Spacecraft pneumatic structure

Abstract

A spacecraft pneumatic structure includes a spacecraft body. The spacecraft body includes a column portion which is positioned on the bottom of the spacecraft body; a top cover portion which is positioned on the top of the spacecraft body; and a cone portion which is positioned between the column portion and the top cover portion. The pneumatic structure includes a cone head, a cone portion and a column portion from top to bottom, adopts a small head and a big tail, and can allow the pressure center to close to the bottom of the spacecraft as much as possible; the demand that the pressure center is positioned behind the mass center can be met, pneumatic resistance can be converted into a control torque facilitating a stable attitude of the spacecraft, and in this way, the spacecraft can continuously stably fly under a significant aerodynamic force in an atmospheric environment.

Description

technical field [0001] The invention belongs to the field of aerospace technology, relates to spacecraft, in particular to the aerodynamic configuration of the spacecraft. Background technique [0002] According to the international division of the aerospace field, the aerospace field is defined as being more than 100 kilometers from the ground. Generally, spacecraft operate at an orbital altitude above 300 kilometers from the ground. The space environment above this altitude basically does not contain atmospheric substances. In traditional spacecraft design, it is considered to be in a vacuum state. At present, the design idea of ​​the main structure of spacecraft generally adopts space The "square" or "cylindrical" configuration method with relatively large utilization rate and relatively simple and stable installation of instruments and equipment. [0003] However, the space environment within the extremely low orbit range of 100 kilometers to 300 kilometers from the gro...

AI Technical Summary

Problems solved by technology

In particular, if a traditional spacecraft performs a mission below 150 kilometers and needs to continue flying, at this time, the density of the atmosphere will increase significantly, and the moment generated by the aerodynamic force will increase by about 10 3 At this time, the "square" or "cylindrical" configuration of traditional spacecraft is not conducive to aerodynamic stability, and the general attitude controller is saturated, which cannot achieve stable flight of the spacecraft

[0004] Therefore, an aerodynamically stable spacecraft aerodynamic configuration is needed to convert the aerodynamic resistance into a control torque that is conducive to the stability of the spacecraft attitude, so as to solve the problem of continuous and stable flight of the spacecraft in an atmospheric environment with significant aerodynamic force

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