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Method for generating safe launching window of weak-gravitation small celestial body surface lander

A small celestial body and lander technology, applied in the field of deep space exploration, can solve the problems of inability to describe the safety degree of the launch state, inability to obtain window boundaries, and large amount of calculations

Active Publication Date: 2020-11-24
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

Although this method can obtain the delivery window, it has a huge amount of calculation, and cannot obtain a strict window boundary, nor can it describe the security degree of the delivery status in the window

Method used

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  • Method for generating safe launching window of weak-gravitation small celestial body surface lander
  • Method for generating safe launching window of weak-gravitation small celestial body surface lander
  • Method for generating safe launching window of weak-gravitation small celestial body surface lander

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Embodiment 1

[0098] In order to verify the feasibility of the method, for the landing problem of the asteroid 433Eros, the polyhedron model is used as the shape approximation of the small celestial body, and the landing dynamics and gravitational field model of the small celestial body are established. Suppose the spin angular velocity of the small celestial body is a constant value ω=3.31×10 -4 rad / s, the position vector of the landing point in the small celestial body fixed coordinate system (hereinafter referred to as the body-solid system) is r L=[8.5426,-3.9511,-5.1855] T km, the lower limit of the tangential landing speed constraint v in the tangential coordinate system of the landing point of the small celestial body (hereinafter referred to as the tangential system) tfmin =-1m / s, tangential landing speed constraint upper limit v tfmax = 1m / s, normal landing speed constraint lower limit v nfmin =-1m / s, the lower limit h of the launch height to ensure that the main detector can re...

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Abstract

The invention discloses a method for generating a safe launching window of a weak-gravitation small celestial body surface lander, and belongs to the technical field of deep space exploration. The implementation method comprises the steps of: firstly, defining a landing point tangent normal coordinate system of a small celestial body, and deriving the analytical relation among the launching state,the landing state and the landing time of a lander near the small celestial body; secondly, establishing a launching constraint meeting the safety rising requirement of a main detector and a landingconstraint meeting the safety landing requirement of the lander on a tangent system, and defining a launching window; then, deducing a two-dimensional projection boundary analytic expression of a window of the landing speed constraint on a two-dimensional plane according to the landing dynamics analytic relation and the launch landing constraint; and finally, designing evaluation indexes representing landing safety to obtain a safe launching window with index distribution. The generated safe launching window can provide a basis for rapid selection of the launching state of the lander, and thelanding safety and the landing success rate are improved.

Description

technical field [0001] The invention relates to a method for generating a launch window of a lander, in particular to a method for generating a safe release window in a fixed-point landing mission on the surface of a small celestial body with weak gravitational force, and belongs to the technical field of deep space detection. Background technique [0002] Small celestial body detection is an important part of the field of deep space exploration, and it is also one of the main tasks in my country's space industry development plan. In Japan's "Hayabusa" series of small celestial body detection missions, several small landers were dropped on the surface of small celestial bodies by the main probe to complete various scientific detection tasks. The surface gravity of small celestial bodies is weak, and the escape velocity is low, which makes the lander easy to rebound and lose control when landing, and the landing constraints are relatively strict. The small lander itself has ...

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Application Information

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IPC IPC(8): G06F30/15G06F119/14
CPCG06F30/15G06F2119/14
Inventor 梁子璇鲁冰洁崔平远朱圣英徐瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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