Spacecraft orbit period adjustment method and device, electronic equipment and storage medium

Abstract

The invention provides a spacecraft orbit period adjustment method and device, electronic equipment and a storage medium, and relates to the technical field of spacecraft control, and the method comprises the steps: determining a current orbit period of a spacecraft based on a current flight state parameter of the spacecraft; determining the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft; determining a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount; the first candidate adjustment scheme is used for performing track period adjustment at any point of the current track; the second candidate adjustment scheme is used for performing orbit period adjustment at the perigee of the current orbit; and selecting and determining an orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme. According to the method and the device provided by the invention, the orbital period of the on-orbit spacecraft is accurately adjusted, and the service life of the on-orbit spacecraft is prolonged.

Description

Technical Field

[0001] The present application relates to the field of spacecraft control technology, and in particular to a method, device, electronic device and storage medium for adjusting the orbital period of a spacecraft. Background Art

[0002] The orbital period is an important parameter that determines the coverage of the earth by the spacecraft in orbit. The flight deviation of the rocket or the influence of various perturbation factors during the actual launch process will cause the orbital parameters of the spacecraft after entering orbit / on-orbit to deviate from the design values ​​to a certain extent, and ultimately make the actual effect of the spacecraft's earth observation fail to meet expectations. In this case, the orbital period must be adjusted to eliminate the deviation and ensure the coverage of the spacecraft.

[0003] In the related technologies, the orbital period adjustment of on-orbit spacecraft is mostly carried out in the form of offline calculation. The offline calculation results cannot adapt to the actual flight status of the spacecraft and there are deviations. At the same time, the energy source for orbital period adjustment of on-orbit spacecraft is mostly consumable working fluids such as chemical propellants and cooling air. Since the spacecraft itself carries limited working fluids, this has a great constraint on the adjustment of the orbital period. If the adjustment consumes too much working fluid, it may even shorten the life of the spacecraft.

[0004] Therefore, how to accurately adjust the orbital period of on-orbit spacecraft, avoid excessive consumption of working fluid, and increase the life of on-orbit spacecraft has become a technical problem that the industry urgently needs to solve. Summary of the invention

[0005] The present application provides a spacecraft orbital period adjustment method, device, electronic equipment and storage medium, which are used to solve the technical problem of how to accurately adjust the orbital period of an on-orbit spacecraft, avoid excessive consumption of working fluid, and increase the life of the on-orbit spacecraft.

[0006] The present application provides a method for adjusting a spacecraft orbit period, comprising: Determining a current orbital period of the spacecraft based on current flight state parameters of the spacecraft; Determining an orbital period adjustment amount for the spacecraft based on the current orbital period and a target orbital period for the spacecraft; Based on the orbital period adjustment amount, determining a first candidate adjustment scheme and a second candidate adjustment scheme; the first candidate adjustment scheme is used to adjust the orbital period at any point of the current orbit; the second candidate adjustment scheme is used to adjust the orbital period at the perigee of the current orbit; An orbital period adjustment scheme for the spacecraft is determined by selecting from the first candidate adjustment scheme and the second candidate adjustment scheme.

[0007] In some embodiments, determining the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft includes: Determining the orbital period adjustment amount based on a difference between the current orbital period and a target orbital period of the spacecraft; When the orbital period adjustment amount is greater than a preset adjustment threshold, determining to adjust the orbital period of the spacecraft; When the orbital period adjustment amount is less than or equal to the preset adjustment threshold, it is determined that the orbital period of the spacecraft is not adjusted.

[0008] In some embodiments, determining a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount includes: Based on the current flight state parameters, determining a first speed-up direction and a first speed-up magnitude for the spacecraft to perform orbital period adjustment at any point of the current orbit, and determining a second speed-up direction and a second speed-up magnitude for the spacecraft to perform orbital period adjustment at the perigee of the current orbit; Determining the working fluid consumption mass of the spacecraft in the first candidate adjustment scheme based on the first acceleration magnitude, the mass of the spacecraft at the engine ignition time, and the specific impulse of the engine of the spacecraft; The working fluid consumption mass of the spacecraft in the second candidate adjustment scheme is determined based on the magnitude of the second acceleration, the mass of the spacecraft at the engine ignition moment, and the specific impulse of the engine of the spacecraft.

[0009] In some embodiments, the method further comprises: When the target orbital period is less than the current orbital period, the speed increasing direction for adjusting the orbital period is along the tangent direction of the current orbit and is the same as the flight direction of the spacecraft; In the case where the target orbital period is greater than the current orbital period, the speed increasing direction for adjusting the orbital period is along the tangent direction of the current orbit and opposite to the flight direction of the spacecraft.

[0010] In some embodiments, the selecting and determining the orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme includes: Determining the current remaining mass of the working fluid of the spacecraft; Compare the working fluid consumption mass in each candidate adjustment scheme with the current working fluid remaining mass respectively; The candidate adjustment scheme in which the working fluid consumption mass is less than the current working fluid remaining mass and the working fluid consumption mass is relatively small is determined as the orbital period adjustment scheme of the spacecraft.

[0011] In some embodiments, the selecting and determining the orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme includes: determining a flight position of the spacecraft in the current orbit; In a case where the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is less than a preset distance, determining the second candidate adjustment scheme as the orbital period adjustment scheme of the spacecraft; When the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is greater than the preset distance, or the flight position has crossed the perigee of the current orbit, the first candidate adjustment scheme is determined as the orbital period adjustment scheme of the spacecraft.

[0012] In some embodiments, before determining the current orbital period of the spacecraft based on the current flight state parameters of the spacecraft, the method further includes: Based on the orbit adjustment instruction sent by the control system of the spacecraft or the orbit adjustment instruction sent by the ground control station, it is determined to adjust the current orbit period of the spacecraft.

[0013] The present application provides a spacecraft orbit period adjustment device, comprising: a period calculation unit, configured to determine a current orbital period of the spacecraft based on a current flight state parameter of the spacecraft; a period comparison unit, configured to determine an orbital period adjustment amount of the spacecraft based on the current orbital period and a target orbital period of the spacecraft; a scheme determination unit, configured to determine a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount; the first candidate adjustment scheme is used to perform orbital period adjustment at any point of the current orbit; the second candidate adjustment scheme is used to perform orbital period adjustment at the perigee of the current orbit; A period adjustment unit is used to select and determine the orbit period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme.

[0014] The present application provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the spacecraft orbit period adjustment method when executing the computer program.

[0015] The present application provides a non-transitory computer-readable storage medium having a computer program stored thereon, and when the computer program is executed by a processor, the spacecraft orbit period adjustment method is implemented.

[0016] The spacecraft orbital period adjustment method, device, electronic device and storage medium provided in the present application determine the current orbital period of the spacecraft based on the current flight state parameters of the spacecraft; determine the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft; determine a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount; the first candidate adjustment scheme is used to adjust the orbital period at any point in the current orbit; the second candidate adjustment scheme is used to adjust the orbital period at the perigee of the current orbit; the orbital period adjustment scheme of the spacecraft is determined by selecting from the first candidate adjustment scheme and the second candidate adjustment scheme; since the orbital period adjustment scheme is determined based on the current flight state parameters of the spacecraft, and the optimal scheme is selected based on the current remaining mass of the working fluid of the spacecraft, the actual on-orbit situation of the spacecraft is taken into consideration, and the orbital period of the on-orbit spacecraft can be accurately adjusted, excessive consumption of working fluid is avoided, and the life of the on-orbit spacecraft is increased. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0018] In order to more clearly illustrate the technical solutions in the present application or the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 This is one of the flow charts of the spacecraft orbit period adjustment method provided in this application.

[0020] Figure 2 This is the second flow chart of the spacecraft orbit period adjustment method provided in this application.

[0021] Figure 3 It is a schematic diagram of the structure of the spacecraft orbit period adjustment device provided in this application.

[0022] Figure 4 It is a structural schematic diagram of the electronic device provided by this application. DETAILED DESCRIPTION

[0023] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0024] It should be noted that the terms "first", "second" etc. in the present application are used to distinguish similar objects, and need not be used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchangeable in appropriate circumstances, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, the process, method, system, product or equipment comprising a series of steps or units or modules need not be limited to those steps or units or modules clearly listed, but may include other steps or units or modules that are not clearly listed or inherent to these processes, methods, products or equipment.

[0025] Due to the influence of various factors, the orbital period of an on-orbit spacecraft may deviate from the designed value, and the orbital period determines the quality of its ground coverage. At this time, the orbital period must be corrected and adjusted. In actual engineering applications, the correction and adjustment of the orbital period of an on-orbit spacecraft must take into account multiple factors such as the simplicity of the adjustment method, the satisfaction of the adjustment accuracy, and the acceptable adjustment energy consumption.

[0026] In order to solve the shortcomings of related technologies, Figure 1 This is one of the flow charts of the spacecraft orbit period adjustment method provided in this application, such as Figure 1 As shown, the method includes step 110 , step 120 , step 130 and step 140 .

[0027] Step 110: Determine the current orbital period of the spacecraft based on the current flight state parameters of the spacecraft.

[0028] Specifically, the execution subject of the spacecraft orbit period adjustment method provided in the embodiment of the present application is a spacecraft orbit period adjustment device. The device can be implemented by software, such as a spacecraft orbit period adjustment program running in a spacecraft control system; or by hardware, such as a computer or server that executes the spacecraft orbit period adjustment method.

[0029] The application scenario of the spacecraft orbital period adjustment method provided in the embodiment of the present application is the real-time flight scenario of an on-orbit spacecraft. On-orbit spacecraft refers to spacecraft that are in orbit, such as satellites and orbit-retaining platforms, and does not include suborbital spacecraft that are not in orbit and other spacecraft that are not in orbit. Orbital adjustment refers to changing the orbital period of an on-orbit spacecraft by external force.

[0030] Flight state parameters refer to the parameters that describe the various important physical characteristics and states of the rocket during flight, such as position, speed, and trajectory. Current flight state parameters refer to the flight state parameters of the spacecraft at the current moment.

[0031] The orbital period of a spacecraft refers to the time it takes for a spacecraft to complete one complete motion in its orbit. The orbital period is closely related to the orbit. The current orbital period refers to the orbital period of the spacecraft in its current orbit.

[0032] According to the current flight status parameters of the spacecraft, the parameters such as the orbital semi-major axis, eccentricity, true anomaly angle and current orbital period of the spacecraft in the current orbit can be obtained.

[0033] Among them, the semi-major axis of the orbit is the distance from the center to the end point of the major axis of the ellipse in the elliptical orbit; it represents the size of the orbit and is the main scale of the ellipse. Eccentricity is a dimensionless parameter that describes the shape of the elliptical orbit. The true anomaly angle refers to the angle swept by the radial direction of the celestial body when it moves along the orbit from the perigee. It is the angle between the orbit perigee and the satellite position vector at a certain moment. The true anomaly determines the specific position of the satellite in the orbit.

[0034] Step 120: Determine the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft.

[0035] Specifically, the target orbital period refers to the orbital period of the spacecraft flying in the target orbit. The target orbit is the ideal orbit or designed orbit for the spacecraft to perform its flight mission. By comparing the current orbital period with the target orbital period of the spacecraft, the orbital period adjustment amount of the spacecraft can be determined.

[0036] Step 130: Based on the orbital period adjustment amount, determine a first candidate adjustment scheme and a second candidate adjustment scheme; the first candidate adjustment scheme is used to adjust the orbital period at any point of the current orbit; the second candidate adjustment scheme is used to adjust the orbital period at the perigee of the current orbit. In the first candidate adjustment scheme, any point of the current orbit does not include the perigee.

[0037] Specifically, based on the principle of space orbit perturbation, the perturbation equation of the orbital period is established, and the following conclusions can be obtained by deducing and proving it: When a spacecraft makes orbital period adjustments at any point in its orbit, there is a way to adjust it in the most energy-efficient way, which can be understood as the local optimal adjustment way; compared with any point in the orbit, the energy required to make orbital period adjustments at the perigee of the orbit is the smallest, which can be understood as the global optimal adjustment way. The perigee of the orbit refers to the point on its elliptical orbit where the spacecraft is closest to the center of the earth.

[0038] According to the above conclusions, two candidate adjustment schemes can be determined according to the orbital period adjustment amount to adjust the current orbital period of the spacecraft. The two candidate adjustment schemes are: the first candidate adjustment scheme is used to adjust the orbital period at any point in the current orbit, which can also be called the local optimal adjustment method; the second candidate adjustment scheme is used to adjust the orbital period at the perigee of the current orbit.

[0039] Step 140: Select and determine the orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme.

[0040] Specifically, the first candidate adjustment scheme and the second candidate adjustment scheme have different impacts on the spacecraft. For example, they will have a significant impact on the working fluid consumption of the spacecraft.

[0041] The working fluid is the medium carried by the spacecraft to generate propulsion, which can include fuel and oxidizer. The energy source for spacecraft to adjust the orbital period is mostly consumable working fluids such as chemical propellants and cooling air. Since the spacecraft itself carries limited working fluids, this has a great constraint on the adjustment of the orbital period. If the adjustment consumes too much working fluid, it may even shorten the life of the spacecraft.

[0042] The current remaining mass of the working fluid is the remaining mass of the working fluid in the spacecraft at the current moment. It can be used to measure the remaining working fluid in the spacecraft, and can also be used to indicate the remaining energy of the spacecraft. The remaining energy of the spacecraft can measure the on-orbit life of the spacecraft.

[0043] The working fluid mass consumed by the first candidate adjustment scheme and the second candidate adjustment scheme can be calculated. The working fluid mass consumed is compared with the current remaining working fluid mass to determine an adjustment scheme that can be implemented and consumes less working fluid mass, that is, the final orbital period adjustment scheme.

[0044] The spacecraft orbital period adjustment method provided in the embodiment of the present application determines the current orbital period of the spacecraft based on the current flight state parameters of the spacecraft; determines the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft; determines a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount; the first candidate adjustment scheme is used to adjust the orbital period at any point in the current orbit; the second candidate adjustment scheme is used to adjust the orbital period at the perigee of the current orbit; the orbital period adjustment scheme of the spacecraft is determined by selecting from the first candidate adjustment scheme and the second candidate adjustment scheme; since the orbital period adjustment scheme is determined based on the current flight state parameters of the spacecraft, and the optimal scheme is selected based on the current remaining mass of the working fluid of the spacecraft, the actual on-orbit situation of the spacecraft is taken into consideration, and the orbital period of the on-orbit spacecraft can be accurately adjusted, thereby avoiding excessive consumption of working fluid and increasing the life of the on-orbit spacecraft.

[0045] It should be noted that each implementation method of the present application can be freely combined, the order can be changed, or it can be executed separately, and does not need to rely on or depend on a fixed execution order.

[0046] In some embodiments, determining the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft includes: determining an orbital period adjustment based on a difference between a current orbital period and a target orbital period of the spacecraft; When the orbital period adjustment amount is greater than a preset adjustment threshold, determining to adjust the orbital period of the spacecraft; When the orbital period adjustment amount is less than or equal to a preset adjustment threshold, it is determined that the orbital period of the spacecraft is not adjusted.

[0047] Specifically, according to the current orbital period The target orbital period of the spacecraft The difference between , which can be expressed as: .

[0048] A preset adjustment threshold can be set to indicate the allowable fluctuation range of the orbital period, that is, the threshold of the orbital period adjustment. The preset adjustment threshold can be determined according to the design requirements of the spacecraft or the flight mission requirements performed by the spacecraft. For example, if the flight mission has a high requirement for the orbital period, the preset adjustment threshold can be set to a smaller value; if the flight mission has a low requirement for the orbital period, the preset adjustment threshold can be set to a larger value.

[0049] When the orbital period adjustment amount is greater than the preset adjustment threshold, it means that the deviation between the current orbital period and the target orbital period is large, exceeding the allowable fluctuation range of the orbital period, so the orbital period of the spacecraft needs to be adjusted; when the orbital period adjustment amount is less than or equal to the preset adjustment threshold, it means that the deviation between the current orbital period and the target orbital period is small, within the allowable fluctuation range of the orbital period, so there is no need to adjust the orbital period of the spacecraft.

[0050] It is understandable that the smaller the preset adjustment threshold is, the more times the orbital period is adjusted, the more the spacecraft's working fluid is consumed, and the shorter the life of the spacecraft.

[0051] The spacecraft orbital period adjustment method provided in the embodiment of the present application compares the orbital period adjustment amount with a preset adjustment threshold to determine whether to adjust the orbital period of the spacecraft, thereby avoiding frequent orbital period adjustments, avoiding excessive consumption of working fluids, and increasing the life of the on-orbit spacecraft.

[0052] In some embodiments, based on the orbital period adjustment amount, determining a first candidate adjustment solution and a second candidate adjustment solution includes: Based on the current flight state parameters, determine the orbital semi-major axis, eccentricity, true anomaly and current orbital period of the spacecraft in the current orbit; Determine a first acceleration direction and a first acceleration magnitude of the orbital period adjustment of the spacecraft at any point in the current orbit based on the orbital period adjustment amount, the orbital semi-major axis, the eccentricity, the true anomaly angle and the current orbital period; The working fluid consumption mass of the spacecraft in the first candidate adjustment scheme is determined based on the first acceleration magnitude, the mass of the spacecraft at the engine ignition moment, and the specific impulse of the engine of the spacecraft.

[0053] Specifically, the current flight state parameters can be obtained according to the receivers and sensors installed in the spacecraft, and the orbital semi-major axis, eccentricity, true anomaly angle and current orbital period of the spacecraft in the current orbit can be calculated based on the current flight state parameters.

[0054] If the spacecraft makes an orbital period adjustment at any point in its current orbit, it can be adjusted based on the orbital semi-major axis. , eccentricity True Anomaly and the current orbital period , according to the basic function relationship of the elliptical orbit, calculate the first acceleration , expressed as: .

[0055] In the formula, is the first speed calculation function; is an intermediate variable, expressed by the formula: .

[0056] In the formula, It is the first speed increasing direction.

[0057] The formula for the first speed increase can be proved by trigonometric functions, which has a local minimum and can be expressed as: .

[0058] Furthermore, it can be proved that there is a global minimum in the entire orbit. At this time, any point is the perigee on the current orbit, and the second acceleration can be obtained. The formula is: .

[0059] For the first acceleration direction, when the orbital period adjustment amount is less than 0, the first acceleration direction is 0°; when the orbital period adjustment amount is greater than 0, the first acceleration direction is 180°.

[0060] According to the first speed increase , the mass of the spacecraft at the time of engine ignition and the specific impulse of the spacecraft's engine , the Tsiolkovsky formula can be used to derive the mass of the working fluid consumed by the spacecraft in the first candidate adjustment scheme , expressed as: .

[0061] In the formula, Is the natural base.

[0062] The spacecraft orbital period adjustment method provided in the embodiment of the present application determines the first acceleration direction, the first acceleration magnitude and the working fluid consumption mass of the first candidate adjustment scheme according to the current flight state parameters, so as to facilitate comprehensive consideration and global evaluation of other systems such as the spacecraft's energy management and life management.

[0063] In some embodiments, based on the orbital period adjustment amount, determining a first candidate adjustment solution and a second candidate adjustment solution includes: Based on the current flight state parameters, determine the orbital semi-major axis, eccentricity and current orbital period of the spacecraft in the current orbit; Determine a second speed increase direction and a second speed increase magnitude of the orbital period adjustment of the spacecraft at the perigee of the current orbit based on the orbital period adjustment amount, the orbital semi-major axis, the eccentricity and the current orbital period; The working fluid consumption mass of the spacecraft in the second candidate adjustment scheme is determined based on the second acceleration magnitude, the mass of the spacecraft at the engine ignition moment, and the specific impulse of the engine of the spacecraft.

[0064] Specifically, if the spacecraft makes an orbital period adjustment at the perigee of the current orbit, it can adjust the orbital period according to the semi-major axis of the orbit. , eccentricity and the current orbital period , according to the basic function relationship of the elliptical orbit, calculate the second speed increase , expressed as: .

[0065] In the formula, is the second speed calculation function. The specific calculation formula of the second speed has been listed in the above embodiment and will not be repeated here.

[0066] For the second acceleration direction, when the orbital period adjustment amount is less than 0, the second acceleration direction is 0 degrees; when the orbital period adjustment amount is greater than 0, the second acceleration direction is 180 degrees. In other words, the determination of the second acceleration direction is the same as the first acceleration direction.

[0067] According to the second speed increase , the mass of the spacecraft at the time of engine ignition and the specific impulse of the spacecraft's engine , the Tsiolkovsky formula can be used to derive the mass of the working fluid consumed by the spacecraft in the second candidate adjustment scheme , expressed as: .

[0068] In the formula, Is the natural base.

[0069] The spacecraft orbital period adjustment method provided in the embodiment of the present application determines the second acceleration direction, second acceleration magnitude and working fluid consumption mass of the second candidate adjustment scheme according to the current flight state parameters, so as to facilitate comprehensive consideration and global evaluation of other systems such as energy management and life management of the spacecraft.

[0070] In some embodiments, the method further comprises: When the target orbital period is smaller than the current orbital period, the speed increase direction for orbital period adjustment is along the tangent direction of the current orbit and is the same as the flight direction of the spacecraft; When the target orbital period is greater than the current orbital period, the speed increase direction for adjusting the orbital period is along the tangent direction of the current orbit and opposite to the flight direction of the spacecraft.

[0071] Specifically, according to the principle of space orbit perturbation, the perturbation equation of the orbit period is established, and the following conclusions can be obtained by deducing and proving it: When the target orbital period is smaller than the current orbital period, The first acceleration direction or the second acceleration direction for orbital period adjustment is along the tangent direction of the current orbit and is the same as the flight direction of the spacecraft, that is, forward, and the acceleration direction is 0 degrees.

[0072] When the target orbital period is greater than the current orbital period, The acceleration direction for orbital period adjustment is along the tangent direction of the current orbit and opposite to the flight direction of the spacecraft, that is, forward, and the acceleration direction is 180 degrees.

[0073] The spacecraft orbital period adjustment method provided in the embodiment of the present application determines the speed increase direction for orbital period adjustment according to the size of the target orbital period and the current orbital period, thereby accurately adjusting the orbital period of the on-orbit spacecraft.

[0074] In some embodiments, selecting and determining the orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme includes: Determine the current remaining mass of the working fluid in the spacecraft; Compare the working fluid consumption mass in each candidate adjustment scheme with the current working fluid remaining mass; The candidate adjustment scheme whose working fluid consumption mass is less than the current working fluid remaining mass and whose working fluid consumption mass is smaller is determined as the orbital period adjustment scheme of the spacecraft.

[0075] Specifically, the working fluid consumption mass in each candidate adjustment scheme is compared with the current working fluid remaining mass. If the working fluid consumption mass is less than the current working fluid remaining mass, it means that the candidate adjustment scheme can be executed. At this time, the candidate adjustment scheme with a smaller working fluid consumption mass can be selected as the orbital period adjustment scheme of the spacecraft, so that the energy consumed by the orbital period adjustment of the spacecraft is minimized.

[0076] The spacecraft orbital period adjustment method provided in the embodiment of the present application selects a candidate adjustment scheme whose working fluid consumption mass is less than the current remaining mass of the working fluid and whose working fluid consumption mass is smaller as the final orbital period adjustment scheme, thereby avoiding excessive consumption of working fluid and increasing the life of the on-orbit spacecraft.

[0077] In some embodiments, selecting and determining the orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme includes: Determine the spacecraft's flight position in its current orbit; When the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is less than a preset distance, determining the second candidate adjustment scheme as the orbital period adjustment scheme of the spacecraft; When the flight position has not reached the perigee of the current orbit and the distance between the flight position and the perigee is greater than a preset distance, or the flight position has crossed the perigee of the current orbit, the first candidate adjustment scheme is determined as the orbital period adjustment scheme of the spacecraft.

[0078] Specifically, according to the current flight status parameters of the spacecraft, the flight position of the spacecraft in the current orbit can also be determined.

[0079] Compare the flight position to the perigee of the current orbit: If the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is less than the preset distance, considering that the energy consumption at the perigee is usually the smallest, the second candidate adjustment scheme can be determined as the orbital period adjustment scheme of the spacecraft, that is, the orbital period adjustment is performed after the spacecraft reaches the perigee. The preset distance can be adjusted as needed.

[0080] If the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is greater than the preset distance, or the flight position has crossed the perigee of the current orbit, then considering the real-time requirements of the flight mission, the first candidate adjustment plan can be determined as the orbital period adjustment plan of the spacecraft, that is, to perform orbital period adjustment at the current flight position.

[0081] The spacecraft orbital period adjustment method provided in the embodiment of the present application can flexibly select candidate adjustment schemes according to the flight position of the spacecraft in the current orbit, which can meet the flight mission requirements of the spacecraft, improve the real-time performance of the orbital period adjustment, and reduce the energy consumed by the orbital adjustment.

[0082] In some embodiments, before determining the current orbital period of the spacecraft based on the current flight state parameters of the spacecraft, the method further includes: Based on the orbit adjustment instruction sent by the control system of the spacecraft or the orbit adjustment instruction sent by the ground control station, it is determined to adjust the current orbit period of the spacecraft.

[0083] Specifically, the above-mentioned spacecraft orbit period adjustment method can be triggered to run in two ways.

[0084] The first way is that the spacecraft's control system sends an orbit adjustment command, which triggers the adjustment of the spacecraft's current orbit period. The control system automatically judges and executes according to the settings.

[0085] The second way is that the orbit adjustment command sent by the ground control station triggers the adjustment of the current orbit period of the spacecraft. The ground control personnel of the ground control station make judgments and execute them according to the actual flight situation.

[0086] The spacecraft orbit period adjustment method provided in the embodiment of the present application uses two methods to trigger the operation of the spacecraft orbit period adjustment, thereby improving the flexibility of the spacecraft orbit period adjustment.

[0087] Figure 2 This is the second flow chart of the spacecraft orbit period adjustment method provided by this application, such as Figure 2 As shown, the method includes: Step 210: Status acquisition and judgment.

[0088] The current flight status parameters of the spacecraft are obtained based on the receiver, sensors and other equipment, and the corresponding orbital parameters are calculated; at the same time, the difference between the current orbital period and the expected orbital period is calculated. If the difference is small, the parameters will continue to be updated. If it exceeds the expected range, the subsequent process will be executed.

[0089] Step 220: Calculate the speed increase and energy required for orbital period adjustment.

[0090] Determine candidate adjustment schemes using any point on the orbit (excluding perigee) and perigee, and calculate the speed increase and energy required for orbital period adjustment.

[0091] Step 230: Decision making and execution.

[0092] The results of each candidate adjustment plan in the previous step are fed back to the energy / life management system. If the remaining energy is seriously insufficient or the life is seriously affected after adjustment, no adjustment will be performed. If there is a feasible plan among the candidate adjustment plans, a plan will be selected according to the situation and fed back to the power and control system to enter the execution process.

[0093] For example, taking a satellite in orbit, its orbit semi-major axis is 6886.6 km, the orbit eccentricity is 0.000, and the current orbit period (5688 seconds) deviates from the expected value (5690 seconds) by 2 seconds. If the adjustment at the perigee is adopted, the corresponding speed increase is per second per meter (the acceleration rate is negative, that is, its direction is along the tangent of the track and opposite to the flight speed), corresponding to a working fluid consumption of 0.01 kg.

[0094] The spacecraft orbital period adjustment method provided in the embodiment of the present application can calculate the deviation from the original design or expected orbital period according to the current flight situation of the on-orbit spacecraft. Based on the deviation and combined with the current flight parameters of the spacecraft, the acceleration direction and minimum speed value required for the spacecraft to adjust the orbital period at any position can be calculated, and the energy (propellant mass) required to generate the acceleration can be given. The various results are fed back to the on-orbit spacecraft energy / life management system for comprehensive evaluation, and then it is decided whether the spacecraft should adjust the orbital period and when and where to adjust the orbital period. This method can monitor the flight situation of the on-orbit spacecraft in real time, and can provide the most energy-saving orbital period adjustment plan in real time when necessary, and make corresponding decisions taking into account the subsequent on-orbit life of the spacecraft.

[0095] The device provided in the embodiment of the present application is described below. The device described below and the method described above can be referenced to each other.

[0096] Figure 3 is a schematic diagram of the structure of the spacecraft orbit period adjustment device provided by the present application, such as Figure 3 As shown, the device comprises: The period calculation unit 310 is used to determine the current orbit period of the spacecraft based on the current flight state parameters of the spacecraft; A period comparison unit 320, for determining an orbital period adjustment amount for the spacecraft based on the current orbital period and the target orbital period of the spacecraft; A scheme determination unit 330 is used to determine a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount; the first candidate adjustment scheme is used to perform orbital period adjustment at any point of the current orbit; the second candidate adjustment scheme is used to perform orbital period adjustment at the perigee of the current orbit; The period adjustment unit 340 is used to select and determine the orbit period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme.

[0097] The spacecraft orbital period adjustment device provided in the embodiment of the present application determines the current orbital period of the spacecraft based on the current flight state parameters of the spacecraft; determines the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft; determines a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount; the first candidate adjustment scheme is used to adjust the orbital period at any point in the current orbit; the second candidate adjustment scheme is used to adjust the orbital period at the perigee of the current orbit; the orbital period adjustment scheme of the spacecraft is determined by selecting from the first candidate adjustment scheme and the second candidate adjustment scheme; since the orbital period adjustment scheme is determined based on the current flight state parameters of the spacecraft, and the optimal scheme is selected based on the current remaining mass of the working fluid of the spacecraft, the actual on-orbit situation of the spacecraft is taken into consideration, and the orbital period of the on-orbit spacecraft can be accurately adjusted, thereby avoiding excessive consumption of working fluid and increasing the life of the on-orbit spacecraft.

[0098] In some embodiments, the cycle comparison unit is used to: determining an orbital period adjustment based on a difference between a current orbital period and a target orbital period of the spacecraft; When the orbital period adjustment amount is greater than a preset adjustment threshold, determining to adjust the orbital period of the spacecraft; When the orbital period adjustment amount is less than or equal to a preset adjustment threshold, it is determined that the orbital period of the spacecraft is not adjusted.

[0099] In some embodiments, the regimen determination unit is configured to: Based on the current flight state parameters, determine the orbital semi-major axis, eccentricity, true anomaly and current orbital period of the spacecraft in the current orbit; Determine a first acceleration direction and a first acceleration magnitude of the orbital period adjustment of the spacecraft at any point in the current orbit based on the orbital period adjustment amount, the orbital semi-major axis, the eccentricity, the true anomaly angle and the current orbital period; The working fluid consumption mass of the spacecraft in the first candidate adjustment scheme is determined based on the first acceleration magnitude, the mass of the spacecraft at the engine ignition moment, and the specific impulse of the engine of the spacecraft.

[0100] In some embodiments, the regimen determination unit is configured to: Based on the current flight state parameters, determine the orbital semi-major axis, eccentricity and current orbital period of the spacecraft in the current orbit; Determine a second speed increase direction and a second speed increase magnitude of the orbital period adjustment of the spacecraft at the perigee of the current orbit based on the orbital period adjustment amount, the orbital semi-major axis, the eccentricity and the current orbital period; The working fluid consumption mass of the spacecraft in the second candidate adjustment scheme is determined based on the second acceleration magnitude, the mass of the spacecraft at the engine ignition moment, and the specific impulse of the engine of the spacecraft.

[0101] In some embodiments, when the target orbital period is less than the current orbital period, the speed increase direction for adjusting the orbital period is along the tangent direction of the current orbit and is the same as the flight direction of the spacecraft; When the target orbital period is greater than the current orbital period, the speed increase direction for adjusting the orbital period is along the tangent direction of the current orbit and opposite to the flight direction of the spacecraft.

[0102] In some embodiments, the period adjustment unit is configured to: Determine the current remaining mass of the working fluid in the spacecraft; Compare the working fluid consumption mass in each candidate adjustment scheme with the current working fluid remaining mass; The candidate adjustment scheme whose working fluid consumption mass is less than the current working fluid remaining mass and whose working fluid consumption mass is smaller is determined as the orbital period adjustment scheme of the spacecraft.

[0103] In some embodiments, the period adjustment unit is configured to: Determine the spacecraft's flight position in its current orbit; When the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is less than a preset distance, determining the second candidate adjustment scheme as the orbital period adjustment scheme of the spacecraft; When the flight position has not reached the perigee of the current orbit and the distance between the flight position and the perigee is greater than a preset distance, or the flight position has crossed the perigee of the current orbit, the first candidate adjustment scheme is determined as the orbital period adjustment scheme of the spacecraft.

[0104] In some embodiments, the device is used to: Based on the orbit adjustment instruction sent by the control system of the spacecraft or the orbit adjustment instruction sent by the ground control station, it is determined to adjust the current orbit period of the spacecraft.

[0105] Figure 4 is a schematic diagram of the structure of the electronic device provided by this application, such as Figure 4As shown, the electronic device may include: a processor (Processor) 410, a communication interface (Communications Interface) 420, a memory (Memory) 430 and a communication bus (Communications Bus) 440, wherein the processor 410, the communication interface 420, and the memory 430 communicate with each other through the communication bus 440. The processor 410 may call the logic command in the memory 430 to execute the method described in the above embodiment, for example: Based on the current flight status parameters of the spacecraft, the current orbital period of the spacecraft is determined; based on the current orbital period and the target orbital period of the spacecraft, the orbital period adjustment amount of the spacecraft is determined; based on the orbital period adjustment amount, a first candidate adjustment scheme and a second candidate adjustment scheme are determined; the first candidate adjustment scheme is used to make orbital period adjustments at any point in the current orbit; the second candidate adjustment scheme is used to make orbital period adjustments at the perigee of the current orbit; the orbital period adjustment scheme of the spacecraft is determined by selecting between the first candidate adjustment scheme and the second candidate adjustment scheme.

[0106] In addition, the logical commands in the above-mentioned memory can be implemented in the form of software functional units and can be stored in a computer-readable storage medium when sold or used as an independent product. Based on this understanding, the technical solution of the present application can be essentially or partly embodied in the form of a software product that contributes to the prior art. The computer software product is stored in a storage medium and includes several commands to enable a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc., which can store program code.

[0107] The processor in the electronic device provided in the embodiment of the present application can call the logic instructions in the memory to implement the above method. Its specific implementation method is consistent with the implementation method of the aforementioned method and can achieve the same beneficial effects, which will not be repeated here.

[0108] An embodiment of the present application also provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the methods provided in the above embodiments are implemented.

[0109] Its specific implementation is consistent with the aforementioned method implementation and can achieve the same beneficial effects, so it will not be repeated here.

[0110] An embodiment of the present application provides a computer program product, including a computer program, which implements the above method when executed by a processor.

[0111] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0112] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0113] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A method for adjusting a spacecraft orbit period, characterized in that: include: Determining a current orbital period of the spacecraft based on current flight state parameters of the spacecraft; Determining an orbital period adjustment amount for the spacecraft based on the current orbital period and a target orbital period for the spacecraft; Based on the orbital period adjustment amount, determining a first candidate adjustment scheme and a second candidate adjustment scheme; the first candidate adjustment scheme is used to adjust the orbital period at any point of the current orbit; the second candidate adjustment scheme is used to adjust the orbital period at the perigee of the current orbit; An orbital period adjustment scheme for the spacecraft is determined by selecting from the first candidate adjustment scheme and the second candidate adjustment scheme.

2. The method for adjusting the spacecraft orbital period according to claim 1, characterized in that: The step of determining the orbital period adjustment amount of the spacecraft based on the current orbital period and the target orbital period of the spacecraft comprises: Determining the orbital period adjustment amount based on a difference between the current orbital period and a target orbital period of the spacecraft; When the orbital period adjustment amount is greater than a preset adjustment threshold, determining to adjust the orbital period of the spacecraft; When the orbital period adjustment amount is less than or equal to the preset adjustment threshold, it is determined that the orbital period of the spacecraft is not adjusted.

3. The method for adjusting the spacecraft orbital period according to claim 1, characterized in that: The determining, based on the orbital period adjustment amount, a first candidate adjustment scheme and a second candidate adjustment scheme comprises: Based on the current flight state parameters, determining a first speed-up direction and a first speed-up magnitude for the spacecraft to perform orbital period adjustment at any point of the current orbit, and determining a second speed-up direction and a second speed-up magnitude for the spacecraft to perform orbital period adjustment at the perigee of the current orbit; Determining the working fluid consumption mass of the spacecraft in the first candidate adjustment scheme based on the first acceleration magnitude, the mass of the spacecraft at the engine ignition time, and the specific impulse of the engine of the spacecraft; The working fluid consumption mass of the spacecraft in the second candidate adjustment scheme is determined based on the magnitude of the second acceleration, the mass of the spacecraft at the engine ignition moment, and the specific impulse of the engine of the spacecraft.

4. The method for adjusting the spacecraft orbital period according to claim 1, characterized in that: The method further comprises: When the target orbital period is less than the current orbital period, the speed increasing direction for adjusting the orbital period is along the tangent direction of the current orbit and is the same as the flight direction of the spacecraft; In the case where the target orbital period is greater than the current orbital period, the speed increasing direction for adjusting the orbital period is along the tangent direction of the current orbit and opposite to the flight direction of the spacecraft.

5. The method for adjusting the spacecraft orbital period according to claim 1, characterized in that: The step of selecting and determining the orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme comprises: Determining the current remaining mass of the working fluid of the spacecraft; Compare the working fluid consumption mass in each candidate adjustment scheme with the current working fluid remaining mass respectively; The candidate adjustment scheme in which the working fluid consumption mass is less than the current working fluid remaining mass and the working fluid consumption mass is relatively small is determined as the orbital period adjustment scheme of the spacecraft.

6. The method for adjusting the spacecraft orbital period according to claim 1, characterized in that: The step of selecting and determining the orbital period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme further includes: determining a flight position of the spacecraft in the current orbit; In a case where the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is less than a preset distance, determining the second candidate adjustment scheme as the orbital period adjustment scheme of the spacecraft; When the flight position has not yet reached the perigee of the current orbit and the distance between the flight position and the perigee is greater than the preset distance, or the flight position has crossed the perigee of the current orbit, the first candidate adjustment scheme is determined as the orbital period adjustment scheme of the spacecraft.

7. The method for adjusting the spacecraft orbital period according to claim 1, characterized in that: Before determining the current orbital period of the spacecraft based on the current flight state parameters of the spacecraft, the method further includes: Based on the orbit adjustment instruction sent by the control system of the spacecraft or the orbit adjustment instruction sent by the ground control station, it is determined to adjust the current orbit period of the spacecraft.

8. A spacecraft orbit period adjustment device, characterized in that: include: a period calculation unit, configured to determine a current orbital period of the spacecraft based on a current flight state parameter of the spacecraft; a period comparison unit, configured to determine an orbital period adjustment amount of the spacecraft based on the current orbital period and a target orbital period of the spacecraft; a scheme determination unit, configured to determine a first candidate adjustment scheme and a second candidate adjustment scheme based on the orbital period adjustment amount; the first candidate adjustment scheme is used to perform orbital period adjustment at any point of the current orbit; the second candidate adjustment scheme is used to perform orbital period adjustment at the perigee of the current orbit; A period adjustment unit is used to select and determine the orbit period adjustment scheme of the spacecraft from the first candidate adjustment scheme and the second candidate adjustment scheme.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the spacecraft orbit period adjustment method according to any one of claims 1 to 7 is implemented.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the spacecraft orbit period adjustment method according to any one of claims 1 to 7 is implemented.

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