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Sleeve cover type spaceflight rocket

A shroud and rocket technology, which is applied in the field of aerospace rockets, can solve the problems of high rocket launch costs, and achieve the effects of easy control, cost saving, and reduced launch costs

Inactive Publication Date: 2022-07-12
精易兴航(北京)科技创新有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Domestic launch vehicles have not yet achieved engineering recovery, and the launch costs of rockets are higher than those of foreign companies

Method used

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  • Sleeve cover type spaceflight rocket
  • Sleeve cover type spaceflight rocket
  • Sleeve cover type spaceflight rocket

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0049] Example 1: Three "non-swing" recovery power engine solutions

[0050] Three recovery power engines are fixedly installed on the outer side of the shell section (or sleeve) of the conical top cover. The thrust of the recovery power engine is preferably 5t, and the engine and the arrow body are fixedly installed at an angle of 30° (the engine nozzles are oriented outwardly and obliquely). below), the recovery power engine and its engine nozzle do not swing, only the recovery thrust is adjusted. The rocket separation force is provided by two reverse thrust rockets symmetrically installed on the outer edge of the bottom of the first-stage rocket body. (1) Recovery power thrust function: During the ascent of the rocket, the recovery power engine starts and provides positive thrust to accelerate the rocket ascent. During the recovery process of the rocket, the recovery power engine starts to provide reverse thrust, and the rocket decelerates and descends. (2) The attitude c...

Embodiment 2

[0051] Example 2: Four "non-swing" recovery power engine solutions

[0052]Four "non-swing (that is, fixed)" recovery power engines are installed evenly around the circumference to provide rocket boost and recovery power thrust; the rocket separation force is provided by two reverse thrust rockets symmetrically installed on the outer edge of the bottom of the first-stage rocket body. Its working mechanism: (1) Attitude control function of recovery power: the thrust adjustment of two symmetrical recovery power engines controls the pitch attitude of the rocket, and the thrust adjustment of the other two recovery power engines controls the yaw attitude of the rocket (through the "pneumatic attitude control system"). control the roll attitude of the rocket). (2) Recovery power thrust function: During the ascent of the rocket, the recovery power engine starts and provides positive thrust to accelerate the rocket ascent. During the recovery process of the rocket, the recovery power...

Embodiment 3

[0053] Example 3: Four "circumferential pendulum" recovery power engine scheme

[0054] Four "one-way swing" (circumferential) recovery power engines are installed evenly around the circumference to provide rocket boost, recovery power and attitude control thrust; the rocket separation force is provided by two reverse thrust rockets symmetrically installed on the outer edge of the bottom of the first-stage rocket body. Among them, the "circumferential direction" is relative to the overall columnar launch vehicle, which refers to, see Figure 2B , the engine nozzle can rotate in the direction perpendicular to the plane of the drawing with the swing mechanism as the axis. Its working mechanism: (1) Recovery power thrust function: During the rocket ascent, the recovery power engine starts, provides positive thrust, and accelerates the rocket ascent. During the recovery process of the rocket, the recovery power engine starts to provide reverse thrust, and the rocket decelerates a...

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Abstract

The invention discloses a cover type spaceflight rocket, which relates to the technical field of spaceflight rockets, and comprises a first-stage rocket body, a cone top cover arranged at the upper end of the first-stage rocket body, and a power recovery device, the conic top sleeve cover sequentially comprises a conic top cover and a sliding rail cylinder cover from top to bottom; the cone top cover sequentially comprises a scalloped segment part and a shell section from top to bottom; the sliding rail cylinder cover comprises a sleeve, a sliding rail and a load support. The upper portion of the sleeve is connected with the lower portion of the shell section, the lower portion of the sleeve is connected with the load support, and the sliding rail is arranged on the inner side face of the sleeve. The cone top cover, the sleeve and the load support jointly define a space which can be opened and closed and is used for containing a load, and at least one part of the load is slidably connected with the sliding rail in a matched mode. The cone top sleeve cover and the first-stage rocket body are integrally recycled, and a pull type recycling mode is adopted, so that stable and accurate landing is ensured; the device can be applied to tests of ground launch, flight and sub-orbit flight.

Description

technical field [0001] The invention belongs to the technical field of aerospace rockets, and in particular relates to a hood type aerospace rocket. Background technique [0002] Since the middle of the last century, the world's aerospace powers have continued to carry out research and experiments on reusable space transportation systems. From the perspective of configuration and technical characteristics, reusable vehicles can be divided into two categories: horizontal recovery and reuse vehicles and vertical recovery and reuse of launch vehicles. The premise of carrying out the research on vertical recovery and reuse of the launch vehicle is to carry out the research on the sub-stage recovery technology of the launch vehicle, preferably the "Falcon-9R" rocket of SpaceX, which adopts the method of vertical return; among them, the space shuttle is recovered by horizontal rolling. Horizontal recovery method; "Falcon" rocket fairing splitting adopts parachute marine recovery,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/00
CPCF42B15/00
Inventor 隋国发
Owner 精易兴航(北京)科技创新有限公司
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