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An engine characteristic processing method for vertical take-off and landing rocket on-line trajectory planning

A trajectory planning, vertical take-off and landing technology, applied in special data processing applications, electrical digital data processing, instruments, etc., can solve the problem that the engine cannot respond in time, and achieve the effect of ensuring stability

Active Publication Date: 2019-05-03
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST +1
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  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a method for processing the engine characteristics of the vertical take-off and landing rocket online trajectory planning. The engine characteristics are introduced into the online trajectory planning dynamic equation constraint description, and the introduced quantity includes the engine steady-state characteristics and engine adjustment characteristics to solve the problem that the engine cannot respond in time to the control instructions given by the main controller during the real flight, and finally make the rocket complete the flight mission according to the established planned trajectory

Method used

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  • An engine characteristic processing method for vertical take-off and landing rocket on-line trajectory planning
  • An engine characteristic processing method for vertical take-off and landing rocket on-line trajectory planning
  • An engine characteristic processing method for vertical take-off and landing rocket on-line trajectory planning

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Embodiment Construction

[0039] The technical solution of the present invention is to add the engine characteristic part to the existing on-line trajectory planning dynamic equation constraint description, and change the engine characteristic description into a dynamic differential equation form and introduce it into the online trajectory planning dynamic equation differential equation. Such as figure 1 shown.

[0040] The specific implementation steps are as follows:

[0041] 1) Constructing dynamic differential equations for online trajectory planning of rockets

[0042] According to the origin of the launch inertial coordinate system at the launch point o, the ox axis is in the horizontal plane of the launch point, pointing to the launch aiming direction; the y axis is perpendicular to the horizontal plane of the launch point, pointing upward, and the oz axis is perpendicular to the xoy plane, forming a right-handed coordinate system.

[0043] Let the displacement of the rocket in the vertical di...

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Abstract

The invention relates to an engine characteristic processing method for vertical take-off and landing rocket on-line trajectory planning. The rocket engine characteristics measured offline are added to an online trajectory planning dynamics differential equation, the technical problem that an engine cannot respond to a control instruction given by a main control computer in time in the real flightprocess is solved, and finally the rocket completes a flight task according to a set planning trajectory. By directly limiting the instruction value of the engine, the range of the acceleration of the rocket in the vertical direction is restrained, and the stability of the rocket in the flying process is guaranteed. When flight is close to the end, the instruction value of the engine can be directly limited to be equal to g / k, it is guaranteed that the acceleration value generated by the real thrust of the rocket is equal to g, and soft landing is achieved.

Description

technical field [0001] The invention relates to an engine characteristic processing method for online trajectory planning of vertical take-off and landing rockets, and relates to the technical field of online trajectory planning of rockets. Background technique [0002] The online trajectory planning technology is a technology that plans a vehicle trajectory in real time during the flight of the vehicle to satisfy various equations and inequality constraints. In the flight control of vertical take-off and landing reusable rockets, the introduction of online trajectory planning technology can solve the problem of uncertainty in the starting position of the rocket. The dynamic equation constraint description in the existing trajectory planning problem description generally only considers the relationship between the position, velocity, acceleration and control quantity during flight, and does not introduce the engine characteristic description into it, resulting in poor guidan...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 骆无意吕新广施健锋王聪宋征宇巩庆海郭少波柳嘉润
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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