Method of measuring relative flight altitude of "air-surface" class rockets
 Method for finding one's bearings on the ground and device for its realization / 2247921The method consists in measurement of the object coordinates, observer's coordinates and transmission of them for further use, as well as in finding of the observer's bearings with due account of obtaining of target designation and determination of the error of the preset and current coordinates. The observer performs scanning of the ground with fixation of the readings of the azimuth and elevation angle sensors, readings of the device for determination of the observer's own coordinates at detection by it of the object of observation. These data are transmitted to an individual control device of the observer. The own coordinates of each observer via individual transceivers are transmitted to the control and computations device of a group equipment, having a storage unit, which contains a digital model of the ground relief of observation and a data base for target distribution and renewal. The obtained data on location of the observers, as well as of the targets from the data base for target distribution are applied to the relief digital model. The data on the relative location of the observer and the target distributed to him are transmitted via the transceivers to the observer's control device, in which they are compared with the data obtained from the azimuth and elevation is transmitted to the indicators of the vertical and horizontal turning of the observer's scanning device. The device for finding one's bearings on the ground has location and orientation sensors, control and computations device, transceivers, scanning device for the observer with indicators of vertical and horizontal turning, sensors of the location in space in azimuth and angle of elevation, device for determination of the observer's own coordinates, having a navigational equipment linked with a satellite. The observer's transceiver is coupled to a group transceiving device connected to the control and computations device of the group equipment. The control and computations device of the group equipment comprises a storage unit, having a ground relief digital model and a data base for target distribution. |
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Method for finding one's bearings on the ground and device for its realization / 2247921 The method consists in measurement of the object coordinates, observer's coordinates and transmission of them for further use, as well as in finding of the observer's bearings with due account of obtaining of target designation and determination of the error of the preset and current coordinates. The observer performs scanning of the ground with fixation of the readings of the azimuth and elevation angle sensors, readings of the device for determination of the observer's own coordinates at detection by it of the object of observation. These data are transmitted to an individual control device of the observer. The own coordinates of each observer via individual transceivers are transmitted to the control and computations device of a group equipment, having a storage unit, which contains a digital model of the ground relief of observation and a data base for target distribution and renewal. The obtained data on location of the observers, as well as of the targets from the data base for target distribution are applied to the relief digital model. The data on the relative location of the observer and the target distributed to him are transmitted via the transceivers to the observer's control device, in which they are compared with the data obtained from the azimuth and elevation is transmitted to the indicators of the vertical and horizontal turning of the observer's scanning device. The device for finding one's bearings on the ground has location and orientation sensors, control and computations device, transceivers, scanning device for the observer with indicators of vertical and horizontal turning, sensors of the location in space in azimuth and angle of elevation, device for determination of the observer's own coordinates, having a navigational equipment linked with a satellite. The observer's transceiver is coupled to a group transceiving device connected to the control and computations device of the group equipment. The control and computations device of the group equipment comprises a storage unit, having a ground relief digital model and a data base for target distribution. |
 Method of measuring relative flight altitude of "air-surface" class rockets / 2249830Method can be used for designing of control system for rockets and radio altimeter for getting information on relative altitude of flight of rocket without irradiating radio signals at low and high frequencies and at irradiating of low energy at extremely low altitude flights. Before flight airplane-carrier of "air-surface" class rockets is placed into position with well known coordinates. Airplane-carrier is equipped with consumer navigation instrumentation which receives radio signals of GLONASS or GPS either both systems. Coordinates of position of aerial of consumer navigation instrumentation are calculated on the base of radio signals. Differential corrections if coordinates of airplane-carrier on the base of known real coordinates airplane-carrier. Values of differential corrections are introduced into consumer navigation instrumentation placed onto rocket before taking off. During flight of consumer navigation instrumentation rocket the plane coordinates of rocket and absolute altitude of flight of rocket are determined when taking differential corrections into account. Plane coordinates of rocket achieved during flight are introduced into digital map of region and height of region above which the rocket moves instantly is determined from plane coordinates. Relative altitude of flight is calculated and radio altimeter is switched on if relative altitude drops lower than calculated altitude of safe flight. |
 Method of finding location of mobile station / 2252429Method can be used in cellular communication systems for finding location of mobile station. Maximal precision of location is achieved at minimal total energy of signals transmitted during location procedure. Correction of errors is provided which errors relate to absence of signal propagation direct beam. Decision of location completeness is made upon forming estimation of coordinates of mobile station. For the purpose the data is used which are available at any base station immediately after reception of location signal as well as estimations of coordinates formed later. Moreover, step of correction of measured times of arrival of location signal is introduced to correct errors. Correction is based upon detecting of absence of propagation direct beam and on subtracting value of compensation being proportional to average radius r of area of objects of dissipation close to mobile station. |
 United universal control system / 2255350The united universal control system has an integrating control center with a central server, party dispatching system and party control centers, the interconnected by communication means integrating control center has an additional cartographic server and a router, the cartographic server and the central server are connected to the router, which, in its turn is connected to the dispatching system and party control centers via communication means, for example, via wire ones via modems. Each party control center has a server connected via a modem to the communication line. The party control systems have: a party navigation system, party remote measurement system, party telecontrol system and a monitoring system of object travel. |
 Method and system for quality-based location of site / 2255433Novelty is that request on location includes information about quality for determining desired quality of location service quality, checkup of information about quality in location request transmission channel of cellular communication network, and selection of network component to be used for locating wireless terminal basing on requirement to quality indicated by means of information about quality, network component being chosen out of base network and cellular communications radio access network components in which location can be found. |
 Method for spectral-temporal signals transformation / 2256934Signal U1 is converted from analog form to frequency form, forming its frequency spectrum S1, received frequency spectrum S1 is converted to frequency spectrum S2 by multiplication of each component of spectrum S1 on transformation coefficient N - constant, value of which is selected on basis of providing of necessary length of output signal, frequency spectrum S2 is scaled by division of amplitude of each component on compression coefficient N, thereby forming scaled frequency spectrum S2m, scaled frequency spectrum S2m is converted from frequency zone to time zone, thereby forming a digital signal, which is then converted from digital form to analog with parameters different from base signal. |
 System, method and user's terminal in system of unambiguous determination of location with the use of two satellites on lo- altitude near-earth orbit / 2256935The offered system has a mobile telephone set, interline integration unit, at least two satellites with known orbits, means for determination of such parameters as the distance from the user's terminals to each of the satellites and their difference. Provision is also made for means (one or both) for determination of such parameters as the radial velocity of one of the satellites relative to the user's terminal and the difference between the radial velocities of one and the other satellite relative to the user's terminals. The means for location of the user terminal in the interline integration unit is engageable with the above means. It acts on the basis of the known positions and velocities (orbits) of the satellites and the above parameters: distances of satellites from the user's terminals, radial velocities and the their differences. Estimations of the positions of the satellites are specified on the basis of processing of the results of measurements of the given parameters. |
 Method for forming and compressing radio signals / 2258939Method includes emission of packet of M radio pulses, each on own frequency, different from frequency of adjacent radio pulse for frequency Δf. radio signals reflected from radio-contrast objects, which amplify and digitize, are received, while frequency of discretization for analog-digital conversion is set equal to Fadc=MΔf, to form M·K amplitudes of received radio signals, which are subjected to amplitude weighing operations and discontinuous Fourier transformation for M points. Resulting signals are compressed in M times compared to received ones. |
 Railway train location checking system / 2265543Proposed system has "n" navigational satellites, checking-and-correcting station determining information on satellites required for operation of railway train which contains navigational receiver and position computer. Checking-and-correcting station contains additionally input unit whose output is connected with second input of modulator and series connected section-between-stations computer, block section computer and interface unit whose output is connected with locomotive control system, section-between stations memory unit whose output is connected with first input of section-between-stations computer, second input of which is connected with output of position computer, block section memory unit whose output is connected with second input of block section computer whose third input is connected with output of demodulator. |
 Arrangement for radio navigational determination of the coordinates and the speed of a moving object in conditions of action of unfavorable geometric factor / 2265864The arrangement has four blocks of aboard equipment of navigational cosmic apparatus(NCA), two blocks of navigational equipment of the user(NEU), a block of correcting evaluations of the coordinates and the velocity component of the object, a demodulator, a receiver, two antennas, a block of computation of evaluations of the navigational equipment of the user each of which has two accumulating summation units with reset, a block of computing weight coefficients, nine blocks of subtraction, a meter of cycle impulses, eight elements «I», six blocks of remultiplication and a block of multiplication on a constant coefficient. |
FIELD: navigation.
SUBSTANCE: method can be used for designing of control system for rockets and radio altimeter for getting information on relative altitude of flight of rocket without irradiating radio signals at low and high frequencies and at irradiating of low energy at extremely low altitude flights. Before flight airplane-carrier of "air-surface" class rockets is placed into position with well known coordinates. Airplane-carrier is equipped with consumer navigation instrumentation which receives radio signals of GLONASS or GPS either both systems. Coordinates of position of aerial of consumer navigation instrumentation are calculated on the base of radio signals. Differential corrections if coordinates of airplane-carrier on the base of known real coordinates airplane-carrier. Values of differential corrections are introduced into consumer navigation instrumentation placed onto rocket before taking off. During flight of consumer navigation instrumentation rocket the plane coordinates of rocket and absolute altitude of flight of rocket are determined when taking differential corrections into account. Plane coordinates of rocket achieved during flight are introduced into digital map of region and height of region above which the rocket moves instantly is determined from plane coordinates. Relative altitude of flight is calculated and radio altimeter is switched on if relative altitude drops lower than calculated altitude of safe flight.
EFFECT: improved precision of measurement.
1 dwg
The alleged invention relates to navigation, and more particularly to meters altitude, is aimed at solving stealth missile of class "air-surface" and can be used for designing control systems of missiles and radio altimeters.
Known radio way of measuring the relative flight altitude H of the aircraft (LA) [1], pages 10-17, namely, that on the LA set the radio altimeter (RV), measured time t of passage of radio waves from the aircraft to the ground and back calculate the altitudewhere C is the speed of light. As RV used RV with frequency [2] or pulse [3] modulation of the emitted signal.
The disadvantage of this method of measuring the altitude of LA is a large range of dORTRdetection LA means electronic reconnaissance on radiation PB, which can be defined [4], page 330, as
where PAnd- average radiated power;
λ - wavelength PB;
GPB, n is the gain and level of the lateral radiation of the transmitting antenna PB, respectively;
GPTP, RCR- gain antenna and the minimum received power of the receiver station signals intelligence (RTR), respectively.
If, for example, [2] PAnd =0.1 W, λ =0,07 m, GRV=20, n=0,01, a GRTR=200, PCR=10-12W, DORTR=35,4 km
This value of DORTRgreatly exceeds the range of DRadardetection of missile radar station (radar), defined according to [5], page 14, as
where RRadarthat λ , G, PDIRLSrespectively radiated power, wavelength, the antenna gain and the minimum received power receiver radar;
S - scattering cross-section of the rocket.
If, for example, RRadar=25000 W λ =0.25 m, G=1000, S=0.01 m2and RDIRLS=10-12W, DRadar=9.4 km, i.e. the detection range missile radar is significantly less than the detection range missiles station RTR signals emitted from the RV.
The purpose of the proposed invention is to reduce the detection range missiles station RTR on radiation RV.
This objective is achieved in that before take-off aircraft-carrier missile of class “air-surface”, equipped with the navigation equipment of the consumer (EmOC), set in the point whose coordinates are known with high accuracy, take a NAP aircraft navigation radio satellite navigation systems (SNS) GLONASS or GPS, or both, calculate the coordinates of the voltage plane, knowing true to the ordinate, calculate and memorize differential corrections (DOC) Δ x, Δ, Δ N and introduce them to the NRA missiles before launch, in-flight NAP missiles determine with regard to PD planned coordinates and the absolute height of Handenter the planned coordinates of the missile, its flight, a digital terrain map (CSM), define a height Htothe terrain over which flies at the moment the missile, and calculate the relative flight altitude Habout=Nand-Nto.
The technical result of the implementation of the proposed method is to obtain sufficiently accurate information about the relative flight altitude without emitting radio signals during flight at low and high altitudes, and when the radiation of low power when flying at extremely low altitudes, which increases the stealth and combat effectiveness of the missile of class “air-surface”, the control system which implements the proposed method for obtaining information about the relative flight altitude.
As shown in [6], page 367, the required radiated power PAnddefining dORTRproportional to the square of the maximum height Hmax. Therefore, to reduce the dORTRit is proposed to obtain information about small and large relative heights of the rocket flight using (crns), operating in differential mode [8], the Tr. 162 to 165, upon receipt and entry of the DP on the proposed method, and SMC, and the smallest height Hminflight measured with PB midget heights (RSPS)with low radiant power PAnd. In this case, RAndmay be reduced To time
The sequence of operations of the proposed method is illustrated in the functional diagram in the drawing, which shows:
1 - instrument aircraft carrier missiles (ASNR), which includes:
2 - navigation equipment consumer EmOC;
3 - transmitter differential corrections (TTP);
4 - apparatus missiles (AR), which includes:
5 - navigation equipment consumer (NAB-P);
6 - digital maps (CSM);
7 - the transmitter relative height (WWII);
8 - radio ultra-low heights (RSMV).
Communication between blocks is shown in the drawing and are, for example, the serial code and the code RS-232C interface.
The inventive method is characterized by the following sequence of actions:
1 - the plane before takeoff include NAP-2;
2 - establish the aircraft in a location whose coordinates are known with high precision;
3 - receive navigation signals of at least four navigation satellites and determine a pseudorange;
4 - calculate what the pseudorange planned coordinates of the aircraft;
5 - knowing the true coordinates of the plane, compute the DP on the planned coordinates Δ x, Δ and the height Δ N and memorize them;
6 - enter the DP before launch at NAB-P 5;
7 - in the process of rocket flight using NAB-R 5 is determined taking into account DP absolute flight altitude Handand the planned coordinates xandand Iandgiving CKM;
8 - determine the altitude Htoover which flies at the moment the rocket, by entering information about the planned coordinates output voltage-R 5 in CCM;
9 - calculate the relative height according to the formula
Habout=Nand-Nto
and give information about it to the consumers;
10 - include RSMV 8 when H0equal to the estimated height of the flight safety;
11 - give consumers information about the height of RSMV 8.
Additional measurement error of height, resulting in the implementation of this method, minor and its mean value can be definitely as
where σSMC- the standard error of the SMC;
σIn- error “age”.
As shown in [7], pages 47-48,
where σto- error primary mapping, σto=(2-3) m;
σDP- accuracy sample rate field.
According to the schedule, given Nomo in [7] on page 48, for moderate terrain σDP<1.5 m for sampling Δ <250 m
Then
In [8], page 165, it is shown that σIn=σFO+t· V+b· L,
where σFO=2.28 m;
t is the time between time tDPcalculate the PD and its use;
L - distance between points get DP and its use;
V and b are coefficients, time-based and range, respectively,
V=1,32· 10-3m/s, b=438· 10-5m/km
We can assume that L=LWith+LAnd,
where LWith- the range of the joint flight of aircraft and missiles;
LAnd- range Autonomous flight of a rocket.
If, for example, LWith=350 km, LAnd=150 km, and the average flight speed of the aircraft and rockets VWith=300 m/s, then
t=500· 103/300=1666 s and σB=2,28+1,32· 10-3·1666+438· 10-5·500=6,66 m
Thus, for the considered case
Such a small error can reduce the maximum measured height of the RV to the value
Hmin=Nbp=Nb+3σD,
where Nbp- estimated height of a safe flight;
Hballowable height of a safe flight.
If Hb=20 m, Hmin=20+22,5=42,5 m
The resulting value of Hminconsiderably is about less than the maximum height H max=2000 m, measured RVA [2].
Such a low altitude allowstime to reduce the radiated power and
time to reduce the detection range of radiation PB, i.e. dORTR=0,75 km
Instrument realization of the proposed method will not lead to a significant increase in mass and volume of the onboard devices. The main device that increases the weight of the devices necessary for the implementation of this method is NAP-R. But, as shown in [9], page 6, OAD installed on the newly designed and upgraded aircraft and missiles. As for the mass of the SMC, it is insignificant. As shown in [7], page 107, discretes planned coordinates SMC, it is advisable to select equal to 125 m, and for recording one field value of the relief is rather 8 bits. If the area of the launch aircraft carrier is limited by the size of 200x200 km, the SMC (VSMC=8• 8• 200• 8• 200=2.56 MB).
This memory provides one ROM type LH28F032 SUTD [11]with the amount of memory is 4 MB.
Currently, user navigation equipment SRNS GLONASS and GPS is widely used for determining the location of a wide class of objects for military and civilian purposes, as with the use of modern integrated circuits is achieved small overall size is, weight and low cost OAD.
Therefore, the proposed method meets the requirement of the terms "Industrial applicability" (P "Rules SP-2").
Thus, the proposed method of measuring the relative height of the missiles flight navigation spacecraft radio signals of satellite radio navigation systems and digital map is new and gives a positive effect, which consists in reducing the detection range of radiation PB means RTR.
Literature
1. Zhukovsky A.P. and other Theoretical issues radioisotopes. - Moscow: Soviet radio, 1979, p.10-17.
2. The product of RWA. Technical description GU-TO /WPCB “Item”, 1999, p.15.
3. Product A-035. Manual /WPCB “Item”, 1985, p.21.
4. Belotserkovsky G.B. fundamentals of pulse technique and radar systems, Leningrad: Sudostroenie, 1965, s.
5. SKOLNIK M. Introduction to the technique of radar systems. - M.: Mir, 1965, p.14.
6. Finkelstein M.I. fundamentals of radar. - M.: Radio and communication, 1983, s.
7. I. N. Beloglazov. Dzhandzhgava GI basics of navigation by means of geophysical fields. - M.: Nauka, 1985, p.47-48, 107, 162 to 165.
8. Global satellite navigation system GLONASS. Edited Vinaria, Ahipara, Vasoline. - M.: IPGR, 1998, s.162-164, 165.
9. Samples of the prospective impact of aviation armament US to you is take in Farnborough //Aviation and rocketry. - 2000. No. 34 (2142), p.6.
10. Efimenko B.C., Gorev A.P. study of the characteristics of the spatial-temporal processing for reception of signals of satellite radio navigation systems //Radiotekhnika. - 2001. No. 7, p.46-50.
11. Sharp FLASH Memoru LH28F032SUTD: Ad. prospect company SHARP, 2002.
The method of measuring the relative altitude of the missile of class "air-surface"consists in the fact that the relative flight altitude is determined by using the navigation equipment of the consumer satellite navigation system, digital terrain map or radio altimeter, characterized in that before take-off aircraft-carrier missile of class "air-surface", equipped with the navigation equipment of the consumer, set in the point whose coordinates are known with high accuracy, take the navigation equipment of the consumer, which is equipped with aircraft-carrier, the navigation radio navigation satellite system GLONASS or GPS or both systems, calculate the coordinates of the antenna navigation the equipment of the consumer, which is equipped with aircraft-carrier, knowing the true coordinates of the aircraft carrier calculates differential corrections coordinates of the aircraft carrier, is injected into a navigation apparatus of a consumer that is installed on the rocket before launch, in-flight missile Naviga the ion equipment consumer installed on the rocket, is determined taking into account differential corrections planned coordinates of the rocket and the absolute height of the rocket flight, enter the planned coordinates of the missile, its flight, a digital map of the area, determine the elevation of the TC, above which flies in the moment, rocket, calculate the relative height of the flight But=-NK and include the radio while reducing the relative flight altitude below the estimated height of the flight safety.