Flight attitude simulation test tool, system and method

Abstract

The invention relates to a flight attitude simulation test, in particular to a flight attitude simulation test tool, system and method. An azimuth axis rotary table is arranged in the middle of the lifting platform, a base of the azimuth axis rotary table is connected with the lifting platform, and a U-shaped supporting frame is arranged at the top of a rotary platform of the azimuth axis rotary table. A pitch axis motor and a pitch axis encoder are arranged on the two sides of the supporting frame respectively, and an output shaft of the pitch axis motor and an input shaft of the pitch axis encoder both extend into the supporting frame; the upper part of the support frame is provided with a product mounting frame of which the two ends are respectively connected with an output shaft of the pitch shaft motor and an input shaft of the pitch shaft encoder; a protective cylinder is arranged on one side of the product mounting rack, a transverse roller rotary table is arranged on the other side of the product mounting rack, a base of the transverse roller rotary table is connected with the product mounting rack, and a mounting seat is arranged on a rotary table of the transverse roller rotary table; and a fixed carrier of the product penetrates through the protective cylinder and is connected with the mounting seat. According to the invention, the requirements of modern missiles on high-precision and multi-degree-of-freedom simulation tests can be met.

Description

Technical Field

[0001] The present invention relates to flight attitude simulation testing, and particularly to a flight attitude simulation testing tooling, system and method. Background Art

[0002] As an important weapon system in modern national defense, the precise control of the flight attitude of a missile is a key factor to ensure the hitting accuracy and mission success. During the flight process, the missile needs to experience complex attitude changes, including pitching, rolling and yawing motions. In order to ensure that the missile can perform these attitude changes stably and accurately during actual flight, it is necessary to conduct strict flight attitude simulation tests during the R & D and production stages.

[0003] Traditional flight attitude simulation testing methods mainly rely on static testing and simple dynamic simulation, and these methods often cannot comprehensively simulate the complex attitude changes of the missile during actual flight. In addition, traditional testing equipment usually has a simple structure and single function, and it is difficult to meet the requirements of modern missiles for high-precision and multi-degree-of-freedom simulation testing.

[0004] Therefore, there is an urgent need to provide a testing tooling and system that can accurately simulate the flight attitude of a missile to improve the R & D efficiency and quality of the missile. Summary of the Invention

[0005] The object of the present invention is to solve the technical problem that the existing testing equipment has a simple structure and single function and is difficult to meet the requirements of high-precision and multi-degree-of-freedom simulation testing, and to provide a flight attitude simulation testing tooling, system and method.

[0006] To solve the above technical problems, the technical solution provided by the present invention is as follows:

[0007] A flight attitude simulation testing tooling includes a base and a lifting platform installed in the base through a lifting assembly;

[0008] A azimuth axis turntable is provided in the middle of the lifting platform. The base of the azimuth axis turntable is connected to the lifting platform, and a U-shaped support frame is provided at the top of the rotating platform of the azimuth axis turntable;

[0009] A pitching axis motor and a pitching axis encoder are respectively provided on both sides of the support frame. The output shaft of the pitching axis motor and the input shaft of the pitching axis encoder both extend into the interior of the support frame;

[0010] A product mounting frame is provided at the upper part of the support frame, and both ends of the product mounting frame are respectively connected to the output shaft of the pitching axis motor and the input shaft of the pitching axis encoder;

[0011] One side of the product mounting bracket is provided with a protection cylinder, and the other side of the product mounting bracket is provided with a roll axis turntable. The base of the roll axis turntable is connected to the product mounting bracket, and a mounting seat is provided on the rotating table of the roll axis turntable; the fixed carrier of the product passes through the protection cylinder and is connected to the mounting seat.

[0012] Further, the lifting assembly includes two fixed brackets. On one side of the two fixed brackets close to each other, a motor fixing seat, an upper threaded seat and a lower threaded seat are successively arranged from top to bottom;

[0013] A lifting servo motor is provided on the motor fixing seat;

[0014] A stud is rotatably installed between the upper threaded seat and the lower threaded seat, and two guide columns distributed on both sides of the stud;

[0015] The output end of the lifting servo motor is connected to the stud;

[0016] A nut seat is threadedly installed on the stud, and the nut seat is slidably sleeved on the guide column.

[0017] Further, one end of the product is provided with an external thread, and the fixed carrier is provided with an internal thread corresponding to the external thread of the product;

[0018] One end of the product close to the external thread is provided with a product fastener, and the inner wall of the product fastener fits against the outer wall of the fixed carrier;

[0019] A plurality of circumferentially evenly distributed threaded holes are provided in the product fastener, and screws are threadedly installed in the threaded holes of the product fastener. The ends of the screws penetrate through the fixed carrier and abut against the product.

[0020] Further, a spirit level seat is fixed on the top of the lifting platform by a plurality of fastening screws;

[0021] A spirit level is provided on the top of the spirit level seat, and the spirit level is fixed on the top of the spirit level seat by a plurality of adjusting screws.

[0022] Further, a locking screw is threadedly installed on the outer side wall of the mounting seat;

[0023] The end of the locking screw penetrates through the fixed carrier and abuts against a touch signal receiver arranged inside the fixed carrier.

[0024] Further, a north finder is provided on the top of the lifting platform.

[0025] A flight attitude simulation test system includes a measurement and control unit, and a flight attitude simulation control unit, a video monitoring unit and a remote control terminal connected to the measurement and control unit;

[0026] The measurement and control unit includes a cRIO system, as well as a device power supply and control unit, a product power supply, and a signal conditioning module that are respectively connected to the cRIO system through an I / O interface, an RS422 communication interface, and an analog signal acquisition module;

[0027] The cRIO system is also connected with a signal isolation and switching control module through an RS232 interface and three RS422 communication interfaces;

[0028] The video monitoring unit, the flight attitude simulation control unit, the product power supply, the signal conditioning module, and the signal isolation and switching control module are all connected to the device power supply and control unit;

[0029] The product power supply, the signal conditioning module, and the signal isolation and switching control module are connected to the product;

[0030] The cRIO system is respectively connected to the flight attitude simulation control unit and the video monitoring unit through a USB control interface and a Lan port; the cRIO system communicates with the remote control terminal wirelessly.

[0031] Further, the flight attitude simulation control unit includes a controller, a driver module, and a power supply module;

[0032] The driver module includes multiple drivers that are respectively connected to an azimuth axis turntable, a pitch axis motor, a roll axis turntable, and a lift servo motor, and the multiple drivers are all connected to the controller;

[0033] The controller is connected to a north finder, a touch signal receiver, a pitch axis encoder, an azimuth axis encoder of the azimuth axis turntable, and a roll axis encoder of the roll axis turntable;

[0034] The controller is connected to the RS422 communication interface of the cRIO system through a serial bus interface;

[0035] The azimuth axis turntable, the pitch axis motor, the roll axis turntable, the lift servo motor, the north finder, the controller, and the driver are all connected to the power supply module, and the power supply module is connected to the device power supply and control unit.

[0036] A flight attitude simulation test method includes the following steps:

[0037] S1. Set flight attitude simulation motion parameters through the remote control terminal and send them to the cRIO system;

[0038] S2. Send a power supply instruction to the cRIO system through the remote control terminal;

[0039] The cRIO system executes the power supply instruction and drives the device power supply and control unit to supply power to the video surveillance unit, flight attitude simulation control unit, product power supply, signal conditioning module, and signal isolation switching control module;

[0040] S3. The flight attitude simulation control unit controls the actions of the corresponding azimuth axis turntable, pitch axis motor, and roll axis turntable according to the flight attitude simulation motion parameters;

[0041] S4. The cRIO system collects the operation data of the product through the analog signal acquisition module and the signal conditioning module, and sends it to the remote control terminal;

[0042] S5. The remote control terminal receives the operation data and compares it with the operation data of the standard product;

[0043] If the difference between the operation data and the operation data of the standard product is within the threshold range, the product is qualified; otherwise, the product is unqualified;

[0044] Complete the flight attitude simulation test of the product.

[0045] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0046] The flight attitude simulation test tooling, system, and method provided by the present invention can realize the simulation of the azimuth, pitch, and roll flight postures of a missile by integrating a lifting component, an azimuth axis turntable, a pitch axis motor, and a roll axis turntable; at the same time, through the cRIO system, the analog signal acquisition module, and the signal conditioning module, it can realize the real-time acquisition and processing of the product operation data, ensuring the accuracy and reliability of the test results; it can not only meet the requirements of modern missiles for high-precision and multi-degree-of-freedom simulation tests, but also improve the test efficiency and accuracy, providing strong technical support for the research and development and production of missiles. Description of the Drawings

[0047] Figure 1 It is a schematic structural diagram of an embodiment of the flight attitude simulation test tooling of the present invention;

[0048] Figure 2 It is a schematic structural diagram of the lifting component in the embodiment of the flight attitude simulation test tooling of the present invention;

[0049] Figure 3 It is a schematic structural diagram of the product mounting rack and the product in the embodiment of the flight attitude simulation test tooling of the present invention;

[0050] Figure 4 It is a schematic structural diagram of the bubble seat and the bubble in the embodiment of the flight attitude simulation test tooling of the present invention;

[0051] Figure 5Schematic structural diagram of an embodiment of the flight attitude simulation test system of the present invention;

[0052] Figure 6 Schematic structural diagram of the flight attitude simulation control unit in an embodiment of the flight attitude simulation test system of the present invention;

[0053] Figure 7 Schematic flow diagram of an embodiment of the flight attitude simulation test method of the present invention.

[0054] Description of reference numerals: 1 - base, 2 - lifting assembly, 21 - fixing frame, 22 - motor fixing base, 23 - upper threaded seat, 24 - lower threaded seat, 25 - lifting servo motor, 26 - stud, 27 - guide post, 28 - nut seat, 3 - lifting platform, 4 - azimuth axis turntable, 5 - support frame, 6 - pitch axis motor, 7 - pitch axis encoder, 8 - product mounting frame, 9 - protection cylinder, 10 - roll axis turntable, 11 - mounting seat, 12 - product, 121 - product fastener, 122 - threaded hole, 13 - fixed carrier, 14 - spirit level seat, 15 - fastening screw, 16 - spirit level, 17 - adjusting screw, 18 - locking screw, 19 - north finder. Detailed implementation manners

[0055] The following will clearly and completely describe the technical solutions in the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without making creative efforts belong to the scope of protection of the present invention.

[0056] As Figure 1 shown, a flight attitude simulation test tooling includes a base 1 and a lifting platform 3 installed in the base 1 through a lifting assembly 2;

[0057] As Figure 1 shown, in order to implement the test of the azimuth data of the product 12, an azimuth axis turntable 4 is provided in the middle of the lifting platform 3. The base of the azimuth axis turntable 4 is connected to the lifting platform 3, and a U-shaped support frame 5 is provided at the top of the rotating platform of the azimuth axis turntable 4; A pitch axis motor 6 and a pitch axis encoder 7 are respectively provided on both sides of the support frame 5, and the output shaft of the pitch axis motor 6 and the input shaft of the pitch axis encoder 7 both extend into the interior of the support frame 5;

[0058] As Figure 1 and Figure 3As shown in the figure, in order to test the pitching data of product 12, a product mounting bracket 8 is provided at the upper part of the support frame 5, with both ends thereof being connected to the output shaft of the pitching axis motor 6 and the input shaft of the pitching axis encoder 7 respectively; in order to ensure the safety of the test process and prevent product 12 and the fixed carrier 13 from being thrown out, a protective cylinder 9 is provided on one side of the product mounting bracket 8; in order to test the roll data of product 12, a roll axis turntable 10 is provided on the other side of the product mounting bracket 8, the base of the roll axis turntable 10 is connected to the product mounting bracket 8, and a mounting seat 11 is provided on the rotating table of the roll axis turntable 10; the fixed carrier 13 of product 12 passes through the protective cylinder 9 and is connected to the mounting seat 11.

[0059] In order to ensure the electrical isolation between product 12 and the flight attitude simulation test tooling, both the mounting seat 11 and the protective cylinder 9 are made of high-strength polytetrafluoroethylene material.

[0060] As Figure 2 shown in the figure, in order to facilitate the disassembly and assembly of product 12 and avoid the interference of the external environment on the test process of product 12, the lifting assembly 2 includes two fixed brackets 21. On the side where the two fixed brackets 21 are close to each other, a motor fixing seat 22, an upper threaded seat 23 and a lower threaded seat 24 are successively provided from top to bottom; a lifting servo motor 25 is provided on the motor fixing seat 22; a stud 26 is rotatably installed between the upper threaded seat 23 and the lower threaded seat 24, and two guide posts 27 are distributed on both sides of the stud 26; the output end of the lifting servo motor 25 is connected to the stud 26; a nut seat 28 is threadedly installed on the stud 26, and the nut seat 28 is slidably sleeved on the guide post 27.

[0061] As Figure 3 shown in the figure, in order to fix product 12 to the fixed carrier 13, one end of product 12 is provided with an external thread, and the fixed carrier 13 is provided with an internal thread corresponding to the external thread of product 12; a product fastener 121 is provided at one end of product 12 close to the external thread, and the inner wall of the product fastener 121 is attached to the outer wall of the fixed carrier 13; a plurality of circumferentially evenly distributed threaded holes 122 are provided on the product fastener 121, and screws are threadedly installed in the threaded holes 122 of the product fastener 121, and the end of the screw penetrates through the fixed carrier 13 and abuts against product 12.

[0062] As Figure 4 shown in the figure, in order to facilitate leveling after the flight attitude simulation test tooling is installed on the mechanical motion unit; a bubble seat 14 is fixed to the top of the lifting platform 3 through a plurality of fastening screws 15; a bubble 16 is provided on the top of the bubble seat 14, and the bubble 16 is fixed to the top of the bubble seat 14 through a plurality of adjusting screws 17.

[0063] As Figure 1 and Figure 3As shown, a locking screw 18 is threadedly installed on the outer side wall of the mounting base 11; the end of the locking screw 18 penetrates through the fixed carrier 13 and abuts against a touch signal receiver provided inside the fixed carrier 13.

[0064] As Figure 1 shown, a north-seeking instrument 19 is provided on the top of the lifting platform 3. The north-seeking instrument 19 is a gyro north-seeking instrument 19, which uses the two basic characteristics of the precession and fixed-axis properties of the gyroscope to achieve autonomous north-seeking. The axis of rotation of the gyroscope remains fixed in orientation relative to inertial space while the Earth rotates relative to inertial space about its polar axis with its angular velocity of rotation. If the Earth is taken as the reference benchmark, it will be seen that the axis of rotation of the gyroscope rotates relative to the Earth. Therefore, the gyroscope can track and measure the angular velocity of the Earth's rotation, and obtain the azimuth information of the reference axis of the product 12 by using the different motion components of the angular velocity of the Earth's rotation sensed by the gyroscope. Then, through two-axis accelerometers, the inclination data of the product 12 in the axial direction can be obtained. Thus, the angle between the gyro spindle and the true north direction of the Earth is calculated. The north-seeking instrument 19 sends the angle between the zero position of the flight attitude simulation test tooling and the true north direction to the controller, and then the controller controls the azimuth axis turntable to rotate so that the zero position (the product under test) of the flight attitude simulation test tooling faces true north. After facing true north, the communication between the product under test and the satellite is started.

[0065] As Figure 1 shown, in order to ensure that the turntable does not move during the installation of the product 12, an anti-rotation safety plug is designed between the turntable and the lifting table. When the turntable is lifted to the highest position for the installation of the product 12, if the anti-rotation safety plug is not pulled out, then even if the device is powered on, the azimuth axis turntable 4 cannot operate; this avoids the harm or physical strike caused to the product 12 installers by the misoperation of other operators when the product 12 is lifted to the highest position or when the operator installs the product 12.

[0066] As Figure 5 shown, a flight attitude simulation test system includes a measurement and control unit, and a flight attitude simulation control unit, a video monitoring unit, and a remote control terminal connected to the measurement and control unit;

[0067] The measurement and control unit includes a cRIO system, and a device power supply and control unit, a product power supply, and a signal conditioning module respectively connected to the cRIO system through an I / O interface, an RS422 communication interface, and an analog signal acquisition module; the cRIO system is also connected to a signal isolation and switching control module through an RS232 interface and three RS422 communication interfaces;

[0068] The video monitoring unit, the flight attitude simulation control unit, the product power supply, the signal conditioning module, and the signal isolation and switching control module are all connected to the device power supply and control unit;

[0069] The product power supply, signal conditioning module, signal isolation and switching control module are connected to Product 12;

[0070] The cRIO system is connected to the flight attitude simulation control unit and the video monitoring unit through the USB control interface and the Lan port respectively; the cRIO system communicates with the remote control terminal wirelessly.

[0071] The video monitoring unit is a video monitoring camera, which can be installed near the flight attitude simulation test tooling according to the actual monitoring area size and location. The video monitoring unit is mainly for the operator to observe the states of the flight attitude simulation test tooling and Product 12 in real time through the remote control terminal; the video output by the video monitoring camera can be transmitted to the remote control terminal.

[0072] The equipment power supply and control unit is used to supply power to the video monitoring unit, flight attitude simulation control unit, product power supply, signal conditioning module, and signal isolation and switching control module. In order to achieve mutual isolation between power supplies, each module adopts a separate power supply system; that is: the equipment power supply and control unit includes five electromagnetic relays, and the control terminals of the five electromagnetic relays are all connected to the cRIO system through the I / O interface; the moving contacts of the five electromagnetic relays are all connected to the power isolation and filtering module, and the power isolation and filtering module is connected to the 220V power supply; the static contacts of the five electromagnetic relays are respectively connected to the video monitoring unit, flight attitude simulation control unit, product power supply, signal conditioning module, and signal isolation and switching control module.

[0073] In actual applications, some of the various signals that need to be output and collected may not be within the output or acquisition input range of the cRIO system. Therefore, a signal conditioning module is required to condition this part of the signals. That is, attenuate and condition signals with larger amplitudes; if there are large interferences in the signals, filtering processing is also required; signals that may impact the test system and the product 12 to be measured may also require isolation, etc.

[0074] As Figure 6 shown, the flight attitude simulation control unit includes a controller, a driver module, and a power supply module; the driver module includes multiple drivers respectively connected to the azimuth axis turntable 4, pitch axis motor 6, roll axis turntable 10, and lift servo motor 25, and multiple drivers are all connected to the controller; the controller is connected to the north-seeking instrument 19, touch signal receiver, pitch axis encoder 7, azimuth axis encoder of the azimuth axis turntable 4, and roll axis encoder of the roll axis turntable 10; the controller is connected to the RS422 communication interface of the cRIO system through the serial bus interface;

[0075] The azimuth axis turntable 4, pitch axis motor 6, roll axis turntable 10, lift servo motor 25, north-seeking instrument 19, controller, and driver are all connected to the power supply module, and the power supply module is connected to the equipment power supply and control unit.

[0076] The controller is a DSP controller.

[0077] As Figure 7 shown, the present invention also provides a flight attitude simulation test method, and the specific steps are as follows:

[0078] 1) Establish communication connections between the cRIO system, the remote control terminal, the flight attitude simulation control unit, and the video monitoring unit;

[0079] 2) Configure the flight attitude simulation motion parameters through the remote control terminal and send them to the cRIO system;

[0080] 3) Send a power supply instruction to the cRIO system through the remote control terminal;

[0081] The cRIO system executes the power supply instruction and drives the device power supply and control unit to supply power to the video monitoring unit, the flight attitude simulation control unit, the product power supply, the signal conditioning module, and the signal isolation and switching control module;

[0082] 4) The video monitoring unit acquires the real-time video images of the flight attitude simulation test tooling and the product 12, and transmits them to the remote control terminal through the cRIO system;

[0083] 5) The flight attitude simulation control unit controls the corresponding azimuth axis turntable 4, pitch axis motor 6, and roll axis turntable 10 to act according to the flight attitude simulation motion parameters;

[0084] 6) The cRIO system acquires the operation data of the product 12 through the analog signal acquisition module and the signal conditioning module, and sends it to the remote control terminal;

[0085] 7) The remote control terminal receives and stores the operation data; at the same time, it judges whether to adjust the flight attitude simulation motion parameters according to the test requirements. If adjustment is needed, the flight attitude simulation motion parameters are adjusted through the remote control terminal, sent to the cRIO system after adjustment, and step 5) is re-executed;

[0086] Otherwise, step 8) is executed;

[0087] 8) Compare the operation data with the operation data of the standard product;

[0088] If the difference between the operation data and the operation data of the standard product is within the threshold range, the product 12 is qualified; otherwise, the product 12 is unqualified; the flight attitude simulation test of the product 12 is completed.

[0089] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims described.

Claims

1. A flight attitude simulation test tooling, characterized in that: It includes a base (1), and a lifting platform (3) installed in the base (1) through a lifting component (2); A bearing axis turntable (4) is provided in the middle of the lifting platform (3). The base of the bearing axis turntable (4) is connected to the lifting platform (3), and a U-shaped support frame (5) is provided at the top of the rotating platform of the bearing axis turntable (4); A pitching axis motor (6) and a pitching axis encoder (7) are respectively provided on both sides of the support frame (5). The output shaft of the pitching axis motor (6) and the input shaft of the pitching axis encoder (7) both extend into the interior of the support frame (5); An upper part of the support frame (5) is provided with a product mounting rack (8) whose two ends are respectively connected to the output shaft of the pitching axis motor (6) and the input shaft of the pitching axis encoder (7); A protective cylinder (9) is provided on one side of the product mounting rack (8), and a rolling axis turntable (10) is provided on the other side of the product mounting rack (8). The base of the rolling axis turntable (10) is connected to the product mounting rack (8), and a mounting seat (11) is provided on the rotating platform of the rolling axis turntable (10); A fixed carrier (13) of the product (12) passes through the protective cylinder (9) and is connected to the mounting seat (11).

2. The flight attitude simulation test tooling according to claim 1, wherein: The lifting component (2) includes two fixed frames (21). On one side of the two fixed frames (21) close to each other, a motor fixing seat (22), an upper threaded seat (23), and a lower threaded seat (24) are successively provided from top to bottom; A lifting servo motor (25) is provided on the motor fixing seat (22); A stud (26) and two guide columns (27) distributed on both sides of the stud (26) are rotatably installed between the upper threaded seat (23) and the lower threaded seat (24); The output end of the lifting servo motor (25) is connected to the stud (26); A nut seat (28) is threadedly installed on the stud (26), and the nut seat (28) is slidably sleeved on the guide column (27).

3. The flight attitude simulation test tooling according to claim 1, characterized in that: One end of the product (12) is provided with an external thread, and the fixed carrier (13) is provided with an internal thread corresponding to the external thread of the product (12); One end of the product (12) close to the external thread is provided with a product fastener (121), and the inner wall of the product fastener (121) is attached to the outer wall of the fixed carrier (13); A plurality of circumferentially evenly distributed threaded holes (122) are formed in the product fastener (121). Screws are threadedly installed in the threaded holes (122) of the product fastener (121), and the ends of the screws penetrate through the fixed carrier (13) and abut against the product (12).

4. The flight attitude simulation test tooling according to claim 1, wherein: A spirit level seat (14) is fixed to the top of the lifting platform (3) by a plurality of fastening screws (15); A spirit level (16) is provided on the top of the spirit level seat (14), and the spirit level (16) is fixed to the top of the spirit level seat (14) by a plurality of adjusting screws (17).

5. The flight attitude simulation test tooling according to claim 1, wherein: A locking screw (18) is threadedly installed on the outer side wall of the mounting seat (11); The end of the locking screw (18) penetrates through the fixed carrier (13) and abuts against a touch signal receiver provided inside the fixed carrier (13).

6. The flight attitude simulation test tooling according to claim 1, characterized in that: A north finder (19) is provided on the top of the lifting platform (3).

7. A flight attitude simulation test system, characterized in that: It includes a measurement and control unit, a flight attitude simulation control unit, a video monitoring unit, and a remote control terminal connected to the measurement and control unit; The measurement and control unit includes a cRIO system, and a device power supply and control unit, a product power supply, and a signal conditioning module respectively connected to the cRIO system through an I / O interface, an RS422 communication interface, and an analog signal acquisition module; The cRIO system is also connected with a signal isolation and switching control module through an RS232 interface and three RS422 communication interfaces; The video monitoring unit, the flight attitude simulation control unit, the product power supply, the signal conditioning module, and the signal isolation and switching control module are all connected to the device power supply and control unit; The product power supply, the signal conditioning module, and the signal isolation and switching control module are connected to the product (12); The cRIO system is respectively connected to the flight attitude simulation control unit and the video monitoring unit through a USB control interface and a Lan port; the cRIO system communicates with the remote control terminal wirelessly.

8. The flight attitude simulation test system according to claim 7, wherein: The flight attitude simulation control unit includes a controller, a driver module, and a power supply module; The driver module includes a plurality of drivers respectively connected to an azimuth axis turntable (4), a pitch axis motor (6), a roll axis turntable (10), and a lifting servo motor (25), and the plurality of drivers are all connected to the controller; The controller is connected to a north-seeking instrument (19), a touch signal receiver, a pitch axis encoder (7), an azimuth axis encoder of the azimuth axis turntable (4), and a roll axis encoder of the roll axis turntable (10); The controller is connected to the RS422 communication interface of the cRIO system through a serial bus interface; The azimuth axis turntable (4), the pitch axis motor (6), the roll axis turntable (10), the lifting servo motor (25), the north-seeking instrument (19), the controller, and the driver are all connected to the power supply module, and the power supply module is connected to the device power supply and control unit.

9. A flight attitude simulation test method, characterized in that It includes the following steps: S1. Set the flight attitude simulation motion parameters through the remote control terminal and send them to the cRIO system; S2. Send a power supply instruction to the cRIO system through the remote control terminal; The cRIO system executes the power supply instruction and drives the device power supply and control unit to supply power to the video monitoring unit, the flight attitude simulation control unit, the product power supply, the signal conditioning module, and the signal isolation and switching control module; S3. The flight attitude simulation control unit controls the corresponding azimuth axis turntable (4), pitch axis motor (6), and roll axis turntable (10) to act according to the flight attitude simulation motion parameters; S4. The cRIO system collects the operation data of the product (12) through the analog signal acquisition module and the signal conditioning module and sends it to the remote control terminal; S5. The remote control terminal receives the operation data and compares it with the operation data of the standard product; If the difference between the operation data and the operation data of the standard product is within the threshold range, the product (12) is qualified; otherwise, the product (12) is unqualified; Complete the flight attitude simulation test of the product (12).

Images