CN112468218B - Satellite communication method and device for resisting non-stationary rotating speed shielding - Google Patents
Satellite communication method and device for resisting non-stationary rotating speed shielding Download PDFInfo
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- H04W4/40—Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P]
- H04W4/44—Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P] for communication between vehicles and infrastructures, e.g. vehicle-to-cloud [V2C] or vehicle-to-home [V2H]
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Abstract
The application discloses a satellite communication method and a satellite communication device for resisting non-stationary rotating speed shielding, wherein the method comprises the following steps: when the rotating speed of the helicopter changes, calculating according to the rotating speed to obtain a shielding time interval and a sending time interval; determining non-shielding time and shielding time according to the shielding time interval and the sending time interval, and sending data to the master station in the non-shielding time; and sending the shielding time interval, the sending time interval and the shielding time to the master station, and receiving adjusted frame data sent by the master station, wherein the adjusted frame data is obtained by adjusting initial frame data sent by the master station according to the shielding time interval, the sending time interval and the preset shielding time. The method and the device solve the technical problems that in the prior art, due to the change of the rotating speed of the airplane, communication is interrupted and the service efficiency of the satellite bandwidth is low.
Description
Technical Field
The application relates to the technical field of satellite communication, in particular to a satellite communication method and device for resisting non-stable rotating speed blocking.
Background
Because the installation position of the satellite antenna of the existing helicopter platform is limited, the satellite antenna can only be installed below the rotor, and the satellite antenna is shielded when the rotor rotates, so that the data forward link data receiving and the data reverse link data sending are influenced. Therefore, the problem that satellite communication antenna beams are shielded by the rotor of the helicopter is urgently needed to be solved, and stable and reliable satellite communication application on the helicopter is realized.
At present, in order to avoid the influence of the change of the course and the attitude of an airplane on the communication quality and the communication efficiency in the flight process of a helicopter, a design scheme combining an outer channel interleaver and a forward error correction code is often adopted, or a helicopter satellite communication system adopts a method of framing retransmission, diversity transmission and combination and a gap communication strategy to carry out rotor-wing-shielding-resistant communication, namely, an algorithm is adopted to process communication signals to carry out rotor-wing-shielding-resistant communication. However, in the prior art, when the communication signal is processed by an algorithm to resist the rotor-wing blocking, only the influence of the rotor-wing blocking on the communication signal is considered, and the problems of the satellite channel utilization rate, the bandwidth, the transmission reliability and the like of the change of the aircraft rotating speed are not considered.
Disclosure of Invention
The technical problem that this application was solved is: aiming at the problems of communication interruption and low satellite bandwidth utilization efficiency caused by the change of the rotating speed of an airplane in the prior art, the application provides a satellite communication method and a satellite communication device for resisting non-stable rotating speed blocking.
In a first aspect, an embodiment of the present application provides a satellite communication method for resisting non-stationary rotation speed blocking, which is applied to a helicopter satellite communication system, where the system includes a satellite, a master station, and an onboard station, and the method includes:
when the rotating speed of the helicopter changes, calculating according to the rotating speed to obtain a shielding time interval and a sending time interval;
determining non-shielding time and shielding time according to the shielding time interval and the sending time interval, and sending data to the master station in the non-shielding time;
and sending the shielding time interval, the sending time interval and the shielding time to the master station, and receiving adjusted frame data sent by the master station, wherein the adjusted frame data is obtained by adjusting initial frame data sent by the master station according to the shielding time interval, the sending time interval and the preset shielding time.
In the scheme provided by the embodiment of the application, when the rotating speed of the helicopter changes, a shielding time interval and a sending time interval are calculated according to the rotating speed; determining non-occlusion time and occlusion time according to the occlusion time interval and the sending time interval, and sending data to the master station within the non-occlusion time; and sending the shielding time interval, the sending time interval and the shielding time to the master station, and receiving adjusted frame data sent by the master station, wherein the adjusted frame data is determined by the non-shielding time and the shielding time. Therefore, in the scheme provided by the embodiment of the application, when the rotating speed of the helicopter changes, the data is sent to the main station within the non-shielding time and the initial frame data sent by the main station is adjusted according to the non-shielding time and the shielding time, so that the communication efficiency of a reverse link is improved, the satellite bandwidth is saved, the data frame structure of a forward link can be adjusted in real time according to the rotating speed of the airplane, the problem of communication interruption caused by the change of the rotating speed of the airplane is avoided, and the reliability of data transmission is ensured.
Optionally, calculating an occlusion time interval and a transmission time interval according to the rotation speed includes:
if a data interface exists between the airborne station and the avionics system, transmitting the current helicopter rotating speed to a satellite, and receiving a shielding time interval and a transmitting time interval which are calculated by the satellite based on the rotating speed; or
And if no data interface exists between the airborne station and the avionics system, calculating the shielding time and the sending time interval according to the rotating speed.
Optionally, sending data to the master station within the non-occluded time includes:
determining the total length, the effective data length and the test length of the data according to the non-shielding time, and determining the data according to the total length, the effective data length and the test length of the data;
and transmitting the data to a master station in the non-shielded time.
Optionally, the initial frame data comprises: the device comprises a plurality of first frames and a plurality of second frames, wherein the first frames comprise two second frames, and the two second frames are any original frame and a copied frame copied by the original frame respectively.
Optionally, a length of each second frame in the adjusted frame data is greater than the occlusion time interval, and a length of each first frame is greater than the occlusion time.
Optionally, the primary station transmits the initial frame data and the adjusted frame data in a broadcast form.
Optionally, the method further comprises: and if the data of the rear half part of the original frame in the adjusted frame data is shielded, the data of the front half part of the copied frame data is shielded, and the complete data is restored in a merging mode.
In a second aspect, an embodiment of the present application provides a satellite communication device resistant to non-stationary rotation speed blocking, the device including:
the calculating unit is used for calculating and obtaining a shielding time interval and a sending time interval according to the rotating speed when the rotating speed of the helicopter changes;
the determining unit is used for determining non-occlusion time and occlusion time according to the occlusion time interval and the sending time interval, and sending data to the master station in the non-occlusion time;
and a transceiver unit, configured to send the blocking time interval, the sending time interval, and the blocking time to the master station, and receive adjusted frame data sent by the master station, where the adjusted frame data is obtained by adjusting initial frame data sent by the master station according to the blocking time interval, the sending time interval, and a preset blocking time.
Optionally, the computing unit is specifically configured to:
if a data interface exists between the airborne station and the avionic system, sending the current helicopter rotating speed to a satellite, and receiving a shielding time interval and a sending time interval which are calculated by the satellite based on the rotating speed; or
And if no data interface exists between the airborne station and the avionic system, calculating the shielding time and the sending time interval according to the rotating speed.
Optionally, the transceiver unit is specifically configured to:
determining the total length, the effective data length and the test length of the data according to the non-shielding time, and determining the data according to the total length, the effective data length and the test length of the data;
and transmitting the data to a master station in the non-shielded time.
Optionally, the initial frame data comprises: the first frames comprise two second frames, wherein the two second frames are any original frame and a copied frame copied by the original frame respectively.
Optionally, the length of each second frame in the adjusted frame data is greater than the occlusion time interval, and the length of each first frame is greater than the occlusion time.
Optionally, the primary station transmits the initial frame data and the adjusted frame data in a broadcast form.
Optionally, the determining unit is further configured to: and if the data of the rear half part of the original frame in the adjusted frame data is shielded, the data of the front half part of the copied frame data is shielded, and the complete data is restored in a merging mode.
Drawings
Fig. 1 is a schematic flowchart of a satellite communication method for resisting non-stationary rotation speed blocking according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of a helicopter satellite communication system provided in an embodiment of the present application;
fig. 3 is a schematic structural diagram of data transmitted by an airborne station according to an embodiment of the present application;
FIG. 4 is a diagram illustrating forward link data frame transmit times according to an embodiment of the present application;
fig. 5 is a schematic structural diagram of an airborne station recovery data according to an embodiment of the present application;
fig. 6 is a schematic structural diagram of a satellite communication device resistant to non-stationary rotation speed blocking according to an embodiment of the present disclosure.
Detailed Description
In the solutions provided in the embodiments of the present application, the described embodiments are only a part of the embodiments of the present application, and not all of the 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 order to better understand the technical solutions of the present application, the following detailed descriptions are provided with accompanying drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and in a case of no conflict, the technical features in the embodiments and examples of the present application may be combined with each other.
The following describes in further detail a non-stationary rotation speed obstruction resistant satellite communication method provided in an embodiment of the present application with reference to the drawings in the specification, where the method is applied to a helicopter satellite communication system, where the system includes a satellite, a master station, and an onboard station, and a specific implementation manner of the method may include the following steps (a method flow is shown in fig. 1):
step 101, when the rotating speed of the helicopter changes, calculating according to the rotating speed to obtain a shielding time interval and a sending time interval.
And 102, determining non-occlusion time and occlusion time according to the occlusion time interval and the transmission time interval, and transmitting data to the master station in the non-occlusion time.
103, sending the blocking time interval, the sending time interval and the blocking time to the master station, and receiving adjusted frame data sent by the master station, where the adjusted frame data is obtained by adjusting initial frame data sent by the master station according to the blocking time interval, the sending time interval and the preset blocking time.
In particular, referring to fig. 2, a helicopter satellite communication system provided by the embodiment of the present application includes a satellite 1, a master station 2 and an onboard station 3, where the master station 2 is a ground station communicating with the satellite. The helicopter satellite communication system comprises two communication links, namely a forward link and a reverse link, wherein the forward link refers to a communication link between a master station 2 and an airborne station 3, and the reverse link refers to a communication link between the airborne station 3 and the master station 2. When the rotation speed of the helicopter changes, the communication quality of the forward link and the reverse link is affected, and therefore, in order to improve the communication quality, consideration is given below to both the forward link and the reverse link, respectively.
1. Reverse link
In the scheme provided by the embodiment of the application, in order to improve the transmission efficiency, the data frame structure sent by the main station to the onboard station is changed according to the change of the rotating speed of the helicopter.
Further, when the rotating speed of the helicopter changes, in order to change the data frame structure of the master station transmitted to the onboard station, the shielding time interval and the transmitting time interval need to be calculated according to the rotating speed of the helicopter. Because a data interface may exist between the onboard station and the avionic system or may not exist, the shielding time interval and the sending time interval obtained by calculation according to the rotating speed of the helicopter under different conditions are different in mode.
In a possible implementation manner, calculating the occlusion time interval and the transmission time interval according to the rotation speed includes: if a data interface exists between the airborne station and the avionic system, sending the current helicopter rotating speed to a satellite, and receiving a shielding time interval and a sending time interval which are calculated by the satellite based on the rotating speed; or if no data interface exists between the airborne station and the avionics system, calculating the shielding time and the sending time interval according to the rotating speed.
Specifically, if a data interface exists between the onboard station and the avionics, the onboard station sends the rotating speed of the helicopter to the satellite modem through the avionics interface, and an occlusion time calculation module of the satellite modem calculates an occlusion time interval and a sending time interval and sends data to the master station by using the unoccluded time; if no data interface exists between the onboard station and the avionics, a frame sending module of the master station sends initial frame data to a modem of the onboard station, the modem of the onboard station demodulates the data, calculates an occlusion time interval and a sending time interval through an internal occlusion time detection module, and sends the data to the master station by using the unoccluded time.
Further, in order to improve the utilization rate of the bandwidth, there are various ways for the onboard station to send data to the master station by using the non-blocked time, and a preferred way is taken as an example for description below.
In one possible implementation, transmitting data to a primary station during the non-occlusion time includes: determining the total length, the effective data length and the test length of the data according to the non-shielding time, and determining the data according to the total length, the effective data length and the test length of the data; and transmitting the data to a master station in the non-shielded time.
In the scheme provided by the embodiment of the application, the data length of the returned data is determined by the reverse link according to the shielding time, so that the returned data can be sent to the master station within the non-shielding time, and further the bandwidth utilization rate is improved. Referring to fig. 3, a schematic structural diagram of data transmitted by an airborne station according to an embodiment of the present application is provided.
2. Forward link
Specifically, in the solution provided in this embodiment of the present application, after the on-board station receives the blocking time interval and the sending time interval sent by the satellite or calculates the blocking time interval and the sending time interval by itself, the blocking time interval and the sending time interval are sent to the master station, the master station adjusts its initial frame data structure according to the blocking time interval and the sending time interval to obtain adjusted frame data, and then sends the adjusted frame data to the on-board station, thereby implementing reverse link communication of the communication system.
Further, in the solution provided in the embodiment of the present application, there are multiple formats of initial frame data sent by the master station to the onboard station, and a preferred example is described below.
In one possible implementation, the initial frame data includes: the device comprises a plurality of first frames and a plurality of second frames, wherein the first frames comprise two second frames, and the two second frames are any original frame and a copied frame copied by the original frame respectively.
Further, in the solution provided in the embodiment of the present application, in order to improve the transmission efficiency, there are various types of adjusted frame formats, and a preferred example is described below.
In a possible implementation manner, the length of each second frame in the adjusted frame data is greater than the occlusion time interval, and the length of each first frame is greater than the occlusion time.
Further, in a possible implementation manner, the primary station transmits the initial frame data and the adjusted frame data in a broadcast manner.
Specifically, the forward link information is broadcast data, generally signaling information and scheduling command information, and the data rate is relatively low, but the requirement on reliability is high, so that a time transmit diversity technique is adopted. When the master station designs a frame structure, each original frame (original data) is copied as a unit to obtain a copied frame (diversity data), the 2 small frames jointly form a large frame, and meanwhile, in order to avoid the situation that the small frame data is completely shielded, the length of one frame is ensured to be greater than shielding time when the small frame is designed, and the length of the large frame is smaller than a shielding period, so that the situation that the data is shielded for 2 times or more in one large frame cannot occur, and the situation that the data is lost at a receiving end is ensured not to occur. When the rotating speed of the airplane changes, the onboard station calculates the shielding time and sends the shielding time to the main station, and the main station adjusts the frame lengths of the small frame and the large frame according to the rotating speed change so as to adapt to different rotating speed changes of the airplane. When the rotating speed of the airplane changes, the airborne station can demodulate forward data accurately. Referring to fig. 4, a diagram of forward link data frame transmission time provided in the embodiment of the present application is shown.
Further, referring to fig. 5, in a possible implementation manner, the method further includes: and if the data of the second half part of the original frame in the adjusted frame data is shielded, the data of the first half part of the copied frame data is shielded, and the complete data is recovered in a merging mode.
In the scheme provided by the embodiment of the application, when the rotating speed of the helicopter changes, a shielding time interval and a sending time interval are calculated according to the rotating speed; determining non-occlusion time and occlusion time according to the occlusion time interval and the sending time interval, and sending data to the master station within the non-occlusion time; and sending the shielding time interval, the sending time interval and the shielding time to the master station, and receiving adjusted frame data sent by the master station, wherein the adjusted frame data is determined by the non-shielding time and the shielding time. Therefore, in the scheme provided by the embodiment of the application, when the rotating speed of the helicopter changes, the data is sent to the main station within the non-shielding time and the initial frame data sent by the main station is adjusted according to the non-shielding time and the shielding time, so that the communication efficiency of a reverse link is improved, the satellite bandwidth is saved, the data frame structure of a forward link can be adjusted in real time according to the rotating speed of the airplane, the problem of communication interruption caused by the change of the rotating speed of the airplane is avoided, and the reliability of data transmission is ensured.
Based on the same inventive concept as the method shown in fig. 1, the embodiment of the present application provides a satellite communication device resisting non-stationary rotation speed blocking, referring to fig. 6, the device includes:
the calculating unit 601 is configured to calculate a shielding time interval and a sending time interval according to a rotating speed of the helicopter when the rotating speed of the helicopter changes;
a determining unit 602, configured to determine non-occlusion time and occlusion time according to the occlusion time interval and the transmission time interval, and send data to the master station within the non-occlusion time;
a transceiver 603, configured to send the occlusion time interval, the transmission time interval, and the occlusion time to the master station, and receive adjusted frame data sent by the master station, where the adjusted frame data is obtained by adjusting initial frame data sent by the master station according to the occlusion time interval, the transmission time interval, and preset occlusion time.
Optionally, the calculating unit 601 is specifically configured to:
if a data interface exists between the airborne station and the avionic system, sending the current helicopter rotating speed to a satellite, and receiving a shielding time interval and a sending time interval which are calculated by the satellite based on the rotating speed; or
And if no data interface exists between the airborne station and the avionic system, calculating the shielding time and the sending time interval according to the rotating speed.
Optionally, the transceiver 603 is specifically configured to:
determining the total length, the effective data length and the test length of the data according to the non-shielding time, and determining the data according to the total length, the effective data length and the test length of the data;
and transmitting the data to a master station in the non-shielded time.
Optionally, the initial frame data comprises: the first frames comprise two second frames, wherein the two second frames are any original frame and a copied frame copied by the original frame respectively.
Optionally, a length of each second frame in the adjusted frame data is greater than the occlusion time interval, and a length of each first frame is greater than the occlusion time.
Optionally, the primary station transmits the initial frame data and the adjusted frame data in a broadcast form.
Optionally, the determining unit 602 is further configured to: and if the data of the second half part of the original frame in the adjusted frame data is shielded, the data of the first half part of the copied frame data is shielded, and the complete data is recovered in a merging mode.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, 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, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. 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.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (7)
1. A satellite communication method for resisting non-stationary rotating speed blocking is applied to a helicopter satellite communication system, the system comprises a satellite, a main station and an onboard station, and is characterized by comprising the following steps:
when the rotating speed of the helicopter changes, calculating to obtain a shielding time interval and a sending time interval according to the rotating speed; if a data interface exists between the onboard station and the avionics, the onboard station sends the rotating speed of the helicopter to the satellite modem through the avionics interface, and the satellite modem calculates an occlusion time interval and a sending time interval and sends data to the main station by using the unoccluded time; if no data interface exists between the onboard station and the avionics, the master station sends initial frame data to a modem of the onboard station, the modem of the onboard station demodulates the data, calculates an occlusion time interval and a sending time interval at the same time, and sends the data to the master station by using the unoccluded time;
the method comprises the steps that after an onboard station receives an occlusion time interval and a transmission time interval sent by a satellite or calculates the occlusion time interval and the transmission time interval by the onboard station, the occlusion time interval and the transmission time interval are sent to a master station, the master station adjusts an initial frame data structure according to the occlusion time interval and the transmission time interval to obtain adjusted frame data, and then the adjusted frame data are sent to the onboard station.
2. The method of claim 1, transmitting data to a primary station during the unoccluded time, comprising:
determining the total length, the effective data length and the test length of the data according to the non-shielding time, and determining the data according to the total length, the effective data length and the test length of the data;
and transmitting the data to a master station in the non-shielded time.
3. The method of claim 2, wherein the initial frame data comprises: the device comprises a plurality of first frames and a plurality of second frames, wherein the first frames comprise two second frames, and the two second frames are any original frame and a copied frame copied by the original frame respectively.
4. The method of claim 3, wherein each of the second frames in the adjusted frame data has a length greater than the occlusion time interval and each of the first frames has a length greater than the occlusion time.
5. The method of claim 4, wherein the primary station transmits the initial frame data and the adjusted frame data in a broadcast.
6. The method of claim 5, further comprising: and if the data of the rear half part of the original frame in the adjusted frame data is shielded, the data of the front half part of the copied frame data is shielded, and the complete data is restored in a merging mode.
7. A non-stationary speed obscuration resistant satellite communication device, comprising:
the calculating unit is used for calculating and obtaining a shielding time interval and a sending time interval according to the rotating speed when the rotating speed of the helicopter changes;
the determining unit is used for determining the non-shielding time and the shielding time according to the shielding time interval and the sending time interval and sending data to the master station in the non-shielding time;
a transceiver unit, configured to send the blocking time interval, the sending time interval, and the blocking time to the master station, and receive adjusted frame data sent by the master station, where the adjusted frame data is obtained by adjusting initial frame data sent by the master station according to the blocking time interval, the sending time interval, and preset blocking time;
if a data interface exists between the airborne station and the avionics system, transmitting the current helicopter rotating speed to a satellite, and receiving a shielding time interval and a transmitting time interval which are calculated by the satellite based on the rotating speed; or
If no data interface exists between the airborne station and the avionic system, calculating the shielding time and the sending time interval according to the rotating speed;
determining the total length, the effective data length and the test length of the data according to the non-shielding time, and determining the data according to the total length, the effective data length and the test length of the data;
and transmitting the data to a master station in the non-shielded time.
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| CN111924128A (en) * | 2020-06-30 | 2020-11-13 | 南京天际易达通信技术有限公司 | Helicopter satellite communication rotor wing shielding resistance key technology research method |
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| CN112468218A (en) | 2021-03-09 |
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