Takeoff stability modeling method

A modeling method and a stable technology, applied in the field of multi-body dynamics analysis of spacecraft, can solve problems such as blanks, not belonging to the same field, and large differences in content, etc., to achieve strong engineering practicability, less time-consuming, and convenient The effect of streamlining

Active Publication Date: 2016-09-28
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

Domestic research on launch dynamics analysis technology based on take-off platforms is currently limited to the field of missiles, including vehicle-mounted, ship-borne, airborne, submarine-borne, etc., which are very different from the requirements and content of take-off dynamics ana

Method used

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Embodiment Construction

[0030] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0031] Such as figure 1 As shown, a method for modeling the take-off stability of the surface of an extraterrestrial celestial body includes the following steps:

[0032] Step 1: Establish the dynamic model of the ascender and the dynamic model of the take-off platform, establish the locking constraints between the dynamic model of the ascender and the dynamic model of the take-off platform, and establish the relationship between the soil on the surface of the extraterrestrial celestial body and the dynamic model of the take-off platform Contact relationship;

[0033] The specific process of step 1 is:

[0034] Step 1.1, utilize multi-body system dynamics method to establish lifter dynamics model and take-off platform dynamics model; Described riser dynamics model includes quality characteristics such as mass, center of mass position, moment of inertia, ...

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Abstract

The invention discloses a takeoff stability modeling method. The method comprises the following steps: firstly establishing an ascender and a takeoff platform model, establishing locking constraint between the ascender and the takeoff platform model, and establishing contact relationship between extraterrestrial object surface soil and a takeoff platform; and carrying out calculation by adopting a quasi-static landing process simulation method to obtain an extraterrestrial object surface takeoff initial attitude of a combination of the takeoff platform and the ascender and a support load of the takeoff platform, carrying out physical parameter sensitivity analysis to obtain parameters with relatively high takeoff stability sensitivity, taking the worst numerical value in an initial range of the parameters to carry out calculation so as to obtain a takeoff stability boundary, comparing a numerical value of the boundary with the ability of an attitude control system, and carrying out iterative calculation to finally obtain an ascender takeoff stability boundary which satisfies an ability range of the attitude control system. The invention discloses a set of integrated ascender attitude takeoff stability boundary modeling method which is high in feasibility for the first time, and the method can be used for the parameter design and optimization of spacecraft.

Description

technical field [0001] The invention belongs to the technical field of multi-body dynamics analysis of spacecraft, and in particular relates to a modeling method for take-off stability on the surface of an extraterrestrial celestial body. Background technique [0002] The take-off and ascension on the surface of an extraterrestrial celestial body refers to a series of flights in which the ascender and the take-off platform are unlocked, and then under the thrust of its own engine, on the take-off (launch) platform, the preparation for take-off from the surface of the extraterrestrial celestial body begins until the ascender enters the target orbit. The process of taking off from the surface of an extraterrestrial celestial body means that the ascender independently, safely and reliably realizes the lift-off process on the take-off (launch) platform (hereinafter referred to as the take-off platform) under the environment of the surface of an extraterrestrial celestial body, re...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/367
Inventor 张志娟葛东明柳翠翠
Owner BEIJING INST OF SPACECRAFT SYST ENG
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