Method for indirectly moving celestial body by using spacecraft
The spacecraft exerted a driving force on the celestial body β, indirectly changing the motion state of the celestial body group, solving the problem that the prior art is difficult to safely change the motion of the celestial body or the earth, and achieving safe and reliable adjustment of the motion state, suitable for avoiding impacts and responding to radiation changes.
Patent Information
- Application Number
- CN202510073893.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-17
- Publication Date
- 2025-04-25
AI Technical Summary
The prior art is difficult to safely change the state of motion of celestial bodies or the earth, especially in avoiding devastating impacts and responding to changes in solar radiation.
By using the spacecraft to apply driving force to the celestial body β, the motion state of the celestial body group is indirectly changed. The driving force may come from an artificial explosion, an impact or indirect influence of an injection engine, an external celestial body, ensuring that the driving force direction conforms to the desired acceleration direction.
The safe change of the motion state of the celestial body or the earth is achieved, avoiding devastating impacts, and providing a way to mitigate the effects of changing solar radiation, such as by changing the Earth's orbit to reduce radiation.
Smart Images
Figure CN119872921A_ABST
Abstract
Description
Technical Field
[0001] This technology belongs to aerospace engineering technology. Background Art
[0002] Since the 1960s, aerospace technology has made great progress.
[0003] In order to avoid disasters caused by small near-Earth celestial bodies hitting the Earth, engineers began to study and even test methods to change the orbits of small celestial bodies. People are also worried that the energy of solar radiation will change in the near or distant future, so they began to explore or fantasize about technical ways to change the Earth's orbit away from the Sun. Using celestial bodies to hit the Earth to push it to change its position is destructive and obviously not feasible. Using the reaction force of super-powerful jet engines to push the Earth will also have insurmountable difficulties: the ejected matter must exceed the second cosmic speed - 11.2 kilometers per second. When they pass through the atmosphere, they will entrain a huge amount of air, making it impossible for humans to survive. The crust and mantle will also find it difficult to withstand the corresponding huge thrust without a catastrophe. People need to find a more feasible and reliable method in the near or future to safely change the motion state of certain celestial bodies or even the Earth. Summary of the invention
[0004] The purpose of the present invention is to provide a space engineering technology method that can safely change the motion state of certain celestial bodies. The following is an explanation:
[0005] This technology is a method of indirectly moving celestial bodies using spacecraft, including:
[0006] A. There are at least two celestial bodies that orbit each other due to the gravitational attraction of each other, forming a celestial body group;
[0007] B1. Determine the desired acceleration direction caused by the driving force affecting the common center of mass of all celestial bodies in the celestial body group, which is called trend X; select at least one celestial body in the celestial body group to bear the required driving force, which is called celestial body β, and the other celestial bodies or celestial body collections surrounded by celestial body β in the celestial body group are called celestial body α, so that the driving force direction conforms to or conforms to trend X in most cases; the driving force directly borne by celestial body β comes from the direct or indirect action of the spacecraft;
[0008] B2. Arranging the spacecraft to directly or indirectly exert a driving force on the celestial body β, the driving force including one or more of the following forces:
[0009] First: the force of an artificial explosion carried out by a spacecraft on a celestial body β, whereby at least part of the dispersed matter of the explosion or the material lifted from the celestial body β reaches an escape velocity capable of escaping from the group of celestial bodies;
[0010] Second: the force generated by the jet engine placed on the celestial body β by the spacecraft, at least part of the matter ejected into space reaches the escape velocity that allows it to escape from the group of celestial bodies;
[0011] Third: The force generated when celestial bodies or materials outside the celestial body group change their movement mode under the control or influence of the spacecraft and impact the celestial body β;
[0012] Fourth: The celestial bodies or materials outside the celestial body group change their running mode under the control or influence of the spacecraft, causing them to impact or affect the running mode of other celestial bodies, resulting in the force generated when the other celestial bodies impact the celestial body β;
[0013] Fifth: Under the control or influence of the spacecraft, celestial bodies or materials outside the celestial body group change their operating mode, and through more levels of indirect impact or influence than the fourth one, the force generated when other celestial bodies impact celestial body β.
[0014] in:
[0015] Celestial bodies refer to objects or stars moving in space, such as planets, satellites, comets or meteorites, man-made spacecraft and others;
[0016] The celestial body group may be an asteroid-asteroid system, or a comet-comet system, or a comet-asteroid system, or a planet-satellite system.
[0017] The trend X should refer to the desired acceleration direction or movement trend caused by the driving force to the common center of mass of all celestial bodies in the celestial body group;
[0018] Bearing driving force may refer to being directly subjected to the required impact force from celestial bodies or materials outside the celestial body group, or being subjected to the reaction force of engines arranged thereon or artificial explosions;
[0019] The direction of the driving force is consistent with the trend X, which can mean that they are consistent or the angle between them is significantly smaller than a right angle;
[0020] If the driving force is the force of an artificial explosion on celestial body β, it is preferred that most or at least part of the materials emitted by the explosion or lifted from celestial body β reach an escape velocity capable of escaping from the celestial body group; the explosion may be a chemical reaction explosion, or a nuclear reaction explosion if necessary;
[0021] If the driving force is generated by a jet engine installed on celestial body β, it is preferred that most or at least part of the matter ejected into space reaches an escape velocity capable of escaping from the group of celestial bodies;
[0022] Jet engines can be chemical reaction jet engines or nuclear reaction jet engines, or engines that accelerate ions or particles by electric or magnetic fields;
[0023] If the driving force on celestial body β is generated by the impact force of a celestial body or material outside the celestial body group, the movement mode of the celestial body or material outside the celestial body group before the impact may be or has been controlled or influenced by the spacecraft;
[0024] The driving force directly borne by the celestial body β is generated by the impact force of the celestial body or matter outside the celestial body group. The movement mode of the celestial body or matter outside the celestial body group before the impact is or has been subjected to earlier direct or gradual collision, contact, adhesion, attraction or influence by another celestial body or matter, and the other celestial body or matter has been controlled or influenced by the space device before or earlier.
[0025] Celestial bodies affected by the gravitational force and its changes of other celestial bodies in the celestial body group are not directly subjected to driving forces;
[0026] When the celestial body α is a celestial body set, the position of the celestial body α may refer to the position of the common center of mass of several celestial bodies constituting the set.
[0027] The method of the present technology may also include:
[0028] C. To make a certain part of the orbit of celestial body β around celestial body α (such as the point near celestial body α or the point far from celestial body α) within the required range of distance from celestial body α, one or more of the following operations can be taken at least for part of the time period:
[0029] Operation 1: When celestial body β is located on the opposite side of a certain part of celestial body β's orbit, celestial body β can be made to bear or increase the driving force that is consistent with its own direction or more consistent with the direction of celestial body β, so as to increase the distance between the part of celestial body β's orbit (such as the near celestial body α point) and celestial body α;
[0030] Operation 2: When celestial body β is located on the opposite side of a certain part of celestial body β's orbit, celestial body β can be prevented from bearing or reduced from bearing the driving force that is against its own direction or even more against the direction of celestial body β; so as to maintain or not significantly reduce the distance between a certain part of celestial body β's orbit (such as the pericelestial body α point) and celestial body α;
[0031] Operation 3: When celestial body β is located on the opposite side of a certain part of celestial body β's orbit, celestial body β can be made to bear or increase the driving force against its own direction or even more against the direction of celestial body β, so as to reduce the distance between a certain part of celestial body β's orbit (such as the far celestial body α point) and celestial body α;
[0032] Operation 4: When celestial body β is located on the opposite side of a certain part of celestial body β's orbit, celestial body β can be made not to bear or to bear less driving force that is in line with its own direction or more in line with the direction of celestial body β; so as to maintain or not significantly increase the distance between a certain part of celestial body β's orbit (such as the far celestial body α point) and celestial body α;
[0033] In the above operation, the effect will be better if the celestial body β is located in the middle of the orbit on the opposite side of this part.
[0034] Operation 5: When a certain part of the orbit of celestial body β (such as the point near the celestial body α) is on the retreating side and celestial body β is on the advancing side, celestial body β can be subjected to a driving force toward the forward direction (in line with the trend X) to increase the distance between the part of the orbit of celestial body β (such as the point near the celestial body α) and celestial body α;
[0035] Operation 6: When a certain part of the orbit of celestial body β (such as the far celestial body α point) is on the advancing side and celestial body β is on the retreating side, celestial body β can be subjected to a driving force toward the front (in line with the trend X) to reduce the distance between the part of the orbit of celestial body β (such as the far celestial body α point) and celestial body α;
[0036] in:
[0037] The orbit of celestial body β around celestial body α is simply called celestial body β orbit;
[0038] The straight line passing through celestial body α and perpendicular to the line connecting a certain part of the orbit of celestial body β is the dividing line. The side of the line where celestial body β is located is the same side, and the other side of the line is the opposite side.
[0039] The direction of celestial body β relative to celestial body α at a certain moment or the direction of the tangent line of the orbit at the point where celestial body β is located is the direction of celestial body β;
[0040] "Conforming to the celestial body's β trend" means that a certain direction is the same as or close to the celestial body's β trend, or the angle between them is less than a right angle; "more consistent with the celestial body's β trend" means that a certain direction is closer to the celestial body's β trend, or the angle between them is smaller;
[0041] Against the celestial body β trend means that a certain direction is contrary to or basically contrary to the celestial body β trend, or the angle between them is greater than a right angle. More against the celestial body β trend means that a certain direction is more contrary to the celestial body β trend, or the angle between them is closer to a right angle.
[0042] Taking the straight line passing through celestial body α and parallel to the trend X as the dividing line, when celestial body β is around celestial body α, the side where the direction of motion of celestial body β relative to celestial body α is mainly in line with the trend X is the advancing side, and the side where the direction of motion of celestial body β relative to celestial body α is mainly away from the trend X is the retreating side;
[0043] The direction that meets or substantially meets trend X is the front direction, and the direction opposite to the front direction is the rear direction.
[0044] The distance between celestial body α and celestial body α is within the required range may mean that the distance between the near-body α point of celestial body β's orbit and celestial body α is not too small, or the distance between the far-body α point of celestial body β's orbit and celestial body α is not too large; or it may mean that the shape of celestial body β's orbit or orbital parameters (such as eccentricity or major axis) are within the expected limited range.
[0045] This technology may also include:
[0046] D. If a certain part of the orbit of celestial body β around celestial body α, or a point near celestial body α, or a point far from celestial body α, is temporarily not located at the desired advancing side, retreating side, or other desired position, at least part of the time, it is possible to wait for the part, the point near celestial body α, or the point far from celestial body α to precess along with the celestial body β around the orbit of celestial body α to reach the desired advancing side, retreating side, or other desired position, and then perform one or more of the methods in B or the operations in C above.
[0047] Why does the method of the present invention sometimes use the precession described in D? In fact, for example, if we blindly make a certain part of the orbit of celestial body β around celestial body α (such as the near celestial body α point or the far celestial body α point) not too far or too close to celestial body α, we will find that the direction of the driving force that can be applied for this purpose may not be consistent with the trend X. Using the precession of the orbit of celestial body β around celestial body α allows us to wait for the opportunity to take both into account.
[0048] The orbital precession of the celestial body β around the celestial body α in D of the method of the present invention may be caused by the space environment around the celestial body group, which may be called natural precession.
[0049] The orbital precession of the celestial body β around the celestial body α in D of the method of the present invention may also be a driving force precession, which may include one or more of the following ways:
[0050] Method 1: The driving force on celestial body β when it orbits celestial body α can be made to have a component of force toward the inside of the orbit of celestial body β, so that the orbit will have the same precession or precession trend as the direction of celestial body β orbiting celestial body α;
[0051] Method 1: The driving force exerted on celestial body β when it orbits celestial body α can be made to have a component force toward the outside of the orbit of celestial body β, so as to cause the orbit to precess or have a precession tendency in the opposite direction to the direction of celestial body β orbiting celestial body α.
[0052] The precession trend may refer to the direction of the precession acceleration.
[0053] Why do we need the method of this technology to change the motion state of celestial bodies? For example, the nucleus of some comets is very soft and rough. It is difficult to change its orbit by installing artificial engines. If we use objects to hit it, it will break down and the effect will not be good. If we use the method of this invention to indirectly push the small celestial body around it, it is likely to succeed.
[0054] The celestial body group may even be an earth-moon system, where celestial body α may refer to the earth, celestial body β may refer to the moon, the perigee α point or the apogee α point of the orbit of celestial body β around celestial body α may refer to the perigee or apogee of the orbit of the moon around the earth, and the orbital precession may refer to the precession of the moon's orbit. Under the influence of extraterrestrial bodies such as the sun, the semi-major axis of the moon's orbit, the longest diameter of the orbit, and its perigee and apogee, perform a complete prograde revolution-precession every 8.85 earth years or 3232.6054 days.
[0055] In recent years, the temperature of the earth has been rising, and it is likely to rise in the future. Solar radiation may also increase slowly in the next tens of thousands of years. In the past, people had no way to significantly change the orbit of the earth unless they guided asteroids or comets to directly hit the earth and cause destruction. However, according to the method of the present invention, we use decades or more to guide or indirectly guide comets or near-Earth asteroids to hit the right part of the moon at the right time, which may very slowly and effectively increase the distance between the earth and the sun. If the distance between the earth and the sun increases by 0.5%, that is, 750,000 kilometers (twice the average distance between the earth and the moon), the radiation received by the earth will decrease by 1%, and the average temperature will decrease by 2-3°C. The earth may never wander out of the solar system, but it is possible to adjust its orbit.
[0056] Therefore, this technology can bring outstanding technical effects and significant progress to aerospace engineering. BRIEF DESCRIPTION OF THE DRAWINGS
[0057] Figure 1 This is a schematic diagram of a celestial body group consisting of celestial body β surrounding celestial body α according to Example 1 of the present invention.
[0058] Figure 2 This is a schematic diagram of the orbital change of the celestial body β in Example 1 of the present invention before and after the celestial body β is subjected to the driving force on the forward side.
[0059] Figure 3 This is a schematic diagram of the orbital change of the celestial body β in Example 1 of the present invention before and after it is subjected to the driving force on the retreating side.
[0060] Figure 4 This is a schematic diagram of the precession of celestial body β around the orbit of celestial body α in Example 1 of the present invention.
[0061] Among them, 11 is celestial body α, 12 is celestial body β, 13 is the trend X, 14 is the driving force direction, and 15 is the direction of motion of celestial body β relative to celestial body α;
[0062] 21 is the dividing line between the advancing side and the retreating side, 22 is the advancing side, 23 is the retreating side, 24 is the orbit of celestial body β before it directly receives the driving force, and 25 is the orbit of celestial body β after it directly receives the driving force;
[0063] 41 and 42 are the positions of the far celestial body α point of the orbit of celestial body α at an earlier time, 43 is the position of the far celestial body α point of the orbit of celestial body β at a later time, and 44 is the precession direction of the far celestial body α point of the orbit of celestial body β.
[0064] Specific implementation method
[0065] The following is a detailed description with reference to the accompanying drawings.
[0066] In Example 1, the method of the present invention relates to a method for driving the asteroid B-asteroid A system, see Figure 1 Among them, asteroid B (12) is equivalent to the aforementioned celestial body β; asteroid A (11) is the main star and is not convenient to directly bear the driving force, which is equivalent to the aforementioned celestial body α. Asteroid B orbits asteroid A (15), and asteroid B bears the driving force caused by humans (14). People hope that their common center of mass will move roughly towards trend X (13).
[0067] See also Figure 2 When the "point near asteroid A" of the orbit (24) of asteroid B is on the receding side (23) and asteroid B is on the advancing side (22), it can be subjected to a driving force toward the front (14) to increase the distance between the "point near asteroid A" of the orbit and asteroid A;
[0068] See also Figure 3 When the "far asteroid A point" of the orbit of asteroid B is on the advancing side (22) and asteroid B is on the receding side (23), it can be subjected to a driving force toward the front (14) to reduce the distance between the "near asteroid A point" of the orbit and asteroid A;
[0069] However, if at some point the "far asteroid A point" of asteroid B's orbit is too far and is located on the receding side, or if its "near asteroid A point" of asteroid B's orbit is too close and is located on the advancing side, we can no longer subject it to the driving force consistent with the trend X, and it may escape from asteroid A or fall and collide with asteroid A.
[0070] What can we do? We can use the precession of the orbit of asteroid B (see Figure 4 ), that is, wait for its "far asteroid A point" (far celestial body α point) or "near asteroid A point" (near celestial body α point) to precess to the forward or backward side we expect, and then make it bear the driving force consistent with the trend X, so that their common center of mass moves roughly toward the trend X. If we think the natural precession of asteroid B's orbit is too slow, we can make the driving force on asteroid B have a component toward the inner side of the celestial body β orbit, so as to cause the orbit to produce the same precession direction as asteroid B around asteroid A.
[0071] In this embodiment, the driving force on asteroid B comes from the reaction force of a jet engine installed on its surface. The engine generates reaction force by accelerating ions ejected by electric or magnetic fields.
[0072] In Example 2, a method for driving an asteroid-comet system is involved, wherein an asteroid (equivalent to a celestial body) β orbits a comet (equivalent to a celestial body α), and the driving method is basically the same as that in Example 1.
[0073] In Example 3, a method for driving an asteroid-comet system is involved, in which an asteroid (equivalent to a celestial body) β orbits a comet (equivalent to a celestial body α), and the driving method is roughly the same as that in Example 1, but the driving force borne by the asteroid comes from the explosion reaction force of a device set on its surface.
[0074] In Example 4, a method for driving an asteroid-comet system is involved. The driving method is substantially the same as that in Example 1, except that the driving force on the asteroid comes from the impact of other small celestial bodies on its surface guided by humans.
[0075] In Example 5, the driven celestial body group involved is the Earth-Moon system, where celestial body α refers to the Earth and celestial body β refers to the Moon. The purpose is to provide decades or even hundreds or thousands of years of persistent driving, so that the Earth gradually moves slightly away from the Sun to avoid global warming. The driving method is roughly the same as that in Example 1, and the driving force on the Moon comes from the long-term and multiple impacts of artificially guided comets or asteroids on its surface. Obviously, they need to change their original orbits so that they are subjected to earlier direct or gradual collisions or contacts or adhesions or attraction by other celestial bodies or substances, and those celestial bodies have been manipulated or affected by spacecraft before. In other words, we can use spacecraft to accurately affect (such as impact) small-mass celestial bodies, so that they affect or indirectly affect other slightly larger celestial bodies, and then directly or indirectly affect (such as impact) the Moon, thereby affecting the operating state of the Earth-Moon system.
[0076] The above embodiments are for illustrative purposes only and shall not be used to limit the protection scope of the present technology.
Claims
1. A method for indirectly moving a celestial body using a spacecraft, comprising: A. There are at least two celestial bodies that orbit each other due to the gravitational attraction of each other, forming a celestial body group; B1. Determine the desired acceleration direction caused by the driving force affecting the common mass center of all celestial bodies in the celestial body group, which is called trend X; select at least one celestial body in the celestial body group to bear the required driving force, which is referred to as celestial body β, and the other celestial bodies or celestial body collections surrounded by celestial body β in the celestial body group are referred to as celestial body α, so that the driving force direction conforms to or conforms to trend X in most cases; the driving force directly borne by celestial body β comes from the direct or indirect action of the spacecraft; B2. Arranging the spacecraft to directly or indirectly exert a driving force on the celestial body β, the driving force including one or more of the following forces: First: the force of an artificial explosion carried out by a spacecraft on a celestial body β, whereby at least part of the dispersed matter of the explosion or the material lifted from the celestial body β reaches an escape velocity capable of escaping from the group of celestial bodies; Second: the force generated by the jet engine placed on the celestial body β by the spacecraft, at least part of the matter ejected into space reaches the escape velocity that allows it to escape from the group of celestial bodies; Third: The force generated when celestial bodies or materials outside the celestial body group change their movement mode under the control or influence of the spacecraft and impact the celestial body β; Fourth: The celestial bodies or materials outside the celestial body group change their running mode under the control or influence of the spacecraft, causing them to impact or affect the running mode of other celestial bodies, resulting in the force generated when the other celestial bodies impact the celestial body β; Fifth: Under the control or influence of the spacecraft, celestial bodies or materials outside the celestial body group change their operating mode, through more levels of indirect impact or influence than the fourth level, causing other celestial bodies to impact celestial body β. C. Make the distance between celestial body β and celestial body α fall within the required range at a certain part of the orbit of celestial body β or a point near celestial body α or a point far from celestial body α, and take one or more of the following operations at least for part of the time: Operation 1: When celestial body β is located at a certain part of celestial body β's orbit or on the opposite side of the point near celestial body α, celestial body β is made to bear or increase the driving force that is consistent with its own direction or more consistent with the direction of celestial body β, so as to increase the distance between the part of celestial body β's orbit or the point near celestial body α and celestial body α; Operation 2: When celestial body β is located at a certain part of celestial body β's orbit or on the opposite side of the point near celestial body α, celestial body β is not subjected to or is subjected to a driving force that is contrary to its own direction or even more contrary to the direction of celestial body β; so as to maintain or not significantly reduce the distance between a certain part of celestial body β's orbit or the point near celestial body α and celestial body α; Operation 3: When celestial body β is located at a certain part of celestial body β's orbit or on the opposite side of the far celestial body α point, celestial body β is made to bear or increase the driving force against its own direction or even more against the direction of celestial body β, so as to reduce the distance between a certain part of celestial body β's orbit or the far celestial body α point and celestial body α; Operation 4: When celestial body β is located at a certain part of celestial body β's orbit or on the opposite side of the far celestial body α point, celestial body β is not subjected to or is subjected to less driving force that is consistent with its own direction or more consistent with the direction of celestial body β; so as to maintain or not significantly increase the distance between a certain part of celestial body β's orbit or the far celestial body α point and celestial body α; Operation 5: When a certain part of the orbit of celestial body β or a point close to celestial body α is on the retreating side and celestial body β is on the advancing side, celestial body β is subjected to a driving force toward the front to increase the distance between the certain part of the orbit of celestial body β or a point close to celestial body α and celestial body α; Operation 6: When a certain part of the orbit of celestial body β or a point far from celestial body α is on the advancing side and celestial body β is on the retreating side, celestial body β is subjected to a driving force toward the front to reduce the distance between the certain part of the orbit of celestial body β or a point far from celestial body α and celestial body α; in: The orbit of celestial body β around celestial body α is simply called celestial body β orbit; When celestial body α is a celestial body set, the position of celestial body α refers to the position of the common center of mass of the several celestial bodies constituting the set; The boundary line is a straight line passing through celestial body α and perpendicular to the line connecting celestial body α to a certain part of the orbit of celestial body β. The side of the line where celestial body β is located is the same side, and the other side of the line is the opposite side. The direction of celestial body β relative to celestial body α at a certain moment or the direction of the tangent line of the orbit at the point where celestial body β is located is the direction of celestial body β; "Conforming to the celestial body's β trend" means that a certain direction is the same as or close to the celestial body's β trend, or the angle between them is less than a right angle; "more consistent with the celestial body's β trend" means that a certain direction is closer to the celestial body's β trend, or the angle between them is smaller; Against the celestial body β trend means that a certain direction is contrary to or basically contrary to the celestial body β trend, or the angle between them is greater than a right angle. More against the celestial body β trend means that a certain direction is more contrary to the celestial body β trend, or the angle between them is closer to a right angle. Taking the straight line passing through celestial body α and parallel to the trend X as the dividing line, when celestial body β is around celestial body α, the side where the direction of motion of celestial body β relative to celestial body α is mainly in line with the trend X is the advancing side, and the side where the direction of motion of celestial body β relative to celestial body α is mainly away from the trend X is the retreating side; The direction that is consistent with or substantially consistent with trend X is the front direction, and the direction opposite to the front direction is the back direction: D. At least part of the time, if a certain part, a point near the celestial body α, or a point far from the celestial body α of the orbit of the celestial body β is temporarily not located at the desired advancing side, retreating side, or other desired position, wait for the part, the point near the celestial body α, or the point far from the celestial body α to precess along with the celestial body β around the orbit of the celestial body α to the desired advancing side, retreating side, or other desired position, and then perform one or more of the methods in B above or the multiple operations in C.
2. The method according to claim 1, wherein the orbital precession of the celestial body β around the celestial body α in D is caused by the space environment around the celestial body group.
3. The method according to claim 1, wherein the driving force causes the celestial body β in D to precess around the orbit of the celestial body α, including one or more of the following methods: Method 1: Make the driving force on celestial body β when it orbits celestial body α have a component toward the inner side of the orbit of celestial body β, so that the orbit will have the same precession or precession tendency as the direction of celestial body β orbiting celestial body α; Method 1: Make the driving force on celestial body β when it orbits celestial body α have a component toward the outside of the orbit of celestial body β, so as to cause the orbit to precess or have a precession tendency in the opposite direction to the direction of celestial body β orbiting celestial body α.
4. The method according to claim 3, wherein the celestial body group is an asteroid-asteroid system, or a comet-comet system, or a comet-asteroid system, or a planet-satellite system.
5. The method according to claim 4, wherein the celestial body group is an earth-moon system, celestial body α refers to the earth, celestial body β refers to the moon, and the perigee α point or the apogee α point of the orbit of celestial body β around celestial body α refers to the perigee or apogee of the orbit of the moon around the earth.
6. The method according to claim 1, wherein the driving force directly borne by the celestial body β is the force of an artificial explosion on the celestial body β, and at least part of the dispersed matter of the explosion or the material lifted from the celestial body β reaches an escape velocity capable of escaping from the celestial body group.
7. The method according to claim 1, wherein the driving force directly borne by the celestial body β is generated by a jet engine, and at least part of the matter ejected into space by the jet engine reaches an escape velocity capable of escaping from the celestial body group.
8. A method according to claim 1, wherein the driving force directly borne by the celestial body β is generated by the impact force of a celestial body or material outside the celestial body group, and the movement mode of the celestial body or material outside the celestial body group before the impact is or has been controlled or influenced by the aerospace device.
9. A method according to claim 1, wherein the driving force directly borne by the celestial body β is generated by the impact force of a celestial body or substance outside the celestial body group, and the movement mode of the celestial body or substance outside the celestial body group before the impact is or has been subjected to an earlier direct or gradual collision or contact or adhesion or attraction or influence by another celestial body or substance, and the other celestial body or substance has been controlled or influenced by the spacecraft before or earlier.
10. The method according to claim 1, wherein the celestial body α is also subjected to a driving force in a direction consistent with the trend X for part of the time.