Method to detect support of power transmission line
SUBSTANCE: in the method for detection of a power transmission line support a radiolocating signal is emitted with an antenna, a reflected signal is received, the amplitude of the received signal is compared with the threshold value, at the same time scanning is carried out with a directivity pattern in a sector of power transmission line location, the distance D1 is measured by the first received reflected signal, which has exceeded the threshold value, the distance D2 is measured by the second received reflected signal, which has exceeded the threshold value, the absolute value of difference is found between measured distances ΔD=|D1-D2|, the decision on availability of a power transmission line support is made by position of the value ΔD within 0.1K≤ΔD≤K, where K - value of span between supports of a power transmission line.
EFFECT: provision of the possibility to detect a support of a power transmission line when there is no current in its wires.
There is a method of detecting electric pylons, which consists in first radiation antenna in the direction of bearing of the radar signal, receiving a reflected from the support signal, comparing the amplitude of a received signal with a threshold value, and the second antenna having a mechanical connection with the first antenna and spatial combined with her pattern, perform receiving and detecting the signal emitted by the wires of the transmission line, the decision about the presence of electric pylons take simultaneous exceed the amplitude of the received signal reflected from the electric pylons, and the detected signal radiated power transmission line wires, the threshold value (RF Patent for invention No. 2410709, m CL G01S 7/32 stranded, publ. 27.01.2011).
A device detection support power lines containing sequentially connected to the first antenna, transmitting a radar signal in the direction of electric pylons and receiving reflected from the support signal, the first mixer, the first intermediate frequency amplifier and the first threshold unit, and the first local oscillator, the output of which is connected to a second input of the first mixer and connected in series to the second antenna, which is the reception, mechanically connected with the first antenna and the within combined with her pattern, the second mixer, the second intermediate frequency amplifier and the second threshold unit and the second local oscillator, the output of which is connected to a second input of the second mixer, the outputs of the first and second threshold blocks are connected respectively with the first and second inputs of the device matches the output of which is the output device (RF Patent for the invention №2410709, m CL G01S 7/32 stranded, publ. 27.01.2011).
A disadvantage of the known method and device is a low probability of detection supports transmission line in the absence of current in the wires of the transmission line.
An object of the invention is the provision of opportunities for discovery supports transmission line in the absence of a current in its wires.
The technical result is achieved in that in the method for detecting electric pylons, which consists in radiating antenna of the radar signal, receiving a reflected signal, comparing the amplitude of a received signal with a threshold value, additionally carry out the scan pattern in a particular sector, measure the distance D1 to the first signal exceeding the threshold value, measure the distance D2 to the second signal exceeding a threshold value, find the absolute value of the difference between the measured distancesthe decision on on the icii electric pylons are accepted by finding the value of ∆ D within C≤AD≤K, where the K - value of the span between supports transmission line.
The detecting device supports transmission line containing consistently connected the antenna, mixer, intermediate frequency amplifier and the first threshold unit and the local oscillator, the output of which is connected to a second input of the mixer further comprises a counter and a decoder, the odd-numbered outputs of which are connected with inputs of the first circuit OR, and even-numbered outputs of the decoder are connected to inputs of the second circuit OR, all outputs of the decoder, except the first, are connected with the inputs of the third circuit OR, and the scanning unit, mechanically coupled with the antenna, the transmitter, the unit of measurement of distance, and the second output of the transmitter connected to the first the input unit of measurement of distance, a second input connected to the output of the first threshold unit, the output unit measurement range is connected with the first inputs of the first and second registers, a second input of the first register is connected to the output of the first circuit OR the second input of the second register is connected to the output of the second circuit OR the third inputs of the first, second register and a second input of the counter is connected with an electric output of the scanning unit, the outputs of the first and second registers are connected to first and second inputs of the subtraction unit, a third input connected to vyhoda the third scheme, OR the output of the subtraction unit is connected to the input of the unit for computing the absolute value, and its output to the input of the second threshold device whose output is the output device.
The drawing shows a functional diagram of the device detection support power lines, where: 1 - antenna, 2 - mixer, 3 - amplifier intermediate frequency, 4, 18 - threshold block, 5 - lo, 6 - block scan 7 - transmitter, 8 - unit measurement range, 9 - count, 10 - decoder, 11, 12, 13 schema, OR, 14, 15 registers, a 16 - block subtraction, 17 - unit finding the absolute value.
The detecting device supports transmission line contains consistently connected the antenna 1, a mixer 2, the intermediate frequency amplifier 3, the first 4 threshold unit, the counter 9 and the decoder 10, the odd-numbered outputs of which are connected with the inputs of the first 11 scheme OR, and even-numbered outputs of the decoder 10 is connected to the second inputs 12 schema OR all outputs of the decoder 10, except the first, are connected with the inputs of the third 13 scheme OR, as well as the local oscillator 5, the output of which is connected to a second input of the mixer 2, the scanner unit 6 is mechanically connected to the antenna 1, the transmitter 7, the unit of measurement of distance is 8, and the second output of the transmitter 7 is connected to the first input unit measurement range 8, a second input connected to the output of the first 4 p the horn unit, the output unit measurement range 8 is connected with the first inputs of the first 14 and second 15 registers, a second input of the first 14 of the register is connected to the first output 11 of the scheme OR, as the second input of the second 15 of the register is connected to the second output 12 of the circuit OR the third inputs of the first 14, 15-second registers and a second input of the counter 9 is connected to the electrical output of the scanning unit 6, the outputs of the first 14 and second 15 registers are connected to first and second inputs of the subtraction unit 16, the third input of which is connected with the third output 13 of the circuit OR the output of the subtraction unit 16 is connected to the input of block calculate the absolute value of 17, and its output to the input of the second threshold device 18 whose output is the output device.
The device operates as follows.
When scanning the airspace chart the direction of the radar device, the scanning unit 6 is mechanically controls the antenna in a predetermined path scanning. First sector scanning of the scanning unit 6 given the signal to reset the counter 9, the first 14 and second 15 registers. The signal reset is supplied to the second input of the counter 9 and the third inputs of the registers. The transmitter 7 generates a pulse signal through the antenna 1 sends them into the air. The transmitter 7 outputs a signal, synchronously with the emitted pulse and signals, at the first input of the computing unit range 8. The reflected signal is received by the antenna 1 is converted, amplified and fed to the input of the first 4 threshold device. If the received signal exceeds the threshold value, which is designed for electric poles, then the output of the first threshold device 4, a signal occurs. This signal is applied to the measurement unit, range 8, and the counter 9. The output signal from the counter is supplied to the decoder 10, at the first output of the decoder 10, a signal is generated. The output of the decoder 10 has two output groups. The first group consists of the outputs, with odd numbers, the second group is even. Thus, with the first group of outputs of the decoder 10, the signal at the first input 11 of the circuit OR. With the release of the first 11 circuit OR the signal at the second input (input record) of the first 14 of the register, to the first input of which has already received a signal proportional to the distance to the support, with the unit of measurement of distance is 8. When the presence of a signal on the second input of the first 15 register provides a record of information about the distance to the first bearing in the first 15 to register. Upon further scanning at the output of the first 4 threshold unit 4 again, you may receive the signal which is also fed to the second input unit measurement range 8 and to the input of the counter 9. From the output of the counter 9, the signal is sent to the decoder 10. When the volume on the second output of the decoder 10, a signal is generated. This signal through a second group of outputs of the decoder 10 is supplied to the second input 12 of the circuit OR, and with its output to the second input (input record) 15 second register to the first input of which has already received a signal from the measurement unit, range 8. When this signal proportional to range, is recorded at 15 second register. The output signal of the first 14 and second 15 registers are received at first and second inputs of the subtraction unit 16. The third input (control input) signal from the third output 13 of the circuit OR. The signal at the third output 13 of the circuit OR in the presence of a signal on at least one of the outputs of the decoder 10, except the first. The presence of a signal on the third input of the subtraction unit 16 initiates his work. A signal proportional to the difference of the distances, from the output of the subtraction unit 16 via the unit by finding the absolute value of 17 is supplied to the second threshold device 18. If the values of ∆ D is within K≤ ∆ D≤K, then this means that a radiopaque object is the electricity pylon.
The way to detect electric pylons, which consists in radiating antenna of the radar signal, receiving a reflected signal, comparing the amplitude of a received signal with a threshold value, characterized in that you are doing the scanning pattern in the sector location of the transmission line to measure the relevance of D1 on the first taken to the reflected signal, exceeding the threshold value, measure the distance D2 adopted on the second signal exceeding a threshold value, find the absolute value of the difference between the measured distances ∆ D=|D1-D2|, the decision on whether electric pylons are accepted by finding the value of ∆ D within 0.1K≤ ∆ D≤K, where K is the magnitude of the span between supports transmission line.
FIELD: radio engineering.
SUBSTANCE: measurement of aircraft flight altitude is carried out by changing resolution characteristics by distance of a complicated probing radar signal. A radar meter of low heights comprises a weakly directional transceiving antenna, a circulator, a high frequency generator, a modulator, a mixer, a narrow band filter, a frequency indicator, a frequency detector, a clock pulse generator, a pulse accumulator and a logical device "AND", which are connected to each other in a certain manner. At the same time first inputs of the high frequency generator, the clock pulse generator and the height indicator are connected to a terminal, to which a "Start" command is sent.
EFFECT: ability to measure low heights at a final stage of aircraft landing onto a lengthy surface.
SUBSTANCE: invention relates to aircraft engineering and may be used in developing helicopters with in-line rotors. Proposed system comprises set of transmitters, analysis unit and set of receivers. Receiver outputs are connected to first set of data inputs of analysis unit. Analysis unit output is connected via onboard computer with helicopter control and/or indication components. Second set of data inputs s connected with appropriate set of onboard computer outputs.
EFFECT: helicopter safety.
3 cl, 3 dwg
FIELD: radio engineering.
SUBSTANCE: device to prevent helicopter collisions with high-voltage power transmission lines, comprises an antenna connected at a receiver's input, n narrow-band filters and n threshold units, a detector of k/n type, a sound indicator, a circuit OR, a brightness indicator, besides, the receiver's output is connected to inputs of n narrow-band filters, outputs of which are connected to inputs of n threshold units, outputs of which are connected to inputs of the detector of k/n type, the output of which is connected to the input of the sound indicator and with the first input of the circuit OR, m-1 inputs of which are connected to the outputs of the detector of k/n type of m-1 devices of helicopter collision prevention, arranged on the same helicopter, at the same time antennas of devices for prevention of helicopter collisions arranged on the helicopter are aligned in different directions, the output of the circuit OR is connected to the input of the brightness indicator.
EFFECT: reduced time for detection of signals of a high-voltage power transmission line and simplified arrangement of the device.
SUBSTANCE: proposed device additionally comprises unit configured in definite way to determine encounter conditions, indicator of safe approach time and warning device to annunciate critical safe distance to obstacle. Note here that car speed meter, first and second data processing system outputs and power supply are connected to first, second, third and fourth inputs of encounter condition unit with its first and second outputs connected to inputs of safe approach time indicator, and critical safe distance annunciator.
EFFECT: higher safety.
2 cl, 2 dwg
SUBSTANCE: proposed method comprises determining critical safe distance at given speed in compliance with the following expression: where Scur is current distance to obstacle, Vapp in approach speed, Sbr is forecast braking distance determined on short-term depressing brake pedal in compliance with the following expression: where V0 is initial braking speed, km/h; τc is braking system delay; τinc is delay increase interval; js-st is steady-state increase, m/s2. Braking system delay is determined in compliance with expression τc=τr+τinc where τr is driver reaction time, τinc is delay increase interval. Driver reaction time is determined periodically in preset intervals proceeding from recording intervals between receiving command signal on pedal depression and pedal depression by driver.
EFFECT: higher safety.
3 cl, 2 dwg
FIELD: radio engineering.
SUBSTANCE: proposed method can be used to provide safety of flights of aircrafts, to monitor the approach and docking of space vehicles (SV). Composite signal is shaped with double phase manipulation corresponding to processing of signal and separation of low-frequency voltage proportional to identification number of object.
EFFECT: enlarging functional capabilities of the method by providing the objects with ID numbers.
SUBSTANCE: value of a signal which forms the width of the overlap zone of the directional pattern in the vertical plane is determined. The value of the signal which determines the range of angles of displacement of the directional pattern upwards and downwards is calculated. During antenna scanning in the vertical plane relative a stabilised position in the horizontal plane, the range signal for dangerous approach of the aircraft to the position of the object in the vertical plane relative the given altitude interval between flight levels in the overlap zone is determined, relative which a signal is generated in form of UP or DOWN marks when a dangerous object is found above or below the given altitude interval in the overlap zone. When a dangerous object is found in the overlap zone, UP and DOWN mark signals are generated simultaneously and when the dangerous object reaches the dangerous approach range, a collision prevention signal is generated.
EFFECT: high flight safety due to automatic flight control and preventing collision with objects in the vertical plane in a given flight altitude interval between flight levels.
2 cl, 6 dwg
SUBSTANCE: set of invention relates to road traffic safety. In compliance with this invention, set of acceleration magnitudes for target vehicle is defined proceeding from input values derived from determined distances between vehicle and target vehicle (moving ahead and behind of it). Accelerations are further processed to obtain data describing said target vehicle. Said data is transmitted for adjustment of vehicle driving.
EFFECT: higher safety thanks to better adaption to target vehicles.
21 cl, 9 dwg
FIELD: physics, radio.
SUBSTANCE: invention can be used to prevent collision of helicopters with high-voltage power transmission lines (PTL). The method involves receiving electromagnetic oscillations reflected from power transmission line poles in the radio wave range using a radar direction finder mounted on the helicopter. The direction finder scans space in the direction of flight of the helicopter. Locating angles α1, α2 and range values D1, D2 to each of the two power transmission line poles are determined. The range values are then compared and if D1<D2, the range DPTL to cables of the PTL in the direction of the axis of the helicopter and the angle β of the position of the cables of the PTL relative the direction of the axis of the helicopter, respectively, are determined using the expression:
if D1>D2 the range DPTL in the direction of the axis of the helicopter and the angle β of the position of the cables of the PTL relative the direction of the axis of the helicopter, respectively, are determined using the expression:
if D1=D2, the range DPTL in the direction of the axis of helicopter is determined using the expression: DPTL=D2·cosα2. The decision to correct the direction of flight of the helicopter is made based on the range value.
EFFECT: high accuracy of determining distance to cables.
FIELD: physics, radio.
SUBSTANCE: invention relates to radar engineering and can be used to prevent collision of helicopters with high-voltage power transmission lines. The invention involves receiving electromagnetic oscillations reflected from a power transmission line pole in the radio wave range using a first and a second direction finder mounted on a helicopter and lying on the front at a distance B from each other. Each direction finder scans the space in the direction of flight of the helicopter, where the first direction finder scans anticlockwise and the second - clockwise. Locating angles of each of the two power transmission line poles is determined by each direction finder, where α1, α2 are locating angles of the first and second power transmission line poles determined by the first direction finder, and β1, β2 are locating angles of the first and second power transmission line poles relative the axis of the helicopter, determined by the second direction finder. Distance to cables of the power transmission line in the direction of the axis of the helicopter is determined using the expression , where B is distance between direction finders, µ is the angle between the power transmission line and the axis of the helicopter. The distance to the cables of the power transmission line on the direction of the axis of the helicopter is determined taking into account wind velocity using the expression: , where αdr is the angle of drift (the angle between the course surface and the path plane). The decision to correct the direction of flight of the helicopter is made based on the range value.
EFFECT: high reliability of preventing collision of a helicopter with power transmission lines.
FIELD: radio detection and ranging, applicable in traffic control systems and prevention of collisions of transport facilities.
SUBSTANCE: the method is accomplished by radiation of a continuous frequency-modulated sounding signal, reception of the reflected signal in one or several spatial positions, multiplication of it with the radiated signal and subtraction of the matrix of the values of the correlation functions of the obtained homodyne signal and the two-dimensional (range, speed) matrix of the base signals formed of the modulating signal. The ranges and speeds of the detected objects are computed according to the number of the elements of the matrix of the correlation functions, in which the values of the correlation functions exceed the threshold level. The value of speed is specified by subtraction of the frequencies of the spectrum components of the correlation signals obtained as a sequence of values of the correlation function values during the time of signal accumulation. At reception of the reflected signal in several spatially spaced positions a three-dimensional (range, speed, angular coordinate) or four-dimensional matrix of base signals is formed for each position, and, according to the numbers of the respective matrix summary to the positions of the correlation functions, the range, angular co-correlation functions, the range, angular co-ordinates and speeds of the detected objects are determined. The system for measurement of speeds and co-ordinates of the objects has an antenna-feeder device, homodyne transceiver correlometer forming the matrices of the base signals and computing the functions of correlation and correlation signals, and a processor forming the modulating signal and computing the object speeds and coordinates.
EFFECT: enhanced accuracy of measurement of object speeds and coordinates, effective range, resolving power at provision of safety of road traffic.
24 cl, 9 dwg
FIELD: aeronautical engineering; determination of aircraft-to-aircraft distance.
SUBSTANCE: aircraft-to-aircraft distance is determined by the following formula: where position of first of first aircraft is defined by azimuth α1, slant range d1, altitude h1 and position of second aircraft is determined by azimuth α2, slant range d2 and altitude h2. Proposed device includes aircraft azimuth indicators (1,4), flying altitude indicators (2,5), indicator of slant range to aircraft (3,6), adders (7, 14, 15, 19), multiplication units (8-12, 16, 18), cosine calculation unit 913), square root calculation units (17-20) and indicator (21).
EFFECT: avoidance of collision of aircraft; enhanced safety of flight due to determination of true aircraft-to-aircraft distance with altitude taken into account.
FIELD: radio engineering.
SUBSTANCE: radar can be used for view forwarding of front semi-sphere (lower and upper) of light-weight maneuver airplanes and helicopters to prevent collision against other flying vehicles, high-voltage power lines, towers, pipes and etcetera. Radar is made of three parts: aerial which has first and second phased aerial sub-arrays and control computing unit. Any sub-array has N irradiators, phase commutator, ferrite circulator, first self-excited oscillator and low noise amplifier. Control computing unit has adder, receiver, microcontroller, second self-excited oscillator, and LCD indicator and alarm unit.
EFFECT: improved safety of flight.
4 cl, 4 dwg
FIELD: control of air transport motion.
SUBSTANCE: in each design of the group for measurement of the altitude relative to the ground radio waves are received radiated downwards by a lying-by aeroplane. Then, the data on fluctuations of the level of the electric field strength of such radio waves are introduced and recorded in the computer. The time of passage-by of the nearest point is determined on the basis of the time of onset of clearly defined peaks irrespective of the frequency of motion.
EFFECT: enhanced accuracy.
8 cl, 12 dwg, 12 tbl
FIELD: radio engineering, in particular, radiolocation, possible use for observing frontal hemisphere, measuring flight height of light maneuverable planes and helicopters, having minimal equipment, and also for preventing collisions with other aircrafts, high power communication lines, towers, pipes and the like.
SUBSTANCE: multifunctional radio-locator contains phased antenna array, supporting quartz generator, impulse power amplifier, antenna switch, low-noise amplifier, video detector, digital computing device and liquid-crystalline indicator, and also additionally includes second of the following: supporting quartz generator, impulse power amplifier, antenna switch, phased antenna array, low-noise amplifier and video detector.
EFFECT: increased flight safety of light motor aircraft due to radio locator, combining functions of both surveillance radio locator and height meter.
4 cl, 3 dwg
FIELD: transport engineering.
SUBSTANCE: invention can be used as sensor warning the driver of possibility of collision of automobile with obstacle in emergency. Proposed system to prevent collision of vehicles moving in column has antenna, modulator, two power amplifiers, mixer, frequency converter, detector, two speed recorders, distance recorder, dangerous distance calculator as to distance, running speed and approach speed, continuous-wave oscillator, summer, circulator, Doppler frequency filter, antenna position control circuit and two actuating circuits.
EFFECT: reduction of mutual interferences and provision of direct action onto moving automobile when distance between vehicles is dangerous.
FIELD: radar systems used for prevention of collision of helicopter with high-voltage power lines.
SUBSTANCE: device proposed for prevention of collision of helicopter with high-voltage power lines includes first antenna (1), receiver (2), first and second switches (3) and (4), first threshold unit (5), first flip-flop (6), tuneable filter (7), second threshold unit (8), n-discharge shift register (9), type k/n detector (10), first AND-circuit (11), second flip-flop (12) and brightness indicator (13), first OR-circuit (14), third flip-flop (15), sound indicator (16), clock pulse generator (17), second AND-circuit (18), frequency divider (19), second OR-circuit (20) and single-discharge counter (21), logic unit (22), first and second time delay units (23) and (24), third switch (25), fourth switch (26), second antenna (27), antenna switch (28), shift register (29), n-AND gates(30), n-decoders (31), third OR gate (32), command forming unit (33) for performing "anti-collision" maneuver of helicopter, indicator (34) for furnishing the signal on change of helicopter motion trajectory and fourth flip-flop (35).
EFFECT: enhanced safety of helicopter flights.
3 cl, 3 dwg
FIELD: measuring technique.
SUBSTANCE: device comprises request unit and repeater. The request unit has master oscillator, first local oscillator, first mixer, shift register, phase manipulator, amplifier of intermediate frequency, first and second power amplifiers, first diplexer, first receiving-transmitting aerial, second local oscillator, second mixer, amplifier of the third intermediate frequency, unit for doubling phase, phase divider, first and second narrow-band filters, fourth mixer, unit for measuring Doppler frequency, correlator, multiplier, low-pass filter, extremum controller, unit for controlled delay, and distance indicator. The repeater has the second receiving transmitting aerial, second diplexer, third and fourth power amplifiers, third local oscillator, third mixer, and amplifier of the second intermediate frequency.
EFFECT: expanded functional capabilities.
2 cl, 4 dwg
FIELD: flying safety.
SUBSTANCE: method comprises scanning in the direction of helicopter flight with a narrow-band aerial, analyzing the signals obtained at each angular position of the aerial, determining angular position of the high-voltage power line with respect to the helicopter, comparing the angular position obtained with reference one, and sending a signal to the pilot on changing trajectory.
EFFECT: enhanced reliability.
FIELD: radio engineering, possible use for detecting position of objects using radiolocation systems, may be used for observation of frontal hemisphere, measuring flight height of light maneuverable airplanes and helicopters, having minimal hardware, and also for preventing collisions with other aircrafts, high voltage electric lines, towers, pipes, etc.
SUBSTANCE: multi-functional radio-locator contains first and second supporting quartz generators, power amplifiers, antenna switches with diagram generation circuits, phased antenna arrays, low noise amplifiers, video detectors and also - digital computing device, liquid crystalline indicator, information processing block, "dangerous height" indicator and "turn-away" indicator.
EFFECT: increased flight safety of light airplane due to radio locator which determines minimally safe distance to moving object or an obstacle, and also minimally safe flight height.