Planetary exploration landing trajectory comprehensive optimization method

An optimization method and planetary technology, applied in the field of deep space exploration, to achieve the effect of reducing fuel consumption and ensuring safe and accurate landing

Active Publication Date: 2018-07-13
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] The technical problem to be solved by the comprehensive optimization method for planetary exploration and landing trajectory disclosed by the present invention is: taking into account the fuel consumption performance, the uncertainty of planetary la

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  • Planetary exploration landing trajectory comprehensive optimization method
  • Planetary exploration landing trajectory comprehensive optimization method

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Embodiment 1

[0065] like figure 1 As shown, the comprehensive optimization method for planetary exploration and landing trajectory disclosed in this embodiment, the specific implementation steps are as follows:

[0066] Step 1. Establish the landing dynamic equation of the probe.

[0067] Define the celestial fixed coordinate system Σ a : Origin O a Located at the center of mass of the celestial body, z a axis coincides with the axis of maximum inertia of the celestial body, that is, the axis of rotation, x a with y a axes coincide with the minimum and intermediate inertia axes respectively, x a ,y a ,z a Three axes satisfy the right-hand rule.

[0068] Establish the planetary probe landing dynamic equation in the celestial fixed coordinate system:

[0069]

[0070] where r=[x,y,z] T is the position vector of the detector in the celestial body-fixed coordinate system, v=[v x ,v y ,v z ] T is the velocity vector of the detector, m is the quality of the detector, ω=[0,0,ω] ...

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Abstract

The invention discloses a planetary exploration landing trajectory comprehensive optimization method, and relates to a planetary landing trajectory optimization method, belonging to the field of deepspace exploration. The method is implemented by the following steps: establishing a detector landing dynamics equation; calculating the probability of collision between a detector and planetary surface obstacles; setting up a planetary exploration landing trajectory comprehensive optimization problem by taking the uncertainty of fuel consumption performance and planetary landing as well as the complex terrain conditions of the obstacles existing on the planet surface into account; solving the planetary exploration landing trajectory comprehensive optimization problem, and completing the comprehensive optimization of the planetary exploration landing trajectory by taking the uncertainty of fuel consumption performance and planetary landing as well as the complex terrain conditions of the obstacles existing on the planet surface into account so as to realize safe and accurate landing. In addition, in the calculation of the collision probability, the description of the degree of threat tothe detector under the condition of uncertainty is more accurate. By simplifying a collision probability formula, the calculation amount is reduced and the optimization speed is accelerated under thepremise of guaranteeing accuracy.

Description

technical field [0001] The invention relates to a method for optimizing a planetary landing trajectory, in particular to a comprehensive optimization method for a planetary detection and landing trajectory, belonging to the field of deep space detection. Background technique [0002] Planetary surface landing is an important form of planetary exploration and a research hotspot in the field of deep space exploration. Among them, the planetary exploration and landing trajectory optimization technology is the key technology to realize the planetary surface landing, which is related to the success or failure of the exploration mission. In order to achieve a safe and precise soft landing, the optimal landing trajectory for planetary exploration needs to meet multiple constraints such as initial, terminal state constraints, control constraints, and safety constraints, while optimizing performance indicators such as fuel consumption. [0003] Planetary landing dynamics and environ...

Claims

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Application Information

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IPC IPC(8): G01C21/24G06Q10/04
CPCG01C21/24G06Q10/047
Inventor 崔平远袁旭朱圣英徐瑞于正湜
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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