders 49 installed on both sides of the base 4 are embedded in the side line grooves 13, serving the dual purpose of limiting the rotation of the base 4 and ensuring that it can only slide axially.

[0035] It should be understood that, in some specific embodiments, the length of the adapter segment 1 and the specific dimensions of the side line slide groove 13 can be adjusted according to key parameters such as the maximum launch speed of the impact mass block 2 and the expected sliding distance of the base 4, so as to ensure sufficient movement stroke and observation range.

[0036] Preferably, at both ends of the side groove 13, the tube body of the adapter section 1 retains a complete wall thickness section of about 15% of the total length to enhance the rigidity and deformation resistance of the structure at both ends and maintain the geometric stability of the internal channel.

[0037] In one specific embodiment, the impact mass 2 moves at high speed along the internal channel of the launch tube and the adapter section 1 under the drive of the air gun, with an initial velocity v 0 The impact base 4 is subjected to a high-g impact by the front pulse shaper 3.

[0038] Preferably, the weight of the impact mass block 2 is approximately 80%-90% of the weight of the base 4 and the measuring body 5 assembly, ensuring that it produces a slight rebound after impact to prevent secondary chasing impact and control the rebound speed.

[0039] Preferably, the impact mass block 2 is made of high-strength alloy steel with an aspect ratio of not less than 1.0 to ensure axial motion stability. The tail is made of a conical nozzle to reduce mass, reduce stress wave reflection effect and tail drag.

[0040] In one specific embodiment, three pulse shapers are attached to the front end face of the base 4 to adjust the waveform of the impact load generated by the impact mass block 2. When using elastic rubber pads or felt-type fiber network materials, the pulse waveform is shaped by utilizing the typical nonlinear hyperelastic characteristics of the compressive stress-strain response. The stress growth rate increases rapidly with increasing strain, while there is a hysteresis effect during unloading, easily generating a half-sine wave acceleration curve, which can simulate the overload characteristics of a projectile penetrating a thin target. When using foam metal, honeycomb aluminum, or multi-cell thin-walled structures, the waveform is shaped by plastic crushing response, generating a trapezoidal acceleration curve. It mainly utilizes its large elastic stiffness and unloading rate to generate approximately linear rising and falling edges, and its long crushing stroke to generate an acceleration curve plateau. The level of the plateau is adjusted by the average crushing load of the material structure, and the amplitude and duration of the pulse plateau for high g-value overload can be customized, which can simulate the overload characteristics of a projectile penetrating a semi-infinite thickness target.

[0041] In one specific embodiment, the base 4 is a carrier for receiving high g-value pulses, and from the impact end to the tail end, it includes a thin film pressure gauge 41, a front end cover 42, a front cavity 44, an accelerometer, a wire groove 45, a rear cavity 46, a height adapter block 47, a rear end cover 48, and a limiting slider 49.

[0042] Preferably, the base 4 is made of high-strength alloy material with an aspect ratio of 1.5-2.0 and a dumbbell shape to optimize the sliding contact surface between the outer periphery and the inner wall of the adapter section 1, maintaining smooth axial movement and preventing jamming. A diaphragm pressure gauge 41 is attached to the interface between the front end cover 42 and the pulse shaper 3, used to measure the actual impact load borne by the base 4 to calculate its rigid body acceleration. Preferably, the thickness of the diaphragm pressure gauge 41 does not exceed 0.15 mm, and the bonding surface is kept flat to reduce its influence on the load transmission to the impact surface.

[0043] Furthermore, a locally polarized PVDF array piezoelectric thin-film pressure sensor is preferred. It features an accurate sensing element area and extremely high frequency response, enabling accurate measurement of stress on the impact surface while retaining rich frequency domain signals of the impact load. The sensing element can be configured as an array using local polarization technology on the entire PVDF film, ensuring the flatness of the measurement layer and improving measurement accuracy through multi-point distributed measurements and averaging.

[0044] The front cover 42 and rear cover 48 are all bolted to the outer shell of the base 4. The outer surface of the end cover is countersunk to maintain its flatness. The front cavity 44 is a cylindrical cavity with a side window, which can be equipped with piezoelectric or piezoresistive accelerometers to provide response signals for the base 4 under impact loads. The signal lines can be led out from the side window for fixed protection. The rear cavity 46 is the installation space for the electronic instrument under test 54 or the measuring body 5. Four wire grooves 45 are axially opened in the rear cavity 46. The width of the wire grooves 45 is 10mm and the length is 70%-80% of the length of the rear cavity 46. The signal lines inside the measuring body 5 are led out from these grooves for fixed protection.

[0045] The height adapter block 47 is located between the measuring body 5 and the rear end cover 48. It is made of materials such as aluminum alloy, copper, cardboard, and bakelite to meet the pre-tightening requirements of the measuring body 5 at different heights. The limiting slider 49 has a lead screw at the front end and a cylindrical section with a diameter of 18mm at the rear end. It is installed on the left and right sides of the base 4. The cylindrical section is located in the measuring line groove and is used to limit the rotation of the base 4 and guide the axial sliding.

[0046] In one specific embodiment, the measurement body 5 is either the package of the electronic instrument under test (DUT) 54 or the DUT 54 itself. The measurement body 5 includes a measurement body housing 56, a measurement body end cap 51, a multi-parameter sensor 53, a potting material 52, and an external buffer layer 57. The measurement body housing 56 has a blind-hole structure, internally housing the DUT 54 and the multi-parameter sensor 53, and is reinforced with potting material. The tail end is sealed with an end cap.

[0047] Preferably, the measuring body housing 56 is made of lightweight aluminum alloy and adopts a dumbbell-shaped structure similar in shape to the base 4, which facilitates the axial movement of the measuring body 5 inside the rear cavity 46 of the base 4.

[0048] The multi-parameter sensor 53 includes sensors such as accelerometers, strain gauges, pressure gauges, and thermometers. It is set up reasonably according to the physical parameters that the instrument needs to assess. All sensor leads are led out through the wire holes 55 opened on the side of the measuring body 5.

[0049] The measuring body end cap 51 is connected to the measuring body housing 56 by bolts, forming a sealed installation space for the test instrument. The potting material 52 is one or more composites of polymer materials such as epoxy resin, polyurethane, and rubber, which enhances the structural stability of internal components under high overload environments through potting reinforcement.

[0050] The buffer layer 57 can be located at the front or rear end of the measuring body 5. It can be made of elastic damping material, such as polyurethane or rubber, or crushable energy-absorbing material, such as metal fiber network material, foam metal, thin-walled tube, multi-cell thin-walled structure, etc.

[0051] When the buffer layer 57 is not installed between the base 4 and the measuring body 5, both are subjected to the same overload, and only the protective effectiveness of active design factors such as the internal potting and component layout of the measuring body 5 is evaluated. When the buffer layer 57 is installed, the buffer layer 57 is used to reduce the high g-value impact load transmitted by the base 4 to form a buffer protection for the internal electronic instrument under test 54. In this case, the device is used to evaluate the comprehensive protective effectiveness of factors such as the external passive buffering and internal hardening design of the measuring body 5.

[0052] In one specific embodiment, the kinetic energy trap 6 includes an energy-absorbing block 61 at the front end, a slider 62 in the middle, and a brake 63 at the rear end. These components absorb the remaining kinetic energy of the measuring body 5 after the buffer base 4 has applied load, and prevent rebound and secondary impact damage. The energy-absorbing block 61 is made of a low-strength, low-stiffness crushable plastic energy-absorbing material. At the moment of impact with the base 4, it provides a stable feedback load through its own gradual crushing, causing the base 4 to decelerate uniformly and adhere to the front end of the kinetic energy trap 6 without rebounding.

[0053] Preferably, the energy-absorbing block 61 is made of porous materials and structures that can generate long-range plateau stress, such as high-porosity foamed metal, polyurethane foam, plastic foam, collapsible thin-walled tube, and honeycomb structure. More preferably, the energy-absorbing block 61 is made of closed-cell foamed aluminum with a relative density of 0.2-0.3, whose plateau stress... σ pl =6 MPa-12 MPa, compression ratio ε d =60%. Cross-section and base 4 impact area A To maintain consistency, provide cushioning for base 4 with an average acceleration of [value missing]. σ pl A / M To ensure that its energy storage capacity is greater than the remaining energy of the base 4, and to allow the base 4 to decelerate smoothly after the test, the thickness of the energy-absorbing block 61 is controlled. This is to ensure that the energy absorption block 61 is always in a high specific energy absorption state.

[0054] Based on the above embodiment, the intermediate slider 62 is further defined as a large-mass rigid body in the shape of a circular shaft, connected to the front energy-absorbing block 61, with a mass ratio to the base 4 assembly greater than 30. Multiple constraints ensure that it can only slide axially, serving to bear the load on the back of the energy-absorbing block 61 and further convert the remaining energy into low-speed axial motion. According to the momentum theorem, without considering energy dissipation, the velocity of the intermediate slider 62 after impact buffering is no higher than... v 0 / 30; Considering the energy dissipation of the energy-absorbing block 61 at the front end, the actual speed of the intermediate slider 62 is much lower than this. This speed can be controlled by controlling the mass ratio of the intermediate slider 62 to the base 4. The brake 63 is located at the tail of the intermediate slider 62, with a 20cm-30cm gap between them. It is used to control the slow-moving intermediate slider 62 to quickly reduce its speed to zero and prevent it from rebounding.

[0055] Preferably, the brake 63 is filled with a viscous putty medium, and the tail of the intermediate slider 62 is equipped with a lead screw, threaded steel bar and other penetrating bodies. After the intermediate slider 62 is impacted and absorbs energy by the base 4, it moves backward at a low speed. The penetrating body is inserted into the putty and immediately decelerates to zero due to its resistance. The strong adsorption force of the putty can also ensure that the intermediate slider 62 does not detach and rebound after deceleration.

[0056] In one specific implementation, the energy-absorbing block 61 at the front end of the kinetic energy trap 6 maintains an initial distance of approximately 80 mm from the base 4. The energy-absorbing block 61 is preferably made of crushable metal foam material, a density-increasing material with a porosity combination of 90%, 80%, and 75%. The intermediate slider 62 has the following dimensions: φ 100mm × 600mm, weight 36kg. The sampling rate of the testing system is 5M.

[0057] Figure 9 This is a schematic diagram of a typical acceleration signal obtained in this embodiment. As shown in the figure, the excitation acceleration obtained through front-end stress measurement is an unfiltered wave, but the details are clear. The pulse shaper 3 exhibits initial strength failure, generating an acceleration of approximately 7000g, and then rapidly enters the strengthening stage, generating an overload as high as 46180g. The pulse width is approximately 0.3ms, exhibiting a half-sine wave pattern with clear amplitude and pulse width. The acceleration of the front cavity 44 is clearly coupled with a large amount of high-frequency vibration, with a peak value reaching approximately 80000g, far exceeding the actual excitation overload amplitude. This is mainly related to the propagation of the stress wave within the base 4, the high-frequency vibration response of the base 4, and the resonance of the acceleration sensor (frequency response is generally 20-30kHz). In traditional measurement schemes, this is often used as the system input excitation, which is clearly inappropriate. Its peak value and pulse width information differ from the excitation acceleration, and it is impossible to accurately calculate parameters such as the displacement of the base 4 (corresponding to the projectile penetration depth). The acceleration of the measuring body 5, after the excitation signal has passed through the crushing energy absorption of the buffer layer 57 and the attenuation of the potting material 52, is approximately 22% of the excitation signal, demonstrating the protective effect of the aforementioned active and passive buffer devices. The measuring body 5 of the wired measurement system can also simultaneously measure information such as temperature, pressure, strain, and stress, enabling more detailed diagnostic analysis of the internal structural response.

[0058] Example 2 Embodiment 2 of the present invention provides a high-g impact characteristic testing and evaluation device for electronic instruments. This device uses the same impact loading system as Embodiment 1, including the adapter section 1, impact mass block 2, pulse shaper 3, and base 4, but employs a storage-type wireless testing system in the measurement system. Specifically, in this embodiment, the measurement system includes an external excitation measurement module and an internal response measurement module.

[0059] The external excitation measurement module includes a PVDF diaphragm pressure gauge 41 mounted on the end face of the front cover 42 of the base 4, which is used to measure the end impact load to determine the external excitation overload acting on the base 4.

[0060] The internal response measurement module adopts a wireless storage design and is entirely encapsulated within the measurement body 5. It includes two acceleration measurement channels: one is an acceleration sensor AS1 installed in the front cavity 44 of the base 4, used to measure the impact overload response of the base 4; the other is an acceleration sensor AS2 installed inside the measurement body 5, used to measure the overload response within the body 5. This internal response measurement module integrates the adapter circuitry, analog-to-digital conversion circuitry, storage circuitry, and power supply system required for the two acceleration channels, and is reinforced by encapsulation with epoxy resin and other potting materials 52.

[0061] In this embodiment, the signal lead of the accelerometer AS1 needs to be connected to the storage circuit located inside the measurement body 5. This embodiment provides two connection paths: In one specific embodiment, internal wiring is carried out through through holes in the partition plate between the front cavity 44 and the rear cavity 46. However, the lead wires of this path need to pass through the buffer pad 57, which is easily damaged by the crushing and deformation of the buffer pad 57 during the impact.

[0062] In another specific embodiment, the wire groove 45 on the side of the base 4 is used for external wiring, that is, the lead wire is connected from the outside of the base 4 through the wire groove 45 on the side of the front and rear cavities to the front cavity 44 and the rear cavity 46, and finally introduced into the measuring body 5. This method can effectively protect the lead wire.

[0063] During the experiment, the impact mass 2 strikes the pulse shaper 3 and the base 4. A thin-film pressure gauge 41 at the front end of the base 4 measures the external excitation load; simultaneously, the accelerometer AS1 inside the measuring body 5 triggers the internal storage circuit to begin acquiring and storing signals from two acceleration channels via a preset trigger level. After the experiment, the base 4 and measuring body 5 are disassembled, and the internal storage module is removed to export the stored acceleration data.

[0064] The storage-type wireless testing system eliminates the need for external real-time wiring, avoiding the risk of signal cables being broken during high-speed movement. However, its limitations include the inability to synchronously acquire stress signals measured by the front-end thin-film pressure gauge 41, and the relatively limited number of measurement channels that can be configured for a single test due to the need for integrated circuits and power supplies within the limited space of the measurement body 5.

[0065] Example 3 Embodiment 3 of the present invention provides a method for testing and evaluating the high-g impact characteristics of electronic instruments. Based on the high-g impact characteristic testing and evaluation device for electronic instruments described in the above embodiments, the method includes the following steps: S1. Preparation and Installation of the Measurement System. The electronic instrument under test 54 and the multi-parameter sensor 53 are fixedly installed inside the measurement body 5, with sensor leads extending from the wire through hole 55. After sealing the end cap 51 of the measurement body, potting material 52 is poured into the measurement body 5 for curing. The base accelerometer 43 is installed in the front cavity 44 of the base 4, with leads extending from the side window. According to the testing requirements, a buffer pad 57 (optional), the measurement body 5, and a height adapter block 47 are sequentially placed in the rear cavity 46 of the base 4, and then the rear end cap 48 is installed and pre-tightened. All signal lines leading from the base 4 are neatly arranged and passed through the wire groove 45 on its side.

[0066] S2. Assemble the test system. Attach the diaphragm pressure gauge 41 to the impact surface of the front end cover 42 of the base 4. Push the base 4 assembly, with its internal components already installed, into place from the rear of the adapter section 1, positioning it in the center of the observation window 12. Then, tightly install the pulse shaper 3 onto the front end of the base 4. Next, push the kinetic energy trap 6 into place from the rear of the adapter section 1, adjusting its front energy-absorbing block 61 to maintain a preset initial gap (e.g., 80mm) with the rear end of the base 4. Finally, install the limiting slider 49 on the side of the base 4 into place, allowing its cylindrical section to engage with the side line groove 13 of the adapter section 1, and connect all signal lines through the side line groove 13 to the external data acquisition system.

[0067] S3. Perform the impact loading test. Based on the required impact overload level, set the firing pressure and acceleration distance of the air cannon and launch the impact mass 2. After accelerating within the air cannon, the impact mass 2 enters the adaptation section 1 and impacts the pulse shaper 3 at a predetermined velocity. The pulse shaper 3 shapes the impact load and transmits a high-g pulse of a specific waveform to the base 4. The diaphragm pressure gauge 41 records the pressure-time history of the impact interface in real time. Under the action of this pulse load, the base 4 begins to accelerate backward, and its internal base accelerometer 43 records the acceleration response.

[0068] S4. Measurement Body 5 Response and Energy Absorption. During the acceleration of the base 4, it loads the measurement body 5 through the buffer pad 57 (if installed) in the rear cavity 46. Sensors inside the measurement body 5 (such as accelerometers, strain gauges, etc.) record the mechanical response of the electronic instrument under test 54 and the potting compound under various protective measures. After loading the measurement body 5, the base 4 slides through the preset gap with a certain residual speed and impacts the energy-absorbing block 61 of the kinetic energy trap 6. The energy-absorbing block 61 is crushed, absorbing most of the kinetic energy and decelerating the base 4. Subsequently, the base 4, the energy-absorbing block 61, and the intermediate slider 62 move together at a low speed until the penetrating body at the tail of the intermediate slider 62 inserts into the putty of the brake 63, and the entire system is braked to a stop.

[0069] S5. Data Processing and Performance Evaluation. After the experiment, the collected data is processed. First, the pressure data measured using the diaphragm pressure gauge 41 is processed. p (t) Bearing area of ​​the front cover 42 of the base 4 A and the weight of the base 4 assembly (including internal components) M The rigid body acceleration excitation signal of base 4 was calculated: a (t)= p (t)· A / M This signal, free from the influence of structural vibration, serves as the most realistic input excitation for the system. Then, the acceleration signal (including rigid body acceleration and structural vibration) measured in the front cavity 44 of the base 4, along with the response signals of various physical quantities (such as acceleration and strain) measured inside the measuring body 5, are compared and analyzed with the excitation signal. By changing the initial velocity of the impact mass block 2 or replacing the pulse shaper 3 with different materials / configurations, high-g excitations with different pulse widths and amplitudes can be generated, thereby systematically evaluating the internal layout of the electronic instrument under test 54, the performance of the potting material 52, and the protective effectiveness of the external buffer layer 57 under different impact conditions.

[0070] Compared with the prior art, the present invention discloses at least the following beneficial effects: 1. Flexible and reliable measurement methods: The device is compatible with both wired and wireless measurement modes. In wired measurement, all test leads are fixed and guided by a dedicated lateral slide, allowing them to slide synchronously with the base 4, effectively avoiding damage to signal lines due to inertial shearing during high-speed movement. The wired system provides more test channels, enabling distributed, simultaneous measurement of multiple physical quantities, significantly improving testing efficiency and signal transmission reliability.

[0071] 2. Accurate acquisition of excitation signals and rich dimensions of response analysis: In view of the problem that the traditional method of coupling the acceleration signal of the base 4 with the structural vibration is difficult to reflect the true excitation, the present invention proposes a three-layer progressive measurement scheme.

[0072] First layer (excitation layer): The impact force is directly measured by an ultra-thin, high-frequency response array-type thin-film pressure gauge 41 at the front interface of the base 4. The rigid body acceleration calculated based on this is pure and accurate, and the amplitude and pulse width of the excitation can be clearly interpreted.

[0073] The second layer (structural response layer): Acceleration is measured in the front cavity 44 of the base 4. This signal includes rigid body acceleration and the vibration response of the base 4 itself, which can be used to jointly analyze the impact dynamics behavior of the base 4.

[0074] The third layer (comprehensive response layer): Acceleration is measured inside the measurement body 5, and this signal is further superimposed with multiple factors such as the crushing of the buffer pad layer 57 and the response of the potting compound. This progressive measurement system provides multi-dimensional data support for in-depth analysis of the influence mechanism of multiple factors such as the layout of the electronic instrument under test 54, potting technology, buffer energy absorption, and structural vibration on the protective effectiveness.

[0075] 3. Controllable impact loading process, avoiding secondary interference: By precisely matching the mass ratio of the impact mass block 2 to the base 4 assembly (approximately 80%-90%), and in conjunction with the pulse shaper 3, secondary loading of the base 4 by the mass block is effectively prevented. The rear end of the device is designed with multi-stage kinetic energy traps 6. Energy is initially absorbed by the crushable energy-absorbing block 61, then the remaining kinetic energy is transferred and reduced by the large-mass intermediate slider 62, and finally the system is brought to a smooth stop by the brake 63. This design ensures a single, clean impact loading, completely avoiding interference to the measurement signal from the rebound or secondary collision of the base 4.

[0076] 4. Flexible nested structural design and configurable testing functions: The air gun adapter section 1, base 4, and measuring body 5 adopt a three-layer nested structure. Adapter section 1 provides axial motion constraint and radial protection throughout the collision process; the base 4 and measuring body 5 form a flexibly configurable testing space. By adding, removing, or changing the buffer pad 57, the device can simulate the condition where the excitation load is directly transmitted to the measuring body 5 to evaluate the active protection effects such as internal layout and potting reinforcement; it can also set the buffer pad 57 between the base 4 and the body to evaluate the combined active and passive protection effectiveness. This design makes the adjustment of the test object and evaluation target extremely flexible.

[0077] 5. Strong device adaptability and high testing efficiency: The configuration and size of the measuring body 5 can be customized according to the testing requirements of different electronic instruments 54 under test, with a wide range of adaptability. At the same time, thanks to the standardized nested design, the measuring body 5 can be mass-produced, supporting rapid and continuous multi-batch impact tests, thereby significantly improving the overall testing efficiency.

[0078] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0079] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A device for testing and evaluating the high-g impact characteristics of electronic instruments, characterized in that, include: The adapter section (1) is used to connect coaxially with the tail of the high-speed air gun to form a loading channel with radial constraints. An impact mass block (2) is movably connected inside the adapter section (1). The pulse shaper (3) is located in the adapter section (1) at the front end of the base (4) in the impact direction; The base (4) is slidably connected within the adapter section (1) and located behind the pulse shaper (3) to bear the impact load transmitted from the impact mass block (2) striking the pulse shaper (3); the base (4) has a front cavity (44) and a rear cavity (46), the rear cavity (46) being used to accommodate the measuring body (5). The measurement system includes a thin-film pressure gauge (41) disposed on the front impact surface of the base (4), a base accelerometer (43) disposed in the front cavity (44), and a multi-parameter sensor (53) disposed in the measurement body (5).

2. The high-g impact characteristic testing and evaluation device for electronic instruments according to claim 1, characterized in that, The multi-parameter sensor (53) includes at least one of an accelerometer, a strain gauge, a pressure gauge, and a thermometer.

3. The high-g impact characteristic testing and evaluation device for electronic instruments according to claim 1, characterized in that, The diaphragm pressure gauge (41) is attached to the interface between the front end cover (42) of the base (4) and the pulse shaper (3).

4. The high-g impact characteristic testing and evaluation device for electronic instruments according to claim 3, characterized in that, The thin-film pressure gauge (41) is an array-type piezoelectric thin-film pressure sensor with a high-frequency response. Its measurement frequency response reaches the GHz level. It is used to capture the complex high-frequency component signals contained in the impact load and reflect the true excitation spectrum characteristics that the electronic instrument under test (54) and its internal structure may withstand.

5. The high-g impact characteristic testing and evaluation device for electronic instruments according to claim 1, characterized in that, The adapter section (1) is a thick-walled circular tube structure, and its inner diameter is consistent with the inner diameter of the firing tube of the high-speed air gun. A side line groove (13) is provided on the tube wall of the adapter section (1) along the axial direction. The side line groove (13) extends along the axial direction of the adapter section (1) to accommodate the signal line led out from the base (4).

6. The high-g impact characteristic testing and evaluation device for electronic instruments according to claim 5, characterized in that, The base (4) is provided with a limiting slider (49) on the outside. The protrusion of the limiting slider (49) is embedded in the side groove (13) to limit the circumferential rotation of the base (4) and guide its axial sliding.

7. The high-g impact characteristic testing and evaluation device for electronic instruments according to claim 1, characterized in that, A buffer layer (57) is provided between the base (4) and the measuring body (5), and the buffer layer (57) is an elastic damping material or a plastic crushable energy-absorbing material.

8. The high-g impact characteristic testing and evaluation device for electronic instruments according to any one of claims 1 to 7, characterized in that, It also includes a kinetic energy trap (6) disposed in the adapter section (1), the kinetic energy trap (6) being located behind the base (4) to absorb the residual kinetic energy of the base (4); the kinetic energy trap (6) includes an energy-absorbing block (61), an intermediate slider (62) and a brake (63) arranged sequentially along the impact direction; the energy-absorbing block (61) is made of a crushable plastic energy-absorbing material; the brake (63) is filled with a viscous medium to decelerate the intermediate slider (62) to a stop.

9. The high-g impact characteristic testing and evaluation device for electronic instruments according to claim 8, characterized in that, The mass of the intermediate slider (62) is more than 30 times the mass of the base (4) assembly.

10. A method for testing and evaluating the high-g impact characteristics of electronic instruments, based on the high-g impact characteristic testing and evaluation device for electronic instruments as described in claim 8, characterized in that... Includes the following steps: Assemble the test system: Place the measuring body (5) with the electronic instrument under test (54) and sensor installed inside the base (4), attach the thin film pressure gauge (41) to the front end of the base (4), and place the base (4), pulse shaper (3) and kinetic energy trap (6) into the adapter section (1) in sequence. Perform impact loading: drive the impact mass block (2) to strike the pulse shaper (3) and apply a high g-value impact load to the base (4); Synchronous data acquisition: The impact interface pressure is measured by the thin film pressure gauge (41), the response acceleration of the base (4) is measured by the base accelerometer (43), and the response physical quantity of the electronic instrument under test (54) is measured by the multi-parameter sensor (53). Data processing and evaluation: Based on the pressure data measured by the thin-film pressure gauge (41) and the mass of the base (4) assembly, the rigid body acceleration of the base (4) is calculated as the input excitation; the response signals measured by the base accelerometer (43) and the multi-parameter sensor (53) are compared and analyzed with the input excitation to evaluate the performance of the electronic instrument under test (54) or its protective components under high g-value impact.

Images