RU2391262C1 - Target sight system for aircraft - Google Patents

Abstract

FIELD: physics, optics.

SUBSTANCE: invention relates to automation of programmed and operational target detection process. The target sight system consists of: a detection and tracking unit, a target database, an operational target unit, an external target designation unit, a residual error generation unit, a unit for generating control parametres and a display unit. Programmed or operational target parametres are respectively entered into the external target designation unit from the target database. Parametres of relative position of the target and the aircraft are determined, which are compared with the current position of the line of vision in the residual error generation unit. The obtained residual error is processed in a filtration unit, at the output of which an estimate of the state vector of the system is generated, from which control parametres of onboard target sight apparatus are calculated in the unit for generating control parametres, where the said control parametres of onboard target sight apparatus are entered the detection and tracking apparatus unit where movement of the viewing device is controlled such that the line is directed on the target.

EFFECT: higher probability of hitting a target and efficiency of deployment of aircraft fitted with the target sight system.

1 dwg

Description

The invention relates to measuring systems and systems of aircraft (LA) - aircraft and helicopters.

In the closest analogue given in the book [1] on page 352, an overview and sighting system (OPS) of the aircraft is presented. OPS includes on-board detection means, on-board tracking means, a computer and an indication unit. When approaching the combat mission area, on-board detection means search for the target, for example, by scanning the space at the intended location of the target. After successful completion of the search, the target is indicated on the indicator, on-board support means begin to track its position relative to the aircraft, changing in time, and the pilot gets the opportunity, observing the target on the indicator, to determine its significance and decide on attacking the target. After this, the solution to the aiming problem begins. The total time spent preparing for the use of weapons consists of the aiming time and the time of preliminary search for the target by onboard detection means.

The closest analogue has a significant drawback, namely, that a preliminary search for the target may turn out to be such that its duration will be commensurate with the amount of time the aircraft was in the target area. This, accordingly, will lead to the fact that there is too little time left for aiming and using weapons and the probability of hitting the target will be insufficient. An effective solution to the problem of reducing the time of preliminary target search is external target designation with a forced turn of the line of sight of the OPS at given angles.

The objective of the invention is to expand the functionality of the OPS LA due to the automation of the aiming process and, as a result, increase the combat readiness and efficiency of use of objects equipped with such a system.

This result is achieved by the fact that the survey and aiming system, which contains a block of detection and tracking means (BOS) and a display unit (BI), is additionally equipped with a database of targets (BDC), a block of operational targets (BOC), an external target designation unit (BVTS), residual formation unit (BFN), filtration unit (BF), control parameter formation unit (BFUP). In this case, the first and second inputs of the BVCU are connected to the outputs of the BDC and BOC, the third input of the BVCU is connected to the outputs of the BIS 9, the first and second inputs of the BFN are connected to the outputs of the BFB and BVCU, the output of the BFN is connected to the input of the BF, the output of the BF is connected to the input of the BFUP, and the BFUP output is connected to the BOS input. The second output of the biofeedback is connected to the input of the BI.

The drawing shows a block diagram of an overview and sighting system of an aircraft, containing:

1 - block of detection and tracking of biofeedback;

2 - database of goals of the BDC;

3 - block operational objectives of the BOTs;

4 - block external target designation BVCU;

5 - block forming residuals BFN;

6 - filtering unit BF;

7 - block forming control parameters BFUP;

8 - block indication BI.

The drawing also shows the blocks that are not part of the OPS LA:

9 - external on-board information system LSI.

The information interconnection of the OPS aircraft blocks is carried out along the lines of information exchange (indicated by a thin solid line in the drawing).

The first output of the BOS 1 unit is connected to the first input of the BFN 5 unit, the output of the BDC 2 unit is connected to the first input of the BVCU 4 unit, the output of the BOTs 3 unit is connected to the second input of the BVCU 4 unit, the output of the BVCU 4 unit is connected to the second input of the BFN 5 unit. Output unit BFN 5 is connected to the input of unit BF 6, the output of unit BF 6 is connected to the input of unit BFUP 7, the output of unit BFUP 7 is connected to the input of unit BOS 1. The second output of unit BOS 1, which is the output of the OPS system, is connected to the input of unit BI 8. The third input of the BVCU unit is connected to the output of the BIS 9.

Block BOS 1 is a well-known, described in the literature, for example [1], pp. 358-375, means: optical radar station (OLS), thermal imaging station with automatic target tracking (FA), radar station. Block BOS 1 detects in space the target, its capture and automatic tracking. The output parameters of the block are the parameters of the relative coordinates of the target relative to the aircraft (for example, in the form of angles φ _y and φ _{z of} rotation of the line of sight relative to the normal and lateral axes of the aircraft, respectively), which are fed to the input of the BFN 1, to the input of the BI 8 unit and to the output of the OPS for other airborne systems.

Block BDC 2 is made in the form of, for example, operational or read-only memory ([2], p.30). Block CC 8 provides input of parameters (coordinates) of operational targets and is made, for example, in the form of a multichannel complex of communication equipment (see [4], p. 241) for maintaining stable two-way communication between crew members and the command and control center and between aircraft in the air , as well as for the exchange of tactical information between aircraft. The BI unit 8 is made in the form, for example, of a liquid crystal screen or cathode ray tube [5]. Blocks BVCU 4, BFN 5, BF 6, BFUP 7 are made, for example, in the form of single-processor computers ([2], p.31).

LSI 9 is a well-known information system, for example, an inertial navigation system described in the literature, for example [3]. Block BIS 9 determines the parameters of the aircraft: coordinates, speed, orientation angles.

Information communication lines are known (described, for example, in the book [2], p.21-24, 394-406) communication lines and information exchange, for example, via serial code, parallel code, multiplex, etc.

OPS LA works as follows.

When you turn on the block BOS 1 gives the values of the angles φ _y and φ _{z of} rotation of the line of sight relative to the normal and lateral axes of the aircraft, which from the output of the block BOS 1 enter the block BFN 5.

The task of finding and capturing the target is to orient the line of sight in the direction of the target, while these angles will represent the angles of sight of the target. To point the line of sight to the program target, its coordinates are read from BDC 2, for example, longitude λ _c , latitude φ _c and height H _c . These parameters enter block BVCU 4, in which the specified position of the line of sight is determined, determined by the given viewing angles φ _y * and φ _z *, using formulas of the form

Where

ΔX = X _c -X; ΔY = Y _c -Y; ΔZ = Z _c , -Z;

B is the matrix of guide cosines corresponding to the transition from the geographic trihedron OENH to the Greenwich trihedron OXYZ (see [7], p. 329);

D is the matrix of direction cosines corresponding to the transition from the Oxyz trihedron to the OENH geographic trihedron [7] (see [7], p. 329);

T is the symbol for transposing matrices.

Cartesian coordinates of the target and the aircraft — the values of X _c , Y _c , Z _c and X, Y, Z, respectively, are associated with the geographical coordinates of the target and the aircraft — the values of λ _c , φ _c , H _c and λ _c , φ, H known [3 , 6] expressions.

The parameters of the aircraft motion necessary for the implementation of the calculations using these formulas: longitude λ, latitude φ, height H, course ψ, pitch ϑ, roll γ — enter block БВЦУ 4 from LSI 9. To direct the line of sight to the operational target, its coordinates, for example, longitude λ _{p, q} latitude φ and height H _u, proceed to block BVTSU Bots 4 of unit 3.

The obtained calculated values of φ _y * and φ _z * from the output of BVCU 4 are fed to the second input of BFN 2, in which measurements ν ₁ and ν ₂ are constructed using formulas of the form

ν ₁ = φ _y -φ _y *;

ν ₂ = φ _z -φ _z *.

The residuals ν ₁ and ν ₂ from the output of the BFN 5 are fed to the input of the BF 6, in which these residuals are processed by suboptimal filtering methods, for example, by modifying the Kalman filter [3]. The basic equations of the Kalman filtering algorithm are written as

или

or

или

or

или

or

или

or

Here

- прогнозируемое значение вектора Х в k-тый момент времени;

- the predicted value of the vector X at the k-th point in time;

- оценка значения вектора в k-тый момент времени;

- assessment of the value of the vector at the k-th moment in time;

- прогнозируемое значение ковариации вектора состояния в k-тый момент времени;

- the predicted value of the covariance of the state vector at the k-th point in time;

- оценка ковариации вектора состояния в k-тый момент времени;

- assessment of the covariance of the state vector at the k-th point in time;

Q, R - covariance of input and measuring noise, respectively;

F, G - matrix of the linearized model of the system;

Ф - function of a nonlinear model of the system;

H is a linear measurement matrix;

h is the nonlinear measurement function.

From the output of BF 6, the estimation of the state vector is sent to the BFUP 7 unit, in which the control parameters U _y and U _z are generated for the tracking systems of the BFB 1. The control parameters are, for example, of signals proportional to the required values of the angular velocities of the line of sight around normal and aircraft lateral axes and the magnitude of the angular mismatch

U _y = k _y1 · ω _y + k _y2 · Δφ _y

U _z = k _z1 · ω _z + k _z2 · Δφ _z .

These signals are fed to the input of the biofeedback unit 1, for example, to the amplifiers of the moment sensors of the gyroscopic stabilizer of the sighting device, which ensure the rotation of the line of sight so that it is aimed at the target. In this case, the target is captured and its position is displayed on the screen of the BI 8 unit. This allows the pilot to carry out an operational analysis of the type and state of the target, clarify its position and angle and decide on the use of weapons for the target.

The introduction of BDCs 2, BOTS 3, BVTSU 4, BFN 5, BF 6, BFUP 7 into the OPS LA provides a simple and effective automatic guidance of the target line to the target, while eliminating the noted disadvantages of the analogue, since the search and additional reconnaissance of the target is drastically reduced - both software and operational. Unloading of the crew (especially single-seat aircraft) takes place at the crucial stage of the flight mission, which allows the crew, without compromising the quality of aiming, to focus on solving other tasks, in particular defense against the attacking enemy. This significantly increases the safety of the crew, the combat readiness of the aircraft and the effectiveness of the performance of flight missions.

The technical implementation examples show the achievement of a technical result in terms of expanding the functionality of the aircraft’s sighting and sighting system, as a result of which the crew’s safety, combat readiness and the effectiveness of the use of objects equipped with the aircraft’s fire alarm system are increased.

LITERATURE

1. Grishutin V.G. Lectures on aircraft sighting systems. - Kiev: KVVAIU, 1980.

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

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

5. Fomin A.V. Su-27. The history of the fighter. - M .: RA "Intervestnik", 2000.

6. Andreev V.D. Theory of inertial navigation. Autonomous systems. - M .: Nauka, 1966.

7. Gyroscopic systems. Part II Gyroscopic devices and systems. / Ed. D.S. Pelpora. - 2nd ed. - M.: Higher School, 1988.

Claims (1)

Survey and aiming system of the aircraft, containing a block of detection and tracking means and an indication unit, the output of the first being connected to the input of the second, characterized in that the survey and aiming system of the aircraft is additionally equipped with a database of targets, a block of operational targets, an external target designation unit, a block residuals formation, filtering unit, control parameter generating unit, the first and second inputs of the external target designation unit are connected to the output of the target database and to the output b operational targets, the third input of the external target designation unit is connected to the output of the on-board information system, the first and second inputs of the residual formation unit are connected to the outputs of the detection and tracking unit and the external target designation unit, the output of the residual formation unit is connected to the input of the filter unit, the output of the filter unit is connected to the input of the control parameter generation unit, the output of the control parameter formation unit is connected to the input of the detection and tracking unit.