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Servo load moment calculation method and equipment applied to aircraft and storage medium

A technology of load moment and aircraft, applied in special data processing applications, instruments, aircraft component testing, etc., can solve the problems of upper limit calculation of test load, requirements for structural strength design of servo system, and inability to accurately reflect the characteristics of servo system, etc. achieve the effect of improving accuracy

Inactive Publication Date: 2020-12-25
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional test items only focus on the lower limit of the load torque that the control system can provide to the servo, and do not calculate the upper limit of the test load that may occur during the ground test, nor do they put forward requirements for the structural strength design of the servo system, and the test results cannot be accurately determined. Reflect the characteristic index of the servo system

Method used

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  • Servo load moment calculation method and equipment applied to aircraft and storage medium
  • Servo load moment calculation method and equipment applied to aircraft and storage medium
  • Servo load moment calculation method and equipment applied to aircraft and storage medium

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Embodiment 1

[0022] This embodiment provides a calculation method for servo load torque, which can be applied to a servo system in an aircraft to calculate the servo load torque, thereby improving the control accuracy of the servo system. The servo system is used to control the air rudder to work to adjust the flight attitude of the aircraft. The aircraft can be an aircraft that can fly in the atmosphere, such as an airship, an airplane, etc., or a spacecraft that can fly outside the atmosphere, such as an artificial satellite, a manned spacecraft, a space probe, a space shuttle, etc., or it can be for rockets or missiles.

[0023] In practical applications, the method for calculating the servo load moment can be implemented by a computer program, such as application software, etc.; or, the method can also be implemented as a medium that stores related computer programs, such as a U disk, cloud disk, etc.; or, The method can also be implemented by an entity device integrated or installed ...

Embodiment 2

[0037] This embodiment optimizes the calculation method of the servo load moment on the basis of the above embodiments, and in particular provides a method for determining the static load through static load parameters.

[0038] figure 2 It is a schematic diagram of the rudder surface serial number and rudder deviation symbol of the air rudder provided in the second embodiment of the present application. In this embodiment, a rocket is used as an aircraft as an example for description. figure 2 Shown is the direction of the arrow base, that is, the direction seen from the bottom of the rocket. Such as figure 2 As shown in , the four air rudders are evenly arranged along the circumference, each located in one of the four quadrants. The air rudder trailing edge deflects clockwise for positive rudder deflection.

[0039] The data format of the rudder surface normal force and hinge moment coefficient is as follows:

[0040] Table 1 Table of normal force of rudder surface a...

Embodiment 3

[0057] This embodiment optimizes the calculation method of the servo load moment on the basis of the above embodiments, and in particular provides a method for determining the dynamic load through dynamic load parameters.

[0058] In this embodiment, the dynamic load parameters include: moment of inertia of the air rudder, rotation amplitude and angular velocity of the rotating part. Step 102 in the above embodiment can specifically calculate the dynamic load by the following formula:

[0059] m 动 =J×A×ω 2 ×sin(ωt),

[0060] Among them, M 动 is the dynamic load of the air rudder, J is the moment of inertia of the air rudder, t is the time parameter, ω is the rotational angular velocity of the air rudder, and sin(ωt) is the law of the torque changing with time period. A is the rotation amplitude of the air rudder, which is equal to the control command value of the air rudder multiplied by the amplitude magnification, and the calculation is based on the frequency characterist...

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Abstract

The embodiment of the invention provides a servo load moment calculation method and equipment applied to an aircraft and a storage medium. The method comprises the steps of: acquiring a static load parameter of an air rudder in the aircraft, and determining a static load of the air rudder according to the static load parameter; acquiring a dynamic load parameter of the air rudder, and determininga dynamic load of the air rudder according to the dynamic load parameter; and determining a servo load moment of an aircraft servo system according to the static load and the dynamic load. According to the servo load moment calculation method and equipment applied to the aircraft and the storage medium provided by the embodiment of the invention, the control precision of the servo system can be improved.

Description

technical field [0001] The present application relates to aircraft servo system control technology, in particular to a calculation method, device and storage medium for servo load moment applied to aircraft. Background technique [0002] During the development of the aircraft, it is necessary to conduct multiple tests on the ground. Among them, the purpose of testing the servo system in the aircraft is to obtain the frequency characteristic index under the load and no-load conditions of the servo system. When the servo system is performing a frequency sweep test on the ground, it is necessary to ensure that the structural strength of the air rudder transmission system in the aircraft, including the rudder shaft, rudder bracket, and connecting rod, meets the requirements of the test load moment. The traditional test items only focus on the lower limit of the load torque that the control system can provide to the servo, and do not calculate the upper limit of the test load th...

Claims

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Application Information

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IPC IPC(8): B64F5/60G06F30/15G06F119/14
CPCB64F5/60G06F30/15G06F2119/14
Inventor 马奥家高峰龚旻张东黄建友赵洪张磊佟泽友李亚辉康珅杨东生王宁宋志国严大卫刘博张意国张帆曾伟冯铁山周国哲张志勇韩敬永谭杰孙晓峰陈政罗波于贺任新宇王冀宁年永尚张聪杨瑜
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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