Satellite-rocket separation power supply control circuit and method and satellite

Abstract

The invention discloses a satellite-rocket separation power supply control circuit, which is used for a satellite and comprises a multi-path solar array, a weak light shunting module, a power-up control module, a storage battery pack and a load, the multi-path solar array is connected with the load through the weak light shunting module, and the storage battery pack is connected with the load through the power-up control module; the weak light shunting module is used for cutting off the multi-path solar array to power up the load before satellite-rocket separation; the power-up control module is used for cutting off the storage battery pack to power up the load before the satellite and the rocket are separated; and the power-up control module is also used for controlling the storage battery pack to power up the load after the satellite and the rocket are separated. The satellite can be automatically powered up through the power-up control module after the satellite and the rocket are separated, and the power-off state of the satellite can be maintained through the weak light shunting module before the satellite and the rocket are separated.

Description

Technical Field

[0001] The present invention belongs to the field of on-board electronic technology and relates to a satellite-rocket separation power supply control circuit, method and satellite. Background Art

[0002] In the field of space engineering, solar energy is currently the only energy source for most spacecraft. The power controller obtains energy from solar arrays and batteries, and generates a stable bus voltage through control to meet the power needs of various devices in the spacecraft.

[0003] In the prior art, in order to prevent the failure of the battery's autonomous powering function when the satellite and rocket separate and enter orbit, and at the same time increase the reliability of orbital powering, the solar panels of some small satellites are designed with at least one side of the battery facing outward after being folded. In this state, even if the autonomous powering function fails after the separation of the satellite and rocket, resulting in the satellite being unable to be initially powered by the battery, there is a certain probability that the satellite will be powered by the voltage stabilization module after the outer panel is illuminated, completing the subsequent orbital entry process, thereby normally unfolding the panel to obtain energy.

[0004] However, if the design of folding the sails and facing the cells outward is adopted, in the active phase of satellite launch, the carrier rocket will usually continue to carry the satellite for a period of time after completing the fairing jettisoning action to reach the designated orbital position before separating the satellite from the rocket. During this period, because there is no fairing to block it, the satellite may be exposed to sunlight, and the light intensity and angle conditions are unstable, which is generally referred to as "weak light conditions" in the industry. At this time, the output of the voltage stabilization module is unstable, which can easily cause an uncontrollable power-on state. The equipment on the satellite may experience unstable power-on conditions, which in turn causes abnormal operating conditions such as undervoltage and repeated power on and off, greatly increasing the probability of equipment damage.

[0005] Therefore, it is necessary to provide an improved technical solution to overcome the above technical problems existing in the prior art. Summary of the invention

[0006] The purpose of the present invention is to provide a satellite-rocket separation power supply control circuit, which is used for a satellite. It can not only power on the satellite autonomously after the satellite-rocket separation through the power-on control module, but also maintain the satellite in a power-off state before the satellite-rocket separation through the weak light shunt module.

[0007] To achieve the above objectives: In a first aspect, the present invention provides a satellite-rocket separation power supply control circuit for a satellite, comprising a multi-channel solar array, a weak light shunt module, a power-on control module, a battery pack, and a load; The multi-channel solar array is connected to the load via the weak light shunting module, and the battery pack is connected to the load via the power-on control module; The weak light shunting module is used to cut off the multi-channel solar array to power the load before the satellite-rocket separation; The power-on control module is used to cut off the battery pack to power the load before the satellite-rocket separation; The power-on control module is also used to control the battery pack to power the load after the satellite-rocket separation.

[0008] In one implementation, the weak light shunt module includes a weak light shunt fuse and a weak light shunt NMOS tube that are connected to each other.

[0009] In one embodiment, the circuit further comprises a voltage stabilization shunt module; The voltage stabilization shunt module includes a voltage stabilization shunt fuse, a voltage stabilization shunt NMOS tube, a voltage stabilization control circuit and a bus capacitor array. The voltage stabilization shunt NMOS tube is connected to the voltage stabilization control circuit through the voltage stabilization shunt fuse and is connected in parallel with the bus capacitor array to stabilize the voltage output by the multi-channel solar array.

[0010] In one embodiment, the power-on control module includes a charge and discharge control module; The charge and discharge control module includes a plurality of PMOS tubes and parasitic diodes respectively connected to the plurality of PMOS tubes, and is used to control the charging and discharging of the battery pack.

[0011] In one embodiment, the power-on control module further includes a discharge permission prohibition module; The discharge prohibition module includes a resistor voltage divider network, a discharge prohibition switch and a first star table. One end of the resistor voltage divider network is connected to the first star table through the discharge prohibition switch, and the other end of the resistor voltage divider network is respectively connected to the charge and discharge control module and the positive electrode of the battery pack.

[0012] In one embodiment, the power-on control module further includes a shunt permission prohibition module; The shunt prohibition module includes a shunt prohibition switch, a second star table, a first travel switch and a second travel switch. The shunt prohibition switch is connected to the first travel switch through the second star table, and the first travel switch is respectively connected to the first star table, the second travel switch and the negative pole of the battery pack.

[0013] In a second aspect, the present invention provides a control method for the satellite-rocket separation power supply control circuit according to any one of the first aspects, comprising: Before the separation of the rocket and the satellite, the weak light shunt module is controlled to cut off the multi-channel solar array to power the load, and the battery pack is cut off through the power-on control module to power the load; After the satellite and rocket are separated, the power-on control module controls the battery pack to power the load.

[0014] In one embodiment, after the satellite and rocket are separated, the method further comprises: The shunt permission prohibition module in the power-on control module is controlled to be in a disconnected state through the digital control module, thereby ensuring that the weak light shunt module is in a completely cut-off state.

[0015] In one embodiment, after controlling the battery pack to power the load through the power-on control module, the method further includes: The weak light shunting module is controlled to restore the multi-channel solar array to power the load.

[0016] In a third aspect, the present invention provides a satellite, characterized in that it includes a satellite-rocket separation power supply control circuit as described in any one of the first aspects.

[0017] The present invention provides a satellite-rocket separation power supply control circuit, which is used for a satellite and includes a multi-channel solar array, a weak light shunt module, a power-on control module, a battery pack, and a load; the multi-channel solar array is connected to the load through the weak light shunt module, and the battery pack is connected to the load through the power-on control module; the weak light shunt module is used to cut off the multi-channel solar array to power the load before the satellite-rocket separation; the power-on control module is used to cut off the battery pack to power the load before the satellite-rocket separation; the power-on control module is also used to control the battery pack to power the load after the satellite-rocket separation. The present invention can not only autonomously power on the satellite after the satellite-rocket separation through the power-on control module, but also maintain the satellite in a power-off state before the satellite-rocket separation through the weak light shunt module. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 A circuit structure diagram before satellite-rocket separation provided by an embodiment of the present invention; Figure 2 A circuit structure diagram after satellite-rocket separation provided by an embodiment of the present invention; Figure 3 A schematic flow chart of a control method provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0020] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are merely examples of systems and methods consistent with some aspects of the present invention as detailed in the appended claims.

[0021] It should be noted that, in this article, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "includes a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element. In addition, components, features, and elements with the same name in different embodiments of the present invention may have the same meaning or different meanings, and their specific meanings need to be determined by their explanation in the specific embodiment or further combined with the context of the specific embodiment.

[0022] It should be understood that, although the terms first, second, third, etc. may be used to describe various information in this article, these information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of this article, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein can be interpreted as "at the time of..." or "when..." or "in response to determination". Furthermore, as used in this article, the singular forms "one", "one" and "the" are intended to also include plural forms, unless there is an opposite indication in the context. It should be further understood that the terms "comprising", "including" indicate that there are described features, steps, operations, elements, components, projects, kinds, and / or groups, but do not exclude the existence, occurrence or addition of one or more other features, steps, operations, elements, components, projects, kinds, and / or groups. The terms "or" and "and / or" used herein are interpreted as inclusive, or mean any one or any combination. Thus, “A, B or C” or “A, B and / or C” means “any of the following: A; B; C; A and B; A and C; B and C; A, B and C”. An exception to this definition will occur only when a combination of elements, functions, steps or operations are inherently mutually exclusive in some manner.

[0023] It should be understood that, although the various steps in the flowchart in the embodiment of the present invention are displayed in sequence according to the indication of the arrows, these steps are not necessarily executed in sequence in the order indicated by the arrows. Unless there is a clear description in this article, the execution of these steps is not strictly limited in order, and they can be executed in other orders. Moreover, at least a portion of the steps in the figure may include a plurality of sub-steps or a plurality of stages, and these sub-steps or stages are not necessarily executed at the same time, but can be executed at different times, and their execution order is not necessarily carried out in sequence, but can be executed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.

[0024] It should be noted that, in this article, step codes such as S101, S102, etc. are used for the purpose of expressing the corresponding content more clearly and concisely, and do not constitute a substantial limitation on the sequence. When implementing the step codes, those skilled in the art may execute S102 first and then S101, etc., but these should all be within the scope of protection of the present invention.

[0025] It should be understood that the specific embodiments described herein are only used to explain the present invention, and are not used to limit the present invention.

[0026] In the subsequent description, the suffixes such as "module", "component" or "unit" used to represent elements are only used to facilitate the description of the present invention, and have no specific meanings. Therefore, "module", "component" or "unit" can be used in a mixed manner.

[0027] like Figure 1 As shown, the circuit structure diagram before the satellite-rocket separation provided by the embodiment of the present invention includes a multi-channel solar array 110, a weak light shunt module 120, a power-on control module 130, a battery pack 140 and a load 150; the multi-channel solar array 110 is connected to the load 150 through the weak light shunt module 120, and the battery pack 140 is connected to the load 150 through the power-on control module 130; the weak light shunt module 120 is used to cut off the multi-channel solar array 110 to power the load 150 before the satellite-rocket separation; the power-on control module 130 is used to cut off the battery pack 140 to power the load 150 before the satellite-rocket separation; the power-on control module 130 is also used to control the battery pack 140 to power the load 150 after the satellite-rocket separation.

[0028] It can be understood that the multi-channel solar array 110 is distributed on the satellite solar panels. When the panels are folded, the direction of the outermost patch surface is from the satellite's center of mass to the outside of the satellite.

[0029] In one implementation, the weak light shunt module includes a weak light shunt fuse and a weak light shunt NMOS tube that are connected to each other.

[0030] It can be understood that the weak light shunt module 120 is composed of a weak light shunt fuse and a weak light shunt NMOS tube, wherein the weak light shunt fuse is used for overcurrent protection of the circuit, and the weak light shunt fuse blows when the circuit is overcurrent; the weak light shunt NMOS tube is controlled by the shunt permission module 133 in the power-on control module 130, and when the weak light shunt NMOS tube in the weak light shunt module 120 is in the on state, the voltage stabilization shunt module 160 is shielded, and the current of the multi-channel solar array 110 flows back to the ground through the weak light shunt module 120 along the route with the lowest impedance.

[0031] In one embodiment, Figure 1 The circuit shown also includes a voltage stabilizing shunt module 160, which includes a voltage stabilizing shunt fuse, a voltage stabilizing shunt NMOS tube, a voltage stabilizing control circuit and a bus capacitor array. The voltage stabilizing shunt NMOS tube is connected to the voltage stabilizing control circuit through the voltage stabilizing shunt fuse and is connected in parallel with the bus capacitor array to stabilize the voltage output by the multi-channel solar array.

[0032] It can be understood that the voltage stabilization shunt module 160 is composed of a voltage stabilization shunt fuse, a voltage stabilization shunt NMOS tube, a voltage stabilization control circuit and a bus capacitor array. The voltage stabilization control circuit is used to generate a frequency-modulated or amplitude-modulated pulse wave to control the conduction or cutoff of the voltage stabilization shunt NMOS tube, and to modulate the solar array power. The voltage stabilization control circuit also works together with the bus capacitor array to output a stable voltage.

[0033] In one embodiment, the power-on control module 130 includes a charge-discharge control module 131 ; the charge-discharge control module 131 includes a plurality of PMOS transistors and parasitic diodes respectively connected to the plurality of PMOS transistors, for controlling the charging and discharging of the battery pack 140 .

[0034] It can be understood that the charge and discharge control module 131 is composed of multiple PMOS tubes in parallel, the charging function is realized by the parasitic diode of each PMOS tube, the discharging function is realized by the PMOS tube, and the conduction and cutoff of the PMOS tube are controlled by the resistor voltage divider network in the discharge prohibition module 132.

[0035] In one embodiment, the power-on control module 130 also includes a discharge inhibition module 132; the discharge inhibition module 132 includes a resistor voltage divider network, a discharge inhibition switch and a first star table, one end of the resistor voltage divider network is connected to the first star table through the discharge inhibition switch, and the other end of the resistor voltage divider network is respectively connected to the charge and discharge control module and the positive electrode of the battery pack 140.

[0036] It can be understood that the discharge prohibition module 132 is composed of a resistor voltage divider network, a discharge prohibition switch and a first star table, which is used to realize the conduction of the discharge path when any one of the first travel switch and the second travel switch in the shunt prohibition module 133 performs a switching action.

[0037] In one embodiment, the power-on control module 130 also includes a shunt prohibition module 133; the shunt prohibition module 133 includes a shunt prohibition switch, a second star table, a first travel switch and a second travel switch, the shunt prohibition switch is connected to the first travel switch through the second star table, and the first travel switch is respectively connected to the first star table, the second travel switch and the negative pole of the battery pack 140.

[0038] It can be understood that the shunt prohibition module 133 is composed of a shunt prohibition switch, a second star meter, a first travel switch and a second travel switch, and is used to shut off the discharge path when any one of the first travel switch and the second travel switch performs a switching action.

[0039] Continue reading Figure 1 Before the satellite-rocket separation, all switches in the shunt prohibition module 133 are turned on, and all weak light shunt NMOS tubes in the weak light shunt module 120 are turned on. At this time, the battery pack 140 cannot power the load 150, and the entire satellite is in a power-off state. The satellite maintains this state during the launch phase of the carrier rocket.

[0040] Furthermore, the satellite jettisons the fairing at the end of the launch phase of the carrier rocket, but the satellite and rocket have not yet separated, and the satellite maintains the aforementioned state. At this time, if sunlight shines on the sailboard, the weak light shunt NMOS tube in the weak light shunt 120 is turned on, and the current generated by the multi-channel solar array 110 flows back to the ground through the weak light shunt module 120, and the back end is still in a power-off state, thereby avoiding the possible negative effects of unstable power supply on the load 150 during the launch phase.

[0041] See also Figure 2 , is a circuit structure diagram after the satellite-rocket separation provided by an embodiment of the present invention. After the satellite-rocket separation, the first travel switch and the second travel switch in the shunt permit module 133 are opened, the shunt permit module 133 is in the off state, and the weak light shunt NMOS tubes in the weak light shunt module 120 are all cut off, and the current generated by the multi-channel solar array 110 is no longer shunted; at the same time, the discharge permit module 132 is turned on, the battery pack 140 is discharged, and the multi-channel PMOS tubes in the charge and discharge control module 131 are turned on, and the battery pack 140 is discharged to the outside, completing the initial autonomous power-up of the satellite into orbit.

[0042] Furthermore, when the digital control module 170 is powered on, it receives the satellite-rocket separation signal, sends a weak light shunt prohibition instruction, and disconnects the second travel switch in the shunt prohibition module 133, thereby ensuring that the trigger path of the weak light shunt module 120 is completely disconnected and the weak light shunt module 120 is completely cut off; and uses the satellite-rocket separation signal and the battery pack voltage signal as input variables, sends a sailboard deployment instruction, deploys the satellite sailboard, and completes the normal power generation of the satellite sailboard. At this point, the satellite completes the power-off maintenance before separation and the autonomous power-on after separation.

[0043] It can be understood that the digital control module 170 can be a lower computer module of the power controller, or a satellite service module of the satellite integrated electronic computer, which is used to collect signals from the power system and output corresponding instructions according to the signals. In this application, the digital control module 170 is used to collect satellite-rocket separation signals and output battery discharge prohibition instructions and weak light shunt prohibition instructions; when the satellite-rocket separation signal indicates that the current state is separation, the digital control module 170 outputs instructions to close the first travel switch and open the second travel switch. Thereby, the satellite can be powered on autonomously.

[0044] Optionally, the digital control module 170 can be functionally expanded to collect other signals and output corresponding control instructions, and perform other logical judgments and fault processing.

[0045] Preferably, after the satellite is separated, if the satellite sailboard is not unfolded, the design of the satellite sailboard's outer panel facing outward can still allow the satellite to be illuminated with a higher probability to generate partial current, thereby charging the battery pack 140 and powering the load 150. The ground can establish communication with the satellite when appropriate to handle the fault.

[0046] Furthermore, when the satellite sailboard does not have enough energy due to faults such as abnormal satellite in-orbit attitude, the digital control module 170 collects the power supply voltage signal and automatically sends an instruction to disconnect the first travel switch through fault logic judgment, disconnecting the discharge path of the battery pack 140, thereby avoiding damage caused by excessive discharge of the battery pack 140; at the same time, the current energy of the entire satellite is insufficient, and the satellite still has a high probability of charging the battery pack 140 through the parasitic diode in the charge and discharge control module 131 through the current generated when the sailboard is illuminated. When the voltage of the battery pack 140 is charged to a preset reasonable threshold, the digital control module 170 turns on the first travel switch, the satellite resumes stable power supply, and the ground can establish stable communication to intervene and handle the fault.

[0047] Based on the same inventive concept as the above embodiments, the present invention provides a control method for a satellite-rocket separation power supply control circuit. Figure 3 As shown, including: Step S201, before the rocket and satellite are separated, the weak light splitter module 120 is controlled to cut off the multi-channel solar array 110 to power the load 150, and the power control module 130 is used to cut off the battery pack 140 to power the load 150; Step S202 , after the satellite and rocket are separated, the power-on control module 130 controls the battery pack 140 to power the load 150 .

[0048] In one embodiment, after the satellite and rocket are separated, the method further comprises: The digital control module 170 controls the shunt prohibition module 133 in the power-on control module 130 to be in an off state, thereby ensuring that the weak-light shunt module 120 is in a completely off state.

[0049] In one embodiment, after the power-on control module 130 controls the battery pack 140 to power the load 150, the method further includes: The weak light diversion module 120 is controlled to restore the multi-channel solar array 110 to power the load 150 .

[0050] For the specific steps to implement the above method, please refer to Figure 1 as well as Figure 2 The description of the illustrated embodiment will not be repeated here.

[0051] Based on the same inventive concept as the aforementioned embodiments, an embodiment of the present invention provides a satellite, comprising the satellite-rocket separation power supply control circuit as described in any one of the aforementioned embodiments.

[0052] In the present invention, the same or similar terminology concepts, technical solutions and / or application scenario descriptions are generally described in detail only the first time they appear. When they appear again later, they are generally not repeated for the sake of brevity. When understanding the technical solution and other contents of the present invention, for the same or similar terminology concepts, technical solutions and / or application scenario descriptions that are not described in detail later, reference can be made to the previous related detailed descriptions.

[0053] In the present invention, the description of each embodiment has its own emphasis. For parts that are not described or recorded in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0054] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0055] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A satellite-rocket separation power supply control circuit, used for a satellite, characterized in that: It includes multi-channel solar array, weak light shunt module, power-on control module, battery pack and load; The multi-channel solar array is connected to the load via the weak light shunting module, and the battery pack is connected to the load via the power-on control module; The weak light shunting module is used to cut off the multi-channel solar array to power the load before the satellite-rocket separation; The power-on control module is used to cut off the battery pack to power the load before the satellite-rocket separation; The power-on control module is also used to control the battery pack to power the load after the satellite-rocket separation.

2. The circuit according to claim 1, characterized in that The weak light shunt module comprises a weak light shunt fuse and a weak light shunt NMOS tube which are connected to each other.

3. The circuit according to claim 1, characterized in that The circuit also includes a voltage stabilization shunt module; The voltage stabilization shunt module includes a voltage stabilization shunt fuse, a voltage stabilization shunt NMOS tube, a voltage stabilization control circuit and a bus capacitor array. The voltage stabilization shunt NMOS tube is connected to the voltage stabilization control circuit through the voltage stabilization shunt fuse and is connected in parallel with the bus capacitor array to stabilize the voltage output by the multi-channel solar array.

4. The circuit according to claim 1, characterized in that The power-on control module includes a charge and discharge control module; The charge and discharge control module includes a plurality of PMOS tubes and parasitic diodes respectively connected to the plurality of PMOS tubes, and is used to control the charging and discharging of the battery pack.

5. The circuit according to claim 4, characterized in that The power-on control module also includes a discharge permission prohibition module; The discharge prohibition module includes a resistor voltage divider network, a discharge prohibition switch and a first star table. One end of the resistor voltage divider network is connected to the first star table through the discharge prohibition switch, and the other end of the resistor voltage divider network is respectively connected to the charge and discharge control module and the positive electrode of the battery pack.

6. The circuit according to claim 5, characterized in that The power-on control module also includes a shunt permission prohibition module; The shunt prohibition module includes a shunt prohibition switch, a second star table, a first travel switch and a second travel switch. The shunt prohibition switch is connected to the first travel switch through the second star table, and the first travel switch is respectively connected to the first star table, the second travel switch and the negative pole of the battery pack.

7. A control method based on the satellite-rocket separation power supply control circuit according to any one of claims 1 to 6, characterized in that: The method comprises: Before the separation of the rocket and the satellite, the weak light shunt module is controlled to cut off the multi-channel solar array to power the load, and the battery pack is cut off through the power-on control module to power the load; After the satellite and rocket are separated, the power-on control module controls the battery pack to power the load.

8. The method according to claim 7, characterized in that After the satellite and rocket are separated, the method further comprises: The shunt permission prohibition module in the power-on control module is controlled to be in a disconnected state through the digital control module, thereby ensuring that the weak light shunt module is in a completely cut-off state.

9. The method according to claim 7, characterized in that: After controlling the battery pack to power the load through the power-on control module, the method further includes: The weak light shunting module is controlled to restore the multi-channel solar array to power the load.

10. A satellite, characterized in that: It comprises a satellite-rocket separation power supply control circuit as described in any one of claims 1-6.

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