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Carrier rocket elliptical orbit online planning method

An elliptical orbit, launch vehicle technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as difficult online solutions, missing the best rescue time for rocket missions, and failed rescue missions.

Active Publication Date: 2021-01-26
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The trajectory planning methods developed in recent years, such as pseudospectral method, indirect method, etc., have shortcomings in solution speed and initial guess dependence, which make it difficult to solve online. In this way, when the rocket encounters an abnormal state during flight, It can only be solved offline, and then upload the trajectory parameters to the arrow. This method requires a lot of manpower and material support on the ground, and the rocket's flight area has measurement and control blind spots and communication restrictions, so it may miss the rocket mission. The optimal rescue time of the rocket will cause more energy loss of the rocket, and even lead to the failure of the rescue mission

Method used

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  • Carrier rocket elliptical orbit online planning method
  • Carrier rocket elliptical orbit online planning method
  • Carrier rocket elliptical orbit online planning method

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Embodiment

[0128] Taking a certain type of rocket as the object, in such as figure 1 The L1 point in the ellipse needs to be planned online, and the planning goal is to maximize the apogee height of the ellipse, such as figure 1 r in p As shown, finally make the rocket in such as figure 1 The point L2 in enters the planned elliptical orbit.

[0129] Simulation results: Using the online planning method of the elliptical orbit of the present invention, the simulation results are obtained, so that the rocket enters an elliptical orbit of , wherein the perigee height is 200km, and the apogee height is 32800km. The simulation results are shown in the figure figure 2 shown, where:

[0130] 1) The dotted line represents the parking orbit at the beginning of trajectory planning;

[0131] 2) The curve indicated by "○" represents the flight trajectory from the planned current state to the moment of entering the elliptical orbit;

[0132] 3) The solid line represents the planned final ellipt...

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Abstract

The invention relates to a carrier rocket elliptical orbit online planning method, in particular to a rocket online trajectory planning method, and belongs to the field of aerospace guidance control.According to the method, the nonlinear constraint, namely the elliptical orbit injection constraint, can be converted into the convex constraint so that the elliptical orbit planning problem can be constructed into the convex planning problem, and online solving and implementation are facilitated. By updating the orbit injection point conjecture and establishing a new elliptical orbit convex programming model through the sequence, the orbit injection precision can be ensured, and the terminal constraint of elliptical orbit planning is accurately met.

Description

technical field [0001] The invention relates to an online planning method for an elliptical orbit of a carrier rocket, which is an online trajectory planning method for a rocket and belongs to the field of aerospace guidance and control. Background technique [0002] For a multi-stage launch vehicle, if the previous stage rocket fails to reach the predetermined state when it is shut down, causing the follow-up rocket to fail to enter the predetermined orbit, or when the rocket has a non-fatal failure, it is necessary for the rocket to use the remaining fuel as much as possible to satisfy the predetermined orbit inclination, lift Under the conditions of intersection point accuracy, argument of perigee and height of perigee, the height of apogee entering the orbit is the largest, so that the rocket can reach the highest apogee, which is convenient for further rescue of subsequent missions. [0003] The trajectory planning methods developed in recent years, such as pseudospectr...

Claims

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Application Information

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IPC IPC(8): G06F30/20G06Q10/04G06F119/14
CPCG06F30/20G06Q10/04G06F2119/14Y02T90/00
Inventor 程晓明王晋麟吕新广吕建强王锋李杰
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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