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Satellite-rocket integrated multifunctional structure aircraft for ground simulation

A ground-simulating and multi-functional technology, which is applied to aircrafts, astronauts, and astronaut guides, etc. It can solve the problems of low payload ratio and poor performance of integrated aircraft, and improve the payload ratio and reduce the structure. Effects of mass and redundant volume

Active Publication Date: 2017-09-08
NAT UNIV OF DEFENSE TECH
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AI Technical Summary

Problems solved by technology

[0010] The purpose of the present invention is to provide a ground simulation satellite-rocket integrated multifunctional structure aircraft, which is used to solve the technical problems that the payload ratio of the satellite used in the existing integrated structure is low; the performance of the integrated aircraft is poor

Method used

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  • Satellite-rocket integrated multifunctional structure aircraft for ground simulation
  • Satellite-rocket integrated multifunctional structure aircraft for ground simulation
  • Satellite-rocket integrated multifunctional structure aircraft for ground simulation

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[0048] (1) Overall layout and envelope size

[0049] The main body of the satellite-rocket integrated multifunctional structure aircraft for ground simulation is a nearly cylindrical shape of Φ1200mm×3211mm (the one including the adapter is Φ1200mm×3283mm). The front end is arranged with the required payload 800, such as high-resolution cameras, communication antennas, etc., which are in the shape of a cylinder of Φ940mm×1203mm; A nearly cylindrical shape of ×1916mm; the rear end of the aircraft with a star-rocket integrated multifunctional structure for ground simulation is connected to the adapter of the carrier, and the envelope size of the adapter is Φ1200mm×500mm.

[0050] A multi-functional solar battery sail panel is installed in each ±Y direction of the star. It is folded on the side of the shared service cabin during the launch phase. Its envelope size is a cylindrical shape of Φ1200mm×1374mm. The array is 1846mm×1374mm, and the distance between the farthest ends of ...

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Abstract

The invention provides a satellite-rocket integrated multifunctional structure aircraft for ground simulation and relates to the technical field of aerospace structure design. The satellite-rocket integrated multifunctional structure aircraft mainly comprises a propulsion subsystem, a common multifunctional solar panel, a common multifunctional service module and an effective load, wherein the effective load is arranged at the front end; the common multifunctional service module is located in the middle; the propulsion subsystem is located at the bottom of the common multifunctional service module; and the rear end of the system is also connected with an adapter of a vehicle. Through designing a series of novel concept multifunctional structures, such as the common multifunctional solar panel, a multifunctional structure cable, a multifunctional satellite-rocket adapter, a multifunctional structure battery and a multifunctional structure computer, deep integration of the structures is achieved, and the structure quality and redundancy volume of a system are effectively reduced, so that the payload ratio of a satellite is greatly improved, and the performance of the satellite-rocket integrated aircraft is greatly strengthened.

Description

technical field [0001] The invention relates to the technical field of spaceflight structure design, in particular to an aircraft with an integrated multifunctional structure of satellite and rocket for ground simulation. Background technique [0002] In order to improve the rapid response capability in space, it is of great strategic significance to develop the integration of satellites and rockets. The satellite-rocket integration has the characteristics of rapid development, rapid integration, rapid testing, rapid launch and rapid orbit entry, etc., and can be applied to various emergency situations (such as natural disasters and communication system failures, etc.), realizing the Rapid launch and space deployment, timely access to disaster situation information, minimize disaster losses and organize disaster relief. [0003] In order to achieve maximum performance, the Star-Array integrated aircraft requires a lightweight structure. By reducing the mass of the payload ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/26B64G1/44B64G1/66
CPCB64G1/10B64G1/26B64G1/44B64G1/66
Inventor 李东旭曾国强黄奕勇张峰彭超义尹昌平蒋建平李德湛杜金榜刘望
Owner NAT UNIV OF DEFENSE TECH
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