CN113815909A - Uplink determining method and device for peer-to-peer mode combined configuration spacecraft - Google Patents

Uplink determining method and device for peer-to-peer mode combined configuration spacecraft Download PDF

Info

Publication number
CN113815909A
CN113815909A CN202111054067.XA CN202111054067A CN113815909A CN 113815909 A CN113815909 A CN 113815909A CN 202111054067 A CN202111054067 A CN 202111054067A CN 113815909 A CN113815909 A CN 113815909A
Authority
CN
China
Prior art keywords
spacecraft
measurement
control
peer
uplink
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202111054067.XA
Other languages
Chinese (zh)
Other versions
CN113815909B (en
Inventor
李斌
梁爽
陈俊刚
彭德云
陈海
王炎娟
李晓明
杨少博
赵兴乾
周心婷
马鹏德
郭祥艳
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Unit 63920 Of Pla
Original Assignee
Unit 63920 Of Pla
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Unit 63920 Of Pla filed Critical Unit 63920 Of Pla
Priority to CN202111054067.XA priority Critical patent/CN113815909B/en
Publication of CN113815909A publication Critical patent/CN113815909A/en
Application granted granted Critical
Publication of CN113815909B publication Critical patent/CN113815909B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • G—PHYSICS
    • G08—SIGNALLING
    • G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
    • G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
    • G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Astronomy & Astrophysics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Radio Relay Systems (AREA)

Abstract

The embodiment of the application provides an uplink determining method and device for a peer-to-peer mode combined configuration spacecraft, wherein the method comprises the following steps: determining measurement and control arc sections corresponding to all components of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecasting 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 of the spacecraft and a ground measurement and control device according to a measurement and control arc section corresponding to each component of the spacecraft, so that the ground measurement and control device and the spacecraft component in the measurement and control arc section establish a communication link and send the uplink remote control instruction to each component of the spacecraft through the determined instruction uploading mode; the uplink of the peer-to-peer mode combined configuration spacecraft can be automatically and accurately determined.

Description

Uplink determining method and device for peer-to-peer mode combined configuration spacecraft
Technical Field
The application relates to the technical field of spaceflight, in particular to a method and a device for determining an uplink of a peer-to-peer mode combined configuration spacecraft.
Background
The peer-to-peer mode combined configuration spacecraft is composed of more than two spacecrafts with complete and independent measurement and control functions. Taking an assembly spacecraft (hereinafter referred to as an assembly) composed of two spacecrafts as an example, the two spacecrafts are a spacecraft a and a spacecraft B (hereinafter referred to as A, B), the overall configuration is shown in fig. 8, and the relationship of the mechanical coordinate systems of the two spacecrafts is shown in fig. 9.
The measurement and control antenna of the A is arranged towards the-X axis direction, and the measurement and control antenna of the B is arranged towards the + X axis direction.
In the combined state, the partial view fields of the A, B measurement and control antennas are respectively blocked by the other party. Therefore, the combination body adopts a method of A, B two-device combined measurement and control, namely, the measurement and control antenna of A is responsible for the measurement and control communication of the lower semispherical, the measurement and control antenna of B is responsible for the measurement and control communication of the upper semispherical, A, B two devices carry out independent measurement and control in time division, and the measurement and control antennas have no shielding view fields in the space parts which are respectively responsible for A and B.
According to the analysis result of the antenna field under the combined state, A, B method of combined measurement and control is implemented, namely A, B measurement and control antennas of the two devices are respectively responsible for measurement and control communication of the upper and lower semispherical balls. 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 pointing condition of the measurement and control antenna of the spacecraft to the ground, and selects A or B for uplink remote control, while the antenna is opposite to the other side of the earth, so that the remote control instruction sent by the ground cannot be directly received, and the instructions of the two devices need to be transmitted mutually.
If the antenna of the A points to the earth, the ground measurement and control equipment can track the A, a stable uplink communication link is established after double-capture is completed, the ground measurement and control equipment can directly send a remote control instruction to the A, and the B cannot establish a communication link with the ground due to the fact that the B is shielded by the A and cannot directly receive the instruction sent by the ground measurement and control equipment.
On the contrary, if the antenna of the B points to the earth, the ground measurement and control equipment can track the B, a stable uplink communication link is established after double-capture is completed, the ground measurement and control equipment can directly send a remote control instruction to the B, the A cannot establish a communication link with the ground due to the fact that the A is shielded by the B, and cannot directly receive the instruction sent by the ground measurement and control equipment, and under the condition, the instruction of the A can be sent to the B and is transmitted to the A by the B generation.
To date, spacecraft that have terminated, or are still in orbit, and combi-craft 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 ensured to be always pointed to the earth, the space-ground link communication can be carried out as long as the spacecraft runs over the ground measurement and control equipment, a communication link is established, and the spacecraft is remotely controlled by the ground measurement and control equipment.
(2) The monomers are launched in an in-orbit configuration. The spacecraft is a single spacecraft with a single structure in the launching and orbit entering stage and the initial operation stage, after the spacecraft operates for a period of time, two or more single spacecrafts are jointed and butted to form an assembly, the antennas of all components of the assembly are arranged on the same side, the antenna installation surfaces face the same direction, the antennas of all the components can be ensured to point to the earth at the same time by controlling the attitude of the assembly and adjusting the direction of the antenna in the operation process, and the earth link communication can be carried out as long as the assembly operates above the ground measurement and control equipment, so that a communication link is established, and the ground measurement and control equipment can independently control each component in a remote mode.
(3) Master-slave mode configuration. The spacecraft is formed by combining a plurality of spacecrafts in the launching and orbit stage, however, in the assembly stage before separation, only the measurement and control equipment of the main machine is started, the antenna of the main machine is enabled to always point to the earth by controlling the attitude of the main machine and adjusting the steering direction 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 with the ground measurement and control equipment is not independent, the communication link is controlled by replacing a command with the main machine, and after the assembly is separated, all the components fly independently to become the single spacecraft which runs in orbit and are respectively and independently measured and controlled.
Based on the facts, the existing 3 types of configurations (single body configuration, single body launching in-orbit combination configuration and master-slave mode configuration) can always keep the antenna pointing to the earth by controlling the attitude of the spacecraft and adjusting the steering of the antenna, so that the prediction calculation needs to be carried out on the operation orbit of each spacecraft to obtain the accurate measurement and control arc section of each spacecraft, and the measurement and control arc section of each spacecraft is not influenced by other spacecrafts and can be completely used for providing measurement and control service for the spacecraft.
The peer-to-peer mode configuration combination spacecraft is a combination spacecraft which is different from the above 3 configurations. Since each component of the peer-to-peer mode configuration assembly spacecraft is a spacecraft with complete and independent measurement and control functions, although the spacecraft runs in an assembly state from launching and entering to separating, measurement and control equipment of each component is started up in the whole process and needs to be independently measured and controlled, and then forecasting calculation needs to be carried out on the running orbit of each component, so that an accurate measurement and control arc section of each component is obtained.
Meanwhile, because the antennas of the components point to different directions, the antennas of the components cannot be ensured to point to the earth at the same time in the time period from the operation to the overhead of the ground measurement and control equipment, so that the measurement and control of each component cannot be carried out at the same time.
Under the condition, the uplink of the ground measurement and control equipment needs to be judged manually, and then the corresponding direct transmission or to-be-transmitted instruction is arranged according to the uplink, so that time-sharing measurement and control of all components of the combination are realized.
The inventor finds that the prior art scheme has three preconditions: firstly, the antenna of the spacecraft can always point to the earth; secondly, forecasting calculation is carried out on the measurement and control arc section of each independent spacecraft; and thirdly, manually judging whether a certain spacecraft can be measured and controlled, and manually appointing instructions of other spacecrafts to be transmitted by the spacecraft under the condition that the spacecraft can be measured and controlled. Therefore, the technical solutions in the prior art have at least the following disadvantages:
(1) when the combination body is used as an integral target to carry out measurement and control arc section forecast calculation, the measurement and control arc sections of all the components cannot be accurately defined.
(2) If the accurate measurement and control arc section of each component is to be obtained, the measurement and control arc section forecast is calculated once for each component, and the calculation amount is large.
(3) When flight control instructions are arranged, an operator needs to analyze measurement and control arc segment forecast in advance and manually appoint a generation link: when the device A is in the range of the measurement and control arc section of the device A, the instruction of the designated device A is directly transmitted by the link of the device A, and the instruction of the device B is transmitted by the link of the device A.
When the device is positioned in the range of the measurement and control arc section of the device B, the instruction of the designated device B is directly transmitted by the link of the device B, and the instruction of the device A is transmitted by the link of the device B.
(4) A, B the two devices establish a transmission channel through data bus, and in the case of transmission instruction, the specific transmission channel needs to be manually designated according to the type of the transmission instruction.
Disclosure of Invention
Aiming at the problems in the prior art, the method and the device for determining the uplink of the peer-to-peer mode combined configuration spacecraft are provided, and the uplink of the peer-to-peer mode combined configuration spacecraft can be automatically and accurately determined.
In order to solve at least one of the above problems, the present application provides the following technical solutions:
in a first aspect, the present application provides a method for determining an uplink of a peer-to-peer mode combined configuration spacecraft, including:
determining measurement and control arc sections corresponding to all components of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecasting of the spacecraft and measurement and control antenna installation parameters of the spacecraft;
and determining an instruction uploading mode of the ground measurement and control equipment and uplink remote control instructions corresponding to the components of the spacecraft according to the measurement and control arc sections corresponding to the components of the spacecraft, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components 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 and the 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 includes:
determining the numerical range of an alpha angle when each component of the spacecraft is visible to the ground according to time period information in measurement and control arc section forecasting of the spacecraft and measurement and control antenna installation parameters of the spacecraft;
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 the measurement and control arc section.
Further, the determining, according to the measurement and control arc segment corresponding to each component of the spacecraft, an instruction uploading mode of the ground measurement and control equipment and the uplink remote control instruction corresponding to each component of the spacecraft includes:
if the spacecraft component is positioned in the measurement and control arc section, the uplink remote control instructions of the ground measurement and control equipment and the spacecraft component are transmitted in a direct transmission mode;
and if the spacecraft component is not positioned in the measurement and control arc section, the uplink remote control instructions of the ground measurement and control equipment and the spacecraft component are transmitted in a transmission mode.
Further, the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component part is transmitted by adopting a transmission mode, and the method further comprises the following steps:
and determining a corresponding generation channel when the uplink remote control command is transmitted in a generation mode according to the command type of the uplink remote control command.
In a second aspect, the present application provides an uplink determining apparatus for a peer-to-peer mode combined configuration spacecraft, including:
the measurement and control arc segment determining module is used for determining measurement and control arc segments corresponding to all the components of the spacecraft according to time period information and alpha angle information in measurement and control arc segment prediction of the spacecraft and measurement and control antenna installation parameters of the spacecraft;
and the uploading mode determining module is used for determining the instruction uploading mode of the uplink remote control instructions corresponding to the ground measurement and control equipment and the components of the spacecraft according to the measurement and control arc sections corresponding to the components of the spacecraft, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components of the spacecraft in the determined instruction uploading mode.
Further, the measurement and control arc segment determination module comprises:
the alpha angle numerical range determining unit is used for determining the alpha angle numerical range when each component of the spacecraft is visible to the ground according to time period information in measurement and control arc segment prediction of the spacecraft and 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 comprises:
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 in a direct transmission mode if the spacecraft component is positioned in the measurement and control arc section;
and the generation transmission unit is used for transmitting the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component in a generation transmission mode if the spacecraft component is not positioned in the measurement and control arc section.
Further, the transmission means further includes:
and the generation channel determining subunit is used for determining a corresponding generation channel when the generation mode is adopted for transmission according to the instruction type of the uplink remote control instruction.
In a third aspect, the present application provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor, where the processor implements the steps of the uplink determining method for a peer-to-peer mode combined configuration spacecraft when executing the program.
In a fourth aspect, the present application provides a computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method for determining an uplink of a peer-to-peer mode combined configuration spacecraft.
According to the technical scheme, under the condition that the peer-to-peer mode combined configuration spacecraft is used as a whole target to perform measurement and control arc section forecasting calculation, the measurement and control arc sections of all the components of the spacecraft are accurately defined according to time period information, alpha angle information and measurement and control antenna installation parameters of the spacecraft in the measurement and control arc section forecasting, and then a communication link, a direct transmission/generation mode of an explicit instruction and a specific generation channel used under the condition of the generation instruction are automatically determined, so that 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 needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a flowchart illustrating one of the uplink determining methods of a peer-to-peer mode combined configuration spacecraft in the embodiment of the present application;
fig. 2 is a second flowchart of a method for determining an uplink of a peer-to-peer mode combined configuration spacecraft in the embodiment of the present application;
fig. 3 is a third flowchart of a method for determining an uplink of a peer-to-peer mode combined configuration spacecraft in the embodiment of the present application;
fig. 4 is one of the structural diagrams of an uplink determining apparatus of a peer-to-peer mode combined configuration spacecraft in the embodiment of the present application;
fig. 5 is a second block diagram of an uplink determining apparatus of a peer-to-peer mode combined configuration spacecraft in the embodiment of the present application;
fig. 6 is a third block diagram of an uplink determining apparatus of a peer-to-peer mode combined configuration spacecraft in the embodiment of the present application;
fig. 7 is a fourth block diagram of an uplink determination device of a peer-to-peer mode combined configuration spacecraft in the embodiment of the present application;
FIG. 8 is a schematic block diagram of a spacecraft in a configuration assembled in accordance with an embodiment of the present application;
FIG. 9 is a schematic view of a combination and a relationship of mechanical coordinates of each device in an embodiment of the present application;
FIG. 10 is a schematic view of the antenna pointing at an angle α of less than 90 in one embodiment of the present application;
FIG. 11 is a schematic view of the antenna pointing at an angle α greater than 90 in one embodiment of the present application;
fig. 12 is a schematic structural diagram of an electronic device in an embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In view of the problems in the prior art, the application provides a method and a device for determining an uplink of a peer-to-peer mode combined configuration spacecraft, wherein under the condition that the peer-to-peer mode combined configuration spacecraft is used as an overall target to perform measurement and control arc section forecasting calculation, measurement and control arc sections of all components of the spacecraft are accurately defined according to time period information, alpha angle information and measurement and control antenna installation parameters of the spacecraft in the measurement and control arc section forecasting, and then a communication link, a direct transmission/generation mode of an instruction and a specific generation channel used under the condition of generation of the instruction are automatically determined, so that the uplink of the peer-to-peer mode combined configuration spacecraft can be automatically and accurately determined.
In order to automatically and accurately determine an uplink of a peer-to-peer mode combined spacecraft, the present application provides an embodiment of a method for determining an uplink of a peer-to-peer mode combined spacecraft, and referring to fig. 1, the method for determining an uplink of a peer-to-peer mode combined spacecraft specifically includes the following steps:
step S101: and determining the measurement and control arc sections corresponding to all the components of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecasting of the spacecraft and the installation parameters of the measurement and control antenna of the spacecraft.
It can be understood that the measurement and control arc segment 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 range of the measurement and control arc segment, an antenna terminal arranged on the spacecraft points to ground measurement and control equipment, and the ground can receive telemetering data transmitted by the spacecraft; after the double-catching is completed, the ground can send a remote control instruction and an upper injection flight parameter to the spacecraft so as to measure and control the spacecraft.
It can be understood that the angle α refers to a ray pointing from the mechanical coordinate system + X axis of the spacecraft to the ground measurement and control equipment, and an included angle between the ray pointing from the spacecraft to the ground measurement and control equipment is referred to as angle α.
Alternatively, referring to fig. 10, the + X axis of the combined unit (i.e. the space vehicle with peer-to-peer mode combined configuration) in the present application is oriented towards the earth, the α angle is smaller than 90 °, i.e. the antenna of B is directed towards the earth, and both devices use B as uplink.
Alternatively, referring to fig. 11, the-X axis of the combined unit (i.e. the space vehicle with peer-to-peer mode combined configuration) in the present application is oriented towards the earth, the α angle is greater than 90 °, i.e. the antenna of a is directed towards the earth, and both devices use a as the uplink.
Therefore, the uplink of the ground measurement and control equipment can be selected according to the value of the alpha angle.
Specifically, the measurement and control arc sections of all the components can be accurately defined according to time period information and alpha angle information in the measurement and control arc section prediction and spacecraft measurement and control antenna installation parameters.
Step S102: and determining an instruction uploading mode of the ground measurement and control equipment and uplink remote control instructions corresponding to the components of the spacecraft according to the measurement and control arc sections corresponding to the components of the spacecraft, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components of the spacecraft through the determined instruction uploading mode.
Optionally, after the measurement and control arc sections of the components of the spacecraft can be accurately defined, the ground measurement and control equipment can establish a communication link with the spacecraft with the measurement and control arc sections, and send the uplink remote control instruction through the communication link.
Optionally, if the instruction is sent to the link building spacecraft in the application, the instruction sending mode is direct transmission; if the command is sent to another spacecraft (without a measurement and control arc segment and without a chain), the command sending mode is transmission instead.
Optionally, when the instruction is judged to adopt a transmission-replacing mode, a specific transmission-replacing channel is determined by judging the type of the instruction.
As can be seen from the above description, the method for determining the uplink of the peer-to-peer mode combined spacecraft provided in the embodiment of the present application can accurately define the measurement and control arc segments 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 under the condition that the peer-to-peer mode combined spacecraft is used as an overall target for measurement and control arc segment prediction calculation, and further automatically determine the communication link, the direct transmission/generation mode of the explicit instruction, and which specific generation channel is used under the condition of generation instruction, so that the uplink of the peer-to-peer mode combined spacecraft can be automatically and accurately determined.
In order to accurately define the measurement and control arc segments of each component of the combined configuration spacecraft, in an embodiment of the uplink determining method for the peer-to-peer mode combined configuration spacecraft of the present application, referring to fig. 2, the step S101 may further specifically include the following steps:
step S201: and determining the numerical range of the alpha angle when each component of the spacecraft is visible to the ground according to the time interval 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 the measurement and control arc section.
In a specific embodiment of the application, the application can accurately define the measurement and control arc sections of all the components according to the time interval information and the alpha angle information in the measurement and control arc section prediction and the installation parameters of the measurement and control antenna of the spacecraft.
Specifically, the measurement and control arc segment prediction is recorded as Y ═ Y (Y)1,Y2,…,Yi,…,Yn) Wherein Y isi＝(ti,αi) Denotes tiTime assembly is to groundIt can be seen that the angle alpha of the combined body at the moment is alphai,i＝1,2,…,n。
The installation parameters of the spacecraft measurement and control antenna are recorded as A ═ A1,A2,…,Aj,…,Am) Wherein, in the step (A),
Figure BDA0003253957760000081
Figure BDA0003253957760000082
denotes the antenna installation parameter for the jth spacecraft, j ═ 1,2, …, m.
Figure BDA0003253957760000083
Indicating the range that the alpha angle value of the assembly should satisfy when the spacecraft is visible to the ground, i.e. if the alpha angle value of the assembly satisfies
Figure BDA0003253957760000084
Then tiAt the moment, the jth spacecraft in the combination is visible to the ground, and the ground measurement and control equipment can measure and control the jth spacecraft and send an uplink remote control instruction to the spacecraft.
Note TBj＝Min(ti) Representing the starting moment of a measurement and control arc section of the spacecraft; TEj＝Max(ti) And represents the ending time of the measurement and control arc segment of the spacecraft.
Remember I ═ I (I)1,I2,…,Ij,…,Im) In which Ij＝(Qj,TBj,TEj) And j is 1,2, … and m of the j-th spacecraft. QjDenotes the jth spacecraft, TBj,TEjThe meaning of (A) is as described hereinbefore.
After the measurement and control arc sections of all the components are accurately defined, the ground measurement and control equipment can establish a communication link with a spacecraft with the measurement and control arc sections, and sends an uplink remote control instruction through the communication link.
In order to accurately determine the instruction uploading mode of the uplink remote control instruction, in an embodiment of the uplink determining method for a peer-to-peer mode combined configuration spacecraft of the present application, referring to fig. 3, the step S102 may further specifically include the following steps:
step S301: and if the spacecraft component is positioned in the measurement and control arc section, the uplink remote control instructions of the ground measurement and control equipment and the spacecraft component are transmitted in a direct transmission mode.
Step S302: and if the spacecraft component is not positioned in the measurement and control arc section, the uplink remote control instructions of the ground measurement and control equipment and the spacecraft component are transmitted in a transmission mode.
It can be understood that the direct transmission means that the ground measurement and control equipment directly sends an instruction to the spacecraft after establishing a communication link with the spacecraft.
It can be understood that the substitute transmission means that, under the condition that one set of ground measurement and control equipment measures and controls two spacecrafts and can only establish a communication link with one of the spacecrafts, after the ground measurement and control equipment establishes a communication link with one of the spacecrafts, an instruction is sent to the link of the spacecraft and the spacecraft forwards the instruction to the other spacecraft.
In one embodiment of the present application, let C ═ C (C)1,C2,…,Ck,…,Cp) In which C isk＝(Qj,TYPEl,TIMEk) Attributes representing the kth instruction, namely: the jth spacecraft of TYPElTIME is TIMEkK is 1,2, …, p. Wherein Q isjAs previously described, TYPElIndicates the type of instruction, 1, 2; TIMEkIndicating the instruction time.
For arbitrary instructions
Figure BDA0003253957760000091
j11,2, …, m, and the measurement and control arc of any spacecraft
Figure BDA0003253957760000092
j21,2, …, m, determining a command uploading mode:
when j is1＝j2And is and
Figure BDA0003253957760000093
when the spacecraft is in a measurement and control arc section, the command is in a direct transmission mode;
when j is1≠j2And is and
Figure BDA0003253957760000094
and meanwhile, the instruction is positioned in the measurement and control arc sections of other spacecrafts, and a transmission mode is adopted.
In order to accurately determine the transmission channel when the transmission is performed in the transmission manner, in an embodiment of the uplink determining method for a peer-to-peer mode combined configuration spacecraft, the step S302 may further specifically include the following steps:
and determining a corresponding generation channel when the uplink remote control command is transmitted in a generation mode according to the command type of the uplink remote control command.
In an embodiment of the present application, a command C in a transfer mode is replaced for any one of the commands Ck＝(Qj,TYPEl,TIMEk) J is 1,2, …, m, and its command type is determined:
when TYPElWhen the data bus is 1, the data bus carries out generation transmission;
when TYPElWhen 2, the data is transmitted through the data bus 2 generation.
As can be seen from the above, the present application can achieve at least the following technical effects:
(1) the method for determining the uplink of the peer-to-peer mode combined configuration spacecraft reduces the calculation times of measurement and control arc section forecasting, and realizes that the result of calculating the measurement and control arc section at one time can be applied to the measurement and control of a plurality of spacecrafts.
(2) The method for determining the uplink of the peer-to-peer mode combined configuration spacecraft realizes an automatic instruction uploading determination mode, and replaces a manual comparison and judgment mode.
(3) The method for determining the uplink of the peer-to-peer mode combined configuration spacecraft realizes the channel generation and transmission according to the automatic determination instruction, and replaces the manual designation mode.
In order to automatically and accurately determine the uplink of the peer-to-peer mode combined spacecraft, the present application provides an embodiment of an uplink determining apparatus of the peer-to-peer mode combined spacecraft, which is used for implementing all or part of the contents of the uplink determining method of the peer-to-peer mode combined spacecraft, and referring to fig. 4, the uplink determining apparatus of the peer-to-peer mode combined spacecraft specifically includes the following contents:
and the measurement and control arc segment determining module 10 is used for determining the measurement and control arc segments corresponding to all the components of the spacecraft according to the time period information and the 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.
And the uploading mode determining module 20 is configured to determine, according to the measurement and control arc sections corresponding to the components of the spacecraft, an instruction uploading mode of the uplink remote control instructions corresponding to the components of the spacecraft and the ground measurement and control equipment, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components of the spacecraft in the determined instruction uploading mode.
As can be seen from the above description, the uplink determining device for a peer-to-peer mode combined spacecraft provided in the embodiment of the present application can accurately define the measurement and control arc segments 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 calculation when the peer-to-peer mode combined spacecraft is used as an overall target, and further automatically determine a communication link, a direct transmission/generation manner of a specific instruction, and which specific generation channel is used in the case of generation of the instruction, so that the uplink of the peer-to-peer mode combined 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 uplink determining device of the peer-to-peer mode combined configuration spacecraft of the present application, referring to fig. 5, the measurement and control arc segment determining module 10 includes:
the alpha angle numerical range determining unit 11 is configured to determine an alpha angle numerical range when each component of the spacecraft is visible to the ground according to time period information in measurement and control arc segment prediction of the spacecraft and measurement and control antenna installation parameters of the spacecraft.
And the visible state determining unit 12 is configured to determine whether the α angle information is within the α angle numerical range, and if so, determine that the corresponding spacecraft component is in the measurement and control arc segment.
In order to accurately determine an instruction uploading mode of an uplink remote control instruction, in an embodiment of the uplink determining apparatus of a peer-to-peer mode combined configuration spacecraft of the present application, referring to fig. 6, the uploading mode 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 in a direct transmission mode if the spacecraft component is positioned in the measurement and control arc section.
And the transmission unit 22 is used for transmitting the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component in a transmission mode if the spacecraft component is not in the measurement and control arc section.
In order to accurately determine the transmission channel when the transmission is performed by using the transmission method, in an embodiment of the uplink determining apparatus for a peer-to-peer mode combined configuration spacecraft of the present application, referring to fig. 7, the transmission unit 22 further includes:
and the generation channel determining subunit 221 is configured to determine, according to the instruction type of the uplink remote control instruction, a corresponding generation channel when the transmission is performed in a generation manner.
In terms of hardware, in order to be able to automatically and accurately determine an uplink of a peer-to-peer mode combined configuration spacecraft, the present application provides an embodiment of an electronic device for implementing all or part of contents in an uplink determination method of the peer-to-peer mode combined configuration spacecraft, where the electronic device specifically includes 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 mutual communication through the bus; the communication interface is used for realizing information transmission between an uplink determining device of the peer-to-peer mode combined 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, and the like, but the embodiment is not limited thereto. In this embodiment, the logic controller may refer to an embodiment of an uplink determining method of a peer-to-peer mode combined spacecraft in the embodiment, and may implement an embodiment of an uplink determining apparatus of a peer-to-peer mode combined spacecraft, which are incorporated herein, and repeated details are not repeated.
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), an in-vehicle device, a smart wearable device, and the like. Wherein, intelligence wearing equipment can include intelligent glasses, intelligent wrist-watch, intelligent bracelet etc..
In practical applications, part of the uplink determining method for the peer-to-peer mode combined configuration spacecraft may be performed on the electronic device side as described above, or all operations may be performed in the client device. The selection may be specifically performed according to the processing capability of the client device, the limitation of the user usage scenario, and the like. This is not a limitation of the present application. The client device may further include a processor if all operations are performed in the client device.
The client device may have a communication module (i.e., a communication unit), and may be communicatively connected to a remote server to implement data transmission with the server. The server may include a server on the task scheduling center side, and in other implementation scenarios, the server may also include a server on an intermediate platform, for example, a server on a third-party server platform that is communicatively linked to the task scheduling center server. The server may include a single computer device, or may include a server cluster formed by a plurality of servers, or a server structure of a distributed apparatus.
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 can 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 structure to implement telecommunications or other functions.
In an embodiment, the uplink determination method function of the peer-to-peer mode combined configuration spacecraft may be integrated into the central processor 9100. The central processor 9100 may be configured to control as follows:
step S101: and determining the measurement and control arc sections corresponding to all the components of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecasting of the spacecraft and the installation parameters of the measurement and control antenna of the spacecraft.
Step S102: and determining an instruction uploading mode of the ground measurement and control equipment and uplink remote control instructions corresponding to the components of the spacecraft according to the measurement and control arc sections corresponding to the components of the spacecraft, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components of the spacecraft through the determined instruction uploading mode.
As can be seen from the above description, in the electronic device provided in the embodiment of the present application, when the measurement and control arc segment prediction calculation is performed on the peer-to-peer mode combined configuration spacecraft as an overall target, the measurement and control arc segments of each component of the spacecraft are accurately defined according to the time period information and the α angle information in the measurement and control arc segment prediction and the measurement and control antenna installation parameters of the spacecraft, so as to automatically determine a communication link, a direct transmission/generation manner for specifying an instruction, and a specific generation channel used in the case of generating an instruction, thereby automatically and accurately determining an uplink of the peer-to-peer mode combined configuration spacecraft.
In another embodiment, the uplink determining apparatus of the peer-to-peer mode combined spacecraft may be configured separately from the central processor 9100, for example, the uplink determining apparatus of the peer-to-peer mode combined spacecraft may be configured as a chip connected to the central processor 9100, and the uplink determining method function of the peer-to-peer mode combined spacecraft is realized 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 also does not necessarily include all of the components shown in fig. 12; further, the electronic device 9600 may further include components not shown in fig. 12, which can be referred to in the related art.
As shown in fig. 12, a central processor 9100, sometimes referred to as a controller or operational control, can include a microprocessor or other processor device and/or logic device, which central processor 9100 receives input and controls the operation of the various components of the electronic device 9600.
The memory 9140 can 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 relating to the failure may be stored, and a program for executing the information may be stored. And the central processing unit 9100 can execute the program stored in the memory 9140 to realize information storage or processing, or 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. Power supply 9170 is used to provide power to electronic device 9600. The display 9160 is used for displaying display objects such as images and characters. The display may be, for example, an LCD display, but is not limited thereto.
The memory 9140 can be a solid state memory, e.g., Read Only Memory (ROM), Random Access Memory (RAM), a SIM card, or the like. There may also be a memory that holds information even when power is off, can be selectively erased, and is provided with more data, an example of which is sometimes called an EPROM or the like. The memory 9140 could also be some other type of device. 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 being used for storing application programs and function programs or for executing a flow of operations of the electronic device 9600 by the central processor 9100.
The memory 9140 can also include a data store 9143, the data store 9143 being used to store 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 for the electronic device for communication functions and/or for performing other functions of the electronic device (e.g., messaging applications, contact book applications, etc.).
The communication module 9110 is a transmitter/receiver 9110 that transmits and receives signals via an antenna 9111. The communication module (transmitter/receiver) 9110 is coupled to the central processor 9100 to provide input signals and receive output signals, which may be the same as in the case of a conventional mobile communication terminal.
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, 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 receive audio input from the microphone 9132, thereby implementing ordinary telecommunications functions. The audio processor 9130 may include any suitable buffers, decoders, amplifiers and so forth. In addition, the audio processor 9130 is also coupled to the central processor 9100, thereby enabling recording locally through the microphone 9132 and enabling locally stored sounds to be played through the speaker 9131.
An embodiment of the present application further provides a computer-readable storage medium capable of implementing all the steps in the uplink determination method for a peer-to-peer mode combined configuration spacecraft, where the execution subject of the method is a server or a client in the foregoing embodiment, and the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the computer program implements all the steps in the uplink determination method for a peer-to-peer mode combined configuration spacecraft, where the execution subject of the computer program 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 sections corresponding to all the components of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecasting of the spacecraft and the installation parameters of the measurement and control antenna of the spacecraft.
Step S102: and determining an instruction uploading mode of the ground measurement and control equipment and uplink remote control instructions corresponding to the components of the spacecraft according to the measurement and control arc sections corresponding to the components of the spacecraft, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components of the spacecraft through the determined instruction uploading mode.
As can be seen from the above description, in the computer-readable storage medium provided in this embodiment of the present application, when the measurement and control arc prediction calculation is performed on the peer-to-peer mode combined configuration spacecraft as a whole target, the measurement and control arc of each component of the spacecraft is accurately defined according to the time period information and the α angle information in the measurement and control arc prediction and the measurement and control antenna installation parameters of the spacecraft, and then the communication link, the direct transmission/generation manner of the explicit instruction, and which specific generation channel is used in the case of the generation instruction are automatically determined, so that the uplink of the peer-to-peer mode combined configuration spacecraft can be automatically and accurately determined.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, apparatus, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention 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 flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams 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 principle and the implementation mode of the invention are explained by applying specific embodiments in the invention, and the description of the embodiments is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims (10)

1. A method for uplink determination of a peer-to-peer mode combined configuration spacecraft, the method comprising:
determining measurement and control arc sections corresponding to all components of the spacecraft according to time period information and alpha angle information in measurement and control arc section forecasting of the spacecraft and measurement and control antenna installation parameters of the spacecraft;
and determining an instruction uploading mode of the ground measurement and control equipment and uplink remote control instructions corresponding to the components of the spacecraft according to the measurement and control arc sections corresponding to the components of the spacecraft, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components of the spacecraft through the determined instruction uploading mode.
2. The uplink determining method of a peer-to-peer mode combined configuration spacecraft according to claim 1, wherein the determining of the measurement and control arc segment corresponding to each component of the spacecraft according to the time period information and the α angle information in the measurement and control arc segment prediction of the spacecraft and the measurement and control antenna installation parameters of the spacecraft comprises:
determining the numerical range of an alpha angle when each component of the spacecraft is visible to the ground according to time period information in measurement and control arc section forecasting of the spacecraft and measurement and control antenna installation parameters of the spacecraft;
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 the measurement and control arc section.
3. The method for determining the uplink of the peer-to-peer mode combined configuration spacecraft according to claim 1, wherein the step of determining the instruction uploading mode of the uplink remote control instruction corresponding to the ground measurement and control equipment and each component of the spacecraft according to the measurement and control arc segment corresponding to each component of the spacecraft comprises the following steps:
if the spacecraft component is positioned in the measurement and control arc section, the uplink remote control instructions of the ground measurement and control equipment and the spacecraft component are transmitted in a direct transmission mode;
and if the spacecraft component is not positioned in the measurement and control arc section, the uplink remote control instructions of the ground measurement and control equipment and the spacecraft component are transmitted in a transmission mode.
4. The method for determining the uplink of a peer-to-peer mode combined configuration spacecraft as claimed in claim 3, wherein the uplink remote control commands of the ground measurement and control equipment and the spacecraft component are transmitted by transmission, further comprising:
and determining a corresponding generation channel when the uplink remote control command is transmitted in a generation mode according to the command type of the uplink remote control command.
5. An uplink determining apparatus for a peer-to-peer mode combined configuration spacecraft, comprising:
the measurement and control arc segment determining module is used for determining measurement and control arc segments corresponding to all the components of the spacecraft according to time period information and alpha angle information in measurement and control arc segment prediction of the spacecraft and measurement and control antenna installation parameters of the spacecraft;
and the uploading mode determining module is used for determining the instruction uploading mode of the uplink remote control instructions corresponding to the ground measurement and control equipment and the components of the spacecraft according to the measurement and control arc sections corresponding to the components of the spacecraft, so that the ground measurement and control equipment and the components of the spacecraft in the measurement and control arc sections establish a communication link and send the uplink remote control instructions to the components of the spacecraft in the determined instruction uploading mode.
6. The apparatus for determining uplink of a spacecraft of claim 5, wherein said measurement and control arc segment determining module comprises:
the alpha angle numerical range determining unit is used for determining the alpha angle numerical range when each component of the spacecraft is visible to the ground according to time period information in measurement and control arc segment prediction of the spacecraft and 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.
7. The apparatus for determining uplink of a peer-to-peer mode combined configuration spacecraft of claim 5, wherein said upload mode determination module comprises:
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 in a direct transmission mode if the spacecraft component is positioned in the measurement and control arc section;
and the generation transmission unit is used for transmitting the uplink remote control instruction of the ground measurement and control equipment and the spacecraft component in a generation transmission mode if the spacecraft component is not positioned in the measurement and control arc section.
8. The apparatus for determining uplink of a peer-to-peer mode combined configuration spacecraft of claim 7, wherein said proxy transmission unit further comprises:
and the generation channel determining subunit is used for determining a corresponding generation channel when the generation mode is adopted for transmission according to the instruction type of the uplink remote control instruction.
9. 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 an uplink of a combined peer-to-peer mode spacecraft of any one of claims 1 to 4 when executing said program.
10. A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the steps of the method for uplink determination of a peer-to-peer mode combining configuration spacecraft of any one of claims 1 to 4.
CN202111054067.XA 2021-09-09 2021-09-09 Uplink determining method and device for peer-to-peer mode combination configuration spacecraft Active CN113815909B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202111054067.XA CN113815909B (en) 2021-09-09 2021-09-09 Uplink determining method and device for peer-to-peer mode combination configuration spacecraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202111054067.XA CN113815909B (en) 2021-09-09 2021-09-09 Uplink determining method and device for peer-to-peer mode combination configuration spacecraft

Publications (2)

Publication Number Publication Date
CN113815909A true CN113815909A (en) 2021-12-21
CN113815909B CN113815909B (en) 2023-10-27

Family

ID=78914296

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202111054067.XA Active CN113815909B (en) 2021-09-09 2021-09-09 Uplink determining method and device for peer-to-peer mode combination configuration spacecraft

Country Status (1)

Country Link
CN (1) CN113815909B (en)

Citations (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0624008A2 (en) * 1993-05-07 1994-11-09 Space Systems / Loral, Inc. Mobile communication satellite payload
CN1154022A (en) * 1995-08-23 1997-07-09 环球星有限合伙人公司 Satellite beam steering reference using terrestrial beam steering terminals
CA2199884A1 (en) * 1996-03-26 1997-09-26 Bronson Murray Spacecraft with modular communication payload
JPH11180400A (en) * 1997-12-24 1999-07-06 Mitsubishi Electric Corp Observation device
CA2260455A1 (en) * 1998-02-11 1999-08-11 Space Systems/Loral, Inc. Antenna system with plural reflectors
CN1268088A (en) * 1997-06-25 2000-09-27 内沃克斯公司 Vehicle tracking and security system incorporating simultaneous voice and data communication
CN1284223A (en) * 1997-12-18 2001-02-14 欧洲卫星股份有限公司 Method and appts for determining characteristics of components of communication channel under load
CN101288249A (en) * 2005-10-18 2008-10-15 三星电子株式会社 Method and apparatus for receiving an allocated transmission period in a wireless communication system
JP2008302808A (en) * 2007-06-07 2008-12-18 Mitsubishi Electric Corp Orbit control programming device for spacecraft
CN101584131A (en) * 2006-12-14 2009-11-18 维尔塞特公司 Satellite communication system and method with asymmetric feeder and service frequency bands
CN101590918A (en) * 2009-06-19 2009-12-02 上海微小卫星工程中心 Method for automatic fault diagnosis of satellite and diagnostic system thereof
DE102009059694B3 (en) * 2009-12-18 2011-03-17 Astrium Gmbh Method for determining position of spacecraft by multiple transmitters, involves measuring three orthogonal components of electromagnetic radiation fields on spacecraft
CN102446397A (en) * 2011-10-18 2012-05-09 南京信息职业技术学院 Dynamic experimental testing wireless management system and method
CN102521953A (en) * 2011-11-15 2012-06-27 北京空间飞行器总体设计部 Method for recording and downloading satellite measured and controlled telemetry parameters of invisible arc section
CN102520262A (en) * 2011-11-15 2012-06-27 上海卫星工程研究所 Device and method for testing radio-frequency waveguide of deep space aircraft
CN102795350A (en) * 2012-07-06 2012-11-28 中国航天科技集团公司第五研究院第五一三研究所 Physical discrete type satellite system structure
CN102956096A (en) * 2011-08-25 2013-03-06 南京能瑞自动化设备股份有限公司 Ethernet passive optical network (EPON) and wireless ad hoc network technology-based electricity consumption information acquisition system
CN103241393A (en) * 2013-05-17 2013-08-14 哈尔滨工业大学 Spacecraft space firm docking method
CN103795593A (en) * 2014-01-24 2014-05-14 武汉大学 Testing system and method of uplink of high-speed communication processor of spaceship
DE102014100084A1 (en) * 2013-01-11 2014-07-17 General Motors Llc Short-range wireless communication between a vehicle and a portable communication device
CN104058110A (en) * 2014-06-04 2014-09-24 清华大学 Remote sensing satellite system
CA2905887A1 (en) * 2014-11-13 2016-05-13 The Boeing Company Deployable airborne sensor array system and method of use
CN105846886A (en) * 2016-03-31 2016-08-10 四川泰立科技股份有限公司 Satellite of providing satellite network data enabling service and emission method thereof
CN106028352A (en) * 2016-05-12 2016-10-12 西南交通大学 Wireless detection and communication integrated area danger early-warning system and method
CN106125749A (en) * 2016-07-19 2016-11-16 中国人民解放军63920部队 The teleoperation method of a kind of spacecraft and device
CN106205101A (en) * 2016-09-28 2016-12-07 申丽 A kind of M BUS communication interface transducer for the most compatible Europe superscript agreement of centralized meter-reading system
CN106547516A (en) * 2016-11-01 2017-03-29 航天恒星科技有限公司 Spacecraft telecommand instructs upload control method and device
CN106610500A (en) * 2015-10-23 2017-05-03 中国科学院国家空间科学中心 Distributed multidirectional high-energy electron detection device based on multiple satellites
CN106892136A (en) * 2017-02-16 2017-06-27 北京航天自动控制研究所 A kind of aerospace craft metro planning method based on world communication
CN107240756A (en) * 2017-05-19 2017-10-10 上海宇航系统工程研究所 A kind of antenna expansion controller with on-orbit fault diagnosis and autonomous processing function
CN107331967A (en) * 2017-06-20 2017-11-07 中国电子科技集团公司第五十四研究所 A kind of complex tracking method of onboard satellite communication antenna
CN107341953A (en) * 2017-07-07 2017-11-10 成都汉度科技有限公司 A kind of electric device debugging switching device and concentrator telecommunication system
CN107816973A (en) * 2017-09-29 2018-03-20 北京空间飞行器总体设计部 Photography task automatic planning system and method for visual remote sensing spacecraft
CN108298078A (en) * 2013-07-31 2018-07-20 深圳市大疆创新科技有限公司 Long-range control method and terminal
WO2018139357A1 (en) * 2017-01-27 2018-08-02 国立研究開発法人情報通信研究機構 Spatial optical communication device and method
US10277308B1 (en) * 2016-09-22 2019-04-30 Viasat, Inc. Methods and systems of adaptive antenna pointing for mitigating interference with a nearby satellite
WO2019153786A1 (en) * 2018-02-09 2019-08-15 深圳市道通智能航空技术有限公司 Data transmission method, device and system
CN111770155A (en) * 2020-01-03 2020-10-13 中国人民解放军63920部队 Data processing method, device, storage medium and processor
CN112470341A (en) * 2018-07-12 2021-03-09 空中客车防务及航天有限公司 Array-fed reflector antenna
CN112949044A (en) * 2021-02-08 2021-06-11 北京京航计算通讯研究所 Method for determining spacecraft antenna installation position and antenna pointing selection
CN113065243A (en) * 2021-03-23 2021-07-02 中国科学院微小卫星创新研究院 Optimization method for satellite-borne antenna layout

Patent Citations (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0624008A2 (en) * 1993-05-07 1994-11-09 Space Systems / Loral, Inc. Mobile communication satellite payload
CN1154022A (en) * 1995-08-23 1997-07-09 环球星有限合伙人公司 Satellite beam steering reference using terrestrial beam steering terminals
CA2199884A1 (en) * 1996-03-26 1997-09-26 Bronson Murray Spacecraft with modular communication payload
CN1268088A (en) * 1997-06-25 2000-09-27 内沃克斯公司 Vehicle tracking and security system incorporating simultaneous voice and data communication
CN1284223A (en) * 1997-12-18 2001-02-14 欧洲卫星股份有限公司 Method and appts for determining characteristics of components of communication channel under load
JPH11180400A (en) * 1997-12-24 1999-07-06 Mitsubishi Electric Corp Observation device
CA2260455A1 (en) * 1998-02-11 1999-08-11 Space Systems/Loral, Inc. Antenna system with plural reflectors
CN101288249A (en) * 2005-10-18 2008-10-15 三星电子株式会社 Method and apparatus for receiving an allocated transmission period in a wireless communication system
CN101584131A (en) * 2006-12-14 2009-11-18 维尔塞特公司 Satellite communication system and method with asymmetric feeder and service frequency bands
JP2008302808A (en) * 2007-06-07 2008-12-18 Mitsubishi Electric Corp Orbit control programming device for spacecraft
CN101590918A (en) * 2009-06-19 2009-12-02 上海微小卫星工程中心 Method for automatic fault diagnosis of satellite and diagnostic system thereof
DE102009059694B3 (en) * 2009-12-18 2011-03-17 Astrium Gmbh Method for determining position of spacecraft by multiple transmitters, involves measuring three orthogonal components of electromagnetic radiation fields on spacecraft
CN102956096A (en) * 2011-08-25 2013-03-06 南京能瑞自动化设备股份有限公司 Ethernet passive optical network (EPON) and wireless ad hoc network technology-based electricity consumption information acquisition system
CN102446397A (en) * 2011-10-18 2012-05-09 南京信息职业技术学院 Dynamic experimental testing wireless management system and method
CN102521953A (en) * 2011-11-15 2012-06-27 北京空间飞行器总体设计部 Method for recording and downloading satellite measured and controlled telemetry parameters of invisible arc section
CN102520262A (en) * 2011-11-15 2012-06-27 上海卫星工程研究所 Device and method for testing radio-frequency waveguide of deep space aircraft
CN102795350A (en) * 2012-07-06 2012-11-28 中国航天科技集团公司第五研究院第五一三研究所 Physical discrete type satellite system structure
DE102014100084A1 (en) * 2013-01-11 2014-07-17 General Motors Llc Short-range wireless communication between a vehicle and a portable communication device
CN103241393A (en) * 2013-05-17 2013-08-14 哈尔滨工业大学 Spacecraft space firm docking method
CN108298078A (en) * 2013-07-31 2018-07-20 深圳市大疆创新科技有限公司 Long-range control method and terminal
CN103795593A (en) * 2014-01-24 2014-05-14 武汉大学 Testing system and method of uplink of high-speed communication processor of spaceship
CN104058110A (en) * 2014-06-04 2014-09-24 清华大学 Remote sensing satellite system
CA2905887A1 (en) * 2014-11-13 2016-05-13 The Boeing Company Deployable airborne sensor array system and method of use
CN106610500A (en) * 2015-10-23 2017-05-03 中国科学院国家空间科学中心 Distributed multidirectional high-energy electron detection device based on multiple satellites
CN105846886A (en) * 2016-03-31 2016-08-10 四川泰立科技股份有限公司 Satellite of providing satellite network data enabling service and emission method thereof
CN106028352A (en) * 2016-05-12 2016-10-12 西南交通大学 Wireless detection and communication integrated area danger early-warning system and method
CN106125749A (en) * 2016-07-19 2016-11-16 中国人民解放军63920部队 The teleoperation method of a kind of spacecraft and device
US10277308B1 (en) * 2016-09-22 2019-04-30 Viasat, Inc. Methods and systems of adaptive antenna pointing for mitigating interference with a nearby satellite
CN106205101A (en) * 2016-09-28 2016-12-07 申丽 A kind of M BUS communication interface transducer for the most compatible Europe superscript agreement of centralized meter-reading system
CN106547516A (en) * 2016-11-01 2017-03-29 航天恒星科技有限公司 Spacecraft telecommand instructs upload control method and device
WO2018139357A1 (en) * 2017-01-27 2018-08-02 国立研究開発法人情報通信研究機構 Spatial optical communication device and method
CN106892136A (en) * 2017-02-16 2017-06-27 北京航天自动控制研究所 A kind of aerospace craft metro planning method based on world communication
CN107240756A (en) * 2017-05-19 2017-10-10 上海宇航系统工程研究所 A kind of antenna expansion controller with on-orbit fault diagnosis and autonomous processing function
CN107331967A (en) * 2017-06-20 2017-11-07 中国电子科技集团公司第五十四研究所 A kind of complex tracking method of onboard satellite communication antenna
CN107341953A (en) * 2017-07-07 2017-11-10 成都汉度科技有限公司 A kind of electric device debugging switching device and concentrator telecommunication system
CN107816973A (en) * 2017-09-29 2018-03-20 北京空间飞行器总体设计部 Photography task automatic planning system and method for visual remote sensing spacecraft
WO2019153786A1 (en) * 2018-02-09 2019-08-15 深圳市道通智能航空技术有限公司 Data transmission method, device and system
CN112470341A (en) * 2018-07-12 2021-03-09 空中客车防务及航天有限公司 Array-fed reflector antenna
CN111770155A (en) * 2020-01-03 2020-10-13 中国人民解放军63920部队 Data processing method, device, storage medium and processor
CN112949044A (en) * 2021-02-08 2021-06-11 北京京航计算通讯研究所 Method for determining spacecraft antenna installation position and antenna pointing selection
CN113065243A (en) * 2021-03-23 2021-07-02 中国科学院微小卫星创新研究院 Optimization method for satellite-borne antenna layout

Also Published As

Publication number Publication date
CN113815909B (en) 2023-10-27

Similar Documents

Publication Publication Date Title
CN111491332B (en) Dynamic service migration method and device
CN111786885B (en) Distributed full-link gray level routing method and device
CN109496419B (en) File processing method, device and system
CN104394191B (en) The method of remote control mobile terminal, control terminal and system
CN111031058A (en) Websocket-based distributed server cluster interaction method and device
WO2017143991A1 (en) Vehicle-mounted navigation method, interactive system server, terminal and system
US10542375B2 (en) System and method for transmitting information about task to external device
CN111246228B (en) Method, device, medium and electronic equipment for updating gift resources of live broadcast room
US9662572B1 (en) Seamless continuation of entertainment content
CN104158719A (en) Information processing method and system, IM application device, and terminal
CN111679811B (en) Web service construction method and device
CN105653035B (en) virtual reality control method and system
CN114168018A (en) Data interaction method, data interaction device, electronic equipment, storage medium and program product
CN115167182A (en) Automatic driving simulation test method, device, equipment and computer readable medium
CN111263220B (en) Video processing method and device, electronic equipment and computer readable storage medium
CN112689012A (en) Cross-network proxy communication method and device
CN113815909B (en) Uplink determining method and device for peer-to-peer mode combination configuration spacecraft
CN111478916B (en) Data transmission method, device and storage medium based on video stream
CN115097984B (en) Interaction method, interaction device, electronic equipment and storage medium
CN114332328A (en) Scene rendering method, scene rendering device, electronic device and readable storage medium
CN112492520A (en) Positioning method, device, equipment and storage medium
CN114153542A (en) Screen projection method and device, electronic equipment and computer readable storage medium
CN113992660A (en) File transmission method and device, electronic equipment and storage medium
CN112543228A (en) Data transmission method and device, electronic equipment and computer readable medium
TWI564739B (en) System, method and non-transitory computer-readable medium of globally distributed virtual cache for worldwide real-time data access

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant