CN115946873A - Attack type primary and secondary satellite system based on rail descending of electrodynamic force tether - Google Patents
Attack type primary and secondary satellite system based on rail descending of electrodynamic force tether Download PDFInfo
- Publication number
- CN115946873A CN115946873A CN202310237554.2A CN202310237554A CN115946873A CN 115946873 A CN115946873 A CN 115946873A CN 202310237554 A CN202310237554 A CN 202310237554A CN 115946873 A CN115946873 A CN 115946873A
- Authority
- CN
- China
- Prior art keywords
- satellite
- tether
- tethered
- platform
- target
- 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.)
- Pending
Links
- 230000005520 electrodynamics Effects 0.000 title claims description 7
- 230000009467 reduction Effects 0.000 claims description 5
- 238000004891 communication Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000013473 artificial intelligence Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Abstract
The invention discloses an attack type primary-secondary satellite system based on electric power rope system orbit-lowering, which comprises: a platform satellite on which a tethered satellite is mounted; the platform satellite transmits the tethered satellite according to an instruction for striking a target satellite in an attack range, and adheres and lowers the orbit of the target satellite. By adopting the technical scheme of the invention, the generation of space debris is greatly reduced, and the space environment protection is favorably realized.
Description
Technical Field
The invention belongs to the technical field of aerospace satellites, and particularly relates to an attack type primary and secondary satellite system for electric power tether orbit reduction.
Background
In the development process of the human society, the functions of the artificial satellite are gradually improved. Nowadays, satellites all bear important missions in daily life and military, and are mainly used in the fields of scientific exploration and research, weather forecast, land resource investigation, land utilization, area planning, communication, tracking, navigation and the like, and at present, resource satellites, meteorological satellites, communication satellites, navigation satellites and the like are commonly used. With the continuous progress of the aerospace technology level of each country, the requirement on satellites is higher and higher in the future. The satellite field is developing for decades now, and is facing the key period of technological innovation breakthrough. In recent years, due to the development of industrialization and the increasing demand of satellites for communication, navigation, monitoring and the like in all countries of the world, people transmit a large number of satellites to outer space, and meanwhile, increasingly outstanding maintenance cost and outer space environment problems follow. In response to these problems, many efforts have been made to search for and develop multipurpose multifunctional satellites, and research on combination satellites is one of them. The appearance of a large-scale constellation system represented by American star chain shows a prospect prototype of the Internet and aerospace era, the artificial intelligence technology is rapidly developed, and the spacecraft is developed towards the networking, intelligentization, environmental protection, low cost, autonomous controllability and other directions in the future.
Currently about 1.7 million space debris and 3000 "dead" satellites fly around the earth, and there are currently over 2000 operating satellites around the world, primarily distributed in space orbits at 800 km and 36,000 km from the earth, where debris and debris have exceeded the operating satellites and pose a potential threat to the orbiting satellites. Due to the limited frequency orbit resources, the satellite frequencies interfere with each other and even cause satellite collision. With these problems, there will be a large number of satellites that can be cleaned of space debris or automatically recycled in the future.
Disclosure of Invention
The invention aims to solve the technical problem of providing an attack type primary-secondary satellite system for electric power tether rail lowering, which greatly reduces the generation of space debris and is beneficial to realizing space environmental protection.
In order to achieve the purpose, the invention adopts the following technical scheme:
an aggressive primary-secondary satellite system based on electric power tether landing rail, comprising: a platform satellite on which a tethered satellite is mounted; the platform satellite transmits the tethered satellite according to an instruction for striking a target satellite in an attack range, and adheres to the target satellite and performs orbit reduction.
Preferably, the tethered satellite uses electrically powered tethers for the target satellite to effect descent.
Preferably, the target satellite is descended by taking a fully-exposed conductive rope as a tether.
Preferably, the platform satellite comprises a launch bin in which the tethered satellite is stored.
Preferably, the platform satellite transmits the tethered satellite by cold launching according to an instruction of striking the target satellite within an attack range.
Preferably, the launching bin is a hexagonal launching bin.
Preferably, each of the six launching bins stores 6 tethered satellites arranged in a straight line.
Preferably, the platform satellite performs a strike on a target satellite within 900km orbital range.
According to the invention, the tethered satellite is carried on the platform satellite, and the tethered satellite is launched in a cold launching mode to adhere to the target satellite, so that the electric power tethered orbit reduction is realized, and the device has high accuracy and small volume. The integrated use of the combined satellite reduces the operation cost of the satellite to a certain extent; the target satellite is in orbit descending mode, so that the generation of space debris is greatly reduced, and the space environment is favorably realized.
Drawings
FIG. 1 is a schematic structural diagram of a platform satellite according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a tethered satellite according to an embodiment of the present invention.
Detailed Description
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 only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example 1:
the embodiment of the invention provides an attack type primary and secondary satellite system based on electric power tether orbit reduction, which comprises: a platform satellite 1 on which a tethered satellite is mounted in the platform satellite 1; the platform satellite 1 transmits the tethered satellite according to an instruction for striking a target satellite in an attack range, and adheres to the target satellite and electrically descends the tethered system.
As an implementation manner of the embodiment of the present invention, as shown in fig. 1, the platform satellite 1 includes a launching bin 11, where the launching bin 11 is a hexagonal launching bin; when the platform satellite 1 receives an instruction for striking the target satellite in an attack range, starting the hexagonal launching bin; each of the six launching bins 11 stores 6 tethered satellites arranged in a straight line shape, and can launch the tethered satellites with different quantities according to task requirements in a cold launching mode after locking a target satellite in a 900km orbit range.
As an implementation manner of the embodiment of the present invention, as shown in fig. 2, after the tethered satellite leaves the platform satellite 1, the tethered satellite flies to the target satellite by means of the tethered satellite guidance system, and when the tethered satellite flies into a proper range, the casing of the tethered satellite is unfolded in a direction perpendicular to the movement trajectory, and the thrust reverser 2 is started at the same time, so that the tethered satellite approaches the target satellite at a proper speed.
As an embodiment of the present invention, as shown in fig. 2, the casing 3 of the tethered satellite slides in the direction parallel to the moving direction to expose the adhering device 4, and the attitude and the speed are adjusted by the tethered satellite thruster 5 and the thrust reverser 2 to complete the adhering and adhering with the target satellite. At the moment, the roller 6 for fixing the tether starts to rotate, and the hollow body at the end of the tether starts to fly towards the height lower than the running orbit of the target satellite at a proper component speed which is the same as the moving direction of the target satellite under the action of centrifugal force.
As an embodiment of the present invention, as shown in fig. 2, after the tethered satellite is successfully adhered, the hollow object flies to the orbit lower than the target satellite until the tether is completely released and deployed, and then the orbit lowering damage task for the target satellite is started. And when the electrodynamic force direction is opposite to the running direction of the target satellite system, the orbit speed of the target satellite system is reduced, the orbit of the target satellite is reduced, and finally the target satellite is completely burnt in the atmosphere.
The embodiment of the invention integrates civil and military functions and plays a role of civil soldiers. The civil state can be used as an auxiliary system when 5G and Beidou are integrated, and certain communication and observation services are provided; the military state can be used for an attack task in a special period, a hidden attack function is played when needed, and the target satellite finally burns out in the atmosphere by the electric power tether landing orbit through the subsatellite adhered to the target satellite.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention shall be covered within the scope of the present invention, and therefore, the scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. An aggressive primary-secondary satellite system based on electric power tether landing rail, comprising: a platform satellite on which a tethered satellite is mounted; the platform satellite transmits the tethered satellite according to an instruction for striking a target satellite in an attack range, and adheres to the target satellite and performs orbit reduction.
2. The electric power tether descent based aggressor sub-primary satellite system of claim 1 wherein the tether satellite provides for descent of a trajectory using an electric power tether to the target satellite.
3. The aggressive sub-primary satellite system based on electric power tether descent of claim 2, wherein the target satellite is descended using a fully bare conductive rope as a tether.
4. The electromotive force tethered descent based aggressor sub-parent satellite system of claim 3 wherein said platform satellite comprises a launch bin in which to store said tethered satellite.
5. The electrodynamic tether drop rail-based aggressor sub-primary satellite system of claim 4, wherein the platform satellite transmits the tethered satellite in cold launch based on a command to strike a target satellite within an attack range.
6. The electrodynamic tether drop rail-based aggressor sub-primary satellite system of claim 5, wherein the launch bin is a hexagonal launch bin.
7. The electrodynamic tether drop rail-based aggressor sub-primary satellite system of claim 6, wherein each of the six-sided launch bins stores 6 of the tethered satellites in a "straight" arrangement.
8. The electrodynamic tether descent-based aggressor sub-primary satellite system of claim 7, wherein the platform satellite strikes a target satellite within 900km of orbit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310237554.2A CN115946873A (en) | 2023-03-14 | 2023-03-14 | Attack type primary and secondary satellite system based on rail descending of electrodynamic force tether |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310237554.2A CN115946873A (en) | 2023-03-14 | 2023-03-14 | Attack type primary and secondary satellite system based on rail descending of electrodynamic force tether |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115946873A true CN115946873A (en) | 2023-04-11 |
Family
ID=87287910
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310237554.2A Pending CN115946873A (en) | 2023-03-14 | 2023-03-14 | Attack type primary and secondary satellite system based on rail descending of electrodynamic force tether |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115946873A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007041994A1 (en) * | 2007-09-04 | 2009-04-02 | Schepelmann, Jürgen | Device, particularly auxiliary satellite for ejecting impulse mass for deflecting disturbing satellite on tolerable path by collision, has drive unit for ejecting impulse mass on trajectory in direction of target satellite |
| CN101767657A (en) * | 2009-12-30 | 2010-07-07 | 哈尔滨工业大学 | Electro-dynamic tether based satellite deorbit device and method thereof |
| US20170015444A1 (en) * | 2014-04-04 | 2017-01-19 | Astroscale Japan Inc. | Debris removal device and debris removal system |
| CN110473431A (en) * | 2019-09-17 | 2019-11-19 | 中国民用航空飞行学院 | A kind of conflict prediction method under the height limitation of approach control airspace |
| US20220380066A1 (en) * | 2021-05-26 | 2022-12-01 | National University Of Defense Technology | Harmless low-consumption on-orbit continuous launch system |
-
2023
- 2023-03-14 CN CN202310237554.2A patent/CN115946873A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007041994A1 (en) * | 2007-09-04 | 2009-04-02 | Schepelmann, Jürgen | Device, particularly auxiliary satellite for ejecting impulse mass for deflecting disturbing satellite on tolerable path by collision, has drive unit for ejecting impulse mass on trajectory in direction of target satellite |
| CN101767657A (en) * | 2009-12-30 | 2010-07-07 | 哈尔滨工业大学 | Electro-dynamic tether based satellite deorbit device and method thereof |
| US20170015444A1 (en) * | 2014-04-04 | 2017-01-19 | Astroscale Japan Inc. | Debris removal device and debris removal system |
| CN110473431A (en) * | 2019-09-17 | 2019-11-19 | 中国民用航空飞行学院 | A kind of conflict prediction method under the height limitation of approach control airspace |
| US20220380066A1 (en) * | 2021-05-26 | 2022-12-01 | National University Of Defense Technology | Harmless low-consumption on-orbit continuous launch system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Lee et al. | Optimal path planning of solar-powered UAV using gravitational potential energy | |
| Chaisson | The Hubble wars: Astrophysics meets astropolitics in the two-billion-dollar struggle over the Hubble Space Telescope | |
| WO2015190527A1 (en) | Method and system for space debris orbit descent, and method and system for changing orbit of artificial satellite | |
| Genta | Introduction to the mechanics of space robots | |
| CN1085177A (en) | Handle the method and apparatus that minces with the showy space of withdrawal | |
| WO2009148625A2 (en) | Space station, launch vehicle, and method of assembly | |
| Genta et al. | Space, the final frontier? | |
| CN115946873A (en) | Attack type primary and secondary satellite system based on rail descending of electrodynamic force tether | |
| CN107792395A (en) | The deployable spacecraft of radome fairing primary integration heavy caliber | |
| CN104443358A (en) | Power propulsion device for aeronautical and space aircraft and application of power propulsion device for aeronautical and space aircraft | |
| Gierulski et al. | Electric-powered aircraft | |
| Smitherman Jr et al. | Space elevators | |
| CN101992699A (en) | Solar unmanned spaceship | |
| Bolonkin | Innovations and New Technologies (v. 2) | |
| Bolonkin | Innovations and new technologies | |
| Harvey et al. | New rockets, launch sites and ships | |
| Hahn et al. | Exploring the Solar System | |
| Owen | Final Frontier: Voyages into Outer Space | |
| Herres | The military in space: A historical relationship | |
| Kortenkamp | Mars Exploration Rovers: An Interactive Space Exploration Adventure | |
| Bhattacharjee et al. | A Simplified Guide To Rocket Science and Beyond--Understanding The Technologies of The Future | |
| Bizony | New space frontiers: venturing into Earth orbit and beyond | |
| CN117922852A (en) | Solar cell array driven asteroid mining device and method | |
| Cameron et al. | Portable unmanned aircraft system concept investigation | |
| RU2250860C2 (en) | Method of acceleration of spacecraft |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20230411 |
|
| RJ01 | Rejection of invention patent application after publication |