WO2014153712A1

WO2014153712A1 - Dynamic rocket propelling device

Info

Publication number: WO2014153712A1
Application number: PCT/CN2013/073154
Authority: WO
Inventors: 刘志伟
Original assignee: Liu Zhiwei
Priority date: 2013-03-25
Filing date: 2013-03-25
Publication date: 2014-10-02

Abstract

Disclosed is a dynamic rocket propelling device using solid fuel (1a) and provided with a control element (2a), thereby making the bottom part of the rocket body form a Laval nozzle structure (3a) suitable for rocket flight. The control element (2a) comprises a rocket body casing (21a), and when the solid fuel undergoes combustion, a lower edge of the casing (21a) can be dynamically ablated along with the combustion front of the solid fuel. In this way, during the flight of the rocket, the bottom part of the rocket body can be dynamically made to form the nozzle structure (3a) suitable for rocket flight, and the waste generated essentially serves as a working medium to propel the flight of the rocket and is ejected by the nozzle structure, i.e. excess weight of the rocket can be discarded in a timely manner, and waste of a relatively large volume is not generated, thereby improving the degrees of freedom for designing a rocket flight path.

Description

Dynamic rocket thruster

Technical field

The invention belongs to the field of rockets, and in particular relates to a dynamic rocket propeller.

Background technique

The rocket is a jet propulsion device that is jetted back at a high speed by a hot air flow and moves forward using the generated reaction force. It carries the combustion agent and oxidant itself, does not rely on the oxygen in the air to support combustion, and can fly in the atmosphere or in outer space. Modern rockets can be used as fast long-distance vehicles for launching satellites and delivering weapons warheads (such as warheads).

Traditional rockets are generally composed of rocket casings, fuels, engines, and the like. The role of the rocket casing is to protect the internal components of the rocket and to support the rocket. The energy generated by the rocket fuel burning powers the rocket flight. The engine controls the combustion of the fuel and the injection of the flame.

During the rocket flight, due to the gradual consumption of fuel, the original fuel-filled casing will gradually become empty, and the extra empty shell has no meaning for the rocket's propulsion, and will become the excess weight carried during the rocket flight, so to reduce the entire rocket. The weight is usually discarded directly in the air. The existing method is to make the rocket into a multi-stage rocket. Each stage of the rocket is equipped with an engine, and the empty shell of the first-class rocket is discarded every time the fuel of the first-class rocket is used.

Therefore, from the perspective of discarding excess weight, the rocket should be manufactured in an infinite number of stages so that excess weight can be discarded as quickly as possible. However, the more rocket stages, the more complex the rocket is, and each stage must have its own engine, which in turn increases the weight, so the rocket stage can not be too much. The current rocket series usually does not exceed three levels. Therefore, the existing rocket cannot do so in a very timely manner to discard excess weight.

In addition, the shells discarded by the rocket may hit people or objects on the ground, so the discarding location cannot be chosen at will, so it will also limit the flight path of the rocket to some extent.

Existing rocket engines use the engine to control fuel combustion and injection to power the rocket. The main components of the engine are the combustion chamber and the nozzle. The fuel is combusted in the combustion chamber and then ejected through the nozzle to generate power. Both the combustion chamber and the nozzle are made of high temperature resistant, high strength materials. Sometimes these two parts are also equipped with cooling devices to protect the mechanism from burning at high temperatures. It has the following shortcomings: First, the engine needs to be made of high temperature resistant and high strength materials, which results in higher engine manufacturing costs. Second, the engine is an integral part of the rocket and needs to be used on each stage of the rocket. Equipped with an engine, since the weight of the engine itself is usually heavier, the setting of the engine is also objectively exacerbated by 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 liquid fuel rockets, the engine pipeline is many and easy to leak liquid, which is extremely dangerous; fifth, the engine nozzle opening usually cannot follow the external air pressure. Adjust the size of the opening to make the engine lose efficiency.

technical problem

The technical problem to be solved by the present invention is to provide a dynamic rocket thruster, thereby reducing the following problems:

1. The existing rockets produce discards that are too large in size and cannot discard the excess weight of the rocket in time;

2. The manufacturing cost is too high;

3. Fuel energy utilization efficiency is low.

Technical solution

The dynamic rocket thruster provided by the present invention is implemented as follows:

a dynamic rocket propeller comprising an arrow body filled with solid fuel and having a control element on the arrow body that dynamically generates a Laval nozzle structure suitable for rocket flight when the solid fuel is burned with the solid fuel The control element includes an outer casing encasing the solid fuel and having a lower edge rim that can be consumed in conjunction with combustion dynamic combustion of the solid fuel when the solid fuel is combusted.

Specifically, the arrow body is provided with a plurality of electrodes and a discharge control system for controlling the discharge state of each of the electrodes and/or at least one cooling passage for injecting the coolant.

Specifically, the outer casing is a memory casing made of a shape memory material, the memory casing having a cross-sectional area that is smaller than a cross-sectional area of the arrow body.

Specifically, the memory housing surface is provided with lateral scratches and/or the interior of the memory housing material is provided with a transverse fibrous material.

In particular, the control element further includes a tubular member disposed within the body and made of a memory material, the tubular member memorizing a cross-sectional area greater than a cross-sectional area of the tubular member.

In particular, the tubular member surface is provided with lateral scratches and/or its material is internally provided with a transverse fibrous material.

Specifically, the control element further includes a nozzle generating member disposed under the solid fuel inside the arrow body; and the first portion of the nozzle generating member penetrates from the top to the bottom with at least one shape such as a Laval nozzle The passage and/or the outer wall of the nozzle generating member together with the inner wall of the outer casing form a second passage shaped like a Laval nozzle.

Specifically, the dynamic rocket propeller is internally provided with a traction climbing mechanism that connects the nozzle generating members.

Specifically, a cooling device is disposed in the nozzle generating member, and a surface of the nozzle generating member is provided with a cooling material outlet that communicates with the cooling device.

Beneficial effect

The invention has the beneficial effects that the dynamic rocket propeller provided by the invention adopts solid fuel and is provided with a control element, so that the bottom of the arrow body generates a Laval nozzle structure suitable for rocket flight. The control element includes an arrow housing that can be dynamically ablated with the combustion surface of the solid fuel as the solid fuel burns. In this way, during the flight of the rocket, the bottom of the arrow body can dynamically generate a Laval nozzle structure suitable for rocket flight, and the generated discards are substantially used as the working medium for propelling the rocket to fly by the Laval spray. When the pipe structure is sprayed out, the excess weight of the rocket can be discarded in time, and no large discards are generated, thereby improving the freedom of the rocket flight path design. In addition, since the pusher has a simple structure, the manufacturing cost can be reduced. Since the propeller acts as a part of the nozzle during operation, the propeller is easy to generate a larger Laval nozzle structure, and the larger Laval nozzle structure is advantageous for improving the energy utilization efficiency of the fuel.

DRAWINGS

1 is a schematic structural view of a first embodiment of a dynamic rocket propeller provided by the present invention;

2 is a schematic structural view of a second embodiment of a dynamic rocket propeller provided by the present invention;

3 is a schematic structural view of a third embodiment of a dynamic rocket propeller provided by the present invention.

Embodiments of the invention

The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It is understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Embodiment 1

Referring to FIG. 1 , a dynamic rocket propeller includes an arrow body filled with a solid fuel 1 a and the arrow body is provided with a dynamic force for burning the bottom of the arrow body to facilitate rocket flight when the solid fuel 1 a is burned. A control element 2a of the Val spout structure 3a, the control element 2a comprising a casing 21a encasing the solid fuel and having a lower edge rim that can be consumed with combustion dynamic combustion of the solid fuel when the solid fuel is combusted.

The dynamic rocket thruster provided by the present invention adopts an arrow body internally filled with the solid fuel 1a, and a control element 2a is disposed on the solid fuel 1a, so that the bottom of the arrow body generates a nozzle structure 3a suitable for rocket flight. At the same time, the surface of the solid fuel 1a is provided with a casing 21a which encloses the solid fuel 1a and which can be ablated along with the arrow body when the solid fuel 1a is burned. In this way, during the flight of the rocket, the bottom of the solid fuel 1a can dynamically generate a nozzle structure 3a suitable for rocket flight, and the generated discard substantially serves as a working medium for propelling the rocket to fly from the nozzle structure. When 3a is ejected, the excess weight of the rocket can be discarded in time, and no large discards are generated, thereby improving the freedom of design of the rocket flight path.

In the present embodiment, the solid fuel 1a is provided with a plurality of electrodes 5a and a discharge control system for controlling the discharge state of each of the electrodes 5a and/or at least one cooling passage 6a for injecting the coolant 7a. Here, the burning state of the solid fuel 1a is controlled by injecting the discharge state of the coolant 7a and the control electrode 5a through the cooling passage 6a, thereby achieving the purpose of adjusting the shape of the combustion surface 4a. When the burning speed is too fast, the combustion surface 4a can be cooled or even extinguished by increasing the injection amount of the coolant 7a. The electrode 5a may radiate an arc toward the lower end of the combustion face 4a, thereby accelerating the combustion of the solid fuel on the combustion face 4a, or accelerating the burning rate at certain specific positions, or igniting the solid fuel. Further, the gas atmosphere required for the discharge of the electrode 5a can be provided by vaporization of the coolant 7a injected into the cooling passage 6a. In addition, it should be noted that the cooling passage 6a and the electrode 5a employed in the present invention are both dynamically ablated with the advancement of the combustion surface 4a on the solid fuel 1a, and the cooling passage 6a, the electrode 5a, and the injection passage 6a are injected. The gas generated after the gasification of the coolant 7a can be ejected from the nozzle structure 3a along with the gas generated by the combustion of the solid fuel 1a, that is, the cooling passage 6a, the electrode 5a, and the cooling passage. The gas produced by the gasification of the injected coolant 7a of 6a should be considered as part of the working medium that propels the rocket. More specifically, the electrode 5a and the cooling passage 6a are both disposed in the axial direction of the solid fuel 1a and in parallel to the axial direction of the solid fuel 1a. Further, in the present embodiment, the mechanical strength of the solid fuel 1a can also be enhanced by appropriately enhancing the mechanical strength of each of the electrodes 5a.

Further, by adding an inductance detecting device for detecting the inductance of the electrode 5a to the arrow body, the length of the electrode can be known, and the remaining amount of the solid fuel 1a can be converted. The resistance detecting device for detecting the electric resistance of the electrode 5a is used to know the temperature of the flame combustion, thereby converting the speed at which the solid fuel 1a burns and whether the rocket thruster has been turned off.

Further, the area size of the combustion surface 4a is controlled by controlling the distance of the liquid surface of the coolant 7a on the cooling passage 6a from the combustion surface 4a. Specifically, when the coolant 7a is far from the combustion surface 4a, the combustion flame on the combustion surface 4a will ignite the portion of the cooling passage 6a where there is no coolant 7a, in which case The portion of the cooling passage 6a where the coolant 7a is not present also becomes a part of the combustion surface 4a, so that the total area of the combustion surface 4a is relatively large. Therefore, the area of the combustion surface 4a can be adjusted by adjusting the distance of the coolant 7a from the combustion surface 4a.

In an embodiment, the outer casing 21a is a memory casing made of a shape memory material, the memory casing having a memory cross-sectional area smaller than a cross-sectional area of the solid fuel 1a. The memory casing may be specifically manufactured by first making the memory casing remember a shape having a smaller cross section than the cross section of the solid fuel 1a, and expanding the cross section of the memory casing to be wrapable. The structure of the solid fuel 1a, thereby completing the process of providing a memory casing on the solid fuel 1a.

The shape memory material used in the above described memory casing may be a memory alloy or a polymer heat shrinkable material. The outer casing of the solid fuel 1a is made of a shape memory material, wherein the material of the arrow body provides mechanical support for the arrow body, and the material also dynamically generates a Laval nozzle structure, which is also a consumable material, and is also a kind of propulsion. Working quality.

Wherein, the memory alloy may be the following formulas Au-Cd, Ag-Cd, Cu-Zn, Cu-Zn-Al, Cu-Zn-Sn, Cu-Zn-Si, Cu-Sn, Cu-Zn-Ga, One of In-Ti, Au-Cu-Zn, NiAl, Fe-Pt, Ti-Ni, Ti-Ni-Pd, Ti-Nb, U-Nb, and Fe-Mn-Si. The polymer heat-shrinkable material is also called a polymer shape memory material, and is an intelligent material which is a combination of a polymer material and a radiation processing technology. Ordinary polymer materials such as polyethylene, polyvinyl chloride, etc. are usually linear structures. After being irradiated by a radiation source such as an electron accelerator into a network structure, these materials have a unique "memory effect", expansion, cooling and shaping. The material can re-shrink to restore its original shape when heated. The memory properties of the heat-shrinkable material can be used to make heat-shrinkable pipes, membranes and profiled materials. The main characteristic is that the heat shrinkage is coated on the outer surface of the object, which can function as insulation, moisture, seal, protection and connection, and the diameter of the shrinkage material. The shrinkage rate can reach 50%~80%.

During the flight of the rocket, the solid fuel on the solid fuel 1a is gradually moved upward by its bottom portion along its combustion surface 4a, and the memory casing will dynamically form a Laval nozzle structure commonly used in rocket nozzles. As is well known, the Laval nozzle is composed of three parts, which are respectively a shrink tube 31a, a expansion tube 33a, and a throat 32a connecting the shrink tube 31a and the expansion tube 33a.

The process of forming the various sections of the Laval nozzle structure by the memory casing is described below. Due to the difference in heating time of the respective portions of the memory casing, the higher the temperature of the portion of the memory casing which is farther from the burning surface 4a, the lower the temperature of the portion of the memory casing which is closer to the burning surface 4a. The portion of the memory casing that is closer to the burning surface is contracted by heat to form the shrinking tube 31a; the portion of the memory casing that is farther from the burning surface and that is connected to the shrinking tube 31a is heated more time than the shrinking tube 31a. Forming the throat 32a sufficiently; the portion of the memory casing that is further away from the combustion surface and connected to the throat 32a has been softened due to the longer heating time, and is subjected to the combustion medium on the combustion surface 4a. Under the influence of the pressure of the generated high pressure gas, the memory casing of this portion will expand outward to form the expansion tube 33a. Therefore, in the present embodiment, during the combustion of the solid fuel 1a, the memory casing follows the advancing process of the combustion surface 4a of the solid fuel 1a, and the lower portion thereof will exhibit the Laval commonly used in the rocket nozzle structure. Nozzle structure. Further, as the combustion surface 4a is advanced, the shrinkage tube 31a will gradually become the throat 32a, which will gradually become the softening expansion tube 33a, and the expansion tube 33a will increase in temperature as the temperature thereof increases. It will begin to melt or vaporize away from the memory casing. Thus, in the present embodiment, during the combustion process of the solid fuel 1a, the memory casing thereon will dynamically form a Laval nozzle structure, and the memory casing made of the memory material may follow the solid fuel 1a. The formation dynamics and dynamic burning of the combustion surface 4a described above, and no large discards appear throughout the combustion process.

In order to prevent the Laval nozzle structure from being formed due to the ablation unevenness of the end portion of the expansion portion 33a during the ablation of the memory casing, as a further improvement of the embodiment, the memory casing surface is provided. Lateral scratches and/or transverse fibrous material are provided within the memory shell material. In this way, the memory casing can be ablated more evenly.

Further, as a further improvement of the embodiment, the center of the solid fuel 1a is provided with a rod member or a tubular member 22a. Since the cross-sectional area of the throat 32a is small, and the rod or tubular member 22a occupies a large cross-sectional area of the throat 32a, the ventilation area passing through the throat 32a can be reduced, so that the throat is passed through the throat. The air flow of the tube 32a is faster. In this way, the shrinking ability required to fabricate the memory material of the memory casing can be effectively reduced, thereby reducing the difficulty in manufacturing the memory casing.

In this embodiment, dynamically generating and burning the Laval nozzle structure has the following advantages:

1. The memory case made of memory material has lower requirements on the heat resistance of the memory material.

In this embodiment, the dynamic rocket propeller can dynamically generate a combustion chamber during flight. When the temperature in the combustion chamber is high and the pressure is high, the memory casing will be melted or vaporized by heat in a short time, at which time the Laval nozzle structure is generally short and the throat 32a is relatively thick and short. Conversely, when the temperature in the combustion chamber is low and the pressure is low, the Laval nozzle structure will be long overall and the throat 32a will be elongated. At the same time, the shape of the Laval nozzle structure also has an influence on the temperature in the combustion chamber 4a. The longer Laval nozzle structure and the elongated throat structure have a large gas discharge resistance, thereby contributing to an increase in the combustion chamber temperature. The short Laval nozzle structure and the short and short throat structure have low gas discharge resistance, which is beneficial to lower the combustion chamber temperature, and the low combustion chamber temperature is beneficial to protect the Laval nozzle structure, thereby reducing the memory shell forming the Laval nozzle structure. Heat resistance requirements.

2. The dynamically generated Laval nozzle structure has an opening size of the throat 32a, which is favorable for improving the kinetic energy conversion rate.

In this embodiment, the entire Laval nozzle structure is dynamically generated. The outside air pressure is an important factor affecting the size of the opening of the nozzle structure 3a. When the rocket is flying at a low altitude, the opening of the nozzle structure 3a will be made smaller due to the large outside air pressure, which will cause the nozzle structure 3a to eject a gas having a higher pressure. When the rocket is flying at a high altitude, the outside air pressure is small, the nozzle structure 3a is subjected to a small outside air pressure, and its opening is large, so that the nozzle structure 3a will eject a gas having a lower pressure. It can be seen that the opening size of the nozzle structure 3a on the dynamically generated Laval nozzle structure in the embodiment can automatically adjust the output state of the kinetic energy according to the external air pressure, which is beneficial to improving the conversion rate of the kinetic energy.

3. The gasification of the memory shell generates kinetic energy and improves the kinetic energy conversion rate of the combustion medium.

When the outer casing is ablated, part or all of it is vaporized, and gas is ejected from the tail of the arrow to generate kinetic energy. This part of the kinetic energy is actually the conversion of the rocket's exhaust heat, which is equivalent to improving the rocket kinetic energy conversion rate.

4. The structure of the entire rocket propeller is simple, low in cost, safe and reliable.

Since each part of the dynamic rocket thruster of the present embodiment undertakes a plurality of functions as much as possible, the structure thereof becomes simple, and the simple structure is advantageous in reducing the manufacturing cost, and the manufacturing error between the respective parts affects the probability of the entire performance. Decline, which increases its security.

5, the rocket shakes small

Rocket vibration mainly comes from the unstable combustion of fuel in the combustion chamber. Excessive vibration easily affects the safety of the rocket and the safety of people or objects that affect the transportation. In this embodiment, during the flight of the rocket, since the memory casing is in a high temperature state, the Laval nozzle structure formed is in a soft state or a highly elastic rubber state, which can effectively buffer the vibration. In addition, some solid fuels are themselves rubbery, highly elastic materials, which themselves have the ability to cushion vibration.

6, generate a large nozzle to improve the rocket kinetic energy conversion rate

Due to the weight of the nozzle and the manufacturing process, the existing rocket cannot produce a nozzle with a large size, so that the conversion rate of the kinetic energy of the rocket is not high. With the dynamic rocket propeller provided in this embodiment, the rocket nozzle can be generated by the outer casing 21a, and a larger volume nozzle can be generated, which is beneficial for converting more exhaust heat energy into kinetic energy.

Embodiment 2

Referring to FIG. 2, the embodiment is different from the first embodiment in that the control elements are arranged in different manners. In the present embodiment, the control element 2b includes a casing 21b encasing the solid fuel and when the solid fuel 1b is burned, the lower end edge thereof may be consumed along with the combustion dynamic combustion of the solid fuel, and further includes A tubular member 22b in the body of the arrow and made of a memory material, the tubular member 22b memorizing a cross-sectional area greater than the cross-sectional area of the tubular member 22b. When the solid fuel 1b on the arrow body is burned, the tubular member 22b will gradually return to the original memory section as the combustion surface 4b is moved, and the lower portion thereof will form an expanded state of a larger sectional area. Thus, the tubular member 22b will form a Laval nozzle structure with the outer casing 21b.

It should be noted that in the present embodiment, the outer casing 21b may also be made of a memory material to facilitate the formation of the Laval nozzle structure. Of course, in the present embodiment, similar to the memory case described in the first embodiment, the tubular member 22b is provided with a lateral scratch on the surface and/or a material of a transverse fiber material is disposed inside the material. In this way, the tubular member 22b can be ablated more uniformly.

Embodiment 3

Referring to FIG. 3, the embodiment is different from the first embodiment or the second embodiment in that the control elements are arranged in different manners. In the present embodiment, the control element 2c includes a casing 21c that encloses the solid fuel and that consumes the lower end edge of the solid fuel 1c as it burns, and further includes a nozzle generating member 22c below the solid fuel 1c inside the arrow; a first passage 221c and/or the nozzle of the nozzle forming member 22c extending from top to bottom through at least one shape such as a Laval nozzle The outer wall of the generating member 22c and the inner wall of the outer casing 21c together form a second passage 222c shaped like a Laval nozzle. Thus, during the flight of the rocket, the gas generated during the combustion of the solid fuel 1c can be ejected through the first passage 221c and/or the second passage 222c shaped as a Laval nozzle.

As a further improvement of the embodiment, the dynamic rocket thruster is internally provided with a traction climbing mechanism 23c that connects the nozzle generating member 22c. As the solid fuel 1c is consumed, the combustion surface 4c is moved upward, and the traction climbing mechanism 23c pulls the nozzle generating member 22c upward, thereby ensuring that the Laval nozzle structure is always at the bottom end of the arrow.

Further, a cooling device is disposed in the nozzle generating member 22c, and a surface of the nozzle generating member 22c is provided with a coolant outlet connected to the cooling device.

The working principle of this embodiment is described below:

During the flight of the rocket, when the gas generated by the combustion on the combustion surface 4c passes through the nozzle generating member 2c, the velocity of the gas will rise sharply and exceed the speed of sound because the area through which the gas passes is small. The gas exceeding the speed of sound continues to accelerate toward the portion of the outer end of the outer casing 21c which is expanded to generate thrust. As the solid fuel on the solid fuel 1c is consumed, the combustion surface 4c moves upward, and the traction climbing mechanism 23c pulls the nozzle generating member 22c upward. At the same time, the lower end of the outer casing 21c is also gradually consumed by the exhaust ablation. In addition, the cooling liquid of the cooling device may be stored in the nozzle generating member 22c or conveyed from the front portion of the rocket through a conveying pipe. Wherein, the gas generated by the evaporation of the cooling liquid by the heat may be discharged from the outlet of the cooling material, and may also provide part of the power of the rocket flight.

In addition, it should be noted that in the embodiment, the control method of the electrode and the cooling channel described in the first embodiment may be provided on the solid fuel 1c; and the design method described in the first embodiment may also be used. A lateral scratch is provided on the outer casing and/or a transverse fiber material is disposed inside the outer casing material, which is not described herein.

In addition, in the embodiment, the outer casing 21c may also be made of a memory material, and the inner diameter of the memory material is greater than the outer diameter of the solid fuel 1c. Thus, during the flight of the rocket, as the combustion surface 4c moves, the lower end of the outer casing 21c will automatically expand, thereby forming a diverging pipe section that facilitates the formation of the spout.

The above is only the preferred embodiment of the present invention, and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection of the present invention. Within the scope.

Claims

a dynamic rocket propeller comprising an arrow body filled with solid fuel and having a control element on the arrow body that dynamically generates a Laval nozzle structure suitable for rocket flight when the solid fuel is burned with the solid fuel The control element includes an outer casing encasing the solid fuel and having a lower edge rim that can be consumed in conjunction with combustion dynamic combustion of the solid fuel when the solid fuel is combusted.
A dynamic rocket propeller according to claim 1, wherein said body is provided with a plurality of electrodes and a discharge control system for controlling the discharge state of said electrodes and/or at least one cooling passage for injecting a coolant.
A dynamic rocket propeller according to claim 1 or 2, wherein said outer casing is a memory casing made of a shape memory material, said memory casing having a memory cross-sectional area smaller than a cross-sectional area of said arrow body. .
The dynamic rocket propeller according to claim 3, wherein the surface of the memory casing is provided with lateral scratches and/or the interior of the memory casing material is provided with a transverse fiber material.
A dynamic rocket propeller according to claim 1 or 2, wherein said control member further comprises a tubular member disposed in said body and made of a memory material, said tubular member having a memory cross-sectional area greater than The cross-sectional area of the tubular member.
A dynamic rocket propeller according to claim 5 wherein the tubular member surface is provided with lateral scratches and/or the material therein is provided with a transverse fibrous material.
The dynamic rocket propeller according to claim 1, wherein said control element further comprises a nozzle generating member disposed below said solid fuel inside said arrow; said nozzle generating member from top to bottom A first passage therethrough having at least one shape such as a Laval nozzle and/or an outer wall of the nozzle generating member together with an inner wall of the outer casing form a second passage shaped like a Laval nozzle.
The dynamic rocket thruster according to claim 7, wherein said dynamic rocket thruster is internally provided with a traction climbing mechanism that connects said nozzle generating member.
The dynamic rocket thruster according to claim 7, wherein a cooling device is disposed in the nozzle generating member, and a surface of the nozzle generating member is provided with a coolant outlet connected to the cooling device.