Vibration response detection device for unmanned aerial vehicle seeker and detection method thereof

Abstract

The invention discloses a vibration response detection device for an unmanned aerial vehicle seeker and a detection method thereof, the vibration response detection device comprises a vibration tool, a switching tool and a group of acceleration sensors, and three mounting point sensors are arranged near a connection point of a bottom plate and a vibration table; a switching tool sensor is arranged on the switching tool; an azimuth axis sensor is arranged on an azimuth axis shell of the unmanned aerial vehicle seeker; and the two pitch axis sensors are arranged on a pitch axis system shell of the unmanned aerial vehicle seeker. The installation point sensor can directly monitor whether energy input by the vibration table is effectively transmitted to the vibration tool or not in real time. The switching tool sensor is used for evaluating the connection rigidity and vibration energy transfer characteristics from the vibration tool to the unmanned aerial vehicle seeker body. The azimuth axis sensor can reflect the torsion and bending response of the azimuth axis system in a vibration environment. The pitch axis sensor is used for monitoring the vibration response difference of the two ends of the pitch axis system.

Description

Technical Field

[0001] This application relates to the technical field of unmanned aerial vehicle (UAV) seeker testing devices, and in particular to a vibration response detection device and method for UAV seekers. Background Technology

[0002] The vibration environment adaptability of unmanned aerial vehicle (UAV) seekers is a crucial evaluation criterion and basis for passing actual flight tests. Currently, the industry mainly relies on standards to conduct random vibration tests on UAV seekers on vibration tables to assess their product reliability.

[0003] However, traditional random vibration testing methods have significant drawbacks. These methods focus solely on standardized control of the vibration table input energy, neglecting the individual variability between the tested UAV seeker heads. This leads to occasional instances during mass production where individual UAV seeker heads from the same batch, following the same manufacturing processes, fail the random vibration test upon delivery and acceptance (e.g., azimuth axis failure during Y-axis testing).

[0004] Because traditional testing methods cannot provide detailed response data of critical internal components of an unmanned aerial vehicle (UAV) seeker under vibration conditions, engineers struggle to quickly and accurately pinpoint the root cause of failures in the event of an incident. They are unable to determine whether the anomaly stems from insufficient mechanical structural rigidity or improper bandwidth settings in the servo control system. This predicament severely reduces the efficiency of troubleshooting and product optimization, and has become a long-standing and unresolved engineering challenge regarding the environmental adaptability and delivery milestones of mass-produced products. Summary of the Invention

[0005] This application provides a vibration response detection device and method for the guidance head of an unmanned aerial vehicle (UAV), which can solve the technical problem in the prior art where individual products (corresponding to batch products) fail random vibration tests, making it impossible to determine whether the abnormality is due to insufficient mechanical structure stiffness or unreasonable bandwidth settings of the servo control system. The technical solution is as follows:

[0006] In a first aspect, this application provides a vibration response detection device for an unmanned aerial vehicle (UAV) seeker head, comprising: a vibration fixture having a base plate for connection to a vibration table and a vertical plate perpendicularly arranged to the base plate; a transition fixture for mounting the UAV seeker head and detachably connected to the vertical plate; and a set of acceleration sensors, the arrangement of which includes: at least three mounting point acceleration sensors arranged near the connection point between the base plate and the vibration table; at least one transition fixture sensor arranged on the transition fixture; at least one azimuth axis sensor arranged on the azimuth axis housing of the UAV seeker head; and at least two pitch axis sensors arranged on the pitch axis housing of the UAV seeker head.

[0007] Optionally, the base plate is connected to the vibration table by at least three screws, and the at least three mounting point sensors are arranged one-to-one with the screws.

[0008] Optionally, all of the aforementioned accelerometers are triaxial accelerometers.

[0009] Optionally, the upright plate is provided with mounting holes, and the adapter tool is connected to the upright plate through the mounting holes; and the adapter tool includes an upright plate connecting part for assembly with the upright plate, and a simulation compartment for connecting the unmanned aerial vehicle (UAV) seeker head, the simulation compartment having a variety of different size specifications to adapt to UAV seekers of different shapes and sizes.

[0010] Optionally, a random vibration data acquisition system may also be included, wherein all of the set of acceleration sensors are electrically connected to the data acquisition system.

[0011] Optionally, the at least two pitch axis sensors are respectively installed at the pitch axis housing points corresponding to the pitch motor and the pitch angle measuring element.

[0012] Secondly, this application also provides a method for detecting the vibration response of an unmanned aerial vehicle (UAV) seeker head using the above-mentioned vibration response detection device, comprising the following steps:

[0013] Step S1: Install the unmanned aerial vehicle seeker head onto the vibration response detection device via the adapter fixture, and connect it to the data acquisition system;

[0014] Step S2: Control the vibration table to apply unidirectional random excitation forces in the X, Y, and Z directions in sequence;

[0015] Step S3: In each excitation direction, control the unmanned aerial vehicle seeker servo system to sequentially enter the working state determined by multiple different combinations of pitch and azimuth angles;

[0016] Step S4: Under each test condition determined by the excitation direction, pitch angle, and azimuth angle, the vibration response data of the set of acceleration sensors are simultaneously acquired and recorded.

[0017] Optionally, in step 3, the multiple different combinations of pitch and azimuth angles include at least the following four states:

[0018] State 1: Pitch 0 degrees, Azimuth 0 degrees;

[0019] Status 2: Pitch -20 degrees, Azimuth 0 degrees;

[0020] Status 3: Pitch -20 degrees, Azimuth -45 degrees;

[0021] Status 4: Pitch -20 degrees, Azimuth 45 degrees.

[0022] Optionally, after step S4, the method further includes: step S5: based on the vibration response data, calculate the root mean square value of the vibration response of the azimuth axis and pitch axis of the unmanned aerial vehicle's seeker head, and calculate its amplification factor relative to the input energy of the vibration table.

[0023] Optionally, the vibration response detection method is used to test multiple unmanned aerial vehicle seekers from the same batch, and the individual differences between products are quantified by comparing the magnification.

[0024] The beneficial effects of the technical solutions provided in this application include at least the following:

[0025] A vibration response detection device for an unmanned aerial vehicle (UAV) seeker head includes: a vibration fixture, a transition fixture, and a set of acceleration sensors. At least three mounting point sensors are arranged near the connection point between the base plate and the vibration table; at least one transition fixture sensor is arranged on the transition fixture; at least one azimuth axis sensor is arranged on the azimuth axis housing of the UAV seeker head; and at least two pitch axis sensors are arranged on the pitch axis housing of the UAV seeker head. The mounting point sensors can directly and in real-time monitor whether the energy input from the vibration table is effectively transferred to the vibration fixture. The data from the mounting point sensors will serve as a benchmark reference for the entire test, used to distinguish whether the subsequent response is a product characteristic or a structural installation problem. The transition fixture sensors are used to evaluate the connection stiffness and vibration energy transfer characteristics of the critical interface from the vibration fixture to the UAV seeker head body. The azimuth axis sensors can most directly reflect the torsional and bending responses of the azimuth axis system under vibration conditions. Pitch axis sensors are positioned at both ends of the pitch axis housing to monitor the difference in vibration response at both ends, thereby assessing the smoothness of the axis's motion and the uniformity of the structural dynamic stiffness distribution. This coordinated layout, from the vibration input point to the transmission path and then to the core moving components, constitutes a complete vibration energy transmission path. This architecture aims to accurately trace the transmission path and amplification source of vibration energy within the UAV's seeker head, providing data support for addressing the industry pain point of "difficult fault location."

[0026] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 This is a three-dimensional structural diagram of the seeker head of an unmanned aerial vehicle;

[0029] Figure 2 This is a schematic diagram of an unmanned aerial vehicle (UAV) seeker head mounted on a vibration response detection device provided in an embodiment of this application.

[0030] Figure 3 yes Figure 2 A schematic diagram of the decomposition process;

[0031] Figure 4 These are the standard inputs and root mean square values ​​of the vibration table (5.7346g≈5.735g).

[0032] Figure 5 It is the acceleration acquisition data (time domain) of the vibration fixture and the transfer fixture.

[0033] Figure 6 It is the tooling response of the random vibration test in the X direction of product #1;

[0034] Figure 7 This is the tooling response of product #1 during vibration testing in state 1.

[0035] Figure 8 This is the tooling response of product #1 during vibration testing in state 3;

[0036] Figure 9 It is the tooling response of product #1 under vibration test in state 4;

[0037] Figure 10 It is the tooling response of the random vibration test in the X direction of product #2;

[0038] Figure 11 It is the tooling response of product #2 under vibration test in state 1;

[0039] Figure 12 It is the tooling response of product #2 under vibration test in state 3;

[0040] Figure 13 It is the tooling response of product #2 under vibration test in state 4;

[0041] Figure 14 It is the tooling response of the random vibration test in the X direction of product #3;

[0042] Figure 15 It is the tooling response of product #3 under vibration test in state 1;

[0043] Figure 16 It is the tooling response of product #3 under vibration test in state 3;

[0044] Figure 17 It is the tooling response of product #3 under state 4 vibration test.

[0045] Explanation of reference numerals in the attached figures

[0046] 1-Unmanned aerial vehicle seeker head; 2-Vibration fixture; 201-Base plate; 202-Upright plate; 203-Mounting hole; 3-Transfer fixture; 301-Upright plate connection part; 302-Simulation compartment section; 4-Mounting point sensor; 5-Transfer fixture sensor; 6-Azimuth axis sensor; 7-Pitch axis sensor. Detailed Implementation

[0047] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0048] In this disclosure, unless otherwise stated, directional terms such as "upper" and "lower" generally refer to the relative positions of the corresponding components in the direction of gravity when they are in use, and "inner" and "outer" refer to their relative positions to the contours of the corresponding components themselves. Furthermore, the terms "first," "second," etc., used in this disclosure are for distinguishing one element from another and do not have sequential or importance implications. In the following description, when referring to the accompanying drawings, unless otherwise explained, the same reference numerals in different drawings denote the same or similar elements.

[0049] In the product development and quality control of unmanned aerial vehicle (UAV) seekers, the problem of sporadic and difficult-to-reproduce failures in random vibration tests of the same batch of products has long been a serious challenge in this field.

[0050] Through in-depth research and analysis, the inventors discovered that the fundamental reason why traditional methods cannot solve the problem of "individual products failing accidentally in vibration tests" is that traditional testing methods cannot quantitatively assess the abnormal changes in "connection stiffness" caused by a series of random factors, and the impact of these changes on vibration response under different working conditions.

[0051] These factors mainly include: 1. Microscopic dispersion of assembly process: such as slight differences in the preload of mounting screws, fluctuations in the bearing clearance of the azimuth axis system, and changes in the additional torque of cable laying; 2. Parameter dispersion of core component performance: such as the output characteristics of the maximum holding torque of different motors are not completely consistent; 3. Working condition coupling effect of low-frequency structural resonance frequency characteristics: traditional single-condition testing ignores the fact that in actual operation, the real-time changes of the pitch and azimuth angles of the UAV seeker will significantly affect the mass distribution and stiffness matrix variation of the overall structure, thereby causing a sharp amplification of structural frequency drift and vibration response.

[0052] It is precisely because traditional methods lack effective monitoring means for the above mechanisms that the industry faces the dilemma of "individual failures with unknown causes".

[0053] To solve this fundamental engineering problem, in one aspect, the present invention provides a ground vibration response detection device for the guidance head of an unmanned aerial vehicle.

[0054] The core concept of this device is to construct a complete monitoring network from the vibration energy input reference to the interface transmission path and then to the internal core moving components such as the azimuth axis and pitch axis through a carefully designed sensor collaborative layout for the vibration energy transmission path of the unmanned aerial vehicle's seeker head. This enables accurate tracing and quantitative evaluation of vibration response amplification phenomena.

[0055] Please see Figure 1 , Figure 2 and Figure 3 The vibration response detection device mainly includes a vibration fixture 2, a transfer fixture 3, and a set of acceleration sensors.

[0056] The vibration fixture 2 is machined from high-strength aluminum alloy and its structure includes a horizontally positioned base plate 201 and a vertical plate 202 welded perpendicularly to the base plate 201. The base plate 201 has at least three mounting holes 203, which are used to securely connect it to the vibration table via screws. This design aims to ensure that vibration energy can be effectively transferred from the vibration table to the entire vibration fixture through rigid connections, providing a stable foundation for testing.

[0057] The upright plate 202 has a standardized installation interface, such as a threaded hole or flange, at its center. This centrally symmetrical design aims to ensure that the excitation force is transmitted along the center line of the tooling, minimize the additional bending moment introduced by the eccentric installation, and ensure the purity and consistency of the input excitation.

[0058] Furthermore, the adapter fixture 3, as a key component connecting the vibration fixture 2 and the UAV seeker head 1, adopts a modular design. It includes a vertical plate connecting part 301 that mates with the central mounting interface of the vertical plate 202, and a simulation compartment 302 for mounting the UAV seeker head 1. The simulation compartment 302 can be quickly replaced according to the size and specifications of the tail interface of the UAV seeker head 1 under test. In this way, the testing device can be effectively adapted to multiple different models of UAV seeker heads 1 within a product series, greatly improving the versatility and efficiency of the testing platform and reducing the tooling cost for batch testing.

[0059] The placement of the set of acceleration sensors constitutes a logically clear three-layer diagnostic architecture.

[0060] Install a baseline monitoring layer: such as Figure 2 As shown, at least three mounting point sensors 4 are respectively arranged near the three mounting screws of the base plate 201 and the vibration table, and correspond one-to-one with each other. The purpose of this arrangement is to directly and in real time monitor whether the energy input from the vibration table is effectively transferred to the vibration fixture 2. This layer of data will serve as a benchmark reference for the entire test, used to distinguish whether the subsequent response is a product characteristic or an installation problem.

[0061] Transmission path monitoring layer: such as Figure 2 As shown, at least one adapter sensor 5 is mounted on the adapter 3. This adapter sensor 5 is used to evaluate the connection stiffness and vibration energy transfer characteristics of the critical interface from the vibration fixture 2 to the unmanned aerial vehicle seeker head 1 body. Its data can be used to monitor changes in installation status, such as whether the connecting screws are loose.

[0062] Core component response layer: such as Figure 2 As shown, at least one azimuth axis sensor 6 is disposed on the housing surface of the azimuth axis system of the unmanned aerial vehicle seeker head 1. Specifically, the azimuth axis sensor 6 is preferably attached to the center point directly above the azimuth motor housing, which can most directly reflect the torsional and bending response of the azimuth axis system under vibration environment.

[0063] At the same time, such as Figure 2 As shown, at least two pitch axis sensors 7 are respectively arranged at both ends of the pitch axis housing along the pitch axis. Furthermore, these two pitch axis sensors 7 are preferably precisely attached to the housing surfaces corresponding to the pitch motor and the pitch angle measuring element, respectively. The purpose is to monitor the difference in vibration response at both ends of the pitch axis system, thereby evaluating the smoothness of the axis system's motion and the distribution of the structure's dynamic stiffness.

[0064] The aforementioned coordinated layout, from vibration input points such as mounting point sensor 4, to transmission paths such as adapter tooling sensor 5, and then to core moving components such as azimuth axis sensor 6 and pitch axis sensors 7, together constitutes a complete vibration energy transmission diagnostic chain. This architecture aims to accurately trace the transmission path and amplification source of vibration energy within the unmanned aerial vehicle's seeker head 1, providing data support for solving the industry pain point of "difficulty in fault location."

[0065] The vibration response detection device also includes a random vibration data acquisition system. All of the accelerometers are electrically connected to the input of this data acquisition system via low-noise shielded cables to ensure the integrity and accuracy of the high-frequency vibration signal acquisition.

[0066] It should be clarified that, in this embodiment, the core function of the data acquisition system is to synchronously acquire, convert analog to digital and store sensor signals, providing raw, high-quality time-domain data for subsequent offline analysis.

[0067] See Figure 1 , Figure 2 and Figure 3 The working principle and assembly process of the ground vibration response detection device for unmanned aerial vehicle seeker head of the present invention will be further explained through a comprehensive embodiment below.

[0068] First, the operator selects the corresponding simulation cabin section 302 from a set of standardized adapter tooling 3 libraries according to the interface specifications of the UAV seeker 1 to be measured, assembles it with the vertical plate connecting part 301 into a complete adapter tooling 3, inserts the simulation cabin section 302 into the mounting hole 203 at the center of the vertical plate 202, and connects the vertical plate connecting part 301 to the vertical plate 202 with bolts, thereby fixing the adapter tooling 3 on the vibration tooling 2.

[0069] Subsequently, firmly install the UAV seeker 1 on the adapter tooling 3.

[0070] Next, according to the previously determined layout plan, use the process of compounding high-strength double-sided tape and cyanoacrylate instant adhesive to paste a total of seven acceleration sensors, namely three mounting point sensors 4, one adapter tooling sensor 5, one azimuth axis sensor 6, and two pitch axis sensors 7, at the designated monitoring points.

[0071] Finally, neatly lay and reliably connect the cables of all acceleration sensors to the corresponding channels of the random vibration data acquisition system.

[0072] When the device is assembled according to the above steps, a physical platform dedicated to the refined vibration response detection of the UAV seeker 就是搭建完成。此时,操作人员可将该平台通过底板201固定于振动台,即可准备进行后续的、基于本发明方法的振动测试与数据采集工作。

[0073] Second, the present invention also provides a detection method配套的检测方法。包括以下步骤:

[0074] Step S1: Install the UAV seeker on the vibration response detection device through the adapter tooling and connect the data acquisition system;

[0075] Step S2: Control the vibration table to apply a single-direction random excitation force in the X, Y, and Z directions in sequence;

[0076] Step S3: In each excitation direction, control the UAV seeker servo system to make it successively in the working states determined by multiple different combinations of pitch angles and azimuth angles;

[0077] Step S4: In each test condition determined by the excitation direction, pitch angle, and azimuth angle, synchronously collect and record the vibration response data of the group of acceleration sensors.

[0078] Further, in step 3, the multiple different combinations of pitch angles and azimuth angles at least include the following four states:

[0079] State 1: Pitch 0 degrees, azimuth 0 degrees;

[0080] Status 2: Pitch -20 degrees, Azimuth 0 degrees;

[0081] Status 3: Pitch -20 degrees, Azimuth -45 degrees;

[0082] Status 4: Pitch -20 degrees, Azimuth 45 degrees.

[0083] The four operating states selected above represent four typical operating conditions in actual product use. State 1 is the electric lock state, State 2 is the ideal operating condition, and States 3 and 4 are common operating states. In other embodiments, the orientation angles of States 3 and 4 can reach ±90° or greater, and this application embodiment does not impose any limitations on this.

[0084] Optionally, after step S4, the method further includes: step S5: based on the vibration response data, calculate the root mean square value of the vibration response of the azimuth axis and pitch axis of the unmanned aerial vehicle (UAV) seeker, and calculate its amplification factor relative to the input energy of the vibration table.

[0085] Optionally, the vibration response detection method is used to test multiple unmanned aerial vehicle seekers from the same batch, and the individual differences between products are quantified by comparing the magnification.

[0086] The essence of this method lies in actively stimulating and quantifying the vibration response characteristics of the unmanned aerial vehicle's seeker under different flight conditions through "multi-dimensional working condition coupling test", thereby exposing its inherent and hidden dynamic defects to a controllable ground test.

[0087] To fully verify the effectiveness of this testing method, the vibration response testing device and method described above were used to conduct a complete test on three unmanned aerial vehicle (UAV) seeker head products (product 1#, product 2#, and product 3#) from the same batch, in conjunction with a specific embodiment. The testing process is as follows:

[0088] Step 1: According to the requirements of a certain standard, set the relevant parameters on the vibration table. The test standard spectrum is a power spectrum curve formulated according to the given requirements. Taking the random vibration test spectrum of a certain product as an example: (10Hz~2000Hz), then the inflection point frequency (100Hz, 1000Hz) and the average spectrum (0.02g) 2 According to a certain standard, a corresponding random vibration test spectrum can be formulated in combination with the overall requirements, and the root mean square value (rms) of the test spectrum can be calculated as the basis for evaluating the product's vibration response.

[0089] Step 2: The time-domain data collected by the accelerometer is the actual acceleration response data of the product in the random vibration test. It has a certain randomness and cannot be judged from the amplitude in the time domain. In engineering, the frequency and root mean square value obtained from the power spectrum curve are usually used as the energy evaluation basis of the random vibration test.

[0090] Step 3: Use MATLAB software to perform self-power spectrum calculation on time-domain data. Alternatively, you can use relevant software from the random vibration test bench to perform self-power calculation and obtain the power spectrum curve and root mean square value of the random vibration test.

[0091] Step 4: Data preparation, reference Figures 4 to 17 First, statistics were performed according to the random vibration test directions X, Y, and Z. Taking the X direction as an example, statistics were performed on three working states (state 1, state 3, and state 4). The statistical results are shown in the table below. For ease of statistical analysis, the three mounting point sensors correspond to sensor 1, sensor 2, and sensor 3 respectively; the adapter tool sensor corresponds to sensor 4; the azimuth axis sensor corresponds to sensor 7; and the two pitch axis sensors correspond to sensor 5 and sensor 6 respectively. Specifically, sensor 5 is installed at the housing point corresponding to the pitch motor, and sensor 6 is installed at the housing point corresponding to the pitch angle measuring element. The statistical results are shown in Tables 1 and 2 below.

[0092] Table 1 - Comparison of root mean square power spectrum values ​​of random vibration tests in the X direction

[0093]

[0094] Table 2 - Ground Vibration Response Amplification Factor

[0095]

[0096] Using the standard input level of 5.735g for the vibration table as a benchmark, it can be seen that: First, among multiple products #1, #2, and #3, the vibration amplification factor of the vibration fixture (sensor 1, sensor 2, and sensor 3) and the adapter fixture (sensor 4) is mainly between 0.9973 and 1.0007. It can be assumed that the fixture for random vibration testing can ensure accurate energy input to the vibration test table, and energy loss can be ignored. Second, the amplification factor of the azimuth axis (sensor 7) ranges from 1.4207 to 2.4415, indicating that there is an amplification phenomenon in the energy input of the azimuth axis, and the energy transmission fluctuates greatly. Finally, the amplification factor of the pitch motor (sensor 5) ranges from 1.0125 to 1.0220, and the amplification factor of the pitch angle measurement (sensor 6) ranges from 1.2071 to 1.7368. The total energy amplification of the pitch axis is lower than that of the azimuth axis because the energy of the structure is transferred from the azimuth axis to the pitch axis.

[0097] Significance: When the data is large enough, the amplification factor of random vibration energy can be used as an evaluation standard. That is, the random vibration spectrum of the azimuth axis should be higher than that of the pitch axis (2.4415 is larger than 1.7368). Therefore, the random vibration conditions proposed by the UAV seeker distribution system (the manufacturers of pitch and azimuth axes) need to be tightened. All the above information shows that the UAV seeker has peak values ​​in the low-frequency range (10Hz~40Hz). Therefore, when setting PID parameters, the servo control system should design corresponding filtering algorithms to avoid amplification of random vibration response in the low-frequency range, thereby affecting control performance. If there are large differences in the random vibration spectrum of products in the same batch, it indicates that the structural characteristics of the products are quite different. This can help distinguish between problems in the azimuth and pitch axes, which is beneficial for locating specific abnormal components.

[0098] In summary, the structured data and quantitative indicators produced by the method of this invention successfully transform "invisible" individual differences and operating condition coupling effects into "visible" data. This data provides designers with direct, reliable, and efficient decision-making support for locating structural vulnerabilities and control engineers with the ability to adjust disturbance suppression bandwidth, thus fundamentally solving the long-standing technical problem of "individual failures that are difficult to locate" in the prior art.

[0099] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.

[0100] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.

[0101] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.

Claims

1. A vibration response detection device for the seeker head of an unmanned aerial vehicle, characterized in that, include: A vibration fixture (2) has a base plate (201) for connecting to a vibration table and a vertical plate (202) arranged perpendicularly to the base plate (201). A transition tool (3) is used to install the unmanned aerial vehicle seeker (1) and is detachably connected to the upright plate (202). A set of accelerometers, deployed at the following locations: At least three mounting point sensors (4) are arranged near the connection point between the base plate (201) and the vibration table; At least one adapter sensor (5) is disposed on the adapter (3); At least one azimuth axis sensor (6) is installed on the azimuth axis housing of the unmanned aerial vehicle seeker (1); At least two pitch axis sensors (7) are installed on the pitch axis housing of the unmanned aerial vehicle seeker (1).

2. The vibration response detection device according to claim 1, characterized in that, The base plate (201) is connected to the vibration table by at least three screws, and the at least three mounting point sensors (4) are arranged one-to-one with the screws.

3. The vibration response detection device according to claim 1, characterized in that, All of the aforementioned accelerometers are triaxial accelerometers.

4. The vibration response detection device according to claim 1, characterized in that, The upright plate (202) is provided with mounting holes (203), and the adapter (3) is connected to the upright plate (202) through the mounting holes (203); and the adapter (3) includes an upright plate connecting part (301) for assembly with the upright plate (202), and a simulation section (302) for connecting the unmanned aerial vehicle seeker (1). The simulation section (302) has a variety of different size specifications to adapt to unmanned aerial vehicle seekers (1) of different shapes and sizes.

5. The vibration response detection device according to claim 1, characterized in that, It also includes a random vibration data acquisition system, and all of the set of acceleration sensors are electrically connected to the data acquisition system.

6. The vibration response detection device according to claim 1, characterized in that, The at least two pitch axis sensors (7) are respectively installed at the pitch axis housing points corresponding to the pitch motor and the pitch angle measuring element.

7. A method for detecting the vibration response of an unmanned aerial vehicle (UAV) seeker head using the vibration response detection device as described in any one of claims 1-6, characterized in that, Includes the following steps: Step S1: Install the unmanned aerial vehicle seeker head onto the vibration response detection device via the adapter fixture, and connect it to the data acquisition system; Step S2: Control the vibration table to apply unidirectional random excitation forces in the X, Y, and Z directions in sequence; Step S3: In each excitation direction, control the unmanned aerial vehicle seeker servo system to sequentially enter the working state determined by multiple different combinations of pitch and azimuth angles; Step S4: Under each test condition determined by the excitation direction, pitch angle, and azimuth angle, the vibration response data of the set of acceleration sensors are simultaneously acquired and recorded.

8. The vibration response detection method according to claim 7, characterized in that, In step 3, the multiple different combinations of pitch and azimuth angles include at least the following four states: State 1: Pitch 0 degrees, Azimuth 0 degrees; Status 2: Pitch -20 degrees, Azimuth 0 degrees; Status 3: Pitch -20 degrees, Azimuth -45 degrees; Status 4: Pitch -20 degrees, Azimuth 45 degrees.

9. The vibration response detection method according to claim 8, characterized in that, Following step S4, the following is also included: Step S5: Based on the vibration response data, calculate the root mean square value of the vibration response of the azimuth axis and pitch axis of the UAV seeker, and calculate its amplification factor relative to the input energy of the vibration table.

10. The vibration response detection method according to claim 9, characterized in that, The vibration response detection method is used to test multiple unmanned aerial vehicle seekers from the same batch, and the individual differences between products are quantified by comparing the magnification.

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