Satellite in-orbit operation method, satellite orbital transfer method and rotating satellite
By obtaining the orbital speed information and the perimeter information of the rotating satellite at the orbital height of 35786km, calculating the difference length information, controlling the rotation speed and direction, the composite control of rotational motion and orbital motion is achieved, and the attitude and orbital deviation in the satellite's orbital operation is solved. The shifting problem improves the flexibility and safety of the orbital altitude and speed of the satellite.
Patent Information
- Application Number
- CN202411654867.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-19
- Publication Date
- 2025-01-07
AI Technical Summary
Existing satellites are affected by external factors during orbit, resulting in attitude and orbital deviation. The orbital speeds of satellites at different orbital heights are different, resulting in inconsistent orbital periods and the space environment becomes crowded, increasing the risk of satellites colliding with each other.
By obtaining orbital speed information at an orbital height of 35786km, combining the perimeter information of the rotating satellite, calculating the differential length information, controlling the rotation speed and direction of the satellite, the composite motion of rotation and orbital motion is realized, and the orbital height and speed of the satellite are adjusted. , maintain its own rotation state, and advance and adjust through the power device to enter the target track.
Flexible control of orbital altitude and speed is achieved, reducing the influence of external factors, allowing satellites of different altitudes and longitude to coexist closer, improving the safety of collision avoidance, and increasing the number of satellites in orbit.
Smart Images
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Abstract
Description
Technical Field
[0001] The present invention relates to the field of aerospace satellites, and in particular to a satellite on-orbit operation method, a satellite orbit change method and a rotating satellite. Background Art
[0002] It can be deduced from Newton's law of universal gravitation that if an object is thrown on the surface of the earth, as long as the speed is greater than 7.9 km / s, the object can escape from the earth's gravity and leave the earth (without considering air resistance, etc.). The farther away from the earth's surface, the slower the escape speed will be. When the escape speed of the object at a certain distance is equivalent to the speed of the earth's traction on the object, the object will move in a circular or elliptical orbit around the earth. This is the basic principle of launching satellites. In the field of aerospace, 7.9 km / s is defined as the first cosmic speed, or the minimum launch speed of a spacecraft.
[0003] As for artificial satellites, their orbits are divided into low orbits and high orbits according to their altitude, and into prograde orbits and retrograde orbits according to the direction of the earth's rotation. Among them, there are some orbits of special significance, such as equatorial orbits, geosynchronous orbits, geostationary orbits, polar orbits and sun-synchronous orbits.
[0004] The role of satellites is to utilize the basic principles of optical or electromagnetic communication technology. According to needs, specially designed artificial satellites receive light or electromagnetic waves in orbit and feed them back to the ground receiving center for information reception and application. They can receive information and feedback for long-term or periodic monitoring of the ground and outer space, they can also provide self-sustaining feedback of self-sending and self-receiving information, and they can also send information from the ground, which is received by satellites and then forwarded back to the ground for relay feedback. Satellites can largely complete communication tasks that are difficult for us to complete on the ground or require greater costs to complete.
[0005] Satellites can be roughly divided into three categories according to different application scenarios: Technical test satellites: The application of satellites usually requires networking. Before the official launch, various tests are carried out under the conditions that can be met on the ground, or some test satellites are launched before networking, thereby greatly reducing the cost and risk of trial and error. Scientific satellites: This type of satellite is used for astronomical observation, such as carrying telescopes and other instruments to observe and study celestial bodies in the universe. Compared with astronomical telescopes on the ground, telescopes can obtain better observation results because there is no interference from the atmosphere in the outer space. Current scientific satellites also carry out space biological experiments and microgravity experiments. Application satellites: This is the most launched category of all satellites. Application satellites can be divided into three categories according to their uses: communication, observation, and navigation: communication satellites are used for international communication satellites, domestic communication satellites, maritime communication satellites, broadcast satellites, tracking and data relay satellites, etc.; observation satellites are used for various earth remote sensing satellites for earth observation, such as meteorological satellites, earth resources satellites, reconnaissance satellites, etc.; navigation satellites are used for positioning, navigation and geodetic benchmark positioning, such as Beidou navigation satellites, GPS, radio positioning satellites and geodetic satellites.
[0006] 1. Due to the uneven distribution of celestial body structure material density and terrain, satellites will be affected by the space environment during operation, such as the perturbation of the non-spherical shape of the earth, the perturbation of atmospheric drag, the perturbation of solar light pressure, the gravitational perturbation of the sun and the moon, etc. These perturbations often affect the orbit of the satellite, affect the attitude of the satellite, and cause the orbit to shift. In view of this situation, the power device of the satellite itself needs to be properly adjusted; 2. Satellites at different orbital altitudes will have different orbital speeds and orbital periods. Only the geostationary orbit satellite located at an altitude of 35,786 km above the equator can achieve relative stillness at this orbital altitude; satellites at other orbital altitudes may have orbital periods that are too short or too long. 3. In order to prevent collisions with other satellites, current satellites in the same orbit or different orbits need to maintain a large safety distance between each other; coupled with the scrapped spacecraft and satellites and space junk remaining in space, the number of space debris is increasing. Currently, the number of debris orbiting the Earth has exceeded 160 million, and these fragments are of different sizes, making the Earth's orbit "crowded", and there are fewer and fewer "blank" areas available for launching new satellites in the future. Summary of the invention
[0007] The purpose of the present invention is to at least solve the problem that the attitude and orbit of existing satellites may be affected by external factors.
[0008] In order to solve the above technical problems, the satellite on-orbit operation method of the present invention comprises: The orbital satellite is at an orbital altitude of 35786 km as first altitude information, and first orbital velocity information of the first altitude information is obtained, where the orbital velocity information is first length information; Acquire second altitude information of the orbit of the rotating satellite, and obtain corresponding second orbital velocity information according to the second altitude information; the second orbital velocity information is second length information; and obtain first difference length information using the first length information and the second length information; Acquire the circumference information of the rotating satellite after one rotation; and obtain the first rotation information of the rotating satellite according to the first difference length information and the circumference information; The rotating satellite is kept rotating in orbit at a first rotation speed; the rotation speed of the first rotation speed is second rotation information, the second rotation information is N times the first rotation information, and N is a natural number, a decimal, or a negative number.
[0009] As a preferred implementation of the satellite on-orbit operation method of the present invention, the second rotation information is second difference length information, and the second difference length information is used to replace the first difference length information.
[0010] As a preferred implementation of the satellite in-orbit operation method of the present invention, the rotation state of the rotating satellite itself is counterclockwise rotation or clockwise rotation.
[0011] As a preferred implementation of the satellite on-orbit operation method of the present invention, the rotation of the rotating satellite and the orbit in which it is located form a composite motion.
[0012] As a preferred implementation scheme of the satellite in-orbit operation method of the present invention, when the orbital altitude of the rotating satellite is higher than the 35786 km, the rotating satellite's own rotation state is counterclockwise rotation; when the orbital altitude of the rotating satellite is lower than the 35786 km, the rotating satellite's own rotation state is clockwise rotation.
[0013] The satellite orbit change method of the present invention comprises any one of the satellite on-orbit operation methods described above, and further comprises: Acquire third height information of the target track, and obtain corresponding third orbital speed information according to the third height information; the third orbital speed information is third length information; and obtain second difference length information by using the third length information and the first length information; Increasing or decreasing the rotation speed of the rotating satellite itself, and making the rotating satellite enter the target orbit; Deriving third rotation information of the rotating satellite according to the second difference length information and the circumference information; The rotating satellite is kept rotating at a second rotation speed in the target orbit; the second rotation speed is fourth rotation information; the fourth rotation information is N times the third rotation information, and N is a natural number, a decimal, or a negative number.
[0014] As a preferred implementation of the satellite orbit change method of the present invention, when the third altitude information of the target orbit is lower than the first altitude information, the rotating satellite rotates clockwise; Before the rotating satellite enters the target orbit, the first rotation speed is increased to a third rotation speed, and the third rotation speed is fifth rotation information; After the rotating satellite enters the target orbit, the third rotation speed is adjusted to the second rotation speed; the rotation speed of the second rotation speed is the fourth rotation information; The fifth rotation information is greater than the fourth rotation information.
[0015] As a preferred implementation of the satellite orbit change method of the present invention, when the second altitude information of the target orbit is higher than the first altitude information, the rotating satellite rotates counterclockwise; Before the rotating satellite enters the target orbit, the first rotation speed is increased to a fourth rotation speed, and the fourth rotation speed is sixth rotation information; After the rotating satellite enters the target orbit, the fourth rotation speed is adjusted to the second rotation speed; the second rotation speed is the fourth rotation information; The sixth rotation information is greater than the fourth rotation information.
[0016] The rotating satellite of the present invention adopts any one of the above-mentioned satellite on-orbit operation methods or any one of the above-mentioned satellite orbit change methods.
[0017] As a preferred embodiment of the rotating satellite of the present invention, the rotating satellite at least includes a satellite body and a power device installed in the satellite body; solar panels are installed on the outside of the satellite body, and the power device has at least propulsion nozzles in the first direction, the second direction and the third direction respectively.
[0018] As a preferred embodiment of the rotating satellite of the present invention, the mass of the satellite body is distributed in the annular periphery of the satellite body from the inside to the outside and from small to large.
[0019] Beneficial Effects The present invention solves the above existing problems and other existing problems not mentioned above and accordingly brings at least the following innovative advantages: The satellite on-orbit operation method, satellite orbit change method and rotating satellite of the present invention adopt an operation mode of allowing the satellite to replace the orbital linear motion with the rotational motion of the orbital points (relative to a certain point of the reference system) in opposite directions and / or allowing the satellite to have a combination of rotational motion and linear motion at the same time, so as to control the satellite's on-orbit altitude and speed, and control the satellite's attitude and change its orbit by controlling the satellite's rotation direction and speed.
[0020] A major advantage of the satellite on-orbit operation method, satellite orbit change method and rotating satellite of the present invention is that it can be stationary at any given relative spatial position, thus avoiding a series of problems caused by uneven gravitational field. Of course, the satellite can combine linear motion and rotational motion to achieve free control of orbit, speed and attitude. And the orbit speed and height of the satellite relative to the intersection of the line connecting the center of the earth and the satellite on the earth's surface can be controlled more flexibly.
[0021] The satellite on-orbit operation method, satellite orbit change method and rotating satellite of the present invention are less affected by external factors in the rotating state, the distance between different satellites can be closer, and the space can accommodate more geostationary orbit satellites at different altitudes and different longitudes and latitudes; in addition to adding more satellites to the orbit, the safety of avoiding collisions between different satellites is also improved. BRIEF DESCRIPTION OF THE DRAWINGS
[0022] Figure 1 This is a flow chart of Embodiment 1 of the present invention; Figure 2 This is a flow chart of Embodiment 2 of the present invention; Figure 3 This is a schematic diagram of the structure of Embodiment 3 of the present invention; Figure 4 is a cross-sectional schematic diagram of embodiment 3 of the present invention; Figure 5 It is a theoretical schematic diagram of the present invention; Figure 6 It is a theoretical schematic diagram of the present invention.
[0023] In the picture: 1. Satellite body, 2. Solar panels, 3. Propulsion nozzle. DETAILED DESCRIPTION
[0024] In order to make the purpose, technical solution and advantages of the technical solution of the present disclosure clearer, the technical solution of the embodiments of the present disclosure will be clearly and completely described below in conjunction with the drawings of specific embodiments of the present disclosure.
[0025] The same reference numerals in the drawings represent the same components. It should be noted that the described embodiments are only part of the embodiments of the present disclosure, but not all of the embodiments.
[0026] Based on the described embodiments of the present disclosure, all other embodiments obtained by those of ordinary skill in the art without creative work are within the scope of protection of the present disclosure.
[0027] The satellite on-orbit operation method of the present invention is as follows: Figure 1 As shown, it includes: the orbital satellite is at an orbital altitude of 35786km as first altitude information, and first orbital speed information of the first altitude information is obtained, and the orbital speed information is first length information; Acquire second altitude information of the orbit of the rotating satellite, and obtain corresponding second orbital velocity information according to the second altitude information; the second orbital velocity information is second length information; and obtain first difference length information using the first length information and the second length information; Acquire the circumference information of the rotating satellite after one rotation; and obtain the first rotation information of the rotating satellite according to the first difference length information and the circumference information; The rotating satellite is kept rotating in orbit at a first rotation speed; the rotation speed of the first rotation speed is second rotation information, the second rotation information is N times the first rotation information, and N is a natural number, a decimal, or a negative number.
[0028] Furthermore, the second rotation information is second difference length information, and the second difference length information is used to replace the first difference length information.
[0029] Furthermore, the rotation state of the rotating satellite itself is counterclockwise rotation or clockwise rotation.
[0030] Furthermore, the rotation of the rotating satellite and the orbit of the rotating satellite form a composite motion.
[0031] Furthermore, when the orbital altitude of the rotating satellite is higher than the 35786 km, the rotating satellite's own rotation state is counterclockwise rotation; when the orbital altitude of the rotating satellite is lower than the 35786 km, the rotating satellite's own rotation state is clockwise rotation.
[0032] The satellite orbit change method of the present invention is as follows: Figure 2 As shown, it includes: the orbital satellite is at an orbital altitude of 35786km as first altitude information, and first orbital speed information of the first altitude information is obtained, and the orbital speed information is first length information; Acquire second altitude information of the orbit of the rotating satellite, and obtain corresponding second orbital velocity information according to the second altitude information; the second orbital velocity information is second length information; and obtain first difference length information using the first length information and the second length information; Acquire the circumference information of the rotating satellite after one rotation; and obtain the first rotation information of the rotating satellite according to the first difference length information and the circumference information; The rotating satellite is kept rotating in orbit at a first rotation speed; the rotation speed of the first rotation speed is second rotation information, the second rotation information is N times the first rotation information, and N is a natural number, a decimal, or a negative number.
[0033] Furthermore, the second rotation information is second difference length information, and the second difference length information is used to replace the first difference length information.
[0034] Furthermore, the rotation state of the rotating satellite itself is counterclockwise rotation or clockwise rotation.
[0035] Furthermore, the rotation of the rotating satellite and the orbit in which it is located form a composite motion.
[0036] Furthermore, when the orbital altitude of the rotating satellite is higher than the 35786 km, the rotating satellite's own rotation state is counterclockwise rotation; when the orbital altitude of the rotating satellite is lower than the 35786 km, the rotating satellite's own rotation state is clockwise rotation.
[0037] Furthermore, it also includes: Acquire third height information of the target track, and obtain corresponding third orbital speed information according to the third height information; the third orbital speed information is third length information; and obtain second difference length information by using the third length information and the first length information; Increasing or decreasing the rotation speed of the rotating satellite itself, and making the rotating satellite enter the target orbit; Deriving third rotation information of the rotating satellite according to the second difference length information and the circumference information; The rotating satellite is kept rotating at a second rotation speed in the target orbit; the second rotation speed is fourth rotation information; the fourth rotation information is N times the third rotation information, and N is a natural number, a decimal, or a negative number.
[0038] Further, when the third altitude information of the target orbit is lower than the first altitude information, the rotating satellite rotates clockwise; Before the rotating satellite enters the target orbit, the first rotation speed is increased to a third rotation speed, and the third rotation speed is fifth rotation information; After the rotating satellite enters the target orbit, the third rotation speed is adjusted to the second rotation speed; the rotation speed of the second rotation speed is the fourth rotation information; The fifth rotation information is greater than the fourth rotation information.
[0039] Further, when the second altitude information of the target orbit is higher than the first altitude information, the rotating satellite rotates counterclockwise; Before the rotating satellite enters the target orbit, the first rotation speed is increased to a fourth rotation speed, and the fourth rotation speed is sixth rotation information; After the rotating satellite enters the target orbit, the fourth rotation speed is adjusted to the second rotation speed; the second rotation speed is the fourth rotation information; The sixth rotation information is greater than the fourth rotation information.
[0040] To increase the orbital altitude of a rotating satellite, it is necessary to change the orbit. The satellite is accelerated once in the existing orbit to make the orbit become an elliptical orbit, and then accelerated a second time at the apogee to a stable on-orbit altitude. The orbital altitude can be continuously increased through multiple accelerations. To lower the orbital altitude of an orbiting satellite, it is necessary to first reduce the satellite speed to make the circular orbit of the satellite become an elliptical orbit, and then increase the satellite speed at the perigee. The orbital altitude can be continuously reduced through multiple decelerations and accelerations.
[0041] The rotating satellite of the present invention will adopt the satellite on-orbit operation method described in Example 1 or the satellite orbit change method described in Example 2.
[0042] Further, such as Figure 3 and Figure 4 As shown, the rotating satellite at least includes a satellite body 1 and a power device installed in the satellite body 1; a solar panel 2 is installed on the outside of the satellite body 1, and the power device has at least a propulsion nozzle 3 in the first direction, the second direction and the third direction. In Examples 1 to 3, the rotation and orbit change of the satellite can be achieved by the power device respectively; the power device of the satellite body can be a chemical propulsion power device and a non-chemical propulsion power device, wherein the chemical propulsion power device can be: a liquid rocket engine, a solid rocket engine, a solid-liquid hybrid rocket engine; wherein the non-chemical propulsion power device can be: nuclear propulsion, electric propulsion, solar propulsion. In this embodiment, the power device is preferably an ion thruster.
[0043] For further information, see Figure 4 The mass of the satellite body 1 is distributed from the inside to the outside and from small to large around the annular periphery of the satellite body. The partial material distribution design on the satellite body 1 and the rotational motion further enhance the attitude control of the satellite.
[0044] The specific principles and formulas of the satellite on-orbit operation method, satellite orbit change method and satellite rotation method of Embodiments 1 to 3 of the present invention are as follows: When we examine the movement of an object, we can ignore its shape but we must start from its shape.
[0045] As we all know, there are only two ways for an object to move: one is linear motion; the other is rotational motion. Usually, the motion of an object has two composite situations: linear motion and rotational motion, and any complex curved motion can be compounded by the interaction and combination of linear motion and rotational motion. According to the law of conservation of energy, the two can be converted into each other and there is a quantitative relationship.
[0046] When a rigid spherical satellite, that is, a satellite with uniform density distribution, moves, we quantitatively analyze the quantitative relationship and physical meaning between the satellite's rotational motion and linear motion.
[0047] A sphere can be viewed as composed of countless circular surfaces with diameters ranging from 0 to 2r, which are superimposed on each other with r as the radius twice. The motion state of the sphere is the collection of the motion states of the circular surfaces.
[0048] like Figure 5 As shown in the figure, when a circular surface a with a radius of r rotates one circle, the movement of the circular surface is visualized as shown in b, which can be understood as the sum of the movement of all points on the circular surface. The movement is: ; Assuming that the circular surface moves along a straight line and the distance of movement is exactly the amount of rotation of the outermost point of the circular surface, the movement of the circular surface can be visualized as shown in c, and its movement is: , As demonstrated above, for the same circular surface, with the edge of the surface as a reference, the rotation speed of the circular surface is v, and the linear motion speed is V. When the rotation and linear motion speeds are equal, the amount of rotational motion must be half of the amount of linear motion, that is: .
[0049] like Figure 6 As shown, we examine the motion of two special types of objects: A is Figure 5 In the case described, the radius of cylinder B is equal to A, and the height is h. According to Figure 5 Further deduction, cylinder B is moving with all circular surfaces of radius r and height h, so the amount of motion of its linear motion and rotational motion also has the following linear relationship: ; The radius of the sphere C is also equal to A. Along the axis of rotation, countless circular surfaces with diameters from 0 to 2r can be cut out, with r as the radius and superimposed twice. Each circular surface is in Figure 5 , then the entire sphere must also have the following relationship: ; When the sphere has a combined rotational and linear motion, the sphere's motion is the sum of the two motion modes, namely: .
[0050] Under the initial assumption, the letters m and f represent the mass and motion of the spherical satellite respectively, then: .
[0051] Applying the above technical methods to satellite orbit control will provide more flexible application methods for satellites. For example, when a satellite is 2000km above the ground, the required orbital speed is about 7.8km / s. For a satellite at the same altitude, assuming that the star is Figure 6 B and C in the figure are ideal uniform rigid cylinders or spheres. As long as the rotation speed along the direction of the earth's rotation is 15.6 km / s, the satellite will always maintain this distance at the same ground coordinate. The satellite no longer has orbital motion, but instead has orbital rotation motion, just like a geostationary orbit satellite.
[0052] If the satellite is not rotating, according to Newton's theory of mechanics, the satellite's orbital period will be synchronized with the Earth's rotation period only when it is at an altitude of 35,786 km above the ground at the equator. We define the satellite operating on this orbit as a geostationary orbit satellite. The most ideal geostationary orbit is only about 35,786 km above the ground at the equator. According to international regulations, the distance between any two geostationary orbit satellites must not be less than 3°, so the circular geostationary orbit can only accommodate a maximum of 120 satellites. Satellites can be set up at any position within the control range of the Earth's gravity through rotation control.
[0053] According to the law of conservation of energy, the energy required to accelerate the linear speed of the same uniform rigid spherical satellite to 7.8 km / s and the rotational speed to 15.6 km / s is the same or similar.
[0054] In addition, to maintain the periodic motion of the satellite outside the geostationary orbit, the orbital velocity of the satellite will be less than the velocity of the geostationary orbit - that is, the orbital period of the satellite is greater than the rotation period of the earth. To maintain an equal distance between the rotating satellites, the direction of the satellite's rotation must be opposite to the direction of the earth's rotation, and the rotation speed must be equal to the geostationary orbit speed minus twice the orbital speed. In this case, the rotating satellite is still in the geostationary orbit satellite state.
[0055] There are requirements for the control of the satellite's orbital altitude and orbital speed, which only requires the satellite to have matching linear motion and rotational motion at the same time.
[0056] Further deducing from the above mathematical arguments, if we concentrate the satellite's mass in the outer layer, then theoretically the satellite's maximum rotational speed is the orbital speed. That is to say, by concentrating the matter on the satellite's outer shell, the satellite can maintain a relative orbital altitude even if it rotates at a speed slightly greater than the orbital speed.
[0057] The satellite on-orbit operation method, satellite orbit change method and rotating satellite of Examples 1 to 3 of the present invention, the rotating satellite refers to completely using the satellite's rotational motion to replace the orbital motion, and the theoretical basis in this regard is based on the above-mentioned mathematical research on the motion of objects. According to the relationship between energy conservation and physical quantization equivalent conversion, the orbital linear motion of the satellite is replaced by the orbital point rotational motion, which causes the satellite's on-orbit mode to inevitably change from the orbital motion mode to the orbital point motion mode. By making the satellite have both linear and rotational composite motion, it is further obtained that the satellite's orbital altitude and orbital speed can be freely controlled.
[0058] Since satellites have corresponding orbiting speeds when they operate at different orbital heights above the ground in extraterrestrial space, all satellites currently adopt a motion mode of running along a set orbital line. The satellite on-orbit operation method and satellite orbit change method and rotating satellite of the present invention adopt an operation mode of allowing the satellite to rotate with opposite and reverse orbital points (relative to a certain point in the reference system) instead of orbital line motion and / or allowing the satellite to have both rotational motion and linear motion at the same time, to control the satellite's on-orbit height and speed, and to control the satellite's attitude and change its orbit by controlling the satellite's rotation direction and speed.
[0059] The earth is not a regular sphere. The uneven mass distribution leads to an uneven gravitational field in space, which makes the orbit of the orbiting satellite easily deviate and requires energy to correct. A major advantage of the satellite on-orbit operation method, satellite orbit change method and rotating satellite of the present invention is that it can be stationary at any given relative spatial position, thus avoiding a series of problems caused by uneven gravitational field. Of course, the satellite can combine linear motion and rotational motion to achieve free control of orbit, speed and attitude. And the orbital speed and altitude of the satellite relative to the intersection of the line connecting the center of the earth and the satellite on the surface of the earth can be controlled more flexibly.
[0060] The satellite on-orbit operation method, satellite orbit change method and rotating satellite of the present invention are less affected by external factors in the rotating state, the distance between different satellites can be closer, and the space can accommodate more geostationary orbit satellites at different altitudes and different longitudes and latitudes; in addition to adding more satellites to the orbit, the safety of avoiding collisions between different satellites is also improved.
[0061] The satellite on-orbit operation method and satellite orbit change method of the present invention and the formula for rotating the satellite are analyzed in combination with the law of conservation of angular momentum. The mass of the satellite is distributed from small to large from the inside to the outside, which can reduce the rotation speed of the satellite, and vice versa, can increase the rotation speed of the satellite.
[0062] The words "first", "second" and similar words used in the specification and claims do not indicate any order, quantity or importance, but are only used to distinguish different components. Similarly, words such as "one", "an" or "the" do not indicate a quantitative limitation, but rather indicate the presence of at least one. Words such as "include" or "comprise" and similar words mean that the elements or objects appearing before "include" or "comprises" include the elements or objects listed after "include" or "comprises" and their equivalents, and do not exclude other elements or objects. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.
[0063] The preferred embodiments of the present invention described above are only the preferred embodiments of the present invention and are not intended to limit the present invention. The protection scope of the present invention is defined by the attached claims. For ordinary technicians in this field, other embodiments can be obtained according to the drawings without creative work, and any changes based on the claims of the present invention are within the protection scope of the present invention.
Claims
1. A satellite in-orbit operation method, characterized in that: include: The orbital satellite is at an orbital altitude of 35786 km as first altitude information, and first orbital velocity information of the first altitude information is obtained, where the orbital velocity information is first length information; Acquire second altitude information of the orbit of the rotating satellite, and obtain corresponding second orbital velocity information according to the second altitude information; the second orbital velocity information is second length information; and obtain first difference length information using the first length information and the second length information; Acquire the circumference information of the rotating satellite after one rotation; and obtain the first rotation information of the rotating satellite according to the first difference length information and the circumference information; The rotating satellite is kept rotating in orbit at a first rotation speed; the rotation speed of the first rotation speed is second rotation information, the second rotation information is N times the first rotation information, and N is a natural number, a decimal, or a negative number.
2. The satellite on-orbit operation method according to claim 1, characterized in that: The second rotation information is second difference length information, and the first difference length information is replaced by the second difference length information.
3. The satellite on-orbit operation method according to claim 1, characterized in that: The rotating satellite can rotate counterclockwise or clockwise.
4. The satellite on-orbit operation method according to claim 1, characterized in that: The rotation of the rotating satellite and the orbit of the rotating satellite form a composite motion.
5. The satellite on-orbit operation method according to claim 1 or 3, characterized in that: When the orbital altitude of the rotating satellite is higher than the 35786 km, the rotating satellite's own rotation state is counterclockwise rotation; when the orbital altitude of the rotating satellite is lower than the 35786 km, the rotating satellite's own rotation state is clockwise rotation.
6. A satellite orbit change method, characterized in that: The method for satellite in-orbit operation comprises the method according to any one of claims 1 to 5, and further comprises: Acquire third height information of the target track, and obtain corresponding third orbital speed information according to the third height information; the third orbital speed information is third length information; and obtain second difference length information by using the third length information and the first length information; Increasing or decreasing the rotation speed of the rotating satellite itself, and making the rotating satellite enter the target orbit; Deriving third rotation information of the rotating satellite according to the second difference length information and the circumference information; The rotating satellite is kept rotating at a second rotation speed in the target orbit; the second rotation speed is fourth rotation information; the fourth rotation information is N times the third rotation information, and N is a natural number, a decimal, or a negative number.
7. The satellite orbit change method according to claim 6, characterized in that: When the third altitude information of the target orbit is lower than the first altitude information, the rotating satellite rotates clockwise; Before the rotating satellite enters the target orbit, the first rotation speed is increased to a third rotation speed, and the third rotation speed is fifth rotation information; After the rotating satellite enters the target orbit, the third rotation speed is adjusted to the second rotation speed; the rotation speed of the second rotation speed is the fourth rotation information; The fifth rotation information is greater than the fourth rotation information.
8. The satellite orbit change method according to claim 6, characterized in that: When the second altitude information of the target orbit is higher than the first altitude information, the rotating satellite rotates counterclockwise; Before the rotating satellite enters the target orbit, the first rotation speed is increased to a fourth rotation speed, and the fourth rotation speed is sixth rotation information; After the rotating satellite enters the target orbit, the fourth rotation speed is adjusted to the second rotation speed; the second rotation speed is the fourth rotation information; The sixth rotation information is greater than the fourth rotation information.
9. A rotating satellite, characterized in that The rotating satellite will adopt the satellite on-orbit operation method described in any one of claims 1 to 5 or the satellite orbit change method described in any one of claims 6 to 8.
10. The rotating satellite according to claim 9, characterized in that: The rotating satellite comprises at least a satellite body and a power device installed in the satellite body; a solar panel is installed outside the satellite body, and the power device has at least propulsion nozzles in a first direction, a second direction and a third direction respectively.
11. The rotating satellite according to claim 9, characterized in that: The mass of the satellite body is distributed around the annular periphery of the satellite body from the inside to the outside and from small to large.