Dynamic loading device for guided missile steering engine

Abstract

The utility model relates to a missile steering engine dynamic loading device, which comprises a working rack, a fixing tool, a torque support and an encoder support, the fixing tool, the torque support and the encoder support are arranged on the working rack and used for fixing and supporting the missile steering engine dynamic loading device, and the fixing tool is used for fixedly arranging a missile steering engine to be tested; the clamping tool, the accelerometer, the torque sensor, the magnetic powder brake and the magnetoelectric encoder are sequentially arranged, an opening is formed in the middle of the clamping tool, the clamping tool is used for clamping and fixing an air rudder wing of a missile steering engine to be tested, the accelerometer is arranged on the clamping tool, a bearing is arranged in the torque support, the clamping tool is connected with the torque sensor through the bearing, and the magnetoelectric encoder is arranged on the clamping tool. The torque sensor is connected with a magnetic powder brake, and the magnetic powder brake is connected with a magnetoelectric encoder fixedly arranged on an encoder support. According to the missile steering engine dynamic loading device, missile steering engine detection dynamic loading and multi-channel multi-feedback can be realized.

Description

Technical Field

[0001] This utility model relates to the field of missile servo testing technology, and more specifically, to a multi-channel, multi-feedback dynamic loading device for missile servos. Background Technology

[0002] The missile servo is the actuator of the guided munition flight control system, and its proper functioning directly affects the missile's flight attitude and accuracy. During flight, the missile servo's air control wings deflect according to guidance commands, creating a pressure difference in the airflow across the control surfaces, thus generating aerodynamic forces. Therefore, to simulate the forces experienced by the missile servo during actual flight, torque loading tests are required on the missile servo's air control wings during ground testing.

[0003] Currently, most missile servo motor loading devices are static loading devices, while the forces acting on the servo motor during flight are dynamic and can easily cause measurement errors, thus affecting product performance. In addition, most missile servo motor loading devices use single-channel, single-feedback, which cannot achieve effective data comparison. Summary of the Invention

[0004] The technical problem this invention aims to solve is that existing servo motor loading devices can only perform static loading and cannot perform dynamic loading, and they also cannot perform simultaneous multi-channel measurements, and traditional single feedback is prone to errors.

[0005] To solve the above-mentioned technical problems, this utility model provides a dynamic loading device for a missile servo motor, comprising: a workbench and a fixed fixture, a torque support, and an encoder support mounted on the workbench, for fixing and supporting the dynamic loading device for the missile servo motor. The fixed fixture is used to fix the missile servo motor under test. A clamping fixture, an accelerometer, a torque sensor, a magnetic powder brake, and a magnetoelectric encoder are sequentially arranged. The clamping fixture has an opening in the middle for clamping and fixing the air fins of the missile servo motor under test. The accelerometer is mounted on the clamping fixture. A bearing is installed in the torque support. The clamping fixture is connected to the torque sensor via the bearing. The torque sensor is connected to the magnetic powder brake. The magnetic powder brake is connected to the magnetoelectric encoder fixedly mounted on the encoder support.

[0006] According to an embodiment of the present invention, the missile servo dynamic loading device includes multiple sets of clamping fixtures, accelerometers, torque sensors, magnetic powder brakes, and magneto-electric encoders arranged sequentially from the same fixed fixture to multiple torque supports.

[0007] According to an embodiment of this utility model, the missile servo dynamic loading device consists of four sets of clamping fixtures, accelerometers, torque sensors, magnetic powder brakes, and magneto-electric encoders arranged sequentially from the same fixed fixture to four torque supports.

[0008] According to an embodiment of this utility model, the missile servo dynamic loading device further includes: a coupling, through which the torque sensor is connected to the magnetic powder brake.

[0009] According to an embodiment of this utility model, the missile servo dynamic loading device further includes: an extension rod, and a torque sensor connected to a magnetic powder brake via a coupling and the extension rod.

[0010] According to an embodiment of this utility model, the accelerometer adopts a MEMS inertial measurement unit with the specification model: SNC200G-C0.

[0011] According to an embodiment of this utility model, the torque sensor specification is: HCNJ-104.

[0012] According to an embodiment of this utility model, the coupling specification is: GL-12×15.9.

[0013] According to an embodiment of this utility model, the magnetic powder brake has the following specifications: WSB-1N, with a rated torque of 1N / M.

[0014] According to an embodiment of this utility model, the specification model of the magneto-electric encoder is: BRT38-P0TY-1000L-RT.

[0015] Compared with the prior art, the technical solution provided by the embodiments of this utility model can achieve at least the following beneficial effects:

[0016] This utility model provides a multi-channel dual-feedback dynamic loading device for missile servos. This device can not only dynamically load missile servos, but also provide feedback on the torque value of the loaded load, as well as measure performance parameters such as servo deflection angle and deflection angular velocity.

[0017] The missile servo dynamic loading device of this invention can realize dynamic torque loading of the missile servo through a magnetic powder brake, receive torque data in real time through a torque sensor, and compare the performance data of the missile servo by using feedback such as accelerometers and magneto-electric encoders, so as to test the performance of the missile servo more accurately and completely. Attached Figure Description

[0018] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings of the embodiments will be briefly introduced below. Obviously, the drawings described below only involve some embodiments of this utility model, and are not intended to limit this utility model.

[0019] Figure 1 This is a schematic diagram showing a missile servo dynamic loading device according to an embodiment of the present invention;

[0020] Figure 2This is a top view showing a missile servo dynamic loading device according to an embodiment of the present invention;

[0021] Figure 3 This is a side view showing a missile servo dynamic loading device according to an embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of a clamping fixture according to an embodiment of the present utility model;

[0023] Figure 5 This is a schematic diagram showing an air rudder according to an embodiment of the present invention. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the described embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0025] Unless otherwise defined, the technical or scientific terms used herein shall have the ordinary meaning as understood by one of ordinary skill in the art to which this invention pertains. The terms “first,” “second,” and similar terms used in this patent application specification and claims do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Similarly, the terms “an” or “a” and similar terms do not indicate a limitation of quantity, but rather indicate the presence of at least one.

[0026] Figure 1 This is a schematic diagram showing a missile servo dynamic loading device according to an embodiment of the present invention; Figure 2 This is a top view showing a missile servo dynamic loading device according to an embodiment of the present invention; Figure 3 This is a side view showing a missile servo dynamic loading device according to an embodiment of the present invention; Figure 4 This is a schematic diagram of a clamping fixture according to an embodiment of the present utility model; Figure 5 This is a schematic diagram showing an air rudder according to an embodiment of the present invention.

[0027] like Figures 1 to 5As shown, the dynamic loading device for the missile servo 2 includes: a workbench 1 and a fixed fixture 11, a torque support 12, and an encoder support 13 mounted on the workbench 1, for fixing and supporting the dynamic loading device for the missile servo 2. The fixed fixture 11 is used to fix the missile servo 2 under test. The device also includes a clamping fixture 3, an accelerometer 4, a torque sensor 5, a magnetic powder brake 8, and a magneto-electric encoder 9, which are arranged in sequence.

[0028] The clamping fixture 3 has an opening in the middle for clamping and fixing the air rudder 21 of the missile servo motor 2 under test. The accelerometer 4 is installed on the clamping fixture 3. The torque support 12 is equipped with a bearing. The clamping fixture 3 is connected to the torque sensor 5 via the bearing. The torque sensor 5 is connected to the magnetic powder brake 8. The magnetic powder brake 8 is connected to the magnetoelectric encoder 9 fixed on the encoder support 13.

[0029] The missile servo motor 2 dynamic loading device of this utility model can realize dynamic torque loading of the missile servo motor 2 through the magnetic powder brake 8, receive torque data in real time through the torque sensor 5, and compare the performance data of the missile servo motor 2 by using feedback such as the accelerometer 4 and the magneto-electric encoder 9, so as to test the performance of the missile servo motor 2 more accurately and completely.

[0030] According to one or more embodiments of the present invention, the missile servo motor 2 dynamic loading device includes multiple sets of clamping fixtures 3, accelerometers 4, torque sensors 5, magnetic powder brakes 8, and magneto-electric encoders 9, which are arranged sequentially from the same fixed fixture 11 to multiple torque supports 12.

[0031] According to one or more embodiments of the present invention, the missile servo motor 2 dynamic loading device consists of four sets of clamping fixtures 3, accelerometers 4, torque sensors 5, magnetic powder brakes 8, and magneto-electric encoders 9 arranged sequentially from the same fixed fixture 11 to four torque supports 12.

[0032] The missile servo motor 2 dynamic loading device of this utility model provides a multi-channel dual feedback dynamic loading device. This device can not only dynamically load the missile servo motor 2, but also provide feedback on the torque value of the loaded load, as well as measure the performance parameters such as the deflection angle and deflection angular velocity of the servo wing.

[0033] According to one or more embodiments of the present invention, the dynamic loading device for the missile servo motor 2 further includes: a coupling 6, wherein the torque sensor 5 is connected to the magnetic powder brake 8 via the coupling 6.

[0034] According to one or more embodiments of the present invention, the missile servo motor 2 dynamic loading device further includes: an extension rod 7, and a torque sensor 5 connected to a magnetic powder brake 8 via a coupling 6 and the extension rod 7.

[0035] According to one or more embodiments of the present invention, the accelerometer 4 adopts a MEMS inertial measurement unit with the specification model: SNC200G-C0.

[0036] According to one or more embodiments of this utility model, the torque sensor 5 has the following specifications: HCNJ-104.

[0037] According to one or more embodiments of this utility model, the coupling 6 has the following specifications: GL-12×15.9.

[0038] According to one or more embodiments of this utility model, the magnetic powder brake 8 has the following specifications: WSB-1N, rated torque 1N / M.

[0039] According to one or more embodiments of the present invention, the specification model of the magneto-electric encoder 9 is: BRT38-P0TY-1000L-RT.

[0040] In use, the missile servo motor 2 receives control commands to control the rotation of the brushless DC motor, which in turn drives the ball screw to rotate, causing the air control fin 21 to deflect. The air control fin 21 is attached to the clamping fixture 3 and connected by bolts. The deflection of the air control fin 21 causes the clamping fixture 3 to deflect. The accelerometer 4 is connected to the clamping fixture 3 by bolts. When the clamping fixture 3 deflects, the accelerometer 4 converts the deflection signal into an electrical signal and transmits it to the PC. The clamping fixture 3 is coaxially connected to the torque sensor 5. The torque sensor 5 is connected to the magnetic powder brake 8 through a coupling 6. To meet the dynamic torque loading requirements, [further details are needed]. The torque data received by the air control fin 21 during the flight of the guided missile is obtained through aerodynamic simulation. By adjusting the torque output of the magnetic powder brake 8, the torque sensor 5 feeds back the received torque to the PC and compares it with the torque information input to the magnetic powder brake 8. The magnetic powder brake 8 is connected to the magneto-electric encoder 9, which converts the received angle deflection signal into an electrical signal and feeds it back to the PC. The signal is then compared with the feedback signal from the accelerometer 4 and the potentiometer feedback signal from the missile servo 2 itself, thereby realizing the dynamic torque loading of the missile servo 2 with multi-channel dual feedback.

[0041] The above description is merely an exemplary embodiment of the present utility model and is not intended to limit the scope of protection of the present utility model. The scope of protection of the present utility model is determined by the appended claims.

Claims

1. A missile rudder dynamic loading device, characterized by, include: The workbench and the fixed fixtures, torque supports, and encoder supports mounted on the workbench are used to fix and support the missile servo dynamic loading device. The fixed fixtures are used to fix the missile servo under test. The clamping fixture, accelerometer, torque sensor, magnetic powder brake, and magneto-electric encoder are arranged sequentially. The clamping fixture has an opening in the middle for clamping and fixing the air rudder of the missile servo motor under test. An accelerometer is installed on the clamping fixture. A bearing is installed in the torque support. The clamping fixture is connected to the torque sensor via the bearing. The torque sensor is connected to the magnetic powder brake. The magnetic powder brake is connected to the magnetoelectric encoder fixed on the encoder support.

2. The dynamic loading device for missile rudder as claimed in claim 1, wherein, It includes multiple sets of clamping fixtures, accelerometers, torque sensors, magnetic powder brakes, and magneto-electric encoders, which are arranged sequentially from the same fixed fixture to multiple torque supports.

3. The dynamic loading device for missile rudder as claimed in claim 2, wherein, Four sets of clamping fixtures, accelerometers, torque sensors, magnetic powder brakes, and magneto-electric encoders are sequentially arranged from the same fixed fixture to four torque supports.

4. The dynamic loading device for missile rudder as claimed in claim 1, wherein Also includes: The torque sensor is connected to the magnetic powder brake via the coupling.

5. The dynamic loading device for missile rudder as claimed in claim 4, wherein, Also includes: The extension rod connects the torque sensor to the magnetic powder brake via a coupling and the extension rod.

6. The missile servo dynamic loading device as described in claim 1, characterized in that, The accelerometer uses a MEMS inertial measurement unit with the model number SNC200G-C0.

7. The dynamic loading device for missile rudder as claimed in claim 1, wherein The torque sensor is model number HCNJ-104.

8. The dynamic loading device for missile rudder as claimed in claim 4, wherein, The coupling has the following specifications: GL-12×15.

9.

9. The dynamic loading device for missile rudder as claimed in claim 1, wherein, The magnetic powder brake has the following specifications: WSB-1N, rated torque 1N / M.

10. The dynamic loading device for missile rudder as claimed in claim 1, wherein, The specifications and model of the magneto-electric encoder are: BRT38-P0TY-1000L-RT.

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