RU2158407C1 - Aircraft optoelectronic sighting system - Google Patents

Abstract

FIELD: aircraft sighting systems. SUBSTANCE: the aircraft optoelectronic sighting system has series-connected helmet target designation unit and optical location station with a laser range finder, target lock-on clearance button controlled by the pilot, homing head of aircraft guided missile. Besides, it has a driver of target designation to the aircraft guided missile, driver of sign of stable target lock-on by the homing head of the aircraft guided missile, control unit of operation regime of the homing head of the aircraft guided missile with a capability of reaming. The driver of sign of stable target lock-on by the homing head of the aircraft guided missile is made with a capability of functioning at short-time lock-on rejections by the homing head of the aircraft guided missile. EFFECT: enhanced antijamming capability of the sighting system. 3 cl, 1 dwg

Description

 The invention relates to weapons for a wide class of military aircraft, and in particular for multi-functional fighters.

 One of the tasks accomplished by weapons of military aircraft is the task of hitting visually visible and, in particular, highly maneuverable air targets. For multi-functional fighters, this is the task of close maneuverable air combat. For aircraft of other types, this is a defense task.

 One of the ways to solve these problems is to use aviation guided missiles with homing heads, as a means of destruction, helmet-mounted target indicators for sighting targets and issuing target designation, high-precision optical location systems with a laser range finder for information support of launch with a high probability of destruction.

These systems are described in:
- the book "Combat aircraft: Aircraft armament" (DI Gladkov and others) M .: Military Publishing House, 1987, p. 218,
- the book "Su-27", POLYGON - aviation series Red Flag for modellers, Moscow, 1993

 The disadvantages of existing systems of this type are their low noise immunity, application restrictions associated with the capabilities of an optical radar station with a laser rangefinder, as well as the significant time required for retargeting in close air combat.

 SUMMARY OF THE INVENTION

The basis of the invention is the solution of the following tasks:
- increasing the noise immunity of the system by forming and using in the system a sign of stable capture of the homing of an aircraft guided missile, obtained on the basis of logical processing of the signals of the homing head,
- operational retargeting of an aircraft guided missile using a helmet-mounted target designator due to the specific logic of homing control.

 The goal set in the first and second tasks is achieved by the fact that in the optoelectronic sighting system of the aircraft, which contains a serially connected aiming element, a target designator of an aircraft guided missile and a homing head of an aircraft guided missile, an optical locating station with a laser range finder is introduced, the first input of which is connected to the output of the helmet-mounted unit target designation and aiming, used as an aiming element, the first output is with the second input of the target designator I am an aircraft guided missile, the second exit is with the third input of the target designator of the aircraft guided missile and the first input of the helmet-mounted target designation and aiming unit, a target capture resolution button controlled by a pilot, connected to the second input of the optical locating station with a laser range finder, a condition indicator of stable target capture by a homing head aircraft guided missile, the input of which is connected to the output of the homing head of the aviation guided missile, and the output to the second input a helmet for targeting and aiming, a control unit for operating modes of the homing head of an aircraft guided missile with the possibility of re-targeting, the inputs of which are connected to a resolution button for capturing a target controlled by a pilot, a driver of a sign of stable capture of a target by a homing head of an aircraft guided missile, and the second output of an optical locating station with a laser range finder and the first and second outputs are connected to the second and third inputs of the homing aircraft guided missiles with tvetstvenno, wherein the generator characteristic stable capture target seeker aircraft guided missile configured to operate during short discharges capture homing guided missile aircraft.

 The shaper of the sign of stable target capture by the homing head of an aircraft guided missile is made in the form of a first memory block, the input and output of which are the input and output of the block, respectively, of the first memory block, connected in series with the first logical element NOT, a counter and the first comparator, and the input of the block connected to the input the first logical element is NOT, the second input of the first comparator is connected to the first memory block, and the output is connected to the control input of the first memory block.

 The control unit for the operation modes of the homing head of an aircraft guided missile with the possibility of retargeting is made in the form of series-connected logic element OR and a second memory unit, series-connected second logic element NOT, the first logical element AND and the delay element, the output of which is connected to the control input of the second memory unit, moreover, the inputs of the logical element OR - the first and third inputs of the block, the second input of the first logical element And - the second input of the block, output the second block of memorization is the output of the block.

 Information confirming the possibility of carrying out the invention.

 The possibility of carrying out the invention is illustrated by the example of an optoelectronic sighting system of a multifunctional fighter. This example should not be construed either as limiting the scope of the invention, or as the preferred form of its implementation for all cases.

 The block diagram of the device shown in the drawing.

 The device comprises a helmet-mounted target designation and indication unit 1, an optical radar station 2 with a laser range finder, a pilot-controlled target capture permission button 3, an aircraft guided missile 4 homing target, an aircraft guided missile target designator 5, an indicator of a stable target capture by an aircraft-guided missile 6 homing head , unit 7 control modes of operation of the homing head of an aircraft guided missile with the possibility of retargeting.

 Block 6 contains a first memory block 8, a memory block 9, a first logical element NOT 10, a counter 11 and a comparator 12.

 Block 7 contains a logical element OR 13, a second storage unit 14, a second logical element NOT 15, a logical element AND 16 and a delay element 17.

 Block 1 is connected to blocks 2 and 5. The second and third inputs of block 5 are connected to the first and second outputs of block 2, the output of block 5 is connected to the first input of block 4, the output of which is connected to the inputs of blocks 8, 10. The output of block 10 is connected to the block 11, the output of which is connected to block 12, the second input of which is connected to block 9, and the output to the control input of block 8. Block 3 is connected to the second input of block 2 and the first input of block 13, the second input of which is connected to the second output of block 2, and the output - with blocks 14, 15. The output of block 15 is connected to the input of block 16, the second input of which about 8 connected to the unit, and output - with the unit 17 and second input unit 4. The output unit 17 is connected to the control input unit 14, whose output is connected to the third input unit 4. The unit 1 inputs connected to the second output of the unit 2 and 8.

 The following describes the operation of the device.

 Block 1 helmet-mounted target designation and indication includes a device for determining the angular position of the pilot’s head and a sighting device with a fixed crosshair, where target acquisition by the optical station 2 and homing 4 are also indicated.

 The pilot combines the fixed crosshair of the helmet-mounted visor with an air target, and then presses the button 3. Target designation from block 1 enters the optical location station 2 and homing head 4 through unit 5. The optical resolution station 2 receives the capture resolution command from block 3, after which it goes to detection and capture of targets in the capture field.

В блоке 6 формируется сигнал устойчивого захвата цели головкой самонаведения 4. Сигнал захвата с блока 4 поступает на блок 8, где запоминается. При пропадании сигнала с блока 4 запускается счетчик 11 (U10=1). При превышении выходным сигналом счетчика 11 порогового значения, запомненного в блоке 9, срабатывает компаратор 12 (U12=1), что обнуляет выход блока 8. Т.е. при кратковременных пропаданиях сигнала с блока 4 сигнал устойчивого захвата с блока 8 не снимается. Величина допустимого времени пропадания сигнала с блока 4 задается величиной порога U9.In block 5, a target designation signal is generated for head 4. Block 5 is a key. In the normally closed state, a target designation signal from block 1 passes to its output, and when a target is captured by an optical pickup station 2, a capture signal from the second output of block 2 is received at the third input of block 5 and a target designation signal from the first output of block 2 passes to the output of block 5 block 5 is formed in accordance with the expression:

In block 6, a signal is generated for stable capture of the target by the homing head 4. The capture signal from block 4 is sent to block 8, where it is stored. If the signal disappears from block 4, counter 11 starts (U10 = 1). If the output signal of the counter 11 exceeds the threshold value stored in block 9, the comparator 12 (U12 = 1) is activated, which resets the output of block 8. That is, in case of short-term signal failures from block 4, the signal of stable capture from block 8 is not removed. The value of the allowable signal loss time from block 4 is set by the threshold value U9.

 In block 7, control signals for homing head 4 are generated. When a button 3 is pressed or a target is captured by an optical pick-up station 2, the signal from the output of block 14 (U13 = U14 = 1) is fed to the third input of the homing head 4, which switches to the target development mode coming from the block 5. When the button 3 is released and there is no capture of station 2 (U13 = 0, U14 = 1) and there is a capture of the target by the homing head (U8 = 1, U16 = 1), the second input of block 4 receives a signal to switch the homing head to auto tracking mode, and target designation signal with block and 14 is removed (U17 = 1, U14 = 0). To redirect the missile, the pilot imposes the crosshair of the helmet-mounted visor on another target and presses button 3 again, after which (U13 = U14 = 1) homing head 4 goes into target development mode for the new target, the auto tracking mode is removed (U15 = U16 = 0).

 Thus, effective control of the homing head of an aircraft guided missile for a visually visible target is ensured both under the condition that the target is tracked by an optical radar station with a laser rangefinder, and outside its area of operation (or under interference), while it is possible to quickly redirect the missile to another target.

Claims (3)

 1. The optoelectronic aiming system of an aircraft, comprising a series-connected aiming element, a target designator of an aircraft guided missile and a homing head of an aircraft guided missile, characterized in that it is equipped with an optical locating station with a laser range finder, the first input of which is connected to the output of the helmet-mounted target designation and aiming unit used as an aiming element, the first output is with the second input of the target designator of the aircraft guided missile, watts swarm exit - with the third input of the target designator of the aircraft guided missile and the first input of the helmet-mounted target designation and aiming unit, a pilot-controlled target capture enable button connected to the second input of the optical locating station with a laser range finder, a sign of stable target capture by an aircraft-guided missile homing head, input which is connected to the output of the homing of an aircraft guided missile, and the output to the second input of the helmet-mounted target designation unit refueling, control unit operating modes of the homing head of an aircraft guided missile with the possibility of retargeting, the inputs of which are connected to a button to enable the capture of a target controlled by a pilot, a shaper of a sign of stable capture of a target by a homing head of an aircraft guided missile and the second output of an optical location station with a laser rangefinder, and the first and second the outputs are connected to the second and third inputs of the homing of an aircraft guided missile, respectively, and s feature sustained capture target seeker aircraft guided missile configured to operate during short discharges capture homing guided missile aircraft.  2. The system according to claim 1, characterized in that the shaper of the sign of stable capture of the target by the homing head of an aircraft guided missile is made in the form of a first storage unit, the input and output of which are the input and output of the unit, respectively, of a memory unit connected in series to the first logical element NOT, a counter and a comparator, the input of the unit being connected to the input of the first logical element NOT, the second input of the comparator connected to the memory unit, and the output to the control input of the first memory unit.  3. The system according to claim 1 or 2, characterized in that the control unit operating modes of the homing head of an aircraft guided missile with the possibility of retargeting is made in the form of series-connected logical element OR and the second storage unit, series-connected second logical element NOT, logical element AND and delay element, the output of which is connected to the control input of the second storage unit, and the output of the OR logic element is connected to the input of the second logical element NOT, the inputs Skog OR element - the first and third inputs of the block, the second input of the AND gate - a second input of the unit and its output - the first output unit, output the second memory unit - a second output block.