CN116395148A - Satellite and rocket separation control system and control method - Google Patents
Satellite and rocket separation control system and control method Download PDFInfo
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- CN116395148A CN116395148A CN202310267538.8A CN202310267538A CN116395148A CN 116395148 A CN116395148 A CN 116395148A CN 202310267538 A CN202310267538 A CN 202310267538A CN 116395148 A CN116395148 A CN 116395148A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
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Abstract
The invention provides a satellite and rocket separation control system and a control method, wherein the control method responds to a trigger instruction for powering up a satellite, acquires sailboard state information corresponding to a solar sailboard, acquires satellite and rocket separation state information related to the satellite and acquires satellite and rocket separation switch state information corresponding to a satellite and rocket separation switch; determining satellite separation state information of a satellite according to the sailboard unfolding state information, the satellite separation state information and the separation switch state information, wherein the satellite separation state information is used for indicating the current satellite separation state, and the satellite separation state comprises the following steps: during testing, before separation, during separation, after separation; and carrying out corresponding satellite separation operation according to the determined satellite separation state information. Under the condition that the satellite triggers the power-on operation instruction at different time, the satellite can correctly perform corresponding processing, and the safety of a control system is improved.
Description
Technical Field
The invention relates to the technical field of satellites, in particular to a satellite and rocket separation control system and a satellite and rocket separation control method.
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.
However, for reasons such as program control, the satellite computer may receive instructions to power up the satellite at a different time. Therefore, if the power-up and the separation operation are performed at the wrong timing, bad results may occur, and the safety is poor.
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.
Disclosure of Invention
The invention provides a satellite and arrow separation control system and a satellite and arrow separation control method, which are used for enabling satellites to correctly perform corresponding processing under the condition of different trigger power-on operation instructions, and improving the safety of a control system.
In a first aspect, an embodiment of the present invention provides a satellite-rocket separation control system, including: 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 in place and is 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 control terminal connected to the sailboard detector, the rocket separation detector, and the rocket separation switch detector, respectively, the control terminal determining satellite separation state information of the satellite according to the solar sailboard's deployment state information, the rocket separation state information, and the separation switch state information, wherein the satellite separation state information is used for indicating a current satellite separation state, and wherein the satellite separation state comprises: during testing, before separation, during separation, and after separation.
In a second aspect, an embodiment of the present invention provides a satellite-rocket separation control method, including:
s302, responding to a triggering instruction for powering up a satellite, acquiring the state information of a sailboard corresponding to a solar sailboard, acquiring the state information of a satellite and an arrow separation switch corresponding to the satellite, and acquiring the state information of the satellite and the arrow separation switch corresponding to the arrow separation switch;
s304, determining satellite separation state information of a satellite according to the sailboard unfolding state information, the satellite separation state information and the separation switch state information, wherein the satellite separation state information is used for indicating the current satellite separation state, and the satellite separation state comprises: during testing, before separation, during separation, after separation;
s306, corresponding satellite separation operation is carried out according to the determined satellite separation state information.
The invention provides a satellite and arrow separation control system and a control method, wherein the control method comprises the following steps: responding to a triggering instruction for powering up the satellite, acquiring the state information of the solar sailboard, acquiring the satellite-rocket separation state information related to the satellite and acquiring the state information of the satellite-rocket separation switch corresponding to the satellite-rocket separation switch; determining satellite separation state information of a satellite according to the sailboard unfolding state information, the satellite separation state information and the separation switch state information, wherein the satellite separation state information is used for indicating the current satellite separation state, and the satellite separation state comprises the following steps: during testing, before separation, during separation, after separation; and carrying out corresponding satellite separation operation according to the determined satellite separation state information. Under the condition that the satellite triggers the power-on operation instruction at different time, the satellite can correctly perform corresponding processing, and the safety of a control system is improved.
It should be understood that the description in this summary is not intended to limit the critical or essential features of the embodiments of the invention, nor is it intended to limit the scope of the invention. Other features of the present invention will become apparent from the description that follows.
Drawings
The above and other features, advantages and aspects of embodiments of the present invention will become more apparent by reference to the following detailed description when taken in conjunction with the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements.
FIG. 1 shows a schematic diagram of a satellite-rocket separation control system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a satellite flight management program according to an embodiment of the present invention;
FIG. 3 shows a flow chart of a satellite-arrow separation control method according to an embodiment of the invention;
fig. 4 shows a flowchart of a satellite-rocket separation control method according to a preferred embodiment of the present invention.
In the figure: a star computer 101 (control terminal); a satellite and arrow separation detector 102; a satellite-rocket disconnecting switch 103; a satellite-rocket disconnecting switch detector 104; solar sailboards 105a and 105b; windsurfing detectors 106a and 106b; a battery 107; a battery discharge switch 108; a discharge control circuit 109.
Detailed Description
In order to enable a person skilled in the art to better understand the technical solutions in one or more embodiments of the present specification, the technical solutions in one or more embodiments of the present specification will be clearly and completely described below with reference to the drawings in one or more embodiments of the present specification, and it is obvious that the described embodiments are only some embodiments of the present specification, not all embodiments. All other embodiments, which can be made by one or more embodiments of the present disclosure without inventive faculty, are intended to be within the scope of the present disclosure.
It should be noted that, the description of the embodiment of the present invention is only for the purpose of more clearly describing the technical solution of the embodiment of the present invention, and does not constitute a limitation on the technical solution provided by the embodiment of the present invention.
Fig. 1 shows a schematic structural diagram of a satellite-rocket separation control system according to an embodiment of the present invention. Referring to fig. 1, the satellite-rocket separation control system of the present invention includes:
the array panel detector is used for acquiring the unfolding state information of the solar array panel, and the unfolding state information comprises: expanded into place and unexpanded into place. In this embodiment, there are two windsurfing detectors, a first windsurfing detector 106a and a second windsurfing detector 106b. Wherein the first windsurfing board detector 106a corresponds to the first solar windsurfing board 105a and the second windsurfing board detector 106b corresponds to the second solar windsurfing board 105 b.
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.
A satellite-rocket disconnecting switch detector 104 connected to the satellite-rocket disconnecting switch 103 for detecting disconnecting switch state information of the satellite-rocket disconnecting switch 103, the disconnecting switch state information including: closing and opening.
The star computer 101 (i.e., control terminal) is connected to the first sailboard detector 106a, the second sailboard detector 106b, the star separation detector 102, and the star separation switch detector 104, respectively. The satellite computer 101 determines satellite separation status information of the satellite based on the sailboard status information, the satellite separation status information, and the separation switch status information. The satellite separation status information is used to indicate the current satellite separation status. Wherein, the satellite separation state includes: during testing, before separation, during separation, and after separation.
Illustratively, the satellite computer 101 is connected to a satellite-rocket separation detector 102 for detecting whether the satellite is separated from the rocket by the satellite-rocket separation detector 102. The satellite-rocket separating switch 103 is used for controlling the unlocking and separating of the satellite and the rocket, and when the satellite-rocket separating switch 103 is closed, the unlocking and separating of the satellite and the rocket are started. The satellite-arrow-separation-switch detector 104 is connected to the satellite-arrow-separation switch 103, and detects a state (open or closed) of the satellite-arrow-separation switch 103. Further, the star computer 101 is connected to the star separation switch detector 104 for detecting the state of the star separation switch 103 by the star separation switch detector 104. The first windsurfing board detector 106a is connected with the corresponding first solar windsurfing board 105a, and is used for detecting the unfolding state (i.e. unfolded or not unfolded in place) of the first solar windsurfing board 105 a; the second windsurfing board detector 106b is connected to the corresponding second solar windsurfing board 105b for detecting the unfolded state (i.e. unfolded or not unfolded in place) of the second solar windsurfing board 105 b.
Illustratively, the first solar array 105a and the second solar array 105b are coupled to a primary bus bar for providing power to the satellites. The battery 107 is connected to the primary bus bar through a battery discharge switch 108 and a discharge control circuit 109. The star computer 101 is connected to a battery discharge switch 108 and a discharge control circuit 109, controls on and off of the battery discharge switch 108, and controls the discharge control circuit 109, thereby controlling discharge of the battery 107.
In addition, fig. 2 shows a schematic structural diagram of a satellite flight management program according to an embodiment of the present invention. Referring to fig. 2, the satellite flight management program executed by the satellite computer 101 includes: the device comprises a satellite and arrow state acquisition module, a separation state determination module, a power-on test module, a separation front program control module, a separation middle program control module and a separation rear program control module. The satellite and rocket state acquisition module is used for acquiring the unfolding state information of the solar sailboard through the sailboard detector. 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 power-on test module is capable of powering on the satellite when the satellite is in a state under test. When the satellite is in a state before separation, the program control module before separation can run an operation instruction before separation from the satellite. The in-separation process control module is capable of executing the operating instructions in separation from the satellite when the satellite is in a state of separation. When the satellite is in a separated state, the separated program control module can run an operation instruction separated from the satellite.
Optionally, the operation of the pre-separation programming module includes: closing a storage battery discharging switch; 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.
In embodiments of the invention, words such as "exemplary" or "such as" are used to mean serving as an example, instance, or illustration. Any embodiment or design described herein as "exemplary" or "e.g." in an embodiment should not be taken as preferred or advantageous over other embodiments or designs. Rather, the use of words such as "exemplary" or "such as" is intended to present related concepts in a concrete fashion.
Based on the system, a satellite-rocket separation control method for satellites is provided. Fig. 3 shows a flowchart of a satellite-rocket separation control method according to an embodiment of the present invention. Fig. 4 shows a flowchart of a satellite-rocket separation control method according to a preferred embodiment of the present invention. Referring to fig. 3 and 4, the method is performed by the star computer 101, and the method includes:
s302: and responding to a triggering instruction for powering up the satellite, acquiring the state information of the sailboard corresponding to the solar sailboard, acquiring the satellite-arrow separation state information related to the satellite and acquiring the state information of the satellite-arrow separation switch corresponding to the satellite-arrow separation switch.
Specifically, first, the satellite computer 101 enters a program for powering up the satellite in response to an instruction for powering up the satellite. Then, a star arrow state acquisition module operated by the star computer 101 acquires the sailboard state information corresponding to the first solar sailboard 105a through the first sailboard detector 106 a; the windsurfing board status information corresponding to the second solar windsurfing board 105b is acquired by means of the second windsurfing board detector 106b. Wherein the windsurfing status information is used to indicate the unfolded status of the first solar windsurfing board 105a and the second solar windsurfing board 105 b. And wherein the deployed state of the first and second solar panels 105a, 105b may be deployed in place or undeployed in place, for example.
Further, the star computer 101 acquires the star separation state information indicating the star separation state through the star separation detector 102. The satellite-rocket separation state includes separation and non-separation, for example.
Further, the star computer 101 detects the disconnection-switch state information of the star disconnection switch 103 by the star disconnection-switch detector 104. The disconnecting switch state information is used for indicating the state of the satellite-rocket disconnecting switch. And wherein separating the switch state information includes, for example, closing and opening.
S304: the satellite computer 101 determines satellite separation state information of the satellite according to the sailboard state information, the satellite separation state information and the separation switch state information, wherein the satellite separation state information is used for indicating the current satellite separation state, and the satellite separation state comprises: during testing, before separation, during separation, and after separation.
Specifically, the separation state determining module operated by the star computer 101 determines satellite separation state information of the satellite according to the obtained sailboard state information, the satellite separation state information and the separation switch state information. Wherein "under test" indicates 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.
Further preferably, step S304 may further include the steps of:
s3042: and accessing a preset separation state table, wherein the separation state table records the corresponding relations of different sailboard state information, satellite and rocket separation state information and separation switch state information and each satellite separation state information. Specifically, the following table 1 shows a separation state table:
TABLE 1
Wherein, the sailboard status information is "Y" indicating that at least one sailboard status is "unfolded in place", and "N" indicating that all sailboard status is "unfolded in place". The satellite-arrow separation state information is 'Y' which indicates that the satellites are separated at present, and the satellite-arrow separation state information is 'N' which indicates that the satellites are not separated yet. The disconnecting switch state information is "Y" indicating that the disconnecting switch state of the satellite-rocket disconnecting switch is closed, and "N" indicating that the disconnecting switch state of the satellite-rocket disconnecting switch is open.
And further referring to table 1, different windsurfing status information, satellite separation status information, and separation switch status information correspond to different satellite separation status information.
For example, when the windsurfing board state information is "Y", the satellite separation state information is "Y", and the separation switch state information is "Y", the satellite separation state information is "after separation". When the sailboard state information is 'Y', the satellite separation state information is 'Y', and the separation switch state information is 'N', the satellite separation state information is 'after separation'. And so on.
S3044: the satellite computer 101 determines satellite separation state information corresponding to the acquired sailboard state information, satellite separation state information, and separation switch state information in the separation state table according to the acquired sailboard state information, satellite separation state information, and separation switch state information.
S306: the satellite computer 101 performs a corresponding satellite separation operation based on the determined satellite separation status information.
Specifically, when the separation state determining module operated by the satellite service computer 101 determines that the satellite is in the state of "under test", the satellite is electrified by the electrification module operated. 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.
1) For example, when the windsurfing board status information and the satellite-rocket separation status information are both "Y", the satellite is in a "separated" state at this time, and if the "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 state information is "Y" and the satellite and rocket separation state information is "N", the satellite is in a test state at this time, so that the satellite-borne computer performs a power-on operation on the satellite through the power-on test module in response to the power-on instruction.
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 in a state that the sailboard is not unfolded in place, the satellite and the arrow are not separated, and the separation switch is closed, 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:
closing a storage battery discharging switch; and
continuously monitoring the satellite and arrow separation state information, and executing a separation program control program (namely a program called by a separation middle program control module) under the condition that the satellite and arrow separation state information is 'Y' (namely, the satellite and arrow is in a separation state).
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 a power-off abnormal state, so that the abnormal power-off recovery flow is invoked by the separation middle-range control module and recovered from the abnormal power-off state.
6) 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 "Y" at this time, the satellite computer 101 determines that the current satellite is in a separated state, so that the separation program is invoked by the separation middle program module:
wherein the separate programming procedure comprises the following operations: initially powering up the whole satellite; damping the whole satellite speed to stop the rotation of the satellite; powering up a motor module of the solar sailboard and unfolding the solar sailboard; after the solar sailboard is unfolded, finishing the sun-facing operation; and ending the program control separation program.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present invention. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The above description is only illustrative of the preferred embodiments of the present invention and of the principles of the technology employed. It will be appreciated by persons skilled in the art that the scope of the invention referred to in the present invention is not limited to the specific combinations of the technical features described above, but also covers other technical features formed by any combination of the technical features described above or their equivalents without departing from the inventive concept. Such as the above-mentioned features and the technical features disclosed in the present invention (but not limited to) having similar functions are replaced with each other.
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
the control terminal is respectively connected with the sailboard detector, the satellite and arrow separation detector and the satellite and arrow separation switch detector, and determines satellite separation state information of a satellite according to the unfolding state information, the satellite and arrow separation state information and the separation switch state information of the solar sailboard, wherein the satellite separation state information is used for indicating the current satellite separation state, and the satellite separation state comprises: during testing, before separation, during separation, and after separation.
2. The control system of claim 1, wherein the solar array is coupled to a primary bus for providing power to the satellite.
3. The control system of claim 2, wherein the control system further comprises:
the storage battery is connected with the primary bus through the storage battery discharging switch and the discharging control circuit, the control terminal is connected with the storage battery discharging switch and the discharging control circuit, and is configured to control the connection and disconnection of the storage battery discharging switch and the discharging control circuit, so that the discharging of the storage battery is controlled.
4. A control system according to claim 2 or 3, wherein the management program for controlling the operation of the terminal comprises:
the satellite and arrow state acquisition module acquires the unfolding state information of the solar sailboard through the sailboard detector;
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.
5. The control system of claim 4, wherein the pre-separation programming module is configured to:
closing the battery discharge 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.
6. The satellite and rocket separation control method is characterized by comprising the following steps of:
s302, responding to a triggering instruction for powering up a satellite, acquiring the state information of a sailboard corresponding to a solar sailboard, acquiring the satellite-rocket separation state information related to the satellite and acquiring the satellite-rocket separation switch state information corresponding to the satellite-rocket separation switch;
s304, determining satellite separation state information of the satellite according to the sailboard unfolding state information, the satellite and rocket separation state information and the separation switch state information, wherein the satellite separation state information is used for indicating the current satellite separation state, and the satellite separation state comprises: during testing, before separation, during separation, after separation;
s306, performing corresponding satellite separation operation according to the determined satellite separation state information.
7. The control method according to claim 6, characterized in that step S304 further comprises the steps of:
s3042: accessing a preset separation state table, wherein the separation state table records the corresponding relations of different sailboard state information, satellite and arrow separation state information and separation switch state information and the satellite separation state information;
s3044, determining satellite separation state information corresponding to the acquired sailboard state information, satellite separation state information and separation switch state information in the separation state table according to the acquired sailboard state information, satellite separation state information and separation switch state information.
8. The control method according to claim 6, wherein the management program for controlling the operation of the terminal includes:
the satellite and arrow state acquisition module acquires the unfolding state information of the solar sailboard through the sailboard detector;
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.
9. The control method according to claim 6, characterized by 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.
10. The control method according to claim 9, characterized by 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 after the solar sailboard is unfolded, finishing the sun-facing operation.
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Citations (18)
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