CN113815909B - Uplink determining method and device for peer-to-peer mode combination configuration spacecraft - Google Patents
Uplink determining method and device for peer-to-peer mode combination configuration spacecraft Download PDFInfo
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Abstract
The embodiment of the application provides an uplink determining method and device of a peer-to-peer mode combination configuration spacecraft, wherein the method comprises the following steps: determining a measurement and control arc section corresponding to each component part of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecast of the spacecraft and measurement and control antenna installation parameters of the spacecraft; determining an instruction uploading mode of an uplink remote control instruction corresponding to each component part of the spacecraft according to the measurement and control arc section corresponding to each component part of the spacecraft, so that the ground measurement and control equipment and the spacecraft component parts in the measurement and control arc section establish a communication link and send the uplink remote control instruction to each component part of the spacecraft through the determined instruction uploading mode; the method and the device can automatically and accurately determine the uplink of the peer-to-peer mode combination configuration spacecraft.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to an uplink determining method and device of a peer-to-peer mode combination configuration spacecraft.
Background
The peer-to-peer mode combined configuration spacecraft consists of more than two spacecrafts with complete and independent measurement and control functions. Taking an example of a combined spacecraft (hereinafter referred to as a combined spacecraft) formed by two spacecrafts, the two spacecrafts are respectively a spacecraft A and a spacecraft B (hereinafter referred to as A, B), the overall configuration is shown in fig. 8, and the mechanical coordinate system relationship of the two spacecrafts is shown in fig. 9.
The measurement and control antenna of A faces the-X axis direction, and the measurement and control antenna of B faces the +X axis direction.
In the assembled state, part of the view field of the measurement and control antenna of A, B is respectively blocked by the other side. Therefore, the combination adopts a A, B two-device combined measurement and control method, namely, the measurement and control antenna of A is responsible for the measurement and control communication of the lower celestial sphere, the measurement and control antenna of B is responsible for the measurement and control communication of the upper celestial sphere, A, B is used for carrying out independent measurement and control in a time-sharing manner, and the field of view of the measurement and control antenna is not blocked in the space parts of the A and the B respectively.
According to the analysis result of the antenna view field under the state of the combination, a A, B two-device combined measurement and control method is implemented, namely A, B two-device respective measurement and control antennas are respectively responsible for measurement and control communication of the upper and lower celestial spheres. At the same time, only one antenna of the two devices can point to the earth, the ground needs to judge which spacecraft can be tracked by the ground measurement and control equipment according to the situation that the measurement and control antenna of the spacecraft points to the earth, A or B is selected for uplink remote control, the antenna is opposite to the other side of the earth, remote control instructions sent by the ground cannot be directly received, and the two devices need to mutually replace each other instructions.
If the antenna of A points to the earth, the ground measurement and control equipment can track A, after double-capturing is completed, a stable uplink communication link is established, the ground measurement and control equipment can directly send a remote control instruction to A, and because B is shielded by A, the communication link cannot be established with the ground, and the instruction sent by the ground measurement and control equipment cannot be directly received, in this case, the instruction of B can be sent to A, and the instruction of B is sent to B by the A generation.
On the contrary, if the antenna of the B points to the earth, the ground measurement and control equipment can track the B, after double-capturing is completed, a stable uplink communication link is established, the ground measurement and control equipment can directly send a remote control instruction to the B, and because the A is shielded by the B, the communication link cannot be established with the ground, and the instruction sent by the ground measurement and control equipment cannot be directly received, in this case, the instruction of the A can be sent to the B, and the instruction of the A is sent to the A by the B.
To date, spacecraft and composite spacecraft that have been terminated, or remain in-orbit, have mainly 3 configurations:
(1) Monomer configuration. During the on-orbit operation of the spacecraft, the attitude of the spacecraft can be controlled, the steering of the antenna can be adjusted, the antenna is always directed to the earth, the space-earth link communication can be carried out as long as the spacecraft operates above the ground measurement and control equipment, a communication link is established, and the ground measurement and control equipment is used for remotely controlling the spacecraft.
(2) The monomer emission is in an on-orbit combination configuration. The spacecraft is a single spacecraft with a single configuration in the launching and orbit entering stage and the initial operation stage, after a period of operation, two or more single spacecraft are intersected and butted to form a combined body, the antennas of each component part of the combined body are all arranged on the same side face, the mounting faces of the antennas are the same, the antenna of each component part can be ensured to simultaneously point to the earth by controlling the posture of the combined body and adjusting the steering of the antennas in the operation process, the communication link can be established as long as the combined body is operated above ground measurement and control equipment, and the ground measurement and control equipment can independently remotely control each component part.
(3) A master-slave mode configuration. The spacecraft is formed by combining a plurality of spacecrafts in the launching and orbit entering stage, however, in the combined body stage before separation, only the measurement and control equipment of the main device is started, the antenna of the main device always points to the earth by controlling the posture of the main device and adjusting the steering of the antenna, a communication link is established, the measurement and control equipment of other components is not started before separation, the communication link established by the ground measurement and control equipment is not independent, the control is carried out by virtue of a main device substitution transmission instruction, and after the combined body is separated, each component independently flies to become an on-orbit running single spacecraft, and the measurement and the control are respectively independent.
Based on the facts, the existing 3 configurations (a single configuration, a single emission on-orbit combined configuration and a master-slave mode configuration) can always keep the antenna to point to the earth by controlling the posture of the spacecraft and adjusting the steering of the antenna, so that the running orbit of each spacecraft is required to be subjected to forecast calculation to obtain an accurate measurement and control arc section of each spacecraft, and the measurement and control arc section of each spacecraft is not influenced by other spacecraft, so that the method can be completely used for providing measurement and control services for the spacecraft.
The peer-to-peer mode configuration composite spacecraft is one composite spacecraft that differs from the above 3 configurations. Because each component of the peer-to-peer mode configuration combined spacecraft is a spacecraft with complete and independent measurement and control functions, the measurement and control equipment of each component is started in the whole process from the beginning of launching and orbit entering until the separation, and is required to be independently measured and controlled, and further the running orbit of each component is required to be respectively subjected to forecast calculation, so that the accurate measurement and control arc section of each component is obtained.
Meanwhile, because the antenna directions of the components are different, the antenna of each component cannot be ensured to be simultaneously directed to the earth in the period from the operation to the overhead of the ground measurement and control equipment, and therefore, each component cannot be measured and controlled simultaneously.
Under the condition, firstly, the uplink of the ground measurement and control equipment is required to be judged manually, and then corresponding direct transmission or waiting transmission instructions are arranged according to the uplink, so that the time-division measurement and control of each component part of the combined body is realized.
The inventor finds that the preconditions for realizing the prior art scheme are three: firstly, the antenna of the spacecraft can always point to the earth; secondly, forecasting calculation is carried out on the measurement and control arc segments of each independent spacecraft respectively; thirdly, whether a certain spacecraft can be measured and controlled is judged manually, and instructions of replacing other spacecraft by the spacecraft are required to be designated manually under the condition that the spacecraft can be measured and controlled. Therefore, the technical solutions in the prior art have at least the following drawbacks:
(1) When the combined body is used as an integral target for carrying out measurement and control arc segment forecast calculation, the measurement and control arc segments of all the component parts cannot be accurately defined.
(2) If the accurate measurement and control arc segment of each component is to be obtained, the measurement and control arc segment forecast is calculated once for each component, and the calculated amount is large.
(3) When the flight control instruction is arranged, an operator is required to analyze measurement and control arc segment forecast in advance, and a substitute transmission link is manually designated: when the command is in the measurement and control arc section range of the A device, the command of the A device is directly transmitted by the link of the A device, and the command of the B device is transmitted by the link of the A device instead.
When the command is in the measurement and control arc section range of the B device, the command of the appointed B device is directly transmitted by the link of the B device, and the command of the A device is transmitted by the link of the B device instead.
(4) A, B two devices establish a substitution transmission channel through a data bus, and under the condition of substitution transmission instruction, specific substitution transmission channels are manually designated according to the substitution transmission instruction type.
Disclosure of Invention
Aiming at the problems in the prior art, the application provides a method and a device for determining the uplink of a peer-to-peer mode combination configuration spacecraft, which can automatically and accurately determine the uplink of the peer-to-peer mode combination configuration spacecraft.
In order to solve at least one of the problems, the application provides the following technical scheme:
in a first aspect, the present application provides a method for determining an uplink of a peer-to-peer mode combination configuration spacecraft, including:
determining a measurement and control arc section corresponding to each component part of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecast of the spacecraft and measurement and control antenna installation parameters of the spacecraft;
determining an instruction uploading mode of an uplink remote control instruction corresponding to each component part of the spacecraft according to the measurement and control arc section corresponding to each component part of the spacecraft, so that the ground measurement and control equipment and the component parts of the spacecraft in the measurement and control arc section establish a communication link and send the uplink remote control instruction to each component part of the spacecraft through the determined instruction uploading mode.
Further, the determining the measurement and control arc segment corresponding to each component of the spacecraft according to the time period information, the alpha angle information and the measurement and control antenna installation parameters of the spacecraft in the measurement and control arc segment forecast of the spacecraft comprises:
according to time period information in measurement and control arc segment forecast of a spacecraft and measurement and control antenna installation parameters of the spacecraft, determining an alpha angle numerical range when each component of the spacecraft is visible to the ground;
and judging whether the alpha angle information is in the alpha angle numerical range, and if so, judging that the corresponding spacecraft component is in a measurement and control arc section.
Further, determining an instruction uploading mode of an uplink remote control instruction corresponding to each component of the spacecraft by using the ground measurement and control equipment according to the measurement and control arc segments corresponding to each component of the spacecraft, including:
if the spacecraft component part is in the measurement and control arc section, the ground measurement and control equipment and the uplink remote control instruction of the spacecraft component part are transmitted in a direct transmission mode;
and if the spacecraft component is not in the measurement and control arc section, transmitting the uplink remote control command of the ground measurement and control equipment and the spacecraft component in a transmission substitution mode.
Further, the ground measurement and control device and the uplink remote control command of the spacecraft component part are transmitted in a transmission-substituted mode, and the method further comprises the following steps:
and determining a corresponding transmission channel when adopting a transmission mode for transmission according to the instruction type of the uplink remote control instruction.
In a second aspect, the present application provides an uplink determining apparatus of a peer-to-peer mode combination configuration spacecraft, including:
the measurement and control arc segment determining module is used for determining measurement and control arc segments corresponding to all components of the spacecraft according to time period information, alpha angle information and measurement and control antenna installation parameters of the spacecraft in measurement and control arc segment forecast of the spacecraft;
the uploading mode determining module is used for determining an instruction uploading mode of an uplink remote control instruction corresponding to each component part of the spacecraft according to the measurement and control arc section corresponding to each component part of the spacecraft, so that the ground measurement and control equipment and the spacecraft component parts in the measurement and control arc section establish a communication link and send the uplink remote control instruction to each component part of the spacecraft through the determined instruction uploading mode.
Further, the measurement and control arc segment determining module includes:
the alpha angle numerical range determining unit is used for determining the alpha angle numerical range when each component part of the spacecraft is visible to the ground according to the time period information in the measurement and control arc section forecast of the spacecraft and the measurement and control antenna installation parameters of the spacecraft;
And the visible state determining unit is used for judging whether the alpha angle information is in the alpha angle numerical range, and if so, judging that the corresponding spacecraft component is in the measurement and control arc section.
Further, the uploading mode determining module includes:
the direct transmission mode transmission unit is used for transmitting the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component part in a direct transmission mode if the spacecraft component part is in the measurement and control arc section;
and the transmission unit of a transmission substitution mode is used for transmitting the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component part by the transmission substitution mode if the spacecraft component part is not in the measurement and control arc section.
Further, the transmission-substitution transmission unit further includes:
and the transmission channel determination subunit is used for determining a corresponding transmission channel when adopting a transmission mode for transmission according to the instruction type of the uplink remote control instruction.
In a third aspect, the present application provides an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the steps of the method for determining the uplink of a peer-to-peer mode combination configuration spacecraft when executing the program.
In a fourth aspect, the present application provides a computer readable storage medium having stored thereon a computer program which when executed by a processor implements the steps of the method for determining an uplink of a peer mode combination configuration spacecraft.
According to the technical scheme, the method and the device for determining the uplink of the peer-to-peer mode combined configuration spacecraft are provided, under the condition that the peer-to-peer mode combined configuration spacecraft is used as an integral target for measurement and control arc segment forecast calculation, the measurement and control arc segment of each component of the spacecraft is accurately defined according to the time period information, the alpha angle information and the measurement and control antenna installation parameters of the spacecraft in the measurement and control arc segment forecast, and then a communication link, a direct transmission/substitution transmission mode of an explicit instruction and a specific substitution transmission channel are automatically determined, and the uplink of the peer-to-peer mode combined configuration spacecraft can be automatically and accurately determined.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is one of the flow diagrams of a method for determining an uplink of a peer-to-peer mode combination configuration spacecraft in an embodiment of the application;
FIG. 2 is a second flow chart of a method for determining an uplink of a peer-to-peer mode combination configuration spacecraft in an embodiment of the application;
FIG. 3 is a third flow chart of a method for determining an uplink of a peer-to-peer mode combination configuration spacecraft in an embodiment of the application;
FIG. 4 is one of the block diagrams of the uplink determining apparatus of the peer-to-peer mode combination configuration spacecraft in an embodiment of the application;
FIG. 5 is a second block diagram of an uplink determination device of a peer-to-peer mode combination configuration spacecraft in an embodiment of the application;
FIG. 6 is a third block diagram of an uplink determination device of a peer-to-peer mode combination configuration spacecraft in an embodiment of the application;
FIG. 7 is a fourth block diagram of an uplink determination device of a peer-to-peer mode combination configuration spacecraft in an embodiment of the application;
FIG. 8 is a schematic block diagram of a spacecraft of a modular configuration in accordance with an embodiment of the present application;
FIG. 9 is a schematic diagram showing the mechanical coordinate system relationship of the combination and each device according to an embodiment of the present application;
fig. 10 is a schematic view of antenna pointing when the angle α is less than 90 ° in an embodiment of the present application;
FIG. 11 is a schematic view of the antenna pointing direction when the angle α is greater than 90 ° in an embodiment of the present application;
fig. 12 is a schematic structural diagram of an electronic device according to an embodiment of the present application.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In consideration of the problems in the prior art, the application provides a method and a device for determining the uplink of a peer-to-peer mode combination configuration spacecraft, which accurately define the measurement and control arc segments of each component of the spacecraft according to the time period information, the alpha angle information and the measurement and control antenna installation parameters of the spacecraft in the measurement and control arc segment forecast under the condition that the peer-to-peer mode combination configuration spacecraft is used as an integral target for measurement and control arc segment forecast calculation, so as to automatically determine a communication link, a direct transmission/substitution transmission mode of an explicit instruction and a specific substitution transmission channel under the condition of substitution transmission instructions, thereby being capable of automatically and accurately determining the uplink of the peer-to-peer mode combination configuration spacecraft.
In order to automatically and accurately determine the uplink of the peer mode combination configuration spacecraft, the application provides an embodiment of an uplink determination method of the peer mode combination configuration spacecraft, referring to fig. 1, the uplink determination method of the peer mode combination configuration spacecraft specifically comprises the following contents:
step S101: and determining the measurement and control arc segments corresponding to each component part of the spacecraft according to the time period information and alpha angle information in the measurement and control arc segment forecast of the spacecraft and the measurement and control antenna installation parameters of the spacecraft.
It can be understood that the measurement and control arc section refers to a time range in which the ground measurement and control equipment can observe the spacecraft when the spacecraft flies in orbit. In the measurement and control arc section range, an antenna terminal arranged on the spacecraft points to ground measurement and control equipment, and the ground can receive telemetry data downloaded by the spacecraft; after the double-capturing is completed, the ground can send a remote control instruction to the spacecraft and annotate flight parameters, so that measurement and control are carried out on the spacecraft.
It can be understood that the alpha angle refers to that the mechanical coordinate system of the spacecraft and the X-axis point to be one ray, and the other ray points to the ground measurement and control equipment from the spacecraft, and the included angle between the two rays is called alpha angle.
Alternatively, referring to fig. 10, the +x axis of the combination (i.e., the peer-to-peer mode combination configuration spacecraft) of the present application is oriented toward the earth, and the α angle is less than 90 °, i.e., the antenna of B is oriented toward the earth, and both devices use B as the uplink.
Alternatively, referring to fig. 11, in the present application, the-X axis of the assembly (i.e., the peer-to-peer mode assembly configuration spacecraft) is oriented towards the earth, and the α angle is greater than 90 °, i.e., the antenna of a is oriented towards the earth, and both devices use a as the uplink.
Therefore, the application can select the uplink of the ground measurement and control equipment according to the value of the alpha angle.
Specifically, the application can accurately define the measurement and control arc segments of each component according to the time period information and alpha angle information in the measurement and control arc segment forecast and the installation parameters of the measurement and control antenna of the spacecraft.
Step S102: determining an instruction uploading mode of an uplink remote control instruction corresponding to each component part of the spacecraft according to the measurement and control arc section corresponding to each component part of the spacecraft, so that the ground measurement and control equipment and the component parts of the spacecraft in the measurement and control arc section establish a communication link and send the uplink remote control instruction to each component part of the spacecraft through the determined instruction uploading mode.
Optionally, after the measurement and control arc segments of all the components of the spacecraft are accurately defined, the ground measurement and control equipment can establish a communication link with the spacecraft with the measurement and control arc segments and send an uplink remote control instruction through the communication link.
Optionally, in the application, if the instruction is sent to the chain-building spacecraft, the instruction sending mode is direct transmission; if the command is sent to another spacecraft (no measurement and control arc section, no chain is built), the command sending mode is substitution transmission.
Optionally, under the condition that the instruction is judged to adopt the substitution transmission mode, a specific substitution transmission channel is determined by judging the instruction type.
As can be seen from the above description, in the uplink determining method of the peer-to-peer mode combination configuration spacecraft provided by the embodiment of the application, under the condition that the peer-to-peer mode combination configuration spacecraft is used as an overall target to perform measurement and control arc segment prediction calculation, the measurement and control arc segment of each component part of the spacecraft is accurately defined according to the time period information, the alpha angle information and the measurement and control antenna installation parameters of the spacecraft in the measurement and control arc segment prediction, so that a communication link, a direct transmission/substitution transmission mode of a specific instruction and a specific substitution transmission channel are automatically determined, and the uplink of the peer-to-peer mode combination configuration spacecraft can be automatically and accurately determined.
In order to accurately define the measurement and control arc segments of the components of the combined configuration spacecraft, in an embodiment of the method for determining the uplink of the peer-to-peer mode combined configuration spacecraft according to the application, referring to fig. 2, the step S101 may further specifically include the following:
step S201: and determining an alpha angle numerical range when each component of the spacecraft is visible to the ground according to the time period information in the measurement and control arc section forecast of the spacecraft and the measurement and control antenna installation parameters of the spacecraft.
Step S202: and judging whether the alpha angle information is in the alpha angle numerical range, and if so, judging that the corresponding spacecraft component is in a measurement and control arc section.
In a specific embodiment of the application, the measurement and control arc segments of each component can be accurately defined according to the time period information, the alpha angle information and the spacecraft measurement and control antenna installation parameters in the measurement and control arc segment forecast.
Specifically, the measurement and control arc segment is predicted as y= (Y) 1 ,Y 2 ,…,Y i ,…,Y n ) Wherein Y is i ＝(t i ,α i ) Represents t i Time assemblyVisible to the ground, and the alpha angle value of the combination at this moment is alpha i ,i＝1,2,…,n。
The spacecraft measurement and control antenna installation parameter is marked as A= (A) 1 ,A 2 ,…,A j ,…,A m ) Wherein, the method comprises the steps of, wherein, represents the antenna installation parameters for the j-th spacecraft, j=1, 2, …, m. / >Indicating the range that the value of the angle alpha of the combination should satisfy when the spacecraft is visible to the ground, i.e. if the value of the angle alpha of the combination satisfies +.>Then t i At moment, the j-th spacecraft in the assembly is visible to the ground, and the ground measurement and control equipment can measure and control the j-th spacecraft and send an uplink remote control instruction to the j-th spacecraft.
Recording TB j ＝Min(t i ) Representing the starting time of a measurement and control arc section of the spacecraft; TE (TE) j ＝Max(t i ) Representing the end time of the measurement and control arc section of the spacecraft.
Note i= (I) 1 ,I 2 ,…,I j ,…,I m ) Wherein I j ＝(Q j ,TB j ,TE j ) Represents the measurement and control arc section of the jth spacecraft, j=1, 2, …, m. Q (Q) j Represents the jth spacecraft, TB j ,TE j The meaning of (2) is as described above.
After the measurement and control arc segments of the components are accurately defined, the ground measurement and control equipment can establish a communication link with the spacecraft with the measurement and control arc segments and send an uplink remote control instruction through the communication link.
In order to accurately determine the instruction uploading manner of the uplink remote control instruction, in an embodiment of the method for determining the uplink of the peer-to-peer mode combination configuration spacecraft according to the present application, referring to fig. 3, the step S102 may further specifically include the following:
step S301: and if the spacecraft component part is in the measurement and control arc section, transmitting the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component part in a direct transmission mode.
Step S302: and if the spacecraft component is not in the measurement and control arc section, transmitting the uplink remote control command of the ground measurement and control equipment and the spacecraft component in a transmission substitution mode.
It can be understood that the direct transmission means that after the ground measurement and control equipment establishes a communication link with the spacecraft, an instruction is directly sent to the spacecraft.
It can be understood that the transmission-substitution refers to that when one set of ground measurement and control equipment performs measurement and control on two spacecrafts and can only establish a communication link with one of the spacecrafts, after the ground measurement and control equipment establishes the communication link with one of the spacecrafts, an instruction is sent to the link of the spacecraft, and the instruction is forwarded to the other spacecraft by the spacecraft.
In one embodiment of the present application, the notation c= (C 1 ,C 2 ,…,C k ,…,C p ) Wherein C k ＝(Q j ,TYPE l ,TIME k ) The attribute representing the kth instruction, namely: the j-th spacecraft is of TYPE TYPE l TIME is TIME k K=1, 2, …, p. Wherein Q is j Is as defined above for TYPE l Indicating instruction type, l=1, 2; TIME (TIME) k Indicating the instruction time.
For any instructionj 1 =1, 2, …, m, and +.>j 2 =1, 2, …, m, comparison condition, determine instruction upload mode:
when j is 1 ＝j 2 And (2) and When the command is in the measurement and control arc section of the spacecraft, adopting a direct transmission mode;
when j is 1 ≠j 2 And (2) andwhen the command is in the measurement and control arc section of other spacecrafts, adopting a substitution transmission mode.
In order to accurately determine the transmission path when the transmission is performed by the transmission-by-transmission method, in an embodiment of the method for determining the uplink of the peer-to-peer mode combination configuration spacecraft of the present application, the step S302 may further specifically include the following:
and determining a corresponding transmission channel when adopting a transmission mode for transmission according to the instruction type of the uplink remote control instruction.
In one embodiment of the present application, command C is transmitted in a substitute way to any one k ＝(Q j ,TYPE l ,TIME k ) J=1, 2, …, m, determine its instruction type:
when TYPE is l When=1, 1 generation transmission is performed through the data bus;
when TYPE is l When=2, transfer is performed through the data bus for 2 generations.
As can be seen from the above, the present application can achieve at least the following technical effects:
(1) The uplink determining method of the peer-to-peer mode combined configuration spacecraft reduces the calculation times of measurement and control arc segment forecast, realizes that the result of calculating the measurement and control arc segment once can be applied to measurement and control of a plurality of spacecrafts.
(2) The uplink determining method of the peer-to-peer mode combination configuration spacecraft provided by the application realizes an automatic determining instruction uploading mode and replaces a manual comparing mode.
(3) The uplink determining method of the peer-to-peer mode combination configuration spacecraft provided by the application realizes that the command transmission channel is automatically determined instead of a manual assignment mode.
In order to be able to automatically and accurately determine the uplink of the peer mode combining configuration spacecraft, the application provides an embodiment of an uplink determining device of the peer mode combining configuration spacecraft for realizing all or part of the content of the uplink determining method of the peer mode combining configuration spacecraft, and referring to fig. 4, the uplink determining device of the peer mode combining configuration spacecraft specifically comprises the following contents:
the measurement and control arc segment determining module 10 is configured to determine a measurement and control arc segment corresponding to each component of the spacecraft according to time period information, alpha angle information and measurement and control antenna installation parameters of the spacecraft in measurement and control arc segment prediction of the spacecraft.
The uploading mode determining module 20 is configured to determine, according to the measurement and control arc segments corresponding to each component of the spacecraft, an instruction uploading mode of an uplink remote control instruction corresponding to each component of the spacecraft, so that the ground measurement and control equipment and the component of the spacecraft in the measurement and control arc segments establish a communication link and send the uplink remote control instruction to each component of the spacecraft through the determined instruction uploading mode.
As can be seen from the above description, the uplink determining device for the peer-to-peer mode combination configuration spacecraft provided by the embodiment of the application can accurately define the measurement and control arc segments of each component of the spacecraft according to the time period information, the alpha angle information and the measurement and control antenna installation parameters of the spacecraft in the measurement and control arc segment forecast under the condition that the peer-to-peer mode combination configuration spacecraft is used as an overall target for measurement and control arc segment forecast calculation, so as to automatically determine a communication link, a direct transmission/substitution transmission mode of a specific instruction and what specific substitution transmission channel is used under the condition of substitution transmission instruction, thereby being capable of automatically and accurately determining the uplink of the peer-to-peer mode combination configuration spacecraft.
In order to accurately define the measurement and control arc segments of the components of the combined configuration spacecraft, in one embodiment of the uplink determining device of the peer-to-peer mode combined configuration spacecraft of the application, referring to fig. 5, the measurement and control arc segment determining module 10 comprises:
the alpha angle numerical range determining unit 11 is used for determining the alpha angle numerical range when each component of the spacecraft is visible to the ground according to the time period information in the measurement and control arc section forecast of the spacecraft and the measurement and control antenna installation parameters of the spacecraft.
And the visible state determining unit 12 is used for judging whether the alpha angle information is in the alpha angle numerical range, and if so, judging that the corresponding spacecraft component part is in the measurement and control arc section.
In order to accurately determine the instruction upload manner of the uplink remote control instruction, in an embodiment of the uplink determining apparatus of the peer-to-peer mode combination configuration spacecraft of the present application, referring to fig. 6, the upload manner determining module 20 includes:
and the direct transmission mode transmission unit 21 is used for transmitting the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component part in a direct transmission mode if the spacecraft component part is in the measurement and control arc section.
And the transmission unit 22 is used for transmitting the uplink remote control command of the ground measurement and control equipment and the spacecraft component part in a transmission mode if the spacecraft component part is not in the measurement and control arc section.
In order to accurately determine the transmission path when the transmission is performed by the transmission-by-transmission method, in an embodiment of the uplink determining device of the peer-to-peer mode combination configuration spacecraft of the present application, referring to fig. 7, the transmission-by-transmission method transmission unit 22 further includes:
and the transmission-substitution channel determining subunit 221 is configured to determine, according to the instruction type of the uplink remote control instruction, a transmission-substitution channel corresponding to the transmission-substitution mode.
In order to automatically and accurately determine the uplink of the peer mode combination configuration spacecraft from the aspect of hardware, the application provides an embodiment of an electronic device for realizing all or part of the content in the uplink determination method of the peer mode combination configuration spacecraft, wherein the electronic device specifically comprises the following contents:
a processor (processor), a memory (memory), a communication interface (Communications Interface), and a bus; the processor, the memory and the communication interface complete communication with each other through the bus; the communication interface is used for realizing information transmission between an uplink determining device of the peer-to-peer mode combination configuration spacecraft and relevant equipment such as a core service system, a user terminal and a relevant database; the logic controller may be a desktop computer, a tablet computer, a mobile terminal, etc., and the embodiment is not limited thereto. In this embodiment, the logic controller may be implemented with reference to an embodiment of the method for determining an uplink of the peer mode combination configuration spacecraft and an embodiment of the uplink determining device of the peer mode combination configuration spacecraft in the embodiment, and the contents thereof are incorporated herein, and are not repeated here.
It is understood that the user terminal may include a smart phone, a tablet electronic device, a network set top box, a portable computer, a desktop computer, a Personal Digital Assistant (PDA), a vehicle-mounted device, a smart wearable device, etc. Wherein, intelligent wearing equipment can include intelligent glasses, intelligent wrist-watch, intelligent bracelet etc..
In practical application, part of the uplink determining method of the peer-to-peer mode combination configuration spacecraft may be performed on the electronic device side as described above, or all operations may be performed in the client device. Specifically, the selection may be made according to the processing capability of the client device, and restrictions of the use scenario of the user. The application is not limited in this regard. If all operations are performed in the client device, the client device may further include a processor.
The client device may have a communication module (i.e. a communication unit) and may be connected to a remote server in a communication manner, so as to implement data transmission with the server. The server may include a server on the side of the task scheduling center, and in other implementations may include a server of an intermediate platform, such as a server of a third party server platform having a communication link with the task scheduling center server. The server may include a single computer device, a server cluster formed by a plurality of servers, or a server structure of a distributed device.
Fig. 12 is a schematic block diagram of a system configuration of an electronic device 9600 according to an embodiment of the present application. As shown in fig. 12, the electronic device 9600 may include a central processor 9100 and a memory 9140; the memory 9140 is coupled to the central processor 9100. Notably, this fig. 12 is exemplary; other types of structures may also be used in addition to or in place of the structures to implement telecommunications functions or other functions.
In an embodiment, the uplink determination method functionality of the peer mode combination configuration spacecraft may be integrated into the central processor 9100. The central processor 9100 may be configured to perform the following control:
step S101: and determining the measurement and control arc segments corresponding to each component part of the spacecraft according to the time period information and alpha angle information in the measurement and control arc segment forecast of the spacecraft and the measurement and control antenna installation parameters of the spacecraft.
Step S102: determining an instruction uploading mode of an uplink remote control instruction corresponding to each component part of the spacecraft according to the measurement and control arc section corresponding to each component part of the spacecraft, so that the ground measurement and control equipment and the component parts of the spacecraft in the measurement and control arc section establish a communication link and send the uplink remote control instruction to each component part of the spacecraft through the determined instruction uploading mode.
As can be seen from the above description, in the electronic device provided by the embodiment of the present application, when the peer-to-peer mode combination configuration spacecraft is used as an overall target to perform measurement and control arc segment prediction calculation, the measurement and control arc segments of each component of the spacecraft are accurately defined according to the period information, the α -angle information and the measurement and control antenna installation parameters of the spacecraft in the measurement and control arc segment prediction, so that the communication link, the direct transmission/substitution transmission mode of the specific instruction and what specific substitution transmission channel is used in the case of substitution transmission instruction are automatically determined, and therefore, the uplink of the peer-to-peer mode combination configuration spacecraft can be automatically and accurately determined.
In another embodiment, the uplink determining device of the peer mode combining configuration spacecraft may be configured separately from the central processor 9100, for example, the uplink determining device of the peer mode combining configuration spacecraft may be configured as a chip connected to the central processor 9100, and the uplink determining method function of the peer mode combining configuration spacecraft is implemented by the control of the central processor.
As shown in fig. 12, the electronic device 9600 may further include: a communication module 9110, an input unit 9120, an audio processor 9130, a display 9160, and a power supply 9170. It is noted that the electronic device 9600 need not include all of the components shown in fig. 12; in addition, the electronic device 9600 may further include components not shown in fig. 12, and reference may be made to the related art.
As shown in fig. 12, the central processor 9100, sometimes referred to as a controller or operational control, may include a microprocessor or other processor device and/or logic device, which central processor 9100 receives inputs and controls the operation of the various components of the electronic device 9600.
The memory 9140 may be, for example, one or more of a buffer, a flash memory, a hard drive, a removable media, a volatile memory, a non-volatile memory, or other suitable device. The information about failure may be stored, and a program for executing the information may be stored. And the central processor 9100 can execute the program stored in the memory 9140 to realize information storage or processing, and the like.
The input unit 9120 provides input to the central processor 9100. The input unit 9120 is, for example, a key or a touch input device. The power supply 9170 is used to provide power to the electronic device 9600. The display 9160 is used for displaying display objects such as images and characters. The display may be, for example, but not limited to, an LCD display.
The memory 9140 may be a solid state memory such as Read Only Memory (ROM), random Access Memory (RAM), SIM card, etc. But also a memory which holds information even when powered down, can be selectively erased and provided with further data, an example of which is sometimes referred to as EPROM or the like. The memory 9140 may also be some other type of device. The memory 9140 includes a buffer memory 9141 (sometimes referred to as a buffer). The memory 9140 may include an application/function storage portion 9142, the application/function storage portion 9142 storing application programs and function programs or a flow for executing operations of the electronic device 9600 by the central processor 9100.
The memory 9140 may also include a data store 9143, the data store 9143 for storing data, such as contacts, digital data, pictures, sounds, and/or any other data used by an electronic device. The driver storage portion 9144 of the memory 9140 may include various drivers of the electronic device for communication functions and/or for performing other functions of the electronic device (e.g., messaging applications, address book applications, etc.).
The communication module 9110 is a transmitter/receiver 9110 that transmits and receives signals via an antenna 9111. A communication module (transmitter/receiver) 9110 is coupled to the central processor 9100 to provide input signals and receive output signals, as in the case of conventional mobile communication terminals.
Based on different communication technologies, a plurality of communication modules 9110, such as a cellular network module, a bluetooth module, and/or a wireless local area network module, etc., may be provided in the same electronic device. The communication module (transmitter/receiver) 9110 is also coupled to a speaker 9131 and a microphone 9132 via an audio processor 9130 to provide audio output via the speaker 9131 and to receive audio input from the microphone 9132 to implement usual telecommunications functions. The audio processor 9130 can include any suitable buffers, decoders, amplifiers and so forth. In addition, the audio processor 9130 is also coupled to the central processor 9100 so that sound can be recorded locally through the microphone 9132 and sound stored locally can be played through the speaker 9131.
The embodiment of the present application further provides a computer readable storage medium capable of implementing all the steps in the uplink determination method of the peer mode combination configuration spacecraft in which the execution subject is a server or a client, and the computer readable storage medium stores thereon a computer program, which when executed by a processor implements all the steps in the uplink determination method of the peer mode combination configuration spacecraft in which the execution subject is a server or a client, for example, the processor implements the following steps when executing the computer program:
step S101: and determining the measurement and control arc segments corresponding to each component part of the spacecraft according to the time period information and alpha angle information in the measurement and control arc segment forecast of the spacecraft and the measurement and control antenna installation parameters of the spacecraft.
Step S102: determining an instruction uploading mode of an uplink remote control instruction corresponding to each component part of the spacecraft according to the measurement and control arc section corresponding to each component part of the spacecraft, so that the ground measurement and control equipment and the component parts of the spacecraft in the measurement and control arc section establish a communication link and send the uplink remote control instruction to each component part of the spacecraft through the determined instruction uploading mode.
As can be seen from the above description, in the case of performing measurement and control arc segment prediction calculation by using the peer-to-peer mode combination configuration spacecraft as an overall target, the computer readable storage medium provided by the embodiment of the application accurately defines the measurement and control arc segment of each component of the spacecraft according to the time period information, the α -angle information and the measurement and control antenna installation parameters of the spacecraft in the measurement and control arc segment prediction, so as to automatically determine the communication link, the direct transmission/substitution transmission mode of the specific instruction and what specific substitution transmission channel is used in the case of substitution transmission instruction, thereby being capable of automatically and accurately determining the uplink of the peer-to-peer mode combination configuration spacecraft.
It will be apparent to those skilled in the art that embodiments of the present application may be provided as a method, apparatus, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (devices), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.
Claims (6)
1. An uplink determining method of a peer-to-peer mode combination configuration spacecraft, which is characterized in that the peer-to-peer mode combination configuration spacecraft consists of more than one pair of spacecraft with complete and independent measurement and control functions, wherein the measurement and control antenna of one spacecraft is arranged towards the-X axis direction, and the measurement and control antenna of the other spacecraft is arranged towards the +X axis direction, and the method comprises the following steps:
According to time period information in measurement and control arc segment forecast of a spacecraft and measurement and control antenna installation parameters of the spacecraft, determining an alpha angle numerical range when each component of the spacecraft is visible to the ground; judging whether the alpha angle information is in the alpha angle numerical range, if so, judging that the corresponding spacecraft component is in a measurement and control arc section, wherein the alpha angle refers to that the mechanical coordinate system of the spacecraft and the X-axis point to be one ray, the spacecraft points to the ground measurement and control equipment to be the other ray, and the included angle between the two rays is called alpha angle;
if the spacecraft component part is in the measurement and control arc section, the ground measurement and control equipment and the uplink remote control instruction of the spacecraft component part are transmitted in a direct transmission mode; if the spacecraft component is not in the measurement and control arc section, transmitting uplink remote control instructions of the ground measurement and control equipment and the spacecraft component in a transmission substitution mode, so that the ground measurement and control equipment and the spacecraft component in the measurement and control arc section establish a communication link and send the uplink remote control instructions to each component of the spacecraft in a determined instruction uploading mode.
2. The method for determining the uplink of the peer-to-peer mode combination configuration spacecraft according to claim 1, wherein the ground measurement and control device and the uplink remote control command of the spacecraft component part are transmitted in a transmission-substituted mode, and further comprising:
And determining a corresponding transmission channel when adopting a transmission mode for transmission according to the instruction type of the uplink remote control instruction.
3. The utility model provides an uplink determining device of peer mode combination configuration spacecraft, its characterized in that, peer mode combination configuration spacecraft comprises more than one pair of spacecraft that possess complete, independent measurement and control function, and the measurement and control antenna arrangement of one spacecraft is towards-X axis direction, and the measurement and control antenna arrangement of another spacecraft is towards +X axis direction, includes:
the measurement and control arc segment determining module is used for determining an alpha angle numerical range when each component part of the spacecraft is visible to the ground according to the time period information in the measurement and control arc segment forecast of the spacecraft and the measurement and control antenna installation parameters of the spacecraft; judging whether the alpha angle information is in the alpha angle numerical range, if so, judging that the corresponding spacecraft component is in a measurement and control arc section, wherein the alpha angle refers to that the mechanical coordinate system of the spacecraft and the X-axis point to be one ray, the spacecraft points to the ground measurement and control equipment to be the other ray, and the included angle between the two rays is called alpha angle;
the uploading mode determining module is used for transmitting the uplink remote control command of the ground measurement and control equipment and the spacecraft component part in a direct transmission mode if the spacecraft component part is in the measurement and control arc section; if the spacecraft component is not in the measurement and control arc section, transmitting uplink remote control instructions of the ground measurement and control equipment and the spacecraft component in a transmission substitution mode, so that the ground measurement and control equipment and the spacecraft component in the measurement and control arc section establish a communication link and send the uplink remote control instructions to each component of the spacecraft in a determined instruction uploading mode.
4. The uplink determining apparatus of a peer-to-peer mode combination configuration spacecraft of claim 3, wherein said proxy transmission unit further comprises:
and the transmission channel determination subunit is used for determining a corresponding transmission channel when adopting a transmission mode for transmission according to the instruction type of the uplink remote control instruction.
5. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the processor implements the steps of the method for determining the uplink of a peer-to-peer mode combination configuration spacecraft of any of claims 1 to 2 when said program is executed.
6. A computer readable storage medium having stored thereon a computer program, characterized in that the computer program when executed by a processor realizes the steps of the method for determining the uplink of a peer-to-peer mode combination configuration spacecraft of any of claims 1 to 2.
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