Test apparatus and test method for wind resistance testing of unmanned aerial vehicle seeker heads

Abstract

This application discloses a testing device and method for testing the drag of an unmanned aerial vehicle (UAV) seeker head. The testing device includes a mounting frame, an upper support assembly, a lower support shaft, an azimuth axis system, a pitch axis system, an L-shaped adapter rod, an inertial navigation system, and a servo control system. Using this method, the mounting frame is fixed to a test vehicle, and the test vehicle is started and driven to a preset Mach number. The inertial navigation system can acquire the attitude information of the UAV seeker head in real time, and the force measurement assembly can acquire force data. Using the testing device for testing the drag of an UAV seeker head of this application, the test vehicle can acquire drag data of the UAV seeker head under preset angle of attack and preset Mach number conditions even in a normal driving environment. This reduces the conditions for UAV seeker head testing, thereby reducing testing costs. Furthermore, it acquires a large amount of continuous drag data under operating conditions, thus providing guidance for the design of drag reduction schemes for UAV seeker heads.

Description

Technical Field

[0001] This application relates to the field of wind tunnel testing and measurement, and in particular to a testing device and method for testing the wind resistance of an unmanned aerial vehicle (UAV) seeker head. Background Technology

[0002] The optimization of the unmanned aerial vehicle (UAV) seeker head shape is receiving increasing attention in the overall design and demonstration of UAVs. UAVs have long ranges and extended operational times, and the seeker head, located at the nose of the UAV, requires a low-drag shape to effectively reduce overall drag, thereby significantly increasing the UAV's range over the same operational time. Therefore, drag reduction technology for the UAV seeker head is crucial in the overall design and demonstration of UAVs.

[0003] However, the high requirements for testing unmanned aerial vehicle (UAV) seekers, the high cost of ground-based wind tunnel testing, the difficulty in meeting the required test conditions, and the limited and discrete flight conditions (angle of attack, Mach number) all constrain the optimization of UAV seeker shapes and the development of drag reduction technologies. Therefore, there is an urgent need for a testing device with low testing requirements that can accurately measure the drag data of UAV seekers. Summary of the Invention

[0004] This application provides a testing device and method for testing the drag of an unmanned aerial vehicle (UAV) seeker head. It solves the technical problems of high research costs, long testing cycles, limited flight conditions, and discrete states in existing UAV seeker head drag reduction technologies. The technical solution is as follows:

[0005] On one hand, a testing device for testing the wind resistance of an unmanned aerial vehicle (UAV) seeker head is provided. The UAV seeker head includes a housing with a shaft hole inside the housing. The central axis of the shaft hole passes through the center of gravity of the UAV seeker head. The testing device includes: a mounting frame having a lower fixing hole, a middle fixing hole, and an upper fixing hole arranged coaxially from bottom to top; an upper support assembly passing through the upper fixing hole, including an outer cylinder and an inner shaft disposed within the outer cylinder, with the upper end of the inner shaft extending beyond the upper end of the outer cylinder; an upper force measuring assembly disposed between the upper fixing hole and the outer cylinder; a lower support shaft passing through the lower fixing hole, with a lower force measuring assembly disposed between the lower fixing hole and the lower support shaft; and an azimuth axis system having a first mounting cylinder, an azimuth motor, and a first output shaft, wherein the central axis of the first mounting cylinder coincides with the central axis of the first output shaft; the first mounting cylinder is fixedly connected to the middle fixing hole, and the outer... The lower end of the cylinder and the upper end of the lower support shaft are both fixedly connected to the first mounting cylinder, and the lower end of the inner shaft is connected to the first output shaft; the pitch axis system has a second mounting cylinder, a pitch motor, and a second output shaft, with the central axis of the second mounting cylinder coinciding with the central axis of the second output shaft; an L-shaped adapter rod includes a vertical rod and a horizontal rod, with the free end of the vertical rod fixedly connected to the upper end of the inner shaft, and the free end of the horizontal rod fixedly connected to the second mounting cylinder, and the central axis of the second mounting cylinder is horizontal; an inertial navigation system is mounted on the second output shaft, and the coordinate system of the inertial navigation system follows the right-hand coordinate system principle, wherein the Z-axis of the inertial navigation system coincides with the central axis of the second output shaft, and the X-axis coincides with the central axis of the horizontal rod; and a servo control system, wherein the azimuth motor, pitch motor, upper force measuring component, and lower force measuring component are all electrically connected to the control system.

[0006] Optionally, a bearing is provided between the inner shaft and the outer cylinder.

[0007] Optionally, the bearing is located at the upper end of the outer cylinder.

[0008] Optionally, the mounting frame is a spatial cuboid frame, which has a lower grid frame, a middle grid frame, and an upper grid frame arranged sequentially from bottom to top. The lower grid frame and the middle grid frame are connected by a connecting rod, and the middle grid frame and the upper grid frame are connected by a connecting rod. The lower fixing hole is located at the center of the lower grid frame. The middle fixing hole is located at the center of the lower grid frame. The upper fixing hole is located at the center of the lower grid frame.

[0009] Optionally, the upper force measuring assembly includes four force sensors, which are circumferentially evenly distributed between the outer cylinder and the upper fixing hole, with one of the force sensors being in the same plane as the crossbar; the lower force measuring assembly includes four force sensors, which are circumferentially evenly distributed between the lower support shaft and the lower fixing hole, with one of the force sensors being in the same plane as the crossbar.

[0010] Optionally, the inertial navigation system includes a gyroscope and an accelerometer.

[0011] Secondly, a test method is provided for a test apparatus for testing the wind resistance of an unmanned aerial vehicle (UAV) seeker head, applied to the aforementioned test apparatus, the test method comprising:

[0012] Step 1: Install the inertial navigation system to the first output shaft, and then install the unmanned aerial vehicle seeker head to the first output shaft;

[0013] Step 2: Fix the mounting bracket on the test vehicle, so that the pitch and azimuth angles of the UAV seeker are at zero and the electric lock is engaged, and the upper force measuring component and the lower force measuring component are at zero.

[0014] Step 3: Start the test vehicle and accelerate to the set Mach number. The servo control system controls the pitch motor to keep the pitch angle of the UAV seeker near the set angle of attack, and the deviation between the actual angle of attack and the set angle of attack is ±0.1°.

[0015] The servo control system controls the azimuth motor to keep the azimuth angle of the UAV seeker head near 0°, and the deviation between the actual azimuth angle and the azimuth angle of 0° is ±0.1°.

[0016] The inertial navigation system acquires the position, Mach number, azimuth, pitch angle and acceleration of the seeker head in real time;

[0017] The force sensor collects the upper force data of the upper force measuring component and the lower force data of the lower force measuring component in real time;

[0018] Step 4: Use data analysis software to unify the position, velocity, azimuth, pitch, acceleration, upper force, and lower force data over time. Select the position, velocity, azimuth, pitch, acceleration, upper force, and lower force data for the corresponding time period that simultaneously meets the requirements of the set angle of attack and set Mach number, and fit and calculate to obtain the first set of drag data for the UAV seeker.

[0019] Step 5: Repeat steps 3 and 4 with the same set angle of attack and set Mach number to obtain the second set of drag data for the unmanned aerial vehicle seeker.

[0020] Step 6: Repeat steps 3 and 4 with the same set angle of attack and set Mach number to obtain the third set of drag data for the seeker.

[0021] Step 7: Perform mean and variance statistics on the first, second, and third resistance data sets.

[0022] Optionally, between step 2 and step 3, the system may also perform self-tests of the servo control system, the inertial navigation system, the upper force measuring component, and the lower force measuring component.

[0023] Optionally, in step 4, the data analysis software is Matlab, Python, or OriginLab.

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

[0025] A testing device and method for testing the wind resistance of an unmanned aerial vehicle (UAV) seeker head are disclosed. The testing device includes: a mounting frame, an upper support assembly, a lower support shaft, an azimuth axis system, a pitch axis system, an L-shaped adapter rod, an inertial navigation system, and a servo control system. Using the above technical solution, the mounting frame is fixed to a test vehicle. The test vehicle is started and driven to a preset Mach number. The inertial navigation system can acquire the attitude information of the UAV seeker head in real time, such as position, velocity, azimuth angle, pitch angle, and acceleration, and feed this attitude information back to the servo control system. The upper force measuring assembly can acquire the force data of the upper support assembly, and the lower force measuring assembly can acquire the force data of the lower support shaft, and feed this force data information back to the servo control system. During operation, the test vehicle is affected by natural conditions, and its actual speed may not be the preset Mach number. Similarly, the actual angle of attack and azimuth of the UAV seeker may not be the preset angle of attack or azimuth. The servo control system can control the pitch motor in real time based on the acquired attitude information to bring the UAV seeker's angle of attack as close as possible to the preset angle of attack. The servo control system can also control the azimuth motor to bring the UAV seeker's azimuth as close as possible to the preset azimuth, for example, 0°. This reduces the requirements for UAV seeker testing. Using the test device for UAV seeker drag testing proposed in this application, the test vehicle can acquire drag data of the UAV seeker under preset angle of attack and preset Mach number conditions even in a normal driving environment. This reduces the testing conditions and costs, and provides more continuous drag data under various operating conditions, thus providing guidance for the design of drag reduction schemes for UAV seekers.

[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 3D view of a seeker head for an unmanned aerial vehicle;

[0029] Figure 2 This is a partial cross-sectional view of a seeker head for an unmanned aerial vehicle;

[0030] Figure 3 This is a three-dimensional schematic diagram of the test device for wind resistance testing of the seeker head of an unmanned aerial vehicle provided in the embodiments of this application;

[0031] Figure 4 This is a three-dimensional schematic diagram of the connection between the L-shaped adapter rod and the pitch axis of the test device for wind resistance testing of the unmanned aerial vehicle seeker provided in the embodiments of this application;

[0032] Figure 5 This is a front cross-sectional view of the test device for wind resistance testing of the unmanned aerial vehicle seeker provided in the embodiments of this application;

[0033] Figure 6 yes Figure 5 A magnified view of a section at point A in the middle;

[0034] Figure 7 yes Figure 5 A magnified view of a section at point B in the middle;

[0035] Figure 8 This is a three-dimensional schematic diagram of the mounting frame in the test device for wind resistance testing of the unmanned aerial vehicle seeker provided in the embodiments of this application;

[0036] Figure 9 This is a flowchart of a test method for a test device used for wind resistance testing of an unmanned aerial vehicle (UAV) seeker, as provided in an embodiment of this application.

[0037] Explanation of reference numerals in the attached figures

[0038] 1-Unmanned Aerial Vehicle (UAV) seeker head; 101-Housing; 102-Shaft hole; 2-Mounting bracket; 201-Lower fixing hole; 202-Middle fixing hole; 203-Upper fixing hole; 204-Lower grid frame; 205-Middle grid frame; 206-Upper grid frame; 3-Upper support assembly; 301-Outer cylinder; 302-Inner shaft; 4-Upper force measuring assembly; 5-Lower support shaft; 6-Lower force measuring assembly; 7-Azimuth axis system; 701-First mounting cylinder; 702-Azimuth motor; 703-First output shaft; 8-Pitch axis system; 801-Second mounting cylinder; 802-Pitch motor; 803-Second output shaft; 9-L-shaped adapter rod; 901-Vertical rod; 902-Horizontal rod; 10-Inertial navigation system; 11-Bearing. Detailed Implementation

[0039] 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.

[0040] 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.

[0041] Testing unmanned aerial vehicle (UAV) seekers requires stringent environmental conditions. Dedicated ground-based wind tunnel testing is expensive and difficult to meet, and flight conditions (angle of attack, Mach number) are limited and discrete. These factors restrict the optimization of UAV seeker shapes and the development of drag reduction technologies. There is an urgent need for a testing device with low requirements that can accurately measure the drag data of UAV seekers.

[0042] According to a first aspect of this application, a test apparatus is provided for testing the wind resistance of an unmanned aerial vehicle (UAV) seeker head 1, with reference to... Figure 1 and Figure 2 The unmanned aerial vehicle (UAV) seeker 1 includes a housing 101, and the housing 101 has a shaft hole 102 inside. The central axis of the shaft hole 102 passes through the center of gravity of the UAV seeker 1.

[0043] refer to Figures 3 to 7 The testing device includes: a mounting frame 2, an upper support assembly 3, a lower support shaft 5, an azimuth axis system 7, a pitch axis system 8, an L-shaped adapter rod 9, an inertial navigation system 10, and a servo control system.

[0044] Among them, reference Figure 2 The mounting bracket 2 has a lower fixing hole 201, a middle fixing hole 202 and an upper fixing hole 203 arranged coaxially from bottom to top; the upper support assembly 3 passes through the upper fixing hole 203 and includes an outer cylinder 301 and an inner shaft 302 disposed in the outer cylinder 301, with the upper end of the inner shaft 302 extending out of the upper end of the outer cylinder 301; an upper force measuring assembly 4 is disposed between the upper fixing hole 203 and the outer cylinder 301; the lower support shaft 5 passes through the lower fixing hole 201 and a lower force measuring assembly 6 is disposed between the lower fixing hole 201 and the lower support shaft 5.

[0045] refer to Figures 5 to 7 The azimuth axis system 7 has a first mounting cylinder 701, an azimuth motor 702 and a first output shaft 703. The central axis of the first mounting cylinder 701 and the central axis of the first output shaft 703 coincide. The first mounting cylinder 701 is fixedly connected to the central fixing hole 202. The lower end of the outer cylinder 301 and the upper end of the lower support shaft 5 are both fixedly connected to the first mounting cylinder 701. The lower end of the inner shaft 302 is connected to the first output shaft 703.

[0046] refer to Figures 4 to 6 The pitch axis system 8 has a second mounting cylinder 801, a pitch motor 802, and a second output shaft 803. The central axis of the second mounting cylinder 801 and the central axis of the second output shaft 803 coincide. The L-shaped adapter rod 9 includes a vertical rod portion 901 and a horizontal rod portion 902. The free end of the vertical rod portion 901 is fixedly connected to the upper end of the inner shaft 302, and the free end of the horizontal rod portion 902 is fixedly connected to the second mounting cylinder 801. The central axis of the second mounting cylinder 801 is horizontal.

[0047] refer to Figure 4 The inertial navigation system 10 is mounted on the second output shaft 803. The coordinate system of the inertial navigation system 10 follows the right-hand coordinate system principle. Specifically, the Z-axis of the inertial navigation system 10 coincides with the central axis of the second output shaft 803, and the X-axis coincides with the central axis of the crossbar 902. A servo control system is also included, with the orientation motor 702, the servo motor, the upper force measuring component 4, and the lower force measuring component 6 all electrically connected to the control system.

[0048] Using the above technical solution, the mounting bracket 2 is fixed on the test vehicle. Once the test vehicle is started and travels to a preset Mach number, the inertial navigation system 10 can acquire the attitude information of the UAV seeker head 1 in real time, such as position, velocity, azimuth, pitch angle, and acceleration, and feed this attitude information back to the servo control system. The upper force measuring component 4 can acquire the force data of the upper support component 3, and the lower force measuring component 6 can acquire the force data of the lower support shaft 5, and feed this force data information back to the servo control system. During travel, the test vehicle will be affected by natural conditions, and the actual travel speed may not be the preset Mach number. The actual angle of attack of the UAV seeker head 1 may also not be the preset angle of attack, and the actual azimuth angle may also not be the preset azimuth angle. The servo control system can control the pitch motor 802 in real time based on the acquired attitude information to make the angle of attack of the UAV seeker head 1 as close as possible to the preset angle of attack. The servo control system can also control the azimuth motor 702 to make the azimuth angle of the UAV seeker head 1 as close as possible to the preset azimuth angle, for example, 0°. This reduces the requirements for testing the unmanned aerial vehicle (UAV) seeker head 1. Using the test device for wind resistance testing of the UAV seeker head 1 as described in this application, the test vehicle can acquire drag data of the UAV seeker head 1 under preset angle of attack and preset Mach number conditions even in a normal driving environment. This reduces the testing conditions for the UAV seeker head 1, thereby reducing testing costs. Furthermore, the acquired drag data is more abundant and continuous, thus providing guidance for the drag reduction design of the UAV seeker head 1.

[0049] To reduce the frictional resistance between the outer cylinder 301 and the inner shaft 302, refer to Figure 5 and Figure 6 A bearing 11 is provided between the inner shaft 302 and the outer cylinder 301, and the bearing 11 is located at the upper end of the outer cylinder 301. In practice, a collar can be provided between the outer cylinder 301 and the inner shaft 302 according to actual needs, and the friction can be reduced by applying grease to the collar. This application does not limit this.

[0050] According to the embodiments of this application, refer to Figure 3 and Figure 8 The mounting frame 2 is a spatial cuboid frame, which has a lower field frame 204, a middle field frame 205 and an upper field frame 206 arranged sequentially from bottom to top. The lower field frame 204 and the middle field frame 205 are connected by a connecting rod, and the middle field frame 205 and the upper field frame 206 are connected by a connecting rod. The lower fixing hole 201 is located at the center of the lower field frame 204; the middle fixing hole 202 is located at the center of the lower field frame 204; and the upper fixing hole 203 is located at the center of the lower field frame 204.

[0051] With this design, the mounting bracket 2 experiences less resistance when it is installed on the test vehicle, thus enabling the test vehicle to travel at a higher speed.

[0052] According to the embodiments of this application, refer to Figure 3 The upper force measuring component 4 includes four force sensors, which are evenly distributed circumferentially between the outer cylinder 301 and the upper fixing hole 203. One of the force sensors is in the same plane as the crossbar 902. The four force sensors can measure the force on the outer cylinder 301 in four directions, thereby providing a basis for calculating the drag characteristics of the unmanned aerial vehicle seeker 1.

[0053] Similarly, the lower force-measuring assembly 6 includes four force sensors, which are evenly distributed circumferentially between the lower support shaft 5 and the lower fixing hole 201. One of the force sensors is in the same plane as the crossbar 902. The four force sensors can measure the forces acting on the outer cylinder 301 in four directions, thus providing a basis for calculating the drag characteristics of the unmanned aerial vehicle seeker 1.

[0054] According to an embodiment of this application, the inertial navigation system 10 includes a gyroscope and an accelerometer.

[0055] According to the second aspect of this application, reference to Figure 9 A test method for a test apparatus used for wind resistance testing of an unmanned aerial vehicle (UAV) seeker head is provided. The test apparatus is applied to the aforementioned test apparatus, and the test method includes:

[0056] Step 1: Install the inertial navigation system 10 to the first output shaft 703, and then install the unmanned aerial vehicle seeker head 1 to the first output shaft 703;

[0057] Step 2: Fix the mounting bracket 2 on the test vehicle, so that the pitch and azimuth angles of the UAV seeker head 1 are at zero and the electric lock is engaged, and the upper force measuring component 4 and the lower force measuring component 6 are at zero.

[0058] Step 3: Start the test vehicle and accelerate to the set Mach number. The servo control system controls the pitch motor 802 to keep the pitch angle of the unmanned aerial vehicle seeker 1 near the set angle of attack, and the deviation between the actual angle of attack and the set angle of attack is ±0.1°.

[0059] The servo control system controls the azimuth motor 702 to keep the azimuth angle of the unmanned aerial vehicle seeker 1 near 0°, and the deviation between the actual azimuth angle and the azimuth angle of 0° is ±0.1°.

[0060] The inertial navigation system 10 acquires the position, Mach number, azimuth angle, pitch angle, and acceleration of the seeker head in real time.

[0061] The force sensor collects the upper force data of the upper force measuring component 4 and the lower force data of the lower force measuring component 6 in real time;

[0062] Step 4: Use data analysis software to unify the position, velocity, azimuth, pitch, acceleration, upper force data and lower force data over time. Select the position, velocity, azimuth, pitch, acceleration, upper force data and lower force data of the corresponding time period that simultaneously meets the requirements of the set angle of attack and the set Mach number, and fit and calculate to obtain the first set of drag data of the UAV seeker 1.

[0063] Step 5: Repeat steps 3 and 4 with the same set angle of attack and set Mach number to obtain the second set of drag data for the unmanned aerial vehicle seeker 1.

[0064] Step 6: Repeat steps 3 and 4 with the same set angle of attack and set Mach number to obtain the third set of drag data for the seeker.

[0065] Step 7: Perform mean and variance statistics on the first, second, and third resistance data sets.

[0066] In practice, the more resistance data samples there are, the more accurate the results will be, and the closer the obtained resistance data will be to the true value. The tester can decide the number of tests based on the actual situation, and this application does not impose any restrictions on this.

[0067] Optionally, between steps 2 and 3, a self-test of the servo control system, the inertial navigation system 10, the upper force measuring component 4, and the lower force measuring component 6 may be included. This self-test procedure can reduce the error of the testing device itself.

[0068] Optionally, in step 4, the data analysis software can be Matlab, Python, or OriginLab.

[0069] 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.

[0070] 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.

[0071] 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 testing device for wind resistance testing of an unmanned aerial vehicle (UAV) seeker head, wherein the UAV seeker head (1) includes a housing (101), the housing (101) having a shaft hole (102) therein, the central axis of the shaft hole (102) passing through the center of gravity of the UAV seeker head (1), characterized in that, The testing apparatus includes: The mounting bracket (2) has a lower fixing hole (201), a middle fixing hole (202) and an upper fixing hole (203) arranged coaxially from bottom to top; The upper support assembly (3) passes through the upper fixing hole (203) and includes an outer cylinder (301) and an inner shaft (302) disposed in the outer cylinder (301), with the upper end of the inner shaft (302) extending out of the upper end of the outer cylinder (301). An upper force measuring assembly (4) is provided between the upper fixing hole (203) and the outer cylinder (301). The lower support shaft (5) passes through the lower fixing hole (201), and a lower force measuring component (6) is provided between the lower fixing hole (201) and the lower support shaft (5); The azimuth axis system (7) has a first mounting cylinder (701), an azimuth motor (702), and a first output shaft (703). The central axis of the first mounting cylinder (701) and the central axis of the first output shaft (703) coincide. The first mounting cylinder (701) is fixedly connected to the middle fixing hole (202). The lower end of the outer cylinder (301) and the upper end of the lower support shaft (5) are both fixedly connected to the first mounting cylinder (701). The lower end of the inner shaft (302) is connected to the first output shaft (703). The pitch axis system (8) has a second mounting cylinder (801), a pitch motor (802), and a second output shaft (803), wherein the central axis of the second mounting cylinder (801) and the central axis of the second output shaft (803) coincide; L-shaped adapter rod (9) includes a vertical rod part (901) and a horizontal rod part (902). The free end of the vertical rod part (901) is fixedly connected to the upper end of the inner shaft (302). The free end of the horizontal rod part (902) is fixedly connected to the second mounting cylinder (801), and the central axis of the second mounting cylinder (801) is horizontal. An inertial navigation system (10) is installed on the second output shaft (803). The coordinate system of the inertial navigation system (10) follows the right-hand coordinate system principle. The Z-axis of the inertial navigation system (10) coincides with the central axis of the second output shaft (803), and the X-axis coincides with the central axis of the crossbar (902). The servo control system includes an azimuth motor (702), a pitch motor (802), an upper force measuring component (4), and a lower force measuring component (6), all of which are electrically connected to the control system.

2. The testing apparatus for wind resistance testing of unmanned aerial vehicle seeker head according to claim 1, characterized in that, A bearing (11) is provided between the inner shaft (302) and the outer cylinder (301).

3. The testing apparatus for wind resistance testing of unmanned aerial vehicle seeker heads according to claim 2, characterized in that, The bearing (11) is located at the upper end of the outer cylinder (301).

4. The testing apparatus for wind resistance testing of unmanned aerial vehicle seeker head according to claim 3, characterized in that, The mounting frame (2) is a spatial cuboid frame. The spatial cuboid frame has a lower field frame (204), a middle field frame (205) and an upper field frame (206) arranged sequentially from bottom to top. The lower field frame (204) and the middle field frame (205) are connected by a connecting rod, and the middle field frame (205) and the upper field frame (206) are connected by a connecting rod. The lower fixing hole (201) is located at the center of the lower field frame (204); The central fixing hole (202) is located at the center of the lower field frame (204); The upper fixing hole (203) is located at the center of the lower field frame (204).

5. The testing apparatus for wind resistance testing of unmanned aerial vehicle seeker head according to claim 1, characterized in that, The upper force measuring component (4) includes four force sensors. The four force sensors are evenly distributed circumferentially between the outer cylinder (301) and the upper fixing hole (203). One of the force sensors is in the same plane as the crossbar (902). The lower force measuring component (6) includes four force sensors, which are evenly distributed circumferentially between the lower support shaft (5) and the lower fixing hole (201), and one of the force sensors is in the same plane as the crossbar (902).

6. The testing apparatus for wind resistance testing of unmanned aerial vehicle seeker head according to claim 1, characterized in that, The inertial navigation system (10) includes a gyroscope and an accelerometer.

7. A test method for a test apparatus used for testing the wind resistance of an unmanned aerial vehicle (UAV) seeker head, applied to the test apparatus described in any one of claims 1-6, characterized in that, The testing method includes: Step 1: Install the inertial navigation system to the first output shaft, and then install the unmanned aerial vehicle seeker head to the first output shaft; Step 2: Fix the mounting bracket on the test vehicle, so that the pitch and azimuth angles of the UAV seeker are at zero and the electric lock is engaged, and the upper force measuring component and the lower force measuring component are at zero. Step 3: Start the test vehicle and accelerate to the set Mach number. The servo control system controls the pitch motor to keep the pitch angle of the UAV seeker near the set angle of attack, and the deviation between the actual angle of attack and the set angle of attack is ±0.1°. The servo control system controls the azimuth motor to keep the azimuth angle of the UAV seeker head near 0°, and the deviation between the actual azimuth angle and the azimuth angle of 0° is ±0.1°. The inertial navigation system acquires the position, Mach number, azimuth, pitch angle and acceleration of the seeker head in real time; The force sensor collects the upper force data of the upper force measuring component and the lower force data of the lower force measuring component in real time; Step 4: Use data analysis software to unify the position, velocity, azimuth, pitch, acceleration, upper force, and lower force data over time. Select the position, velocity, azimuth, pitch, acceleration, upper force, and lower force data for the corresponding time period that simultaneously meets the requirements of the set angle of attack and set Mach number, and fit and calculate to obtain the first set of drag data for the UAV seeker. Step 5: Repeat steps 3 and 4 with the same set angle of attack and set Mach number to obtain the second set of drag data for the unmanned aerial vehicle seeker. Step 6: Repeat steps 3 and 4 with the same set angle of attack and set Mach number to obtain the third set of drag data for the seeker. Step 7: Perform mean and variance statistics on the first, second, and third resistance data sets.

8. The test method of the test device for testing the wind resistance of an unmanned aerial vehicle seeker according to claim 7, characterized in that, Between step 2 and step 3, there are also self-tests for the servo control system, the inertial navigation system, the upper force measuring component, and the lower force measuring component.

9. The test method of the test device for testing the wind resistance of an unmanned aerial vehicle seeker according to claim 7, characterized in that, In step 4, the data analysis software is Matlab, Python, or OriginLab.

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