CN109870070A - A kind of integrated wireless launch vehicle measurement applied to Solid Launch Vehicle - Google Patents
A kind of integrated wireless launch vehicle measurement applied to Solid Launch Vehicle Download PDFInfo
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Abstract
The invention discloses a kind of integrated wireless launch vehicle measurements applied to Solid Launch Vehicle, it include: that hair control module is surveyed in front end, for Rocket test, firing order and the computer forwarding on Solid Launch Vehicle arrow that reception rear end survey hair control module is sent before carrier rocket emits, while receiving test result, execution state that Solid Launch Vehicle computer passes down；Hair control module is surveyed in rear end, Rocket test, firing order are sent for surveying hair control module to the front end before carrier rocket transmitting, and it receives the front end and surveys test result, execution state on the arrow of hair control module forwards, while the telemetry that reception carrier rocket is issued by wireless channel after carrier rocket transmitting.The present invention is set up flexibly and fast using high bandwidth, the transmission of medium and long distance data between wireless bridge realization front and back end survey launching control equipment, is laid with transmission cable without preparatory long range.
Description
Technical Field
The invention belongs to the field of space launching, and particularly relates to an integrated wireless measurement launching control system applied to a solid carrier rocket.
Background
For a long time, the test and launch control systems of the subsystems of the carrier rocket in China are independent respectively, and all use independent ground test equipment to complete the functions of power supply and distribution, signal excitation, state control, parameter measurement and other tests, launch control and the like of the rocket system. The test mode of the self-forming system is gradually formed along with the development of the aerospace technology, and convenience is brought to the development and management of the system in the early stage. However, with the continuous improvement of technical requirements, the mode brings some disadvantages, such as repeated functions, complex system, increased cost, poor compatibility, great inconvenience for use, maintenance and upgrade, and especially, with the continuous development of systems on rockets, the new generation rockets for heavy delivery and the like also put forward higher requirements for reliability, compatibility and real-time performance of the rocket test and launch control system. Therefore, based on the integrated design concept, a unified ground test launching and control system with high efficiency, high reliability, low cost and high universality is established, resources are reasonably distributed and utilized, object-oriented integration of ground power supply and distribution, testing, launching and control, comprehensive diagnosis and the like is realized, repeated investment is avoided to reduce the system cost, intermediate links are reduced to improve the system reliability and the working efficiency, the launching period is finally shortened, the launching success rate is improved, the transportation capacity is increased, and the method is of great importance to the development of ground test launching and control technology.
At present, the integrated measurement, launch and control system of most solid carrier rockets adopts a wired transmission mode to carry out system interconnection. However, the wired measurement and launch control system has various devices, the cable connection relationship is complex, and the whole system is long in deployment and layout time. Because the ground wired network transmission needs network equipment such as a router, a switch and the like, the system scale is limited by the number of physical interfaces of the network equipment, and the expansibility is poor. In addition, the traditional solid carrier rocket ground measurement, launch and control system mostly adopts a customized special measurement, launch and control console to control equipment such as gas circuits, liquid circuits and ignition safety mechanisms at all levels on the rocket before launch, so that the ground measurement, launch and control equipment has single use, poor universality and high cost; meanwhile, due to the division of labor in the traditional system, the software and hardware of the ground remote measurement system and the measurement, launch and control system are mutually separated, and the traditional ground equipment of the carrier rocket is repeated and complicated.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides an integrated wireless measurement and launch control system applied to a solid carrier rocket. The technical problem to be solved by the invention is realized by the following technical scheme:
an integrated wireless measurement and launch control system applied to a solid carrier rocket comprises:
the front-end test-launch control module is used for receiving a first instruction, sending the first instruction to a carrier rocket, and receiving first detection data of the carrier rocket;
and the rear-end testing, transmitting and controlling module is used for transmitting the first instruction to the front-end testing, transmitting and controlling module and receiving and displaying the first detection data.
In one embodiment of the present invention, further comprising:
the wireless transmission system comprises a first wireless transmission module and a second wireless transmission module; wherein,
the first wireless transmission module is used for sending the first instruction to the front-end test sending control module and sending the first detection data to the second transmission module;
and the second wireless transmission module is used for sending the first instruction to the first wireless transmission module and sending the first detection data to the rear-end test sending control module.
In one embodiment of the present invention, the first wireless transmission module includes:
the system comprises a front-end switch, a front-end wireless network bridge and a front-end microwave antenna; wherein,
the front-end switch is connected with the front-end test, launch and control module; the front-end microwave antenna is connected with the second wireless transmission module;
the front-end switch, the front-end wireless network bridge and the front-end microwave antenna are sequentially connected.
In one embodiment of the present invention, the second wireless transmission module includes:
the system comprises a rear-end switch, a rear-end wireless network bridge and a rear-end microwave antenna; wherein,
the back-end switch is connected with the back-end test, launch and control module; the rear-end microwave antenna is connected with the front-end microwave antenna;
the rear-end switch, the rear-end wireless network bridge and the rear-end microwave antenna are sequentially connected.
In an embodiment of the present invention, the bridge modes adopted by the front-end microwave antenna and the back-end microwave antenna are both IEEE 802.11ac protocols.
In an embodiment of the present invention, the front-end measurement, launch and control module includes:
the transmission and measurement industrial personal computer is used for receiving the first detection data and transmitting the first detection data to the first wireless transmission module;
and the ground power supply is used for supplying power to the carrier rocket.
In one embodiment of the present invention, the test and transmission industrial personal computer includes:
the communication board card is used for receiving second detection data;
the Ethernet board card is used for sending the second instruction to the carrier rocket and receiving third detection data;
and the switching value output board card is used for sending the third instruction to the carrier rocket.
In an embodiment of the present invention, the back-end measurement, launch and control module includes:
the thin clients are used for providing operating instructions for the cloud server;
and the cloud server is used for obtaining a first instruction according to the operation instruction and sending the first instruction to the second wireless transmission module through a wireless router.
In an embodiment of the present invention, the back-end test, launch and control module further includes:
the ground telemetry receiving antenna is used for receiving fourth detection data transmitted by the carrier rocket;
and the ground telemetry station is used for decoding the fourth detection data and sending the fourth detection data to the cloud server.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention adopts the wireless network bridge to realize high-bandwidth, medium-distance and long-distance data transmission between the front-end and the rear-end measuring, transmitting and controlling equipment, is simple to erect, and does not need to lay a transmission cable in a long distance in advance;
2. the invention adopts the wireless router to realize the wireless access interconnection of the back-end measurement, emission and control equipment, the equipment is flexible to lay, and the system is convenient to expand;
3. the invention simplifies the software and hardware interfaces of the rocket ground equipment, adopts the industrial personal computer to control the equipment on the rocket before shooting, and has low cost and strong expansibility.
Drawings
Fig. 1 is a schematic structural diagram of an integrated wireless measurement, launch and control system applied to a solid launch vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of another integrated wireless measurement, launch and control system applied to a solid launch vehicle according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific examples, but the embodiments of the present invention are not limited thereto.
Example one
Referring to fig. 1, fig. 1 is a schematic structural diagram of an integrated wireless measurement, launch and control system applied to a solid launch vehicle according to an embodiment of the present invention.
An integrated wireless measurement and launch control system applied to a solid carrier rocket comprises: and the front-end test-launch control module is used for receiving the first instruction, sending the first instruction to the carrier rocket, and receiving first detection data of the carrier rocket.
Furthermore, the front-end test and launch control module is mainly used for receiving and forwarding the test instruction and the launch instruction sent by the rear-end test and launch control module to the rocket computer before launch of the carrier rocket, and meanwhile sending the test result and the rocket monitoring data sent by the rocket computer to the rear-end test and launch control module for processing.
It should be noted that, the first instruction refers to a test instruction and a transmission instruction; the first detection data refers to a test result sent by a computer on the arrow and monitoring data on the arrow.
Furthermore, the front-end test launch control module is connected and communicated with the solid carrier rocket through the rocket ground unplugging plug, so that the functions of power supply of the rocket electrical equipment, test before launch, launch control, state data receiving and the like are realized.
And the rear end testing and transmitting control module is used for sending a first instruction to the front end testing and transmitting control module and receiving and displaying first detection data.
Furthermore, the rear-end test and launch control module is mainly used for sending test instructions and launch instructions to the front-end test and launch control module before launch, and receiving and displaying test results and arrow monitoring data.
Furthermore, the rear-end test, launch and control module is internally interconnected by building a wireless local area network, and is externally and remotely interconnected with the front-end test, launch and control module, and mainly achieves the functions of remote test, launch and control, remote data measurement in the flight process, image receiving and analysis and the like of the solid carrier rocket.
Further, this integration wireless survey launch control system still includes: the wireless transmission system comprises a first wireless transmission module and a second wireless transmission module;
the first wireless transmission module is used for sending the first instruction to the front-end test and transmission control module and sending the first detection data to the second transmission module;
and the second wireless transmission module is used for sending the first instruction to the first wireless transmission module and sending the first detection data to the rear-end test sending control module.
Further, please refer to fig. 2, fig. 2 is a schematic structural diagram of another integrated wireless measurement and launch control system applied to a solid launch vehicle according to an embodiment of the present invention; the first wireless transmission module includes: the system comprises a front-end switch, a front-end wireless network bridge and a front-end microwave antenna;
the front-end switch is connected with the front-end test, launch and control module through the Ethernet; the front-end microwave antenna is wirelessly connected with the second wireless transmission module;
the front-end switch, the front-end wireless network bridge and the front-end microwave antenna are sequentially connected.
Furthermore, the front-end switch adopts a commercial gigabit switch, so that network transmission among the front-end test, transmission and control modules is realized.
Further, the front-end wireless bridge uses the IEEE 802.11ac protocol bridge mode for long-distance transmission.
Furthermore, the front-end microwave antenna is matched with the wireless network bridge for use, the erection height is 3-5 m, and wireless transmission of data between the front-end measurement, transmission and control modules and the rear-end measurement, transmission and control modules is achieved.
Further, the front-end measurement, emission and control module comprises:
and the test and transmission industrial personal computer is used for receiving the first detection data of the carrier rocket and transmitting the first detection data to the first wireless transmission module.
And the 28V ground power supply is used for supplying power to the electrical equipment on the launch vehicle arrow before launching.
It should be noted that the test and launch industrial personal computer and the 28V ground power supply are both connected with the solid carrier rocket through the Ethernet.
Furthermore, the test and launch industrial personal computer adopts an industrial personal computer case, and a corresponding expansion board card is added on a main board of the industrial personal computer case to be connected and communicated with the equipment on the arrow; the method mainly comprises the following steps:
the system comprises 1 synchronous serial port communication board card, a remote measuring device and a wireless communication device, wherein the synchronous serial port communication board card is connected with the remote measuring device on the rocket and receives rocket remote measuring data, namely second detection data, which is downloaded by a wired channel before transmission; the on-arrow telemetering data comprises on-arrow force/heat environment monitoring data, on-arrow equipment monitoring data and on-arrow camera downward transmission image information.
And 1, 100/1000M self-adaptive Ethernet board card, which is connected with the rocket computer, uploads a second instruction before the rocket is launched and receives third detection data at the same time. The second instruction is a test-launch control software, namely an instruction sent by the cloud server; the third detection data is test state data of the rocket, and the test state data mainly comprises test results of various test items of the carrier rocket before launching.
The system comprises 1 switching value output board card, a control device on the rocket, a third instruction, namely hard instructions such as system power-on, power-switching, emergency power-off and the like, is sent before the rocket is launched, and meanwhile, a signal when the rocket is launched is acquired, namely a takeoff signal is acquired.
It should be noted that the first detection data includes second detection data and third detection data; the first instruction includes a second instruction and a third instruction.
Furthermore, the voltage of the ground power supply is 28V, the ground power supply adopts a commercial high-power stabilized voltage supply, the output voltage and current of the power supply are remotely controlled through testing, launching and controlling software, and power supply and distribution are carried out on electrical equipment on the rocket before launching.
Further, the second wireless transmission module includes: the system comprises a rear-end switch, a rear-end wireless network bridge and a rear-end microwave antenna;
the back-end switch is connected with the back-end test, launch and control module through the Ethernet; the rear-end microwave antenna is wirelessly connected with the front-end microwave antenna;
the rear-end switch, the rear-end wireless network bridge and the rear-end microwave antenna are sequentially connected.
Furthermore, the back-end switch adopts a business switch, so that network transmission among the back-end test, transmission and control modules is realized.
Further, the back-end wireless bridge adopts an IEEE 802.11ac protocol bridge mode for long-distance transmission.
Furthermore, the rear-end microwave antenna and the rear-end wireless network bridge are matched for use, the erection height is 3-5 m, and wireless transmission between the front-end measurement, emission and control data and the rear-end measurement, emission and control data is achieved.
The front end testing, launching and controlling module and the rear end testing, launching and controlling module are connected in an external remote mode through the front end wireless network bridge and the rear end wireless network bridge, existing line connection is replaced, erection is simple, and transmission cables do not need to be laid in advance in a long distance.
In one embodiment, the front-end wireless bridge or the back-end wireless bridge can be replaced by the wireless data radio station and the data link terminal machine, so that the same effect is achieved.
Further, the back end measurement, emission and control module comprises:
and the thin clients are used for providing operating instructions for the cloud server.
The thin clients adopt cloud terminal equipment of a private cloud technology to provide a system operation interface for operators, and the functions of remote testing, launch control, state parameter monitoring and the like of the solid carrier rocket are realized; the operation interface comprises a plurality of operation seats, and the operation seats mainly comprise a measurement, emission and control operation seat, a telemetering processing and interpretation seat and a ground telemetering tracking operation seat.
And the cloud server is used for obtaining a first instruction according to the operation instruction and sending the first instruction to the second wireless transmission module through the wireless router.
Furthermore, the cloud server is built by adopting a commercial private cloud technology, computing and storage capacity is provided for the system, two cloud servers are deployed in the measurement, launch and control system and are mutually in hot backup, and system application software such as ground measurement, launch and control software, telemetering data processing software, telemetering image analysis software and telemetering data interpretation software are mainly deployed.
In addition, this rear end is surveyed and is sent out control module and still includes:
the ground telemetering receiving antenna is used for receiving fourth detection data transmitted by the carrier rocket;
and the ground telemetry station is used for decoding the fourth detection data and sending the fourth detection data to the cloud server.
It should be noted that the fourth detection data includes force/thermal environment monitoring data on the arrow, device monitoring data on the arrow, and image information transmitted by the camera on the arrow.
It should be noted that the second detection data is detection data transmitted by wire before launch of the launch vehicle, and the fourth detection data is detection data transmitted by wireless channel after launch of the launch vehicle.
Further, the ground telemetry station has the main functions of: (1) controlling a ground telemetering receiving antenna to track and align a carrier rocket telemetering antenna according to preset carrier rocket trajectory information; (2) and receiving telemetering data, namely fourth detection data, issued by telemetering equipment on the rocket through a ground telemetering receiving antenna, separating state parameter information and image information in the telemetering data through hardware decoding, and transmitting the separated state parameter information and image information to telemetering data display and judgment software for judgment.
Furthermore, the terms "first", "second", "third", "fourth" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated.
The embodiment of the invention also provides a working process of the test launch control system, which mainly comprises the following parts:
and (1) supplying power to equipment on the rocket.
And (3) electrifying flow: the ground power supply instruction is sent by the test, launch and control operator seat through the test, launch and control software, namely the ground power supply instruction is sent by the thin client through the cloud server, and is transmitted through the cloud server (main) sequentially through the wireless router → the rear-end switch → the rear-end wireless bridge → the rear-end microwave antenna → the front-end wireless bridge → the front-end switch → the ground power supply, so that the ground power supply is controlled to supply power to and output power supply and distribution equipment on the rocket.
And (2) after the ground power supply voltage is confirmed to be stable, the test and launch control operation seat controls a test and launch industrial personal computer at the front end to send a system power-on instruction to a computer on the rocket through test and launch control software.
And (3) after the computer on the rocket receives the system power-on instruction, controlling the power supply and distribution equipment on the rocket to sequentially power on other electrical equipment on the rocket.
And (4) automatically starting self-checking after each device on the rocket is powered on, after the self-checking is normal, carrying out each pre-shooting test detection by the computer on the rocket according to the test instruction on the rocket, and sequentially pulling out the plug → the transmission testing industrial personal computer → the front-end switch → the front-end wireless bridge → the front-end microwave antenna → the rear-end wireless bridge → the rear-end switch → the wireless router → the cloud server (main) to transmit the test result, namely the third detection data, so as to feed the test result back to the transmission testing control software and display the test result on the transmission testing control operation seat.
Before the rocket is launched, the rocket-mounted equipment is connected with the front-mounted launch control module through a rocket ground cable; after the rocket is launched, the rocket ground cable is automatically disconnected under the action of pulling force.
And (5) after the self-checking is finished, the telemetering equipment on the rocket starts to download second detection data on the rocket at the same time through a rocket ground cable wired channel and a telemetering transmitter wireless channel.
It should be noted that, according to the test launching process of the solid carrier rocket, the test launch control operation desk controls the computer on the rocket to complete the corresponding test and state check work through the test launch control software. If the launching needs to be stopped, the measurement and launch control operation seat can control the measurement and launch industrial personal computer to send an emergency power-off instruction to the computer on the rocket through the measurement and launch control software, and the whole rocket is powered off and the launching is stopped.
And (6) operating and adjusting the alignment of the ground telemetering receiving antenna and the rocket telemetering antenna by the ground telemetering tracking operation seat according to the carrier rocket launcher orientation, and receiving fourth detection data issued by a wireless channel, wherein the fourth detection data refer to state parameter information and image information in the rocket flight process.
And (7) after the test and check before the solid carrier rocket is launched are finished, the test, launch and control operator seat sends an ignition instruction to a computer on the rocket through test, launch and control software, and the solid carrier rocket engine is ignited to take off. The test and launch industrial personal computer and the computer on the rocket respectively acquire shedding signals of the rocket ground unplugging plugs of the respective ports as take-off zero time.
And (8) taking the takeoff zero time sent by the measurement and transmission industrial personal computer as a time starting point for tracking by the ground antenna by the ground remote sensing station, tracking and aligning the telemetering transmitting antenna on the rocket in real time, and acquiring data information of the flight of the solid carrier rocket, namely fourth detection data.
And (9) analyzing the flight telemetering data information by the ground telemetering processing and judging software, and then distributing the information to each operation seat for monitoring.
And (10) after the carrier rocket is flown, each design professional carries out interpretation analysis according to the telemetering data to obtain a flight test conclusion.
The invention adopts the wireless network bridge to realize high-bandwidth, medium-distance and long-distance data transmission between the front-end and the rear-end measurement, transmission and control equipment, is flexible and quick to erect, and does not need to lay a transmission cable in a long distance in advance.
In addition, the invention adopts the wireless router to realize the wireless access interconnection of the back-end measurement, transmission and control equipment, the equipment layout is flexible, and the system expansion is convenient.
In addition, the invention simplifies the software and hardware interfaces of the rocket ground equipment, adopts the industrial personal computer to carry out pre-shooting control on the equipment on the rocket, and has low cost and strong expansibility.
In addition, the ground measurement, launch and control and ground remote measurement processing and interpretation are integrated, the system architecture is optimized, meanwhile, a private cloud is adopted to construct an integrated ground measurement and launch system, data are stored and processed uniformly, and the operation seats with multiple functions of rocket measurement, launch and control, ground remote measurement receiving, data processing and interpretation and the like can be flexibly configured as required.
In addition, the measurement, launch and control system is built by adopting a commodity shelf product, and the development and maintenance cost is low.
In addition, the scheme is suitable for development of a carrier rocket test and launch control system taking a solid engine as power, and comprises but not limited to scientific research tests such as scheme design, engineering development and flight test, commercial launch of effective loads and the like.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (9)
1. The utility model provides a be applied to wireless survey of integration launch control system of solid carrier rocket which characterized in that includes:
the front-end test-launch control module is used for receiving a first instruction, sending the first instruction to a carrier rocket, and receiving first detection data of the carrier rocket;
and the rear end testing, transmitting and controlling module is used for transmitting the first instruction to the front end testing, transmitting and controlling module and receiving and displaying the first detection data.
2. The integrated wireless measurement and launch control system applied to the solid launch vehicle of claim 1, further comprising:
the wireless transmission system comprises a first wireless transmission module and a second wireless transmission module; wherein,
the first wireless transmission module is used for sending the first instruction to the front-end test sending control module and sending the first detection data to the second wireless transmission module;
and the second wireless transmission module is used for sending the first instruction to the first wireless transmission module and sending the first detection data to the rear-end test sending control module.
3. The integrated wireless measurement and launch control system applied to a solid launch vehicle of claim 2 wherein the first wireless transmission module comprises:
the system comprises a front-end switch, a front-end wireless network bridge and a front-end microwave antenna; wherein,
the front-end switch is connected with the front-end test, launch and control module; the front-end microwave antenna is connected with the second wireless transmission module;
the front-end switch, the front-end wireless network bridge and the front-end microwave antenna are sequentially connected.
4. The integrated wireless measurement and launch control system applied to the solid launch vehicle of claim 3 wherein the second wireless transmission module comprises:
the system comprises a rear-end switch, a rear-end wireless network bridge and a rear-end microwave antenna; wherein,
the back-end switch is connected with the back-end test, launch and control module; the rear-end microwave antenna is connected with the front-end microwave antenna;
the rear-end switch, the rear-end wireless network bridge and the rear-end microwave antenna are sequentially connected.
5. The integrated wireless measurement, launch and control system applied to the solid launch vehicle of claim 4 wherein the bridge modes adopted by the front-end microwave antenna and the back-end microwave antenna are both IEEE 802.11ac protocols.
6. The integrated wireless test, launch and control system applied to a solid launch vehicle of claim 2 wherein the front-end test, launch and control module comprises:
the transmission and measurement industrial personal computer is used for receiving the first detection data and transmitting the first detection data to the first wireless transmission module;
and the ground power supply is used for supplying power to the carrier rocket.
7. The integrated wireless test and launch control system applied to the solid launch vehicle of claim 6 wherein the test and launch industrial personal computer comprises:
the communication board card is used for receiving second detection data;
the Ethernet board card is used for sending the second instruction to the carrier rocket and receiving third detection data at the same time;
and the switching value output board card is used for sending the third instruction to the carrier rocket.
8. The integrated wireless test, launch and control system applied to a solid launch vehicle of claim 2 wherein the back-end test, launch and control module comprises:
the thin clients are used for providing operating instructions for the cloud server;
and the cloud server is used for obtaining a first instruction according to the operation instruction and sending the first instruction to the second wireless transmission module through a wireless router.
9. The integrated wireless test, launch and control system applied to a solid launch vehicle of claim 8 wherein the back-end test, launch and control module further comprises:
the ground telemetry receiving antenna is used for receiving fourth detection data transmitted by the carrier rocket;
and the ground telemetry station is used for decoding the fourth detection data and sending the fourth detection data to the cloud server.
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