Method and system for changing distance and velocity of space object relative to celestial body

Abstract

A method and system for changing the distance and velocity of a space object relative to a celestial body. The method comprises: making different space objects or space object groups, which are relatively far away each other, be connected to each other and pulled by a tether to orbit around and gyrate with each other, wherein the tether synchronously gyrates along with the space objects or space object groups, and provides a centripetal traction force required by the space objects or space object groups to orbit around each other, so as to form a gyratory gyration system, and the gyration system or the center of mass thereof also moves near a celestial body; and making a carried object connect, dock or moor an object of the system at an appropriate position or enter into a certain object of the system, such that the carried object runs along with the system, or making the carried object detach from the system at an appropriate position, such that the distance between a celestial body and the carried object and the carrying gyration system when or after carrying the carried object changes compared with that between the celestial body and the gyration system not carrying the carried object or before carrying the carried object, or the movement velocity, direction, momentum or orbit of the carried object and the carrying gyration system when or after carrying the carried object changes compared with those of the gyration system not carrying the carried object or before carrying the carried object.

Description

Method and system for changing the distance and speed between space objects and celestial bodies Technical Field

[0001] This technology belongs to aerospace engineering technology. Background Art

[0002] Since Tsiolkovsky proposed the rocket-powered theory of spaceflight in the early 20th century, space exploration technology has made significant progress. Using rocket technology to deliver payloads to near-Earth space requires a takeoff weight dozens of times greater than the payload, making landing and takeoff on the moon or other planets even more expensive. The concept of a "space elevator" was once proposed to reduce the cost of transporting cargo or personnel into space, but fundamental material technology barriers have prevented its implementation. Now, space exploration has evolved toward "space engineering" and "flight-based" operations. As researchers consider exploring or exploring the moon and asteroids, frequent takeoffs and landings on these celestial bodies are essential, creating an urgent need for more efficient and fuel-efficient space lift technologies.

[0003] Summary of the Invention

[0004] The purpose of the present invention is to provide a more efficient new aerospace technology, which first includes a method for changing the distance and speed between a space object and a celestial body, including:

[0005] Different space objects or groups of space objects that are far apart are connected and pulled by ropes, and revolve around each other. The ropes synchronously accompany the revolving and provide the traction centripetal force required for the revolving, thus forming a revolving system; at the same time, the revolving system or its center of mass moves near the celestial body.

[0006] The motion of the gyroscopic system or its center of mass near the celestial body may include orbiting the celestial body, moving away from the celestial body, moving toward the celestial body, or passing by the celestial body.

[0007] The gyroscopic system's gyroscopic or rotational period may be different from or significantly shorter than its orbital period.

[0008] After excluding the elastic or plastic deformation of the rope, the rope pulling length should generally remain unchanged. Unless there is a special adjustment need, the rope retraction and release operation should be carried out.

[0009] Existing rocket or jet technology can easily solve the problem of this gyro system entering space and being deployed. The space object constituting the gyro system can be propelled by its own jet engine or by other aircraft to the desired location and have the desired direction and speed.

[0010] It is obvious that when the space objects of the gyroscopic system orbit each other, the distance or relative speed between each object or the connection point of the connecting object or rope and the celestial body will change.

[0011] The method further comprises:

[0012] Make the other space object to be ridden on the gyroscopic system, i.e., the riding object, connect or hang or moor with the object of the system at an appropriate position, or enter into an object of the system and run with it, i.e., ride the system; or make the space object riding on the gyroscopic system detach from the object or rope in the system at an appropriate position, hang or moor, or come out from an object of the system, i.e., detach from the riding system, so that the distance or orbital altitude of the space object from the celestial body during or after riding is increased or decreased compared with not riding or before riding, or the speed, direction, momentum or orbit of the riding object relative to the celestial body is changed during or after riding compared with not riding or before riding, or correspondingly, the speed, direction, momentum or orbit of the gyroscopic system relative to the celestial body is also changed during or after riding compared with not riding or before riding; wherein the object is a space object.

[0013] In other words, the direction of motion or speed of the cyclonic system or its distance or orbit from the celestial body should be changed, or will be changed, when compared with before or after boarding, or when compared with before or after boarding.

[0014] in:

[0015] Celestial bodies are natural celestial bodies in space, such as planets, asteroids, satellites, comets, stars, etc.;

[0016] The celestial body may be one or more, for example, the orbital system may revolve around the planet and its satellites;

[0017] A space object or object may be a space device, such as a spacecraft, a space person, a space station, a cargo vehicle, a storage facility, or a counterweight facility with a large mass, or a docking facility or mooring connection facility or other functional device, and may also include an ore body or other object;

[0018] A space object group consists of multiple space objects or devices connected to each other at close distances. Close distances may refer to no more than a few hundred meters; relatively far distances refer to distances of several thousand meters or even tens, hundreds of kilometers or more.

[0019] The center of mass of a gyroscopic system refers to the total celestial mechanical mass center or center of gravity of all objects connected by the ropes in the system.

[0020] The method may also include: the space object of the system is or is provided with a mooring device, or is or is provided with a mechanism for connecting a pulling rope or connecting to other space objects, and the device or mechanism is or is an aircraft mooring platform or a hook or a ring or a clamp or a card or a claw or an electromagnetic suction cup or an interface or a connector or a robotic arm or a boom or a robotic hand, or is or is provided with a device for retracting and releasing a rope, and the device or mechanism is used to support the riding object to board or detach from the boarding.

[0021] If necessary, the ride object may also have a device or structure that cooperates with the mooring device or connection mechanism. This device or structure should be compatible with the aircraft mooring platform, hook, ring, clamp, catch, claw, electromagnetic suction cup, interface, connector, robotic arm, boom, or manipulator to facilitate boarding and detaching. For example, the ride object may have a chassis that can match the mooring platform, or a ring, hook, catch, or hole suitable for being hooked, grabbed, or clamped, or a magnetic disk or interface suitable for cooperating with the electromagnetic suction cup or interface of the connection mechanism.

[0022] It should be noted that the gravitational field gradient in interstellar space is much smaller than that on Earth's surface, and the weight of the rope material is also light. Therefore, even with extremely long high-strength ropes, the centrifugal force generated by them is limited as long as the angular velocity of the gyroscopic system is appropriately limited. However, at higher angular velocities, the tangential velocity of the rope's distal end in circular motion is very high, and the centrifugal force generated by its own mass becomes very significant. To reduce this centrifugal force while maintaining the rope's tensile strength, the method described herein can ensure that the rope used for pulling meets one or more of the following characteristics:

[0023] Feature 1: The tensile strength of at least a portion of the rope section closer to the center of mass of the slewing system is significantly greater than the tensile strength of a portion of the rope section further away from the center;

[0024] Feature 2: The average cross-sectional area of ​​at least some of the rope sections closer to the mass center of the gyratory system is significantly larger than the average cross-sectional area of ​​some of the rope sections farther from the center;

[0025] Feature 3: The mass per unit length of at least some of the rope sections closer to the mass center of the gyroscopic system is significantly greater than that of some of the rope sections farther from the center;

[0026] Feature 4: At least a portion of the rope section closer to the mass center of the gyroscopic system contains a significantly larger number of strands than a portion of the rope section further away from the center;

[0027] Feature 5: As the rope extends away from the center of mass of the gyroscopic system, the cross-section of the rope decreases in a step-like or curved shape;

[0028] Feature 6: The ratio of the tensile strength of the material used in the rope section farther away from the mass center of the slewing system to the specific gravity of the material is significantly greater than the ratio of the tensile strength of the material used in some rope sections closer to the center to the specific gravity of the material.

[0029] When the riding object enters the riding position of the swing system, its speed and position should be close to, consistent with, or coordinated with the speed and position of the object or rope at that position in advance.

[0030] That is, the riding object should move to the intersection point at the same time as the object or rope at the riding position for connection or riding, and the riding object should enter the ride roughly in the tangent direction of the circle passing through the intersection point; when the moving direction, speed or position of the riding object meets the requirements, it will leave the ride.

[0031] When the original speed of the riding object is lower than the center of mass of the rotating system, it should approach the riding position of the system from the front and rotate backward; when the original speed of the riding object is higher than the center of mass of the rotating system, it should approach the riding position of the system from the back and rotate forward.

[0032] The method may also include: when the riding object or position of the slewing system rotates at a faster speed or has a larger centripetal acceleration, the riding object or aircraft can start the jet engine to perform a short-term corresponding centripetal acceleration or speed regulation operation to more accurately enter the riding position or maintain a closer or contact state for a longer time in order to complete the riding operation.

[0033] In fact, the turning system can continue to turn by relying on inertia before, during, or after the space object joins the system, or before, during, or after the space object leaves the system.

[0034] During the continuous rotation and revolution of the system, the system may not need to rely on or mainly not need to rely on any jet engine, that is, the objects in the system or the space objects on board do not need or basically do not need to start the jet engine to provide power.

[0035] Because the space objects in the gyroscopic system orbit each other while revolving around a celestial body, their or the rope ends' speed or direction relative to the celestial body constantly changes, causing the speed, direction, or momentum of the space objects riding on them to also change relative to the celestial body. If the gyroscopic system's space objects or rope ends orbit at a high speed, the speed, direction, or momentum of the space objects riding on them relative to the celestial body will also change significantly.

[0036] The riding space object may include multiple parts. When entering or leaving the ride, different parts of the riding space object may enter or leave the ride at different times or movement angles.

[0037] It should be noted that during the operation of the gyro system, the objects orbiting each other may be moving away from the star, while others may be moving toward the star. The gravitational potential energy or mechanical energy added to the objects moving away from the star (including space objects moving away on the gyro system) can be derived from the gravitational potential energy or mechanical energy lost by the objects moving toward the star (including space objects moving toward the star on the gyro system). This energy can be transferred via the traction rope. Therefore, in general, after the system is deployed and started, its operation mainly relies on inertia and centripetal motion, and it requires almost no or only a small amount of rocket engine thrust for adjustment to continue. This is precisely one of the key points of this technology.

[0038] The method may further include one or more of the following methods of changing the trajectory of the riding object:

[0039] Method 1 includes: the gyroscopic system containing a space object near a celestial body, wherein the space object on board detaches from the gyroscopic system at a speed higher than the center of mass of the gyroscopic system, enters a higher orbit or detaches from the celestial body's orbit, and the gyroscopic system or another space object therein orbits or descends to the celestial body at a lower orbital altitude;

[0040] Method 2 includes: the gyroscopic system containing a space object in the vicinity of a celestial body, wherein the space object on board detaches from the gyroscopic system at a speed lower than the center of mass of the gyroscopic system, orbits or descends to the celestial body at a lower orbital altitude, and the gyroscopic system or other space objects therein enter a higher orbit or detach from the celestial body's orbit;

[0041] Mode 3 includes: a space object near a celestial body rides on a gyroscopic system orbiting the celestial body and then leaves at a lower relative stellar speed, orbiting or descending to the celestial body at a lower orbital altitude, so that the gyroscopic system or other space objects therein are able to enter a higher orbit or leave the celestial body's orbit;

[0042] Mode 4 includes: a space object near a celestial body, riding in a circling system orbiting the celestial body and then leaving at a higher relative stellar speed, entering a higher orbit or leaving the celestial orbit, and the circling system or other space objects therein orbiting or descending to the celestial body at a lower orbital altitude.

[0043] Taking into account long-term stable operation, the method may also include: arranging that during the operation of the cyclotron system or within a certain period of time, a space object can ride on the cyclotron system to increase its distance from the celestial body, and a space object can also ride on the cyclotron system synchronously or sooner or later to reduce its distance from the celestial body.

[0044] This method may also include: arranging that during the operation of the cyclotron system or within a certain period of time, a space object, i.e., a space object on board, rides the cyclotron system to increase its speed relative to the celestial body, and simultaneously or sooner or later a space object, i.e., a space object on board, rides the cyclotron system to reduce its speed relative to the celestial body.

[0045] The method may also include: arranging that during the operation of the cyclotron system or after a certain period of operation, the gravitational field potential energy or mechanical energy (including kinetic energy) of the celestial body increased by the space object ascending by the cyclotron system is equal to or similar to the gravitational field potential energy or mechanical energy of the celestial body reduced by the space object descending by the cyclotron system.

[0046] The method may include: arranging that during the operation of the gyro system, the gyro direction of the system, ie the rotation direction, is consistent with or opposite to the direction of its revolution around the celestial body.

[0047] The method of the present technology may also include: arranging the circling direction of the circling system, i.e., the rotation direction, to be consistent with the direction of its revolution around the celestial body, arranging the appropriate orbital height, appropriate rotation speed, and appropriate distance between a space object in the system and the center of mass of the system for the circling system to allow the space object to approach the surface of the celestial body in a short time to determine its position or vicinity, and at this time, its relative running speed with the surface is as small as possible, so as to facilitate the passengers of the space object to disembark and land or be transported to the surface of the celestial body, or to facilitate the space object to receive passengers that have left the surface of the celestial body.

[0048] This is also a method for transporting objects to or near a specific location on a celestial body's surface, or receiving objects from or near a specific location on a celestial body's surface. Specifically, the system's rotational direction, or rotational direction, can be aligned with its orbital direction around the celestial body. By arranging the appropriate orbital altitude, rotational speed, and distance between the space object within the system acting as a transporter and the system's center of mass, the transporter can be brought within a short distance of a specific location on or near a celestial body's surface, while maintaining a minimum relative speed relative to the surface to facilitate transport or reception. The transporter is essentially the object within the system that will connect with the object to be transported.

[0049] The method may further include: the gyroscope system can receive the ride object from a certain position or vicinity on the surface of the celestial body, and then transport it to another certain position or vicinity on the surface of the celestial body and place it down. This can be used to support transportation on complex terrain surfaces of celestial bodies.

[0050] The method may further include: during the process of the space object riding on the rotation system, one object may be allowed to leave the ride and another object may be allowed to ride at the same location or nearby of the system simultaneously, and the masses of the two objects may be similar.

[0051] This is conducive to keeping the orbital height and operating state of the system or center of mass basically unchanged, while keeping the rotation speed and state of the system basically unchanged.

[0052] The method may further include: when the space object is riding on the gyroscopic system, the object's separation from or entry into the system is carried out when, or as far as possible, a point on the riding system approaches or passes through the orbital track or vicinity of the system's center of mass as the system rotates.

[0053] This helps keep the orbital trajectory of the system's center of mass essentially unchanged, and allows space objects to disembark and enter at this location without requiring synchronization. For example, a gyro system could be deployed near a low-Earth orbit space station, accompanying it in its orbit. A cargo or crewed spacecraft arriving at the station could then be boarded and returned to the gyro system's original location or equipment after it returns to the vicinity of the station.

[0054] The method may also include arranging multiple gyroscopic systems, whose orbits may or may not be in the same plane, and whose orbital directions may be the same or different, but whose orbital altitudes may be different, or whose tangential velocities as they pass through their orbital periastron may be different. This facilitates overcoming the limitations of maximum rope length or tension, and by utilizing a multi-stage relay lifting or lowering method, the distance between the space object and a celestial body, or the speed or direction relative to the celestial body, can be varied over a wide range.

[0055] The method of the invention may also include shortening or lengthening the ropes of the gyratory system for pulling different objects over long distances, thereby speeding up or slowing down the angular velocity of the system's rotation.

[0056] The method may further include: long-distance pulling of ropes and objects of different types within the rotating system, wherein the macroscopic distribution unfolded during rotation may be linear, triangular, Y-shaped, cross-shaped, M-shaped, radial, polygonal, ring-shaped, or mesh-shaped, so as to increase the operational stability or working efficiency of the system.

[0057] The method may further include: wherein the space object may be a rope control device or a system control device with a jet engine and the ability to actively move in space, and may be capable of adjusting the position or operation of the rope or system.

[0058] The method may further include: the rope can be connected to, disconnected from, or pulled by another space device through a rope control device or a system control device connected thereto.

[0059] The method may further include: wherein the connection or disconnection of the rope to the space device can be performed directly by engaging or releasing a rope connector on the rope with a device connector on the space device.

[0060] The method may further include: some of the space objects or rope control devices may have the function of lengthening, shortening or storing the rope.

[0061] This method may further include: one of the space objects is a counterweight having a certain mass or inertia. The counterweight can balance the space object at the other end of the rope during the rotation. The counterweight can also be a space station, a space capsule, a rope control device, or a system control device. The counterweight preferably has a large mass or inertia.

[0062] The method may further include: the rope may be composed of multiple parallel sub-ropes with a certain gap, and short connecting ropes or short connecting devices are distributed between the sub-ropes at intervals. This can improve the safety of the rope in the event of an accident.

[0063] The method may further include wherein the rope may contain communication conductors or power conductors.

[0064] The space object described in this method may have warning lights, positioning corner reflectors, or optical or electromagnetic positioning signal generators distributed at intervals along the rope. This can facilitate other spacecraft in determining the spatial positions of various components of the gyroscopic system, thereby improving navigation efficiency and safety.

[0065] The present technology may also include a system for the method, including: different space objects or groups of space objects, which are connected and pulled to each other by ropes at a long distance, and can orbit around each other in space to allow other space objects to board or detach.

[0066] The space object of the system may be or be provided with a mooring device, or be or be provided with a mechanism for connecting a pulling rope or connecting to other space objects. The device or mechanism may be an aircraft mooring platform or a hook or a ring or a clamp or a card or a claw or an electromagnetic suction cup or an interface or a connector or a robotic arm or a boom or a robotic hand, or be or be provided with a device for retracting and releasing a rope.

[0067] The rope described in this system or method can refer to a rope, a cable, a chain, a wire, a cable, a long chord, a long thin rod or other tensile materials. It can be a single piece or multiple pieces, a single strand or multiple strands, and the material can be metal or non-metal wire or glass fiber or carbon fiber or other fibers.

[0068] The rope of the system may meet one or more of the following characteristics:

[0069] Feature 1: The tensile strength of at least a portion of the rope section closer to the center of mass of the slewing system is significantly greater than the tensile strength of a portion of the rope section further away from the center;

[0070] Feature 2: The average cross-sectional area of ​​at least some of the rope sections closer to the mass center of the gyratory system is significantly larger than the average cross-sectional area of ​​some of the rope sections farther from the center;

[0071] Feature 3: The mass per unit length of at least some of the rope sections closer to the mass center of the gyroscopic system is significantly greater than that of some of the rope sections farther from the center;

[0072] Feature 4: At least a portion of the rope section closer to the mass center of the gyroscopic system contains a significantly larger number of strands than a portion of the rope section further away from the center;

[0073] Feature 5: As the rope extends away from the center of mass of the gyroscopic system, the cross-section of the rope decreases in a step-like or curved shape;

[0074] Feature 6: The ratio of the tensile strength of the material used in the rope section farther away from the mass center of the slewing system to the specific gravity of the material is significantly greater than the ratio of the tensile strength of the material used in some rope sections closer to the center to the specific gravity of the material.

[0075] This helps to reduce the centrifugal force generated by the rope material itself and improve the ability of the slewing system to withstand the centrifugal force during rotation.

[0076] The space object of the system can be a rope control device or a system control device with a jet engine, which has the ability to actively move in space and can adjust the position or operation of the rope or system.

[0077] The system may include wherein the rope has a rope control device or system control device coupled thereto.

[0078] The system may include a space object or a rope control device having a mechanism for lengthening, shortening or storing the rope.

[0079] The system may include a plurality of cyclotron systems having orbits at different altitudes.

[0080] The system may include one in which the space object is a counterweight or a spacecraft mooring platform having a certain mass or inertia.

[0081] The system may include wherein the counterweight or vehicle mooring platform is also a space station or a space capsule or a rope control device or a system control device.

[0082] The system may further include the following: the rope is composed of a plurality of sub-ropes arranged in parallel with a certain gap between them, and connecting short ropes or short connecting devices are distributed at intervals between the sub-ropes.

[0083] The system may further include wherein the cord contains communication conductors or power conductors.

[0084] The system may further include the object having or the rope having warning lights or positioning corner reflectors or light or electromagnetic wave positioning signal generators or solar cells distributed at intervals.

[0085] The system may also include, among others: ropes for pulling different space objects at long distances within the rotation system and each space object, the macroscopic distribution of which unfolded during rotation may be linear, triangular, Y-shaped, cross-shaped, M-shaped, radial, polygonal, ring-shaped, or mesh-shaped, wherein the different space objects may be a plurality of space stations connected by suspension ropes distributed in a polygonal or ring-shaped manner, wherein the different space objects may also be or have a plurality of devices or instruments or rope control devices or system control devices for connecting ropes or other space objects, thus forming a space transportation system with multiple loading points.

[0086] The different space objects in the system may be or have a plurality of devices or apparatuses or rope control devices or system control devices for connecting ropes or other space objects.

[0087] The system may also include: the orbit and period of the system's center of mass are the same as or similar to those of another space station or satellite, so as to facilitate helping the spacecraft enter, approach or leave the orbit of another space station or satellite.

[0088] The system can also include: the system's rotation direction, i.e., its rotation direction, is consistent with its revolution around the planet and the planet's rotation direction, and the difference between the system's revolution speed and the linear velocity of the transport boarding position during the system's rotation is slightly less than or close to the linear velocity of the planet's rotational surface. This can form a transportation system that facilitates transportation from space to the asteroid's surface, or vice versa.

[0089] The system may also include: multiple gyroscopic systems, whose orbits are in the same plane and have the same orbital direction, but the heights of the orbits are different, so as to facilitate the use of multi-stage relay lifting or lowering to change the distance between space objects and celestial bodies over a larger range.

[0090] Using traditional jet engine technology, spacecraft require powerful propulsion for round-trip flights near celestial bodies, consuming several times the energy. For multiple round trips like airline flights, the energy consumption is even greater, making future interstellar exploration difficult. The method and system of the present invention effectively utilizes the gravitational field potential and mechanical energy of a spacecraft undergoing multiple round trips, reducing required energy consumption to a minimum—a fraction to a few tenths of the original amount. This resolves previously insurmountable power constraints, bringing about innovation and advancement in aerospace propulsion technology and spaceflight methods, and offers significant technical benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0091] FIG1 is a schematic diagram of the operation of a gyroscope system according to embodiment 1 of the present invention;

[0092] FIG2 is a schematic diagram of the partial operation of the gyroscopic system according to Example 2 of the present invention;

[0093] FIG3 is a schematic diagram of the operation of the gyroscopic system according to Example 3 of the present invention;

[0094] FIG4 is a schematic diagram of a gyratory system according to embodiment 4 of the present invention;

[0095] FIG5 is a schematic diagram of a gyratory system according to embodiment 5 of the present invention;

[0096] FIG6 is a schematic diagram of the main rope layout of the slewing system of Example 6 of the present invention;

[0097] FIG7 is a schematic diagram of the main rope layout of the slewing system of Example 7 of the present invention.

[0098] FIG8 is a schematic diagram of a gyratory system according to embodiment 10 of the present invention;

[0099] Among them, 11 is a rope; 12 is a counterweight; 13 is a space object - a spacecraft riding on the gyro system; 14 is another cargo hold riding on the gyro system; 15 is a rope control device; 16 is the instantaneous motion direction of the gyro system's center of mass; 17 is the surface of a celestial body; 18 is the instantaneous position of the gyro system's center of mass; 19 is the instantaneous direction of the counterweight movement; 21 is a ring connecting other space objects; 31 is a spacecraft that is leaving the gyro system; 32 is a spacecraft that is taking over the system; 33 is a space station; 34 is the rotation direction of the gyro system and the object relative to the system's center of mass; 35 is the motion trajectory of the rope control device relative to the system's center of mass; 41 is the direction of the celestial body's rotation; 42 is the cargo sent to the surface of the celestial body; and 81 is the mass center of the gyro system.

[0100] Specific implementation methods

[0101] The following is a detailed description with reference to the accompanying drawings.

[0102] Example 1 illustrates a system and specific method for assisting a spacecraft in moving away from or approaching a celestial body. Referring to Figure 1 , one of the space objects comprising the gyration system is a relatively large counterweight 12. A spacecraft 13, aboard the gyration system, is remotely pulled by a rope 11 through a rope control device 15, creating a mutually orbiting gyration. The rope synchronizes the gyration in the same direction as the orbit. Unless the system is adjusted, the pull length remains essentially unchanged, providing the centripetal force required for the mutual orbit. Here, the rope control device 15 acts as a mooring station for the spacecraft. The gyration system's center of mass 18 orbits around an asteroid 17 under the influence of gravity, with its gyration plane parallel to its orbital plane and its rotation direction aligned with its orbital direction.

[0103] The system in this embodiment utilizes the changing distance between the rope control device and a celestial body during rotation to increase or decrease the altitude of a spacecraft. For example, a spacecraft that has just taken off from the surface of a celestial body can adjust its speed to approximately the same as the rope control device when the rope control device 15 is closer to the celestial body, connect to it, and simultaneously shut down the engine that originally powered the spacecraft. As the spacecraft moves away from the celestial body, it can then disengage from it, significantly increasing its flight speed compared to its previous landings. Similarly, other spacecraft preparing to land on a celestial body can also board this gyroscopic system when they are far from the celestial body and disengage when they are closer. This allows the spacecraft to get closer to the celestial body, achieve a lower speed, make landing easier, and save significant engine fuel.

[0104] During this process, all devices, including the rope control system and counterweight, do not require the use of jet engines. Of course, to maintain the long-term stable operation of the gyroscopic system, that is, to keep the system's orbital trajectory within a reasonable range, it is best to arrange a basic balance between the number of ascending passengers and the number of descending passengers, such as on a round-trip flight. If the spacecraft is a sightseeing boat, originally only suitable for flying to an altitude of 150 kilometers, it can now board the system's rope control system at this altitude (the system's low point), ascend to an altitude of 250 kilometers, return to 150 kilometers, disengage the system, and then descend, allowing passengers to experience a higher perspective at a low cost. If the system's position, speed, altitude, rope condition, or other parameters are not ideal or need to be adjusted, the jet engines of devices such as the rope control system and counterweight can be used to perform corrective operations.

[0105] In this embodiment, the slewing system also includes a cargo hold 14 directly connected to a rope. Both the counterweight and rope control system include a jet power unit and a rope retraction and extension mechanism to adjust the system's operating parameters when necessary. Appropriately shortening or lengthening the long-distance rope can increase or decrease the slewing system's rotational angular velocity.

[0106] The basic structure and method of use of the slewing system of Example 2 (see Figure 2) are essentially the same as those of Example 1. Its rope control device 15 is connected to the counterweight via rope 11, with the counterweight facing each other. To facilitate connection to an incoming spacecraft, the rope control device and certain locations on the rope are equipped with connecting rings 21, which are used in conjunction with hooks, clamps, or other devices on the spacecraft. The rope control device may also include a robotic arm, hooks, chucks, and other devices.

[0107] Example 3 relates to a gyroscope system serving a large space station. Referring to Figure 3 , the system's composition and operational methods are substantially similar to those of Example 1, where 35 represents the trajectory of the tether control device relative to the system's center of mass. It is desired that the system's center of mass maintain the same orbital and periodicity as another space station 33, operating synchronously and concurrently, enabling repeated shuttle transport between low altitude and the space station. Specifically, when the tether control device 15, carrying the return spacecraft 31, approaches a low point A on the surface 17 of a celestial body, the return spacecraft detaches, and the ascending spacecraft 32 takes over (simultaneously), with the two spacecraft having similar masses. Furthermore, it is required that the ascending spacecraft 32 detaches to the space station or rejoins the return spacecraft when, or as close as possible to, the system's center of mass orbit (point B) is reached by the system's rotational point (the tether control device). This helps maintain the system's center of mass orbital and operational state essentially unchanged, or maintains a relatively close distance from the space station.

[0108] Example 4 is a system and method for delivering or receiving objects to or near a specific location on a celestial body. Specifically, the gyroscopic system's rotational direction and revolution direction 16 are aligned with the celestial body's rotational direction 41. Furthermore, the gyroscopic system's orbital altitude, rotational speed, and distance between the tether control device 15 (transportation mechanism) and the system's center of mass 18 are appropriately configured. This allows the tether control device to approach a specific location (C) on the celestial body's surface, while maintaining a minimum relative speed relative to the planet's surface. This facilitates the delivery of cargo 42 and the receipt of cargo hold 14, both of which are considered passenger objects. Figure 4 shows the gyroscopic system's state and the changes in the positions of cargo hold 14 and cargo 42 on the celestial body over time, from A to B, then to C, and finally to D.

[0109] Example 5, referring to Figure 5 , features a gyroscope system comprising a counterweight 12 with a control device and two space stations 33 with moorings, connected by three ropes to form a triangular system. The system's rotation direction 19 is the same as the direction 16 of revolution around a celestial body 17, and its rotation speed is slightly faster than the revolution speed. This system allows passengers aboard spacecraft 13 to periodically approach or retreat from the surface of an asteroid, satellite, or moon. The triangular structure provides a more stable motion for the gyroscope system.

[0110] Example 6 can be seen in Figure 6. The gyroscopic system is in the shape of a hexagonal mesh rope 11, with six space stations 33 with mooring devices distributed at six vertices, and a rope control device 15 and control center located in the middle of the mesh rope. This layout is conducive to improving system safety and greatly improving transportation efficiency.

[0111] Example 7 can be seen in Figure 7. The gyroscopic system has an inverted Y-shaped layout. The counterweight 12 with a central control system and a jet engine is located in the middle of the network as a space station. Three ropes 11 pull three space stations 33 with mooring devices.

[0112] The system and method of Example 8 require the deployment of three gyro systems at different orbital altitudes around the same celestial body. The rotational and orbital directions of each system must be aligned with the celestial body's rotational direction, and the difference in orbital altitude between two adjacent systems must be significantly greater than the sum of the two system radii. When the spacecraft shuts down and approaches the high end of the first-stage gyro system, it disengages and ascends to the low end of the second stage to rejoin. When approaching the high end of the second stage, it disengages again and freely ascends to the low end of the third stage to rejoin, approaching the high end of the third-stage system's rotation; and vice versa.

[0113] In this way, by using a multi-stage relay lifting or lowering method, the limitation of the maximum length of the rope can be broken through, and the distance between the object and the celestial body can be changed over a larger range.

[0114] Example 9 is a gyroscopic system capable of orbiting a planet, asteroid, or satellite (such as the moon) composed of three cables connected in a triangle. Each of the triangles has a top end connected to a space station, spacecraft, a ride device, or a tethering device capable of boarding an incoming spacecraft. The top ends of the triangles rotate at a relatively high tangential velocity. This ride can slow down a spacecraft originally traveling toward a planet, such as the moon, facilitating its retention or landing. Alternatively, it can accelerate a spacecraft departing from a planet, such as the moon, to the point where it exceeds the breakaway velocity. This system can also provide sufficient artificial gravity for the space station and the boarding spacecraft, facilitating long-term personnel presence.

[0115] The gyration system of Example 10 (see Figure 8) consists of a space station 33 pulled by a rope 11 and a rope control device 15 (also serving as a mooring device). The cross-sectional diameters or areas of different sections of the rope are different. The average cross-sectional diameter or area of ​​the rope section 82 closer to the mass center 81 of the gyration system is significantly larger than the average cross-sectional diameter or area of ​​some rope sections 83 farther away from the center. In this way, when the tangential speed of the circular motion of the far end of the rope is very large and the centrifugal force generated by its own mass is very significant, this centrifugal force can be reduced while ensuring the tensile strength of the rope.

[0116] The above are illustrative examples of the method and system of the present invention, which are not intended to limit the scope of protection of the present technology.

Claims

1. A method for changing the distance and speed between a space object and a celestial body, comprising: Different space objects or groups of space objects that are far apart are connected and pulled by ropes to revolve around each other, and the ropes synchronously accompany the revolving and provide the traction centripetal force required for the revolving, so as to form a revolving revolving system; at the same time, the revolving system or its center of mass moves near the celestial body; Make the other space object to be ridden on the rotary system, i.e., the riding object, connected, hung or moored with the object of the system at an appropriate position, or enter into an object of the system and run with it, i.e., ride the system; or make the space object riding on the rotary system disconnect, hung or moored from the object or rope in the system at an appropriate position, or come out from an object of the system, i.e., leave the riding system, so that the distance or orbital height of the space object from the celestial body during or after riding is increased or decreased compared with not riding or before riding, or the speed, direction, momentum or orbit of the riding object relative to the celestial body is changed during or after riding compared with not riding or before riding, or correspondingly, the speed, direction, momentum or orbit of the rotary system relative to the celestial body is also changed during or after riding compared with not riding or before riding; wherein the object is a space object.

2. [Corrected 08.10.2024 in accordance with Rule 26] A method according to claim 1, comprising: The space object of the system is either or has a mooring device, or is or has a mechanism for connecting towing ropes or connecting to other space objects. The device or mechanism is either an aircraft mooring platform or a hook or a ring or a clamp or a card or a claw or an electromagnetic suction cup or an interface or a connector or a mechanical arm or a boom or a manipulator, or is or has a device for retracting and releasing ropes, and the device or mechanism is used to support the boarding or detachment of the riding object.

3. According to the method described in claim 2, the riding object also has a device or structure that cooperates with the mooring device or connecting mechanism, and the device or structure can match the aircraft mooring platform or hook or ring or clamp or card or claw or electromagnetic suction cup or interface or connector or mechanical arm or boom or manipulator to facilitate boarding or detaching.

4. According to the method of claim 1, the rope for pulling meets one or more of the following characteristics: Feature 1: The tensile strength of at least a portion of the rope section closer to the mass center of the slewing system is significantly greater than the tensile strength of a portion of the rope section further away from the center; Feature 2: The average cross-sectional area of ​​at least part of the rope section closer to the mass center of the gyroscopic system is significantly larger than the average cross-sectional area of ​​part of the rope section farther from the center; Feature 3: The mass per unit length of at least part of the rope section closer to the mass center of the gyroscopic system is significantly greater than that of part of the rope section farther from the center; Feature 4: At least part of the rope section closer to the mass center of the gyroscopic system contains a significantly larger number of rope strands than part of the rope section farther from the center; Feature 5: As the rope extends away from the mass center of the gyroscopic system, the cross-section of the rope decreases in a step-like or curved shape; Feature 6: The ratio of the tensile strength of the material used in the rope section farther away from the mass center of the gyroscopic system to the specific gravity of the material is significantly greater than the ratio of the tensile strength of the material used in some rope sections closer to the center to the specific gravity of the material.

5. The method according to claim 1, comprising: When the riding object or position of the cyclotron system rotates faster or has a larger centripetal acceleration, the riding object or aircraft can start the jet engine to perform a short-term corresponding centripetal acceleration or speed regulation operation to more accurately enter the riding position or maintain a closer or contact state for a longer time in order to complete the riding operation.

6. The method according to claim 1, comprising: When the riding objects are arranged to ride in the rotating system, they are moved from their original positions to different positions. The movement is carried out by moving, sliding, sliding, rolling on pulleys, or moving by a winch mechanism, or by being pulled individually or in coordination by ropes from one or more different space objects in the rotating system, or by being propelled by its own jet engine power.

7. The method according to claim 5, comprising: Arrange the riding object to first ride to the space object or the position of the pulling rope section in the gyroscopic system that is closer to the system center of mass or the system center of mass, and then move to the space object or the position of the pulling rope section that is farther from the system center of mass.

8. The method according to claim 1, comprising one or more of the following steps of changing the trajectory of the riding object: Method 1, including: The gyroscopic system containing a space object in the vicinity of a celestial body, wherein the space object on board is separated from the gyroscopic system at a speed higher than the center of mass of the original gyroscopic system, enters a higher orbit or leaves the orbit of the celestial body, and the gyroscopic system or other space objects therein orbit around or descend to the celestial body at a lower orbital altitude; Mode 2, including: the gyroscopic system containing a space object near a celestial body, the space object on board detaches from the gyroscopic system at a speed lower than the center of mass of the original gyroscopic system, orbits or descends to the celestial body at a lower orbital altitude, and the gyroscopic system or other space objects therein enter a higher orbit or detach from the orbit of the celestial body; Mode 3 includes: a space object near a celestial body rides on a gyroscopic system orbiting the celestial body and then leaves it at a lower relative speed to the celestial body, orbiting or descending to the celestial body at a lower orbital altitude, so that the gyroscopic system or other space objects therein can enter a higher orbit or leave the orbit of the celestial body; Mode 4 includes: a space object near a celestial body rides on a circling system orbiting the celestial body and then leaves it at a higher relative speed to the celestial body, entering a higher orbit or leaving the celestial body orbit, and the circling system or other space objects therein orbit around the celestial body at a lower orbital altitude or descend to the celestial body.

9. The method according to claim 1, comprising: It is arranged that during the operation of the cyclotron system or within a certain period of time, a space object rides on the cyclotron system to increase its distance from the celestial body, and simultaneously, or sooner or later, a space object rides on the cyclotron system to reduce the distance from the celestial body; or a space object rides on the cyclotron system to increase its speed relative to the celestial body, and simultaneously, or sooner or later, a space object rides on the cyclotron system to reduce its speed relative to the celestial body.

10. The method according to claim 1, comprising: The cyclotron system's cyclotron direction, i.e., rotation direction, is arranged to be consistent with its revolution direction around the celestial body, and an appropriate orbital height, an appropriate rotation speed, and an appropriate distance between a space object in the system and the system's center of mass are arranged for the cyclotron system's revolution, so that the space object can approach the celestial body's surface in a short time to determine its position or vicinity, and at this time, its relative running speed with the surface is as small as possible, so that it is convenient for the space object's passengers to disembark and land or be transported to the celestial body's surface, or for the space object to receive passengers that have left the celestial body's surface.

11. The method according to claim 10, comprising: The cyclotron system receives the riding object from a certain position or vicinity on the surface of the celestial body, and then transports it to another certain position or vicinity on the surface of the celestial body and places it down.

12. The method of claim 1, comprising: During the process of the space object riding on the maneuvering system, one object leaves the ride and another object enters the ride at the same position or nearby of the system simultaneously.

13. The method of claim 1, comprising: During the process of the space object riding on the cyclotron system, the object leaves or enters the ride when, or as far as possible, the point on the riding system approaches or passes through the orbit of the system's center of mass or near it as the system rotates.

14. The method of claim 1, comprising: Arrange multiple cyclotron systems with different orbital altitudes, and utilize a multi-stage relay lifting or lowering method to change the distance between the space object and the celestial body or the speed or direction relative to the celestial body over a larger range.

15. The method of claim 1, comprising: The cyclotron system is shortened or lengthened to pull the ropes of different objects over long distances to speed up or slow down the angular velocity of the system's rotation.

16. The method according to claim 1, wherein the space object is a rope control device or system control device with a jet engine and the ability to actively move in space, and the rope is connected to, disconnected from, or pulled by another space device through the rope control device or system control device connected to it.

17. The method according to claim 1, wherein: There is a rope connector on the rope, and there is a device connector on the space device. The connection or disconnection of the rope and the space device is directly carried out by combining or loosening the rope connector on the rope and the device connector on the space device.

18. A system for use in the method of claim 1, comprising: Different space objects or groups of space objects, which are connected and pulled to each other by ropes at a long distance, can orbit around each other in space to allow other space objects to get on or off.

19. According to the system of claim 18, the space object of the system is or is provided with a mooring device, or is or is provided with a mechanism for connecting a pulling rope or connecting to other space objects, and the device or mechanism is or is a spacecraft mooring platform or a hanging or a hook or a ring or a clamp or a card or a claw or an electromagnetic suction cup or an interface or a connector or a mechanical arm or a boom or a mechanical hand, or is or is provided with a device for retracting and releasing a rope.

20. The system according to claim 18, wherein the rope for pulling meets one or more of the following characteristics: Feature 1: The tensile strength of at least a portion of the rope section closer to the mass center of the slewing system is significantly greater than the tensile strength of a portion of the rope section further away from the center; Feature 2: The average cross-sectional area of ​​at least part of the rope section closer to the mass center of the gyroscopic system is significantly larger than the average cross-sectional area of ​​part of the rope section farther from the center; Feature 3: The mass per unit length of at least part of the rope section closer to the mass center of the gyroscopic system is significantly greater than that of part of the rope section farther from the center; Feature 4: At least part of the rope section closer to the mass center of the gyroscopic system contains a significantly larger number of rope strands than part of the rope section farther from the center; Feature 5: As the rope extends away from the mass center of the gyroscopic system, the cross-section of the rope decreases in a step-like or curved shape; Feature 6: The ratio of the tensile strength of the material used in the rope section farther away from the mass center of the gyroscopic system to the specific gravity of the material is significantly greater than the ratio of the tensile strength of the material used in some rope sections closer to the center to the specific gravity of the material.

21. The system according to claim 18, wherein the space object is a rope control device or a system control device with a jet engine having the ability to actively move in space and capable of adjusting the position or operation of the rope or system.

22. The system of claim 18, wherein the rope has a rope control device or a system control device coupled thereto.

23. The system of claim 18, comprising: There are multiple cyclotron systems with different orbital altitudes.

24. The system according to claim 18, wherein some of the space objects are counterweights or aircraft mooring platforms having a certain mass or inertia.

25. The system according to claim 18, wherein the rope is composed of a plurality of sub-ropes arranged in parallel with a certain gap, and connecting short ropes or short connecting devices are distributed at intervals between the sub-ropes.

26. The system of claim 18, wherein the rope comprises communication conductors or power conductors.

27. The system according to claim 18, wherein the space object has or the rope is spaced apart with warning lights or positioning corner reflectors or light or electromagnetic wave positioning signal generators or solar cells.

28. The system of claim 18, comprising: The ropes and various space objects that pull different space objects over long distances in the gyratory system have a macroscopic distribution in the shape of a straight line, triangle, Y, cross, M, radial, polygon, ring or net when they gyrate.

29. A system according to claim 18, wherein different space objects can be or have multiple devices or instruments or rope control devices or system control devices for connecting ropes or other space objects.

30. The system of claim 18, comprising: The revolution orbit and period of the center of mass of the system are the same as or similar to those of another space station or satellite, so as to facilitate the spacecraft to enter, approach or leave the orbit of another space station or satellite.

31. The system of claim 18, comprising: The system's rotation direction is the same as its revolution around the celestial body and the celestial body's rotation direction, and the difference between the system's revolution speed and the linear speed of the transport riding position when the system rotates is slightly less than or close to the linear speed of the celestial body's rotation surface.

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