CN111547271A - Debris removal-asteroid defense dual-purpose space-based laser system - Google Patents
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Abstract
The invention discloses a debris removal-asteroid defense dual-purpose space-based laser system which mainly comprises a plurality of space-based laser driving platforms with the same parameters, wherein each space-based laser driving platform comprises a satellite platform, a laser, a detection tracking and aiming emission system, an array connecting device and a control system, the array connecting device is responsible for being connected with an array connecting device of an adjacent satellite platform when a laser driving array is formed and is in butt joint with a control circuit, the control system is connected with each subsystem through a bus to control the working condition of the subsystem, and the detection tracking and aiming emission system detects and finds space debris and asteroids, stably tracks and aims the space debris and the asteroids and collects laser emitted by the lasers to a target. The invention generates impulse to change the track through impulse coupling effect; when no threat exists, the space debris is dispersedly deployed on the LEO orbit and is actively removed independently.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a space debris removal and small planet defense system driven by space-based laser through ablation.
Background
Space debris refers to space debris generated by human space activity. The total amount of space debris around the earth is close to 7000t, 43% of which are mainly distributed on the 400-2000km low-earth orbit. They seriously threaten the safety of the spacecraft, the mitigation of space debris is imperative, and how to remove the space debris becomes a hotspot and frontier problem concerned in the aerospace field.
The incidents of the asteroid impacting the earth are frequent in history, and the disasters and the biological extinction of the earth environment are caused for many times, so that the potential threat of possibly destroying human beings is great. Defending asteroids from striking the earth has become a hotspot of general concern in international society and a huge challenge facing the world wide aerospace world.
The laser ablation driving technology has wide application prospect in the aspect of asteroid defense. According to the research result of Phipps et al, a high-intensity pulse laser irradiates the surface of a target, so that the surface material is melted and gasified, and a plasma back-jet flow is generated, thereby providing a velocity increment for the target. Based on the principle, professor Lubin et al in the United states propose a set of DE-STAR system and DE-STARLITE system based on high-energy pulse laser and capable of being used for the defense of the asteroid in the near field at the same time. The system is deployed at a ground Lagrange point or a lunar orbit and consists of a laser array consisting of a plurality of pulse lasers, a tracking and aiming transmitting system and a control system. Due to the large mass of the asteroid, the laser ablation drive needs a long-term action to produce a change in velocity sufficient to deflect its orbit. The system has the following problems due to long development period and high production cost: when the defense is started to be prepared for the threatening target, a lot of time is spent on the production, the emission and the flying of the platform to the target, the defense opportunity is easily missed, and the design life of the platform is wasted due to long-time idle when the defense platform is prepared on the track in advance.
According to the research success of NASA, European ESA, JAXA of Japan and Beijing satellite environmental engineering institute in China, the laser ablation driving technology can also be applied to active removal of space debris, the required laser energy is lower than the minor planet defense, the laser ablation driving technology is deployed in a near-earth LEO orbit, and the system comprises a satellite platform, a laser, a detection and tracking emission system and a control system.
Disclosure of Invention
The technical problems to be solved by the invention include: how to solve the contradiction that the minor planet defense platform reacts fast and waits for the waste of the service life of the equipment on the orbit for a long time.
In view of the above defects in the prior art, the invention aims to provide a debris removal-asteroid defense dual-purpose space-based laser system, which can realize the usual scattered deployment by combining and separating laser ablation driving platforms, each platform independently performs the task of removing space debris by laser driving, and when threatened, the platforms are combined into an array to perform the asteroid defense task, thereby taking into account the quick response of asteroid defense and the effective utilization of the long-term on-orbit standby time.
The purpose of the invention is realized by the following technical scheme:
the dual-purpose space-based laser system for removing fragments and defending asteroids mainly comprises a plurality of space-based laser driving platforms with the same parameters, wherein each space-based laser driving platform comprises a satellite platform, a laser, a detection tracking and aiming emission system, an array connecting device and a control system, each satellite platform comprises a solar panel, a heat control system and an attitude and orbit control system, the solar panel is responsible for supplying electric energy to each part, the heat control system is responsible for dissipating heat generated by the laser in working, and the attitude and orbit control system is responsible for maintaining the orbit and the attitude stability of the satellite platform; the array connecting device is used for connecting with the adjacent satellite platform array connecting device when a laser driving array is formed, and is in butt joint with a control circuit, the control system is connected with each subsystem through a bus so as to control the working condition of the control system, the detection tracking and aiming transmitting system detects and finds space fragments and asteroids, performs stable tracking and aiming on the space fragments and the asteroids, and converges laser emitted by a laser on a target; when the collision threat of the asteroid is not found, the space-based laser system is dispersed into a plurality of independent space-based laser driving platforms to carry out active fragment removal, and when the collision threat of the asteroid is found, the space-based laser system is combined into a laser ablation driving array to obtain enough laser ablation driving capability to realize the offset defense of the asteroid.
The array connecting device is fixed on four sides of the satellite platform and is in a cross layout, and the space-based laser driving platform is connected with other platforms on the four sides through the array connecting device when the laser array is formed.
After the laser array is formed, all the platform control systems realize networking and unified control of all the detection tracking and aiming systems and the lasers to work, so that the array points to the asteroid direction, all the platforms uniformly and simultaneously emit pulse lasers to irradiate the asteroid, and all the platforms uniformly and simultaneously emit the pulse lasers to irradiate the asteroid.
The space-based laser driving platform is a high-power space-based communication laser driving platform.
The laser platforms at the periphery of the array are only connected with the two directional platforms, the laser platforms at the top points are connected with the three directional platforms, and the laser platforms in the array are connected with the four directional platforms.
Wherein the single pulse energy of the laser is more than 1kJ, and the frequency is more than 1 Hz;
the number of laser arrays formed by the laser platforms is more than 100, and laser energy of more than 100kJ is emitted in a single time.
The debris removal-asteroid defense dual-purpose space-based laser system can realize the dispersed deployment at ordinary times through the combinable and separable laser driving platform, can be combined into an array working mode when threatened, delivers laser energy with enough energy density on the threatened asteroid, and generates impulse to change the orbit of the asteroid through impulse coupling effect; when no threat exists, the space debris is dispersedly deployed on the LEO orbit and is actively removed independently.
Description of the drawings:
fig. 1 is a schematic structural diagram of an antenna-based laser driving platform in a debris removal-asteroid defense dual-purpose antenna-based laser system of the invention.
Wherein 1 is a satellite platform, an array connecting device, 3 is a detection tracking and aiming transmitting system, 4 is a laser, and 5 is a control system.
FIG. 2 is a schematic layout diagram of the array connection device in the debris removal-asteroid defense dual-purpose space-based laser system of the present invention.
FIG. 3 is a schematic diagram of a laser array in a debris removal-asteroid defense dual-purpose space-based laser system of the present invention.
FIG. 4 is a schematic diagram of a deflecting defense asteroid in the debris removal-asteroid defense dual-purpose space-based laser system of the present invention.
Detailed Description
The debris removal-asteroid defense dual-purpose space-based laser system of the present invention is described in detail below with reference to the accompanying drawings, but the description is merely exemplary and is not intended to limit the scope of the present invention in any way.
Referring to fig. 1, fig. 1 is a schematic structural diagram of a space-based laser driving platform in a debris removal-asteroid defense dual-purpose space-based laser system of the present invention. The dual-purpose space-based laser system for removing fragments and defending asteroids mainly comprises a plurality of space-based laser driving platforms with the same parameters, wherein each space-based laser driving platform comprises a satellite platform 1, a laser 4, a detection tracking and aiming emission system 3, an array connecting device 2 and a control system 5, the satellite platform 1 comprises a solar panel, a thermal control system and an attitude and orbit control system, the solar panel is responsible for providing electric energy for each part, the thermal control system is responsible for dissipating heat generated by the laser in working, and the attitude and orbit control system is responsible for maintaining the orbit and attitude stability of the satellite platform; the array connecting device is used for connecting with the adjacent satellite platform array connecting device when a laser driving array is formed, and is in butt joint with a control circuit, the control system is connected with each subsystem through a bus so as to control the working condition of the control system, the detection tracking and aiming transmitting system detects and finds space fragments and asteroids, performs stable tracking and aiming on the space fragments and the asteroids, and converges laser emitted by a laser on a target; when the collision threat of the asteroid is not found, the space-based laser system is dispersed into a plurality of independent space-based laser driving platforms to carry out active fragment removal, and when the collision threat of the asteroid is found, the space-based laser system is combined into a laser ablation driving array to obtain enough laser ablation driving capability to realize the offset defense of the asteroid. The satellite platform in the system has the main structure composition consistent with that of a common solar energy supply satellite platform, the solar cell panel is responsible for supplying electric energy to the laser, the detection tracking and aiming transmitting system, the array connecting device and the control system, the heat control system is responsible for dissipating heat generated by the laser in work, and the attitude and orbit control system is responsible for maintaining the orbit and the attitude stability of the satellite platform. In addition, other equipment required by the high-power space-based satellite platform is included, and the eastern 4 east 5 platform used for high-power space-based communication in the space five courtyards can meet the requirement. The array connecting devices are fixed on four sides of the satellite platform and are in a cross arrangement, the structural schematic diagram of the array connecting devices is shown in figure 2, the array connecting devices are responsible for being connected with the adjacent satellite platform array connecting devices when a driving array is formed, and butt joint control circuits are connected, the basic composition and the functional principle of the array connecting devices are consistent with the butt joint result of a common space vehicle, and the array connecting devices are mature and applied to space stations, manned spacecrafts and lunar aircrafts in China. When the laser array is formed, the space-based laser driving platform is connected with other platforms on four sides of the space-based laser driving platform through the array connecting device. As shown in fig. 3, fig. 3 is a schematic diagram of a laser array in the debris removal-asteroid defense dual-purpose space-based laser system of the present invention. In order to observe from one side of the detection tracking and aiming emission system, a plurality of lasers which are responsible for providing pulse lasers meeting the system requirements form a laser array, wherein a square is a satellite platform 1, and a circle is a detection tracking and aiming emission system 3.
In the system, the structure of a detection tracking and aiming emission system is consistent with that of a common space-based laser emission system, and the well-developed optical structure design with the same optical path in the three processes of target detection, tracking and laser emission is adopted. The system is responsible for detecting and finding space debris and asteroids, stably tracking and aiming the space debris and the asteroids, and converging laser emitted by a laser to a target. The products of units such as the space courtyard 508 institute and the Changchun optical engine institute can meet the requirements. The control system consists of a computer system and a data transmission bus. Is connected with each subsystem through a bus to control the working condition of the subsystems. The software and hardware of the control system need to meet the aerospace use standard.
In a specific embodiment, when the collision threat of the asteroid is not found, the system is dispersed into a plurality of independent platforms to actively remove fragments, and when the collision threat of the asteroid is found, the independent platforms are combined into a laser ablation drive array to obtain enough laser ablation drive capacity to realize asteroid migration defense.
When there is no asteroid impact threat, the laser platforms are distributed over the LEO orbital regions according to the space debris removal needs. The satellite platform 1 ensures the stable operation of the whole system in orbit. The system relies on ground or other space-based platform data to obtain information about space debris in the vicinity of the system itself. The control system 5 adjusts the detection tracking system 3 through the obtained information, enables the detection tracking system to point to the corresponding direction, finds space debris attached to the detection tracking system, and performs stable tracking on the space debris. After the detection tracking system 4 forms a stable tracking, the control system 5 sends a command to the laser 4 to enable the generated laser to be delivered to the surface of the space debris through the detection tracking system 3, and the speed change quantity is generated by driving impulse coupling effect through laser ablation to enable the debris to be removed by falling the track.
When the threat of the asteroid is found, the control system 5 of each laser platform calculates an orbital transfer scheme according to the orbit of each platform, performs orbital maneuver through the satellite platform 1, enters the asteroid defense orbit (according to different defense strategies, the time-of-the-earth, the earth-sun Lagrange point or the asteroid orbit around the fly) and starts to approach each other. After the distance is close enough, the laser defense array is formed by starting to work through the array connecting device 2 and is connected with the peripheral platform according to different positions in the array. The laser platforms at the periphery of the array are only connected with the two directional platforms, the laser platforms at the top points are connected with the three directional platforms, and the platforms in the array are connected with the four directional platforms. After the laser array is formed, all the platform control systems realize networking and uniformly control all the detection tracking and aiming systems and the lasers to work, so that the array points to the asteroid direction. All the platforms uniformly and simultaneously emit pulse laser to irradiate the asteroid. Through impulse coupling, the device generates speed change quantity, thereby deflecting the track to realize impact defense.
FIG. 4 is a schematic diagram of a deflecting defense asteroid in the debris removal-asteroid defense dual-purpose space-based laser system of the present invention. The detailed deflection defense process is as follows, assuming that the asteroid flies towards the earth in the positive x-axis direction, the deflection force F acts continuously in a direction perpendicular to the direction of motion of the asteroid, and continues to produce an impulse in that direction on the asteroid to deflect its orbit. The criterion for success or failure of defense is whether the minimum distance from the earth when the asteroid flies over the earth is greater than the capture radius Rc. When the distance between the minor planet and the earth is less than the distance, the minor planet is accelerated to collide with the earth under the action of the gravity of the earth. Where S is the small initial position distance from the earth and V is the PHA relative earth velocity.
The capture radius Rc is calculated by:
where Re is the radius of the earth, M is the mass of the earth, and G is the gravitational constant.
When the included angle between the connecting line of the PHA and the earth and the Y-axis direction is theta, the required offset distance Y in the positive direction of the Y coordinate axis is as follows:
Y＝Rccosθ＝Rc[1-(Rc/S)2]1/2
take a laser platform with a 1.5m transmitting mirror aperture, 1kJ laser single pulse energy and 1Hz frequency as an example. The laser array consisting of 100 laser platforms can emit 100kJ laser energy in a single time. Calculated by M types of asteroid with metal components as main components, the impulse coupling coefficient is 0.00005 N.s/J, and the impulse which can be generated per second is 5 N.s. Five closely-spaced asteroids 2006QV89, 2009JF1, 2008UB7, 2010RF12, 1979XB and the like can achieve work deviation within about one year.
Claims (7)
1. The dual-purpose space-based laser system for removing fragments and defending asteroids mainly comprises a plurality of space-based laser driving platforms with the same parameters, wherein each space-based laser driving platform comprises a satellite platform, a laser, a detection tracking and aiming emission system, an array connecting device and a control system, each satellite platform comprises a solar panel, a heat control system and an attitude and orbit control system, the solar panel is responsible for supplying electric energy to each part, the heat control system is responsible for dissipating heat generated by the laser in working, and the attitude and orbit control system is responsible for maintaining the orbit and the attitude stability of the satellite platform; the array connecting device is used for connecting with the adjacent satellite platform array connecting device when a laser driving array is formed, and is in butt joint with a control circuit, the control system is connected with each subsystem through a bus so as to control the working condition of the control system, the detection tracking and aiming transmitting system detects and finds space fragments and asteroids, performs stable tracking and aiming on the space fragments and the asteroids, and converges laser emitted by a laser on a target; when the collision threat of the asteroid is not found, the space-based laser system is dispersed into a plurality of independent space-based laser driving platforms to carry out active fragment removal, and when the collision threat of the asteroid is found, the space-based laser system is combined into a laser ablation driving array to obtain enough laser ablation driving capability to realize the offset defense of the asteroid.
2. The debris removal-asteroid defense dual-purpose space-based laser system of claim 1, wherein the array connecting device is fixed on four sides of the satellite platform and is in a cross layout, and the space-based laser driving platform is connected with other platforms on the four sides of the satellite platform through the array connecting device when the laser array is formed.
3. The debris removal-asteroid defense dual-purpose space-based laser system of claim 1, wherein after the laser array is formed, the platform control systems are networked to uniformly control all the detection tracking systems and the lasers to work, so that the array points to the direction of the asteroid, the platforms uniformly and simultaneously emit pulse laser to irradiate the asteroid, and the platforms uniformly and simultaneously emit pulse laser to irradiate the asteroid.
4. The debris removal-asteroid defense dual-purpose space-based laser system of any one of claims 1-3, wherein the space-based laser driving platform is a high-power space-based communication laser driving platform.
5. The debris removal-asteroid defense dual-purpose space-based laser system of any one of claims 1-3, wherein the laser platforms at the periphery of the array are connected with only two directional platforms, the laser platforms at the vertices are connected with three directional platforms, and the platforms inside the array are connected with four directional platforms.
6. The debris removal-asteroid defense dual-purpose space-based laser system according to any one of claims 1 to 3, wherein the laser has a single pulse energy of 1kJ or more and a frequency of 1Hz or more.
7. The debris removal-asteroid defense dual-purpose space-based laser system of any one of claims 1 to 3, wherein the number of laser arrays formed by the laser platforms is more than 100, and the laser energy is more than 100kJ emitted in a single time.
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| US20110302906A1 (en) * | 2010-06-15 | 2011-12-15 | John Elihu Sinko | Laser Tractor Beam |
| US9021782B1 (en) * | 2010-08-24 | 2015-05-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Aerospace laser ignition/ablation variable high precision thruster |
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