Autonomous power consumption optimization method, device, medium and system for transit satellite payload

Abstract

The present invention discloses a method, device, medium, and system for autonomous power consumption optimization of a transit satellite payload. These methods, which pertain to the field of satellite technology, include an autonomous entry / exit decision process, which rapidly determines the entry / exit status of a satellite payload by calculating distance. This process adapts to the impact of changes in orbital altitude after a satellite orbit change. The transit payload autonomously calculates the satellite's exit and entry delays, and, in conjunction with the satellite's energy management unit, enables autonomous shutdown of the transit payload while it is operating outside the country and autonomous startup before entering the country, thus saving energy consumed by the transit payload during standby operation outside the country. The present invention can address the issue of satellite energy shortages and 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 autonomous power consumption optimization of a transit satellite payload. Background Art

[0002] During a satellite's in-orbit mission, some payloads only operate within the satellite's territory. These payloads switch operating modes based on the satellite's entry / exit status: fully operational within the territory and in standby mode outside the territory. For example, data transmission payloads used for communication between the satellite and ground stations must operate their transmitters while the satellite is in transit and shut down after exiting the territory. This prevents signals from being maliciously received outside the territory and conserves satellite power.

[0003] The working mode of the transit payload in standby mode abroad can certainly save some power consumption, but some modules are still in working state, and this part of the energy will be wasted abroad. In addition, with the vigorous development and application of small low-orbit satellites at this stage, satellite energy is even tighter and the control of power consumption is more stringent. How to utilize the energy consumed by the payload in standby mode 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 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 that includes 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. This threshold 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 calculated angle, and θ = (90 + γ)°, R is the radius of the earth, and 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 payload executes the autonomous calculation process to obtain the satellite position at the current system time T0, which is recorded as X0;

[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 go to step 9;

[0017] 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 simultaneously calculate the straight-line distance d1 between the satellite and the ground station. The satellite autonomously determines whether the ground station is visible.

[0018] 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 the satellite has left the country. The recorded time T1=T0+(n+1)·t is the satellite’s departure time.

[0019] 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;

[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, 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 Earth. The recorded time T2 = T0 + (n + m-1) t is the entry time of the satellite.

[0021] S13: The calculated exit time T1 and entry time T2 are packaged according to the established data packet format and sent to the satellite's energy management unit. The energy management unit performs a countdown to complete the exit shutdown and entry startup operations of the corresponding payload.

[0022] Furthermore, the satellite positions are 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 above methods 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 transit satellite payload autonomous power consumption optimization system comprises the transit satellite payload autonomous power consumption optimization device 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 the 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 entering the country, thereby saving the energy consumed by the transit workload in standby work abroad, solving the problem of tight satellite energy, and promoting the development and application of satellites. 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 following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 any creative work.

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

[0032] Figure 2 This is a schematic diagram of the rapid decision-making process for satellite entry and exit;

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

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

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

[0036] Figure 6 Satellite visibility at T0+27450s startup time. 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 above problems, 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 transit workload and power management unit for realizing load power supply (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. This threshold is related to the satellite's position 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 considered visible. If d>D, the satellite is considered invisible.

[0048] Step 6: Transit payload performs autonomous calculation process (see Figure 3 ), obtain the satellite position at the current system time T0, recorded as X0.

[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 the threshold D and calculate the 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 perform 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 the satellite position X1 at time T0+t, calculate the distance threshold D according to formula (1), and simultaneously calculate the straight-line distance d1 between the satellite and the ground station. The satellite autonomously determines whether the ground station is visible.

[0069] Step 10: If the ground station is visible, execute step 9, continue to extrapolate 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 border. The recorded time T1=T0+(n+1)·t is the satellite’s departure time.

[0070] Step 11: 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.

[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 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.

[0072] Step 13: Package the calculated exit time T1 and entry time T2 according to the established data packet format and send them to the satellite's energy management unit. The energy management unit will execute the countdown to complete the exit shutdown and entry startup operations of the corresponding payload.

[0073] In another embodiment of the present invention, assume that a payload's full-state operating power consumption within the country is 32W, and its standby power consumption outside the country is 16W. The orbit extrapolation interval is set to t = 1s, and satellite positions are acquired through extrapolation and conversion of six numbers. The station address data is detailed in Table 1, and the six numbers corresponding to time T0 are detailed in Table 2.

[0074] The satellite visibility at time T0 for 48 consecutive hours is analyzed, and the simulation results are as follows: Figure 3 The corresponding first seven entry and exit times are shown in Table 3. The longest overseas trip lasted 47,929 seconds, or about 13.3 hours.

[0075] Assuming that the load is turned on at time T0, according to Figure 2 The calculation process is determined to be outside the country and the subsequent calculation process is not executed. Assuming that the payload is turned on at T0+700s, the payload is determined to be within the country and the subsequent calculation process is executed. The calculated entry and exit times are shown in Table 4. Taking the STK result as the reference value, the exit error time is 2s and the entry time error is 6s when compared with the method. Assuming that the payload is turned on at T0+27450s, the payload is determined to be within the country and the subsequent calculation process is executed. The calculated entry and exit times are shown in Table 5. Taking the STK result as the reference value, the exit error time is 1s and the entry time error is 55s when compared with the 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 16W standby power consumption overseas will no longer be consumed. This effect is significant for small low-orbit satellites with tight energy requirements.

[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 (at time T0) Value (T0+700s) Value (T0+27450s) semimajor 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 Time abroad 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 times calculated at time 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 in software or hardware, and the units described may also be provided in a processor. In some cases, the names of these units do not limit the units themselves.

[0088] According to one aspect of an embodiment of the present invention, a computer program product or computer program is provided, comprising computer instructions stored in a computer-readable storage medium. A processor of a computer device reads the computer instructions from the computer-readable storage medium and executes the computer instructions, causing the computer device to perform the methods provided in the various optional implementations described above.

[0089] As another aspect, embodiments of the present invention further provide a computer-readable medium, which may be included in the electronic device described in the above embodiments, or may exist independently and not incorporated into the electronic device. The computer-readable medium carries one or more programs, and when executed by the electronic device, the electronic device implements the methods described in the above embodiments.

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 that includes 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. This threshold 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 calculated angle, and θ = (90 + γ)°, R is the radius of the earth, and 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, recorded 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 the autonomous calculation process to obtain the satellite position at the current system time T0, which is 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 go to 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 simultaneously 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 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 Earth. 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 the established data packet format and sent to the satellite's energy management unit. 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 positions are 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, wherein: 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. A device for optimizing the autonomous power consumption of 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. A transit satellite payload autonomous power consumption optimization system, characterized in that: It includes the autonomous power consumption optimization device for transit satellite payload as described in claim 5.

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