Moving trajectory adjustment method and device and storage medium

Abstract

The invention provides a moving trajectory adjustment method and device and a storage medium, relates to the technical field of communication satellites, and can adjust the moving trajectory of a communication satellite according to the content of a first signal so as to avoid a flying object on an original moving trajectory. The operation of manual intervention is omitted, the communication satellite can autonomously avoid the flying object, and the communication satellite can effectively avoid the flying object in the first time in case of emergency. The method comprises the following steps: receiving a first signal, wherein the first signal comprises a signal obtained by reflecting a detection signal emitted by a communication satellite by a flying object and / or detection signals of other communication satellites; wherein the flying object and the communication satellite are in the same moving track; and adjusting the moving trajectory of the communication satellite according to the first signal.

Description

Technical Field

[0001] The present application relates to the technical field of communication satellites, and in particular to a method, device and storage medium for adjusting an operating trajectory. Background Art

[0002] In the actual operation of communication satellites, they are exposed to the space environment and need not only to process, receive and transmit communication signals, but also to rotate themselves and move with the earth and the entire galaxy. Facing other space objects other than the satellite itself, they are in a weak state of anti-strike and weak defense, so communication satellites need to avoid other space objects in orbit.

[0003] At present, the communication satellite management system mainly combines the ground network to remotely monitor the satellite, and there is no dynamic management system designed for communication satellites and the constellation structure constructed by the satellites. Because the communication satellite is too far away from the ground at the physical level, the ground control sometimes cannot make adjustments and feedback in the first time, resulting in the communication satellite being unable to formulate an effective trajectory adjustment strategy in the first time when facing obstacles such as other satellites and meteorites in orbit. Summary of the invention

[0004] The present application provides a method, device and storage medium for adjusting a running track, which can flexibly adjust the running track according to a received first signal to avoid collision with obstacles on the running track.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] In a first aspect, the present application provides a method for adjusting an operating trajectory, the method comprising: receiving a first signal, the first signal comprising a detection signal transmitted by a communication satellite, a signal reflected back by a flying object and / or detection signals of other communication satellites; wherein the flying object and the communication satellite are in the same operating trajectory; and adjusting the operating trajectory of the communication satellite according to the first signal.

[0007] According to the above technical means, the present application can adjust the orbit of the communication satellite according to the received first signal, so as to avoid the flying object on the original orbit, and omit the process of manual intervention on the ground, so that the communication satellite can effectively avoid the object in the first place.

[0008] In a possible implementation, the type of the flying object is determined based on a signal difference between the detection signal and the first signal.

[0009] According to the above technical means, the present application can determine the type of flying object according to the signal difference between the detection signal and the first signal. Confirming the type of flying object can enable the communication satellite to formulate a trajectory adjustment strategy that is more in line with the actual scenario.

[0010] In a possible implementation manner, the signal difference includes: a color difference between the detection signal and the first signal, and / or a potential energy difference between the detection signal and the first signal.

[0011] According to the above technical means, the present application can determine the signal difference based on the color difference and potential energy difference, and realize the confirmation of the signal difference through physical principles.

[0012] In a possible implementation, a trajectory adjustment strategy matching the first signal is determined, and based on the trajectory adjustment strategy, the operation trajectory of the communication satellite is adjusted.

[0013] According to the above technical means, the present application can formulate trajectory adjustment strategies that match multiple different first signals. When the communication satellite receives the first signal, the preset trajectory adjustment strategy can be executed according to the content of the first signal, which reduces the time for determining the trajectory adjustment strategy, so that the communication satellite can call the adapted trajectory adjustment strategy at the first time.

[0014] In a possible implementation, the detection signal transmitted by the communication satellite includes a first detection signal and a second detection signal, and the signal strength of the first detection signal is greater than the signal strength of the second detection signal;

[0015] When the reflection signal corresponding to the first detection signal and the reflection signal corresponding to the second detection signal are received, the trajectory adjustment strategy is: determine the predicted flight trajectory of the flying object, and adjust the operating trajectory of the communication satellite based on the predicted flight trajectory; when the reflection signal corresponding to the first detection signal and the reflection signal corresponding to the second detection signal are not received, and the first signal includes the detection signals of other communication satellites, the trajectory adjustment strategy is: adjust the operating trajectory of the communication satellite by communicating with other communication satellites.

[0016] According to the above-mentioned technical means, the present application can determine a specific trajectory adjustment strategy according to whether the first signal contains a reflection signal of the first detection signal and / or a reflection signal of the second detection signal, so that the trajectory adjustment strategy of the communication satellite can cover a larger application scenario.

[0017] In a possible implementation, the working mode is turned off, and the variable speed ascent or descent on the same track is turned on to adjust the orbit of the communication satellite.

[0018] According to the above technical means, the present application can enable a communication satellite that needs to adjust its trajectory to shut down its working mode in advance, thereby avoiding imaging of the working process due to trajectory adjustment and causing unnecessary failures.

[0019] In a possible implementation manner, the communication link with the first satellite is disconnected.

[0020] According to the above technical means, the present application can close the working model by disconnecting the communication link with the first satellite, and provides a complete workflow for closing the working model.

[0021] In a possible implementation, when there is still a risk in the adjusted operation trajectory, a first request message is sent to a ground controller; the first request message is used to request manual adjustment of the operation trajectory of the communication satellite.

[0022] According to the above technical means, the present application can send a first request message to the ground controller to request manual adjustment of the orbit of the communication satellite when the communication satellite encounters a situation that it cannot handle, thereby avoiding erroneous orbit adjustment when the communication satellite cannot handle the situation itself.

[0023] In a second aspect, the present application provides a communication satellite, comprising: a first outer shell layer, the first outer shell layer is arranged on the outer layer of the communication satellite; a temperature detection needle, the detection needle is used to detect the temperature around the communication satellite; a transceiver, the transceiver is used to transmit a detection signal and receive a first signal, the first signal includes a reflected signal of the detection signal and / or a detection signal of other communication satellites; a controller, the controller is used to adjust the operating trajectory of the communication satellite according to the first signal.

[0024] In a possible implementation, the first outer shell layer includes: a high temperature resistant layer; and a low temperature resistant layer, wherein the high temperature resistant layer is located on an upper layer of the low temperature resistant layer.

[0025] In a possible implementation, a temperature sensing layer is provided between the first outer shell layer and the transceiver; wherein the temperature sensing layer includes multiple layers of thin films, each layer of the thin films having a different temperature; the temperature detection needle penetrates the temperature sensing layer and contacts each layer of the thin film.

[0026] In a third aspect, the present application provides a device for adjusting a running trajectory, the device comprising: a communication unit and a processing unit.

[0027] A communication unit, configured to receive a first signal, the first signal comprising a signal of a detection signal transmitted by a communication satellite and reflected by the flying object and / or a detection signal of other communication satellites; wherein the flying object and the communication satellite are in the same orbit;

[0028] The processing unit is used to adjust the operation trajectory of the communication satellite according to the first signal.

[0029] In a possible implementation, the processing unit is further used to determine the type of the flying object based on a signal difference between the detection signal and the first signal.

[0030] In a possible implementation manner, the signal difference includes: a color difference between the detection signal and the first signal, and / or a potential energy difference between the detection signal and the first signal.

[0031] In a possible implementation, the processing unit is further used to determine a trajectory adjustment strategy that matches the first signal, and adjust the operating trajectory of the communication satellite based on the trajectory adjustment strategy.

[0032] In one possible implementation, the processing unit is also used for the detection signal transmitted by the communication satellite, including a first detection signal and a second detection signal, and the signal strength of the first detection signal is greater than the signal strength of the second detection signal; when a reflection signal corresponding to the first detection signal and a reflection signal corresponding to the second detection signal are received, the trajectory adjustment strategy is: determining the predicted flight trajectory of the flying object, and adjusting the operation trajectory of the communication satellite based on the predicted flight trajectory; when the reflection signal corresponding to the first detection signal and the reflection signal corresponding to the second detection signal are not received, and the first signal includes the detection signals of other communication satellites, the trajectory adjustment strategy is: adjusting the operation trajectory of the communication satellite by communicating with other communication satellites.

[0033] In a possible implementation, the processing unit is also used to shut down the working mode and start the variable speed ascent or descent on the same track to adjust the orbit of the communication satellite.

[0034] In a possible implementation manner, the processing unit is further configured to disconnect the communication link with the first satellite.

[0035] In a possible implementation, the processing unit is further used to send a first request message to the ground controller when there is still a risk in the adjusted operation trajectory; the first request message is used to request manual adjustment of the operation trajectory of the communication satellite.

[0036] In a fourth aspect, the present application provides a computer-readable storage medium, which stores instructions. When the instructions are executed on a terminal, the terminal executes the method for adjusting the running trajectory as described in the first aspect and any possible implementation of the first aspect.

[0037] In a fifth aspect, the present application provides a computer program product comprising instructions. When the computer program product is run on a device for adjusting a running trajectory, the device for adjusting a running trajectory executes a method for adjusting a running trajectory as described in any possible implementation of the first aspect.

[0038] In a sixth aspect, the present application provides a chip, comprising a processor and a communication interface, wherein the communication interface and the processor are coupled, and the processor is used to run a computer program or instructions to implement a method for adjusting a running trajectory as described in any possible implementation of the first aspect.

[0039] Specifically, the chip provided in the present application also includes a memory for storing computer programs or instructions. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 A schematic diagram of a system for adjusting a running track provided in an embodiment of the present application Figure 1 ;

[0041] Figure 2 A schematic diagram of a system for adjusting a running track provided in an embodiment of the present application Figure 2 ;

[0042] Figure 3 A process of adjusting a running trajectory provided in an embodiment of the present application Figure 1 ;

[0043] Figure 4 A schematic diagram of a method for adjusting a running trajectory provided in an embodiment of the present application Figure 1 ;

[0044] Figure 5 A schematic diagram of a method for adjusting a running trajectory provided in an embodiment of the present application Figure 2 ;

[0045] Figure 6 A process of adjusting a running trajectory provided in an embodiment of the present application Figure 2 ;

[0046] Figure 7 A process of adjusting a running trajectory provided in an embodiment of the present application Figure 3 ;

[0047] Figure 8 A schematic diagram of the structure of a running trajectory adjustment device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0048] The following is a detailed description of the method, device and storage medium for adjusting the running trajectory provided in the embodiments of the present application in conjunction with the accompanying drawings.

[0049] The term "and / or" in this article is merely a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone.

[0050] The terms "first" and "second" and the like in the specification and drawings of this application are used to distinguish different objects, or to distinguish different processing of the same object, rather than to describe a specific order of objects.

[0051] In addition, the terms "including" and "having" and any variations thereof mentioned in the description of the present application are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device comprising a series of steps or units is not limited to the listed steps or units, but may optionally include other steps or units that are not listed, or may optionally include other steps or units that are inherent to these processes, methods, products or devices.

[0052] It should be noted that, in the embodiments of the present application, words such as "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "exemplary" or "for example" is intended to present related concepts in a specific way.

[0053] In the description of the present application, unless otherwise specified, “plurality” means two or more.

[0054] At present, the communication satellite management system mainly combines the ground network to remotely monitor the satellite, and there is no dynamic management system designed for communication satellites and the constellation structure constructed by the satellites. Because the communication satellite is too far away from the ground at the physical level, the ground control sometimes cannot make adjustments and feedback in the first time, resulting in the communication satellite being unable to formulate an effective trajectory adjustment strategy in the first time when facing obstacles such as other satellites and meteorites in orbit.

[0055] In view of this, an embodiment of the present application provides a method for adjusting the operating trajectory, which enables the communication satellite to autonomously perform avoidance operations and, in the face of emergency situations, perform effective avoidance in the first place to avoid collisions with obstacles on the operating orbit.

[0056] For example, Figure 1 The schematic diagram of the structure of a system 10 for adjusting a running track provided in an embodiment of the present application is shown. The system 10 for adjusting a running track may include at least one communication satellite 101 and at least one ground controller 102. The communication satellite 101 may be in communication connection with the ground controller 102. Figure 1 Only one communication satellite 101 and one ground controller 102 are shown. The embodiment of the present application does not impose any limitation on the number of communication satellites 101 and ground controllers 102.

[0057] The communication satellite 101 is used to receive a first signal, wherein the first signal includes a signal of a detection signal transmitted by the communication satellite and reflected by a flying object and / or a detection signal of other communication satellites. The flying object and the communication satellite are in the same orbit. The orbit of the communication satellite is adjusted according to the first signal.

[0058] The ground controller 102 is used to receive the first request information and provide a trajectory adjustment strategy for the communication satellite 101 according to the first request information.

[0059] In one example, Figure 2 As shown, the communication satellite 101 also includes a first outer shell layer, a temperature detection needle, a transceiver, a controller and other components.

[0060] Specifically, the first shell layer includes an extreme temperature resistant shell layer 1, a surface temperature sensing multilayer film layer 3, a magnet connecting line 8, a north pole magnet device 9, and a south pole magnet device 10. The temperature detection needle includes: a nano-scale temperature sensing detection needle 2, and a penetration contact point between the detection needle and the film 4. The controller includes: a telescopic multilayer lens layer 5. The transceiver includes: a plastic glass strong and weak wave emission extremely thin tube 6, and a plastic glass strong and weak wave recovery thick tube 7.

[0061] The above components are described below respectively.

[0062] (1) Extreme temperature resistant outer shell 1:

[0063] The outermost layer of a communication satellite is divided into two layers, one is high temperature resistant and the other is low temperature resistant. Since the communication satellite enters space with the rocket from the ground, the temperature during the boost process on the earth is ultra-high and the working environment in space is ultra-low. The other parts inside the communication satellite are relatively delicate and not resistant to high temperatures. The outer shell can fall off as the rocket carrying the communication satellite rises and passes through different layers, leaving behind the low temperature resistant outer shell to accompany the operation of the communication satellite.

[0064] (2) Nano-scale temperature sensing probe 2:

[0065] Since the low temperature in the satellite operation area is not constant, it can gradually decrease as the communication satellite operates for a longer period of time. Therefore, after a period of operation, the extreme temperature resistant shell will gradually fall off. Therefore, a nano-scale temperature sensing probe is set, exposed at the top of the sensor, to detect the external temperature at any time. At the same time, the probe penetrates the temperature sensing multi-layer film layer.

[0066] (3) Surface temperature sensing multi-layer film layer 3:

[0067] The surface temperature-sensing multi-layer film layer is an infrared temperature-sensing layer, each layer has a different temperature, the detection needle penetrates the temperature-sensing multi-layer film layer and each layer has a contact point, and the film layer can also protect the two different magnetic poles of the communication satellite. As the working time of the communication satellite increases, the temperature-sensing film layer will wear and age, and the multi-layer film layer can also fall off by itself when the outermost film layer is worn and aged, ensuring accurate temperature perception.

[0068] (4) The penetration contact point between the probe needle and the film 4:

[0069] The specific temperature is transmitted back to the dynamic management system through the contact points of each layer, displaying the specific temperature of each layer.

[0070] (5) Telescopic multi-layer lens layer 5:

[0071] The telescopic multi-layer lens layer is mainly distributed in three layers, including a 180° wide-angle lens, a focus telescopic lens, and a magnifying telescopic lens. The telescopic multi-layer lens layer is more targeted for monitoring satellites near communication satellites and distant satellites.

[0072] (6) Plastic glass strong and weak wave emitting extremely fine tube 6:

[0073] In the trajectory adjustment system, the communication satellite can alternately transmit strong and weak waves to nearby objects. Because the plastic glass mixture has been subjected to extremely high or low temperatures, the molecules are unstable and prone to chemical reactions, which damages the structure and affects the normal operation of the communication satellite. Therefore, the plastic glass strong and weak wave emission ultra-fine tube is placed in the surface temperature-sensitive multi-layer film layer. When the communication satellite emits strong and weak waves, the strong and weak waves can pass through the plastic glass strong and weak wave emission ultra-fine tube to increase the speed of the strong and weak waves.

[0074] (7) Plastic glass strong and weak wave recovery thick tube 7:

[0075] The potential energy and propagation speed of strong and weak waves will change during the reflection process, and they may be strong or weak, fast or slow. At the same time, it is also necessary to receive detection signals from other satellites or objects, so it is set to be an extremely thick tube to facilitate the reception of return waves or other waves.

[0076] (8) Magnet connection line 8:

[0077] Set at both ends of the communication satellite to connect the magnet and the communication satellite.

[0078] (9) North Pole Magnet Device 9:

[0079] It is used to disperse some magnets in the operating environment of communication satellites to ensure that the monitoring lens layer in the film layer has a better viewing angle.

[0080] (10) South Pole magnet device 10:

[0081] It is used to disperse some magnets in the operating environment of communication satellites to ensure that the monitoring lens layer in the film layer has a better viewing angle.

[0082] The following is a description of the method for adjusting the running trajectory provided by the embodiment of the present application in conjunction with the accompanying drawings. Among them, the actions, terms, etc. involved in the various embodiments of the present application can refer to each other without limitation. The message name or parameter name in the message exchanged between the various devices in the embodiment of the present application is only an example, and other names can also be used in the specific implementation without limitation. The actions involved in the various embodiments of the present application are only an example, and other names can also be used in the specific implementation, such as: "included in" in the embodiment of the present application can also be replaced by "carried on" or "carried on", etc.

[0083] like Figure 3 As shown, an embodiment of the present application proposes a method for adjusting a running trajectory, and the method includes: S301 to S302.

[0084] S301. A communication satellite receives a first signal.

[0085] The first signal includes a signal reflected by a flying object from a detection signal emitted by a communication satellite and / or a detection signal from other communication satellites. A flying object is an object located in the working environment of a communication satellite other than the communication satellite and other satellites in the constellation to which the satellite belongs. The flying object and the communication satellite are in the same orbit.

[0086] In one example, a communication satellite may transmit a detection signal composed of strong and weak waves, and determine the type of the flying object based on the signal difference between the detection signal and the first signal.

[0087] Among them, strong and weak waves refer to electromagnetic waves with different intensities and / or frequencies, which are used for signal transmission between communication satellites and the ground, and between communication satellites and other satellites. The detection signal includes a first detection signal and a second detection signal. The first detection signal is a strong wave, and the second detection signal is a weak wave. The signal strength and frequency of the first detection signal are greater than the signal strength and frequency of the second detection signal.

[0088] Furthermore, after the detection signal contacts the flying object, the flying object can absorb the color of the detection signal and reflect the color of the detection signal that cannot be absorbed, thereby producing a color difference with the detection signal. After the detection signal contacts the flying object, the flying object can absorb or give a certain amount of potential energy to the strong and weak waves, so that the strong and weak waves of the reflected signal of the detection signal are accelerated, decelerated, heated up, cooled down, and the size of the atoms in the wave particles changes, resulting in a potential energy difference with the detection signal. The communication satellite can mark the flying object according to the signal difference. The type of flying object can be meteorites, space junk, other satellites, and any other objects in the operating environment of the communication satellite.

[0089] In another example, the first detection signal can also be called a triggering strong emergency avoidance marker wave, and the second detection signal can also be called a triggering weak emergency avoidance marker wave. The first signal can include a triggering strong emergency avoidance return marker wave, which is also a reflection signal of the first detection signal, a triggering weak emergency avoidance return marker wave, which is also a reflection signal of the second detection signal, and detection signals of other satellites. The triggering strong emergency avoidance return marker wave is X, the triggering weak emergency avoidance return marker wave is Y, and the detection signals of other satellites are Z. The first signal can be composed of one or more of X, Y, and Z. According to the composition of the first signal, the first signal can be divided into a single strong and weak wave trigger type and a combined strong and weak wave trigger type.

[0090] Among them, the single strong and weak wave trigger type includes signal 1 to signal 3, and the combined strong and weak wave trigger type includes signal 4 to signal 6.

[0091] Signal 1: |X|≠0∩|Y|=0∩|Z|=0.

[0092] Signal 2: |X|=0∩|Y|≠0∩|Z|=0.

[0093] Signal 3: |X|=0∩|Y|=0∩|Z|≠0.

[0094] Signal 4: |X|≠0∩|Y|≠0∩|Z|=0.

[0095] Signal 5: |X|≠0∩|Z|≠0∩|Y|=0.

[0096] Signal 6: |Y|≠0∩|Z|≠0∩|X|=0.

[0097] Furthermore, within the preset time period, signals 1 to 6 are regularly repeated twice or more, and the type of the first signal is an occasional or intermittent trigger type. No first signal is received within the preset time period, indicating that X, Y, and Z are all 0, that is, signal 7: |X|=0∩|Y|=0∩|Z|=0.

[0098] In one possible implementation, Figure 4 As shown, the occasional or intermittent trigger type indicates that the above 7 situations occur repeatedly and regularly in a short period of time. In the case where the first signal is an occasional or intermittent trigger type, the single strong and weak wave trigger, the combined strong and weak wave trigger, and the situation without the first signal can be formed into two mapping groups, and mapping group 1 includes signals 1 to 3, and mapping group 2 includes signals 4 to 7. For example, if the first signal received for the first time is signal 1, a combination of multiple situations can be identified from the two mapping groups to obtain multiple first signals of occasional or intermittent trigger types in the total output set.

[0099] S302. The communication satellite adjusts its trajectory according to the first signal.

[0100] In one example, the communication satellite determines a trajectory adjustment strategy that matches the first signal according to the content of the first signal, and adjusts the operating trajectory of the communication satellite based on the trajectory adjustment strategy.

[0101] When a reflection signal corresponding to the first detection signal and a reflection signal corresponding to the second detection signal are received, the trajectory adjustment strategy is to determine the predicted flight trajectory of the flying object and adjust the operating trajectory of the communication satellite based on the predicted flight trajectory.

[0102] When neither the reflected signal corresponding to the first detection signal nor the reflected signal corresponding to the second detection signal is received, and the first signal includes detection signals of other communication satellites, the trajectory adjustment strategy is to adjust the operating trajectory of the communication satellite by communicating with other communication satellites.

[0103] In one application scenario, before adjusting the orbit, the communication satellite sends a disconnection request to the first satellite, and the first satellite or other satellites in the constellation take over the work of the communication satellite. After receiving the confirmation information from the first satellite, the connection with the first satellite is disconnected, and the orbit is adjusted.

[0104] The first satellite refers to one or more other communication satellites that belong to the same constellation as the communication satellite and have a communication link with the communication satellite.

[0105] In another example, when the first signal received by the communication satellite is a combined strong and weak wave trigger, the communication satellite communicates with the navigation satellite, and the navigation satellite formulates a trajectory adjustment strategy according to the position of the communication satellite in the constellation to which it belongs and the type of obstacle. When the first signal received by the communication satellite is an occasional or intermittent trigger type, a single strong and weak wave trigger type, or the first signal is not received, the processing method is referred to the following cases 1 to 3 for processing until it is determined that the received first signal is valid and corresponding processing is performed.

[0106] Case 1: The first signal is to trigger a strong emergency avoidance return marker wave (ie, |X|≠0∩|Y|=0∩|Z|=0).

[0107] If the reflected signal of the first detection signal in the first signal is not 0, the first detection signal is transmitted again separately. If the reflected signal of the first detection signal is still received, the first signal received this time is deemed to be valid. The communication satellite can shut down the existing working mode and start the trajectory prediction of other flying objects. According to the trajectory prediction results of other flying objects, a trajectory adjustment strategy is formulated. According to the trajectory adjustment strategy, the same-track variable speed ascent or descent action is performed. Compared with the trajectory adjustment strategy of weak emergency avoidance of the return marker wave, the above trajectory adjustment strategy is completed in a shorter time.

[0108] Case 2: The first signal is to trigger a weak emergency avoidance return marker wave (ie, |X|=0∩|Y|≠0∩|Z|=0).

[0109] If the reflected signal of the second detection signal in the first signal is not 0, the second detection signal is transmitted again separately. If the reflected signal of the second detection signal is still received, the first signal received this time is deemed to be valid. The communication satellite can begin to prepare to shut down the existing working mode and start the trajectory prediction of other flying objects. According to the trajectory prediction results of other flying objects, a trajectory adjustment strategy is formulated. According to the trajectory adjustment strategy, the same-track variable speed ascent or descent action is performed. Compared with the trajectory adjustment strategy of strong emergency avoidance of the return marker wave, the above-mentioned trajectory adjustment strategy is completed in a longer time and has a longer buffer and work handover time.

[0110] Case 3: The first signal is a detection signal of another satellite (ie, |X|=0∩|Y|=0∩|Z|≠0).

[0111] If the first signals of other satellites in the first signal are not 0, the data is deemed valid. The communication satellite can begin to prepare to shut down the existing working mode, realize linkage and dynamic coordination with the satellite that transmits the first signal, and start the identification indication of the same-result variable speed ascent or descent action.

[0112] Case 4: No first signal (ie, |X|=0∩|Y|=0∩|Z|=0).

[0113] It means that the first signal is not received, and the detection signals of strong waves, weak waves and other satellites are all 0. The data is invalid and the detection signal needs to be sent again to collect the first signal.

[0114] In one application scenario, the first signal received by the communication satellite is of an occasional or intermittent trigger type, and the first signal includes the above signal 1: |X|≠0∩|Y|=0∩|Z|=0 and signal 4: |X|≠0∩|Y|≠0∩|Z|=0, indicating that the communication satellite receives two first signals, the first first signal includes a strong emergency avoidance return marker wave, and the second first signal includes a strong emergency avoidance return marker wave and a weak emergency avoidance return marker wave, then the communication satellite retransmits the strong emergency avoidance return marker wave and the weak emergency avoidance return marker wave to confirm whether the first signal is valid. And the trajectory adjustment strategy is formulated according to the first signal judged to be valid.

[0115] In a possible implementation, if there is still a risk in the adjusted trajectory, the communication satellite can send a first request message to the ground controller, where the first request message is used to request manual adjustment of the trajectory of the communication satellite. The communication satellite can also send the first request message to the ground controller when encountering a situation that its own system cannot understand and / or cannot handle.

[0116] In another possible implementation, the communication satellite can also adjust its trajectory through interaction with the navigation satellite. When the communication satellite receives the first signal, it can cooperate with the navigation satellite whose orbit altitude is higher than its own to obtain the motion state of the target object and the working environment of the communication satellite itself, and coordinate the formulation of the trajectory adjustment strategy. For example, a communication satellite located outside the constellation is more susceptible to collision risk than a communication satellite located inside the constellation when facing the same target object on the working orbit. Therefore, facing the same target object, different trajectory adjustment strategies can be formulated according to the different working positions of the communication satellite.

[0117] In another possible implementation, Figure 5 As shown in the figure, in the constellation constructed by the communication satellites, each satellite is in an interconnected state during the working process. The constellation can be translated left and right with the star system. For example, the communication satellite 1 can be translated leftward with the constellation to the position of the communication satellite 6, and the communication satellite 1 can also be translated rightward with the constellation to the position of the communication satellite 7. In the case that the operation trajectory of the communication satellite 1 needs to be adjusted, the communication satellite 1 stops working and moves up and down according to the trajectory adjustment strategy to reach the position of the communication satellite 2 and the communication satellite 4. It can also accelerate or decelerate on the original orbit to reach the position of the communication satellite 3 and the communication satellite 5.

[0118] In the case where the communication satellite 1 adjusts its trajectory, the communication satellites adjacent to the communication satellite 1 in the constellation can replace the communication satellite 1 to establish a connection with other communication satellites in the constellation, thereby ensuring the effective operation of the constellation satellite communication. When the communication satellite 1 returns to its original position, the original connection is established.

[0119] Furthermore, multiple communication satellites can transmit signal waves to each other, and after receiving each other's signal waves, they can transmit feedback signal waves to each other. This process covers the entire process of communication satellite and constellation operation, and is used to achieve connection and interaction between the above communication satellites.

[0120] According to the above technical means, the present application can adjust the orbit of the communication satellite according to the content of the first signal, so as to avoid the flying object on the original orbit. The operation process of ground manual intervention is omitted, and the communication satellite can autonomously perform the avoidance operation, and can effectively avoid the emergency in the first time.

[0121] In another embodiment (Example 2), as Figure 6As shown, a method for adjusting the operating trajectory provided in an embodiment of the present application is used to form a communication satellite operating function and construct a satellite communication defense system according to the content of the first signal received by the communication satellite, so that the operating status of the communication satellite can be recorded according to the satellite communication defense system. The method includes S601 to S603.

[0122] S601. Determine the communication satellite operation function framework.

[0123] Among them, the communication satellite can adjust the angle and rotate on a fixed orbit, and move relatively still on a preset orbit at a constant speed with the same frequency as the earth's rotation, and the communication satellite cannot change orbit and continue to work in the working state. Therefore, the relevant information during the satellite operation is sent back to the background, and the data is analyzed and processed through the preset artificial intelligence and the operation function of the communication satellite, and the status of the communication satellite is adjusted.

[0124] In one example, a communication satellite operation function is constructed, and the operation function satisfies Formula 1.

[0125]

[0126] Among them, x indicates the triggering of a strong emergency avoidance return marker wave. y indicates the triggering of a weak emergency avoidance return marker wave. z indicates the reception of detection signals from other satellites. p Indicates the factors that affect the operation of communication satellites, is the γ of the influencing factor group p The average value of μ l represents the error of the function model, The method for calculating the average value is described in the third embodiment and will not be described in detail here.

[0127] S602. Determine the coefficients of the independent variables of the communication satellite operation function.

[0128] Among them, the coefficients α, β, and λ of x, y, and z can be obtained by calling the variance function group. α, β, and λ can satisfy Formula 2, Formula 3, and Formula 4.

[0129] α=Var(x)=E[(xE[x]) 2 Formula 2

[0130] β=Var(y)=E[(yE[y]) 2 Formula 3

[0131] λ=Var(z)=E[(zE[z]) 2 Formula 4

[0132] In one example, during the calculation process, the independent variable data x, y, z can be compared with the average value of the historical data to re-determine the difference between the target function data and the average data.

[0133] The historical data may be independent variable data of the historical communication satellite during operation. The calculation method of the average value is described in the third embodiment and will not be described in detail here.

[0134] In another example, in order to reduce the impact of influencing factors and errors on the communication satellite operation function, the function evaluation regression model fit can be called to correct the coefficients of the communication satellite operation function. The function evaluation regression model fit satisfies Formula 5. According to the calculation result of Formula 5, the function coefficients are further adjusted to minimize the error and obtain the adjusted correlation coefficients of x, y, and z. are the calculated values ​​of α, β, and λ, and their value range is [0, ∞).

[0135]

[0136] Among them, R 2 The coefficient of determination that represents the goodness of fit of the regression model. The closer it is to 1, the better the model fit is. ESS represents the regression sum of squares, which is used to represent the error between the predicted value and the mean. TSS represents the total sum of squares, which is used to represent the error between the actual value and the mean. RSS represents the residual sum of squares, which is used to represent the error between the actual value and the predicted value. For details, refer to the prior art.

[0137] Furthermore, satisfy If the conditions are not met, it indicates that the data and / or calculation model used are abnormal and the data and calculation model used need to be checked.

[0138] S603. Determine constants of the communication satellite operation function.

[0139] Among them, the constants of the communication satellite operation function can include

[0140] in, It represents the average value of factors that affect the operation of communication satellites. During the operation of communication satellites, they are in a fixed orbit in space and are in a semi-unmanned environment. In space, in addition to communication satellites, there are also orbit-changing satellites and navigation satellites. There are also other celestial bodies such as granular meteorites in the universe. There are attraction and repulsion between various celestial bodies, which will affect the operation of the communication satellite itself and the uplink and downlink data, and will also affect the constellation structure constructed by the satellite. Influencing factor group γ p is the data usage level representation of the various influencing factors mentioned above, obtained based on historical communication satellite data.p For the data processing method, please refer to the description of Example 3 and will not be repeated here.

[0141] In one example, to ensure that the influence of multiple known preset influencing factors cannot be ignored, before performing numerical function calculations, a covariance function is applied to determine the correlation between a single influencing factor and a factor group, and the correlation ρ of the influencing factor relative to the factor group is calculated. ρ satisfies Formula 6, and the covariance matrix function satisfies Formula 7.

[0142]

[0143] Where D is the variance formula. or If , then factor t is not linearly correlated with γ, or is too correlated, then there is overfitting between the factors, and it can be determined that there are problems with the data selection and / or operation. When the influencing factor is greater than or equal to the first preset threshold, the influencing factor is determined to be a single influencing factor.

[0144] In another example, according to the above calculation process, multiple influencing factors that affect the communication satellite can be obtained. For multiple influencing factors, the correlation between the multiple influencing factors can be judged by the above formulas 5 and 6, that is, ρ tv , tu , vu Etc., according to the independent factor principle, when the data of the two influencing factors are too complex and / or irregular, the data processing is performed through matrix series distribution. When the two influencing factors are greater than or equal to the second preset threshold, the two influencing factors can be merged into the same influencing factor according to the situation. When the two influencing factors are less than the second threshold and greater than the first preset threshold, they are regarded as independent influencing factors.

[0145] Furthermore, a square root function operation is performed according to multiple independent influencing factors. The square root function operation satisfies Formula 8.

[0146]

[0147] Among them, n represents n influencing factors. t, v, and u are different influencing factors. is the final data of the communication satellite factor group, t i 、v i 、u i Indicates multiple different specific values ​​of multiple influencing factors.

[0148] According to the above technical means, the present application can record the operation status of the communication satellite according to the communication satellite operation function of the satellite communication defense system. The recorded operation status data of the communication satellite can be used for subsequent data analysis, adjustment of the trajectory adjustment strategy of the communication satellite, and other work related to the operation status of the communication satellite.

[0149] In another embodiment (Example 3), as Figure 7 As shown, another method for adjusting the running trajectory provided in an embodiment of the present application is used to perform data preprocessing on the used data set and calculate the average value. The method includes S701 to S703.

[0150] It should be noted that the source of the data can be the influencing factors of the historical communication satellite operation data collection, or it can be the error value of the historical communication satellite operation function. The data used is not limited here. During the calculation process, the data required to be used and the average value of the data used can be calculated using the following steps.

[0151] S701. Form a data set.

[0152] In one example, multiple data are arranged in ascending order to form set A. Multiple data are arranged in descending order to form set B. For example, A is a1, a2, a3, a4, ..., a n , B is b1, b2, b3, b4, …, b n , then b1=a n 、b2=a n-1 , …, b n =a1. For example, A is 1, 3, 5, 7, 9, and B is 9, 7, 5, 3, 1.

[0153] Among them, a n Represented as the nth element of set A. b n Represented as the nth element of set B.

[0154] S702: Call a function to establish an available data set.

[0155] In one example, a function is called to process set A and set B. The function satisfies formula nine and is used to process and filter the original data.

[0156] x i =2a n -1 Formula 9

[0157] Wherein, the value of n is a positive integer greater than or equal to 5. i is the i-th data in the set of processed data, and i=n-4.

[0158] In another example, based on data set A, set C is established through the above data screening. The first to fourth data in set A are unselected data, forming set C1. Similarly, based on data set B, set D is established through the above data screening. The first to fourth data in set D are unselected data, forming set D1.

[0159] Among them, set C is the set consisting of the elements of set A except the 1st to 4th elements, D is the set consisting of the elements of set B except the 1st to 4th elements, C1 is the set consisting of the 1st to 4th elements of set A, and D1 is the set consisting of the 1st to 4th elements of set B.

[0160] S703, calling a function to calculate the average value of each set.

[0161] In one example, the average value of C and D and the average value of C1 and D1 are calculated. The calculation method satisfies Formula 10 and Formula 11.

[0162]

[0163] in, It is the average value of the original data after data filtering. It is the average value of the unselected data in the original data, which can be used to perform error training on the artificial intelligence model, thereby reducing the error rate in the working process.

[0164] According to the above technical means, the average value of multiple data can be obtained, and the error in the subsequent calculation process can be reduced by removing the maximum and minimum values. At the same time, the average value of multiple maximum and minimum values ​​obtained can be used in the subsequent error training process.

[0165] It is understandable that the above-mentioned method for adjusting the running trajectory can be implemented by an adjusting device for the running trajectory. In order to realize the above-mentioned functions, the adjusting device for the running trajectory includes hardware structures and / or software modules corresponding to the execution of each function. Those skilled in the art should easily realize that, in combination with the modules and algorithm steps of each example described in the embodiments disclosed herein, the embodiments disclosed in the present application can be implemented in the form of hardware or a combination of hardware and computer software. Whether a function is executed in the form of hardware or computer software driving hardware depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of the embodiments disclosed in the present application.

[0166] The embodiments disclosed in the present application can divide the functional modules of the adjustment device of the running trajectory generated by the above method example. For example, each functional module can be divided according to each function, or two or more functions can be integrated into one processing module. The above integrated modules can be implemented in the form of hardware or in the form of software functional modules. It should be noted that the division of modules in the embodiments disclosed in the present application is schematic and is only a logical function division. There may be other division methods in actual implementation.

[0167] Figure 8 This is a schematic diagram of the structure of a running track adjustment device provided in an embodiment of the present application. Figure 8 As shown, the running track adjustment device 80 can be used to perform Figure 1-Figure 7 The running track adjustment method shown in the figure. The running track adjustment device 80 includes: a communication unit 801 and a processing unit 802.

[0168] The communication unit 801 is used to receive a first signal, wherein the first signal includes a signal of a detection signal transmitted by a communication satellite and reflected by a flying object and / or a detection signal of other communication satellites. The flying object and the communication satellite are in the same orbit.

[0169] The processing unit 802 is used to adjust the operation trajectory of the communication satellite according to the first signal.

[0170] In a possible implementation, the processing unit 802 is further configured to determine the type of the flying object according to a signal difference between the detection signal and the first signal.

[0171] In a possible implementation manner, the signal difference includes: a color difference between the detection signal and the first signal, and / or a potential energy difference between the detection signal and the first signal.

[0172] In a possible implementation, the processing unit 802 is further configured to determine a trajectory adjustment strategy that matches the first signal, and adjust the operation trajectory of the communication satellite based on the trajectory adjustment strategy.

[0173] In a possible implementation, the processing unit 802 is also used for the detection signal transmitted by the communication satellite to include a first detection signal and a second detection signal, and the signal strength of the first detection signal is greater than the signal strength of the second detection signal. In the case of receiving a reflection signal corresponding to the first detection signal and a reflection signal corresponding to the second detection signal, the trajectory adjustment strategy is: determining the predicted flight trajectory of the flying object, and adjusting the operation trajectory of the communication satellite based on the predicted flight trajectory. In the case of not receiving the reflection signal corresponding to the first detection signal and the reflection signal corresponding to the second detection signal, and the first signal includes the detection signals of other communication satellites, the trajectory adjustment strategy is: adjusting the operation trajectory of the communication satellite by communicating with other communication satellites.

[0174] In a possible implementation, the processing unit 802 is further configured to shut down the working mode and start the variable speed ascent or descent on the same track to adjust the orbit of the communication satellite.

[0175] In a possible implementation, the processing unit 802 is further configured to disconnect the communication link with the first satellite.

[0176] In a possible implementation, the processing unit 802 is further configured to send a first request message to the ground controller when there is still a risk in the adjusted operation trajectory. The first request message is used to request manual adjustment of the operation trajectory of the communication satellite.

[0177] Through the description of the above implementation methods, technicians in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above functional modules is used as an example. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device is divided into different functional modules to complete all or part of the functions described above. The specific working process of the system, device and unit described above can refer to the corresponding process in the aforementioned method embodiment, and will not be repeated here.

[0178] The present disclosure also provides a computer-readable storage medium having instructions stored thereon. When the instructions in the storage medium are executed by a processor of an electronic device, the electronic device is enabled to execute the method for adjusting the running trajectory provided by the above-mentioned embodiment of the present disclosure.

[0179] The embodiments of the present disclosure also provide a computer program product including instructions, which, when executed on an electronic device, enables the electronic device to execute the method for adjusting the running trajectory provided by the embodiments of the present disclosure.

[0180] Among them, the computer readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer readable storage media (a non-exhaustive list) include: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM), a register, a hard disk, an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above, or any other form of computer readable storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read information from the storage medium and write information to the storage medium. Of course, the storage medium can also be a component of the processor. The processor and the storage medium can be located in an application-specific integrated circuit (ASIC). In the embodiments of the present application, a computer-readable storage medium may be any tangible medium that contains or stores a program, which may be used by or in conjunction with an instruction execution system, apparatus, or device.

[0181] The above are only specific implementations of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A method for adjusting a running trajectory, characterized in that: Applied to a communication satellite, the method comprises: receiving a first signal, wherein the first signal includes a signal of a detection signal transmitted by the communication satellite and reflected by the flying object and / or a detection signal of other communication satellites; wherein the flying object and the communication satellite are in the same orbit; The operation trajectory of the communication satellite is adjusted according to the first signal.

2. The method according to claim 1, characterized in that The first signal is a signal generated by a detection signal emitted by the communication satellite and reflected by the flying object, and determining the type of the flying object according to the first signal includes: The type of the flying object is determined based on a signal difference between the detection signal and the first signal.

3. The method according to claim 2, characterized in that The signal difference includes: a color difference between the detection signal and the first signal, and / or a potential energy difference between the detection signal and the first signal.

4. The method according to any one of claims 1 to 3, characterized in that The step of adjusting the operation trajectory of the communication satellite according to the first signal includes: Determine a trajectory adjustment strategy that matches the first signal, and adjust the operation trajectory of the communication satellite based on the trajectory adjustment strategy.

5. The method according to claim 4, characterized in that The detection signal transmitted by the communication satellite includes a first detection signal and a second detection signal, and the signal strength of the first detection signal is greater than the signal strength of the second detection signal; In case of receiving a reflection signal corresponding to the first detection signal and a reflection signal corresponding to the second detection signal, the trajectory adjustment strategy is: determining a predicted flight trajectory of the flying object, and adjusting the operation trajectory of the communication satellite based on the predicted flight trajectory; When the reflection signal corresponding to the first detection signal and the reflection signal corresponding to the second detection signal are not received, and the first signal includes the detection signals of other communication satellites, the trajectory adjustment strategy is: adjusting the operating trajectory of the communication satellite by communicating with the other communication satellites.

6. The method according to claim 5, characterized in that The step of adjusting the operation trajectory of the communication satellite comprises: The working mode is turned off, and variable speed ascent or descent on the same track is turned on to adjust the orbit of the communication satellite.

7. The method according to claim 6, characterized in that There is a communication link between the communication satellite and the first satellite. Before shutting down the working mode, the method further includes: The communication link with the first satellite is disconnected.

8. The method according to any one of claims 1 to 3, characterized in that The method further comprises: In the case that there is still a risk in the adjusted operation trajectory, a first request message is sent to the ground controller; the first request message is used to request manual adjustment of the operation trajectory of the communication satellite.

9. A communication satellite, characterized in that: The communication satellite comprises: a first outer shell layer, the first outer shell layer being disposed on an outer layer of the communication satellite; A temperature probe, the probe being used to detect the temperature around the communication satellite; a transceiver, the transceiver being used to transmit a detection signal and receive a first signal, wherein the first signal includes a reflection signal of the detection signal and / or a detection signal of another communication satellite; A controller is used to adjust the operation trajectory of the communication satellite according to the first signal.

10. The communication satellite according to claim 9, characterized in that: The first outer shell layer comprises: High temperature resistant layer; The low temperature resistant layer is located on the upper layer of the low temperature resistant layer.

11. The communication satellite according to claim 9 or 10, characterized in that: The communication satellite also includes: a temperature sensing layer, the temperature sensing layer being arranged between the first outer shell layer and the transceiver; Wherein, the temperature sensing layer includes multiple layers of thin films, each layer of the thin films has a different temperature; the temperature detection needle penetrates the temperature sensing layer and contacts each layer of the thin film.

12. A running track adjustment device, characterized in that: The device comprises: a communication unit and a processing unit; The communication unit is used to receive a first signal, wherein the first signal includes a signal of a detection signal transmitted by the communication satellite and reflected by the flying object and / or a detection signal of other communication satellites; wherein the flying object and the communication satellite are in the same orbit; The processing unit is used to adjust the operation trajectory of the communication satellite according to the first signal.

13. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer instructions, and when the computer instructions are executed on a computer, the computer is enabled to execute the method for adjusting the running trajectory as described in any one of claims 1 to 8.

14. A computer program product, characterized in that The computer program product comprises computer program instructions, and when the computer program instructions are executed by a processor, the method for adjusting the running trajectory as claimed in any one of claims 1 to 8 is implemented.

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