CN116119031B - Satellite and rocket separation control system, method and storage medium - Google Patents
Satellite and rocket separation control system, method and storage medium Download PDFInfo
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- CN116119031B CN116119031B CN202310413247.5A CN202310413247A CN116119031B CN 116119031 B CN116119031 B CN 116119031B CN 202310413247 A CN202310413247 A CN 202310413247A CN 116119031 B CN116119031 B CN 116119031B
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- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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Abstract
The application discloses a satellite and rocket separation control system, a satellite and rocket separation control method and a storage medium, wherein the satellite and rocket separation control system comprises the following components: the system comprises a sailboard detector, a satellite and arrow separation switch detector and a satellite computer. The star computer is respectively connected with the sailboard detector, the satellite and arrow separation detector and the satellite and arrow separation switch detector and is configured to execute the following operations: responding to a triggering instruction for powering up the satellite, and simultaneously transmitting a state information acquisition instruction to a plurality of detectors; receiving feedback information transmitted by a plurality of detectors, and taking a detector corresponding to the earliest received feedback information as a target detector; accessing a separation status table corresponding to the target detector; acquiring state information measured by a plurality of detectors; determining the separation state information of the satellite according to the state information and the separation state table; and performing corresponding satellite separation operation according to the determined separation state information. Thus, the efficiency of the satellite performing the power-up and separation operations can be improved.
Description
Technical Field
The present disclosure relates to the field of satellite technologies, and in particular, to a satellite and rocket separation control system, a satellite and rocket separation control method, and a storage medium.
Background
The satellite-rocket separation is an important control technology in the technical field of satellites, and in the satellite-rocket separation process, a plurality of operations such as satellite separation, whole satellite power-on, solar sailboard unfolding, sun orientation and the like are needed, so that the process of completing the satellite-rocket separation by energy source is realized. And in the satellite-rocket separation process, relatively complex control requirements are put forward on satellite electrification. For example, the phase of the rocket from ignition to separation of the rocket is usually dominated by the rocket, and the satellite is not powered. Typically, the satellite is powered up after the satellite is separated from the rocket, and further subjected to a subsequent satellite-rocket separation process.
And after the satellite computer receives the instruction for powering up the satellite, corresponding satellite separation operation is required according to the state information corresponding to the satellite. However, if waiting for the state information corresponding to the satellite to be received is too long, the efficiency of the satellite to perform the power-up and separation operations may be reduced, which may have serious consequences.
The publication number is CN115688390A, and the name is a method for designing the separation time sequence de-tasking of the rocket satellites. Comprising the following steps: according to the satellite-rocket separation mode, the position and speed of the rocket immediately before the first satellite-rocket separation, the separation speed, the mass of the satellite and the total mass of the rocket, the installation position of the satellite in the rocket and the number of satellites, the rocket separation time sequence is automatically designed.
The publication number is CN115246492A, and the name is a track-keeping final task planning system. Comprising the following steps: the task planning device is used for sending task control information of a target detection task to the track-remaining final stage after the track-remaining final stage finishes the separation of the satellites and the arrows; and the track-keeping final stage is in communication connection with the task planning device and is used for controlling the attitude control power system in the track-keeping final stage to complete attitude control and/or track control based on task control information of the target detection task, controlling the detection load in the track-keeping final stage to acquire detection data of the target detection task and transmitting the detection data to the task planning device.
Aiming at the technical problems that if the time for waiting to receive the state information corresponding to the satellite is too long in the prior art, the efficiency of the satellite to execute the power-on and separation operation can be reduced, and serious consequences can be caused, no effective solution has been proposed at present.
Disclosure of Invention
The disclosure provides a satellite and arrow separation control system, a satellite and arrow separation control method and a storage medium, which at least solve the technical problems that if waiting for receiving state information corresponding to a satellite is too long, the efficiency of power-on and separation operation of the satellite is possibly reduced, and serious consequences are possibly caused in the prior art.
According to one aspect of the present application, there is provided a satellite-rocket separation control system, comprising: the solar panel display device comprises a panel detector, a display device and a display device, wherein the panel detector is used for acquiring unfolding state information of a solar panel, and the unfolding state information is used for indicating that the solar panel is unfolded or not unfolded in place; the satellite-rocket separation detector is used for acquiring satellite-rocket separation state information indicating a satellite-rocket separation state, wherein the satellite-rocket separation state comprises: separated and unseparated; the satellite rocket disconnecting switch detector is connected with the satellite rocket disconnecting switch and is used for detecting disconnecting switch state information of the satellite rocket disconnecting switch, wherein the disconnecting switch state information comprises: closing and opening; and a star computer connected to the windsurfing board detector, the satellite and rocket separation detector, and the satellite and rocket separation switch detector, respectively, and configured to perform the following operations: responding to a triggering instruction for powering up the satellite, and simultaneously sending a state information acquisition instruction to a plurality of detectors, wherein the state information acquisition instruction is used for indicating an instruction for acquiring the unfolding state information of the solar sailboard, the satellite and arrow separation state information and the separation switch state information of the satellite and arrow separation switch; receiving feedback information transmitted by a plurality of detectors, and taking a detector corresponding to the earliest received feedback information as a target detector; accessing a separation state table corresponding to the target detector, wherein the separation state table is used for indicating the corresponding relation between different state information and separation state information of the satellite; acquiring state information measured by a plurality of detectors; determining the separation state information of the satellite according to the state information and the separation state table, wherein the separation state information of the satellite is used for indicating the current separation state of the satellite; and performing corresponding satellite separation operation according to the determined separation state information.
According to another aspect of the present application, a satellite-rocket separation control method is provided, which is applied to a satellite computer, and includes: responding to a triggering instruction for powering up the satellite, and simultaneously sending a state information acquisition instruction to a plurality of detectors, wherein the state information acquisition instruction is used for indicating an instruction for acquiring the unfolding state information of the solar sailboard, the satellite and arrow separation state information and the separation switch state information of the satellite and arrow separation switch; receiving feedback information transmitted by a plurality of detectors, and taking a detector corresponding to the earliest received feedback information as a target detector; accessing a separation state table corresponding to the target detector, wherein the separation state table is used for indicating the corresponding relation between different state information and separation state information of the satellite; acquiring state information measured by a plurality of detectors; determining the separation state information of the satellite according to the state information and the separation state table, wherein the separation state information of the satellite is used for indicating the current separation state of the satellite; and performing corresponding satellite separation operation according to the determined separation state information.
According to another aspect of the present application, there is provided a storage medium comprising a stored program, wherein the method of any one of the above is performed by a processor when the program is run.
The application provides a satellite and rocket separation control system. The satellite and rocket separation system comprises: the system comprises a sailboard detector, a satellite and arrow separation switch detector and a satellite computer. The star computer is respectively connected with the sailboard detector, the star separation detector and the star separation switch detector. And because the star computer can respond to the triggering instruction for powering up the satellite, send the state information to obtain the instruction to a plurality of detectors at the same time, and regard the detector corresponding to feedback information received earliest as the goal detector, therefore can achieve the technical effect of saving time. In addition, the satellite computer accesses the separation state table corresponding to the target detector and determines the separation state information of the satellite according to the state information and the separation state tables measured by the plurality of detectors, so that the power-on and separation operations can be accurately performed. Therefore, the technical effect of improving the efficiency of the satellite in performing the power-on and separation operation is achieved through the product structure. Further, the technical problems that if the time for waiting to receive the state information corresponding to the satellite is too long, the efficiency of the satellite to execute the power-on and separation operation is possibly reduced and serious consequences are possibly caused in the prior art are solved.
The above, as well as additional objectives, advantages, and features of the present application will become apparent to those skilled in the art from the following detailed description of a specific embodiment of the present application when read in conjunction with the accompanying drawings.
Drawings
Some specific embodiments of the present application will be described in detail hereinafter by way of example and not by way of limitation with reference to the accompanying drawings. The same reference numbers will be used throughout the drawings to refer to the same or like parts or portions. It will be appreciated by those skilled in the art that the drawings are not necessarily drawn to scale. In the accompanying drawings:
FIG. 1 is a schematic diagram of a satellite-rocket separation control system according to a first aspect of the embodiments of the present application;
FIG. 2 is a modular schematic view of a satellite flight management program according to a first aspect of an embodiment of the present application;
FIG. 3A is a flow chart of determining a satellite separation status when a windsurfing board detector is targeted according to a first aspect of an embodiment of the present application;
FIG. 3B is a flow chart of determining a satellite separation status when a satellite separation detector is targeted for a first aspect of an embodiment of the present application;
FIG. 3C is a flow chart of determining a satellite separation status when a satellite separation switch detector is targeted for a first aspect of an embodiment of the present application; and
Fig. 4 is a flow chart of a satellite-arrow separation control method according to another aspect of an embodiment of the present application.
Detailed Description
It should be noted that, without conflict, the embodiments of the present disclosure and features of the embodiments may be combined with each other. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
In order that those skilled in the art will better understand the present disclosure, a technical solution in the embodiments of the present disclosure will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present disclosure, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without inventive effort, based on the embodiments in this disclosure, shall fall within the scope of the present disclosure.
It should be noted that the terms "first," "second," and the like in the description and claims of the present disclosure and in the foregoing figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the terms so used are interchangeable under appropriate circumstances such that the embodiments of the disclosure described herein are, for example, capable of operation in connection with other embodiments. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
Fig. 1 is a schematic structural diagram of a satellite-rocket separation control system according to an embodiment of the present application. Referring to fig. 1, a satellite-rocket separation control system includes: the solar panel display device comprises a panel detector, a display device and a display device, wherein the panel detector is used for acquiring unfolding state information of a solar panel, and the unfolding state information is used for indicating that the solar panel is unfolded or not unfolded in place; the satellite-rocket separation detector is used for acquiring satellite-rocket separation state information indicating a satellite-rocket separation state, wherein the satellite-rocket separation state comprises: separated and unseparated; the satellite rocket disconnecting switch detector is connected with the satellite rocket disconnecting switch and is used for detecting disconnecting switch state information of the satellite rocket disconnecting switch, wherein the disconnecting switch state information comprises: closing and opening; and a star computer connected to the windsurfing board detector, the satellite and rocket separation detector, and the satellite and rocket separation switch detector, respectively, and configured to perform the following operations: responding to a triggering instruction for powering up the satellite, and simultaneously sending a state information acquisition instruction to a plurality of detectors, wherein the state information acquisition instruction is used for indicating an instruction for acquiring the unfolding state information of the solar sailboard, the satellite and arrow separation state information and the separation switch state information of the satellite and arrow separation switch; receiving feedback information transmitted by a plurality of detectors, and taking a detector corresponding to the earliest received feedback information as a target detector; accessing a separation state table corresponding to the target detector, wherein the separation state table is used for indicating the corresponding relation between different state information and separation state information of the satellite; acquiring state information measured by a plurality of detectors; determining the separation state information of the satellite according to the state information and the separation state table, wherein the separation state information of the satellite is used for indicating the current separation state of the satellite; and performing corresponding satellite separation operation according to the determined separation state information.
As described in the background art, the satellite-rocket separation is an important control technology in the satellite technical field, and in the satellite-rocket separation process, multiple operations such as satellite separation, whole satellite power-on, solar panel unfolding, sun orientation and the like are required, so that the process of completing the satellite-rocket separation by energy source is realized. And in the satellite-rocket separation process, relatively complex control requirements are put forward on satellite electrification. For example, the phase of the rocket from ignition to separation of the rocket is usually dominated by the rocket, and the satellite is not powered. Typically, the satellite is powered up after the satellite is separated from the rocket, and further subjected to a subsequent satellite-rocket separation process.
And after the satellite computer receives the instruction for powering up the satellite, corresponding satellite separation operation is required according to the state information corresponding to the satellite. However, if waiting for the state information corresponding to the satellite to be received is too long, the efficiency of the satellite to perform the power-up and separation operations may be reduced, which may have serious consequences.
Fig. 2 is a modular schematic diagram of a satellite flight management program according to an embodiment of the present application. Referring to fig. 2, a power-on test module, a program control module before separation, a program control module during separation, a program control module after separation, a satellite and arrow state acquisition module and a separation state determination module are arranged in the satellite flight management program. The satellite and arrow state acquisition module is configured to acquire state information of a satellite and arrow, the separation state determination module is used for determining a separation state of the satellite, the power-on test module is used for carrying out power-on test on the satellite, the program control module before separation is used for executing operation related to the satellite before separation, the program control module during separation is used for executing operation related to the satellite during separation, and the program control module after separation is used for executing operation related to the satellite after separation.
In view of this, the present application provides a satellite and rocket separation control system. The system comprises: sailboard detectors 106a,106b, a satellite separation detector 102, a satellite separation switch detector 104, and a star computer 101. Wherein, the windsurfing board detectors 106a,106b are configured to obtain the unfolding status information of the solar windsurfing boards 105a,105b, and the unfolding status information includes: expanded into place and unexpanded into place. The star-arrow separation detector 102 is configured to obtain star-arrow separation state information indicating a star-arrow separation state, where the star-arrow separation state includes: separated and not separated. The satellite rocket disconnecting switch detector 104 is connected with the satellite rocket disconnecting switch 103 and is used for detecting disconnecting switch state information of the satellite rocket disconnecting switch 103, wherein the disconnecting switch state information comprises: closing and opening.
The star computer 101 is respectively connected to the sailboard detectors 106a and 106b, the satellite and arrow separation detector 102 and the satellite and arrow separation switch detector 104, and is configured to collect status information measured by the respective detectors.
Further, the star computer 101 is also capable of performing the following operations:
first, after receiving a trigger instruction for powering up the satellite, the satellite computer 101 responds to the trigger instruction for powering up the satellite, and simultaneously transmits a status information acquisition instruction to the sailboard detectors 106a and 106b, the satellite separation detector 102, and the satellite separation switch detector 104. The status information acquiring instruction is used for indicating to acquire the unfolding status information, the satellite separation status information and the separation switch status information of the satellite separation switch 103 of the solar sailboards 105a and 105 b.
The windsurfing detectors 106a,106b then query whether the deployment status information of the solar windsurfing boards 105a,105b is detected; the satellite-arrow separation detector 102 inquires whether satellite-arrow separation state information is detected; the satellite-arrow-separation-switch detector 104 inquires whether the separation-switch state information of the satellite-arrow-separation switch 103 is detected.
After any one of the windsurfing board detectors 106a,106b, the satellite and rocket separation detector 102 and the satellite and rocket separation switch detector 104 detects the corresponding state information, feedback information is sent to the star computer 101. The feedback information may be, for example, information "measured state information". For example, the star separation detector 102 of the windsurfing board detectors 106a,106b, the star separation detector 102, and the star separation switch detector 104 has measured the star separation status information, i.e., after receiving the "status information acquisition instruction" sent by the star computer 101, sends feedback information of "measured status information" to the star computer 101. Since the corresponding status information is measured by the windsurfing detectors 106a,106b and the satellite and rocket isolating switch detector 104 only later, the windsurfing detectors 106a,106b and the satellite and rocket isolating switch detector 104 only later can send feedback information of "the measured status information" to the star computer 101.
Further, the star computer 101 regards a detector corresponding to the feedback information received earliest as a target detector. For example, the star-and-arrow separation detector 102 sends feedback information to the star computer 101 at the earliest, i.e., the star computer 101 treats the star-and-arrow separation detector 102 as the target detector.
And for the windsurfing board detectors 106a,106b, the satellite and rocket separation detector 102 and the satellite and rocket separation switch detector 104, there is a separation status table uniquely corresponding thereto. Table 1 shows a separate status table corresponding to the windsurfing detectors 106a,106 b.
TABLE 1
Referring to Table 1, if the windsurfing detectors 106a,106b are target detectors, it is necessary to first determine whether the deployed state of the solar windsurfing boards 105a,105b is deployed in place or not deployed in place. "N" indicates that all of the windsurfing boards are in a "not deployed in place" and "Y" indicates that at least one of the solar windsurfing boards 105a,105b is in a deployed in place. FIG. 3A is a flow chart of determining a satellite separation status when the windsurfing board detectors 106a,106b are targeted according to an embodiment of the present application. It is noted that table 1 corresponds to the method flow of determining the satellite separation state in fig. 3A.
Table 2 shows a separation status table corresponding to the satellite-arrow separation detector 102.
TABLE 2
Referring to table 2, if the satellite and arrow separation detector 102 is a target detector, it is necessary to determine whether the satellite and arrow separation state is separated (Y) or not separated (N). The satellite separation status information is then determined based on the status information measured by the windsurfing board detectors 106a,106b and the satellite separation switch detector 104, respectively. Fig. 3B is a flowchart of determining a satellite separation state when the satellite-arrow separation detector 102 is the target detector according to an embodiment of the present application. It is noted that table 2 corresponds to the method flow of determining the satellite separation state in fig. 3B.
Table 3 shows a separation status table corresponding to the satellite-arrow separation switch detector 104.
TABLE 3 Table 3
Referring to table 3, if the satellite and rocket disconnecting switch detector 104 is the target detector, it is necessary to determine whether the disconnecting switch state information is on (Y) or off (N). The satellite separation status information is then determined based on the status information measured by the windsurfing board detectors 106a,106b and the satellite separation detector 102, respectively. Fig. 3C is a flowchart of determining a satellite separation status when the satellite-arrow separation switch detector 104 is the target detector according to an embodiment of the present application. It is noted that table 3 corresponds to the method flow of determining the satellite separation state in fig. 3C.
The separation state information of the satellite is used for indicating the current separation state of the satellite. Wherein, the satellite separation state includes: during testing, before separation, during separation, and after separation. And wherein "under test" means that the satellite is currently under test; "before separation" means that the satellite is currently in a pre-separation state; "in separation" means that the satellite is currently in a state of separation; "post-separation" means that the satellite is currently in a post-separation state.
Accordingly, the star computer 101 accesses the separation state table corresponding to the target detector after determining the target detector. For example, after determining that the target detector is the satellite-arrow separation detector 102, the star computer 101 accesses a separation state table corresponding to the satellite-arrow separation detector 102.
Further, the satellite computer 101 receives the state information corresponding to the sailboard detectors 106a and 106b, the satellite separation detector 102, and the satellite separation switch detector 104, and then determines the separation state information of the satellite based on the state information measured by the sailboard detectors 106a and 106b, the satellite separation detector 102, and the satellite separation switch detector 104, and the separation state table corresponding to the target detector.
For example, when the star computer 101 regards the star separation detector 102 as a target detector, it determines that the separation state table corresponding to the target detector is table 2. The satellite separation state information received by the satellite computer 101 and measured by the satellite separation detector 102 is not separated (N); the deployment status information of the solar panel detectors 105a,105b, measured by the panel detectors 106a,106b, is that at least one solar panel is deployed in place (Y); the separation switch state information of the satellite separation switch 103 measured by the satellite separation switch detector 104 is closed (Y). The separation status information of the satellite can be determined as in-test according to table 2. Other possible satellite separation status information may be obtained by the above operations, and will not be described herein.
Finally, the satellite computer 101 performs a corresponding satellite separation operation according to the determined separation status information. Specifically, when the separation state determining module in the satellite computer 101 determines that the satellite is in the state of "under test", the satellite is electrified by the power-on module running. When the satellite is determined to be in a state before separation, the operation related to the satellite before separation is performed through the program control module before separation. Upon determining that the satellite is in the "off-going" state, operations associated with the satellite off-going are performed by the off-going programming module. When the satellite is determined to be in a 'separated' state, the operation related to the satellite after separation is performed through the program control module after separation.
For example, 1. When the windsurfing board status information and the satellite and rocket separation status information are both "Y", the satellite is in a "separated" state at this time, if a "power-up instruction" is received at this time, this means that the satellite is in an abnormal power-off state for some reason. Therefore, after separation, the program control module can call an abnormal power-off recovery flow so as to perform abnormal power-off recovery.
2. For another example, when the sailboard status information is "Y" and the satellite-rocket separation status information is "N", the satellite is in a test state at this time, and thus applied to the "power-on command", and the satellite computer 101 performs a power-on operation on the satellite through the power-on test module.
3. For another example, when the windsurfing status information is "N" and the satellite and rocket separating status information is also "N", if the separating switch status information is "N" at this time. The satellite enters the power-up program when the sailboard is not unfolded in place, the satellite rocket is not separated, and the separating switch is in an off state, so that the satellite computer 101 can judge that the satellite is in the power-up test stage at the moment, and the power-up test module is used for carrying out power-up test on the satellite.
4. For another example, when the windsurfing status information is "N" and the satellite and rocket separating status information is also "N", if the separating switch status information is "Y" at this time. It means that the satellite enters the power-up program when the sailboard is not unfolded in place, the satellite is not separated, and the separation switch is in a closed state, so that the satellite computer 101 can determine that the satellite is in a state before separation at this time, and thus the operation before separation is performed through the program control module before separation. Specifically, the operation of the program control module before separation comprises the following steps: the battery discharge switch 108 is closed. And continuously monitoring the satellite-arrow separation state information, and executing a separation program control program (namely, a program called by a separation program control module) under the condition that the satellite-arrow separation state information is 'Y'.
5. For another example, when the sailboard status information is "N" and the satellite and arrow separation status information is also "Y", if the separation switch status information is "N" at this time, the satellite computer 101 determines that the current satellite is in separation and in an abnormal power-off state, so that the abnormal power-off recovery process is invoked by the separation middle-range control module to recover from the abnormal power-off state.
6. For another example, when the sailboard status information is "N" and the satellite-rocket separation status information is also "Y", if the separation switch status information is "Y" at this time, the satellite computer 101 determines that the current satellite is in a separated state, and thus invokes the separation program through the separation middle program module. Specifically, the split programming procedure includes the following operations: the whole star is initially powered up. The entire satellite rate damps so that the satellite stops rotating. And powering up the click module of the solar sailboard and unfolding the solar sailboard. And after the solar sailboard is unfolded, finishing the daily operation, and ending the program-control separation program.
Therefore, the technical effect of improving the efficiency of the satellite in performing the power-on and separation operation is achieved through the product structure.
Optionally, a solar sailboard is connected to the primary busbar for providing power to the satellite.
Optionally, the solar sailboard comprises: a first solar array and a second solar array, the array detector comprising: the system comprises a first sailboard detector and a second sailboard detector, wherein the first sailboard detector is connected with a first solar sailboard and is configured to acquire unfolding state information of the first solar sailboard; the second sailboard detector is connected with the second solar sailboard and is configured to acquire the unfolding state information of the second solar sailboard; and the first sailboard detector and the second sailboard detector are respectively connected with the star computer.
Specifically, referring to FIG. 1, the solar panels 105a,105b include a first solar panel 105a and a second solar panel 105b. The windsurfing board detectors 106a,106b comprise a first windsurfing board detector 106a and a second windsurfing board detector 106b. The first sailboard detector 106a is connected to the first solar sailboard 105a, and is configured to detect an unfolding state of the first solar sailboard 105a, and obtain information of the unfolding state of the first solar sailboard 105 a; the second sailboard detector 106b is connected to the second solar sailboard 105b, and is configured to detect an unfolding state of the second solar sailboard 105b, and obtain information about the unfolding state of the second solar sailboard 105b. The first sailboard detector 106a and the second sailboard detector 106b are also respectively connected to the star computer 101, and after the obtained expansion state information of the first solar sailboard 105a and the second solar sailboard 105b is obtained, the obtained expansion state information is respectively sent to the star computer 101. Thus, the satellite computer 101 can determine the separation state information of the satellite according to the obtained deployment state information corresponding to the first solar array 105a and the second solar array 105b, respectively.
Optionally, the method further comprises: the storage battery and the storage battery discharging switch are connected with the primary bus through the storage battery discharging switch; and the star computer is connected with the storage battery discharging switch and is configured to control the on and off of the storage battery discharging switch.
Specifically, referring to fig. 1, a battery 107 and a battery discharge switch 108 are also provided in the satellite-rocket separation control system. The battery 107 is connected to the primary bus via a battery discharge switch 108, and the star computer 101 is connected to the battery discharge switch 108. Accordingly, the star computer 101 can further control the supply and discharge of the battery 107 to and from the primary bus bar by controlling the battery discharge switch 108.
Optionally, the method further comprises: the discharging control circuit is respectively connected with the storage battery discharging switch and the primary bus; and the star computer is connected with the discharge control circuit and is configured for controlling the discharge of the storage battery.
Specifically, referring to fig. 1, the satellite-rocket separation control system further includes a discharge control circuit 109. The discharge control circuit 109 is connected to the battery discharge switch 108 and the primary bus bar, respectively. The star computer 101 is also connected to a discharge control circuit 109, and further controls discharge of the battery 107 by controlling the discharge control circuit 109.
Fig. 4 is a flowchart of a satellite-rocket separation control method according to an embodiment of the present application. Referring to fig. 4, according to another aspect of the embodiment of the present application, there is further provided a satellite-rocket separation control method, which is applied to a satellite computer, including:
s402: responding to a triggering instruction for powering up the satellite, and simultaneously sending a state information acquisition instruction to a plurality of detectors, wherein the state information acquisition instruction is used for indicating an instruction for acquiring the unfolding state information of the solar sailboard, the satellite and arrow separation state information and the separation switch state information of the satellite and arrow separation switch;
s404: receiving feedback information transmitted by a plurality of detectors, and taking a detector corresponding to the earliest received feedback information as a target detector;
s406: accessing a separation state table corresponding to the target detector, wherein the separation state table is used for indicating the corresponding relation between different state information and separation state information of the satellite;
s408: acquiring state information measured by a plurality of detectors;
s410: determining the separation state information of the satellite according to the state information and the separation state table, wherein the separation state information of the satellite is used for indicating the current separation state of the satellite; and
S412: and carrying out corresponding satellite separation operation according to the determined separation state information.
Specifically, referring to fig. 3A, 3B, and 3C, the method flow of fig. 3A corresponds to table 1 described above, the method flow of fig. 3B corresponds to table 2 described above, and the method flow of fig. 3C corresponds to table 3 described above.
FIG. 3A is a flow chart of determining the separation status information of satellites when the windsurfing board detectors 106a,106b are the target detectors.
Specifically, first, after the satellite computer 101 receives an instruction for powering up the satellite and determines that the sailboard detectors 106a and 106b are target detectors, it is required to determine whether at least any one of the solar sailboards 105a and 105b is deployed in place according to deployment status information corresponding to the solar sailboards 105a and 105b acquired by the sailboard detectors 106a and 106b as target detectors. Under the condition that at least any one of the solar sailboards 105a and 105b is judged to be unfolded in place, judging whether the satellites are separated or not according to the acquired satellite-rocket separation state information; and under the condition that any one of the solar sailboards 105a and 105b is not unfolded in place, judging whether the satellites are separated or not according to the acquired satellite-rocket separation state information.
Under the condition that at least any one of the solar sailboards 105a and 105b is judged to be unfolded and the satellite-arrow separation state is determined to be separated, whether the satellite-arrow separation switch 103 is closed or not, the satellite separation state is described as abnormal power failure, and the process is required to be restored; and under the condition that any solar sailboard of the solar sailboards 105a and 105b is not unfolded in place and the satellite-rocket separation state is determined to be not separated, the satellite is in the state of power-on test at present.
In the case of determining that at least any one of the solar panels 105a,105b is not deployed in place and determining that the satellite-rocket separation state is not separated, it is necessary to further determine whether the satellite-rocket separation switch 103 is closed according to the satellite-rocket separation switch state information. If the satellite and rocket separating switch 103 is already closed, the storage battery discharging switch 108 is required to be closed, and the satellite and rocket separating signal is continuously monitored until the satellite and rocket are separated, and the primary bus is initially powered up; if the satellite-rocket disconnecting switch 103 is not closed, it indicates that the satellite is currently in the power-on test state.
In the case of determining that either solar panel 105a,105b is not deployed in place and determining that the satellite-arrow separation status is separated, it is necessary to further determine whether the satellite-arrow separation switch 103 is closed according to the satellite-arrow separation switch status information. If the satellite separator switch 103 has been closed, then it is necessary to further close the battery discharge switch 108 and initially power up the primary bus. Further, the entire satellite rate dampens, causing the satellites to stop rotating and power up the motor modules of the solar panels 105a,105b and spread the solar panels 105a,105b. After the solar sailboards 105a and 105b are unfolded, the sun-setting operation is completed, and the program-control separation procedure is finished; if the satellite-rocket disconnecting switch 103 is not closed, it indicates that the satellite is in an abnormal power-off state, and a recovery process is required.
Fig. 3B is a schematic flow chart of determining separation status information of satellites when the satellite-arrow separation detector 102 is a target detector.
Specifically, firstly, after the star computer 101 receives an instruction for powering up a satellite and determines that the satellite-rocket separation detector 102 is a target detector, it is necessary to determine whether the satellite-rocket separation state is separated or not according to the satellite-rocket separation state information acquired by the satellite-rocket separation detector 102 as the target detector. In the event that it is determined that the satellites are not separated, it is necessary to further determine whether at least either of the solar panels 105a,105b is deployed in place. If at least either solar panel 105a,105b is deployed in place, then whether the satellite-rocket disconnect switch 103 is closed or not, it is indicated that the satellite is currently in the stage of power-up testing; if either solar panel 105a,105b is not deployed in place, it is necessary to further determine whether the arrow disconnect switch 103 is closed based on the arrow disconnect switch status information.
If the satellite arrow separation switch state information shows that the satellite arrow separation switch 103 is not closed, the satellite is in the current stage of power-on test; if the satellite-rocket separation switch status information indicates that the satellite-rocket separation switch 103 is already closed, the battery discharging switch 108 needs to be closed, and the satellite-rocket separation signal is continuously monitored until the satellite-rocket separation.
In addition, in the event that it is determined that the arrow has been separated and at least either of the solar panels 105a,105b is not deployed in place, it is desirable to further determine whether the arrow separation switch 103 is closed based on the arrow separation switch status information. If it is determined that the satellite and arrow separation switch 103 has been closed, then it is necessary to further close the battery discharge switch 108 and initially power up the primary bus. Further, the entire satellite rate dampens, causing the satellites to stop rotating and power up the motor modules of the solar panels 105a,105b and spread the solar panels 105a,105b. After the solar sailboards 105a and 105b are unfolded, the sun-setting operation is completed, and the program-control separation procedure is finished; if it is determined that the satellite-rocket separating switch 103 is not closed, it indicates that the satellite is in an abnormal power-off state, and a recovery process is required.
Further, if it is determined that the satellite and arrow have been separated and at least any one of the solar panels 105a,105b has been deployed, the satellite is in an abnormally powered-off state regardless of whether the satellite and arrow separation switch 103 is closed, and a recovery process is required.
Fig. 3C is a schematic flow chart of determining the separation status information of the satellite when the satellite-arrow separation switch detector 104 is the target detector.
Specifically, firstly, after the satellite computer 101 receives an instruction for powering up the satellite and determines that the satellite-arrow separation switch detector 104 is a target detector, it is necessary to determine whether the state of the satellite-arrow separation switch 103 is closed or not according to the state information of the satellite-arrow separation switch 103 acquired by the satellite-arrow separation switch detector 104 as the target detector. In the case of determining that the star arrow separation switch 103 is not closed, it is necessary to further determine whether at least any one of the solar panels 105a,105b is deployed in place based on the panel deployment status information.
If at least either of the solar panels 105a,105b has been deployed in place, then a further determination is needed as to whether the star arrow separated status is separated or not. If the satellite and rocket separation state is separation, the current satellite state is abnormal power failure, and a recovery flow is needed; if the satellite and rocket separation state is not separated, the satellite is in the power-on state at present.
If at least either of the solar panels 105a,105b is not deployed in place, then a further determination is required as to whether the star separated or not separated. If the satellite and rocket separation state is the separation state, the satellite current state is abnormal power failure, and a recovery flow is needed; if the satellite and rocket separation state is not separated, the satellite is in the power-on state at present.
In the state where it is determined that the star arrow separation switch 103 has been closed, it is necessary to further determine whether at least either one of the solar panels 105a,105b is deployed in place based on the panel deployment state information. If at least either of the solar panels 105a,105b has been deployed in place, then a further determination is needed as to whether the star arrow separated status is separated or not. If the satellite and arrow separation state is separated, the satellite is in an abnormal power-off state at present, and a recovery flow is needed; if the satellite and rocket separation state is not separated, the satellite is in the power-on state at present. If at least either of the solar panels 105a,105b is not deployed in place, then a further determination is needed as to whether the star arrow separated status is separated or not separated. If the satellite and rocket separated state is separated, the storage battery discharging switch 108 needs to be further closed, and the primary bus is initially powered up. Further, the entire satellite rate dampens, causing the satellites to stop rotating and power up the motor modules of the solar panels 105a,105b and spread the solar panels 105a,105b. After the solar sailboards 105a and 105b are unfolded, the sun-setting operation is completed, and the program-control separation procedure is finished; if the satellite and rocket separation state is not separated, the storage battery discharging switch 108 needs to be closed, and the satellite and rocket separation information is continuously monitored until the satellite and rocket are separated.
Therefore, the satellite computer 101 can determine the current separation status information of the satellite according to the above-mentioned method flow diagrams corresponding to different target detectors, and further perform corresponding satellite separation operations.
Optionally, the management program operated by the star service computer includes: the satellite and rocket state acquisition module is used for acquiring the unfolding state information of the solar sailboard; the separation state determining module determines satellite separation state information of the satellite according to the obtained sailboard unfolding state information, the satellite separation state information and the separation switch state information; the satellite power-on test module is used for carrying out power-on test on the satellite through the running power-on test module when the satellite is in a test state; the program control module before separation runs an operation instruction before separation with the satellite through the program control module before separation when the satellite is in a state before separation; the separation process program control module is used for running an operation instruction separated from the satellite when the satellite is in a separation state; and the program control module after separation is used for running an operation instruction separated from the satellite when the satellite is in a separated state.
Optionally, the method further comprises: closing a storage battery discharging switch by the program control module before separation; and continuously monitoring the satellite and arrow separation state information, and executing a separation program control program under the condition that the satellite and arrow separation state information is in a separation state.
Optionally, the separation program further comprises: initially powering up the whole satellite; the whole satellite completes rate damping, so that the satellite stops rotating; powering up the motor modules of the solar panels 105a,105b and expanding the solar panels 105a,105b; and completing the sun-to-sun operation after the solar panels 105a,105b are deployed.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present disclosure unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In the description of the present disclosure, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present disclosure and to simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be configured and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present disclosure; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
The foregoing is merely a preferred embodiment of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the technical scope of the present application should be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A satellite-rocket separation control system, comprising:
the solar panel display device comprises a panel detector, a display device and a display device, wherein the panel detector is used for acquiring unfolding state information of a solar panel, and the unfolding state information is used for indicating whether the solar panel is unfolded or not;
the satellite-rocket separation detector is used for acquiring satellite-rocket separation state information indicating a satellite-rocket separation state, wherein the satellite-rocket separation state comprises: separated and unseparated;
the satellite rocket disconnecting switch detector is connected with the satellite rocket disconnecting switch and is used for detecting disconnecting switch state information of the satellite rocket disconnecting switch, wherein the disconnecting switch state information comprises: closing and opening; and
a star computer connected to the sailboard detector, the satellite-rocket separation detector, and the satellite-rocket separation switch detector, respectively, and configured to perform the following operations:
Responding to a triggering instruction for powering up a satellite, and simultaneously sending a state information acquisition instruction to a plurality of detectors, wherein the state information acquisition instruction is used for indicating an instruction for acquiring the unfolding state information of the solar sailboard, the satellite and arrow separation state information and the separation switch state information of the satellite and arrow separation switch;
receiving feedback information transmitted by the plurality of detectors, and taking a detector corresponding to the earliest received feedback information as a target detector;
accessing a separation state table corresponding to the target detector, wherein the separation state table is used for indicating the corresponding relation between different state information and the separation state information of the satellite;
acquiring state information measured by the plurality of detectors;
determining the separation state information of the satellite according to the state information and the separation state table, wherein the separation state information of the satellite is used for indicating the current satellite separation state; and
and carrying out corresponding satellite separation operation according to the determined separation state information.
2. The system of claim 1, wherein the solar array is coupled to a primary bus for providing power to the satellite.
3. The system of claim 2, wherein the solar array comprises: a first solar array and a second solar array, the array detector comprising: a first windsurfing board detector and a second windsurfing board detector, wherein
The first sailboard detector is connected with the first solar sailboard and is configured to acquire unfolding state information of the first solar sailboard;
the second sailboard detector is connected with the second solar sailboard and is configured to acquire unfolding state information of the second solar sailboard; and
the first sailboard detector and the second sailboard detector are respectively connected with the star computer.
4. A system according to claim 3, further comprising: storage battery and storage battery discharging switch, wherein
The storage battery is connected with the primary bus through the storage battery discharging switch; and
the star computer is connected with the storage battery discharging switch and is configured to control the connection and disconnection of the storage battery discharging switch.
5. The system of claim 4, further comprising: discharge control circuit in which
The discharging control circuit is respectively connected with the storage battery discharging switch and the primary bus; and
The star computer is connected with the discharge control circuit and is configured to control the discharge of the storage battery.
6. The satellite and rocket separation control method is applied to a satellite computer and is characterized by comprising the following steps:
responding to a triggering instruction for powering up the satellite, and simultaneously sending a state information acquisition instruction to a plurality of detectors, wherein the state information acquisition instruction is used for indicating an instruction for acquiring the unfolding state information of the solar sailboard, the satellite and arrow separation state information and the separation switch state information of the satellite and arrow separation switch;
receiving feedback information transmitted by the plurality of detectors, and taking a detector corresponding to the earliest received feedback information as a target detector;
accessing a separation state table corresponding to the target detector, wherein the separation state table is used for indicating the corresponding relation between different state information and the separation state information of the satellite;
acquiring state information measured by the plurality of detectors;
determining the separation state information of the satellite according to the state information and the separation state table, wherein the separation state information of the satellite is used for indicating the current satellite separation state; and
And carrying out corresponding satellite separation operation according to the determined separation state information.
7. The method according to claim 6, wherein the management program for the satellite computer to run comprises:
the satellite and rocket state acquisition module is used for acquiring the unfolding state information of the solar sailboard;
the separation state determining module is used for determining satellite separation state information of the satellite according to the obtained sailboard unfolding state information, the satellite separation state information and the separation switch state information;
the satellite power-on test module is used for carrying out power-on test on the satellite through the running power-on test module when the satellite is in a test state;
the satellite control system comprises a pre-separation program control module, a satellite control module and a satellite control module, wherein when the satellite is in a pre-separation state, the pre-separation program control module runs an operation instruction before separation with the satellite;
the separation middle program control module is used for running an operation instruction separated from the satellite when the satellite is in a separation state; and
and when the satellite is in a separated state, the operation instruction separated from the satellite is operated through the separated program control module.
8. The satellite-arrow separation control method according to claim 7, further comprising:
closing a storage battery discharging switch; and
and continuously monitoring the satellite and arrow separation state information, and executing a separation program control program under the condition that the satellite and arrow separation state information is in a separation state.
9. The satellite-arrow separation control method according to claim 8, further comprising:
initially powering up the whole satellite;
the whole satellite completes rate damping, so that the satellite stops rotating;
powering up a motor module of the solar sailboard and expanding the solar sailboard; and
and after the solar sailboard is unfolded, finishing the sun-facing operation.
10. A storage medium comprising a stored program, wherein the method of any one of claims 6 to 9 is performed by a processor when the program is run.
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