RU2355603C1 - Emergency-warning system - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering, in particular, to aircraft and their crew search and rescue systems. The proposed system comprises a radio beacon with parachute arranged in aircraft recess. In incorporates also the mechanism intended for taking the said radio beacon from the said recess and unit to determine the availability of extreme conditions, which controls aforesaid mechanism. Radio beacon is connected with aircraft structure by a towing cable and furnished with water availability pickup, inflatable boat and uncoupling device. The proposed system comprises also the onboard radio beacon hardware and that of detecting crashed crew. The former includes receiving aerial, GPS-signal receiver, micro-controller, power supply controller, supply storage battery, generator of pseudo-random sequence, adder, master oscillator, phase modulator, mike, amplitude modulator, heterodyne, two mixers, first intermediate frequency amplifier, duplexer, transceiver aerial, high-frequency amplifier, 4^th intermediate frequency amplifier, amplitude limiter, synchronous detector and loud speaker. Aforesaid crashed crew detection hardware comprises a master oscillator, mike, amplitude modulator, heterodyne, two mixers, 3^rd intermediate frequency amplifier, duplexer, transceiver aerial, high-frequency amplifier, 2^nd intermediate frequency amplifier, amplitude limiter, synchronous detector, loud speaker, push-push phase amplifier, two narrow-band filters, binary phase divider, phase detector and recording unit. The system establishes a duplex voice communication between crashed crew and rescue team.

EFFECT: higher accuracy of locating crashed aircraft.

6 dwg

Description

The proposed system relates to aircraft, in particular to search and rescue systems for aircraft (aircraft) (aircraft, helicopters and space objects) and their crews.

Modern aircraft search and rescue systems are complex complexes of organizational and communication structures that provide solutions to problems at all stages of search and rescue operations, from transmitting information from disaster victims to planning and conducting rescue operations.

The search and rescue operation begins with the receipt of a message about the fact of the accident, it can be a distress signal from the crew, the aircraft disappearing from the radar screen, or communication is not possible for a certain time. After establishing the fact of the accident, it is necessary to determine the location of those in distress with an accuracy sufficient for the rescue teams to come into direct contact with the victims.

Modern search and rescue systems are being created on an international, national and departmental scale.

There are known systems for searching for missing (crashed) aircraft operating in the International Space Detection System that are in distress, COSPAS-SARSAT, which are based on an emergency beacon ("Emergency aircraft ejection beacon" Veshka-R ". Developer, Scientific Research Institute of Precision Instruments. M. , 1995).

However, the use of this device implies the presence of pyrotechnics, which contradicts the safety requirements and reduces the reliability of the search, thus preventing its use on passenger aircraft.

There are also known emergency signaling devices used on airplanes ("Manual for the technical operation of the TU-154M aircraft", section 025.64.00, C.3, 4, publication of the ANTK named after AN Tupolev, 1985) and are included in the emergency kit - rescue equipment used in the event of an emergency landing on land or on water. These are portable beacons and emergency radio stations located in the crew’s wardrobe, the probability of destruction of which is very high when a plane collides with the ground. Accordingly, the reliability of the search when using these devices is low.

In addition, alarm and rescue systems and devices are known (Auth. USSR certificate No. 431.063, 637.298, 765.113, 988.655, 1.348.256, 1.565.840, 1.506.841, 1.588.636, 1.615.054, 1.643 .325, 1.664.653; RF patents Nos. 2.00.995, 2.038.259, 2.043.259, 2.051.838, 2.130.874, 2.193.990, 2.240.950, 2.265.557; US patents Nos. 3.405.887 , 3.621.501, 3.623.681, 3.921.944, 4.889.511, 6.607.166; UK patents Nos. 1,145.051, 2.228.458 and others).

Of the known systems and devices closest to the proposed is the alarm system (RF patent No. 2.130.874, B64D 25/00, 1999), which is selected as a prototype.

The composition of the known system includes a beacon with a parachute located in a niche on the aircraft, a mechanism for removing a beacon from a niche, and an emergency situation determination unit controlling a mechanism for removing a beacon from a niche. The beacon is equipped with a water sensor, an inflatable swimming device and a trip device. The beacon is connected to the aircraft structure by a towing rope, which ensures the location of the beacon in close proximity to the aircraft in distress. The reliability of the search is increasing both on land and at sea. The location of the aircraft that has suffered an accident should be made with accuracy sufficient for the quick exit of the rescue teams in direct contact with the victims of the disaster. In accidents on land, especially in difficult terrain, the accuracy should not exceed 100 meters.

However, the known system does not provide accurate location of the aircraft, the accident, and voice communication with its crew.

An object of the invention is to increase the accuracy of determining the location of an aircraft that has crashed, and to expand the functionality of the system by establishing duplex voice communication between the crew of the aircraft and rescuers.

The problem is solved in that the alarm system containing, in accordance with the closest analogue, a parachute beacon located in a niche on the aircraft, a beacon withdrawal mechanism from a niche and an emergency situation determination unit, a control mechanism for removing a beacon from a niche, while the beacon is connected to the aircraft structure by a towing file and is equipped with a water sensor, an inflatable swimming means and a trip device, differs from the closest analogue in that it is equipped with accident detection equipment located on board the aircraft, and the beacon equipment is made in the form of a series-connected receiving antenna, a GPS signal receiver, a microcontroller and a power controller, the second input of which is connected to the output of the power batteries, and the outputs are connected to the corresponding functional blocks in series included pseudo-random sequence generator, adder, the second input of which is connected to the second output of the microcontroller, phase mani a puller, the second input of which is connected to the output of the master oscillator, an amplitude modulator, the second input of which is connected to the output of the microphone, the first mixer, the second input of which is connected to the output of the local oscillator, an amplifier of the first intermediate frequency, a duplexer, the input-output of which is connected to the transceiver antenna , a high-frequency amplifier, a second mixer, the second input of which is connected to the output of the local oscillator, an amplifier of the fourth intermediate frequency, an amplitude limiter, a synchronous detector, the second input of which connected to the output of the fourth intermediate frequency amplifier and loudspeaker, the accident detection equipment contains a serially connected master oscillator, an amplitude modulator, the second input of which is connected to the microphone output, the first mixer, the second input of which is connected to the local oscillator output, the third intermediate frequency amplifier, duplexer, the input-output of which is connected to the transceiver antenna, a high-frequency amplifier, a second mixer, the second input of which is connected to the output of the local oscillator, amplifies a second intermediate frequency spool, an amplitude limiter, a synchronous detector, the second input of which is connected to the output of the second intermediate frequency amplifier, and a loudspeaker connected in series to the output of the amplitude limiter by a phase multiplier by two, the first narrow-band filter, a phase divider by two, the second narrow-band filter, phase a detector, the second input of which is connected to the output of the amplitude limiter, and a registration unit.

Figure 1 shows the system in working condition. Figure 2 shows the elements in the retracted position. Figure 3 - the same, at the time of pushing the beacon from a special niche. Figure 4 - the same, with the parachute fully open, pulling the beacon into position. Figure 5 presents the structural diagram of the equipment beacon. Figure 6 shows a structural diagram of equipment for the detection of accident victims.

The system includes a beacon 1 with an emphasis 2, a pusher 3, a node 4 connecting the slings 5, a parachute 6, placed in a special niche 7 of the aircraft 8; a control unit 9, receiving signals from sensors (not shown in FIGS. 1-4), fixing flight parameters, and connected to a toggle switch located in the cockpit (not shown); output mechanism 10 with lock 11; tow hitch 12 connected to the aircraft structure by a node 13 and to the beacon by means of a trip device 14.

The parachute consists of spring-loaded plates 15 with a latch 16, and the beacon is equipped with a sensor 17 for the presence of water and an inflatable swimming means 18.

The beacon equipment contains a serially connected receiving antenna 19, a GPS signal receiver 20, a microcontroller 21 and a power supply controller 22, the second input of which is connected to the output of the power supply battery 23, and the outputs are connected to the corresponding functional blocks, pseudo-random sequence generator (PSP) 24 connected in series, an adder 25, the second input of which is connected to the second output of the microcontroller 21, a phase manipulator 27, the second input of which is connected to the output of the master oscillator 26, the amplitude mode an oscillator 29, the second input of which is connected to the output of the microphone 28, the first mixer 31, the second input of which is connected to the output of the local oscillator 30, an amplifier 32 of the first intermediate frequency, a duplexer 33, the input-output of which is connected to the transceiver antenna 34, a high-frequency amplifier 35 , a second mixer 36, the second input of which is connected to the output of the local oscillator 30, an amplifier 37 of the fourth intermediate frequency, an amplitude limiter 38, a synchronous detector 39, the second input of which is connected to the output of the amplifier 37 of the fourth intermediate frequency, and loud Oritel 40.

The accident detection equipment contains a serially connected master oscillator 41, an amplitude modulator 43, the second input of which is connected to the output of the microphone 42, a first mixer 45, the second input of which is connected to the output of the local oscillator 44, an amplifier 46 of the third intermediate frequency, a duplexer 47, the input-output of which connected to the transceiver antenna 48, a high-frequency amplifier 49, a second mixer 50, the second input of which is connected to the local oscillator 44 output, a second intermediate frequency amplifier 51, an amplitude limiter 52, a synchronous detector 53, the second input of which is connected to the output of the amplifier 51 of the second intermediate frequency, and a loudspeaker 54, connected in series to the output of the amplitude limiter 52, a phase multiplier 55 into two, the first narrow-band filter 56, a phase divider 57 into two, the second narrow-band filter 58, phase a detector 59, the second input of which is connected to the output of the amplitude limiter 52, and the registration unit 60.

The system operates as follows.

In the event of an emergency, which is characterized by critical values of a number of flight parameters of the aircraft 8 (for example, exorbitant values of angles, descent speeds, unacceptable overloads and dangerous proximity to the ground), the control unit 9, receiving a signal from the corresponding sensor or directly from the pilot that turned on the toggle switch , generates a signal for the operation of the output mechanism 10. This opens the lock 11 and, as a result of exposure to the pusher 3 of the output mechanism 10, beacon 1 connected in node 4 with about the slings 5 of the parachute 6 and fastened by the stop 2 with the latch 16 of the spring-loaded plates 15 of the parachute 6, it is pushed out of the special niche 7. The parachute 6, opened by means of the spring-loaded plates 15, draws the beacon 1, removing the latter from the aircraft to the length of the towing rope 12. The towing of the beacon continues until the moment of the collision of the aircraft with the ground or with the water surface. Upon contact with the water surface, the sensor installed in the beacon for opening the inflatable craft 18, and in case of complete immersion of the beacon body in water - for the trip device 14 to trip, thus disconnects the beacon with the aircraft.

If a catastrophic situation was avoided, a parachute buoy towed behind the plane will not prevent the completion of the flight.

Simultaneously with the conclusion from the special niche 7 of the beacon 1, the microcontroller 21 is turned on, which controls the power controller 22, connecting the battery 23 power supply to all functional blocks of the equipment beacon.

To determine the coordinates of the accident site (width and longitude), a GPS signal receiver 20 with an antenna 19 is used, which receives a special navigation signal in the form of a binary phase-shift key (PSK) signal, phase-manipulated by a pseudo-random sequence (PSP). Two types of codes are encrypted in the signal. The C / A code is available to a wide range of civilian consumers, including the proposed system. It allows you to get only a rough estimate of the location of the emergency beacon with an accuracy of 50 meters, therefore it is called a “rough” code. The C / A code is transmitted at a frequency f = 1575 MHz using phase shift keying of the carrier frequency with a pseudorandom sequence of 1023 characters in length. Error protection is provided through the Gold Year. The repetition period of the C / A code is 1 ms, the clock frequency is 1.023 MHz.

The P code provides a more accurate calculation of coordinates, but not everyone can use it; access to it is limited by the GPS service provider.

The microcontroller 21 receives navigation information from the GPS receiver 20, determines the coordinates of the scene of the accident and generates a digital code that is fed to the first input of the adder 25, to the second input of which a digital code is supplied from the output of the PSP generator 24. At the output of the adder 25, a modulating code M (t) is generated, which contains N chips of duration

τ _E. In this case, the first n elementary parcels carry digital information about the aircraft that crashed (country, aircraft type, its board number, crew, etc.), m elementary parcels inform about the coordinates of the accident site (N = n + m )

The master oscillator 26 generates a high-frequency oscillation

which is fed to the first input of the phase manipulator 27, to the second input of which a modulating mode M (t) is supplied from the output of the adder 25. An FMK signal is generated at the output of the phase manipulator 27

where φ _k (t) = {0, π} - manipulated component phase DPSK mapping law in accordance with a modulation code M (t), wherein φ _k (t) = const at kτ _E ≤t≤ (k + 1) τ _E and can change abruptly at t = kτ _E , i.e. at the borders between elementary premises (k = 1, 2, ..., N);

τ _E , N is the duration and number of chips that make up a signal of duration T ₁ (T ₁ = Nτ _E ), which is fed to the first input of the amplitude modulator 29, to the second input of which an analog message is sent from the microphone 28 output (human voice - accident crew member). At the output of the amplitude modulator 29, a complex signal is formed with combined phase shift keying and amplitude modulation (FMn-AM)

where m ₁ (t) is the modulating function of the amplitude modulation (voice of the person who crashed), which is fed to the first input of the first mixer 31, to the second input of which the voltage of the local oscillator 30

At the output of the mixer 31, voltages of combination frequencies are generated. The amplifier 32 is allocated the voltage of the first intermediate (total) frequency

;Where

;

- первая промежуточная (суммарная) частота;

- the first intermediate (total) frequency;

which through the duplexer 32 enters the transceiver antenna 34, is radiated by it, is captured by the transceiver antenna 48, and through the duplexer 47 and the high-frequency amplifier 48 it enters the first input of the mixer 50 of accident detection equipment installed on an aircraft (helicopter, aircraft, spacecraft of the COSPAS-SARSAT system). The voltage of the local oscillator 44 is supplied to the second input of the mixer 50

At the output of the mixer 50, voltages of combination frequencies are generated. The amplifier 51 is allocated the voltage of the second intermediate (differential) frequency

;Where

;

- вторая промежуточная (разностная) частота;

- second intermediate (difference) frequency;

,

,

which is fed to the input of the amplitude limiter 52, at the output of which a voltage is generated

where U ₀ is the limit threshold,

с выхода усилителя 51. На выходе синхронного детектора 53 формируется низкочастотное напряжениеwhich is an QPSK signal, is used as a reference voltage and is fed to the first (reference) input of the synchronous detector 53, to the second (information) input of which a voltage is applied

from the output of the amplifier 51. At the output of the synchronous detector 53, a low-frequency voltage is formed

,

,

,Where

,

which is input to the speaker 54. The latter plays an alarming voice message transmitted from the scene of the accident.

представляющее собой ФМн-сигнал, с выхода амплитудного ограничителя 52 поступает на входы фазового детектора 59 и умножителя 55 на два. На выходе последнего образуется гармоническое напряжениеVoltage

representing an QPSK signal, from the output of the amplitude limiter 52 is fed to the inputs of the phase detector 59 and the multiplier 55 by two. The output of the latter produces a harmonic voltage

,Where

,

in which phase manipulation is already absent. This voltage is allocated by the narrow-band filter 56 and is fed to the input of the phase divider 57 into two. The output of the latter produces a harmonic voltage

which is allocated by a narrow-band filter 58, is used as a reference voltage and is supplied to the reference input of the phase detector 59. At the output of the latter, a low-frequency voltage is generated proportional to the modulating code M (t)

,Where

,

which is fixed by the registration unit 60. The indicated voltage contains information about the aircraft that crashed (country, type of aircraft, its flight number, crew, etc.), as well as information about the coordinates of the scene of the accident. This information is necessary for the rescue teams to come into direct contact with the victims.

After receiving an alarming voice message, rescuers establish a duplex voice communication with the victims. To do this, the master oscillator 41 is turned on, which generates a high-frequency voltage

,

,

which is fed to the first input of the amplitude modulator 43, to the second input of which an analog message is supplied from the output of the microphone 42 (voice of a human rescuer). The output of the amplitude modulator 43 produces a voltage with amplitude modulation (AM)

,

,

where m ₂ (t) is the modulating function of the amplitude modulation (voice - human-savior), which is fed to the first input of the first mixer 45, the second input of which is supplied with the voltage u _g2 (t) of the local oscillator 44. At the output of the mixer 45, the frequencies of the combination frequencies . Amplifier 46 distinguishes the voltage of the third intermediate (total) frequency

,

,

,Where

,

- третья промежуточная (суммарная) частота;

- third intermediate (total) frequency;

,

,

which through the duplexer 47 enters the transceiver antenna 48, is radiated by it into the air. The transceiver antenna 34 is captured and, through the duplexer 33 and the high-frequency amplifier 35, is supplied to the first input of the mixer 36, the second input of which is supplied with the voltage u _g1 (t) of the local oscillator 30. At the output of the mixer 36, the frequencies of the combination frequencies are generated. The amplifier 37 is allocated the voltage of the fourth intermediate (differential) frequency

,

,

;Where

;

- четвертая промежуточная (разностная) частота;

- the fourth intermediate (difference) frequency;

,

,

which is fed to the input of the amplitude limiter 38, at the output of which a harmonic voltage is generated

,

,

where U _o is the limit threshold,

which is fed to the first (reference) input of the synchronous detector 39, the second (information) input of which is supplied with voltage u _pr4 (t) from the output of the amplifier 37 of a quarter intermediate frequency. The output of the synchronous detector 39 is formed low-frequency voltage

,

,

;Where

;

which is fed to the input of the speaker 40. The latter plays the voice message of the rescuer. Thus, a duplex voice communication between victims and rescuers is established, which provides quick detection and rescue of victims of an accident.

If the victims do not have the physical ability to establish duplex voice communication with rescuers, then the proposed system provides automatic rescue of the emergency FMN signal containing information about the aircraft that has suffered an accident (country, aircraft type, its board number, crew, etc.) .) and the coordinates of the scene of the accident. At the same time, the output from the special niche of the beacon and the automatic transmission of the alarm FMN signal does not occur at the moment of contact with the ground, but in advance, in the event of an emergency, and the operating time of the beacon increases, and the probability of damage to it when it collides with the ground decreases.

Thus, the proposed emergency rescue system in comparison with the prototype provides improved accuracy in determining the location of the aircraft of the accident. This is achieved using global navigation satellite systems GPS or GLONASS, which allow you to determine the scene of an accident with an accuracy of several tens of meters, which fully meets the requirements of search and rescue systems. Currently, small-sized GPS receivers with low power consumption have appeared. It became possible to integrate such a receiver into the beacon equipment and broadcast the coordinates of the location of the accident. For this, complex signals with combined phase modulation and amplitude modulation (FMN-AM) are used, which also provide the establishment of duplex voice communication between the accident victims and rescuers.

Signals with phase shift keying open up new possibilities in alarm transmission technology. They allow you to apply a new type of selection - structural selection. This means that there is a new opportunity to separate signals operating in the same frequency band and at the same time intervals.

From the point of view of detection, complex QPSK signals have high energy and structural secrecy. This is especially important in the event of an emergency landing on enemy territory, when a military alarm system should ensure the secrecy of information transmission, since the enemy can detect and capture the victims of disaster by the signals of an emergency beacon.

The energy secrecy of these signals is due to their high compressibility in time and spectrum with optimal processing, which reduces the instantaneous radiated power. As a result, a complex QPSK signal at the receiving point may be masked by noise and interference. Moreover, the energy of a complex QPSK signal is by no means small; it is simply distributed over the time-frequency domain so that at each point of this region the signal power is less than the power of noise and interference.

The structural secrecy of complex QPSK signals is due to the wide variety of their shapes and significant ranges of parameter changes, which makes it difficult to optimize or at least quasi-optimal processing of complex QPSK signals of an a priori unknown structure in order to increase the sensitivity of the receiver.

For synchronous detection of the received QPSK signal, a reference voltage is needed, which is extracted directly from the received QPSK signal.

With the development of microprocessor technology, satellite navigation, and digital radio communications, technical solutions have been well developed that allow developing an alarm system with the technical characteristics required when performing search and rescue tasks. The existing elemental base allows you to implement the equipment in the given weights and dimensions.

Thus, the functionality of the system has been expanded, which allows us to hope for its widespread use by emergency and rescue services of civil and military aviation.

Claims (1)

An alarm system containing a beacon with a parachute located in a niche on an aircraft, a beacon removal mechanism from a niche and an emergency situation determination unit controlling a beacon removal mechanism from a niche, while the beacon is connected to the aircraft structure by a towing rope and is equipped with a water presence sensor , an inflatable swimming means and a trip device, characterized in that it is equipped with accident detection equipment located on board the aircraft, The beacon equipment is made in the form of a series-connected receiving antenna, GPS-signal receiver, microcontroller and power supply controller, the second input of which is connected to the output of the power supply batteries, and the outputs are connected to the corresponding functional blocks, of a pseudo-random sequence generator, of an adder, the second input of which is connected to the second output of the microcontroller, phase manipulator, the second input of which is connected to the output of the master oscillator, amplitude modulator RA, the second input of which is connected to the output of the microphone, the first mixer, the second input of which is connected to the output of the local oscillator, the amplifier of the first intermediate frequency, duplexer, the input-output of which is connected to the transceiver antenna, high-frequency amplifier, second mixer, amplifier of the fourth intermediate frequency , an amplitude limiter, a synchronous detector, the second input of which is connected to the output of the amplifier of the fourth intermediate frequency, and a loudspeaker, the equipment for the detection of accident victims contains the following specifically included a master oscillator, an amplitude modulator, the second input of which is connected to the output of the microphone, the first mixer, the second input of which is connected to the local oscillator output, a third intermediate frequency amplifier, a duplexer, the input-output of which is connected to a transceiver antenna, a high frequency amplifier, a second mixer, the second input of which is connected to the output of the local oscillator, an amplifier of the second intermediate frequency, an amplitude limiter, a synchronous detector, the second input of which is connected to the output of the amplifier of the second intermediate an exact frequency, and a loudspeaker connected in series to the output of the amplitude limiter by a two-phase multiplier, a first narrow-band filter, a phase divider by two, a second narrow-band filter, a phase detector, the second input of which is connected to the output of the amplitude limiter, and a recording unit.

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