RLV landing section guidance law acquiring method based on sliding-mode control theory

A control theory and acquisition method technology, applied in the field of RLV landing guidance law acquisition, can solve catastrophic problems, lack of go-around capability, RLV cannot land safely, etc., achieve the effect of improving guidance accuracy and simplifying the design process

Active Publication Date: 2017-08-29
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0003] The return and re-entry phase of the RLV is usually divided into the initial re-entry phase, the terminal energy management phase, and the approach and landing phase. Go-around capability, if the guidance or control method is unstable or cannot meet the accuracy requirements, it may cause the RLV to fail to land safely, and even lead to catastrophic consequences

Method used

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  • RLV landing section guidance law acquiring method based on sliding-mode control theory
  • RLV landing section guidance law acquiring method based on sliding-mode control theory
  • RLV landing section guidance law acquiring method based on sliding-mode control theory

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Embodiment

[0083] The effectiveness of the method of the present invention is illustrated below through simulation.

[0084] The trajectory of the RLV approach and landing segment is divided into steep glide segment, arc segment, exponential transition segment and shallow glide segment. The specific off-line trajectory design method can be found in the literature (G.H.Barton and S.G.Tragesser, Autolanding trajectorydesign for the X-34, AIAA -99-4161,1999.), this simulation example only gives the relevant parameters of the designed trajectory.

[0085] The coordinate system is established with the projection of the starting point of approach and landing on the ground as the origin, the x-axis points to the touchdown point, the y-axis is perpendicular to the x-axis and points to the sky, and the z-axis is determined according to the right-hand rule. The position of the aircraft in the coordinate system is defined by (x, h, z) said. Let the coordinates of the starting point of approach and l...

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Abstract

A RLV landing section guidance law acquiring method based on a sliding-mode control theory comprises steps of: calculating a height deviation and a lateral distance deviation according to an RLV landing section nominal trajectory; then, selecting an appropriate sliding-mode surface according to the tracking deviation of the nominal trajectory, and equivalently converting a RLV three-degree-of-freedom kinetic equation into a form described by the sliding-mode surface; and finally, designing the guidance law by using a Lyapunov method. In the design process, by analyzing aerodynamic data, the uncertainty upper bound of a guidance circuit is obtained and a compensation term is introduced to suppress the uncertainty so that the guidance system has asymptotic stability to the uncertainties such as disturbance. The method can overcome the influence of the uncertainty of the RLV guidance system so as to improve guidance precision, converts an original second-order system into a first-order system by introducing the sliding-mode control method, thereby achieving a visual design process.

Description

technical field [0001] The invention relates to a method for obtaining guidance law of RLV landing section based on sliding mode control theory. Background technique [0002] Reusable launch vehicles (RLV) are space shuttle vehicles that combine the features and functions of spacecraft and aircraft. They can stay in orbit to complete various space tasks, and can also return safely and accurately like an airplane. ground. Due to its reusable characteristics, RLV will become a highly reliable carrier for human beings to explore the universe at a low cost and a military weapon for competing for space supremacy. Therefore, the major powers in the world continue to invest huge resources in its research and development, and conduct new research and exploration. [0003] The return and re-entry phase of the RLV is usually divided into the initial re-entry phase, the terminal energy management phase, and the approach and landing phase. Go-around capability, if the guidance or con...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 严晗何英姿
Owner BEIJING INST OF CONTROL ENG
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