CN214540529U - Aircraft flight attitude and position monitoring system - Google Patents
Aircraft flight attitude and position monitoring system Download PDFInfo
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- CN214540529U CN214540529U CN202120463063.6U CN202120463063U CN214540529U CN 214540529 U CN214540529 U CN 214540529U CN 202120463063 U CN202120463063 U CN 202120463063U CN 214540529 U CN214540529 U CN 214540529U
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Abstract
The utility model relates to an aircraft flight gesture and position monitoring system. The system comprises: control device, power supply unit, big dipper transceiver and antenna device. The control device comprises an attitude sensor, a memory and a central processing unit; the Beidou transmitting and receiving device is electrically connected with the control device and is used for communicating with a Beidou satellite and ground control equipment; the antenna device is electrically connected with the Beidou transmitting and receiving device, is used for positioning the aircraft and has a short message frequency point; the power supply device is electrically connected with the control device and the Beidou transmitting and receiving device and used for providing electric power for related modules in the control device and the Beidou transmitting and receiving device. The system has the functions of RDSS short message receiving and transmitting, Beidou B1 frequency point and GPS L1 frequency point positioning, can automatically report the flight number, longitude, latitude, altitude and time of the aircraft, can set the reporting interval, and has the functions of flight attitude measurement, monitoring and alarming and internal storage and recording.
Description
Technical Field
The utility model relates to an airborne vehicle's location field especially relates to airborne vehicle flight gesture and position monitoring system based on big dipper satellite communication.
Background
The Beidou satellite navigation system (BDS) is a self-developed global satellite navigation system in China, and a large number of application achievements are obtained in China. The short message is a special function of the Beidou satellite navigation system, and a user provided with the Beidou positioning terminal can position the position of the user and can issue text information to the outside. The aircraft is one of important flight tools, and is an important field of Beidou application. The positioning and monitoring system is usually installed on various flight vehicles, and can realize navigation of the flight vehicles and position tracking of the flight vehicles.
The positioning monitoring system is a monitoring device installed on an aircraft, can monitor the position of the aircraft in real time, and sends the monitored information to a ground control center through a satellite communication system, so that the flight attitude and position of the aircraft can be obtained in ground control.
The above statements in the background are only intended to facilitate a thorough understanding of the present invention (including the technical means used, the technical problems solved and the technical effects produced), and should not be taken as an acknowledgement or any form of suggestion that this message constitutes prior art already known to a person skilled in the art.
SUMMERY OF THE UTILITY MODEL
To the defect that exists among the prior art, the utility model provides an aircraft flight gesture and position monitoring system, its self has attitude sensor, can measure and keep watch on the flight gesture of aircraft, possesses location and automatic alarm function simultaneously.
According to the utility model discloses an embodiment provides an aircraft flight gesture and position monitoring system, and it includes: the Beidou satellite radio frequency identification system comprises a control device, a power supply device, a Beidou transmitting and receiving device and an antenna device; the Beidou transmitting and receiving device is electrically connected with the control device and is configured to communicate with a Beidou satellite and/or a GPS satellite and ground control equipment; the antenna device is electrically connected with the Beidou transmitting and receiving device and is configured to position the aircraft and transmit and receive short message frequency point signals; the power supply device is electrically connected with the control device and the Beidou transmitting and receiving device and is configured to provide electric power for related modules in the control device and the Beidou transmitting and receiving device; the control device includes: an attitude sensor electrically connected to the central processor, the attitude sensor configured to automatically collect current attitude information of the aircraft; a memory electrically connected to the central processor, the memory configured to store position information and attitude information of the aircraft; and the central processing unit is configured to receive information of the attitude sensor and the Beidou transmitting and receiving device, store the received information in the memory and monitor the information, and trigger alarm when abnormity occurs.
Preferably, the aircraft attitude and position monitoring system further comprises a display device; the display device is electrically connected with the control device and is configured to display position information, short messages and attitude sensor information.
Preferably, the antenna device is connected with the Beidou transmitting and receiving device through a wire-line feeder; the wire harness feeder adopts a coaxial cable and an outer sheath.
Preferably, the Beidou transmitting and receiving device comprises an RNSS module and an RDSS module; the RNSS module is configured to receive B1 and/or L1 frequency point signals in a high dynamic environment and finally output a positioning result; the RDSS module is configured to complete short message receiving and sending under a high dynamic environment, including receiving of S frequency point signals and transmitting of L frequency point signals.
Preferably, the Beidou transmitting and receiving device and the control device are communicated through an RS-422 data transmission protocol.
Preferably, the display device and the control device communicate via an RS-422 data transmission protocol.
Preferably, the central processor comprises a processor with a core model of ARM Cortex-M3; the attitude sensor is a six-axis sensor module using an MPU 6050 as a main chip.
Preferably, the acquisition time of the position information and the attitude information of the aircraft is set according to the user requirement.
Preferably, the antenna device comprises an antenna, a first low-frequency noise amplifier, a second low-frequency noise amplifier, a low-frequency power amplifier and a duplexer; b1 and/or L1 frequency point signals are input through an antenna, and enter a wire-line feeder through a first low-frequency noise amplifier and a duplexer; the L frequency point signal is input through a wire-through feeder line and enters the antenna through the duplexer and the low-frequency power amplifier; and the S frequency point signal is input through an antenna, passes through the second low-frequency noise amplifier and the duplexer, and enters a wire-pass feeder.
Preferably, the antenna is a passive antenna or an active antenna; the mode of the antenna adopts a single mode or a multi-mode.
The utility model adopts the above technical scheme, it has following beneficial effect:
the utility model provides an aircraft flight attitude and position monitoring system has RDSS short message receiving and sending function; the Beidou B1 frequency point and GPS L1 frequency point positioning function; the flight number, longitude, latitude, altitude and time of the aircraft can be automatically reported, and the reporting interval can be set; flight attitude measurement and monitoring alarm functions; internal storage records, and the like. Therefore, according to the utility model discloses an aircraft flight gesture and position monitoring system of embodiment measures and monitors the flight gesture of aircraft, possesses location and automatic alarm function simultaneously, has improved the security of aircraft in flight process, can provide important technical support for aircraft information and guarantee system.
Drawings
Exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. For purposes of clarity, the same reference numbers will be used in different drawings to identify the same elements. It is noted that the drawings are merely schematic and are not necessarily drawn to scale. In these drawings:
fig. 1 is a functional block diagram of an aircraft flight attitude and position monitoring system according to an embodiment of the present invention;
fig. 2 is a functional block diagram of a beidou transceiver device according to an embodiment of the present invention;
fig. 3 is a functional block diagram of an antenna arrangement of an aircraft attitude and position monitoring system according to an embodiment of the present invention.
Detailed Description
The embodiments of the present invention will be described in detail below, and the embodiments are implemented on the premise of the technical solution of the present invention, and detailed embodiments and specific operation processes are given, but the scope of the present invention is not limited to the embodiments described below.
Fig. 1 shows a block diagram of an aircraft attitude and position monitoring system according to an embodiment of the present invention. According to the utility model discloses the aircraft flight gesture and the position monitoring system of embodiment install on the aircraft, can search for the satellite signal automatically and accomplish satellite signal locking in a certain time, output location signal such as longitude, latitude, height; reporting information can also be automatically sent to the ground control device for monitoring position and attitude sensor data of the aircraft, the reporting information may include a position report including longitude, latitude and altitude information of the current aircraft, an attitude report including, but not limited to, no less than a set of three-axis angle data and a time stamp, and the like. If the flight parameters are abnormal, an alarm module on the aircraft can be triggered, and abnormal data can be sent to the ground control equipment to give an alarm.
According to the utility model discloses an aircraft flight gesture and position monitoring system of embodiment can include: the device comprises a control device 101, a power supply device 102, a Beidou transmitting and receiving device 103 and an antenna device 104.
The control device 101 includes: a central processing unit 1001, an attitude sensor 1002, and a memory 1003. The cpu 1001 is electrically connected to the attitude sensor 1002 and the memory 1003, respectively.
The central processing unit 1001 is used for receiving information of the Beidou transmitting and receiving device and the attitude sensor, storing the received information in the memory 1003, monitoring and triggering alarm when abnormality occurs. Wherein the sampling time of the positioning and the gesture can be set according to the needs of the user, and the minimum interval is preferably less than or equal to 20 seconds.
The utility model discloses in, what central processing unit 1001 adopted is that the kernel model is ARM Cortex-M3's treater, and it is a 32-bit treater kernel, has adopted the harvard structure, possess independent instruction bus and data bus, and instruction bus and data bus share same memory space, have the advantage of high reliability, low cost.
The memory 1003 is used to store position information and attitude information of the aircraft. The memory 1003 may include: magnetic disks, optical disks, Solid State Disks (SSDs), Secure Digital (SD) cards, mini secure digital (mSD) cards, micro secure digital (micro SD) cards, Secure Digital High Capacity (SDHC) cards, memory stick cards, Smart Media (SM) cards, multimedia cards (MMC), embedded MMC (emmc), Compact Flash (CF) cards, and the like.
The attitude sensor 1002 may be used to automatically collect current attitude information of the aircraft, and may be a high-performance three-dimensional motion attitude measurement device based on mems (micro Electro Mechanical systems) technology. According to the utility model discloses aircraft flight attitude and position monitoring system's attitude sensor 1002 is the six sensor module that adopts InvenSense company's MPU 6050 as the main chip, can detect the motion data and the temperature data of triaxial acceleration, triaxial gyroscope (triaxial angular velocity) simultaneously. The DMP module (Digital Motion Processor) in the MPU 6050 chip can be used for filtering and fusing the sensor data, and the sensor data directly passes through I2And the C interface outputs the attitude data after the attitude calculation to the main controller, so that the operation amount of the main controller is reduced. The maximum attitude calculation frequency can reach 200Hz, and the method is very suitable for the field with higher real-time requirement on attitude control.
The power supply device 102 may convert the input voltage into a voltage required by each module through a DC/DC converter, for example, a direct current voltage of 8V to 40V may be converted into a direct current voltage of 5V for supplying power to the control device. The power supply device 102 also has an EMC filtering function, which can solve the problem of electromagnetic compatibility between the module and the system well, so that the module and the system do not interfere with each other. In the present invention, the power supply device 102 can provide different, stable required voltages for the respective modules, thereby ensuring stable and reliable operation of the entire system.
The Beidou transmitting and receiving device 103 is in communication connection with the control device 101, and can communicate through an RS-422 data transmission protocol. The Beidou transceiver 103 comprises an RNSS module and an RDSS module, receives signals of the Beidou satellite through the RNSS module, calculates the current position of the aircraft, and sends position information of the aircraft to the ground control equipment through the RDSS module, so that the monitoring functions of positioning the aircraft and automatically alarming by the ground control equipment are realized.
According to the utility model discloses an embodiment, aircraft flight attitude and position monitoring system can also include display device 105, display device 105 is connected with controlling means 101 electricity for equipment control, positional information, short message and sensor information's demonstration. The display device and the control device may communicate, for example, via RS-422 data transmission protocol.
The antenna device 104 can be installed outside the aircraft flight attitude and position monitoring system, is suitable for positioning of the aircraft flight attitude and position monitoring system, has short message frequency points, is compatible with the L1 frequency point of a GPS system, and can realize the functions of positioning and satellite-based communication.
The antenna device 104 may include a passive antenna or an active antenna, and the antenna device 104 and the beidou transceiver device 103 are electrically connected via a wire lead feeder.
Fig. 2 is a functional block diagram of a big dipper transceiver device according to the utility model discloses an embodiment.
Unlike other Satellite Navigation systems, the beidou Navigation System provides users with two services, namely, a Satellite Radio Navigation System (RNSS) and a Satellite Radio measurement Service (RDSS), at the same time. RNSS is a satellite radio navigation service in which users receive satellite radio navigation signals and calculate their position, velocity and navigation parameters. The RDSS is a satellite radio measurement service, and the distance measurement and position calculation from a user to a satellite cannot be independently completed by the user, and is completed by an external system through the response of the user, and the user position report to the external system is completed while the positioning is completed through the response of the user.
The Beidou RDSS service belongs to paid service, a user machine can be used only by loading an authorized Beidou user card, and each Beidou smart card has a unique serial number and is used for identity identification. The Beidou RDSS user needs to respond to the service beam and transmit observation data back to the central station for processing. Because the satellite and terrestrial equipment communication links are limited in bandwidth and capacity, and the inbound and outbound resources are limited, the frequency must be limited to differentiate between the needs and the level of importance of the user. The frequency of service for each RDSS authorized user is a fixed value.
According to the utility model discloses aircraft flight attitude and position monitoring system's big dipper transceiver 103 can include RNSS module and RDSS module.
The RNSS module may be configured to complete reception of B1 and/or L1 frequency point signals in a high dynamic environment, and finally output a positioning result, that is, to automatically search for satellite signals and complete locking of the satellite signals, and output position information of longitude, latitude, and altitude of the aircraft. The RNSS module may include a B1 channel element and/or an L1 channel element. If the antenna device adopts a single mode, namely only a Beidou satellite or a GPS satellite is adopted for positioning, the RNSS module can only have a B1 channel unit or an L1 channel unit, and if the antenna device adopts a dual mode, namely both the Beidou satellite and the GPS satellite are adopted for positioning, the RNSS module can have an L1 channel unit and a B1 channel unit.
The RDSS module can be configured to complete short message receiving and sending under a high dynamic environment, including receiving of S frequency point signals and transmitting of L frequency point signals, and Doppler influence caused by aircraft motion is compensated in real time when the L frequency point signals are transmitted.
According to the utility model discloses display device 105 among aircraft attitude and position monitoring system can provide short message communication interface. The RDSS module automatically sends the short message information to the ground control equipment through Beidou satellite communication. The frequency of reporting is determined by the type of the user card.
Fig. 3 is a functional block diagram of an antenna arrangement of an aircraft attitude and position monitoring system according to an embodiment of the present invention.
The antenna device is electrically connected with the Beidou transmitting and receiving device through a wire lead-through feeder, and the wire lead-through feeder adopts a coaxial cable and an outer sheath.
The antenna device may include: an antenna 301, a first low frequency noise amplifier 302, a second low frequency noise amplifier 303, a low frequency power amplifier 304, a duplexer 305, and an antenna power supply unit (not shown).
The principles of the RNSS service receive path are: b1 and/or L1 frequency signals are input through the antenna 301, and finally merged into a wire line feeder through the first low frequency noise amplifier 302 and the duplexer 305.
The principle of RDSS service transmission is: the L-frequency signal is input through a wire-line feeder, and enters the antenna 301 through the duplexer 305 and the low-frequency power amplifier 304.
The principle of RDSS service reception is: the S-frequency signal is input through the antenna 301, and finally merged into a wire-line feeder through the second low-frequency noise amplifier 303 and the duplexer 305.
According to the technical scheme of the utility model, preferably adopt passive antenna, also can adopt active antenna. If the antenna adopts an active antenna, the power supply voltage is less than or equal to +28VDC +/-10%.
According to the technical scheme of the utility model, the antenna system can adopt single mode or multimode, adopts the single mode system to only adopt big dipper satellite or GPS satellite to fix a position promptly, adopts multimode system to adopt big dipper satellite and GPS satellite dual mode to fix a position promptly.
According to the utility model discloses an antenna of embodiment has three kinds of mode of RDSS, RNSS and GPS, adopts the duplexer to send and receive and keep apart, lets the transmitting signal reduce to minimum antenna and send and receive effectively between the passageway and send and receive and keep apart to the interference of received signal.
The above description of exemplary embodiments has been presented only to illustrate the technical solutions of the present invention, and is not intended to be exhaustive or to limit the present invention to the precise forms described. Obviously, many modifications and variations are possible in light of the above teaching to those skilled in the art. The exemplary embodiments were chosen and described in order to explain certain principles of the invention and its practical application to thereby enable others skilled in the art to understand, implement and utilize the invention in various exemplary embodiments and with various alternatives and modifications. It is intended that the scope of the invention be defined by the following claims and their equivalents.
Claims (9)
1. An aircraft attitude and position monitoring system, comprising: the Beidou satellite radio frequency identification system comprises a control device, a power supply device, a Beidou transmitting and receiving device and an antenna device;
the Beidou transmitting and receiving device is electrically connected with the control device and is configured to communicate with a Beidou satellite and/or a GPS satellite and ground control equipment;
the antenna device is electrically connected with the Beidou transmitting and receiving device and is configured to position the aircraft and transmit and receive short message frequency point signals;
the power supply device is electrically connected with the control device and the Beidou transmitting and receiving device and is configured to provide electric power for related modules in the control device and the Beidou transmitting and receiving device;
the control device includes:
an attitude sensor electrically connected to the central processor, the attitude sensor configured to automatically collect current attitude information of the aircraft;
a memory electrically connected to the central processor, the memory configured to store position information and attitude information of the aircraft;
and the central processing unit is configured to receive information of the attitude sensor and the Beidou transmitting and receiving device, store the received information in the memory and monitor the information, and trigger alarm when abnormity occurs.
2. An aircraft flight attitude and position monitoring system according to claim 1, wherein:
the aircraft flight attitude and position monitoring system further comprises a display device;
the display device is electrically connected with the control device and is configured to display position information, short messages and attitude sensor information.
3. An aircraft flight attitude and position monitoring system according to claim 1, wherein:
the antenna device is connected with the Beidou transmitting and receiving device through a wire-line feeder;
the wire harness feeder adopts a coaxial cable and an outer sheath.
4. An aircraft flight attitude and position monitoring system according to claim 1, wherein:
the Beidou transmitting and receiving device comprises an RNSS module and an RDSS module;
the RNSS module is configured to receive B1 and/or L1 frequency point signals in a high dynamic environment and finally output a positioning result;
the RDSS module is configured to complete short message receiving and sending under a high dynamic environment, including receiving of S frequency point signals and transmitting of L frequency point signals.
5. An aircraft flight attitude and position monitoring system according to claim 1, wherein:
the Beidou transmitting and receiving device is communicated with the control device through an RS-422 data transmission protocol.
6. An aircraft flight attitude and position monitoring system according to claim 2, wherein:
the display device and the control device communicate through an RS-422 data transmission protocol.
7. An aircraft flight attitude and position monitoring system according to claim 1, wherein:
the central processor comprises a processor with an ARM Cortex-M3 core model;
the attitude sensor is a six-axis sensor module using an MPU 6050 as a main chip.
8. An aircraft flight attitude and position monitoring system according to claim 1, wherein:
the antenna device comprises an antenna, a first low-frequency noise amplifier, a second low-frequency noise amplifier, a low-frequency power amplifier and a duplexer;
b1 and/or L1 frequency point signals are input through an antenna, and enter a wire-line feeder through a first low-frequency noise amplifier and a duplexer;
the L frequency point signal is input through a wire-through feeder line and enters the antenna through the duplexer and the low-frequency power amplifier;
and the S frequency point signal is input through an antenna, passes through the second low-frequency noise amplifier and the duplexer, and enters a wire-pass feeder.
9. An aircraft flight attitude and position monitoring system according to claim 8, wherein:
the antenna is a passive antenna or an active antenna;
the mode of the antenna adopts a single mode or a multi-mode.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120463063.6U CN214540529U (en) | 2021-03-03 | 2021-03-03 | Aircraft flight attitude and position monitoring system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120463063.6U CN214540529U (en) | 2021-03-03 | 2021-03-03 | Aircraft flight attitude and position monitoring system |
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| CN214540529U true CN214540529U (en) | 2021-10-29 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114040268A (en) * | 2021-11-08 | 2022-02-11 | 北京华力智飞科技有限公司 | Aircraft health monitoring system and control method thereof |
| WO2023134018A1 (en) * | 2022-01-11 | 2023-07-20 | 北京航空航天大学 | Aircraft and emergency navigation communication system based on beidou short message |
-
2021
- 2021-03-03 CN CN202120463063.6U patent/CN214540529U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114040268A (en) * | 2021-11-08 | 2022-02-11 | 北京华力智飞科技有限公司 | Aircraft health monitoring system and control method thereof |
| WO2023134018A1 (en) * | 2022-01-11 | 2023-07-20 | 北京航空航天大学 | Aircraft and emergency navigation communication system based on beidou short message |
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