Energy balance analysis method and device suitable for solar panel driving mechanism

Abstract

The invention provides an energy balance analysis method and device suitable for a solar panel driving mechanism, and the method comprises the steps: calculating the effective total energy of a solar cell array in an orbit period according to a telemetering parameter and a target rotation angle under the condition that the solar panel driving mechanism is locked; calculating load consumed energy of the solar cell array in one track period and illumination supplementary energy of the solar cell array in one track period according to the telemetering parameters and the set shadow time; and establishing an energy balance analysis condition according to the effective total energy, the load consumption energy and the illumination supplementary energy, so that the satellite is judged to realize energy balance when meeting the energy balance analysis condition. On the basis of the mode, the satellite can autonomously analyze whether the solar cell array can meet the requirement or not in an orbit period, ground operation and maintenance personnel can conveniently master the satellite energy condition in time, and the timeliness and accuracy of satellite operation and maintenance are improved.

Description

Technical Field

[0001] The present invention mainly relates to the technical field of satellite-borne equipment, and in particular to an energy balance analysis method and device suitable for a solar sail panel driving mechanism. Background Art

[0002] For satellites in orbit, the solar array drive mechanism (SADM) is connected to the rotation axis of the solar array. The rotation of the SADM drives the onboard solar panels, so that the solar array maintains the optimal angle with the sun to achieve energy supply. If the SADM is blocked, the satellite will not be able to maximize its energy. It is difficult for the ground to grasp the satellite's energy situation, which may cause the energy generated by the solar array to fail to meet demand. Summary of the invention

[0003] The purpose of the present invention is to provide an energy balance analysis method and device suitable for a solar sail driving mechanism, so as to solve the technical problem that when the existing SADM is blocked, it is difficult to analyze the energy balance of the satellite.

[0004] In a first aspect, an energy balance analysis method applicable to a solar panel driving mechanism is provided, comprising:

[0005] In the event of a stall in the solar sail driving mechanism, the total effective energy of the solar array within one orbital period is calculated based on telemetry parameters and a target rotation angle;

[0006] Calculating the load consumption energy of the solar array within one orbital cycle and the illumination supplement energy of the solar array within one orbital cycle according to the telemetry parameters and the set shadow time;

[0007] An energy balance analysis condition is established based on the effective total energy, the load consumption energy and the illumination supplement energy, so that when the satellite meets the energy balance analysis condition, it is determined that it has achieved energy balance.

[0008] In some embodiments, calculating the total effective energy of the solar array within one orbital period according to the telemetry parameters and the target rotation angle includes:

[0009] Detect the maximum current I when the solar panel driving mechanism is aligned with the target rotation angle 0 ;

[0010] The current actual current I is calculated according to the telemetry parameters: I = I0 × cosx, where x is the rotation angle, α is the stuck angle, and β is the satellite solar angle;

[0011] The total effective energy W of the solar array within one orbital cycle is calculated based on the maximum current I0 and the current actual current I: W = (I + I0) × V 母线 , where V 母线 is the bus voltage of the satellite.

[0012] In some embodiments, the load consumes energy W load Calculated by the following formula:

[0013] W load =I load ×V 母线 ×(Tt)÷a÷S3R÷b

[0014] Among them, I load is the load current of the satellite in one orbital period, V 母线 is the bus voltage of the satellite during the orbital period, T is an orbital period, t is the shadow time, a and b are the bus power supply line loss factor and the array power supply line loss factor respectively, and S3R is the efficiency of the sequential switch shunt regulator.

[0015] In some embodiments, the light supplement energy W d Calculated by the following formula:

[0016] W d =Q d ÷c÷BCR÷S3R÷b

[0017] Among them, Q d is the discharge energy of the battery during the shadow time, c is the battery full line loss factor, and BCR is the efficiency of the battery charging regulator.

[0018] In some embodiments, the discharge energy Q of the battery during the shadow time is d for:

[0019] Q d =I load1 ×V 母线 ×t÷a÷BDR÷c

[0020] Among them, I load1 is the load current of the satellite during the shadow time, and BDR is the efficiency of the battery discharge regulator.

[0021] In some embodiments, the energy balance analysis conditions are:

[0022] W≥(W d +W load )

[0023] Wherein, W is the effective total energy, W dThe energy consumed by the load, W load Supplementing energy for the illumination.

[0024] In some embodiments, it also includes:

[0025] When the satellite does not meet the energy balance analysis condition, an instruction is generated according to the result and sent to a ground station.

[0026] In a second aspect, an energy balance analysis device applicable to a solar panel driving mechanism is provided, comprising:

[0027] The first unit is used to calculate the total effective energy of the solar array within one orbital period according to the telemetry parameters and the target rotation angle when the solar sail driving mechanism is locked;

[0028] The second unit is used to calculate the load consumption energy of the solar cell array within the one orbital cycle and the illumination supplement energy of the solar cell array within the one orbital cycle according to the telemetry parameters and the set shadow time;

[0029] The third unit is used to establish energy balance analysis conditions according to the effective total energy, the load consumption energy and the illumination supplement energy, so that when the satellite meets the energy balance analysis conditions, it is determined that it has achieved energy balance.

[0030] In a third aspect, an electronic device is provided, comprising: one or more processors; and one or more memories coupled to the one or more processors and storing instructions thereon, wherein when the instructions are executed individually or collectively by the one or more processors, the electronic device executes a method according to any one of the first aspects.

[0031] In a fourth aspect, a non-transitory computer-readable storage medium storing machine-executable instructions is provided, wherein the machine-executable instructions, when executed by one or more processors of a machine, cause the machine to perform any one of the methods of the first aspect.

[0032] Compared with the prior art, the present invention has the following advantages:

[0033] The present application provides an energy balance analysis method and device suitable for a solar panel drive mechanism. When the solar panel drive mechanism is blocked, energy balance analysis conditions are established through telemetry parameters, so that the satellite can autonomously analyze whether the solar array can meet the demand within an orbital cycle, which is beneficial for ground operation and maintenance personnel to grasp the satellite energy status in a timely manner, thereby improving the timeliness and accuracy of satellite operation and maintenance.

[0034] It should be understood that the invention summary is not intended to identify the key or essential features of the embodiments of the present disclosure, nor is it intended to limit the scope of the present disclosure. Other features of the present disclosure will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The accompanying drawings are included to provide a further understanding of the present application. They are included and constitute a part of the present application. The accompanying drawings illustrate embodiments of the present application and together with the present specification serve to explain the principles of the present application. In the accompanying drawings:

[0036] Figure 1 A flow chart 100 of an energy balance analysis method applicable to a solar panel driving mechanism provided by the present application is shown;

[0037] Figure 2 An exemplary solar cell array topology diagram 200 is shown;

[0038] Figure 3 , Figure 4 Schematic diagrams 300 and 400 of the dual Y-wing sail panels and load power of the dual solar wing on-orbit satellite in one orbital period are shown;

[0039] Figure 5 An energy balance analysis device 500 suitable for a solar sail panel driving mechanism is shown;

[0040] Figure 6 An exemplary electronic device 600 is shown. DETAILED DESCRIPTION

[0041] The principle of the present disclosure will now be described with reference to some embodiments. It should be understood that the description of these embodiments is only for illustrative purposes, and helps those skilled in the art to understand and implement the present disclosure, without any limitation to the scope of the present disclosure. The disclosure described herein can be implemented in a manner different from that described below.

[0042] In the following description and claims, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs.

[0043] References in this disclosure to "one embodiment," "an embodiment," "an exemplary embodiment," etc. indicate that the described embodiment may include a particular feature, structure, or characteristic, but not every embodiment necessarily includes the particular feature, structure, or characteristic. Moreover, such phrases do not necessarily refer to the same embodiment. In addition, when a particular feature, structure, or characteristic is described in conjunction with an exemplary embodiment, whether or not explicitly described, those skilled in the art will recognize that such feature, structure, or characteristic affects incorporation into other embodiments.

[0044] It should be understood that although the terms "first" and "second" etc. may be used to describe various elements herein, these elements should not be limited by these terms. These terms are only used to distinguish one element from another element. For example, without departing from the scope of the exemplary embodiments, a first element may be referred to as a second element, and similarly, a second element may be referred to as a first element. The term "and / or" as used herein includes any and all combinations of one or more of the listed terms.

[0045] The terms used herein are only for describing specific embodiments, rather than for limiting exemplary embodiments. The singular forms "one", "an", and "the" used herein also include plural forms, unless the context clearly indicates otherwise. "A group of elements" or "element set" used herein is intended to include one or more elements. It should also be understood that the terms "include", "comprise", "have", "have", "include" and / or "include", when used herein, specify the presence of the features, elements and / or parts, etc., but do not exclude the presence or addition of one or more other features, elements, parts and / or combinations thereof.

[0046] The "solar panel driving mechanism" referred to herein may be a solar panel driving mechanism in a solar panel driving device (SADA for short). The solar panel driving device may be composed of a solar panel driving mechanism and a solar panel driving circuit (SADE for short). The solar panel driving mechanism may be driven by the solar panel driving circuit to drive the satellite-borne solar wing to rotate.

[0047] Figure 1 A flow chart 100 of an energy balance analysis method applicable to a solar panel driving mechanism provided by the present application is shown, comprising:

[0048] S101, when the solar panel driving mechanism is blocked, the total effective energy of the solar cell array within one orbital period is calculated according to the telemetry parameters and the target rotation angle.

[0049] In some embodiments, calculating the total effective energy of the solar array within one orbital period according to the telemetry parameters and the target rotation angle includes:

[0050] Detect the maximum current I when the solar panel drive mechanism is aligned with the target rotation angle 0 .

[0051] The actual current I is calculated based on the telemetry parameters: I = I0 × cosx, where x is the rotation angle, α is the stuck angle, and β is the satellite solar angle.

[0052] The total effective energy W of the solar array within one orbital cycle is calculated based on the maximum current I0 and the current actual current I: W = (I + I0) × V母线 , where V 母线 is the satellite bus voltage.

[0053] According to the design of the on-orbit satellite, the target rotation angle of the positive Y sailboard of the solar array varies between |β| and (180°-|β|), and the target rotation angle of the negative Y sailboard varies between (180°+|β|) and (360°-|β|). In the case of SADM stalling, the rotation angle x of the positive Y sailboard varies between [α-|β|, 0], [0, 180°-|β|-α], and the rotation angle x of the negative Y sailboard varies between [α-(180°+|β|, 0], [0, 360°-|β|-α].

[0054] S102, calculating the load consumption energy of the solar array within one orbital cycle and the illumination supplement energy of the solar array within one orbital cycle according to the telemetry parameters and the set shadow time.

[0055] Load energy consumption refers to the energy consumed by the load in the solar array during one orbital cycle. Figure 2 FIG. 2 shows an exemplary solar cell array topology diagram 200. Figure 2 As shown, it includes a switch SA, a power source BAT, a load LOAD, a sequential switch shunt regulator S3R, a battery charging regulator BCR and a battery discharging regulator BDR. Among them, the sequential switch shunt regulator S3R, the battery charging regulator BCR and the battery discharging regulator BDR are connected to the bus BUS. The corresponding load consumption energy is calculated according to the relationship between the load LOAD and S3R, BCR and BDR in the above topological structure.

[0056] In some embodiments, the load consumes energy W load Calculated by the following formula:

[0057] W load =I load ×V 母线 ×(Tt)÷a÷S3R÷b

[0058] Among them, I load is the load current of the satellite in one orbital period, V 母线 is the bus voltage of the satellite in one orbital period, T is one orbital period, t is the shadow time, a and b are the bus power supply line loss factor and array power supply line loss factor respectively, and S3R is the efficiency of the sequential switch shunt regulator.

[0059] In some embodiments, the light supplement energy W d Calculated by the following formula:

[0060] W d =Qd ÷c÷BCR÷S3R÷b

[0061] Among them, Q d is the discharge energy of the battery during the shadow time, c is the battery full line loss factor, and BCR is the efficiency of the battery charging regulator.

[0062] In some embodiments, the discharge energy Q of the battery during the shadow time d for:

[0063] Q d =I load1 ×V 母线 ×t÷a÷BDR÷c

[0064] Among them, I load1 is the load current of the satellite during the shadow time, and BDR is the efficiency of the battery discharge regulator.

[0065] S103, establishing energy balance analysis conditions according to the effective total energy, load consumption energy and illumination supplement energy, so that when the satellite meets the energy balance analysis conditions, it is determined that it has achieved energy balance.

[0066] In some embodiments, the energy balance analysis conditions are:

[0067] W≥(W d +W load )

[0068] Where W is the total effective energy, W d Energy consumed by the load, W load Recharge the energy for light.

[0069] In some embodiments, it also includes: when the satellite does not meet the energy balance analysis conditions, an instruction is generated based on this result and the instruction is sent to the ground station, so that ground operation and maintenance personnel can promptly know the satellite energy status and take measures, such as shutting down part of the payload on the satellite to maintain energy balance.

[0070] Furthermore, the above method was used to conduct an on-orbit test on a dual-solar-wing on-orbit satellite. The test data are as follows:

[0071] Orbital period: 13 hours;

[0072] Maximum shadow time: 60min;

[0073] Average on-rail load current: 35A;

[0074] Normal wing sail current: 31A;

[0075] SADM stuck angle: 270°;

[0076] Annual decline in windsurfing power: 1%;

[0077] Average current of the windsurfing board at the end of its life (summer solstice): 29A;

[0078] Maximum BCR input current at the end of life (summer earth shadow): 16A.

[0079] Figure 3 , Figure 4 Schematic diagrams 300 and 400 of the dual Y-wing sail panels and load power of the dual solar wing on-orbit satellite in one orbital period are shown. Figure 3 , for the case where the satellite is in the sunshine season (summer solstice), it can be calculated that the power of a single-circle double Y-wing sailboard is 1498W-2446W, which meets the load requirement of 1477W, and no discharge will occur at the end of the satellite life. Figure 4 , when the satellite is in the earth's shadow period, it can be calculated that the total energy of the battery discharge in a single cycle is 1759WH, and the energy that can be used for charging in a single cycle is 4691WH, and the energy balance of the earth's shadow season at the end of the life span. Substituting the steps in the method, it can be calculated that the battery pack discharge energy of the dual-solar-wing in-orbit satellite during the longest shadow time is 3232Wh, and the discharge depth does not exceed 70%, which meets the design index requirements. The total energy generated by the battery array in one orbital cycle is 21907Wh, which is greater than the load consumption energy of 20468Wh. At the same time, the energy that can be used for charging and supplementing is 3914Wh, which is also greater than the battery pack discharge energy of 3232Wh. Therefore, the energy balance analysis conditions are met, and the dual-solar-wing in-orbit satellite can achieve energy balance.

[0080] Further, if Figure 5 , shows an energy balance analysis device 500 suitable for a solar sail panel driving mechanism, comprising a first unit 501, a second unit 502 and a third unit 503, wherein:

[0081] The first unit 501 is used to calculate the total effective energy of the solar array within one orbital period according to the telemetry parameters and the target rotation angle when the solar sail driving mechanism is locked;

[0082] The second unit 502 is used to calculate the load consumption energy of the solar array within one orbital cycle and the illumination supplement energy of the solar array within one orbital cycle according to the telemetry parameters and the set shadow time;

[0083] The third unit 503 is used to establish energy balance analysis conditions according to the effective total energy, load consumption energy and illumination supplement energy, so that when the satellite meets the energy balance analysis conditions, it is determined that it has achieved energy balance.

[0084] Further, if Figure 6An exemplary embodiment of the present application also provides an electronic device 600, comprising one or more memories 601 and one or more processors 602, wherein the one or more memories 601 are coupled to the one or more processors 602 and store instructions thereon, and the instructions can be executed individually or collectively by the one or more processors 602, so that the electronic device 600 performs any method as in the first aspect.

[0085] It should be understood that the processor mentioned in the embodiments of the present application may be a CPU, or other general-purpose processors, DSPs, ASICs, FPGAs or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor may be a microprocessor or the processor may be any conventional processor, etc.

[0086] It should also be understood that the memory mentioned in the embodiments of the present application may be a volatile memory or a non-volatile memory, or may include both volatile and non-volatile memories. Among them, the non-volatile memory may be a read-only memory (ROM), a programmable read-only memory, an erasable programmable read-only memory, an electrically erasable programmable read-only memory, or a flash memory. The volatile memory may be a random access memory (RAM), which is used as an external cache. By way of example but not limitation, many forms of RAM are available, such as static random access memory, dynamic random access memory, synchronous dynamic random access memory, double data rate synchronous dynamic random access memory, enhanced synchronous dynamic random access memory, synchronously connected dynamic random access memory, and direct memory bus random access memory.

[0087] The present application also provides a non-transient computer-readable storage medium storing machine-executable instructions, and the computer-executable instructions can be executed by one or more processors of a machine. The machine may include the electronic device mentioned above, etc. When the computer-executable instructions are executed by one or more processors, the machine performs any of the methods mentioned above.

[0088] A computer-readable storage medium may include a propagated data signal containing computer program code, such as in baseband or as part of a carrier wave. The propagated signal may have a variety of forms, including electromagnetic, optical, etc., or a suitable combination. The computer-readable storage medium can be connected to an instruction execution system, device or equipment to communicate, propagate or transmit the program for use. The program code located on the computer-readable storage medium can be transmitted through any suitable medium, including radio, cable, fiber optic cable, radio frequency signal, or similar medium, or any combination of the above mediums.

[0089] The basic concepts have been described above. Obviously, for those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0090] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0091] Some aspects of the present application may be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software may be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor may be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. In addition, various aspects of the present application may be expressed as computer products located in one or more computer-readable media, which include computer-readable program codes. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, tapes ...), optical disks (e.g., compact disks CDs, digital versatile disks DVDs ...), smart cards, and flash memory devices (e.g., cards, sticks, key drives ...).

[0092] A computer-readable medium may include a propagated data signal containing computer program code, such as in baseband or as part of a carrier wave. The propagated signal may have a variety of manifestations, including electromagnetic, optical, etc., or a suitable combination. A computer-readable medium may be any computer-readable medium other than a computer-readable storage medium, which may be connected to an instruction execution system, device or apparatus to communicate, propagate or transmit a program for use. The program code on the computer-readable medium may be propagated via any suitable medium, including radio, cable, fiber optic cable, radio frequency signal, or similar medium, or any combination of the above mediums.

[0093] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus help understand one or more embodiments of the invention, in the above description of the embodiments of this application, multiple features are sometimes combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than the features mentioned in the claims. In fact, the features of the embodiments are less than all the features of the single embodiment disclosed above.

[0094] In some embodiments, numbers describing the number of components and attributes are used. It should be understood that such numbers used in the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise specified, "about", "approximately" or "substantially" indicate that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which may change according to the required features of individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and adopt the general method of retaining digits. Although the numerical domains and parameters used to confirm the breadth of their range in some embodiments of the present application are approximate values, in specific embodiments, the setting of such numerical values ​​is as accurate as possible within the feasible range.

[0095] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. An energy balance analysis method applicable to a solar panel drive mechanism, characterized in that: include: In the event of a stall in the solar sail driving mechanism, the total effective energy of the solar array within one orbital period is calculated based on telemetry parameters and a target rotation angle; Calculating the load consumption energy of the solar array within one orbital cycle and the illumination supplement energy of the solar array within one orbital cycle according to the telemetry parameters and the set shadow time; An energy balance analysis condition is established based on the effective total energy, the load consumption energy and the illumination supplement energy, so that when the satellite meets the energy balance analysis condition, it is determined that it has achieved energy balance.

2. The method according to claim 1, characterized in that The method of calculating the total effective energy of the solar array within one orbital period according to the telemetry parameters and the target rotation angle includes: Detecting the maximum current I0 when the solar panel driving mechanism is aligned with the target rotation angle; The current actual current I is calculated according to the telemetry parameters: I = I0 × cosx, where x is the rotation angle, α is the stuck angle, and β is the satellite solar angle; The total effective energy W of the solar array within one orbital cycle is calculated based on the maximum current I0 and the current actual current I: W = (I + I0) × V 母线 , where V 母线 is the bus voltage of the satellite.

3. The method according to claim 1 or 2, characterized in that The load consumes energy W load Calculated by the following formula: W load =I load ×V 母线 ×(T-t)÷a÷S3R÷b Among them, I load is the load current of the satellite in one orbital period, V 母线 is the bus voltage of the satellite during the orbital period, T is an orbital period, t is the shadow time, a and b are the bus power supply line loss factor and the array power supply line loss factor respectively, and S3R is the efficiency of the sequential switch shunt regulator.

4. The method according to claim 3, characterized in that The light supplement energy W d Calculated by the following formula: W d =Q d ÷c÷BCR÷S3R÷b Among them, Q d is the discharge energy of the battery during the shadow time, c is the battery full line loss factor, and BCR is the efficiency of the battery charging regulator.

5. The method according to claim 4, characterized in that The discharge energy Q of the battery during the shadow time d for: Q d =I load1 ×V 母线 ×t÷a÷BDR÷c Among them, I load1 is the load current of the satellite during the shadow time, and BDR is the efficiency of the battery discharge regulator.

6. The method according to claim 1 or 2, characterized in that: The energy balance analysis conditions are: In≥(In d +W load ) Wherein, W is the effective total energy, W d The energy consumed by the load, W load Supplementing energy for the illumination.

7. The method according to claim 1, characterized in that Also includes: When the satellite does not meet the energy balance analysis condition, an instruction is generated according to the result and sent to a ground station.

8. An energy balance analysis device suitable for a solar sail panel drive mechanism, characterized in that: include: The first unit is used to calculate the total effective energy of the solar array within one orbital period according to the telemetry parameters and the target rotation angle when the solar sail driving mechanism is blocked; The second unit is used to calculate the load consumption energy of the solar cell array within the one orbital cycle and the illumination supplement energy of the solar cell array within the one orbital cycle according to the telemetry parameters and the set shadow time; The third unit is used to establish energy balance analysis conditions according to the effective total energy, the load consumption energy and the illumination supplement energy, so that when the satellite meets the energy balance analysis conditions, it is determined that it has achieved energy balance.

9. An electronic device, comprising: one or more processors; as well as, One or more memories coupled to the one or more processors and storing instructions thereon, which, when the instructions are executed individually or collectively by the one or more processors, cause the electronic device to perform a method according to any one of claims 1-7.

10. A non-transitory computer-readable storage medium storing machine-executable instructions, which, when executed by one or more processors of a machine, cause the machine to perform the method of any one of claims 1-7.

Images