Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms

A motion platform and spacecraft technology, applied in the aerospace field, can solve the problems of rocket volume and boost force limit, launch site selection, climate, weather, etc., and accurately grasp the limitations of the suitable launch window, so as to achieve less restrictions on the launch position, Low cost and slow speed

Inactive Publication Date: 2012-07-11
江苏竣智建设有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing technologies are faced with limitations in many aspects such as rocket size and booster limit, launch site selection, climate, meteorological suitability, and precise grasp of the launch window.

Method used

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  • Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms
  • Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms
  • Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms

Examples

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Embodiment Construction

[0019] like figure 1 , figure 2 Shown, two-stage motion platform of the present invention completes the two-stage rocket space vehicle lift-off orbit acceleration aircraft, and its track 2 is to have reliable rail base 1 that starts from assembly workshop, the double track that radial shape extends outwards. Its orbital motion platform 3 is a streamlined, high-power, high-speed motor that runs along the track 2 with an independent active power system, through which the negative pressure release device of the orbital motion platform, fastens and carries the aircraft platform 4, accelerates and releases the aircraft platform 4, and runs along the track 2. locomotive. Its aircraft platform 4 is designed as an open upper part at the position of the conventional cabin, and is fastened by the negative pressure release device of the aircraft platform and carries a circular-arc groove-shaped rocket loading and carrying compartment for two-stage rocket spacecraft. The cockpit of the ...

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Abstract

The invention relates to an orbit accelerating airplane capable of completing lift-off of a two-stage rocket spacecraft with two-stage moving platforms, which comprises an orbit, an orbit moving platform, an airplane platform and the two-stage rocket spacecraft, and is characterized in that the orbit moving platform and the airplane platform complete start, acceleration and lift-off by means of different power sources and pass through a troposphere to enter a stratosphere, and a relaying launch means of sending the spacecraft by a rocket in the stratosphere is realized. Compared with the prior art, the orbit accelerating airplane has the notable advantages that fuels of a jet engine are saved, the rocket is small in size and low in cost, launch is less limited by a launch site, the weather and the climate, a launch window can be selected, the orbit moving platform and the airplane platform can bear various spacecrafts and is reusable and the like, thereby having quite good use value.

Description

1. Technical field: [0001] The invention relates to spaceflight technology, in particular to an orbital acceleration aircraft whose two-stage motion platform completes the launch of a two-stage rocket spacecraft. 2. Background technology: [0002] The theory of three-stage rocket relay boosting spacecraft into space created by Tsiolkovsky, the father of aerospace, has become the basic model of conception, design, and practice of existing aerospace technology. The extension and expansion of utilization have all-round requirements for quality, quantity, technical difficulty and cost reduction for launch frequency, scale, distance deep into space, and return journey. Existing technologies are faced with limitations in many aspects, such as the limit of rocket size and boosting force, the location of the launch site, the suitability of climate and weather, and the precise grasp of the launch window. 3. Contents of the invention: [0003] The object of the present invention is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F1/04
CPCY02T50/82Y02T50/80
Inventor 董兰田张峰
Owner 江苏竣智建设有限公司
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