RU2269452C2 - Method of control of flying vehicle after launching missile - Google Patents

Abstract

FIELD: military aviation; conducting aerial combat.

SUBSTANCE: after launching the missile, aircraft is turned-away to orthogonal course which is corrected continuously for maintaining its orthogonality. Antenna of aircraft onboard radar station is turned in synchronism with aircraft turning-away, thus ensuring tracking the enemy aircraft and guidance of missile. Simultaneously with aircraft turning-away to orthogonal course, its flying altitude is reduced. Probable obstacles during orthogonal maneuver are revealed by means of onboard laser radar for enveloping them.

EFFECT: enhanced safety of aircraft.

2 cl, 8 dwg

Description

The invention relates to the field of military aviation.

With existing methods of controlling the aircraft after launching a guided missile, the guidance of missiles launched by the aircraft often breaks down due to the turnaround of the missile guidance means from the direction to the target (A.I. Kanaschenkov, V.I. Merkulov, O.F. Samarin. The appearance of promising airborne radar systems. M., 2002. S.18-20).

Thus, the disadvantages of existing methods include the following:

- reduction in the probability of tracking the target or a complete disruption of its tracking;

- the impossibility of attacking the target at the time of the maneuver;

- disruption of rocket tracking due to the high speed of maneuvering and an increase in the dynamic errors of its tracking.

The technical result to which the invention is directed is to increase the aircraft’s ability to conduct actions using active orthogonal maneuvering to eliminate the need to move the aircraft after the rocket is launched in order to escort it until the target is captured, which increases the risk of being hit by an enemy response.

In order to achieve the indicated technical result, the aircraft, after launching a rocket on an enemy aircraft, is turned to an orthogonal course relative to the trajectory of the enemy aircraft, while the orthogonal maneuver can remain active, i.e. the plane continuously directs the missile launched by him at the target. This is ensured by the fact that the axis of the radiation pattern of the aircraft’s on-board radar station (BRL) of the aircraft maintains its previous position (the BRL simultaneously with the plane rotates also 90 ° - it monitors the target in automatic mode), and the radar continues to aim the missile fired at the target.

The aircraft constantly changes course so that its path is orthogonal to the line connecting the aircraft and the target at any given time.

The plane carries out in the vertical plane the steepest possible dive for it, dropping to a height when it will be difficult to distinguish visually against the background of the earth (N <3 km).

The orthogonal maneuver of the aircraft ends after the rocket hits the target.

To prevent collisions with obstacles during descent, the aircraft is equipped with a laser radar station (LLS), which provides the opportunity to identify obstacles in advance and go around them.

When using a phased antenna array on an airplane, it is made movable in the azimuthal plane by an angle φ _а = ± (90 ° -α), where α is the maximum antenna scanning angle.

When using a slot antenna, it can be deflected in the azimuthal plane by an angle of ± 90 °, in elevation by ~ 10-15 ° with the location of the axis of the radiation pattern in the horizontal plane of the aircraft, by selecting the distances between the slots in the row and between the rows of antenna slots. An angle of 10-15 ° is provided by the installation of the antenna on the oblique plane of the antenna installation site of its installation.

With an active orthogonal maneuver, the aircraft is in the range of “blind speeds” for the opponent’s radar station and deprives him of the ability to accompany himself, since modern radar systems operate at the Doppler frequency. The Doppler frequency is formed from the moment the radar’s electromagnetic waves are touched until it leaves the detected aircraft, and the wavelength changes to increase if the target moves away from the radar that is irradiating it, and to decrease if the target approaches the radar. Doppler frequency is equal to:

where V _c - target speed;

λ is the wavelength of the station irradiating it;

η is the Doppler frequency;

α _C - the angle between the direction of the target and the speed of the target.

When the aircraft flips to the course orthogonal to the target, α _c = 90 °, Cos 90 ° = 0, the Doppler frequency η = 0, and the enemy’s radar “does not see” the aircraft that has performed the maneuver, cannot aim its missile flying at the initial course and flying past turned away on the orthogonal course of the aircraft.

If it is impossible to accurately maintain the orthogonal course by an airplane, they reduce the visibility of its radar by mismatching the axis of the radiation pattern and the longitudinal axis of the antenna system, for which the mounting surface of the antenna system is inclined. Moreover, the value of the angle of inclination Θ is within the range A≤ А≤30 °.

A = 0.61 λ / a for round antennas;

A = λ / a for rectangular antennas,

where λ is the wavelength of the irradiating station;

and - overall size of the antenna.

For a slot antenna system, the deviation of the axis of the radiation pattern from the longitudinal axis of the antenna system is ensured by phase shifts x ₁ and x ₂ between the currents of adjacent rows of slots and slots in a row, determined in accordance with the expressions (Aizenberg G.Z. Antennas VHF. M .: Communication, 1977. P.119):

x ₁ = (2πd ₁ / λ ₁ ) · SinΘCosφ;

x ₂ = (2πd ₂ / λ ₁ ) · SinΘCosφ,

where λ ₁ is the working wavelength of the antenna,

d ₁ - the distance between the rows of slits,

d ₂ - the distance between the slots in a row,

Θ is the deviation of the antenna surface in a vertical plane,

φ is the deviation of the antenna surface in the horizontal plane.

The lateral surface of the antenna system is performed parallel to the axis of the radiation pattern, and not perpendicular to the surface of the antenna, which makes it possible to reduce the size and mass of the fairing under which the antenna system is installed.

The waveguides are positioned obliquely to the surface of the antenna at an angle Θ, and not perpendicularly, which ensures the conservation of the field of view of the phased antenna array (PAR).

The invention is illustrated by drawings.

Figure 1 presents a diagram of a method of active orthogonal maneuver of an aircraft when launching a rocket at a target that maneuvers in a known manner.

Figure 2 - diagram of a rotating simultaneously with the aircraft headlamp radar.

Figure 3 - diagram of the active orthogonal maneuver of the aircraft.

Figure 4 - diagram of the on-board system of orthogonal maneuvering.

Figure 5 - diagram of the radar with reduced visibility of the antenna.

6 is a diagram of a slot antenna.

7 is a diagram of the placement of the antenna on an airplane.

On Fig - the law of variation of the efficiency of the scattering surface of the antenna depending on the angle of its installation.

The method of controlling the aircraft after launching a guided missile is as follows.

After detecting and capturing the target, the aircraft 1 (Fig. 1) launches the rocket 2 on the target aircraft 3, which launched the rocket, makes a tactical turn-around to the orthogonal course of the trajectory of the target aircraft with a decrease in flight height.

Aircraft 1 becomes "invisible" for the radar of the target aircraft 3, rocket 4 of which becomes uncontrollable and cannot hit aircraft 1.

Antenna 5 of aircraft 1, automatically turning, monitors target aircraft 3, rocket 2 of aircraft 1 continues to aim at target aircraft 3 and hits it. After this, aircraft 1 completes the active orthogonal maneuver.

In the case of inaccurate observance of the orthogonal course by plane 1, the target plane 3 will not capture plane 1 after it is turned away, since the antenna 5 of plane 1 is directed at plane 3 so that it is not "visible" to its radar.

In this case, the on-board system of orthogonal maneuvering works as follows.

When searching for a target, the surface 6 of the antenna 5 with slots 7 (see FIGS. 5, 6) rotates together with the inclined mounting surface 8 of the housing 9 using hydraulic cylinders 10. Due to the inclined position of the mounting surface 8, the location of the axis 11 of the radiation pattern is directed at the target when it detection, and the longitudinal axis 12 of the antenna is deflected at an angle Θ and the surface 6 of the antenna 5 is not perpendicular to the axis of the radiation pattern. Radar radiations from target aircraft 3, falling onto the surface 6 of antenna 5, are reflected in space without falling onto radar from target aircraft 3.

The search for the target is carried out by scanning the beam of the antenna system using phase shifters. The identified target 3 is held by the antenna system of the aircraft 1 for pre-launch operations, launch and guidance of the rocket. When the missile is launched toward the target, the axis of the antenna pattern is located on the target, the surface 6 of the antenna 5 is deflected by an angle Θ. The waveguides 14 are inclined to the axis of the antenna 5 at an angle Θ.

With slot antenna systems and the PAR, the effective scattering surface (EPR) is reduced (Fig. 8).

Aircraft 1 enters the area of the intended target using the satellite navigation system (SNA) 15 (FIG. 4) and inertial navigation system (ANS) 16. The airborne radar station (BRL) 17 of aircraft 1 detects target 3.

On the multifunctional digital indicator (MFCI) 18, target 3 is displayed, the distance to the target, its heading angle, calculated using the on-board, central computer (BCM) 19; at MFCI 18, through the BCVM 19, the coordinates of the rocket 4 of the enemy 3, determined by the heat direction finder (TP) 20, are also received.

The pilot, using the control panel 21 of the control system complex (KSU) 22 through the KSU 22, directs the plane 1 to the target aircraft 3 and, using the remote control 23 of the armament control system (SUV) 24, launches the missile 2 through the SUV 24. flight altitude of airplane 1 from the radio altimeter (RVM) 25 and data on the presence of obstacles in front of airplane 1 from the laser radar station (LLS) 26. After launching rocket 2, airplane 1, according to the program laid down in BTsVM 19, makes orthogonal course of the target airplane 3 lapel and decreases to given height. Aircraft 1 in automatic mode accompanies, using antenna 5, the target aircraft 3 until it is hit by rocket 2.

When using slotted antenna 5 on an airplane 1 when the airplane 1 is flipped to an orthogonal course, antenna 5, in accordance with the program laid down in the digital computer 19, rotates on target simultaneously with the airplane 1 flap.

When using a phased antenna array on airplane 1, its rotation does not have to be synchronous with the airplane 1 flap due to the possibility of scanning the headlight beam, but by the time the airplane 1 flap ends, the antenna 5 rotation must also be completed, which is provided by the corresponding program in the digital computer 19.

Claims (2)

1. The method of controlling the aircraft after launching a guided missile, according to which the aircraft, after launching the missile, is turned off course, orthogonal to the line connecting this aircraft to the enemy’s plane, continuously adjust the course of the aircraft, while maintaining the indicated orthogonality when changing the position of the enemy’s aircraft, rotate the antenna simultaneously airborne radar station, providing escort of the enemy aircraft and guidance of the fired missile at it, and possible during the orthogonal maneuver and obstacles are identified using an aircraft-mounted laser location station and go around them. 2. The method according to claim 1, in which at the same time as the lapel of the plane to the orthogonal course produce a decrease in the height of its flight.

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