Low-wind-drag pipeline type track and launch vehicle spacecraft launching system

A pipeline-type and orbital technology, which is applied in the direction of launch systems, space navigation vehicles, launch/drag transmissions, etc., can solve problems such as high air density, rocket transport devices cannot run at high speed, and transport devices are difficult to run at high speeds, etc., to reduce The effect of gas exchange

Pending Publication Date: 2018-03-30
秦赵修
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The object of the present invention is to provide a low wind resistance ducted track and launch vehicle spacecraft launch system, to alleviate the problem of high air density in low-altitude areas in the prior art, and it is difficult for transport devices to achieve high-speed operation in such areas. The technical problem that the transport device cannot run at high speed from low altitude to high altitude

Method used

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  • Low-wind-drag pipeline type track and launch vehicle spacecraft launching system
  • Low-wind-drag pipeline type track and launch vehicle spacecraft launching system
  • Low-wind-drag pipeline type track and launch vehicle spacecraft launching system

Examples

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Comparison scheme
Effect test

Embodiment 1

[0036] Such as figure 1 As shown, a low-drag pipeline track provided by this embodiment includes a roadbed 1 and a plurality of pipeline bodies 2 fixed on the roadbed 1. The multiple pipeline bodies 2 are successively fixed to each other, and the multiple pipeline bodies 2 Each is provided with a track 3 that is continuous with each other, and the track 3 is laid along the roadbed 1.

[0037]The duct body 2 includes a first fixing piece 21 and a second fixing piece 22 arranged opposite to each other, a plurality of air ducts 23 fixed between them at equal intervals in the circumferential direction, and correspondingly fixed on the inner walls of the plurality of air ducts 23 A plurality of heating units 24, and a plurality of air ducts 23 of the duct body 2 adjacent to each other communicate with each other correspondingly.

[0038] The plurality of air ducts 23 are respectively connected with a plurality of air blowing parts, and the plurality of air ducts 23 are respectivel...

Embodiment 2

[0060] This embodiment provides a launch system for a launch vehicle and a spacecraft, which has the low-drag pipeline track described in the first embodiment above.

[0061] The launch system of the launch vehicle and spacecraft has the same advantages as the above-mentioned low-drag pipeline track, and will not be repeated here.

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Abstract

The invention provides a low-wind-drag pipeline type track and a launch vehicle spacecraft launching system and relates to the technical field of launch vehicle spacecraft launching. The low-wind-dragpipeline type track comprises a roadbed and multiple pipeline bodies fixedly arranged on the roadbed. The multiple pipeline bodies are continuously and fixedly connected with each other in sequence and internally provided with track bodies continuously connected with each other. The track bodies are laid along the roadbed. Each pipeline body comprises a first fixing piece, a second fixing piece,multiple air pipes and multiple heating units. The multiple air pipes of the pipeline bodies adjacent to each other correspondingly communicate with each other. The multiple air pipes correspondinglycommunicate with multiple air blowing pieces. Multiple air outlets are correspondingly formed in the multiple air pipes at equal intervals in the axial direction. Air streams in the positions of the multiple air outlets can join each other. The low-wind-drag pipeline type track has the beneficial effect that a rocket transport device can run to a high-attitude area from a low-attitude area at a high speed.

Description

technical field [0001] The invention relates to the technical field of launching rockets and spacecrafts, in particular to a low-windage ducted track and a launching system for launching rockets and spacecrafts. Background technique [0002] It has been the dream of aerospace scientists and technicians for nearly a hundred years to enter orbit with a single stage or fully recover and reuse the spacecraft. British Aerospace Corporation and Rolls-Royce proposed a HOTOL aerospace transportation system design in the 1980s, but it was stopped due to various reasons. However, its research conclusions show that: the horizontal take-off spacecraft can greatly reduce fuel consumption and save structural weight when its initial speed is high. When the speed of the vehicle reaches Mach 0.2, it can save 8.8% fuel, and when it reaches Mach 0.4, it can save 16.7% fuel, and it can further save fuel when the speed is higher. [0003] Prior art vehicles available to provide this capability...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/00
CPCB64F1/10B64G1/002B64G1/2427
Inventor 秦赵修
Owner 秦赵修
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