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Re-entry attitude control method of reusable launch vehicle

An attitude control and carrier technology, applied in attitude control and other directions, can solve the problem of low efficiency of RCS instruction allocation

Active Publication Date: 2015-05-20
NORTHWESTERN POLYTECHNICAL UNIV
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  • Description
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AI Technical Summary

Problems solved by technology

[0003] In order to overcome the inefficiency of the existing method for RCS instruction distribution, the present invention provides a re-entry attitude control method for reusable vehicles

Method used

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  • Re-entry attitude control method of reusable launch vehicle
  • Re-entry attitude control method of reusable launch vehicle
  • Re-entry attitude control method of reusable launch vehicle

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Embodiment Construction

[0054] refer to Figure 2-4 . The specific steps of the re-entry attitude control method of the reusable vehicle of the present invention are as follows:

[0055] 1. Design of reentry attitude controller for RLV.

[0056] In order to simplify the design of the controller, ignoring the influence of small quantities such as the earth's autobiography and Coriolis force changes on the attitude change of the aircraft, the nonlinear attitude motion model of the RLV reentry process is:

[0057] θ · = [ L cos γ v -Zsin γ v - mg cos θ ] / mV

[0058] σ · = - [ L sin γ v + Z cos γ ...

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Abstract

The invention discloses a re-entry attitude control method of a reusable launch vehicle (RLV), and aims at solving the technical problem of an existing method that the distribution efficiency of an RCS (Reaction Control System) instruction is low. According to the technical scheme, the re-entry attitude control method comprises the following steps: firstly, designing all combinations in all control directions of all thrusters in all control directions of an RCS; adopting an integer linear planning method to realize real-time instruction distribution in a determined required moment direction combination; solving the integer planning method by using a genetic algorithm. Control instruction distribution of the RCS is converted into a dimension-lowering integer linear planning method; compared with a background technology, the requirements of the RLV re-entry attitude control are combined; the amplitudes of the thrusters and the fuel combustion of the RCS are considered, and an offline design optimal table is not needed under the condition that the thrusters have the fault, so that the complexity of the thrusters is reduced; the real-time efficiency of the RCS instruction distribution is improved through the dimension-lowering treatment; the RCS fault reconstruction of minimum RCS energy consumption and instruction moment tracking errors is realized.

Description

technical field [0001] The invention relates to a method for controlling the reentry attitude of a carrier, in particular to a method for controlling the reentry attitude of a reusable carrier. Background technique [0002] refer to figure 1 . The literature "Spacecraft Real-time Command Allocation Optimal Look-Up Method Considering Thruster Thrust Upper Bound and Fault Conditions, Acta Astronautica Sinica, 2010, vol31(6), P1540-1546" discloses an optimal real-time command look-up table for spacecraft Law. This method considers the existence of the upper bound of the thruster amplitude and the failure of the thruster when the satellite is in orbit, and supplements the original optimal look-up table method based on the simplex algorithm in linear programming, and gives the thruster in the two cases Real-time optimal look-up table method for instruction allocation. The algorithm can enhance the control ability of the thruster configuration while maintaining the optimality ...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 周军常晶呼卫军卢青
Owner NORTHWESTERN POLYTECHNICAL UNIV
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