CN113405409A - Mode switching method and system based on rocket measurement and control communication system - Google Patents
Mode switching method and system based on rocket measurement and control communication system Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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Abstract
The invention discloses a mode switching method and a mode switching system based on a rocket measurement and control communication system, wherein the method comprises the following steps: acquiring a mode switching instruction of the rocket measurement and control communication system and/or acquiring current attitude information of a carrier rocket; determining a target working mode of the carrier rocket according to the mode switching instruction and/or the current attitude information; and switching the current working mode of the carrier rocket to the target working mode for data communication. By adopting the method and the device, the technical problems that the reliable communication requirement of special tasks cannot be met and the data transmission requirement under special conditions in the prior art and the like can be solved.
Description
Technical Field
The invention relates to the technical field of carrier rockets, in particular to a mode switching method and system based on a rocket measurement and control communication system.
Background
At present, a carrier rocket adopts a ground remote control station for remote control tracking, or adopts the ground remote control station as a main part and a space-based control station as an auxiliary part to finish remote measurement tracking in the process from launching of the carrier rocket to off-orbit. Along with the requirement of launching operation service level, the image requirement is more and more obvious, the launching of the carrier rocket is along with the investment and operation of relay satellites in China, space-based measurement and control gradually play an important role in the launching of the carrier rocket, and the measurement and control arc section of the rocket can be increased.
When the space-based measurement and control is adopted, a relay satellite which is stationary in a geosynchronous orbit is generally adopted. Because the transmission distance of the space-based measurement and control is long, the reliable communication requirement of special task transmission cannot be met when the carrier works abnormally, or the data transmission requirement cannot be met under the condition of meeting the special communication requirement. Therefore, a highly reliable data communication system is required.
Disclosure of Invention
By providing the mode switching method based on the rocket measurement and control communication system, the embodiments of the application can solve the problems that the reliable communication requirement of special tasks and the data transmission requirement under special conditions cannot be met in the prior art, and realize the reliable data transmission under different working modes.
On one hand, the present application provides a mode switching method based on a rocket measurement and control communication system through an embodiment of the present application, and the method is specifically applied to a measurement and control center unit of the rocket measurement and control communication system, and the method specifically includes:
acquiring a mode switching instruction of a rocket measurement and control communication system and/or acquiring current attitude information of a carrier rocket;
determining a target working mode of the carrier rocket according to the mode switching instruction and/or the current attitude information;
and switching the current working mode of the carrier rocket to the target working mode for data communication.
Optionally, if the current operating mode is a preset first mode, before the obtaining of the mode switching instruction of the rocket measurement and control communication system, the method further includes:
acquiring the flight time of the carrier rocket in the current task stage and binding parameters, wherein the binding parameters are used for representing the threshold value which can be accepted by the current task stage;
if the flight time is less than or equal to the binding parameter, maintaining the current working mode of the carrier rocket;
and if the flight time is greater than the binding parameter, switching the current working mode to a preset second mode.
Optionally, the determining, according to the mode switching instruction and/or the current attitude information, a target operating mode of the launch vehicle specifically includes:
if the mode switching instruction is used for indicating to switch to a preset third mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset third mode; alternatively, the first and second electrodes may be,
if the mode switching instruction is used for indicating to switch to a preset fourth mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset fourth mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
Optionally, if the current working mode is a preset third mode, the determining the target working mode of the launch vehicle according to the mode switching instruction and/or the current attitude information specifically includes:
if the mode switching instruction is used for indicating to switch to a preset second mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset second mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
Optionally, if the current working mode is a preset fourth mode, the determining the target working mode of the launch vehicle according to the mode switching instruction and/or the current attitude information specifically includes:
if the mode switching instruction is used for indicating to switch to a preset second mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset second mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
Optionally, if the current working mode is a preset fifth mode, the determining the target working mode of the launch vehicle according to the mode switching instruction and/or the current attitude information specifically includes:
if the mode switching instruction is used for indicating to switch to a preset third mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset third mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is a preset fourth mode.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset first mode, the method further includes:
and opening a power amplifier in the rocket measurement and control communication system, controlling the phased array antenna to transmit data with corresponding power according to the code rate of the data to be transmitted of the first transmitting channel in the first mode, and controlling the second transmitting channel to transmit data in a relay satellite S-band multiple access SMA mode.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset second mode, the method further includes:
and closing a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to transmit data with high power and narrow wave speed according to the high-code-rate data transmitted by the first transmitting channel in the second mode, and controlling the second transmitting channel to transmit data in a relay satellite S-band multiple access (SMA) mode.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset third mode, the method further includes:
and closing a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to perform low-power and wide-wave-speed data transmission according to the low-code-rate data transmitted by the first transmitting channel in the third mode, and controlling the second transmitting channel to perform data transmission in a relay satellite S-band multiple access (SMA) mode.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset fourth mode, the method further includes:
and opening a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to transmit data with high power and narrow wave speed according to the high-code-rate data transmitted by the first transmitting channel in the fourth mode, and controlling the second transmitting channel to transmit data in a relay satellite S-band multiple access SMA mode.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset fifth mode, the method further includes:
and opening a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to perform low-power and wide-wave-speed data transmission according to the low-code-rate data transmitted by the first transmitting channel in the fifth mode, and controlling the second transmitting channel to perform data transmission under a relay satellite S-band multiple access SMA system.
On the other hand, according to an embodiment of the present application, a rocket measurement and control communication system is provided, which includes a central computer, an inertial integrated navigation, a measurement and control central unit, at least one combiner, a power amplifier, and a phased array antenna, where the measurement and control central unit is specifically configured to execute the above-mentioned mode switching method based on the rocket measurement and control communication system.
On the other hand, the present application further provides a rocket measurement and control communication system (specifically, a measurement and control center unit in the system) according to an embodiment of the present application, including: the device comprises an acquisition module, a determination module and a switching module, wherein:
the acquisition module is used for acquiring a mode switching instruction of the rocket measurement and control communication system and/or acquiring current attitude information of a carrier rocket;
the determining module is used for determining a target working mode of the carrier rocket according to the mode switching instruction and/or the current attitude information;
the switching module is used for switching the current working mode of the carrier rocket to the target working mode for data communication.
For the rocket measurement and control communication system (or measurement and control center unit) introduced in the embodiment of the present application, reference may be specifically made to the related descriptions in the foregoing mode switching method embodiment based on the rocket measurement and control communication system, and details are not described here again.
In another aspect, the present application further provides a computer-readable storage medium, which includes computer instructions, when the computer instructions are executed on a terminal, the terminal executes the mode switching method based on the rocket measurement and control communication system provided above.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages: the method comprises the steps that a measurement and control center unit in the rocket measurement and control communication system is used for detecting and acquiring a mode switching instruction of the system and/or acquiring current attitude information of a carrier rocket; and determining a target working mode required by the carrier rocket according to the mode switching instruction and/or the current attitude information, and finally switching the current working mode of the carrier rocket to the target working mode for corresponding data transmission. Therefore, the problems that the reliable communication requirement or the data transmission requirement of a special task cannot be met in the prior art are solved, and the reliability and the safety of data transmission can be improved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a rocket measurement and control communication system provided in an embodiment of the present application.
Fig. 2 is a schematic flowchart of a mode switching method based on a rocket measurement and control communication system according to an embodiment of the present application.
Fig. 3 is a schematic flowchart of another mode switching method based on a rocket measurement and control communication system according to an embodiment of the present application.
Fig. 4 is a state diagram of mode switching according to an embodiment of the present disclosure.
Fig. 5 is a schematic structural diagram of a measurement and control center unit provided in an embodiment of the present application.
Detailed Description
The embodiment of the application provides a mode switching method based on a rocket measurement and control communication system, and solves the technical problems that the reliable communication requirement or the data transmission requirement of a special task cannot be met in the prior art.
In order to solve the technical problems, the general idea of the embodiment of the application is as follows: the application provides a rocket measurement and control communication system, which comprises a central computer, an inertial integrated navigation and measurement and control central unit and other functional equipment (such as a single machine) which are coupled and connected through a bus. The system comprises a measurement and control central unit, a rocket measurement and control communication system and a carrier rocket, wherein the measurement and control central unit can acquire a mode switching instruction of the rocket measurement and control communication system and/or current attitude information of the carrier rocket; and then determining a target working mode in which the carrier rocket needs to be positioned according to the mode switching instruction and/or the current attitude information, and finally switching the carrier rocket from the current working mode to the target working mode to perform corresponding data transmission so as to meet the reliable communication requirement and the data transmission requirement of a special task, thereby ensuring the high reliability and the safety of data transmission.
In order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the specific embodiments.
First, it is stated that the term "and/or" appearing herein is merely one type of associative relationship that describes an associated object, meaning that three types of relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
Please refer to fig. 1, which is a schematic structural diagram of a rocket measurement and control communication system provided in an embodiment of the present application. As shown in fig. 1, the rocket measurement and control communication system 100 includes a central computer 101, an inertial integrated navigation system 102, other single machines 103, a measurement and control central unit 104, at least one combiner 105 (only 2 are shown as an example, but not limited to the example), a phased array antenna 106, and a power amplifier 107. These components can be coupled and connected by a bus, for example, the central computer 101, the inertial integrated navigation system 102, the other single machines 103 and the measurement and control center unit 104 can be coupled and connected by an arrow bus. The arrow bus is a data transmission channel, and may be a Controller Area Network (CAN) bus, a 1553 bus, a Time-Triggered Ethernet (TTE) bus, or another bus.
The central computer 101 is a central control core of the rocket measurement and control communication system, and implements functions of rocket control, trajectory online planning, information interaction, calculation, processing and the like in charge of a carrier rocket. When performing trajectory replanning, the central computer 101 may replan the mission and send a mode switching command to the measurement and control central unit 104 to switch the working mode of the launch vehicle.
The inertial integrated Navigation System 102 is a Navigation System that is controlled by a monitor and a computer, which integrates various Navigation devices, such as Global Positioning System (GPS) inertial integrated Navigation, BeiDou Navigation Satellite System (BDS), and the like, and the drawings only illustrate the GPS/BD inertial integrated Navigation System as an example, and may be other integrated Navigation systems, which are not limited in the present application. The inertial integrated navigation system 102 is used for providing position and attitude information for a carrier rocket and outputting a result to a bus on the rocket for other single machines 103.
The measurement and control center unit 104 can realize attitude control, time sequence control of the carrier rocket, coordination work of each component in the control system and the like. The measurement and control center unit 104 includes an integrated baseband module, but is not limited to the integrated baseband module, and may also include modules for sensor power supply, sensor information acquisition, and data integration. The integrated baseband module is designed by adopting a software radio architecture and comprises two receiving channels and two transmitting channels.
The combiners 105 are connected to the receiving antennas, wherein the number of the antennas connected to each combiner 105 is not limited, and the illustration only illustrates that each combiner 105 is connected to 2 receiving antennas, and in practical application, the number of the combiners 105 configured in the system is not limited, and the illustration illustrates 2 combiners 105. The rocket measurement and control communication system 100 is further provided with a phased array antenna 106 for space-based measurement and control, which is used for transmitting data in a long distance, and specifically can change the direction of the maximum value of an antenna directional pattern through controlling the phase, so as to achieve the purpose of beam scanning. The phased array antenna 106 may be composed of an antenna array, a transmitting component channel, a wave control panel, a power module and a structural member, has a high-power small-beam directional power or a low-power large-beam function, and can be switched according to a mode switching instruction obtained by the measurement and control center unit 104 to realize switching of different working states.
The rocket measurement and control communication system 100 is further provided with a power amplifier 107, the power amplifier 107 is connected with at least one S-band transmitting antenna, and the two transmitting antennas are taken as an example in the figure, so as to amplify the signal to sufficient power, and then the signal is transmitted by the S-band transmitting antenna connected with the power amplifier via a matching network. In this example, the power amplifier 107 is a filter amplifier for S-band radio Frequency signals, and is composed of a sound meter filter, a pre-stage amplifier, a power divider, a power amplifier, a coupling, an isolation and a cavity filter, and can turn off the amplifier according to an external instruction, and the working Frequency point, the bandwidth and the gain of the amplifier can meet the requirements of a large dynamic Pulse Code/Frequency Code (PCM-FM) Modulation and the working Frequency band of a relay satellite S-band multiple access SMA system.
In practical application, the rocket measurement and control communication system 100 is configured with 5 operating modes, each combiner 105 corresponds to one receiving channel, each transmitting antenna corresponds to one transmitting channel, and the rocket measurement and control communication system 100 related to the drawing corresponds to two transmitting channels (specifically, a first transmitting channel and a second transmitting channel) and two receiving channels (specifically, a first receiving channel and a second receiving channel). The first transmitting channel is used for space-based measurement and control transmission, and the working frequency point of the first transmitting channel is f0High code rate code stream data can be output according to selection (mode) during baseband transmission) And low bit rate code stream data (mode). The working system corresponding to the high-rate mode is Binary Phase Shift Keying (BPSK) and cascaded convolutional (RS) coding, or Quadrature Phase Shift Keying (QPSK) and Low-Density Parity Check Code (LDPC) coding, and in the Low-rate mode, the working system is BPSK and Code Division Multiple Access (CDMA) system, and data is modulated and then output to a phased array antenna for space-based measurement and control, and the pointing direction of the phased array antenna is adjusted according to the posture. The second transmitting channel is used for multi-mode communication and adopts a PCM-FM modulation system, and the working frequency point of the second transmitting channel is f1(ii) a The second transmitting channel also supports the work of SMA system, and the working frequency point is f2. The first receiving channel adopts SMA system, and its working frequency point is f2The system is used for receiving forward data of an SMA system, uploading instructions, ground safety control and the like; the second receiving channel supports the operation under BPSK and CDMA standard, and the working frequency point is f3The device is used for receiving the ground uplink data, transmitting the uplink channel data and the like.
Referring to fig. 2, a schematic flow chart of a mode switching method based on a rocket measurement and control communication system 100 shown in the figure is provided in an embodiment of the present application. The method shown in fig. 2 is applied to the measurement and control center unit 104 in the rocket measurement and control communication system 100, and specifically includes the following implementation steps:
s201, the measurement and control center unit 104 obtains a mode switching instruction of the rocket measurement and control communication system 100 and/or obtains current attitude information of the carrier rocket.
The mode switching instruction is an instruction for requesting to switch a current working mode of the rocket measurement and control communication system 100 to a preset target working mode, and the target working mode is different from the current working mode. In practical application, the mode switching instruction may be specifically generated by user operation triggering, and may also be obtained by system automatic detection, which is not limited in this application.
S202, determining a target working mode of the carrier rocket according to the mode switching instruction and/or the current attitude information.
The target working mode may be determined according to the mode switching instruction and/or the current posture information, and the target working mode (or the current working mode) includes, but is not limited to, any one of the following: the method comprises a first mode, a second mode, a third mode, a fourth mode and a fifth mode which are preset. The five operation modes can be specifically set by a system or a user, and the specific operation modes or conditions thereof will be described in detail below.
In one embodiment, the target working mode required to be switched currently can be determined only according to a mode switching instruction received by the system, for example, if the mode switching instruction is used for instructing to switch from a current first mode to a second mode, the mode can be directly switched to the second mode; the target working mode to be switched may also be determined only according to the acquired current attitude information, and the target working mode to be switched may also be determined according to the acquired mode switching instruction and the current attitude information, which is not limited in this application.
S203, switching the current working mode of the carrier rocket to the target working mode for data communication so as to adapt to reliable communication requirements of different special tasks or data transmission requirements under the special task condition and the like.
In some embodiments, if the current operating mode is a first mode (may also be referred to as an operating mode 1), the mode switching method based on the rocket measurement and control communication system may specifically refer to fig. 3, which specifically includes the following implementation steps:
s301, the measurement and control center unit 104 obtains the flight time and binding parameters of the carrier rocket in the current mission stage. The binding parameter is used to indicate a maximum time threshold acceptable for performing the flight of the current mission phase. In practical application, the binding parameters of the carrier rocket corresponding to different task stages may be different or the same, and the application is not limited.
S302, in the first mode, determining whether the flight time is greater than the binding parameter (may also be referred to as a binding value).
S303, if the flight time is less than or equal to the binding parameter, maintaining the current working mode unchanged, and outputting the current working mode.
S304, if the flight time is larger than the binding parameter, switching the first mode to a preset second mode.
S305, judging whether a mode switching instruction of the rocket measurement and control communication system is received.
When the measurement and control center unit 104 determines that the mode switching instruction is not received, the method continues to execute step S306; when the mode switching instruction is received, the step S306 is still executed.
S306, acquiring the current attitude information of the carrier rocket.
And S307, selecting and switching modes according to the mode switching instruction and/or the current posture information.
After the mode switching instruction and/or the current attitude information are/is obtained, a target working mode corresponding to the mode switching instruction and/or the current attitude information can be determined according to the obtained information, and then the current working mode of the system is switched to the target working mode.
Please refer to fig. 4, which illustrates a state diagram of mode switching. Fig. 4 shows the conditions that need to be satisfied for switching 5 operation modes from one to another, that is, the target operation mode that can be determined according to the mode switching instruction and/or the current posture information. As shown in fig. 4, if the current operating mode is the first mode (may be referred to as mode 1 for short), the target operating mode can be determined only by determining whether the flight time is greater than the binding parameter (binding value), and specifically, when the flight time is less than or equal to the binding value, the target operating mode is still the first mode; if the flight time is greater than the binding value, the target operation mode is the second mode (may be simply referred to as mode 2), and the system may switch the first mode to the second mode.
And if the current working mode is the second mode, determining a target working mode required to be switched in the second mode at the moment according to the acquired mode switching instruction and/or the current attitude information of the carrier rocket. Specifically, if only the current attitude information is used to indicate that the attitude of the launch vehicle is normal, the second mode is maintained, i.e., the target operating mode is still the second mode. If the mode switching instruction is used for indicating to switch to a preset third mode (namely, a mode 3 switching instruction), and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode is the third mode (which may be referred to as mode 3 for short). If the mode switching instruction is used for instructing to switch to a preset fourth mode (that is, the mode switching instruction is a mode 4 instruction), and the current attitude information is used for instructing that the attitude of the launch vehicle is normal, it is determined that the target working mode is the fourth mode (which may be simply referred to as mode 4). If only the current attitude information is used for indicating the attitude abnormality or no attitude (information) of the carrier rocket, and no attitude information indicates that the carrier rocket is in a static state or has no any changed attitude, the target working mode is determined to be the fifth mode (which may be simply referred to as mode 5).
If the current working mode is the third mode, the target working mode required to be switched in the third mode can be determined according to the acquired mode switching instruction and/or the current attitude information of the carrier rocket. Specifically, if only the current attitude information is used to indicate that the attitude of the launch vehicle is normal, the third mode is maintained, that is, the target operating mode is still the third mode. And if the mode switching instruction is used for indicating to switch to a preset second mode (namely, a mode 2 switching instruction), and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode is the second mode. And if only the current attitude information is used for indicating the abnormal attitude or no attitude of the carrier rocket, determining that the target working mode is a fifth mode.
If the current working mode is the fourth mode, the target working mode required to be switched in the fourth mode can be determined according to the acquired mode switching instruction and/or the current attitude information of the carrier rocket. Specifically, if only the current attitude information is used for indicating that the attitude of the launch vehicle is normal, the target working mode is determined to be the fourth mode. And if the mode switching instruction is used for indicating to switch to a second mode (namely, the mode 2 switching instruction), and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode is the second mode. And if only the current attitude information is used for indicating the abnormal attitude or no attitude of the carrier rocket, determining that the target working mode is a fifth mode.
If the current working mode is the fifth mode, the target working mode required to be switched in the fifth mode can be determined according to the acquired mode switching instruction and/or the current attitude information of the carrier rocket. Specifically, if only the current attitude information is used for indicating that the attitude of the launch vehicle is abnormal or has no attitude, it is determined that the target operating mode is still the fifth mode. And if the mode switching instruction is used for indicating to switch to a preset third mode (namely, a mode 3 switching instruction), and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode is the third mode. And if only the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode is a preset fourth mode.
In an alternative embodiment, if the system is in the first mode (mode 1), the power amplifier in the system may be allowed to be turned on, and then the phased array antenna is controlled to perform data transmission with corresponding power based on the code rate of the data transmitted in the first transmission channel, for example, when the first transmission channel transmits high-code-rate data, BPSK modulation and concatenated convolutional RS coding may be used, or QPSK modulation and LDPC coding may be used, and the antenna is controlled to perform high-power and small-angle (i.e., narrow beam angle) data transmission in cooperation with the phased array antenna. For example, when the first transmit channel transmits low-bit-rate data, the BPSK and CDMA operating systems may be used to perform low-power large-angle (i.e., wide beam angle) data transmission in cooperation with the control space-based measurement and control phased array antenna. Wherein narrow and wide beams are relative, for example when the beam angle exceeds a certain threshold, it may be referred to as a wide beam; otherwise called narrow beam.
In an optional embodiment, if the system is in the second mode (mode 2), the first transmitting channel (or the first code stream transmitted by the first transmitting channel, which may be referred to as stream 1 for short) operates in the high-code-rate space-based mode, and the second transmitting channel (or the second code stream transmitted by the second transmitting channel, which may be referred to as stream 2 for short) operates in the SMA system, at this time, the power amplifier may be turned off, and the phased array antenna is controlled to output high power, so as to transmit corresponding code stream data.
In an optional embodiment, if the system is in the third mode (mode 3), the stream 1 operates in the low-bit-rate space-based mode, and the stream 2 operates in the SMA system, at this time, the power amplifier may be turned off, and the low-power output of the phased array antenna is controlled, so as to perform corresponding bit stream data transmission.
In an optional embodiment, if the system is in the fourth mode (mode 4), the stream 1 operates in the high-code-rate space-based mode, and the stream 2 operates in the SMA system, at this time, the power amplifier may be turned on, and the phased array antenna is controlled to output high power, so as to perform corresponding code stream data transmission.
In an optional embodiment, if the system is in the fifth mode (mode 5), the stream 1 operates in the low-bit-rate space-based mode, and the stream 2 operates in the SMA system, at this time, the power amplifier may be turned on, and the phased array antenna may be controlled to output low power, so as to perform corresponding bit stream data transmission.
In the actual use process, the rocket measurement and control communication system supports 5 working modes. In a first mode, a first transmitting channel adopts BPSK modulation and RS cascade convolution coding, or adopts QPSK modulation and LDPC coding, and supports the data transmission of a code stream with a customizable configuration and a high code rate; the second transmitting channel adopts a PCM-CM system, adopts Product Code (Turbo Product Code, TPC) coding, and the phased array antenna with space-based measurement and control outputs high power, and the power amplifier works normally. In a second mode, the first transmission channel adopts BPSK modulation and RS coding, or adopts QPSK modulation and LDPC coding, and also supports the data transmission of the scalable configuration and the high-code-rate code stream; the second transmitting channel adopts an SMA system, the phased array antenna with space-based measurement and control outputs high power, and the power amplifier is closed. In a third mode, the first transmitting channel adopts BPSK modulation and RS coding, or adopts QPSK modulation and LDPC coding, and also supports the data transmission of the low-bit-rate code stream with the customizable configuration; the second transmitting channel adopts an SMA system, the phased array antenna with space-based measurement and control outputs low power, and the power amplifier is closed. In a fourth mode, the first transmitting channel adopts BPSK modulation and RS coding, or adopts QPSK modulation and LDPC coding, and supports the scalable configuration and high-code-rate code stream data transmission; the second transmitting channel adopts an SMA system, the phased array antenna with space-based measurement and control outputs high power, and the power amplifier works normally. In a fifth mode, the first transmitting channel adopts BPSK modulation and RS coding, or QPSK modulation and LDPC coding, and supports the scalable configuration and low-bit-rate code stream data transmission; the second transmitting channel adopts an SMA system, the phased array antenna with space-based measurement and control outputs low power, and the power amplifier works normally.
In an alternative embodiment, the second transmitting channel may operate in PCM-FM and TPC, or in SMA regime, and may operate in PCM-FM modulation and TPC coding at initial power-up, and then switch to SMA regime according to the flight timing of the launch vehicle, and the specific switching process may refer to the mode switching method shown in fig. 2 and fig. 3. And when the flight time is greater than the binding parameter, the second transmitting channel is switched to the SMA system to work once the abnormal posture of the carrier rocket is detected, the transmitting antenna corresponding to the transmitting channel transmits the directional diagram in an omnidirectional manner, and the measurement and control network receives the wireless data of 2 frequency points to ensure that the data are acquired to the maximum extent.
In an optional embodiment, the rocket measurement and control communication system can also switch the working mode according to the trajectory planning condition of the carrier rocket, for example, when an engine is damaged in the flight process, the central computer recalculates the flight time, and needs to switch to low-code-rate data transmission, the working mode can be switched to a third mode for working, and the like. Thus, the energy loss of the battery can be reduced, and the requirement of more ballistic tasks can be met. The system can capture, track and receive data of the working system (or system) of the carrier rocket, and transmits the mode switching instruction through the first receiving channel, thereby improving the safety performance of the carrier rocket.
By implementing the method, a measurement and control center unit in the rocket measurement and control communication system is used for acquiring a mode switching instruction of the system and/or current attitude information of the carrier rocket, and further a target working mode where the system needs to be located is determined according to the mode switching instruction and/or the current attitude information, and then the target working mode is switched to for data transmission. Therefore, the problems that the reliable communication requirement or the data transmission requirement of a special task cannot be met in the prior art and the like can be effectively solved, and the reliability and the safety of data transmission are favorably improved.
Please refer to fig. 5, which is a schematic structural diagram of another rocket measurement and control communication system (specifically, a measurement and control center unit in the system) provided in the embodiment of the present application. The system shown in fig. 5 includes an obtaining module 501, a determining module 502, and a switching module 503, where:
the obtaining module 501 is configured to obtain a mode switching instruction of the rocket measurement and control communication system, and/or obtain current attitude information of a carrier rocket;
the determining module 502 is configured to determine a target working mode of the launch vehicle according to the mode switching instruction and/or the current attitude information;
the switching module 503 is configured to switch the current working mode of the launch vehicle to the target working mode for data communication.
Optionally, if the current operating mode is a preset first mode, before the mode switching instruction of the rocket measurement and control communication system is obtained,
the obtaining module 501 is further configured to obtain a flight time of the carrier rocket at the current task stage and a binding parameter, where the binding parameter is used to represent a threshold value that is acceptable for the current task stage;
the switching module 503 is further configured to maintain the current working mode of the launch vehicle if the flight time is less than or equal to the binding parameter; or, if the flight time is greater than the binding parameter, switching the current working mode to a preset second mode.
Optionally, the determining module 502 is specifically configured to:
if the mode switching instruction is used for indicating to switch to a preset third mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset third mode; alternatively, the first and second electrodes may be,
if the mode switching instruction is used for indicating to switch to a preset fourth mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset fourth mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
Optionally, if the current working mode is a preset third mode, the determining module 502 is specifically configured to:
if the mode switching instruction is used for indicating to switch to a preset second mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset second mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
Optionally, if the current working mode is a preset fourth mode, the determining module 502 is specifically configured to:
if the mode switching instruction is used for indicating to switch to a preset second mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset second mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
Optionally, if the current working mode is a preset fifth mode, the determining module 502 is specifically configured to:
if the mode switching instruction is used for indicating to switch to a preset third mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset third mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is a preset fourth mode.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset first mode, the system further includes a processing module 504;
the processing module 504 is configured to turn on a power amplifier in the rocket measurement and control communication system, control the phased array antenna to perform data transmission with corresponding power according to the code rate of the data to be transmitted by the first transmit channel in the first mode, and control the second transmit channel to perform data transmission in a relay satellite S-band multiple access SMA system.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset second mode, the processing module 504 is further configured to:
and closing a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to transmit data with high power and narrow wave speed according to the high-code-rate data transmitted by the first transmitting channel in the second mode, and controlling the second transmitting channel to transmit data in a relay satellite S-band multiple access (SMA) mode.
Optionally, the rocket measurement and control communication system is configured with a first transmitting channel and a second transmitting channel, and if the target operating mode is a preset third mode, the processing module 504 is further configured to:
and closing a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to perform low-power and wide-wave-speed data transmission according to the low-code-rate data transmitted by the first transmitting channel in the third mode, and controlling the second transmitting channel to perform data transmission in a relay satellite S-band multiple access (SMA) mode.
By implementing the method, a measurement and control center unit in the rocket measurement and control communication system is used for acquiring a mode switching instruction of the system and/or current attitude information of the carrier rocket, and further a target working mode where the system needs to be located is determined according to the mode switching instruction and/or the current attitude information, and then the target working mode is switched to for data transmission. Therefore, the problems that the reliable communication requirement or the data transmission requirement of a special task cannot be met in the prior art and the like can be effectively solved, and the reliability and the safety of data transmission are favorably improved.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, 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 (systems), 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.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A mode switching method based on a rocket measurement and control communication system is characterized in that the mode switching method is applied to a measurement and control center unit in the rocket measurement and control communication system, and the method comprises the following steps:
acquiring a mode switching instruction of the rocket measurement and control communication system and/or acquiring current attitude information of a carrier rocket;
determining a target working mode of the carrier rocket according to the mode switching instruction and/or the current attitude information;
and switching the current working mode of the carrier rocket to the target working mode for data communication.
2. The method according to claim 1, wherein before the obtaining of the mode switching command of the rocket measurement and control communication system if the current operating mode is the preset first mode, the method further comprises:
acquiring the flight time of the carrier rocket in the current task stage and binding parameters, wherein the binding parameters are used for representing the threshold value which can be accepted by the current task stage;
if the flight time is less than or equal to the binding parameter, maintaining the current working mode of the carrier rocket;
and if the flight time is greater than the binding parameter, switching the current working mode to a preset second mode.
3. The method according to claim 2, wherein the determining a target operational mode of the launch vehicle based on the mode switch command and/or the current attitude information specifically comprises:
if the mode switching instruction is used for indicating to switch to a preset third mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset third mode; alternatively, the first and second electrodes may be,
if the mode switching instruction is used for indicating to switch to a preset fourth mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset fourth mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
4. The method according to claim 1, wherein if the current operating mode is a preset third mode, the determining the target operating mode of the launch vehicle according to the mode switching instruction and/or the current attitude information specifically comprises:
if the mode switching instruction is used for indicating to switch to a preset second mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset second mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
5. The method according to claim 1, wherein if the current operating mode is a preset fourth mode, the determining the target operating mode of the launch vehicle according to the mode switching instruction and/or the current attitude information specifically comprises:
if the mode switching instruction is used for indicating to switch to a preset second mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset second mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is abnormal or has no attitude, determining that the target working mode of the carrier rocket is a preset fifth mode.
6. The method according to claim 1, wherein if the current operating mode is a preset fifth mode, the determining the target operating mode of the launch vehicle according to the mode switching instruction and/or the current attitude information specifically comprises:
if the mode switching instruction is used for indicating to switch to a preset third mode and the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is the preset third mode; alternatively, the first and second electrodes may be,
and if the current attitude information is used for indicating that the attitude of the carrier rocket is normal, determining that the target working mode of the carrier rocket is a preset fourth mode.
7. The method of any of claims 1-6, wherein the rocket measurement and control communication system is configured with a first transmit channel and a second transmit channel, and wherein if the target operating mode is a preset first mode, the method further comprises:
and opening a power amplifier in the rocket measurement and control communication system, controlling the phased array antenna to transmit data with corresponding power according to the code rate of the data to be transmitted of the first transmitting channel in the first mode, and controlling the second transmitting channel to transmit data in a relay satellite S-band multiple access SMA mode.
8. The method of any of claims 1-6, wherein the rocket measurement and control communication system is configured with a first transmit channel and a second transmit channel, and wherein if the target operating mode is a predetermined second mode, the method further comprises:
and closing a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to transmit data with high power and narrow wave speed according to the high-code-rate data transmitted by the first transmitting channel in the second mode, and controlling the second transmitting channel to transmit data in a relay satellite S-band multiple access (SMA) mode.
9. The method of any of claims 1-6, wherein the rocket measurement and control communication system is configured with a first transmit channel and a second transmit channel, and wherein if the target operating mode is a predetermined third mode, the method further comprises:
and closing a power amplifier in the rocket measurement and control communication system, controlling a phased array antenna to perform low-power and wide-wave-speed data transmission according to the low-code-rate data transmitted by the first transmitting channel in the third mode, and controlling the second transmitting channel to perform data transmission in a relay satellite S-band multiple access (SMA) mode.
10. A rocket measurement and control communication system is characterized by comprising a central computer, an inertia combination navigation and measurement and control central unit, at least one combiner, a power amplifier and a phased array antenna which are coupled through a bus; wherein the measurement and control center unit is configured to perform a mode switching method of a rocket based measurement and control communication system as claimed in any one of the preceding claims 1-9.
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