Attitude control parameter self-adaptive adjustment method and device, electronic equipment and storage medium

An adaptive adjustment and parameter technology, applied in the aerospace field, can solve problems such as the mismatch between attitude control parameters and flight status, and achieve the effects of increasing rapid response capability, improving adaptability, and improving matching degree

Active Publication Date: 2020-07-10
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In view of this, an embodiment of the present invention provides an attitude control parameter adaptive adjustment method, device, electronic equipment and storage medium to solve the problem of mismatch between attitude control parameters and flight status

Method used

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  • Attitude control parameter self-adaptive adjustment method and device, electronic equipment and storage medium
  • Attitude control parameter self-adaptive adjustment method and device, electronic equipment and storage medium
  • Attitude control parameter self-adaptive adjustment method and device, electronic equipment and storage medium

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Embodiment 1

[0035] Embodiment 1 of the present invention provides an attitude control parameter adaptive adjustment method. figure 1 It is a schematic flow chart of the attitude control parameter adaptive adjustment method in Embodiment 1 of the present invention, as figure 1 As shown, the attitude control parameter adaptive adjustment method in Embodiment 1 of the present invention includes the following steps:

[0036] S101: Obtain the engine apparent velocity increment and flight dynamic pressure of the rocket respectively.

[0037] Specifically, the engine apparent speed increment and flight dynamic pressure of the rocket can be estimated in real time based on the measurement data on the rocket. After the rocket is launched, the navigation module bound in the arrow control computer calculates and outputs the actual engine apparent speed increment of the rocket in real time and flight pressure

[0038] S102: Calculate the rudder surface control efficiency of the rocket by using t...

Embodiment 2

[0066] Embodiment 2 of the present invention provides an attitude control parameter adaptive adjustment device. image 3 It is a schematic structural diagram of the attitude control parameter adaptive adjustment device in Embodiment 3 of the present invention, as image 3 As shown, the attitude control parameter adaptive adjustment device according to Embodiment 2 of the present invention includes an acquisition module 30 , a first calculation module 32 and a second calculation module 34 .

[0067] Specifically, the acquiring module 30 is configured to respectively acquire the engine apparent speed increment and the flight dynamic pressure of the rocket.

[0068] The first calculating module 32 is used for calculating the rudder surface control efficiency of the rocket by using the engine apparent speed increment and the flight dynamic pressure.

[0069] The second calculation module 34 is used to calculate the attitude control parameters of the rocket by using the rudder sur...

Embodiment 3

[0072] An embodiment of the present invention also provides an electronic device, which may include a processor and a memory, where the processor and the memory may be connected through a bus or in other ways.

[0073] The processor may be a central processing unit (Central Processing Unit, CPU). The processor can also be other general-purpose processors, digital signal processors (Digital Signal Processor, DSP), application-specific integrated circuits (Application Specific Integrated Circuit, ASIC), field-programmable gate array (Field-Programmable Gate Array, FPGA) or other Chips such as programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or combinations of the above-mentioned types of chips.

[0074] As a non-transitory computer-readable storage medium, the memory can be used to store non-transitory software programs, non-transitory computer-executable programs and modules, such as the program instructions corresponding to t...

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Abstract

The invention discloses an attitude control parameter self-adaptive adjustment method and device, electronic equipment and a storage medium. The attitude control parameter self-adaptive adjustment method comprises the steps that the engine apparent velocity increment and the flying pressure of a rocket are obtained; the control surface control efficiency of the rocket is calculated by using the engine apparent velocity increment and the flying pressure; and attitude control parameters of the rocket is calculated by using the control surface control efficiency of the rocket. By the adoption ofthe technical scheme, the attitude control parameters can be directly associated with the flight state estimated on the rocket, the matching degree of the attitude control parameters and the real flight state under different launching conditions is improved, and the problem that the rocket is out of control is avoided.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to an attitude control parameter self-adaptive adjustment method, device, electronic equipment and storage medium. Background technique [0002] For the attitude control design of traditional launch vehicles, after selecting the three-channel attitude control parameters of several standard trajectory feature points, usually in the six-degree-of-freedom mathematical simulation of the rocket body movement, half-physical simulation or actual flight test, relative to the take-off time The flight time is the node, and the real-time attitude control parameters are calculated by linear interpolation, and the attitude control loop is introduced to drive the actuator of the control system. [0003] In recent years, the rapid development of the commercial aerospace field has put forward more requirements for rapid response launch vehicles. For this reason, commercial launch vehicles need t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/00F42B15/01F42B10/64G06F30/15
CPCF42B10/64F42B15/00F42B15/01
Inventor 彭小波张勇黄佩
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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