RU2379613C2 - Aircraft sight - Google Patents

Abstract

FIELD: arms and ammunition.

SUBSTANCE: invention relates to sighting systems and can be used interceptor aircraft in close-in dogfight conditions. Proposed system comprises onboard radar incorporating mirror aerial with control unit. The latter comprises mirror title, tilt and azimuth turn angle and angular speed transducers, signal processor with its input connected with receiver output, as well as indicator and unit of communication with missiles. Proposed sight incorporates coverage area shift switch and aiming control processor. First input of the latter is connected with attach mode switch, its second input being connected with coverage area shift switch, its third switch being connected with aerial mirror turn angle and angular speed transducers, its fourth input being connected with data output of the unit of communication with missiles, and fifth input being connected with aircraft altitude and roll pickups. Aiming control processor first output is connected to indicator input, its second output is connected to input of the unit of communication with missiles, third output is connected to aerial control unit input and fourth out is connected to synchroniser control input. Note here that processors are interconnected via communication lines.

EFFECT: reduced aiming interval.

2 dwg

Description

The invention relates to sighting systems and can be used in sighting devices of interceptor aircraft that attack air targets in close air combat.

Aircraft sight is known, comprising an airborne radar station (RLS), comprising a mirror antenna with mirror angle sensors along the azimuth, tilt and roll axes and an antenna control unit, the antenna output through the first input of the antenna switch is connected to the input of the receiver, the second input of the antenna switch is the transmitting device is connected to the output of the synchronizer, as well as a digital computer (digital computer), the input of which is connected to the output of the receiving device. The sight also contains a missile communication unit, the output of which is connected to missile homing heads, and an attack mode switch (Patent of the Russian Federation No. 2265786 in class F41G 3/22 with priority June 24, 2004).

A disadvantage of the known device when using a pulse-Doppler radar in it is a large aiming time of several seconds, due to the lack of operational pointing of the antenna mirror to the target, as well as the fact that the digital computer operates as a processor for processing the reflected signal, and the formation of sighting information and control of the radar with a delay. This aiming time is unacceptable when operating the sight in the conditions of close air combat.

The objective of the invention is to reduce the aiming time.

The solution to this problem is achieved by the fact that the sighting field shift switch and the aiming control processor are introduced into the aircraft sight, the first input of which is connected to the attack mode switch, the second input is with the field of view shift switch, and the third input is with the angle and angle sensors of the antenna mirror , the fourth input is with the information output of the missile communication unit, the fifth input is with the aircraft’s altitude and roll sensors, and the outputs of the aiming control processor are respectively connected: the first is to the input at the indicator, the second to the input of the communication unit with missiles, the third to the input of the antenna control unit, and the fourth to the control input of the synchronizer, while both processors are interconnected via a communication line.

Figure 1 presents a diagram of an aircraft sight, figure 2 is a view of the offset viewing area.

The scope of the sight (figure 1) includes: pulse-Doppler radar 1, including antenna 2 with sensors 3 of the rotation angles and angular velocity of the mirror of the antenna along the axes of azimuth, tilt and roll, antenna switch 4, receiver and transmitter 5 and 6, synchronizer 7, as well as a signal processor 8 and an aiming control processor 9, an indicator 10, an attack mode switch 11 to the front or rear hemisphere, a communication unit with missiles 12, missiles 13, an antenna control unit 14, a viewing area shift switch 15 and height sensors and roll of the airplane 16.

Antenna 2 radar 1 through the first input of the antenna switch 4, the receiver 5 and the signal processor 8 is connected to the processor control aiming 9 through the communication line. The input of the indicator 10 is connected to the first output of the aiming control processor 9, the second output of which is connected to the input of the communication unit with missiles 12, the third to the input of the antenna control unit 14, and the fourth to the control input of the synchronizer 7. The inputs of the processor 9 are respectively connected: the first input - with the switch of attack modes 11, the second input - with the switch of the displacement of the field of view 15, the third input - with the sensors of the angle of rotation and angular velocity of the mirror antenna 3, the fourth input - with the information output of the communication unit with missiles 12, and the fifth stroke - to the outputs of the height sensors and roll of the aircraft 16. The outputs of the communication unit 12 are connected with the missile missile 13 to the inputs.

The device operates as follows. In the process of conducting close air combat, at ranges of 10 to 15 kilometers, the pilot visually detects the target through the cockpit lantern, determines its position relative to the aircraft — to the right or left, its flight direction (approach or removal), sets the attack mode switch 11 to the appropriate position and switch 15 to the "offset left" or "shift right" position. The signal from the output of the attack mode switch 11 is supplied to the first input of the processor 9, by which it selects the radar frequency 1 (high or medium) and gives signals to the control input of the synchronizer 7, by which it changes the pulse repetition period in the packet and their duty cycle in the transmitting device 6, providing the conduct of close air combat.

The signal from the output of the switch 15 is fed to the second input of the processor 9, through which it generates control signals for the width of the field of view, setting the mode "small zone", and its position in the space "left" or "right", which are received at the inputs of the antenna control unit 14 In accordance with these signals, the antenna 2, shifting relative to the zero position (figure 2), begins to produce a line-by-line survey of the front hemisphere with a small viewing area, ensuring the prompt pointing of the antenna's mirror to the target.

During the review, the signal from the output of the transmitting device 6 through the antenna switch 4 is fed to the input of the antenna 2 and is radiated into space. Closed at the time of the pulse sending, the receiving device 5 is opened, and the processor 8 begins to process the received signal using the fast Fourier transform algorithm.

According to the work of V.V. Vasin and others. Aviation radar. Edition of VVIA them. N.E. Zhukovsky, 1964, p. 529, to calculate the data necessary for firing an aircraft interception system, information on the attack mode, type of weapon, range to the target, rotation angles and angle must be supplied to the input of the computing device (aiming control processor) the angular speeds of the antenna mirror, as well as the flight altitude and roll angle of the aircraft.

Until the target is detected, the second, fourth and fifth inputs of the processor 9 already have information about the nature of the attack (in the front or rear hemisphere) from the output of the attack mode switch 15, information about the presence and type of missiles 14 from the information output of the communication unit with missiles 12.

Upon detection of the target, the signal processor 8 through the communication line gives to the input of the targeting control processor 9 information about the distance to the target. At the time of the receipt of the signal about the presence of the target, the processor 9 captures the values of the rotation angles and angular velocities of the mirror of the antenna 2 from the outputs of the sensors of rotation angles and angular velocities 3, as well as information about the flight altitude and roll angles from the output of the aircraft height and roll sensors 16. Having a complete set of source data, the processor 9 generates targeted information, which is fed to the input of the communication unit with the missiles 12 and then to the missiles 13, preparing them for launch with a minimum delay relative to the formation time of the target mark. Introducing the aiming control processor and the switch into the target circuit in combination with the above-described connections allows for the operative aiming of the antenna mirror on the target, as well as the generation of sighting information, and for controlling the radar in parallel with the signal processing, thereby reducing the aiming time, which is especially important when conducting close air combat.

The newly introduced aiming processor and switch are among the typical elements of electronic technology, which makes it possible to implement the proposed sight circuit in full.

Claims (1)

Aircraft sight containing an on-board radar station, including a mirror antenna with an antenna control unit, equipped with sensors of rotation angles and angular velocities of the mirror along the azimuth, tilt and roll axes, the output of which through the first input of the antenna switch is connected to the input of the receiver, the second input of the antenna switch is the transmitting device is connected to the output of the synchronizer, a signal processor, the input of which is connected to the output of the receiving device, as well as an indicator and a communication unit with ket, the output of which is connected to missiles, an attack mode switch and aircraft altitude and roll sensors, characterized in that it is equipped with a field of view offset switch and an aiming control processor, the first input of which is connected to the attack mode switch, the second input is with a zone shift switch overview, the third input - with sensors of rotation angles and angular speeds of the antenna mirror, the fourth input - with the information output of the communication unit with missiles, the fifth input - with the sensors of height and roll of the aircraft, the process outputs ora aiming control are respectively connected: the first - to the input of the indicator, the second - to the input connection of missile third unit - to the input of the antenna control unit, and the fourth - to the control input of the synchronizer, the processors are interconnected link.

Images