CN113911399A

CN113911399A - Spacecraft propeller

Info

Publication number: CN113911399A
Application number: CN202111345083.4A
Authority: CN
Inventors: 谢周安
Original assignee: Xie Zhouan
Current assignee: Xie Zhouan
Priority date: 2021-11-15
Filing date: 2021-11-15
Publication date: 2022-01-11

Abstract

The invention provides a spacecraft thruster, and relates to the technical field of aerospace propulsion. The embodiment of the application provides a spacecraft propeller, which comprises a spacecraft shell, wherein a pushing assembly for driving the spacecraft shell to move is arranged in the spacecraft shell. This technical scheme utilizes the vacuum machine to take out vacuum chamber's air, pulls the rubber slab, is provided with on the rubber slab and deposits the air chamber, and the air storage in the extraction drum is in depositing the air chamber, can install the circular shape positive magnet of ring additional on the lateral wall of rubber slab, and the above-mentioned negative magnet is fixed, and after taking out the air, the rubber slab pulling positive magnet is pushed to negative magnet and is produced thrust. Compared with the aircraft such as rocket based on propellant, the aircraft has the advantages of no need of propellant or intermediate substance for transferring momentum, easy realization of high speed and high load ratio, and the like. These advantages make the spacecraft of the invention have a wide potential application prospect in the field of aerospace, in particular in deep space exploration and interstellar travel.

Description

Spacecraft propeller

Technical Field

The invention relates to the technical field of aerospace propulsion, in particular to a spacecraft propeller.

Background

The second world war has resulted in significant advances in the propulsion technology of traditional aircraft, such as propellant-based rockets. However, the limitations of vehicles using propellant propulsion technology are becoming more and more evident, mainly expressed as: (1) it requires the use of large quantities of propellant; (2) its speed is limited; (3) its load is relatively low. The existing propellant propelling technology cannot meet the requirements of deep space exploration and interstellar navigation. In recent decades, propellant propulsion technology has been constantly improved: from chemical propellants to non-chemical propellants, from generating thrust by heating a working fluid with electricity to using solar sails and laser propulsion, etc. Although the use of solar sails and laser propulsion is a new class of propulsion technology, it is essentially a propellant propulsion mode because it uses the action-reaction forces of the intermediate mass, light, on the sails. Although these technological improvements have greatly advanced the aerospace industry, they have not fundamentally changed the dilemma of deep space exploration and interplanetary navigation. As many scholars indicate that "space flights envisaged by von blaueran early in the 50 th century will not be able to use this concept (propellant propulsion)", and these limitations can only be overcome if new propulsion technologies are found. In recent decades, outside the field of propellant propulsion technology, another new type of propulsion has begun to be explored: "Non-propellant Propulsion" or "break through Propulsion Physics". The term "break through physics" was derived from a project in NASA (1996 + 2002) (https:// doi. org/10.1016/j. actaastro.2017.05.028) which examined the leading edge concepts of non-rocket space-driven, gravity-controlled, hyper-speed travel, curvature engines and wormholes. The essence of this new propulsion is that no propellant or intermediate substance (or other medium with which momentum is transferred) is required. This means that the basic principle of such propulsion no longer follows the principle of conservation of momentum. Therefore, the novel propulsion mode is a great breakthrough of space propulsion technology if being realized. In addition, there are some experimental studies in this field. In 2007, two scientific and technological development companies, Yong-Kang Sun and Rolando Castillejagg, USA, funded by the NASA project, reported their experiments (https:// doi. org/10.2514/6.2007-6147). They designed a propellant-free propulsion device based on the principle of charge repulsion, but there were no experimental results; in 2006, the American air force institute conducted experiments on an European application patent (patent No. 91310395.8) filed in 1991 by Yama Shito (Haruo Yamashita) (https:// doi.org/10.2514/6.2006-4912). This patent designs a device that uses electrical attraction for (propellant-free propulsion) actuation. As a result of the experiment, they failed to see the desired result of the jamashito and concluded that: experiment "one cannot believe that electric attraction has practical significance"; in 2017 NASA has conducted experiments on so-called "EM drive" (EM drive) (https:// doi. org/10.2514/1.B36120). the working principle of EM is actually a part of the energy generated in a conical metal enclosed cavity by electromagnetic waves. The experiment was performed in a ground-based apparatus under vacuum. The experimental result shows that the thrust power ratio of the system is 1.2 +/-0.1 mN/kW. This result is difficult to make practical. The above experiments are mainly based on electrical and/or magnetic principles.

The invention relates to a propellant-free propulsion spacecraft, which is not based on electrical and/or magnetic principles, but on the inertial force theory of classical mechanics, the results of which can be explained by the inertial relativity theory based on the Mach principle. The structure, space propulsion principle and propulsion mode of the spacecraft of the invention are completely different from the traditional spacecraft such as rocket.

Disclosure of Invention

The invention aims to provide a spacecraft propeller, aiming at the limitation of propellant propelling technology and the dilemma of the research of the propellant-free propelling technology based on the electric and/or magnetic principle, and the technical problem to be solved by the invention is to provide a spacecraft which is propelled without propellant and is driven by a rotating motor.

The embodiment of the invention is realized by the following steps:

the embodiment of the application provides a spacecraft propeller, which comprises a spacecraft shell, wherein a pushing assembly for driving the spacecraft shell to move is arranged in the spacecraft shell.

In some embodiments of the present invention, the pushing assembly includes a barrel and a vacuum machine, the inner wall of the barrel is provided with a sealing part connected thereto, the sidewall of the barrel is provided with an airtight barrel, the air exhaust end of the vacuum machine is communicated with the barrel, the air outlet end of the vacuum machine is connected with the airtight barrel, one side of the sealing part away from the airtight barrel is provided with a first magnetic pole in an annular shape, and the barrel is slidably provided with a second magnetic pole repelling the first magnetic pole.

In some embodiments of the present invention, the number of the pushing assemblies is plural, and the plural pushing assemblies are disposed around the aircraft casing.

In some embodiments of the invention, the suction end of the vacuum machine is provided with a suction valve.

In some embodiments of the present invention, the pushing assembly further includes a housing and an oil pump, the housing is slidably provided with a rubber block adapted thereto, the rubber block is provided with a third magnetic pole, and the housing is slidably provided with a fourth magnetic pole repelling the third magnetic pole.

In some embodiments of the present invention, an emulsion sheet is disposed on an outer wall of the fourth magnetic pole, and a plurality of vent holes are disposed on a sidewall of the emulsion sheet.

In some embodiments of the present invention, the pushing assembly further includes a propeller, a protective casing for wrapping the propeller is disposed in the aircraft casing, a driving motor drivingly connected to the propeller is disposed in the protective casing, air blowing equipment is disposed in the protective casing, an output pipe communicated with an output end of the air blowing equipment is disposed in the protective casing, and a free end of the output pipe is disposed on an upper portion of the propeller.

Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:

the embodiment of the application provides a spacecraft propeller, which comprises a spacecraft shell, wherein a pushing assembly for driving the spacecraft shell to move is arranged in the spacecraft shell. The technical scheme is a wind power pushing method; preparing a vacuum-pumping machine, a closed round barrel, wherein the bottom of the round barrel is attached with a layer of elastic rubber plate, holes are arranged on the round barrel to pump air, and the rubber plate is stressed to pull up the iron barrel. And the closed barrel is internally provided with a cathode magnet and an anode magnet. If the strength is enhanced, a plurality of vacuum chambers can be additionally arranged or the vacuum chambers are additionally provided with magnets with the positive pole and the negative pole, and the larger the repulsive force of the magnetic poles is, the stronger the propelling speed is; the vacuum machine is used for pumping away air in the vacuum chamber, the rubber plate is pulled up, the rubber plate is provided with the air storage chamber, air in the extraction cylinder is stored in the air storage chamber, the side wall of the rubber plate can be additionally provided with a circular male magnet, the upper female magnet is fixed, and after the air is pumped away, the rubber plate pulls the male magnet to push the female magnet to generate thrust.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic perspective view of the present invention;

FIG. 2 is a schematic view of a first deformation of the pushing assembly of the present invention;

FIG. 3 is a schematic view of a second deformation assembly of the pushing assembly of the present invention;

fig. 4 is a combined schematic view of a third deformation of the pushing assembly of the present invention.

Icon: 1. a barrel body; 2. a vacuum machine; 3. a sealing part; 4. a second magnetic pole; 5. a first magnetic pole; 6. an oil well pump; 7. a housing; 8. a latex sheet; 9. a fourth magnetic pole; 10. a third magnetic pole; 11. a rubber block; 12. a propeller; 13. an output pipe; 14. a blower device; 15. a drive motor; 16. a protective shell.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the embodiments of the present invention, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention are usually placed in when used, the orientations or positional relationships are only used for convenience of describing the present invention and simplifying the description, but the terms do not indicate or imply that the devices or elements indicated must have specific orientations, be constructed in specific orientations, and operate, and therefore, should not be construed as limiting the present invention.

Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not require that the components be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present invention, "a plurality" represents at least 2.

In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

Examples

Referring to fig. 1-4, fig. 1 is a schematic perspective view of the present invention;

The embodiment of the application provides a spacecraft propeller, which comprises a spacecraft shell, wherein a pushing assembly for driving the spacecraft shell to move is arranged in the spacecraft shell. The technical scheme is a wind power pushing method; a vacuum-pumping machine 2 and a closed barrel are prepared, wherein the bottom of the closed barrel is attached with a layer of elastic rubber plate, holes are formed in the barrel to pump air, and the rubber plate is stressed to pull up the iron barrel. And the closed barrel is internally provided with a cathode magnet and an anode magnet. If the strength is enhanced, a plurality of vacuum chambers can be additionally arranged or the vacuum chambers are additionally provided with magnets with the positive pole and the negative pole, and the larger the repulsive force of the magnetic poles is, the stronger the propelling speed is; the vacuum machine 2 is used for pumping away air in the vacuum chamber, the rubber plate is pulled up, an air storage chamber is arranged on the rubber plate, air in the extraction cylinder is stored in the air storage chamber, a circular male magnet can be additionally arranged on the side wall of the rubber plate, the upper female magnet is fixed, and after the air is pumped away, the rubber plate pulls the male magnet to push the female magnet to generate thrust.

Further, the first magnetic pole 5 is a positive magnetic pole, and the second magnetic pole 4 is a negative magnetic pole.

In some embodiments of the present invention, the pushing assembly includes a barrel 1 and a vacuum machine 2, an inner wall of the barrel 1 is provided with a sealing portion 3 connected thereto, an airtight barrel is provided on a side wall of the barrel 1, an air exhaust end of the vacuum machine 2 is communicated with the barrel 1, an air outlet end of the vacuum machine 2 is connected with the airtight barrel, one side of the sealing portion 3 away from the airtight barrel is provided with a first magnetic pole 5 in an annular shape, and a second magnetic pole 4 which is repelled from the first magnetic pole 5 is slidably provided in the barrel 1.

In some embodiments of the invention, the suction end of the vacuum machine 2 is provided with a suction valve. The provision of the suction valve reduces air loss within the vacuum machine 2.

In some embodiments of the present invention, the pushing assembly further includes a housing 7 and an oil pump 6, a rubber block 11 adapted to the housing 7 is slidably disposed in the housing 7, a third magnetic pole 10 is disposed on the rubber block 11, and a fourth magnetic pole 9 opposing to the third magnetic pole 10 is slidably disposed in the housing 7.

Further, the third magnetic pole 10 is a positive magnetic pole, and the fourth magnetic pole 9 is a negative magnetic pole.

In some embodiments of the present invention, the outer wall of the fourth magnetic pole 9 is provided with a latex sheet 8 wrapping the fourth magnetic pole, and the sidewall of the latex sheet 8 is provided with a plurality of vent holes.

About conversion of energy from rotary machine

1. Expression: the energy increment is the amount of self-movement of energy, and the initial total energy is the amount of movement of final space material.

2. Understanding the law of energy rotation

(1) Some form of space is created without energy, such as a vacuum. There is no need for energy to also have energy movement, so the energy increase or decrease is not in direct energy conversion. The energy is embodied in the law of the self-motion of the matter formed by the space.

The conclusion is that the increase and decrease of energy-spatial formation and material motion morphology, the formation of energy varies in interaction with the various material self-motion and spatial interactions, and the conversion of energy varies depending on the various material self-motion and spatial interactions.

In some embodiments of the present invention, the pushing assembly further includes a propeller 12, a protective casing 16 is disposed in the aircraft casing and used for wrapping the propeller 12, a driving motor 15 in transmission connection with the propeller 12 is disposed in the protective casing 16, a blower device 14 is disposed in the protective casing 16, an output pipe 13 communicated with an output end of the blower device 14 is disposed in the protective casing 16, and a free end of the output pipe 13 is disposed on an upper portion of the propeller 12.

The latex sheet 8 is sealed by a little air against the steel sheet, the latex sheet 8 is pulled to rotate in one direction by utilizing the vacuum pressure, and the continuous movement of the self-rotating machine can be ensured by keeping the vacuum environment in the super-strong state. The air is arranged in the protective shell 16, the propeller 12 can realize space flight by sliding the air in the protective shell 16, an experimental result shows that an unmanned aerial vehicle is installed at the root of a sealed mushroom-shaped cover, a small blower is installed below the unmanned aerial vehicle and connected to the top through a small pipe to form an up-down pressure difference, and the electric propeller 12 realizes thrust by sliding the air.

Depending on whether the moveable material or the object generating motion is in space, the self-motion of the material of the space object may be defined as flying, such as a living being flying on earth, a jet, a helicopter, etc., to create an "environment" in which it is flying. The environment space of the object is formed in the space, and the movable body can fly and travel in the space. Because the earth is the largest space ship among mankind. The earth is wrapped by metal, and the space flight can be realized by installing a propeller. Space sailing conditions are the formation of the motion space required by an individual.

In summary, the embodiment of the present application provides a spacecraft thruster, which includes a spacecraft casing, and a thrust assembly is disposed in the spacecraft casing for driving the spacecraft casing to move. The technical scheme is a wind power pushing method; a vacuum-pumping machine 2 and a closed barrel are prepared, wherein the bottom of the closed barrel is attached with a layer of elastic rubber plate, holes are formed in the barrel to pump air, and the rubber plate is stressed to pull up the iron barrel. And the closed barrel is internally provided with a cathode magnet and an anode magnet. If the strength is enhanced, a plurality of vacuum chambers can be additionally arranged or the vacuum chambers are additionally provided with magnets with the positive pole and the negative pole, and the larger the repulsive force of the magnetic poles is, the stronger the propelling speed is; the vacuum machine 2 is used for pumping away air in the vacuum chamber, the rubber plate is pulled up, an air storage chamber is arranged on the rubber plate, air in the extraction cylinder is stored in the air storage chamber, a circular male magnet can be additionally arranged on the side wall of the rubber plate, the upper female magnet is fixed, and after the air is pumped away, the rubber plate pulls the male magnet to push the female magnet to generate thrust.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A spacecraft thruster is characterized by comprising a spacecraft shell, wherein a pushing assembly for driving the spacecraft shell to move is arranged in the spacecraft shell.

2. A spacecraft thruster according to claim 1, wherein the thruster assembly comprises a barrel and a vacuum machine, the inner wall of the barrel is provided with a seal connected thereto, the sidewall of the barrel is provided with an airtight barrel, the suction end of the vacuum machine is communicated with the barrel, the air outlet end of the vacuum machine is connected with the airtight barrel, one side of the seal facing away from the airtight barrel is provided with a first magnetic pole in an annular shape, and the barrel is slidably provided with a second magnetic pole which repels the first magnetic pole.

3. A spacecraft thruster according to claim 2, wherein said thrust assemblies are plural in number and are disposed circumferentially within said spacecraft envelope.

4. A spacecraft thruster according to claim 2, wherein the bleed end of the vacuum is provided with a bleed valve.

5. A spacecraft thruster according to claim 1, wherein said thrust assembly further comprises a housing and an oil pump, said housing having a rubber block fitted therein slidably, said rubber block having a third magnetic pole, said housing having a fourth magnetic pole slidably opposing said third magnetic pole.

6. A spacecraft thruster according to claim 5, wherein a latex sheet is provided on the outer wall of the fourth magnetic pole to wrap the fourth magnetic pole, and a plurality of vent holes are provided on the sidewall of the latex sheet.

7. A spacecraft thruster according to any one of claims 1 to 6, wherein the thrust unit further comprises a propeller, a protective casing is provided in the aircraft casing to enclose the propeller, a drive motor is provided in the protective casing and is in drive connection with the propeller, a blower unit is provided in the protective casing, an output pipe is provided in the protective casing and is in communication with an output end of the blower unit, and a free end of the output pipe is disposed at an upper portion of the propeller.