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An online trajectory planning method and system for a planetary probe dynamic landing segment

A technology for trajectory planning and detectors, which is applied in the direction of aircraft, aerospace vehicles, and aerospace vehicle guidance devices, etc., can solve the problem that the trajectory planning method is not suitable for landing trajectory planning, etc., to achieve error reduction, high discrete accuracy, and enhanced speed and the effect of precision

Active Publication Date: 2022-07-15
BEIHANG UNIV
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  • Abstract
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  • Claims
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Problems solved by technology

[0004] Therefore, the traditional trajectory planning method is not suitable for online landing trajectory planning

Method used

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  • An online trajectory planning method and system for a planetary probe dynamic landing segment
  • An online trajectory planning method and system for a planetary probe dynamic landing segment
  • An online trajectory planning method and system for a planetary probe dynamic landing segment

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Embodiment

[0083] figure 1 It is a flowchart of the online trajectory planning method in the embodiment of the present invention, such as figure 1 As shown, an online trajectory planning method includes:

[0084] Step 101: Obtain the initial state of the probe; the initial state includes the mass, position and velocity of the probe at the beginning of the landing process.

[0085] Step 102: Establish a landing trajectory optimization model according to the initial state of the probe. The landing trajectory optimization model aims to minimize the fuel consumption and determines the constraints according to the constraints of the planetary probe landing process. Limiting factors include limited thrust from braking the engines and preventing collisions with the ground during flight.

[0086] Step 102 specifically includes:

[0087] The objective function of the landing trajectory optimization model is established according to the following formula:

[0088] min J=-m(t f )

[0089] Th...

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Abstract

The invention discloses an online trajectory planning method and system for a dynamic landing segment of a planetary probe. This method uses the Chebyshev pseudospectral method for discretization, transforms the optimal control problem into a nonlinear programming problem, and uses the successive convex optimization method to solve the nonlinear programming into a successively solved second-order cone programming problem. The point method is used as a numerical solution algorithm to iteratively solve this second-order cone plan to obtain the trajectory of the landing process, and to determine the terminal time at the same time. The method and system of the present invention can enhance the speed and accuracy of trajectory planning, and are suitable for online trajectory planning.

Description

technical field [0001] The invention relates to the technical field of trajectory planning, in particular to an online trajectory planning method and system for a dynamic landing segment of a planetary probe. Background technique [0002] During the landing process of a general planetary probe, the optimal fuel is usually used as the index to design the landing trajectory to guide the probe to land safely. Due to the uncertainty of the parachute landing process, the initial conditions of the power landing process cannot be determined in advance. Therefore, it is an ideal way to design the trajectory online according to the actual situation of the landing stage. The online design of the landing trajectory requires the trajectory planning algorithm to have fast enough planning speed and planning accuracy. However, there are many practical physical constraints in the landing process, such as the limited thrust that can be provided, and the uncertainty of the observation angle...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/18B64G1/24
CPCG06F17/18B64G1/242
Inventor 王卫红夏伟博刘正华
Owner BEIHANG UNIV
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