Transportation work satellite load autonomous power consumption optimization method, device, medium and system

Abstract

The invention discloses a transit working satellite load autonomous power consumption optimization method, device, medium and system, and belongs to the technical field of satellites, comprising an autonomous exit-entry judgment process, realizing rapid judgment of a satellite load exit-entry state in a distance calculation mode, being capable of adapting to the influence brought by orbit height change after satellite orbital transfer, and improving the accuracy of the autonomous power consumption optimization of the transit working satellite load. The exit delay and entry delay of the satellite are calculated autonomously through the transit load, and an energy management unit of the satellite is combined, so that autonomous overseas shutdown of the transit work load and autonomous startup before entry are realized, and energy consumed by overseas standby work of the transit work load is saved. The method can solve the problem that satellite energy is tight, and can promote satellite development and application.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, and more specifically, to a method, device, medium and system for optimizing autonomous power consumption of a transit satellite payload. Background Art

[0002] When the satellite is in orbit and performing its mission, some payloads only need to work in the territory. The payloads switch their working modes by determining the entry and exit status of the current satellite. They work in full state in the territory and in standby mode outside the territory. For example, the data transmission payload used for communication between the satellite and the ground station needs to turn on the transmitting component during the satellite transit and turn off the transmitting component after leaving the territory to prevent the signal from being maliciously received outside the territory, while achieving the purpose of saving satellite power consumption.

[0003] The standby working mode of the transit payload abroad can certainly save some power consumption, but some modules are still in working state. This part of energy will be wasted abroad. In addition, with the vigorous development and application of small low-orbit satellites at this stage, satellite energy is more tight and the control of power consumption is more stringent. How to utilize the energy consumed by the payload standby work after leaving the country is a current problem, and there is no effective solution yet. Summary of the invention

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and to provide a method, device, medium and system for optimizing the autonomous power consumption of a transit satellite payload, which can solve the problem of satellite energy shortage and promote the development and application of satellites.

[0005] The object of the present invention is achieved through the following solutions:

[0006] A method for optimizing autonomous power consumption of a transit satellite payload comprises the following steps:

[0007] S1: Build a system working architecture including a transit workload and a power management unit for powering the workload;

[0008] S2: Get the current satellite position coordinates S, the ground station position coordinates T and the effective visible elevation angle γ of the ground station;

[0009] S3: Calculate the visible distance threshold, which is related to the satellite's position and the ground station's visible angle γ, and can adapt to the impact of satellite orbit changes. The calculation formula is as follows:

[0010]

[0011] Where θ is the calculation angle, and θ = (90 + γ)°, R is the radius of the earth, X s , Y s , Z s are the XYZ coordinates of the satellite in the Earth-fixed coordinate system;

[0012] S4: Calculate the straight-line distance between the satellite position S and the ground station T, recorded as d;

[0013] S5: Determine the difference between the distance d and the threshold. If d≤D, the satellite is considered visible. If d>D, the satellite is considered invisible.

[0014] S6: The transit load executes the autonomous calculation process to obtain the current system time T 0 The satellite position under 0 ;

[0015] S7: Calculate the distance threshold D according to formula (1), and simultaneously calculate the straight-line distance between the satellite and the ground station. The satellite autonomously determines whether the ground station is visible.

[0016] S8: If the ground station is not visible, go back to step 6; if the ground station is visible, it means the satellite is within the territory, and execute step 9;

[0017] S9: Extrapolate time t to obtain T 0 + Satellite position X at time t 1 , calculate the distance threshold D according to formula (1), and calculate the straight-line distance d between the satellite and the ground station 1 , the satellite autonomously determines whether the ground station is visible;

[0018] S10: If the ground station is visible, execute step 9 and continue to extrapolate time t to calculate T 0 Satellite position X at time +2t 2 , and determine whether the satellite is visible according to step 9; after executing n times, T 0 +n·t corresponding to the satellite position is recorded as X n If the ground is not visible, it means the satellite is out of the sky, and the time T is recorded. 1 =T 0 +(n+1)·t is the departure time of the satellite;

[0019] S11: In T 1 On this basis, continue to extrapolate time t to obtain T 0 Satellite position X at time +(n+1)·t n+1 , calculate the distance threshold and determine whether the satellite is visible;

[0020] S12: If the ground station is not visible, indicating that the satellite is outside the country, then execute S11, continue to extrapolate time t, and determine whether the satellite is visible according to step 11; after executing m times, T 0 +(n+m)·t corresponds to the satellite position X n+m If the ground station is visible, it means that the satellite has just entered the country, and the time T is recorded.2 =T 0 +(n+m-1)·t is the entry time of the satellite;

[0021] S13: The calculated departure time T 1 and entry time T 2 The data packets are packaged according to the established data packet format and sent to the satellite's energy management unit, which executes the countdown to complete the outbound shutdown and inbound startup operations of the corresponding payload.

[0022] Furthermore, the satellite position is obtained by extrapolating and converting six numbers.

[0023] Furthermore, in S3, γ ≥ 0°.

[0024] Furthermore, in S3, when the viewing angle γ=0°, the distance threshold calculation formula is:

[0025] A device for autonomous power consumption optimization of a transit satellite payload comprises a processor and a memory, wherein a computer program is stored in the memory, and when the computer program is loaded by the processor, any of the methods described above is executed.

[0026] A computer-readable storage medium stores a computer program, wherein the computer program executes any of the above methods when loaded by a processor.

[0027] A system for optimizing the autonomous power consumption of a transit satellite payload comprises the device for optimizing the autonomous power consumption of a transit satellite payload as described above.

[0028] The beneficial effects of the present invention include:

[0029] The method of the present invention realizes rapid judgment of the entry and exit status of the satellite payload by calculating the distance, can adapt to the influence of the change of orbital altitude after the satellite changes its orbit, and autonomously calculates the satellite exit delay and entry delay through the transit payload. In combination with the satellite's energy management unit, the transit workload can be autonomously shut down abroad and autonomously started before entry, thereby saving the energy consumed by the transit workload in standby work abroad, solving the problem of satellite energy shortage, and promoting satellite development and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in 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 only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0031] Figure 1 Optimize architecture for autonomous power consumption of transit satellite payloads;

[0032] Figure 2 A schematic diagram of the rapid decision on satellite entry and exit;

[0033] Figure 3 Flowchart for autonomous power consumption optimization of transit satellite payloads;

[0034] Figure 4 Satellite visibility for 48 consecutive hours after T0;

[0035] Figure 5 Satellite visibility at T0+700s startup;

[0036] Figure 6 Satellite visibility at T0+27450s. DETAILED DESCRIPTION

[0037] All features disclosed in all embodiments in this specification, or steps in all methods or processes implicitly disclosed, except for mutually exclusive features and / or steps, can be combined and / or expanded or replaced in any manner.

[0038] The specific implementation process of the present invention is as follows:

[0039] In view of the problems in the background, the present invention proposes a method for optimizing the autonomous power consumption of a transit satellite payload, which is divided into the following steps:

[0040] Step 1: The system working architecture includes the transit workload and the power management unit for realizing the power supply of the workload (see Figure 1 ).

[0041] Step 2: Get the current satellite position coordinates S, the ground station position coordinates T, and the effective visible elevation angle γ of the ground station (see Figure 2 ).

[0042] Step 3: Calculate the visible distance threshold, which is related to the satellite's location and the ground station's visible angle γ (γ ≥ 0°), and can adapt to the impact of satellite orbit changes. The calculation formula is as follows:

[0043]

[0044] Where θ is the calculated angle, and θ=(90+γ)°. When the visible angle γ=0°, the satellite position is Figure 1 In the S1 coordinate, the distance threshold calculation formula is simplified to:

[0045]

[0046] Step 4: Calculate the straight-line distance between the satellite position S and the ground station T, denoted as d;

[0047] Step 5: Determine the difference between the distance d and the threshold. If d≤D, the satellite is visible. If d>D, the satellite is not visible.

[0048] Step 6: Transit payload performs autonomous calculation process (see Figure 3 ), get the current system time T 0 The satellite position under 0 .

[0049] Specifically, the autonomous computing process of the environment payload includes the following sub-steps:

[0050] S1, get the current time T0;

[0051] S2, obtain the satellite position X at the current moment;

[0052] S3, calculate threshold D and calculate distance d;

[0053] S4, determine whether it is visible, if not, return to step S1, otherwise proceed to the next step;

[0054] S5, time extrapolation t;

[0055] S6, calculate the extrapolated satellite position X;

[0056] S7, calculating the threshold D and the distance d;

[0057] S8, determine whether it is visible, if yes, return to step S5, otherwise proceed to the next step;

[0058] S9, shutdown delay T1, jump to step S15;

[0059] S10, time extrapolation t;

[0060] S11, calculate the extrapolated satellite position X;

[0061] S12, calculating the threshold D and the distance d;

[0062] S13, determine whether it is visible, if yes, return to step S10, otherwise proceed to the next step;

[0063] S14, power-on delay T2;

[0064] S15, generating satellite data packets;

[0065] S16, sending to the satellite energy management unit to execute the power on / off operation.

[0066] Step 7: Calculate the distance threshold D according to formula (1), and simultaneously calculate the straight-line distance between the satellite and the ground station. The satellite autonomously determines whether the ground station is visible.

[0067] Step 8: If the ground station is not visible, go back to step 6; if the ground station is visible, it means the satellite is within the territory, and go to step 9;

[0068] Step 9: Extrapolate time t to obtain T 0 + Satellite position X at time t 1 , calculate the distance threshold D according to formula (1), and calculate the straight-line distance d between the satellite and the ground station 1 , the satellite autonomously determines whether the ground station is visible;

[0069] Step 10: If the ground station is visible, execute step 9 and continue to extrapolate time t to calculate T 0 Satellite position X at time +2t 2 , and determine whether the satellite is visible according to step 9. After executing n times, T 0 +n·t corresponding to the satellite position is recorded as X n If the ground is not visible, it means the satellite is out of the sky. Record the time T 1 =T 0 +(n+1)·t is the departure time of the satellite.

[0070] Step 11: In T 1 On this basis, continue to extrapolate time t to obtain T 0 Satellite position X at time +(n+1)·t n+1 , calculate the distance threshold, and determine whether the satellite is visible.

[0071] Step 12: If the ground station is not visible, indicating that the satellite is outside the country, then execute step 11, continue to extrapolate time t, and determine whether the satellite is visible based on step 11. After executing m times, T 0 +(n+m)·t corresponds to the satellite position X n+m If the ground station is visible, it means that the satellite has just entered the country, and the time T is recorded. 2 =T 0 +(n+m-1)·t is the entry time of the satellite.

[0072] Step 13: The calculated departure time T 1 and entry time T 2 The data packets are packaged according to the established data packet format and sent to the satellite's energy management unit, which executes the countdown to complete the outbound shutdown and inbound startup operations of the corresponding payload.

[0073] In other embodiments of the present invention, it is assumed that the full-state working power consumption of a certain payload is 32W in China, the standby power consumption is 16W outside China, the orbit extrapolation time interval is t=1s, and the satellite position is obtained by extrapolating and converting six numbers. The station address data is detailed in Table 1, T 0 The six numbers corresponding to the time are detailed in Table 2.

[0074] The satellite visibility at time T0 for 48 hours is analyzed, and the simulation results are as follows: Figure 3 The corresponding first 7 entry and exit times are shown in Table 3. The longest overseas duration was 47929s, about 13.3h.

[0075] Assume that the load is at T 0 Always on, according to Figure 2 The calculation process is determined to be overseas and the subsequent calculation process is not executed; it is assumed that the load is at T 0 +700s, the payload is automatically judged as being in the territory, and the subsequent calculation process is executed. The calculated entry and exit times are detailed in Table 4. The STK result is used as a reference value, and the error time of exit and entry calculated by this method is 2s, and the error time of entry is 6s. Assuming that the payload is at T 0 At +27450s, the payload was turned on and determined to be in the territory. The subsequent calculation process was executed. The calculated entry and exit times are shown in Table 5. The STK result was used as a reference value. The exit error time was 1s and the entry time error was 55s when compared with the calculation method.

[0076] According to the orbital parameters of the embodiment, the average orbit is 6684s, the domestic time is 930s, and the error is 6s to 55s. The overseas duty cycle is 58.26% to 86.00. In conjunction with the satellite's autonomous energy management unit, the transit payload can be autonomously turned on and off in and out of the country. The overseas standby power consumption of 16W will no longer be consumed. This effect is significant for small low-orbit satellites with tight energy.

[0077] Table 1 Site information table

[0078] parameter longitude latitude high Beijing Railway Station 116.42° 39.908° 49m

[0079] Table 2 Six orbital element information at different times

[0080] parameter Value (T0) Value (T0+700s) Value (T0+27450s) Semi-major axis 7378137 7374466.67400000 7372881.99900000 Eccentricity 0 0.00073900 0.00079200 Tilt Angle 44.998° 0.78510146 0.78499674 Ascending node right ascension 359.828° 6.28000881 6.25620252 Perigee angular distance 0 2.58490244 2.82300025 True Anomaly 359.813° 4.39255739 5.72673944

[0081] Table 3 Satellite entry and exit schedule after T0

[0082] Visible segment Entry Time Departure time Duration in China Overseas time 1 679 1623 945 5727 2 7349 8278 930 5738 3 14015 14954 940 5707 4 20660 21563 904 5847 5 27409 27952 544 47929 6 75880 76551 672 5782 7 82332 83258 927 5727

[0083] Table 4 Entry and exit time calculated at T0+700s

[0084] project Theory (STK) calculate error First departure time 923 925 2s First entry time 6649 6655 6s

[0085] Table 5 Entry and exit time calculated at time T0+27450s

[0086] project Theory (STK) calculate error First departure time 502 503 1s First entry time 48430 48485 55s

[0087] The units involved in the embodiments of the present invention may be implemented by software or hardware, and the units described may also be arranged in a processor. The names of these units do not, in some cases, limit the units themselves.

[0088] According to one aspect of an embodiment of the present invention, a computer program product or a computer program is provided, the computer program product or the computer program includes a computer instruction, and the computer instruction is stored in a computer-readable storage medium. A processor of a computer device reads the computer instruction from the computer-readable storage medium, and the processor executes the computer instruction, so that the computer device executes the method provided in the above various optional implementations.

[0089] As another aspect, an embodiment of the present invention further provides a computer-readable medium, which may be included in the electronic device described in the above embodiment; or may exist independently without being assembled into the electronic device. The above computer-readable medium carries one or more programs, and when the above one or more programs are executed by an electronic device, the electronic device implements the method described in the above embodiment.

Claims

1. A method for optimizing autonomous power consumption of a transit satellite payload, characterized in that: The following steps are involved: S1: Build a system working architecture including a transit workload and a power management unit for powering the workload; S2: Get the current satellite position coordinates S, the ground station position coordinates T and the effective visible elevation angle γ of the ground station; S3: Calculate the visible distance threshold, which is related to the satellite's position and the ground station's visible angle γ, and can adapt to the impact of satellite orbit changes. The calculation formula is as follows: Where θ is the calculation angle, and θ = (90 + γ)°, R is the radius of the earth, X s , Y s , Z s are the XYZ coordinates of the satellite in the Earth-fixed coordinate system; S4: Calculate the straight-line distance between the satellite position S and the ground station T, denoted as d; S5: Determine the difference between the distance d and the threshold. If d≤D, the satellite is considered visible. If d>D, the satellite is considered invisible. S6: The transit payload executes an autonomous calculation process to obtain the satellite position at the current system time T0, recorded as X0; S7: Calculate the distance threshold D according to formula (1), and simultaneously calculate the straight-line distance between the satellite and the ground station. The satellite autonomously determines whether the ground station is visible. S8: If the ground station is not visible, go back to step 6; if the ground station is visible, it means the satellite is within the territory, and execute step 9; S9: Extrapolate the time t to obtain the satellite position X1 at time T0+t, calculate the distance threshold D according to formula (1), and calculate the straight-line distance d1 between the satellite and the ground station. The satellite autonomously determines whether the ground station is visible. S10: If the ground station is visible, execute step 9, continue to extrapolate the time t, calculate the satellite position X2 at time T0+2t, and determine whether the satellite is visible according to step 9; after executing n times, the satellite position corresponding to T0+n·t is recorded as X n If the ground is not visible, it means that the satellite has left the country. The recorded time T1=T0+(n+1)·t is the satellite’s departure time. S11: Based on T1, continue to extrapolate time t to obtain the satellite position X at time T0+(n+1)·t n+1 , calculate the distance threshold and determine whether the satellite is visible; S12: If the ground station is not visible, indicating that the satellite is outside the country, then execute S11, continue to extrapolate time t, and determine whether the satellite is visible according to step 11; after executing m times, the satellite position corresponding to T0+(n+m)·t is recorded as X n+m If the ground station is visible, it means that the satellite has just entered the country. The recorded time T2 = T0 + (n + m-1) t is the entry time of the satellite. S13: The calculated exit time T1 and entry time T2 are packaged according to a predetermined data packet format and sent to the energy management unit of the satellite. The energy management unit performs a countdown to complete the exit shutdown and entry startup operations of the corresponding payload.

2. The method for optimizing autonomous power consumption of a transit satellite payload according to claim 1, characterized in that: The satellite position is obtained specifically by extrapolating and converting six numbers.

3. The method for optimizing autonomous power consumption of a transit satellite payload according to claim 1, characterized in that: In S3, γ ≥ 0°.

4. The method for optimizing autonomous power consumption of a transit satellite payload according to claim 3, characterized in that: In S3, when the viewing angle γ = 0°, the distance threshold calculation formula is:

5. An autonomous power consumption optimization device for a transit satellite payload, characterized in that: The method comprises a processor and a memory, wherein a computer program is stored in the memory, and when the computer program is loaded by the processor, the method according to any one of claims 1 to 4 is executed.

6. A computer-readable storage medium, characterized in that: A computer program is stored in a readable storage medium, and the computer program is loaded by a processor to execute the method according to any one of claims 1 to 4.

7. An autonomous power consumption optimization system for transit satellite payloads, characterized in that: It includes the autonomous power consumption optimization device for a transit satellite payload as described in claim 5.

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