CN113022895A - Flywheel ablation space propeller and space debris cleaning platform - Google Patents
Flywheel ablation space propeller and space debris cleaning platform Download PDFInfo
- Publication number
- CN113022895A CN113022895A CN202110280109.5A CN202110280109A CN113022895A CN 113022895 A CN113022895 A CN 113022895A CN 202110280109 A CN202110280109 A CN 202110280109A CN 113022895 A CN113022895 A CN 113022895A
- Authority
- CN
- China
- Prior art keywords
- flywheel
- energy storage
- space
- ablation
- flywheels
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000002679 ablation Methods 0.000 title claims abstract description 44
- 238000004140 cleaning Methods 0.000 title abstract description 17
- 238000004146 energy storage Methods 0.000 claims abstract description 86
- 239000002245 particle Substances 0.000 claims description 17
- 230000008929 regeneration Effects 0.000 claims description 15
- 238000011069 regeneration method Methods 0.000 claims description 15
- 238000010891 electric arc Methods 0.000 claims description 13
- 238000010248 power generation Methods 0.000 claims description 12
- 238000005266 casting Methods 0.000 claims description 7
- 230000000452 restraining effect Effects 0.000 claims description 7
- 238000003723 Smelting Methods 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 3
- 230000008018 melting Effects 0.000 claims description 3
- 230000001172 regenerating effect Effects 0.000 claims description 3
- 239000000126 substance Substances 0.000 abstract description 28
- 238000002309 gasification Methods 0.000 abstract description 4
- 229910052751 metal Inorganic materials 0.000 abstract description 4
- 239000002184 metal Substances 0.000 abstract description 4
- 238000010892 electric spark Methods 0.000 abstract description 3
- 230000007774 longterm Effects 0.000 abstract description 2
- 239000010419 fine particle Substances 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 description 11
- 239000012634 fragment Substances 0.000 description 9
- 239000000843 powder Substances 0.000 description 6
- 239000003380 propellant Substances 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000000608 laser ablation Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 229910001234 light alloy Inorganic materials 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/409—Unconventional spacecraft propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G4/00—Tools specially adapted for use in space
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a flywheel ablation space propeller and a space debris cleaning platform, wherein space debris is used for manufacturing an energy storage flywheel, a high-speed motor is driven by solar energy to drive the energy storage flywheel to rotate at a high speed, so that the energy storage flywheel obtains kinetic energy, two energy storage flywheels which are arranged in a tangent mode are connected with a pulse power supply, electric spark arcs are generated at the tangent position, metal on the outer edge of the flywheel is melted and gasified due to the generated high temperature, flywheel substances are separated from the flywheel and are sprayed at a high speed under the inertia and gasification pressure, and therefore thrust is obtained. The invention converts space debris into propelling substances, generates thrust, simultaneously crushes flywheel substances by electric sparks to form fine particles, does not harm a spacecraft any more, and has the technical characteristics of simple and efficient crushing of the space debris, small total volume and weight, large thrust range, accurate and controllable thrust and long-term on-orbit work.
Description
Technical Field
The invention belongs to the technical field of space garbage cleaning, and particularly relates to a flywheel ablation space propeller and a space debris cleaning platform.
Background
Thousands of tons of space debris exist on the earth's near-earth orbit and the synchronous orbit, which threatens the safety of the space vehicle and cannot clean the space debris slowly. Space debris cleaning technology is listed in 2020 ten technical problems in the field of Chinese space navigation, and an efficient propelling device for cleaning space debris is urgently needed.
Most fragments are formed after the spacecraft is disintegrated, the most common materials of the spacecraft are adopted, such as light alloys of aluminum, magnesium, titanium and the like, and the fragments can be used as a novel propulsion working medium source. At present, the space debris is cleaned mainly by pushing debris into the atmosphere by a propelling device to burn or push the debris away from a working orbit, but a large amount of propellant is consumed, and some organizations research methods for producing metal powder by using space debris to generate propelling force at high speed so as to save the conventional propellant, but devices for producing powder and accelerating the powder are complex and have heavy weight. For example, the scheme that metal powder is prepared from space fragments and used as fragments of a bullet propelled by an electromagnetic gun is reused, the volume and the weight of an electromagnetic gun body and a required high-power supply are large, and for example, the scheme that the space fragment preparation powder is propelled by electrostatic acceleration jet is adopted, but the scheme that ultrafine powder is required for electrostatic acceleration, and the preparation difficulty is large.
Disclosure of Invention
The invention provides a flywheel ablation space thruster and a space debris cleaning platform for solving the technical problems.
In order to solve the problems, the technical scheme of the invention is as follows:
a flywheel ablative space thruster, comprising: a high-speed flywheel set, a pulse power supply and a gap adjusting device;
the high-speed flywheel set at least comprises a pair of energy storage flywheels and a flywheel motor for driving the energy storage flywheels to rotate at a high speed, wherein the same pair of energy storage flywheels rotate oppositely and a discharge gap is arranged between the outlines;
the positive pole of the pulse power supply is electrically connected with one energy storage flywheel in the same pair of energy storage flywheels, and the negative pole of the pulse power supply is electrically connected with the other energy storage flywheel in the same pair of energy storage flywheels, and is used for performing pulse arc discharge ablation in a discharge gap between the energy storage flywheels so as to ablate and generate particles required for propulsion;
the gap adjusting device is used for adjusting the discharge gap in real time according to the loss of the energy storage flywheel so as to maintain the gap size required by the pulse arc discharge ablation.
According to an embodiment of the present invention, the gap adjusting device includes a fixed base, a movable base, and an adjusting motor, wherein the fixed base is rotatably or slidably connected to the movable base, one of the energy storage flywheels and the corresponding motor are mounted on the fixed base, the other of the energy storage flywheels and the corresponding motor is mounted on the movable base, and the adjusting motor is used for adjusting a relative position between the fixed base and the movable base to adjust the discharge gap.
According to an embodiment of the invention, the gap adjusting device comprises a guide rail sliding table and an adjusting motor, wherein different energy storage flywheels are arranged on different sliding tables of the guide rail sliding table in the same pair of energy storage flywheels, and the adjusting motor is used for adjusting the sliding table position of the guide rail sliding table so as to adjust the discharge gap.
According to an embodiment of the invention, the regulating motor is configured to adjust the discharge gap in real time according to a discharge current between the energy storage flywheels.
According to an embodiment of the invention, a restraining magnetic field is further arranged along the direction of the particle jet generated by ablation and used for restraining the jet divergence angle of the particle jet.
According to one embodiment of the invention, grooves are formed in the wheel surface of the energy storage flywheel along the circumferential direction, and in the same pair of energy storage flywheels, the grooves between the two energy storage flywheels are intersected in a staggered mode to form a plurality of divergent nozzles which are used for restraining particles generated by directional jet ablation.
A space debris clearing platform comprising: a solar power generation device, a space debris catching device, a flywheel regeneration device, and a flywheel ablation space thruster as described in any of the above embodiments;
the solar power generation device is used for collecting solar energy to provide electric energy for a high-speed flywheel set and a pulse power supply of the flywheel ablation space thruster, wherein an energy storage flywheel in the high-speed flywheel set is also used for storing energy and providing a power supply for the flywheel regeneration device;
the space debris catching device is used for executing space debris catching operation, flywheel replacing operation and flywheel regenerating operation;
the flywheel regeneration device is used for smelting space debris to cast the energy storage flywheel.
According to one embodiment of the present invention, the space debris catching device is a soft robot.
According to one embodiment of the invention, the flywheel regeneration device comprises an electric arc melting chamber and a casting mold.
Compared with the prior art, the invention has the following advantages and positive effects:
the invention forms pulse arc discharge ablation between energy storage flywheels through a pulse power supply to generate particles required by propulsion, and rotates the energy storage flywheels at high speed, and the particles generated under centrifugal force and gasification pressure can be sprayed at high speed to obtain reaction thrust, wherein, the propulsion substance can be obtained in a space track, space fragments can be utilized to be smelted through vacuum arc, the flywheels are cast, the electric energy used for smelting is provided by the energy storage flywheels, the flywheels can be replaced through a manipulator, the energy can be generated by a solar photovoltaic power generation board, the energy storage flywheels are both the propulsion substance and the energy storage substance, the flywheels are taken as the propulsion substance without special storage containers, the total weight of the model is small, the flywheels can not be subjected to air resistance in the vacuum environment in space, the flywheel energy storage is favorably realized for a long time, the conversion efficiency of the electric energy generated by the photovoltaic board, the efficiency of conversion from chemical energy to kinetic energy of the chemical energy propellant is much higher, and in addition, the spark discharge frequency per second can be controlled by adjusting the power supply pulse, and the thrust is adjusted, so that the invention has the advantages of simple structure, small total weight, large thrust range, accurate and controllable thrust, can work on the orbit for a long time, and can be used for space exploration and space debris cleaning.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention.
FIG. 1 is a schematic view of the overall structure of a flywheel ablation space thruster of the present invention;
FIG. 2 is a schematic diagram of a high-speed flywheel set structure of a flywheel ablation space thruster of the present invention;
FIG. 3 is a schematic cross-sectional view of a high-speed flywheel set of a flywheel ablative space thruster of the present invention;
FIG. 4 is a schematic diagram of the energy-storing flywheel wheel surface structure of the flywheel ablation space thruster of the present invention;
FIG. 5 is a schematic overall structure diagram of a space debris cleaning platform according to the invention.
Description of reference numerals:
11-an energy storage flywheel; 12-a flywheel motor; 21-fixing a base; 22-a movable base; 3-a solar power generation device; 4-space debris catching device; 5-flywheel regeneration device.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.
For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "one" means not only "only one" but also a case of "more than one".
The following will explain the flywheel ablation space thruster and the space debris cleaning platform in detail in conjunction with the attached drawings and the specific embodiments.
Referring to fig. 1, the present application provides a flywheel ablative space thruster, comprising: a high-speed flywheel set, a pulse power supply and a gap adjusting device;
the high-speed flywheel set at least comprises a pair of energy storage flywheels 11 and a flywheel motor 12 for driving the energy storage flywheels to rotate at a high speed, wherein the same pair of energy storage flywheels 11 rotate oppositely and a discharge gap is arranged between the outlines;
the positive pole of the pulse power supply is electrically connected with one energy storage flywheel 11 in the same pair of energy storage flywheels 11, and the negative pole of the pulse power supply is electrically connected with the other energy storage flywheel 11 in the same pair of energy storage flywheels 11, so that pulse arc discharge ablation is carried out on a discharge gap between the energy storage flywheels to ablate and generate particles required for propulsion;
the gap adjusting device is used for adjusting the discharge gap in real time according to the loss of the energy storage flywheel 11 so as to maintain the gap size required by the pulse arc discharge ablation.
The present embodiment will now be described in detail, but is not limited thereto.
In the embodiment, space fragments are cast into the flywheel, the solar drive motor accelerates the flywheel, the flywheel rim obtains high linear speed which can exceed 1 kilometer per second, electric sparks ablate flywheel rim substances, and the ablated flywheel substances are crushed and sprayed at high speed to obtain thrust for space propulsion.
Referring to fig. 2 and 3, in the high-speed flywheel set of this embodiment, at least one pair of energy storage flywheels and a flywheel motor for driving the energy storage flywheels to rotate at a high speed are provided, wherein, in this embodiment, two flywheels are oppositely arranged by using an energy storage flywheel structure, spark discharge is ignited in the tangential direction of the flywheels, flywheel substances are ablated, and the ablated substances fly off in the tangential direction due to being separated from the constraint of the flywheel body, and are accelerated by the gasification pressure of the electric arc, thereby generating a recoil thrust.
In an implementation manner of this embodiment, the energy storage flywheel includes two types, namely, a working medium flywheel and an electrode flywheel, where the working medium flywheel and the electrode flywheel are arranged in pairs and tangent to each other and a discharge gap is reserved, the discharge gap between the electrode flywheel and the working medium flywheel is arc-discharged, the outer edge of the working medium flywheel is flown away by arc ablation to obtain thrust, and the electrode flywheel is not consumed or is consumed very little. In another implementation manner of this embodiment, working medium flywheels can be used for both flywheels, and thrust is obtained through arc ablation and flying.
Referring to fig. 4, it is further preferable that grooves are formed in the wheel surface of the energy storage flywheel 11 in the embodiment along the circumferential direction, in the same pair of energy storage flywheels 11, the grooves between the two energy storage flywheels 11 intersect in a staggered manner to form a plurality of divergent nozzles 111, a discharge gap is left at the intersection of the staggered portions, and particles generated by ablation are constrained by the divergent nozzles to be directionally ejected, so that a high ejection speed can be obtained. In addition, further preferably, a restraining magnetic field is further arranged in the particle jet direction generated by ablation, the divergence angle of jet flow is restrained, and the propelling efficiency is improved.
The pulse power supply of the embodiment provides a direct-current voltage which is switched on and off at intervals, a flywheel gap is broken down in a short time (nanosecond level), flywheel substances are gasified and ablated under high-current impact, the switching time and the frequency of the pulse power supply can be adjusted, the discharge frequency per second can be controlled by controlling the frequency of the pulse power supply, the ablation amount can be conveniently controlled by controlling the discharge frequency, and the thrust can be controlled by controlling the ablation amount.
Referring to fig. 1, in an implementation manner of this embodiment, the gap adjustment apparatus of this embodiment may include a fixed base 21, a movable base 22, and an adjustment motor, where the fixed base 21 is rotatably or slidably connected with the movable base 22, where, in the same pair of energy storage flywheels 11, one energy storage flywheel 11 and a corresponding motor are installed on the fixed base 21, the other energy storage flywheel 11 and a corresponding motor are installed on the movable base 22, and the adjustment motor is used to adjust a relative position between the fixed base 21 and the movable base 22 to adjust a discharge gap.
In another implementation manner of this embodiment, the gap adjustment apparatus of this embodiment may further include a guide rail sliding table and an adjustment motor, where in the same pair of energy storage flywheels, different energy storage flywheels are installed on different sliding tables of the guide rail sliding table, and the adjustment motor is used to adjust the sliding table position of the guide rail sliding table to adjust the discharge gap.
Specifically, the adjusting motor of the embodiment can detect the loss condition of the energy storage flywheel according to the discharge current between the energy storage flywheels, and adjust the discharge gap in real time to maintain the gap size required by the pulse arc discharge ablation.
To further illustrate the feasibility of the present embodiment, the present embodiment is schematically verified by using the structure shown in fig. 1, but is not limited thereto.
Referring to fig. 1, in the embodiment, a 775 type direct current motor is used as a flywheel motor 12, a flywheel clamp is arranged on an output shaft of the motor and used for installing and fixing an energy storage flywheel 11, the energy storage flywheel 11 is made of metal materials of space debris, a pulse power supply adopts an xks-350 type spark machine power supply, one motor flywheel is fixedly installed on a fixed base 21, the other motor is installed on a movable base 22, the gap of the flywheel is controlled and adjusted through the movable base 22, an assembled finished product is suspended into a single pendulum, and thrust is measured through the swing amplitude. Specifically, referring to the table below, a positive correlation of thrust to rotational speed indicates that the higher the linear velocity of the rim material, the greater the momentum, the greater the average thrust obtained, and that thrust is proportional to current, indicating that the faster the ablation rate, the greater the momentum obtained, the greater the average thrust. Data analysis shows that thrust can be rapidly improved by increasing the rotating speed of the flywheel, and the experiment is not carried out in a vacuum environment, if the rotating speed of the flywheel is further increased by adopting a magnetic suspension motor in a space vacuum environment, a high-power pulse power supply can be used for obtaining high thrust so as to be used for propelling and orbital transfer of a spacecraft.
Simple pendulum experiment test record
The embodiment forms pulse arc discharge ablation between the energy storage flywheels through the pulse power supply to generate particles required by propulsion, and rotates the energy storage flywheels at high speed, the particles generated under centrifugal force and gasification pressure can be sprayed at high speed to obtain reaction thrust, wherein the propulsion substance can be obtained in the space track, space fragments can be utilized to be smelted through vacuum arc, the flywheels are cast, electric energy used for smelting is provided by the energy storage flywheels, the flywheels can be replaced through manipulators, energy can be generated by the solar photovoltaic power generation board, the energy storage flywheels are both the propulsion substance and the energy storage substance, the flywheels are used as the propulsion substance without special storage containers, the total weight of the model is small, the flywheels can not be subjected to air resistance in the vacuum environment in space, the flywheel can be used for storing energy for a long time, the conversion efficiency of the electric energy generated by the photovoltaic boards into the, the efficiency of conversion of chemical energy to kinetic energy is far higher than that of a chemical energy propellant, in addition, the spark discharge frequency per second can be controlled by adjusting the power supply pulse, and the thrust is adjusted, so that the device has the advantages of simple structure, small total weight, large thrust range, accurate and controllable thrust, can work on orbit for a long time, and can be used for space exploration and space debris cleaning.
Referring to fig. 5, the present application further provides a space debris cleaning platform based on the above embodiment, including: a solar power generation device 3, a space debris catching device 4, a flywheel regeneration device 5 and a flywheel ablation space thruster as described in any of the above embodiments;
the solar power generation device 3 is used for collecting solar energy to provide electric energy for a high-speed flywheel set and a pulse power supply of the flywheel ablation space propeller, wherein an energy storage flywheel in the high-speed flywheel set is also used for storing energy and providing a power supply for a flywheel regeneration device;
the space debris catching device 4 is used for executing space debris catching operation, flywheel replacing operation and flywheel regenerating operation;
the flywheel regeneration device 5 is used for smelting space debris to cast an energy storage flywheel.
The present embodiment will now be described in detail, but is not limited thereto.
The solar power generation device of the embodiment has no atmosphere in the outer space, has stronger sunlight compared with the ground, collects solar energy by the photovoltaic power generation panel, provides electric energy for the flywheel motor and the pulse power supply, stores energy by the energy storage flywheel, and can provide a high-power supply for the flywheel regeneration device.
The space debris catching device is a soft mechanical arm and is arranged on a platform, and tasks such as flywheel replacement, flywheel regeneration operation and space debris catching are completed through the mechanical arm. However, due to the special environment of the outer space, damage and secondary pollution are generated when the mechanical arm is directly used for capturing, so the embodiment adopts a soft mechanical arm.
The flywheel regeneration device comprises an electric arc melting chamber and a casting mold, so that space fragments are used for casting the flywheel, vacuum obtaining equipment and a sealing device can be omitted in the vacuum environment of the outer space, a required high-power supply can be provided by an energy storage flywheel, melted metal liquid is made into the flywheel through the casting mold, and the flywheel abraded to a certain degree can be used for re-casting.
The propulsion substance can be obtained in the space track, the energy is generated by the solar photovoltaic power generation board, the high-speed flywheel is both the propulsion substance and the energy storage substance, the flywheel is used as the propulsion substance, a special storage container is not needed, the total weight of the model is small, the flywheel is free from air resistance in the vacuum environment in the space, the long-term energy storage of the flywheel is facilitated, the conversion efficiency of converting the electric energy generated by the photovoltaic board into the kinetic energy of the high-speed flywheel can be higher than ninety percent, and the conversion efficiency is far higher than the conversion efficiency of converting the chemical energy of a chemical energy propellant into. The flywheel of the device adopts pulse spark ablation, electric energy is directly converted into heat energy, and compared with laser ablation (the electric energy is converted into the light energy and then into the heat energy), the flywheel of the device is propelled, so that the conversion from the electric energy to the laser light energy is avoided, and the conversion efficiency from the electric energy to the heat energy is greatly improved. The propulsion scheme has a simple structure, parts are widely applied in other fields, the technical maturity of the spark ablation process is high, propulsion energy and propulsion substances can be obtained in outer space, the thrust range is wide, the thrust can be accurately controlled, and the propulsion scheme is expected to be used for space exploration and space debris cleaning.
The flywheel ablation propulsion device has the advantages of simple model structure, small total weight, large thrust range, accurate and controllable thrust and is expected to be used for space propulsion, and all the components of the concept design scheme of the space debris cleaning device are mature processes and are expected to realize space debris resource utilization.
The present embodiment has at least the following advantages:
(1) the embodiment can generate thrust, the higher the rotating speed of the flywheel is, the larger the thrust is, the higher the power of the spark power supply is, the larger the thrust is, and the thrust can be controlled by controlling the power of the spark power supply;
(2) the flywheel substance is crushed while the thrust is generated, the crushing structure and the mode are simple and efficient, the energy efficiency of the electric arc spark ablation is higher than that of the laser ablation, and the spark ablation power supply is simple in structure and light in weight compared with that of the laser ablation;
(3) the energy storage flywheel can be used as an energy storage element to provide high-power-density electric energy for supplying power to the pulse power supply, obtain high ablation rate to generate large thrust, and simultaneously be used as an accelerator for particles and can spray the particles at high speed to generate large thrust;
(4) the space debris cleaning device can work on the orbit for a long time by using energy and material sources required by the space debris cleaning device and outer space.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.
Claims (9)
1. A flywheel ablative space thruster, comprising: a high-speed flywheel set, a pulse power supply and a gap adjusting device;
the high-speed flywheel set at least comprises a pair of energy storage flywheels and a flywheel motor for driving the energy storage flywheels to rotate at a high speed, wherein the same pair of energy storage flywheels rotate oppositely and a discharge gap is arranged between the outlines;
the positive pole of the pulse power supply is electrically connected with one energy storage flywheel in the same pair of energy storage flywheels, and the negative pole of the pulse power supply is electrically connected with the other energy storage flywheel in the same pair of energy storage flywheels, so that pulse arc discharge ablation is carried out on the discharge gap between the energy storage flywheels to ablate and generate particles required for propulsion;
the gap adjusting device is used for adjusting the discharge gap in real time according to the loss of the energy storage flywheel so as to maintain the gap size required by the pulse arc discharge ablation.
2. A flywheel ablation space thruster according to claim 1, wherein the gap adjusting device comprises a fixed base, a movable base and an adjusting motor, the fixed base and the movable base are rotatably or slidably connected, wherein one of the energy storage flywheels and the corresponding motor is mounted on the fixed base, the other energy storage flywheel and the corresponding motor are mounted on the movable base, and the adjusting motor is used for adjusting the relative position between the fixed base and the movable base so as to adjust the discharge gap.
3. A flywheel ablation space thruster according to claim 1, wherein the gap adjusting device comprises a guide rail sliding table and an adjusting motor, wherein different energy storage flywheels are mounted on different sliding tables of the guide rail sliding table in the same pair of energy storage flywheels, and the adjusting motor is used for adjusting the sliding table position of the guide rail sliding table so as to adjust the discharge gap.
4. A flywheel ablative space thruster as in claim 2 or 3 wherein the adjustment motor is adapted to adjust the discharge gap in real time in accordance with the discharge current between the energy storing flywheels.
5. The flywheel ablation space thruster according to any one of claims 1 to 3, wherein a restraining magnetic field is further arranged along the jet direction of the particles generated by ablation for restraining the jet divergence angle of the particle jet.
6. The flywheel ablation space thruster according to any one of claims 1 to 3, wherein grooves are formed in the wheel surface of the energy storage flywheel along the circumferential direction, and in the same pair of energy storage flywheels, the grooves between the two energy storage flywheels intersect in a staggered mode to form a plurality of divergent nozzles which are used for restraining particles generated by directional jet ablation.
7. A space debris clearing platform, comprising: solar power generation means, space debris catching means, flywheel regeneration means, and the flywheel ablative space thruster of any one of claims 1 to 6;
the solar power generation device is used for collecting solar energy to provide electric energy for a high-speed flywheel set and a pulse power supply of the flywheel ablation space propeller, wherein the energy storage flywheel in the high-speed flywheel set is also used for storing energy and providing a power supply for the flywheel regeneration device;
the space debris catching device is used for performing space debris catching operation, flywheel replacing operation and flywheel regenerating operation;
the flywheel regeneration device is used for smelting space debris and casting the energy storage flywheel.
8. A space debris removal platform according to claim 7, wherein said space debris catching means is a soft robot.
9. A space debris removal platform according to claim 7, wherein said flywheel regeneration means comprises an arc melting chamber, a casting mold.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110280109.5A CN113022895B (en) | 2021-03-16 | 2021-03-16 | Flywheel ablation space propeller and space debris cleaning platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110280109.5A CN113022895B (en) | 2021-03-16 | 2021-03-16 | Flywheel ablation space propeller and space debris cleaning platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113022895A true CN113022895A (en) | 2021-06-25 |
| CN113022895B CN113022895B (en) | 2024-01-30 |
Family
ID=76470735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110280109.5A Active CN113022895B (en) | 2021-03-16 | 2021-03-16 | Flywheel ablation space propeller and space debris cleaning platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113022895B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB534220A (en) * | 1938-11-18 | 1941-03-03 | Nat Machinery Co | Improvements in or relating to heavy duty clutch and flywheel assemblies |
| CN102358436A (en) * | 2011-08-31 | 2012-02-22 | 中国航天科技集团公司第五研究院第五一三研究所 | Device for realizing spacecraft orbit keeping by utilizing space debris |
| CN104773307A (en) * | 2015-04-30 | 2015-07-15 | 中国科学院宁波材料技术与工程研究所 | Approximate-light-speed particle moving method and system |
| CN108026902A (en) * | 2015-09-15 | 2018-05-11 | 纽曼空间有限公司 | Inner wire trigger pulse cathode arc propulsion system |
| CN108082537A (en) * | 2017-12-07 | 2018-05-29 | 兰州交通大学 | Space trash clears up satellite equipments |
| RU2663607C1 (en) * | 2017-10-05 | 2018-08-07 | Общество с ограниченной ответственностью "Новые физические принципы" | Power plant with pulse detonation combustion of fuel |
-
2021
- 2021-03-16 CN CN202110280109.5A patent/CN113022895B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB534220A (en) * | 1938-11-18 | 1941-03-03 | Nat Machinery Co | Improvements in or relating to heavy duty clutch and flywheel assemblies |
| CN102358436A (en) * | 2011-08-31 | 2012-02-22 | 中国航天科技集团公司第五研究院第五一三研究所 | Device for realizing spacecraft orbit keeping by utilizing space debris |
| CN104773307A (en) * | 2015-04-30 | 2015-07-15 | 中国科学院宁波材料技术与工程研究所 | Approximate-light-speed particle moving method and system |
| CN108026902A (en) * | 2015-09-15 | 2018-05-11 | 纽曼空间有限公司 | Inner wire trigger pulse cathode arc propulsion system |
| RU2663607C1 (en) * | 2017-10-05 | 2018-08-07 | Общество с ограниченной ответственностью "Новые физические принципы" | Power plant with pulse detonation combustion of fuel |
| CN108082537A (en) * | 2017-12-07 | 2018-05-29 | 兰州交通大学 | Space trash clears up satellite equipments |
Non-Patent Citations (1)
| Title |
|---|
| 叶继飞;李南雷;常浩;: "两种激光烧蚀微推力器工作模式的讨论", 火箭推进, no. 05 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113022895B (en) | 2024-01-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102767497B (en) | Fuel-free spacecraft propelling system based on spatial atomic oxygen and propelling method | |
| US6336844B1 (en) | Method and machine for the ultrasonic peening of parts on a wheel | |
| JP6473960B2 (en) | Space debris orbital descent method, orbital descent system, and satellite orbit conversion method, orbit conversion system | |
| CN111331520B (en) | Sand blasting-laser composite cleaning equipment and cleaning method thereof | |
| CN113022895B (en) | Flywheel ablation space propeller and space debris cleaning platform | |
| WO2020155460A1 (en) | Method for flight on moon and lunar flight device | |
| Göksel et al. | First breakthrough for future air-breathing magneto-plasma propulsion systems | |
| CN201399384Y (en) | Anode vibrating strike hammer of electrical precipitator | |
| CN103909300A (en) | Electrophoresis and supersonic vibration assisted micro-milling and machining device | |
| US20080127775A1 (en) | Inertiatrons and methods and devices using same | |
| CN104726817B (en) | Directional ultrahigh-velocity spraying method and device based on laser induced shock wave technology | |
| Engel et al. | Asteroid mining and deflection using electromagnetic launchers | |
| EP2151346A1 (en) | System for using the air pressure acting on a moving vehicle to produce energy | |
| CN111746829B (en) | Small-size space debris removing method | |
| CN210703073U (en) | Vacuum beam welding machine convenient to remove | |
| CN105201769A (en) | Laser plasma combined propelling system | |
| CN111856495B (en) | Self-adaptive nanosecond pulse laser driving system and method for antenna-ground | |
| JP2007332947A (en) | Wind power generation device and wind power generation method | |
| CN211514869U (en) | Horizontal electric dust removal device for sintering machine head | |
| CN105822397A (en) | Power generation device using thermal energy and kinetic energy of automobile tail gas | |
| JP7455439B1 (en) | Artificial object control method, artificial object control device, and artificial object equipped with the same | |
| CN111516905A (en) | Mars flying method and device | |
| CN213000595U (en) | Graphene-based electrostatic dust collector | |
| CN114486716B (en) | High-speed adjustable rotary ice crystal impactor | |
| CN220462475U (en) | Rust remover for automobile parts |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |