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Reentry guidance method for hypersonic aircraft under terminal time constraints

A time-constrained, hypersonic technology, applied in the direction of vehicle position/route/height control, instruments, control/regulation systems, etc., can solve problems that cannot meet terminal time constraints, achieve good engineering application prospects, improve accuracy, and improve The effect of control precision

Active Publication Date: 2022-02-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] The purpose of the present invention is to provide a hypersonic vehicle reentry guidance method under the terminal time constraint, aiming at the problem that the existing reentry guidance technology cannot meet the terminal time constraints of the coordinated attack mission, while ensuring the altitude, speed, and voyage to be flown. , heading angle and other conventional terminal constraints, further satisfying the terminal time constraints

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  • Reentry guidance method for hypersonic aircraft under terminal time constraints
  • Reentry guidance method for hypersonic aircraft under terminal time constraints
  • Reentry guidance method for hypersonic aircraft under terminal time constraints

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Embodiment Construction

[0055] In order to better illustrate the purpose and advantages of the present invention, the content of the invention will be further described below in conjunction with an embodiment and corresponding drawings.

[0056] In order to verify the feasibility of the method, taking the reentry mission of CAV-H aircraft as an example, the reentry guidance method simulation under the terminal time constraint is carried out. The initial height of the aircraft is h 0 = 60km, the speed is v 0 =6400m / s, the longitude is θ 0 =0, the latitude is φ 0 = 0; the terminal height of the aircraft is h f = 30km, speed v f =2000m / s, the maximum direction angle deviation is Δψ f =5°; the longitude of the target point is θ T =59°, latitude is φ T = 30°; the expected re-entry terminal time is 1600s, and the maximum terminal time error allowed by the coordinated attack is Δt max = 1s.

[0057] Such as figure 1 As shown, the hypersonic vehicle reentry guidance method under the terminal time c...

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Abstract

The hypersonic vehicle reentry guidance method under the terminal time constraint disclosed by the present invention mainly solves the terminal time constraint problem of multi-hypersonic vehicle cooperative attack missions. The realization method of the present invention is as follows: a parameterized U-shaped azimuth deviation corridor is designed, which is used to control the heading angle and terminal time of the aircraft; a dynamic model and a fourth-order The Adams integral method predicts the re-entry terminal time and obtains the time difference; by adjusting the boundary width coefficient of the U-shaped corridor online, the time difference is eliminated, thereby realizing the re-entry terminal time control of the hypersonic vehicle. The guidance method disclosed in the present invention can better meet the terminal time constraints through the lateral roll angle inversion logic without affecting the tracking accuracy of longitudinal states such as altitude and speed, and provide an effective solution for the hypersonic vehicle coordinated attack guidance problem. Solutions.

Description

technical field [0001] The invention relates to a re-entry guidance method, in particular to a hypersonic aircraft re-entry guidance method under terminal time constraints, and belongs to the field of aircraft guidance and control. Background technique [0002] Hypersonic reentry vehicles generally fly in the adjacent space at an altitude of 20 to 100 kilometers, and the reentry speed can reach Mach 20 or more. It has the characteristics of long range, fast speed, and strong maneuverability, and can be used for long-range rapid strikes. However, the development of long-range detection technology and the deployment of advanced defense systems have limited the penetration probability of hypersonic reentry vehicles to a certain extent, and affected its strategic deterrence. In order to increase the probability of defense penetration, an effective attack method must be adopted, and multi-aircraft coordinated attack is an effective way to improve the penetration capability. Due ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10
CPCG05D1/107
Inventor 梁子璇崔平远朱圣英徐瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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