CN108363034B - Thermo-magnetic beacon fog-penetrating navigation landing system - Google Patents
Thermo-magnetic beacon fog-penetrating navigation landing system Download PDFInfo
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- CN108363034B CN108363034B CN201810230945.0A CN201810230945A CN108363034B CN 108363034 B CN108363034 B CN 108363034B CN 201810230945 A CN201810230945 A CN 201810230945A CN 108363034 B CN108363034 B CN 108363034B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S1/00—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
- G01S1/02—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using radio waves
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S1/00—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
- G01S1/70—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using electromagnetic waves other than radio waves
Abstract
The invention discloses a thermomagnetic beacon fog-penetrating navigation landing system, which comprises a ground thermomagnetic beacon transmitting device and an airborne thermomagnetic imaging receiving device, wherein the ground thermomagnetic beacon transmitting device comprises a pulse power supply oscillator, a power amplifier, a pulse amplifier, an infrared thermomagnetic emitter and a signal emitter, the pulse power supply oscillator is connected with the power amplifier, the power amplifier is respectively connected with a power end and an input end of the pulse amplifier, and the infrared thermomagnetic emitter is connected with an output end of the pulse amplifier; the infrared thermo-magnetic emitter is in wireless connection with the airborne thermo-magnetic imaging receiving device through the signal emitter. The invention can send out a thermomagnetic composite signal with kinetic energy effects of fog penetration, light penetration, snow protection coverage and the like on the ground, so that a clear navigation beacon track diagram can be formed on the ground as a thermomagnetic beacon, a pilot can clearly see the navigation beacon track diagram on the ground in severe weather environment, and the technical problem that an airplane cannot land effectively in severe environment is solved.
Description
Technical Field
The invention relates to the technical field of navigation, in particular to a thermo-magnetic beacon fog-penetrating navigation landing system which is used for enabling an aircraft to land safely at night or in a weather state with serious haze.
Background
An aircraft is an aircraft that generates lift by a fixed wing, generates a push (pull) force by a propulsion device, and flies in the atmosphere and is heavier than air. The aircraft is widely applied to civil transportation and scientific research, and is also an important weapon in modern military, so that the aircraft is divided into civil aircraft and military aircraft. Compared with other vehicles, the airplane is widely used by the modern society due to the advantages of high speed, safety, comfort and the like.
However, the aircraft has limitations as a transportation means, and besides the expensive price and the limitation of the landing place, the aircraft is also affected by weather conditions, and although the prior aviation technology can adapt to most of weather conditions, the weather conditions such as wind, rain, snow, fog, haze and the like still influence the landing safety of the aircraft. The method comprises the following steps: when the aircraft is in a night or in a state that haze is serious, and a pilot cannot visually observe a ground navigation signal lamp in a normal landing sight range, the aircraft cannot land safely, so that flight efficiency is affected, and potential safety hazards exist. Therefore, a new technology capable of safely landing on a guided aircraft is urgently required.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provide a thermo-magnetic beacon fog-penetrating navigation landing system.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the utility model provides a thermomagnetic beacon passes through fog navigation landing system which characterized in that: the device comprises a ground thermo-magnetic beacon transmitting device and an airborne thermo-magnetic imaging receiving device, wherein the ground thermo-magnetic beacon transmitting device comprises a pulse power supply oscillator, a power amplifier, a pulse amplifier, an infrared thermo-magnetic emitter and a signal emitter, and the device comprises the following components:
the pulse power supply oscillator is used for providing pulse current and voltage for the power amplifier;
the power amplifier is used for amplifying current and voltage and transmitting the current and the voltage to the pulse amplifier in two paths;
the pulse amplifier is used for amplifying current and providing electromagnetic pulse signals to control the infrared thermo-magnetic emitter to work;
the infrared thermo-magnetic emitter is used for emitting a thermal infrared signal, an electromagnetic pulse signal and an address code signal of the infrared thermo-magnetic emitter and transmitting the signals to the airborne thermo-magnetic imaging receiving device through the signal emitter;
the airborne thermomagnetic imaging receiving device is used for processing the received signals and outputting video signals of the specific position of the infrared thermomagnetic emitter.
The infrared thermo-magnetic emitter comprises an emitting module, a temperature control module and a GPS module, wherein the emitting module is used for emitting thermal infrared signals and electromagnetic pulse signals, the GPS module is used for emitting address code signals, and the temperature control module is used for controlling the temperature of the thermal infrared signals emitted by the emitting module.
The infrared thermo-magnetic emitter is connected with a sampling module, and the sampling module is connected with the monitoring center and used for monitoring the infrared thermo-magnetic emitter.
The ground thermo-magnetic beacon transmitting device further comprises a feedback control resistor, one end of the feedback control resistor is connected between the pulse amplifier and the infrared thermo-magnetic emitter, and the other end of the feedback control resistor is connected to the input end of the pulse amplifier.
The airborne thermomagnetic imaging receiving device comprises a signal receiver, an infrared thermomagnetic signal coding receiver, a processor, a shaping amplifier, an image signal coding processor and display equipment, wherein:
the infrared thermo-magnetic signal coding receiver is used for processing the signals received by the signal receiver and outputting the signals to the shaping amplifier;
the shaping amplifier amplifies the signal and outputs the signal to the image signal coding processor;
the image signal encoding processor processes the input signal and outputs a video signal to the display device.
The number of the shaping amplifiers is two, the infrared thermo-magnetic signal coding receiver outputs two paths of signals to the two shaping amplifiers respectively, and the two paths of signals are video signals and electromagnetic pulse signals respectively.
The display device comprises a display screen and head-mounted LED display glasses, and the image signal encoding processor outputs two paths of video signals to the display screen and the head-mounted LED display glasses respectively.
The invention has the advantages that:
the invention can send out a thermomagnetic composite signal composed of a thermoinfrared signal and an electromagnetic pulse signal through the ground thermomagnetic beacon transmitting device, and the thermomagnetic composite signal has the kinetic energy effects of fog penetration, light transmission, snow prevention coverage and the like, so that a clear navigation beacon track graph can be formed on the ground as a thermomagnetic beacon. The navigation beacon track map information comprises a point track beacon which is formed by guiding infrared thermomagnetic signals and is visible in image and an address code beacon which is formed by a geographic position GPS (BD-Z) of a thermomagnetic infrared emitter, and when the superposition beacons of the two beacons are combined into a whole, a navigation beacon track map of the real-time dynamic auxiliary landing system is formed. The navigation beacon track map can be clearly presented in the display device in the form of real-time video through the onboard thermomagnetic imaging receiving device. Therefore, through the cooperation of the ground thermo-magnetic beacon transmitting device and the airborne thermo-magnetic imaging receiving device, a pilot can clearly observe a navigation beacon track diagram on the ground in a severe weather environment, landing is facilitated, flight efficiency is greatly improved, the safety problem that an airplane cannot land in a severe environment can be avoided, and the technical problem that the airplane cannot land effectively in the severe environment is effectively solved.
Drawings
Fig. 1 is a logic diagram of the present invention.
Fig. 2 is a functional block diagram of the present invention.
Fig. 3 is a schematic circuit diagram of a terrestrial thermo-magnetic beacon transmitting device according to the present invention.
Fig. 4 is a schematic circuit diagram of an on-board thermomagnetic imaging receiving device according to the present invention.
Detailed Description
As shown in fig. 1 and 2, the invention provides a thermomagnetic beacon fog-penetrating navigation landing system, which comprises a ground thermomagnetic beacon transmitting device and an airborne thermomagnetic imaging receiving device, wherein the ground thermomagnetic beacon transmitting device comprises a pulse power supply oscillator, a power amplifier, a pulse amplifier, an infrared thermomagnetic transmitter and a signal transmitter, the pulse power supply oscillator is connected with the power amplifier, the power amplifier is respectively connected with a power end and an input end of the pulse amplifier, and the infrared thermomagnetic transmitter is connected with an output end of the pulse amplifier; the infrared thermo-magnetic emitter is in wireless connection with the airborne thermo-magnetic imaging receiving device through the signal emitter. The infrared thermo-magnetic emitter comprises an emitting module, a temperature control module and a GPS module, wherein the emitting module and the GPS module are connected with the signal emitter, and the pulse amplifier and the temperature control module are connected with the emitting module. The emission module can be an electromagnetic heating coil structure and is used for emitting thermal infrared signals and electromagnetic pulse signals, the GPS module is used for emitting address code signals of the infrared thermal magnetic emitter, the temperature control module is used for controlling heating temperature, and specifically, the temperature difference between the temperature of infrared waves and the temperature difference of environment is controlled to be kept at about 25 degrees. The thermal infrared signal and the electromagnetic pulse signal sent by the transmitting module and the address code signal sent by the GPS module are sent by the signal transmitter. The ground thermo-magnetic beacon transmitting device further comprises a feedback control resistor, one end of the feedback control resistor is connected between the pulse amplifier and the infrared thermo-magnetic emitter, and the other end of the feedback control resistor is connected to the input end of the pulse amplifier. Further, the infrared thermo-magnetic emitter is connected with a sampling module, and the sampling module is connected with a monitoring center and used for monitoring the infrared thermo-magnetic emitter.
The functions of all the components in the ground thermo-magnetic beacon transmitting device are as follows:
the pulse power supply oscillator is used for providing pulse current and voltage for the power amplifier.
The power amplifier is used for amplifying current and voltage, and transmitting the current and the voltage to the pulse amplifier in two paths, wherein one path is directly supplied to the pulse amplifier as a power supply, and the other path is supplied to the pulse amplifier as pulse signal control of the output end of the pulse amplifier.
The pulse amplifier is used for amplifying current and providing electromagnetic pulse signals to control the infrared thermo-magnetic emitter to work.
The infrared thermo-magnetic emitter is used for emitting thermal infrared signals, electromagnetic pulse signals and address code signals of the infrared thermo-magnetic emitter, and the signals emitted by the infrared thermo-magnetic emitter are sent to the airborne thermo-magnetic imaging receiving device through the signal emitter.
The on-board thermomagnetic imaging receiving device is used for processing the received signals, analyzing the specific position of the ground thermomagnetic beacon transmitting device on the ground, forming a navigation beacon track graph according to the specific position of the ground thermomagnetic beacon transmitting device, and finally outputting video signals of the navigation beacon track graph formed by the specific position of the infrared thermomagnetic transmitter.
The feedback control resistor is used for protecting the temperature output by the pulse amplifier to the infrared thermo-magnetic emitter from being controlled to be in a comparison state which is 15-25 ℃ higher than the ambient temperature of the infrared thermo-magnetic emitter.
The machine-mounted thermomagnetic imaging receiving device comprises a signal receiver, an infrared thermomagnetic signal coding receiver, a processor, a shaping amplifier, an image signal coding processor and display equipment, wherein the signal receiver is connected with the infrared thermomagnetic signal coding receiver, the infrared thermomagnetic signal coding receiver is connected with the image signal coding processor sequentially through the shaping amplifier and the processor, and the image signal coding processor is connected with the display equipment. Specifically, the number of the shaping amplifiers is two, and the infrared thermo-magnetic signal coding receivers are respectively connected with the processor through the two shaping amplifiers. The display device comprises a display screen and head-mounted LED display glasses, and the image signal encoding processor is respectively connected with the display screen and the head-mounted LED display glasses.
The function of each component in the airborne thermomagnetic imaging receiving device is as follows:
the infrared thermo-magnetic signal coding receiver is used for processing signals received by the signal receiver and respectively outputting two paths of signals to the two sets of shaping amplifiers, wherein the two paths of signals are video signals and electromagnetic pulse signals respectively.
The two shaping amplifiers amplify the signals respectively and output the amplified signals to the image signal encoding processor respectively.
And the image signal encoding processor processes the input signals to obtain a navigation beacon track diagram formed by the ground thermo-magnetic beacon transmitting device, and outputs video signals of the two navigation beacon track diagrams to the display screen and the head-mounted LED display glasses respectively.
The invention installs a plurality of ground thermo-magnetic beacon transmitting devices beside the navigation light position in the usual navigation line to form the navigation function of the thermo-magnetic beacon. The navigation track map formed by the plurality of ground thermo-magnetic beacon transmitting devices can be clearly presented in the display device when the aircraft lands.
The working principle of the ground thermo-magnetic beacon transmitting device is described below with reference to fig. 3:
1. the power supply rail VCC 12-24 v pulse power supply oscillator is used for carrying out gap oscillation, so as to provide regulated pulse high current and voltage for the power amplifier BG-1, the regulated pulse high current and voltage are supplied to the pulse amplifier AMP-1 through the emitter electrode e, and meanwhile, under the control of a local oscillation signal of the base electrode COS-1 crystal oscillator, the current output end e of the power amplifier BG-1 is ensured to have enough frequency pulse voltage and current.
2. The pulse signal current and voltage supplied from the e pole of the power amplifier BG-1 are transmitted to the pulse amplifier AMP-1 in two paths, one path is directly supplied to the pulse amplifier AMP-1 as the power supply of the amplifier, and the other path is coupled to the pulse amplifier AMP-1 through C1 as the pulse signal control of the output end of the pulse amplifier AMP-1. R2 is a feedback control resistor of the pulse amplifier AMP-1, and the temperature of the pulse amplifier AMP-1 output to the infrared thermo-magnetic emitter RLC-1 is controlled to be in a comparison state of 15-25 ℃ higher than the ambient temperature of the infrared thermo-magnetic emitter RLC-1.
3. When the infrared thermo-magnetic emitter RLC-1 emits a thermal infrared signal and an electromagnetic pulse signal, the temperature of the infrared thermo-magnetic emitter RLC-1 is also controlled to be 15-25 ℃ higher than the temperature of the surrounding environment, and a thermo-magnetic induction signal is continuously emitted, wherein the signal is a thermo-magnetic composite signal of the thermal infrared signal and the electromagnetic pulse signal, and the thermal-magnetic composite signal has the kinetic energy effects of fog penetration, light transmission, snow protection coverage and the like. Simultaneously, the thermo-magnetic composite signal and a signal which is sent by a GPS module and contains the address code of the infrared thermo-magnetic emitter RLC-1 are sent to an airborne thermo-magnetic imaging receiving device through a signal emitter TX; therefore, the device can be used as a thermomagnetic beacon to provide landing-assisting navigation mark signals for an airborne thermomagnetic imaging receiving device, and the safe landing of an aircraft is ensured.
4. When the infrared thermo-magnetic emitter RLC-1 radiates the thermal infrared signal and the electromagnetic pulse signal outwards, the thermal infrared signal and the electromagnetic pulse signal are simultaneously sampled into the sampling module CP-1 through C2 coupling for signal transfer and are supplied to a network interface RJ-45 signal trunk line for networking monitoring, so that the monitoring center can conveniently monitor the signals. Once the infrared thermo-magnetic emitter RLC-1 is damaged, the sampling signal of the sampling module CP-1 is lost, and the networking center has a prompt alarm.
The following describes the working principle of the airborne thermo-magnetic imaging receiving device with reference to fig. 4:
after receiving infrared thermo-magnetic pulse address code GPS/BD-Z transmitting signals transmitted by a ground infrared thermo-magnetic transmitter RLC-1, an airborne window signal receiver RLC-n and an infrared thermo-magnetic signal encoding receiver couple the signals into two paths through R5, C6, C7, L1 and C8 to a shaping amplifier IC-1 and a shaping amplifier IC-2 for shaping and amplifying, wherein the two paths of signals are as follows: one path is Video signals of an infrared band, the other path is electromagnetic pulse GPS/BD-Z signals, the two paths of signals are shaped and amplified and then enter a processor IC-101 to be subjected to in-phase superposition amplification, then enter an image signal coding processor through R11 and C9 to be processed, two paths of Video signals are output, one path is Video-1, and the two paths of signals are matched to an airborne display screen through R12 75 omega impedance to display a navigation beacon track route landing view consisting of ground thermomagnetic signals; the other path is a navigation beacon track diagram formed by the thermo-magnetic beacons, wherein the Video-2 is subjected to R13 omega impedance matching to the head-mounted LED display glasses of the pilot for display, and the two Video signals form a navigation beacon track diagram formed by the thermo-magnetic beacons, so that the pilot can clearly see the ground even in severe haze and other environments, landing is facilitated, and auxiliary navigation landing of the pilot in severe environments is solved.
Claims (4)
1. The utility model provides a thermomagnetic beacon passes through fog navigation landing system which characterized in that: the device comprises a ground thermo-magnetic beacon transmitting device and an airborne thermo-magnetic imaging receiving device, wherein the ground thermo-magnetic beacon transmitting device comprises a pulse power supply oscillator, a power amplifier, a pulse amplifier, an infrared thermo-magnetic emitter and a signal emitter, and the device comprises the following components:
the pulse power supply oscillator is used for providing pulse current and voltage for the power amplifier;
the power amplifier is used for amplifying current and voltage and transmitting the current and the voltage to the pulse amplifier in two paths;
the pulse amplifier is used for amplifying current and providing electromagnetic pulse signals to control the infrared thermo-magnetic emitter to work;
the infrared thermo-magnetic emitter is used for emitting a thermal infrared signal, an electromagnetic pulse signal and an address code signal of the infrared thermo-magnetic emitter and transmitting the signals to the airborne thermo-magnetic imaging receiving device through the signal emitter;
the airborne thermomagnetic imaging receiving device is used for processing the received signals and outputting video signals of the specific position of the infrared thermomagnetic emitter;
the airborne thermomagnetic imaging receiving device comprises a signal receiver, an infrared thermomagnetic signal coding receiver, a processor, a shaping amplifier, an image signal coding processor and display equipment, wherein:
the infrared thermo-magnetic signal coding receiver is used for processing the signals received by the signal receiver and outputting the signals to the shaping amplifier;
the shaping amplifier amplifies the signal and outputs the signal to the image signal coding processor;
the image signal encoding processor processes the input signal and outputs a video signal to the display device;
the number of the shaping amplifiers is two, the infrared thermo-magnetic signal coding receiver outputs two paths of signals to the two shaping amplifiers respectively, and the two paths of signals are video signals and electromagnetic pulse signals respectively;
the two paths of signals form a navigation beacon track diagram formed by the thermo-magnetic beacons, and an airborne pilot can clearly see the ground in a severe environment;
the display device comprises a display screen and head-mounted LED display glasses, and the image signal encoding processor outputs two paths of video signals to the display screen and the head-mounted LED display glasses respectively.
2. The thermo-magnetic beacon fog-penetrating navigational landing system of claim 1, wherein: the infrared thermo-magnetic emitter comprises an emitting module, a temperature control module and a GPS module, wherein the emitting module is used for emitting thermal infrared signals and electromagnetic pulse signals, the GPS module is used for emitting address code signals, and the temperature control module is used for controlling the temperature of the thermal infrared signals emitted by the emitting module.
3. The thermo-magnetic beacon fog-penetrating navigational landing system of claim 1, wherein: the infrared thermo-magnetic emitter is connected with a sampling module, and the sampling module is connected with the monitoring center and used for monitoring the infrared thermo-magnetic emitter.
4. The thermo-magnetic beacon fog-penetrating navigational landing system of claim 1, wherein: the ground thermo-magnetic beacon transmitting device further comprises a feedback control resistor, one end of the feedback control resistor is connected between the pulse amplifier and the infrared thermo-magnetic emitter, and the other end of the feedback control resistor is connected to the input end of the pulse amplifier.
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| CN201810230945.0A CN108363034B (en) | 2018-03-20 | 2018-03-20 | Thermo-magnetic beacon fog-penetrating navigation landing system |
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| CN201810230945.0A CN108363034B (en) | 2018-03-20 | 2018-03-20 | Thermo-magnetic beacon fog-penetrating navigation landing system |
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| CN108363034B true CN108363034B (en) | 2023-09-22 |
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