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Dynamic Rocket Booster

A rocket propulsion and dynamic technology, applied in the field of rockets, can solve the problems of complex engine structure, heavier rocket weight, easy leakage of liquid, etc., and achieve the effects of improving energy utilization efficiency, increasing degree of freedom, and reducing manufacturing costs.

Inactive Publication Date: 2016-02-24
深圳市志简伟异研究中心
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It has the following disadvantages: one, the engine needs to be made of high-temperature-resistant and high-strength materials, which causes higher manufacturing costs of the engine; two, as an integral part of the rocket, the engine needs to be Equipped with an engine, because the weight of the engine itself is usually relatively heavy, the setting of the engine also objectively increases the weight of the entire rocket; third, due to the heat resistance of the engine material, the flame temperature in the engine cannot be too high, This is not conducive to improving the propulsion power of the entire rocket; fourth, the structure of the engine is complex, especially for liquid fuel rockets, there are many engine pipes and it is easy to leak liquid, which is very easy to cause danger; Adjust the size of the opening so that the engine loses efficiency

Method used

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  • Dynamic Rocket Booster
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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] Please refer to figure 1 , a dynamic rocket propulsor, including a rocket body, the rocket body is filled with solid fuel 1a and the rocket body is provided with a Laval nozzle structure that dynamically makes the bottom of the rocket body suitable for rocket flight when burning with the solid fuel 1a 3a is a control element 2a, the control element 2a includes a shell 21a that wraps the solid fuel and its lower end edge can be consumed by dynamic ablation along with the combustion of the solid fuel when the solid fuel burns.

[0029] The dynamic rocket propeller provided by the present invention adopts a rocket body filled with solid fuel 1a inside, and a control element 2a is arranged on the solid fuel 1a, so that the bottom of the rocket body generates a nozzle structure 3a suitable for rocket flight, At the same time, a shell 21a is provided on the surface of the solid fuel 1a to cover the solid fuel 1a and its lower edge can be ablated together with the arrow body w...

Embodiment 2

[0054] Please refer to figure 2 , compared with the first embodiment, the difference of this embodiment is that the arrangement of the control elements is different. In this embodiment, the control element 2b includes a casing 21b that wraps the solid fuel and its lower end edge can be consumed by dynamic ablation along with the combustion of the solid fuel when the solid fuel 1b burns. The tubular member 22b inside the rocket body and made of memory material, the cross-sectional area of ​​the tubular member 22b memory is larger than the cross-sectional area of ​​the tubular member 22b. When the solid fuel 1b on the rocket body burns, the tubular member 22b will gradually restore the original memory cross-section along with the burning surface 4b, and the lower part will form an expanded state with a larger cross-sectional area. In this way, said tubular member 22b will together with said housing 21b constitute a Laval nozzle structure.

[0055] It should be noted that, in ...

Embodiment 3

[0057] Please refer to image 3 , the present embodiment is different from the first or second embodiment in that: the arrangement of the control elements is different. In this embodiment, the control element 2c includes a casing 21c that wraps the solid fuel and its lower end edge can be consumed by dynamic ablation along with the combustion of the solid fuel 1c when the solid fuel 1c burns. The nozzle generating member 22c below the solid fuel 1c inside the arrow body; the nozzle generating member 22c is penetrated from top to bottom by at least one first channel 221c shaped like a Laval nozzle and / or the nozzle The outer wall of the generating member 22c and the inner wall of the casing 21c together form a second channel 222c shaped like a Laval nozzle. In this way, during the flight of the rocket, the gas generated during the combustion of the solid fuel 1c can be ejected through the first channel 221c and / or the second channel 222c shaped like a Laval nozzle.

[0058] A...

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PUM

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Abstract

The invention belongs to the rocket field, especially relating to a dynamic rocket thruster. The dynamic rocket thruster uses solid fuel and is provided with a control component so that the bottom of a rocket body has a Laval nozzle structure which is suitable for the flight of the a rocket. The control component includes a rocket body housing. When the solid fuel burns, the lower edge of the housing can be dynamically ablated and consumed along the burning face of the solid fuel. In this way, during the flying course of the rocket, the bottom of the rocket body dynamically produces a nozzle structure which is suitable for the flight of the rocket. Moreover, the generated waste is actually ejected through the nozzle structure as a working medium that propels the rocket to fly, which means discarding redundant weight of the rocket timely and not producing bigger waste. Thus the freedom degree for designing the flying route of the rocket is improved.

Description

technical field [0001] The invention belongs to the field of rockets, in particular to a dynamic rocket propeller. Background technique [0002] The rocket is a jet propulsion device that is ejected backward at a high speed by thermal air flow and uses the reaction force generated to move forward. It carries combustion agents and oxidizers by itself, does not rely on oxygen in the air to support combustion, and can fly in the atmosphere and in outer space. Modern rockets can be used as rapid long-distance transport vehicles, and can be used to launch satellites and deliver weapons warheads (such as warheads). [0003] A traditional rocket is roughly composed of a rocket shell, fuel, and an engine. The role of the rocket case is to protect the internal components of the rocket and support the rocket. The energy produced when rocket fuel burns powers the rocket's flight. The engine controls the combustion of fuel and the injection of flame. [0004] Due to the gradual con...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/08F02K9/32
Inventor 刘志伟
Owner 深圳市志简伟异研究中心