RU2389001C1 - Complex velocity measurement system - Google Patents

Abstract

FIELD: physics. ^ SUBSTANCE: system additionally has units for high-precision correcting apparatus, for generating and storing correcting adjustments and an environment analyser. The first input of the correcting adjustment generating unit is connected to the output of the unit of correcting apparatus, the second input of the correcting adjustment generation unit is connected to the output of the basic velocity metre. The first input of the correcting adjustment storage unit is connected to the output of the environment analysis unit, and the second input is connected to the output of the correcting adjustment generation unit. Correcting adjustments are generated when information is available from correcting apparatus and are stored together with the feature of specific flight conditions in a correcting adjustment storage unit. ^ EFFECT: increased accuracy of measuring velocity. ^ 1 dwg

Description

The invention relates to complexes for navigation, control and guidance of aircraft (LA).

In the closest analogue given in the book [1] (Flerov AG, Timofeev VT Doppler devices and navigation systems. - M .: Transport, 1987), a speed meter (IS) of an aircraft based on the use of the Doppler effect is a Doppler velocity and drift meter (DISS), one of the serious drawbacks of which is the dependence of the shift of the spectrum of the Doppler signal on the type of reflective surface (see [1], pp. 19-22). Accounting and compensation of this dependence in the analogue is done by entering corrective corrections (ΔХOP _i , i = x, y, z), taking into account the nature of the reflecting surface and the radio transparency of the DISS hatch; moreover, the averaged values of these corrections are introduced for flights over land and over the sea: the correction for land is introduced automatically, for the sea - manually (see [1], pp. 19-22). However, since the indicated dependence is quite complex, the ΔCOP _i values for different specific conditions can differ significantly from the average values (over land, the range of ΔCOP _i varies from 0.09% to 0.71%, over the sea - from 0.97% to 2.3%) . As a result of this, degradation of the quality of the DISS correction is possible and the speed measurement system becomes ineffective.

The objective of the invention is to improve the accuracy of the IP and, as a consequence, increase the efficiency of the aircraft equipped with IP.

This result is achieved by the fact that an integrated system for determining the speed (KSOS), containing a basic speed meter and a correction unit, the input of which is connected to the output of the basic speed meter, and the output is the output of the KSOS, is additionally equipped with a block of corrective means, a block for generating corrective amendments, a storage block corrective amendments, by the situation analysis unit, wherein the first input of the corrective amendment forming unit is connected to the output of the corrective means unit, the second input of the unit correction corrections are connected to the output of the basic speed meter, the first input of the correction corrections storage unit is connected to the output of the situation analysis unit, the second input of the corrections corrections storage unit is connected to the output of the corrections corrections generation unit, the output of the corrections corrections storage unit is connected to the second input of the corrections block.

The drawing shows a block diagram of an integrated system for determining speed, containing the following blocks:

1 - basic speed meter LSI;

2 - block correction BC;

3 - block forming corrective amendments FKP;

4 - block storage corrective amendments BHKP;

5-block corrective tools BCS;

6 - block analysis of the situation of BAO.

The drawing also shows

7 - navigation complex NK,

not included in the proposed device.

Information exchange between the inputs and outputs of the blocks is carried out along the communication lines shown in the drawing by a thin solid line. Communication lines are known (described, for example, in the book [2], pp.21-24, 394-406) communication lines and information exchange, for example, via serial code, parallel code, multiplex, etc.

Block BIS 1 is a known device - DISS, described, for example, in the literature [1].

Block BCS 5 is a well-known sensors and systems on-board equipment of the aircraft described in the literature, for example [3], pp. 8-16,171-243, 316-317, 325-327, 374-385. The BCS 5 unit includes, for example, a satellite navigation system (SSS), which measures the time delay, phase shift, and Doppler frequency shift of radio signals from space satellites, with which the task of determining the time, coordinates and speed of an object is solved with known parameters of satellite motion; high-precision inertial navigation system, calculating the speed and coordinates of the object. Computational logic blocks BK 2, FKP 3, BAO 6 are made, for example, in the form of uniprocessor computers ([2], p.31). Block BHKP 4 is made, for example, on a read-only memory ROM ([2], p.30).

Block BK 2 provides the correction of the parameters issued by BIS 1, by the amount of corrections obtained using blocks FKP 3 and stored in the block BHKP 4, for example, using an algorithm of the form:

суть компоненты скорректированного (выходного) вектора скорости ЛА.Here

the essence of the components of the adjusted (output) aircraft velocity vector.

Additionally introduced block FKP 3 provides the calculation of corrective amendments to the speed of the aircraft, measured by BIS 1 for specific current flight conditions: over a certain type of reflective surface. In this case, the components of the velocity vector are used, measured, on the one hand, using LSI 1 and, on the other hand, using BCS 5. The algorithm for generating corrective corrections ΔХOP _i (i = x, y, z) can consist, for example, in averaging on the time interval T the magnitude of the relative difference of the form

ΔHOP _i (t _j ) = 1-V ^LSI (t _j ) / V ^BCS (t _j ),

where V ^LSI (t _j ) and V ^BCS (t _j ) are aircraft speeds at time t _j measured using LSI 1 and BCS 5, respectively.

ΔHOP _i is found as the average value of the current value ΔHOP _i (t _j ) in the time interval from t _j = t ₀ to t _j = t ₀ + T.

In order to filter measuring high-frequency measurement noise, a more complex algorithm for processing the measured values of V ^LSI and V ^BKS can be applied, for example, based on the least squares method (see, for example, literature [4], pp. 923-927), which minimizes the variance errors in estimating ΔХOP _i .

Additionally introduced block BHKP 4 provides storage of the received corrective corrections and flight conditions (type of underlying surface) for which these corrections are received. Also, this block provides the issuance of the desired correction values in the correction unit BC 2.

The additionally introduced BAO 6 unit, based on the analysis of the current state of the aircraft (coordinates, time of year and day), recognizes the type of reflective surface for address storage and the selection of corrective amendments in the BHKP 5 block.

CSOS works as follows.

Measured using BIS 1 speed V ^BNS LA is fed to the input of the unit BK 2, in which it is corrected using the obtained estimates ΔХOP _i (i = x, y, z) received in the unit BK 2 from the output of the unit BHKP 4. Corrected information

V ^output goes to the output of the BC 2, which is the output of the IC. In addition, the speed V of the ^BNS measured using BIS 1 is supplied to the second input of the FKP 3 block, the first input of which from the output of the BCS 5 receives the value of V ^BKS measured by corrective means from the composition of the BCS 5.

In block ФКП 3, the V ^VNS and V ^BKS values are processed; as a result, the corresponding corrective corrections for the current flight state (type of reflective surface) are determined.

According to the information received from NK 7, in the BAO 6 unit, recognition (identification) of the current flight conditions is carried out, for example: a day flight over a calm sea or a night flight over a forest, etc. Information about the flight conditions enters the unit BHKP 5, for example, in the form of an appropriate attribute.

Block BHKP 4 operates in two main modes: firstly, if there is information from BCS 5 and, accordingly, FKP 3; secondly, in the absence of such information, for example, when the signals of the BCS 5 block disappear (for example, when an aircraft enters the jamming zone for the SNA). In the first mode, the corrections generated in FKP 3 are recorded in the memory cell corresponding to the named flight conditions, and, in addition, these corrections are issued to the BK 2 unit for correction of the signals of the BIS 1 unit. memory (according to the conditions identified by the BAO unit 6) the previously recorded corrective corrections and their issuance to the BC unit 2. Introduction of the FKP 3, BCS 5 blocks to the IS structure ensures the prompt and accurate adjustment of the correction corrections for specific flight conditions, and the introduction of BHKP 4, BAO 6 blocks - storing these corrections for different conditions and selective sampling in the absence of reference information of the BCS 5 block.

Thus, the introduction of the described blocks into the IS structure provides flexible operational reconfiguration of the measurement system information processing algorithms, the formation, storage, and selection of corrective corrections most suitable for the current flight mode, thereby eliminating the shortcomings of the closest analogue and expanding the system's functionality.

The technical implementation examples show the achievement of a technical result in terms of expanding the functionality of the IS and, as a result, increasing the efficiency of the use of aircraft equipped with it.

LITERATURE

1. Flerov A.G., Timofeev V.T. Doppler devices and navigation systems. - M .: Transport, 1987

2. Presnukhin L.N., Nesterov P.V. Digital computers. - M .: Higher school, 1981

3. Babich O.A. Information processing in navigation systems. - M.: Engineering, 1991

4. I.N. Bronstein, K.A.Semendyaev. A reference book in mathematics for engineers and students of technical colleges. - M.: Science, GRFML, 1980

Claims (1)

An integrated system for determining speed, comprising a basic speed meter and a correction unit, the input of which is connected to the output of the basic speed meter, and the output is the output of an integrated system for determining speed, characterized in that the integrated system for determining speed is additionally equipped with a block of corrective means, a block for generating corrective corrections, a correction correction storage unit, a situation analysis unit, the first input of the correction correction generation unit being connected to the output of the correction means block, the second input of the correction corrections generating unit is connected to the output of the basic speed meter, the first input of the correction corrections storage unit is connected to the output of the situation analysis unit, the second input of the correction corrections storage unit is connected to the output of the correction corrections formation unit, the output of the correction corrections storage unit connected to the second input of the correction block.

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