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Hovering soft-landing system for rocket propelling module

A rocket propulsion and recovery system technology, applied to self-propelled bombs, aircraft parts, offensive equipment, etc., can solve the problems of damage in the landing area, cost waste, non-reusable, etc., achieve economical savings, prolong service life, and realize reuse Effect

Inactive Publication Date: 2017-04-19
李爱兵 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, launch vehicles all over the world are disposable aerospace tools. After the first stage of the rocket is completely separated, it will fall in free fall and fall to no-man’s land on land or open sea. It cannot be reused. On the one hand, it may cause damage to the landing area. harm, on the other hand there is a waste of cost

Method used

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  • Hovering soft-landing system for rocket propelling module
  • Hovering soft-landing system for rocket propelling module
  • Hovering soft-landing system for rocket propelling module

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] After the launch of the rocket propulsion module reaches the target airspace and separates the rocket from the star to the rocket ship, it enters the first and second stages of A deep space space recovery: a attitude adjustment stage and b unpowered vertical landing stage, (11) the attitude adjustment device starts to implement the rocket propulsion module Attitude control, (1) in the information remote control system (6) remote control to the full-angle steering gear 8 rudder stock, the directional steering gear 7 sends the rudder plate to rotate 90°, the rudder stock 12 extends out of the cabin, and the rudder plate 90° erects the command , make the (11) attitude adjustment device enter the working state, and then send to the rudder 10 full-angle steering device 8, control the cabin body rollover, control the cabin body rotation command, to deal with the influence of aerodynamic torque and rotation, so that the rocket propulsion cabin has almost no Any roll, always mai...

Embodiment 2

[0031] After the rocket propulsion cabin reaches the high-time space of B, it enters the c auxiliary device work switching stage, which is the third stage. (6) The remote control sends the steering plate to the full-angle steering device 8 directional steering device 7 rudder stock, and the rudder plate is 90° horizontally. rise, the rudder stock 12 shrinks, and the rudder plate flat rotation command shrinks the (11) attitude adjustment device into the (8) rocket cabin device room, and the explosion bolt explodes and fixes (12) the bolts of the power suspension device rotor, and utilizes aerodynamic force to let the The wing blades 5 are unfolded, and under the action of the airflow, the wing blades 5 rotate freely without power, and generate upward lift force to implement the landing deceleration of the rocket propulsion cabin.

[0032] All the other stages are the same as in Embodiment 1.

Embodiment 3

[0034] After the launch of the rocket propulsion module reaches the target airspace and the separation of the rocket from the star and the rocket ship, it enters the first and second stages of A deep-time space recovery: a stage of attitude adjustment and b stage of unpowered vertical landing. Due to inertia, the rocket propulsion module continues to fly into the air. When the lift-off potential energy is about to be zero, (1) in the information remote control system, (6) the remote control sends instructions to (12) the power suspension device, and the explosion bolt is used. The power allows the blades 5 to unfold, and under the action of the airflow, the blades 5 rotate freely without power, generating upward lift force to implement the landing deceleration of the rocket propulsion cabin.

[0035] All the other stages are the same as in Embodiment 1.

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Abstract

The invention discloses a hovering soft-landing system for a rocket propelling module. The hovering soft-landing system comprises a rocket module device chamber device, a rocket engine and a landing receiving device, wherein the rocket module device chamber device is installed above an oxidant box of the rocket propelling module; a power hovering device and an attitude adjustment device are installed at the top and the middle part in the rocket module device chamber device respectively; and the landing receiving device comprises a landing protection device and a landing receiving device. According to the hovering soft-landing system disclosed by the invention, the rocket propelling module is enabled to realize autonomous attitude adjustment, autonomous speed reduction, autonomous flight, autonomous hovering, autonomous protection and fixed-point landing during a recovery process with three time-space domains through the five devices under the twenty-one instruction requirements of one command information system; and great economic saving is realized, the reuse of the rocket propelling module is realized, and the service life of the rocket propelling module is prolonged.

Description

technical field [0001] The invention relates to a recovery technology of a rocket propulsion cabin, in particular to a recovery system for a suspended flight and soft landing of a rocket propulsion cabin. Background technique [0002] Launching a rocket into the sky is a very costly and costly project. Generally speaking, it takes 60-70 kilograms of rockets to send a kilogram of objects into orbit, and about 500 tons of rockets are needed for an 8-ton spaceship. . At present, launch vehicles all over the world are disposable aerospace tools. After the first stage of the rocket is completely separated, it will fall in free fall and fall to no-man’s land on land or open sea. It cannot be reused. On the one hand, it may cause damage to the landing area. Injury, on the other hand, there is a waste of cost. The cost of the rocket is generally 50 million US dollars, but the fuel cost is only 200,000 US dollars. Through repeated use, the cost can theoretically be reduced to 1% o...

Claims

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Application Information

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IPC IPC(8): F42B10/48F42B15/01B64F1/00
Inventor 李爱兵李慧祥
Owner 李爱兵
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