RU2812306C1 - Method for self-homing of air-to-air missile with active radar self-homing head in vertical plane to helicopter with on-board defense complex - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates to the field of radio-electronic missile control systems and can be used to provide self-homing of an air-to-air missile with an active radar self-homing head in the vertical plane to a helicopter with an on-board defense complex. The method consists in generating, at the initial stage of missile self-homing, a signal for deflecting the building axis of the antenna of the active radar self-homing head, taking into account the static direction-finding characteristics of the missile fairing, supplied to the antenna drive in the absence of a control signal for the lateral acceleration of the missile in the vertical plane, ensuring a rectilinear flight path of the missile; formation at the next stage of missile self-homing of a signal to control the lateral acceleration of the missile in the vertical plane, supplied to the drive of the missile's rudders in the absence of a signal to control the deviation of the antenna's building axis, providing a curved trajectory of the missile's flight in the vertical plane outside the zone of its detection and destruction by the on-board defense complex at a constant maximum angle deviations of the building axis of the antenna; parallel to the formation at the final stage of missile self-homing of a control signal for the deviation of the antenna's building axis, returning it to the zero position relative to the missile's building axis, and a control signal for the lateral acceleration of the missile in the vertical plane, supplied to the drive of the missile's rudders, ensuring a rectilinear trajectory of its flight.

EFFECT: providing self-homing of an air-to-air missile with an active radar self-homing head in the vertical plane to a helicopter with an on-board defense system capable of detecting and hitting a missile aimed at it.

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Description

The invention relates to the field of radio-electronic missile control systems (RECS) and can be used to provide homing of an air-to-air missile with an active radar homing head (ARGS) in the vertical plane to a helicopter with an airborne defense complex (ADS).

There is a known method of homing an air-to-air missile, which consists in the fact that the flight of the missile is carried out in accordance with the control signal for the lateral acceleration of the missile in the vertical plane, generated in accordance with the expression

where Kϕ, Kω are constant coefficients, the values of which are chosen in such a way that the trajectory of the missile pointing to the helicopter in the vertical plane would be close to straight line;

ϕ - helicopter bearing in the ARGS goniometer in the vertical plane;

ω is the angular velocity of rotation of the “rocket-helicopter” line of sight in the ARGS goniometer in the vertical plane [1].

The disadvantage of this method is the almost straight trajectory of the missile's flight in the vertical plane, which does not allow it to be homing at a helicopter with an air defense system capable of detecting and hitting a missile aimed at it in the vertical plane.

There is a known method of homing an air-to-air missile, which consists in the fact that the flight of the missile is carried out in accordance with the control signal for the lateral acceleration of the missile in the vertical plane, generated in accordance with the expression

where N is a navigation parameter;

V _sb - the speed of approach of the guided missile with the helicopter;

j is the lateral acceleration of the guided missile in the vertical plane, which is supplied to the drive of the rocket’s rudders [2].

The disadvantage of this method of homing a missile is that it cannot be used to ensure homing of a missile at a helicopter with a BKO. This is due to the fact that in this case, the missile’s homing in the vertical plane is carried out almost along a straight trajectory, which makes it possible to detect and defeat it with an airborne defense complex.

The purpose of the invention is to provide homing of an air-to-air missile with an ARGS in a vertical plane to a helicopter with an air defense system capable of detecting and hitting a missile aimed at it.

To achieve the goal in the method of homing an air-to-air missile with an ARGS in a vertical plane to a helicopter with an ADC, which consists in the fact that the flight of the missile is carried out in accordance with the missile control signal Δ _p in the vertical plane, generated in accordance with expression (2) , which is supplied to the rocket rudders drive, additionally, simultaneously with the signal Δ _p for controlling the lateral acceleration of the rocket in the vertical plane, a signal Δ _α is generated for the deviation of the building axis of the ARGS antenna, taking into account the static direction finding characteristic Δϕ _about the rocket fairing, determined according to the expression

where k _about is the magnitude of the slope of the direction-finding characteristic of the rocket fairing,

arriving at the antenna drive when there is no signal Δ _p for controlling the lateral acceleration of the rocket in the vertical plane, ensuring a rectilinear flight path of the rocket, when the angle of deviation of the building axis of the antenna is close to the maximum value, or when the lateral acceleration j of the rocket in the vertical plane reaches the maximum permissible value, a signal is generated Δ _p control of the lateral acceleration of the rocket in the vertical plane, supplied to the drive of the rocket's rudders when there is no signal Δ _α control of the deviation of the building axis of the antenna, providing a curved flight path of the rocket in the vertical plane outside the zone of its detection and destruction by the on-board defense complex at a constant maximum angle of deviation of the building axis antenna, when the missile flight angle in the vertical plane relative to the helicopter reaches a value of 90°-α _{gsn max} (where α _{gsn max} is the maximum angle of deviation of the building axis of the antenna in the vertical plane), a signal Δ _α is simultaneously generated to control the deviation of the building axis of the antenna, returning it to zero position relative to the construction axis of the rocket, as well as the signal Δ _p for controlling the lateral acceleration of the rocket in the vertical plane, supplied to the drive of the rocket's rudders, ensuring a straight trajectory of its flight.

New features with significant differences are:

1. The logic of parallel generation of the signal Δ _α for controlling the deviation of the building axis of the antenna and the signal Δ _p for controlling the lateral acceleration of the missile in the vertical plane when homing at a helicopter with a missile launcher capable of detecting and hitting a missile aimed at a helicopter.

2. Formation of a signal for deflection of the building axis of the ARGS antenna, taking into account the static direction-finding characteristic Δϕ _of the rocket fairing, calculated in accordance with (3).

The use of new features in combination with the known ones will make it possible to ensure homing of an air-to-air missile in a vertical plane along a trajectory that excludes its detection and destruction by the helicopter’s on-board defense complex.

In fig. 1 shows a block diagram explaining the proposed method of missile homing; FIG. 2 (a, b, c) - stages explaining the process of missile homing.

The method of homing an air-to-air missile with an ARGS in a vertical plane at a helicopter with a BKO is implemented as follows.

From the signal generation unit for controlling the deviation of the building axis of the antenna 1 (Fig. 1), a mismatch signal Δ _α is received to the first input of the analyzer 2, which determines the discrepancy between the required and current deviation angles of the building axis of the antenna in the vertical plane, formed taking into account the static direction finding characteristic of the radome Δϕ _about , calculated in the block for calculating the static direction-finding characteristic of the rocket fairing from bearing angle 3 in accordance with (3). At the same time, the second input of the analyzer 2 from the output of the signal generation unit for controlling the lateral acceleration of the rocket in the vertical plane 4 receives the signal Δ _p for controlling the rocket in the vertical plane, generated in accordance with (2). The third input of the analyzer 2 from the output of the block for calculating the lateral acceleration of the rocket in the vertical plane 5 receives the current value of the lateral acceleration of the rocket in the vertical plane.

At the first output of analyzer 2, a signal Δ _α is generated for the deviation of the building axis of the antenna in the vertical plane, which is supplied to the antenna drive 6, and the signal Δ _p for controlling the lateral acceleration of the rocket at the second output of analyzer 2 is not generated, which ensures a rectilinear flight path of the rocket (Fig. 2, A).

When the angle of deviation of the building axis of the antenna reaches a given value, close to the maximum value, or calculated in the block for calculating the lateral acceleration of the rocket in the vertical plane 5 (Fig. 1) will be the maximum permissible, a signal Δ _p is generated at the second output of the analyzer 2 to control the lateral acceleration of the rocket in the vertical plane plane, formed in accordance with (2), which is supplied to the drive of the rocket rudders 7, and the signal Δ _α by the deviation of the building axis of the antenna at the first output of the analyzer 2 is not generated, which ensures a curved flight path of the rocket in the vertical plane outside the zone of its detection and destruction by airborne defense complex (Fig. 2, b).

When the rocket's flight angle in the vertical plane relative to the helicopter reaches the value ψ _р =90°-α _{gсn max} , at the first and second outputs of analyzer 2 (Fig. 1), a control signal D _and the deviation of the building axis of the antenna, supplied to the antenna drive 6, is simultaneously generated, returning the antenna to the zero position relative to the construction axis of the rocket, as well as the signal Δ _p for controlling the lateral acceleration of the rocket in the vertical plane, supplied to the drive of the rocket's rudders 7 (Fig. 2, c), ensuring a straight trajectory of its flight.

Thus, the use of the proposed method will make it possible to ensure homing of an air-to-air missile with an ARGS in a vertical plane to a helicopter with an air defense system capable of detecting and hitting a missile aimed at it.

INFORMATION SOURCES

1. Aviation radio control systems. Part 1. Theoretical foundations of analysis and synthesis of aviation radio control systems. Part 2.

Radio-electronic homing systems / V.I. Merkulov, V.N. Lepin. - M.: Radio and Communications, 1996, p. 182, formula (7.51) (analog).

2. Aviation radio control systems. Part 1. Theoretical foundations of analysis and synthesis of aviation radio control systems. Part 2. Radio-electronic homing systems / V.I. Merkulov, V.N. Lepin. - M.: Radio and Communications, 1996, p. 176, formula (7.32) (prototype).

Claims (4)

A method of homing an air-to-air missile with an active radar homing head in a vertical plane at a helicopter with an on-board defense complex, which consists in generating a control signal for the lateral acceleration of the missile in the vertical plane, which is supplied to the missile rudders drive, characterized in that simultaneously with the signal for controlling the lateral acceleration of the missile generates a signal for deflecting the building axis of the antenna of the active radar homing head, taking into account the static direction finding characteristic of the missile fairing, determined according to the expression where k _about is the magnitude of the slope of the direction-finding characteristic of the rocket fairing, α is the helicopter bearing in the inclinometer of the active radar homing head in the vertical plane, supplied to the antenna drive in the absence of a control signal for the lateral acceleration of the rocket in the vertical plane, ensuring straight flight of the rocket when the angle of deviation of the building axis of the antenna is reached, close to the maximum value, or the transverse one is reached acceleration of the rocket in the vertical plane of the maximum permissible value, a signal is generated to control the lateral acceleration of the rocket in the vertical plane, supplied to the drive of the rocket's rudders in the absence of a control signal for the deviation of the antenna's building axis, providing a curved trajectory of the rocket's flight in the vertical plane outside the zone of its detection and destruction by the on-board defense complex at at a constant maximum angle of deflection of the building axis of the antenna, when the angle of flight of the rocket in the vertical plane relative to the helicopter reaches the value 90°-α _{GSN max} , where α _{GSN max} is the maximum angle of deflection of the building axis of the antenna in the vertical plane, a control signal for the deviation of the building axis of the antenna is simultaneously generated, returning it to the zero position relative to the construction axis of the rocket, as well as a control signal for the lateral acceleration of the rocket in the vertical plane, supplied to the drive of the rocket's rudders, ensuring a straight trajectory of its flight.

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