Anti-backlash structure and method for connection of linear steering engine and air rudder

Abstract

The invention discloses an anti-backlash structure and method for connection of a linear steering engine and an air rudder. The anti-backlash structure comprises the linear steering engine, a steering engine connecting pin, a rocker arm, a rocker arm connecting pin, a bearing and the air rudder. Output torque of the linear steering engine is transmitted to the air rudder through the rocker arm; the rocker arm connecting pin penetrates through the rocker arm and the rudder shaft, so that the rocker arm and the rudder shaft are integrated; the rocker arm connecting pin is of a taper pin structure. The problem of the design gap between the air rudder and the rocker arm is solved, the backlash angle of the air rudder is reduced, and the problem of nonlinear oscillation caused by the gap of the air rudder in the flight process is solved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of rockets, and particularly relates to a gap-eliminating structure and method for connecting a linear steering engine with an air rudder. BACKGROUND

[0002] During the whole flight of a remote guidance rocket, the flight trajectory and attitude of the rocket need to be controlled by an air rudder, and the rotation of the air rudder needs to be completed by a steering engine. A conventional steering engine generally selects a rotary motion steering engine or a linear motion steering engine. The rated power of the rotary steering engine is relatively small. When the linear motion steering engine is rotated, the transmission path between the steering engine and the air rudder is relatively long, and the gap between the early straight pin structure and the air rudder is relatively large. During the flight process under the unstable aerodynamic effect, the gap causes the nonlinear oscillation of the air rudder and the whole rocket. SUMMARY

[0003] In order to overcome the defects of the prior art, the present application provides a gap-eliminating structure and method for connecting a linear steering engine with an air rudder, which comprises a linear steering engine, a steering engine connecting pin, a rocker arm, a rocker arm connecting pin, a bearing and an air rudder. The output torque of the linear steering engine is transmitted to the air rudder through the rocker arm. The rocker arm is sleeved on the rudder shaft of the air rudder, and the rocker arm connecting pin penetrates the rocker arm and the rudder shaft to make them into one body. The rocker arm connecting pin is a taper pin structure. The present application solves the design gap problem of the air rudder and the rocker arm, reduces the idle angle of the air rudder, and solves the problem of nonlinear oscillation caused by the gap of the air rudder during the flight process.

[0004] The technical scheme adopted by the present application to solve the technical problems is as follows:

[0005] A gap-eliminating structure for connecting a linear steering engine with an air rudder, comprising a linear steering engine, a steering engine connecting pin, a rocker arm, a rocker arm connecting pin, a bearing and an air rudder.

[0006] The output torque of the linear steering engine is transmitted to the air rudder through the rocker arm.

[0007] The rocker arm is sleeved on the rudder shaft of the air rudder, and the rocker arm connecting pin penetrates the rocker arm and the rudder shaft to make them into one body.

[0008] The rocker arm connecting pin is a taper pin structure.

[0009] Preferably, the taper of the rocker arm connecting pin is 1:50.

[0010] Preferably, the large end of the rocker arm connecting pin is designed with an internal hexagonal groove for disassembling and assembling the rocker arm connecting pin, and the small end is designed with a threaded structure for fastening the rocker arm connecting pin.

[0011] Preferably, the pin hole matched with the rocker arm connecting pin is a taper structure with a taper of 1:50, which is consistent with the taper of the rocker arm connecting pin.

[0012] Preferably, the matching pin hole on the air vane and the rocker arm needs to be matched by integral machining.

[0013] A clearance elimination method for connecting a linear actuator with an air vane, specifically as follows:

[0014] The air vane is installed on the cabin body through a set of bearings, the installation process is to fit the rocker arm on the air vane shaft, the rocker arm connecting pin is passed through the rocker arm and the vane shaft taper hole, and then the rocker arm connecting pin is tightened using a nut plus a flat washer, and the tightening torque is 25 N.m.

[0015] A computer program, which enables a computer to execute the above-mentioned clearance elimination method.

[0016] An electronic device, comprising a processor and a memory; the memory is used to store a computer program, and the processor is used to execute the computer program stored in the memory, so that the electronic device executes the above-mentioned clearance elimination method.

[0017] A computer readable storage medium, which stores a computer program, the computer program is executed by a processor to realize the above-mentioned clearance elimination method.

[0018] A chip, comprising a processor, which is used to call and run a computer program from a memory, so that the device installed with the chip executes the above-mentioned clearance elimination method.

[0019] A computer program product, comprising a computer storage medium, the computer storage medium stores a computer program, the computer program comprises instructions executable by at least one processor, and the instructions are executed by the at least one processor to realize the above-mentioned clearance elimination method.

[0020] The beneficial effects of the present application are as follows:

[0021] The present application solves the design gap problem between the air vane and the rocker arm, reduces the dead angle of the air vane, and solves the problem of nonlinear oscillation caused by the gap of the air vane during flight. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a structural schematic diagram of the clearance elimination structure of the present application;

[0023] Figure 2 is an effect schematic diagram of the clearance elimination structure of the present application.

[0024] BRIEF DESCRIPTION OF DRAWINGS: 1: actuator mounting seat 2: mounting seat shaft 3: linear actuator 4: actuator connecting pin 5: locking screw 6: rocker arm connecting pin 7: air vane 8: rocker arm 9: nut. DETAILED DESCRIPTION

[0025] The present application will be further described below in combination with the drawings and examples.

[0026] The application discloses a clearance-eliminating structure and method for connecting a linear servo and an air rudder.

[0027] The clearance-eliminating structure for connecting the linear servo and the air rudder mainly comprises a linear servo, a servo connecting pin, a rocker arm, a rocker arm connecting pin, a bearing, an air rudder, a gasket, a nut and the like.

[0028] The rocker arm connecting pin is in a taper pin structure, and the taper is 1:50; the large end of the rocker arm connecting pin is designed as an internal hexagonal groove for disassembling and assembling the rocker arm connecting pin; and the small end is designed as a threaded structure for fastening the rocker arm connecting pin.

[0029] During work, the air rudder is installed on a cabin body through a group of bearings; during the installation process, the rocker arm is sleeved on a rudder shaft of the air rudder, the rocker arm connecting pin is passed through the taper holes of the rocker arm and the rudder shaft, and then the rocker arm connecting pin is pulled tight by using a nut and a flat gasket, and the fastening torque is 25 N.m.

[0030] Embodiment

[0031] 1. The rocker arm connecting pin is in a taper pin structure, and the taper is 1:50; the large end of the rocker arm connecting pin is designed as an internal hexagonal groove for disassembling and assembling the rocker arm connecting pin; and the small end is designed as a threaded structure for fastening the rocker arm connecting pin.

[0032] 2. The pin hole on the rocker arm matched with the rocker arm connecting pin is in a taper structure, and the taper is consistent with that of the rocker arm connecting pin, i.e. 1:50.

[0033] 3. The matched pin hole on the rocker arm and the air rudder needs to be integrally machined.

[0034] 4. During work, the air rudder is installed on a cabin body through a group of bearings; during the installation process, the rocker arm is sleeved on a rudder shaft of the air rudder, the rocker arm connecting pin is passed through the taper holes of the rocker arm and the rudder shaft, and then the rocker arm connecting pin is pulled tight by using a nut and a flat gasket, and the fastening torque is 25 N.m.

Claims

1. A backlash-eliminating structure for connecting a linear servo and an air rudder, characterized in that: Including linear servo, servo connecting pin, rocker arm, rocker arm connecting pin, bearing, air rudder; The linear servo output torque is transmitted to the air rudder through the rocker arm; The rocker arm is sleeved on the rudder shaft of the air rudder, and the rocker arm connecting pin passes through the rocker arm and the rudder shaft to make them one body; The rocker arm connecting pin is a tapered pin structure.

2. The anti-backlash structure for connecting a linear servo and an air rudder according to claim 1, characterized in that: The taper of the rocker arm connecting pin is 1:

50.

3. The anti-backlash structure for connecting a linear servo and an air rudder according to claim 1, characterized in that: The large end of the rocker arm connecting pin is designed with an inner hexagonal groove for disassembling and assembling the rocker arm connecting pin; the small end is designed with a threaded structure for fastening the rocker arm connecting pin.

4. The anti-backlash structure for connecting a linear servo and an air rudder according to claim 1, characterized in that: The pin hole that cooperates with the rocker arm and the rocker arm connecting pin is a tapered structure, and the taper is consistent with that of the rocker arm connecting pin, which is 1:

50.

5. The anti-backlash structure for connecting a linear servo and an air rudder according to claim 1, characterized in that: The matching pin holes on the rocker arm and the air rudder need to be processed as a whole.

6. A backlash elimination method using the backlash elimination structure according to claim 1, characterized in that: The details are as follows: Install the air rudder on the cabin through a set of bearings. During the installation process, put the rocker arm on the rudder shaft of the air rudder, pass the rocker arm connecting pin through the rocker arm and the rudder shaft tapered hole, and then use a nut and a flat washer to tighten the rocker arm connecting pin with a tightening torque of 25N.m.

7. A computer program, characterized in that The computer program enables a computer to execute the method according to claim 6.

8. An electronic device, characterized in that: include: processor and memory; The memory is used to store a computer program, and the processor is used to execute the computer program stored in the memory, so that the electronic device executes the method as claimed in claim 6.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the method according to claim 6 is implemented.

10. A chip, characterized in that: The device comprises: a processor configured to call and run a computer program from a memory, so that a device equipped with the chip executes the method as claimed in claim 6.

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