CN114802819A - Rocket terminal level off-orbit control method and device - Google Patents
Rocket terminal level off-orbit control method and device Download PDFInfo
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Abstract
The invention provides a rocket terminal level off-orbit control method and a rocket terminal level off-orbit control device, which relate to the technical field of aerospace power, wherein the method comprises the following steps: receiving flight state parameters of the rocket tail sub-stage sent by the rocket-borne computer; the flight state parameters are sent to a ground measurement and control station, so that the ground measurement and control station determines the off-orbit control parameters of the rocket terminal sub-level based on the flight state parameters; receiving off-orbit control parameters sent by a ground measurement and control station; and sending the off-orbit control parameters to the rocket-borne computer so that the rocket-borne computer performs off-orbit control on the rocket tail level based on the off-orbit control parameters. The method and the device provided by the invention reduce the occupation amount of computing resources of the rocket-borne computer, so that the rocket-borne computer can be dedicated to navigation guidance and attitude control of the carrier rocket at the last sublevel, incomplete derailment and incomplete consumption of propellant caused by deviation in rocket flight can be avoided, and the accuracy and the stability of the carrier rocket at the last sublevel derailment are improved.
Description
Technical Field
The invention relates to the technical field of aerospace power, in particular to a rocket terminal-level off-orbit control method and device.
Background
At present, before a solid carrier rocket is launched, the initial condition of the last sublevel derailment of the rocket can be obtained by calculating the standard trajectory of the rocket, the thrust vector parameter of the derailment active section and the engine starting time of the derailment active section are designed according to simulation analysis, and the pre-calculated thrust vector parameter and the engine starting time of the derailment active section are stored in an rocket-borne computer, so that the rocket-borne computer executes the derailment action according to the stored value during the actual flight test.
However, in an actual flight test task, because actual conditions are not completely consistent with theoretical calculation, parameters such as an actual orbit entry point of a rocket final sub-stage and residual fuel quality of a rocket final sub-stage engine are not consistent with theoretical off-orbit scheme design conditions before launch, and if off-orbit actions are executed by fully using pre-calculated values before launch, the off-orbit effect cannot be guaranteed to be consistent with theoretical analysis.
Therefore, how to improve the accuracy and stability of the last sublevel derailment of the carrier rocket becomes a technical problem to be solved urgently in the industry.
Disclosure of Invention
The invention provides a method and a device for controlling last-sublevel derailment of a rocket, which are used for solving the technical problem of how to improve the accuracy and stability of last-sublevel derailment of a carrier rocket in the prior art.
The invention provides a rocket terminal level off-orbit control method, which comprises the following steps:
receiving flight state parameters of the rocket tail sub-stage sent by the rocket-borne computer;
sending the flight state parameters to a ground measurement and control station so that the ground measurement and control station determines the off-orbit control parameters of the rocket terminal sub-stage based on the flight state parameters;
receiving off-orbit control parameters sent by the ground measurement and control station;
and sending the off-orbit control parameters to the rocket-borne computer so that the rocket-borne computer performs off-orbit control on the rocket tail son stage based on the off-orbit control parameters.
According to the rocket terminal-level off-orbit control method provided by the invention, the step of sending the flight state parameters to the ground measurement and control station comprises the following steps:
generating a state telemetry frame based on the flight state parameters;
sending the state telemetry frame to the ground measurement and control station;
wherein the state telemetry frame comprises a telemetry frame header, a telemetry frame data length, telemetry frame contents and a telemetry frame check sequence; the telemetry frame content includes a time of flight, a position vector, a velocity vector, and a remaining fuel mass of the rocket's final substage.
According to the rocket terminal sub-level off-orbit control method provided by the invention, the state telemetry frame is sent to the ground measurement and control station, and the method comprises the following steps:
and sending the state telemetry frame to a telemetry transmitter so that the telemetry transmitter modulates the state telemetry frame into a first wireless signal and sends the first wireless signal to the ground measurement and control station based on a transmitting antenna.
According to the rocket terminal sublevel derailment control method provided by the invention, the step of receiving the derailment control parameters sent by the ground measurement and control station comprises the following steps:
receiving a second wireless signal sent by the ground measurement and control station based on a receiving antenna;
and demodulating the second wireless signal based on a remote control receiver to obtain an off-track remote control frame containing the off-track control parameter.
According to the rocket tail-level off-orbit control method provided by the invention, the off-orbit remote control frame comprises a remote control frame head, a remote control frame data length, a remote control frame content and a remote control frame check sequence; the remote control frame content comprises the off-orbit time and the off-orbit flight attack angle.
According to the rocket terminal level derailment control method provided by the invention, the step of sending the derailment control parameters to the rocket-borne computer comprises the following steps:
receiving off-track confirmation information sent by the rocket-borne computer;
and sending the derailing confirmation information to the ground measurement and control station.
The invention provides a rocket tail-son-level off-orbit control device, which comprises:
the first receiving unit is used for receiving the flight state parameters of the rocket tail sub-stage sent by the rocket-borne computer;
the first sending unit is used for sending the flight state parameters to a ground measurement and control station so that the ground measurement and control station can determine the off-orbit control parameters of the rocket terminal sub-stage based on the flight state parameters;
the second receiving unit is used for receiving the off-orbit control parameters sent by the ground measurement and control station;
and the second sending unit is used for sending the off-orbit control parameters to the rocket-borne computer so as to enable the rocket-borne computer to carry out off-orbit control on the rocket tail son stage based on the off-orbit control parameters.
The invention provides a rocket, wherein a rocket tail-son-stage off-orbit control device, a rocket-borne computer, a telemetering transmitter and a remote control receiver are arranged on a tail-son stage of the rocket;
the remote measuring transmitter is connected with the rocket tail sub-level off-orbit control device and used for transmitting the flight state parameters of the rocket tail sub-level to a ground measurement and control station;
the remote control receiver is connected with the rocket tail sub-level off-orbit control device and is used for receiving the rocket tail sub-level off-orbit control parameters sent by the ground measurement and control station;
the rocket-borne computer is connected with attitude and orbit control equipment at the last sublevel of the rocket and is used for generating the flight state parameters based on the operation parameters of the attitude and orbit control equipment and generating the control parameters of the attitude and orbit control equipment based on the off-orbit control parameters.
The invention provides electronic equipment which comprises a memory, a processor and a computer program stored on the memory and capable of running on the processor, wherein the processor executes the program to realize the rocket end-son-level off-orbit control method.
The invention provides a non-transitory computer-readable storage medium having stored thereon a computer program which, when executed by a processor, implements the rocket end-sub-level off-track control method.
The invention provides a rocket terminal sublevel derailment control method and a device, which receive a flight state parameter of a rocket terminal sublevel sent by an rocket-borne computer, send the flight state parameter to a ground measurement and control station, so that the ground measurement and control station determines a derailment control parameter of the rocket terminal sublevel based on the flight state parameter, receives the derailment control parameter sent by the ground measurement and control station, and sends the derailment control parameter to the rocket-borne computer, so that the rocket-borne computer performs derailment control on the rocket terminal sublevel based on the derailment control parameter, because the derailment control parameter is calculated according to the flight state parameter of the rocket terminal sublevel, the calculation is completed by the ground measurement and control station, the occupation amount of calculation resources of the rocket-borne computer is reduced, the rocket-borne computer can carry navigation guidance and attitude control of the rocket terminal sublevel, the reliability and the real-time performance of the rocket-borne computer are improved, and simultaneously, the obtained off-orbit control parameters have high accuracy, incomplete off-orbit caused by deviation in rocket flight and incomplete consumption of propellant can be avoided, and the accuracy and stability of carrier rocket final-sublevel off-orbit are improved.
Drawings
In order to more clearly illustrate the technical solutions of the present invention or the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described 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 these drawings without creative efforts.
FIG. 1 is a schematic flow chart of a rocket end-stage off-orbit control method provided by the invention;
FIG. 2 is a schematic structural diagram of a rocket final-stage derailment control device provided by the invention;
FIG. 3 is a schematic view of a rocket according to the present invention;
fig. 4 is a schematic structural diagram of an electronic device provided in the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. 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 invention.
Fig. 1 is a schematic flow chart of a rocket end-son-level off-orbit control method provided by the present invention, and as shown in fig. 1, the method includes step 110, step 120, step 130 and step 140.
And step 110, receiving the flight state parameters of the rocket terminal sub-stage sent by the rocket-borne computer.
Specifically, the last substage of the rocket is the last stage of the rocket, and in the rocket launching process, the last stage of the orbital thrust is provided for the satellite. After the rocket and the satellite are separated, if the last sublevel of the rocket flies in orbit for a long time, space debris is left on the orbit and poses a security threat to the in-orbit spacecraft.
The last sublevel derailment of the rocket refers to a process that after the last sublevel of the carrier rocket finishes launching a satellite or other space tasks, a series of measures are taken to enable the flight orbit to deviate from the original orbit. Before the off-orbit control is carried out, the off-orbit control parameters when the off-orbit control is carried out by the rocket terminal sublevel are calculated according to the flight state parameters of the rocket terminal sublevel. The flight state parameters are parameters describing the flight state of the rocket terminal sub-stage and comprise flight positions, flight speeds and the like. The off-orbit control parameters are parameters for controlling the last sublevel of the rocket to enter an off-orbit state, and comprise a pitch angle, a yaw angle, the starting time of an engine and the like during the last sublevel off-orbit of the rocket.
Because the actual values of all flight state parameters of the last substage of the rocket in the actual flight test task may not be consistent with the theoretical values of all parameters before the launch of the carrier rocket, in order to improve the accuracy and stability of the last substage of the carrier rocket in derailment, the derailment control parameters can be calculated according to the actual values of all flight state parameters.
The electrical system on the launch vehicle includes a power supply and distribution system, a flight control and navigation system, a servo control system, a sequence control system, a telemetry system, etc. The flight control and navigation system is realized by adopting an rocket-mounted computer, is a core operation module of the carrier rocket and is responsible for functions of navigation guidance calculation, attitude control and the like of the carrier rocket, and therefore the rocket-mounted computer has the characteristics of high reliability, high real-time performance and the like.
The process of calculating the off-track control parameter according to the flight state parameter is iterative calculation, and certain calculation capacity and calculation memory are required to be occupied. If the rocket-borne computer executes the iterative computation, the computing power and the memory of the rocket-borne computer are occupied, and the functions of the rocket-borne computer on the navigation guidance computation, the attitude control and the like of the rocket terminal sub-stage are influenced.
Therefore, the calculation of the off-orbit control parameters can be finished by the ground measurement and control station with strong calculation capability. Because the rocket-borne computer is not provided with a communication device, a rocket terminal sublevel derailment control device can be arranged on a carrier rocket terminal sublevel or other computers arranged on the carrier rocket are used for controlling data transmission between the rocket-borne computer and the ground measurement and control station.
For example, a rocket terminal sub-stage off-orbit control device can be arranged and is in communication connection with the rocket-borne computer and used for acquiring flight state parameters of the rocket terminal sub-stage. The communication connection mode CAN adopt at least one of 1553B bus protocol, CAN bus protocol, RS422 bus protocol and RS485 bus protocol.
And 120, transmitting the flight state parameters to a ground measurement and control station so that the ground measurement and control station can determine the off-orbit control parameters of the rocket terminal level based on the flight state parameters.
Specifically, after acquiring flight state parameters from the rocket-borne computer, the rocket terminal sublevel derailment control device can send the flight state parameters to the ground measurement and control station, and the ground measurement and control station determines the derailment control parameters of the rocket terminal sublevel according to the flight state parameters.
For example, the orbit determination formula for the semi-major axis of orbit of the rocket's end-child stage can be expressed as:
in the formula (I), the compound is shown in the specification,
in the form of a position vector, the position vector,
in the form of a velocity vector, the velocity vector,
is a semi-major axis of the track,
is the earth's gravity constant.
The orbit semi-major axis is reduced along with the reduction of the speed of the rocket terminal sub-stage, and when the orbit semi-major axis is reduced, the height of the near place corresponding to the rocket terminal sub-stage is reduced. Therefore, theoretically, if the fire at the last substage of the rocket is completely ignited along the reverse direction of the current speed direction of the last substage of the rocket in the off-track section, the height of the near place of the last substage of the rocket can be reduced to the maximum extent. Considering other factors such as safety of off-orbit tracks and the like, the near-to-ground height of the first circle of orbit after the last sublevel of the rocket is off-orbit is generally set to be 100km, and the last sublevel of the rocket can crash within a preset time under the action of atmospheric resistance. In addition, in order to avoid the influence of pollution and the like caused by residual fuel of the engine, the residual fuel of the engine needs to be exhausted as much as possible. Therefore, the attitude angle during the derailment needs to be set, so that the rocket realizes the derailment by the thrust which is not completely opposite to the speed, the attitude angle corresponds to the pitch angle and the yaw angle in the navigation coordinate system, but the last stage of the rocket needs to be kept in the current orbit plane during the derailment process, so that only one independent variable is actually needed, and the independent variable can be replaced by the flight attack angle.
That is, the off-track control parameter may include a flight angle of attack.
And step 130, receiving the off-orbit control parameters sent by the ground measurement and control station.
Specifically, the ground measurement and control station can send the off-orbit control parameters when monitoring that the last sublevel of the rocket flies into the measurement and control range.
And step 140, transmitting the off-orbit control parameters to the rocket-borne computer so that the rocket-borne computer performs off-orbit control on the rocket tail-son stage based on the off-orbit control parameters.
Specifically, the rocket tail son stage derailment control device sends the received derailment control parameters to the rocket-borne computer, and the rocket-borne computer controls the attitude control engine and/or the orbit control engine on the rocket tail son stage to perform attitude adjustment according to the derailment control parameters, so that the rocket tail son stage derailment control device enters a derailment state.
The rocket terminal sublevel derailment control method provided by the embodiment of the invention receives the flight state parameters of the rocket terminal sublevel sent by the rocket-borne computer, sends the flight state parameters to the ground measurement and control station, so that the ground measurement and control station determines the derailment control parameters of the rocket terminal sublevel based on the flight state parameters, receives the derailment control parameters sent by the ground measurement and control station, and sends the derailment control parameters to the rocket-borne computer, so that the rocket-borne computer performs derailment control on the rocket terminal sublevel based on the derailment control parameters, because the derailment control parameters are calculated according to the flight state parameters of the rocket terminal sublevel, the calculation is completed by the ground measurement and control station, the occupation amount of calculation resources of the rocket-borne computer is reduced, the rocket-borne computer can carry navigation guidance and attitude control of the rocket terminal sublevel, the reliability and the real-time performance of the rocket-borne computer are improved, and simultaneously, the obtained off-orbit control parameters have high accuracy, incomplete off-orbit caused by deviation in rocket flight and incomplete consumption of propellant can be avoided, and the accuracy and stability of carrier rocket final-sublevel off-orbit are improved.
Based on the above embodiment, step 120 includes:
generating a state telemetry frame based on the flight state parameters;
sending the state telemetering frame to a ground measurement and control station;
the state telemetry frame comprises a telemetry frame head, a telemetry frame data length, telemetry frame contents and a telemetry frame check sequence; the telemetry frame contents include time of flight, position vector, velocity vector, and remaining fuel mass for the last substage of the rocket.
Specifically, the rocket terminal sublevel derailment control device can send the flight state parameters to the ground measurement and control station in a frame message mode.
The state telemetry frame may be generated from the flight state parameters. The frame format of the status telemetry frame includes a telemetry frame header, a telemetry frame data length, telemetry frame content, and a telemetry frame check sequence. The telemetry header is used for containing sending address information, synchronization information and the like of the frame message. The telemetry frame data length is used to indicate the amount of data contained in the frame message. The telemetry frame check sequence is used to contain error control information for the frame message. The telemetry frame contents include time of flight, position vector, velocity vector and remaining fuel mass for the last substage of the rocket. Since the orbit semi-major axis of the rocket's end sub-stage can be calculated from the position vector and the velocity vector, the telemetry frame contents also include the orbit semi-major axis of the rocket's end sub-stage.
The rocket terminal sublevel off-orbit control device can send state telemetering frames to the ground measurement and control station according to a certain time interval. For example, when the rocket terminal substage is ready to be off-orbit and flies to the measurement and control range of the ground measurement and control station, the state telemetry frame can be sent according to the set time interval, so that the ground measurement and control station can acquire the real-time flight state of the rocket terminal substage.
Based on any one of the above embodiments, sending the status telemetry frame to a ground measurement and control station, comprising:
and sending the state telemetry frame to a telemetry transmitter so that the telemetry transmitter modulates the state telemetry frame into a first wireless signal and sends the first wireless signal to a ground measurement and control station based on a transmitting antenna.
Specifically, the rocket terminal sub-level off-orbit control device sends a state telemetry frame to a telemetry transmitter, the telemetry transmitter modulates the state telemetry frame to generate a first wireless signal, and the first wireless signal is transmitted to a ground measurement and control station through a transmitting antenna.
Based on any of the above embodiments, step 130 includes:
receiving a second wireless signal sent by the ground measurement and control station based on the receiving antenna;
and demodulating the second wireless signal based on the remote control receiver to obtain an off-track remote control frame containing the off-track control parameters.
Specifically, the ground measurement and control station may send the off-orbit control parameters to the rocket terminal level off-orbit control device in a frame message manner.
And the ground measurement and control station modulates the off-orbit remote control frame containing the off-orbit control parameters to obtain a second wireless signal. And when the rocket terminal substage flies to the measurement and control range of the ground measurement and control station, a second wireless signal is sent to the rocket terminal substage.
And the receiving antenna of the rocket tail sub-stage acquires the second wireless signal, and the second wireless signal is demodulated by the remote control receiver to obtain an off-orbit remote control frame containing off-orbit control parameters.
Based on any of the above embodiments, the off-track remote control frame comprises a remote control frame header, a remote control frame data length, a remote control frame content, and a remote control frame check sequence; the remote control frame content comprises the off-orbit time and the off-orbit flight attack angle.
Specifically, the off-track remote control frame comprises a remote control frame head, a remote control frame data length, a remote control frame content and a remote control frame check sequence. The remote control frame header is used for containing the sending address information, the synchronization information and the like of the frame message. The remote control frame data length is used for indicating the data volume contained in the frame message. The remote control frame check sequence is used to contain error control information of the frame message. The remote control frame content comprises the off-orbit time and the off-orbit flight attack angle. The derailing time is the time when the last son stage of the rocket starts to perform derailing control. And the off-orbit flight attack angle is an attitude angle which needs to be adjusted when the last son stage of the rocket starts off-orbit control.
Based on any of the above embodiments, step 140 includes, after:
receiving off-track confirmation information sent by an rocket-borne computer;
and sending the off-track confirmation information to the ground measurement and control station.
Specifically, in order to determine that the rocket tail substage can obtain the off-orbit control parameters, the ground measurement and control station sends the off-orbit control parameters to the rocket tail substage for multiple times. The rocket terminal substage derailment control device is also used for receiving derailment confirmation information sent by the rocket-borne computer and sending the derailment confirmation information to the ground measurement and control station, so that the ground measurement and control station can confirm that the rocket terminal substage can start to perform derailment control at the set derailment moment.
Based on any of the above embodiments, fig. 2 is a schematic structural diagram of a last-son-level off-orbit control device of a rocket provided by the present invention, and as shown in fig. 2, the last-son-level off-orbit control device 200 of the rocket includes:
a first receiving unit 210, configured to receive a flight state parameter of a rocket tail sub-stage sent by an rocket-borne computer;
the first sending unit 220 is configured to send the flight state parameters to the ground measurement and control station, so that the ground measurement and control station determines the off-orbit control parameters of the rocket tail sub-stage based on the flight state parameters;
the second receiving unit 230 is configured to receive the off-track control parameter sent by the ground measurement and control station;
and a second sending unit 240, configured to send the off-orbit control parameter to the rocket-borne computer, so that the rocket-borne computer performs off-orbit control on the rocket tail sub-stage based on the off-orbit control parameter.
The rocket tail-son-level off-orbit control device provided by the embodiment of the invention receives the flight state parameters of the rocket tail-son level sent by the rocket-borne computer, sends the flight state parameters to the ground measurement and control station, so that the ground measurement and control station determines off-orbit control parameters of the rocket tail-son level based on the flight state parameters, receives the off-orbit control parameters sent by the ground measurement and control station, and sends the off-orbit control parameters to the rocket-borne computer, so that the rocket-borne computer performs off-orbit control on the rocket tail-son level based on the off-orbit control parameters, because the off-orbit control parameters are calculated according to the flight state parameters of the rocket tail-son level, the calculation is completed by the ground measurement and control station, the occupation amount of calculation resources of the rocket-borne computer is reduced, the rocket-borne computer can carry navigation guidance and attitude control of the rocket tail-son level, the reliability and the real-time performance of the rocket-borne computer are improved, and simultaneously, the obtained off-orbit control parameters have high accuracy, incomplete off-orbit caused by deviation in rocket flight and incomplete consumption of propellant can be avoided, and the accuracy and stability of carrier rocket final-sublevel off-orbit are improved.
Based on any of the above embodiments, fig. 3 is a schematic structural diagram of the rocket provided by the present invention, as shown in fig. 3, the rocket 300 includes a final sub-stage 310, and the final sub-stage 310 is provided with a rocket final sub-stage off-orbit control device 200, an rocket-mounted computer 320, a telemetry transmitter 321 and a remote control receiver 331; the telemetry transmitter 321 is connected to a transmit antenna 322. The remote control receiver 331 is connected to the receiving antenna 332.
The telemetering transmitter 321 is connected with the rocket final-sub-level off-orbit control device 200 and is used for transmitting the flight state parameters of the rocket final-sub-level to the ground measurement and control station;
the remote control receiver 331 is connected with the rocket final-sub-level off-orbit control device 200 and is used for receiving off-orbit control parameters of the rocket final-sub-level sent by the ground measurement and control station;
and the rocket-borne computer 320 is connected with attitude and orbit control equipment at the last sublevel of the rocket and is used for generating flight state parameters based on the operation parameters of the attitude and orbit control equipment and generating control parameters of the attitude and orbit control equipment based on the off-orbit control parameters.
Specifically, the step of the rocket executing the end-son off-orbit control comprises the following steps:
step one, after the last son stage of the rocket executes the on-orbit task, starting off-orbit control, and sending flight state parameters to a last son stage off-orbit control device of the rocket by an rocket-borne computer. The rocket final sub-stage is provided with a rocket final sub-stage off-orbit control device, a telemetering transmitter, a transmitting antenna, a remote control receiver, a receiving antenna and other carrying systems.
And step two, sending data such as the current position vector of the last sublevel, the orbit long half axis of the velocity vector, the residual fuel quality and the like through a telemetering transmitter. And the last sublevel prepares for derailing, and the rocket tail sublevel derailing control device receives relevant data of the rocket-borne computer through an interface protocol. And the rocket terminal son-level off-orbit control device sends the current relevant data to the telemetering transmitter. The telemetry transmitter modulates data into a first wireless signal and transmits the first wireless signal to the transmitting antenna. The transmitting antenna transmits the first wireless signal.
The telemetry frame format is: frame header + data length + current time + position vector + velocity vector + orbit long semi-axis + remaining fuel mass + calibration.
And step three, the ground measurement and control station receives data issued by the last sub-level and formulates an active off-track strategy according to the last sub-level on-track task. And the last child stage is ready to be off-orbit and flies to the ground station within the measurement and control range. And the ground measurement and control station receives the data issued by the last sub-level transmitting antenna. And the ground measurement and control station demodulates the first wireless signal to obtain data such as a final sub-level position vector, a speed vector, a track long half shaft, residual fuel quality and the like.
And step four, uploading the off-orbit parameters by the ground measurement and control station. And analyzing the ground personnel data and formulating the off-orbit data. And when the terminal level crosses the border ground station, off-rail data is sent to a ground measurement and control station transmitter, and the ground measurement and control station transmitter modulates the data into a second wireless signal to be transmitted.
The remote control frame format is: frame header + data length + off-track time + off-track flight angle of attack + calibration.
And step five, the last sub-level receives the off-orbit parameters and switches to ground control to execute off-orbit. And the receiving antenna receives the off-track data signal transmitted on the ground when the terminal suborder crosses the border. And the last sub-level remote control receiver demodulates and sends the second wireless signal to the rocket last sub-level off-orbit control device. And the rocket tail-son-level off-orbit control device sends off-orbit data to the rocket-borne computer. And when the designed off-orbit time is reached, the rocket-borne computer controls the final sub-stage to actively off-orbit.
Based on any of the above embodiments, fig. 4 is a schematic structural diagram of an electronic device provided by the present invention, and as shown in fig. 4, the electronic device may include: a Processor (Processor) 410, a communication Interface (communication Interface) 420, a Memory (Memory) 430 and a communication Bus (communication Bus) 440, wherein the Processor 410, the communication Interface 420 and the Memory 430 are communicated with each other via the communication Bus 440. The processor 410 may call logical commands in the memory 430 to perform the following method:
receiving flight state parameters of the rocket tail sub-stage sent by the rocket-borne computer; the flight state parameters are sent to a ground measurement and control station, so that the ground measurement and control station determines the off-orbit control parameters of the rocket terminal sub-level based on the flight state parameters; receiving off-orbit control parameters sent by a ground measurement and control station; and sending the off-orbit control parameters to the rocket-borne computer so that the rocket-borne computer performs off-orbit control on the rocket tail level based on the off-orbit control parameters.
In addition, the logic commands in the memory 430 may be implemented in the form of software functional units and stored in a computer readable storage medium when the logic commands are sold or used as independent products. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes a plurality of commands for enabling a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The processor in the electronic device provided in the embodiment of the present invention may call a logic instruction in the memory to implement the method, and the specific implementation manner of the method is consistent with the implementation manner of the method, and the same beneficial effects may be achieved, which is not described herein again.
Embodiments of the present invention further provide a non-transitory computer-readable storage medium, on which a computer program is stored, where the computer program is implemented to perform the method provided in the foregoing embodiments when executed by a processor, and the method includes:
receiving flight state parameters of the rocket tail sub-stage sent by the rocket-borne computer; the flight state parameters are sent to a ground measurement and control station, so that the ground measurement and control station determines the off-orbit control parameters of the rocket terminal sub-level based on the flight state parameters; receiving off-orbit control parameters sent by a ground measurement and control station; and sending the off-orbit control parameters to the rocket-borne computer so that the rocket-borne computer performs off-orbit control on the rocket tail level based on the off-orbit control parameters.
When the computer program stored on the non-transitory computer readable storage medium provided in the embodiments of the present invention is executed, the method is implemented, and the specific implementation manner of the method is consistent with the implementation manner of the method, and the same beneficial effects can be achieved, which is not described herein again.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium, such as ROM/RAM, magnetic disk, optical disk, etc., and includes commands for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method according to the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A rocket terminal level off-orbit control method is characterized by comprising the following steps:
receiving the flight state parameters of the rocket tail sub-stage sent by the rocket-borne computer;
sending the flight state parameters to a ground measurement and control station so that the ground measurement and control station determines the off-orbit control parameters of the rocket terminal sub-stage based on the flight state parameters;
receiving off-orbit control parameters sent by the ground measurement and control station;
and sending the off-orbit control parameters to the rocket-borne computer so that the rocket-borne computer performs off-orbit control on the rocket tail son stage based on the off-orbit control parameters.
2. A rocket end-stage off-orbit control method according to claim 1, wherein said sending said flight state parameters to a ground measurement and control station comprises:
generating a state telemetry frame based on the flight state parameters;
sending the state telemetry frame to the ground measurement and control station;
wherein the state telemetry frame comprises a telemetry frame header, a telemetry frame data length, telemetry frame contents and a telemetry frame check sequence; the telemetry frame content includes a time of flight, a position vector, a velocity vector, and a remaining fuel mass of the rocket's final substage.
3. A rocket end-stage off-track control method as recited in claim 2, wherein said sending said state telemetry frame to said ground test control station comprises:
and sending the state telemetry frame to a telemetry transmitter so that the telemetry transmitter modulates the state telemetry frame into a first wireless signal and sends the first wireless signal to the ground measurement and control station based on a transmitting antenna.
4. A rocket end-son-level off-orbit control method according to claim 1, wherein said receiving off-orbit control parameters sent by said ground measurement and control station comprises:
receiving a second wireless signal sent by the ground measurement and control station based on a receiving antenna;
and demodulating the second wireless signal based on a remote control receiver to obtain an off-track remote control frame containing the off-track control parameter.
5. A rocket end-stage derailment control method according to claim 4, wherein the derailment remote control frame comprises a remote control frame header, a remote control frame data length, a remote control frame content and a remote control frame check sequence; the remote control frame content comprises the off-orbit time and the off-orbit flight attack angle.
6. A rocket end-stage derailment control method according to any one of claims 1 to 5, wherein the sending the derailment control parameters to the rocket-borne computer then comprises:
receiving off-track confirmation information sent by the rocket-borne computer;
and sending the derailing confirmation information to the ground measurement and control station.
7. A rocket terminal level off-orbit control device is characterized by comprising:
the first receiving unit is used for receiving the flight state parameters of the rocket tail sub-stage sent by the rocket-borne computer;
the first sending unit is used for sending the flight state parameters to a ground measurement and control station so that the ground measurement and control station can determine the off-orbit control parameters of the rocket terminal sub-stage based on the flight state parameters;
the second receiving unit is used for receiving the off-orbit control parameters sent by the ground measurement and control station;
and the second sending unit is used for sending the off-orbit control parameters to the rocket-borne computer so as to enable the rocket-borne computer to carry out off-orbit control on the rocket tail son stage based on the off-orbit control parameters.
8. A rocket, characterized in that the last substage of the rocket is provided with a rocket terminal substage off-orbit control device, a rocket-mounted computer, a telemetric transmitter and a remote control receiver according to claim 7;
the telemetering transmitter is connected with the rocket final sub-stage off-orbit control device and is used for transmitting the flight state parameters of the rocket final sub-stage to a ground measurement and control station;
the remote control receiver is connected with the rocket final sub-stage derailment control device and is used for receiving the rocket final sub-stage derailment control parameters sent by the ground measurement and control station;
the rocket-borne computer is connected with attitude and orbit control equipment at the last sublevel of the rocket and is used for generating the flight state parameters based on the operation parameters of the attitude and orbit control equipment and generating the control parameters of the attitude and orbit control equipment based on the off-orbit control parameters.
9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor, when executing the program, implements a rocket end-sub-level off-orbit control method of any one of claims 1 to 6.
10. A non-transitory computer-readable storage medium having stored thereon a computer program, wherein the computer program, when executed by a processor, implements a rocket end-stage derailment control method according to any of claims 1 to 6.
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