JPH0784993B2 - Fire control system for aircraft - Google Patents

Description

Description: TECHNICAL FIELD The present invention relates to an improvement in a fire control system of an aircraft, and more specifically, to an improvement in attack capability in air combat and an ability to avoid an attack from an opponent aircraft. It is about improvement.

[Conventional technology]

FIG. 4 shows an example of the configuration of a conventional system of this type. (1) is a radar that detects reflected waves from the target of the emitted radio waves to search and track the target, and (2) is the radar of the target. FLIR sensor / tracker that obtains and tracks an infrared image from infrared rays emitted, (3) is an inertial navigation device that detects or calculates attitude data of the aircraft and navigation data necessary for autonomous navigation, and (4) is air An air data computer (5), which receives sensor signals such as velocity, pressure, angle of depression, sideslip angle, etc., and calculates the air quality required for fire control calculations, etc. The central computer that controls the entire system such as the control of data flowing on the Tx Data Bus and the fire control calculation, (6) receives information from other avionics (10).
Digital Display Indicator (hereinafter DDI
Display processor that performs display processing such as symbol generation and coordinate calculation for display on a display device such as a display) or a head up display (hereinafter referred to as HUD),
(8) is a weapon controller that performs weapon control such as (15) machine gun and (16) missile weapon selection instruction, and (13) weapon trigger control from the stick, (10) It displays various data such as radar information, navigation data, and weapons control data, and has a selection button to control the system. The DDI stored in the instrument panel inside the cockpit, (11) is above the instrument panel. HUD, (13), which is placed in the field of view of the pilot and displays flight data, fire control data, etc. on its semi-transparent plate,
A stick for giving instructions to fire weapons, etc. (14)
Is a slot for controlling engine power, selecting weapons, and operating radar.

The conventional aircraft-based fire control system is configured as described above, and when the weapons to be used and the operation mode of the radar are selected by the switch of the slot (14) during the air combat, the radar (1) and the inertial navigation system ( 3), Firearms control calculation is performed by the central computer (5) based on the data of the aircraft and the target sent from the air data computer (4) and the data of the weapon used, and the result is displayed by the display processor (6). ) Via DDI
Displayed in (10) and HUD (11). Figure 5 shows the HUD display while attacking the target in close air combat, with a short-range missile (hereinafter referred to as SRM) selected as the weapon. When the radar (1) captures and tracks the target (25) on the HUD screen (20), the target symbol (28) is displayed, and as a result of fire control calculation, the steering dot (21) and SRM indicating the steering direction of the aircraft are displayed. An ASE circle (23) showing the launch range of appears around the aircraft symbol (22). Then, if the steering dot (21) enters the ASE circle (23) and the range is within the maximum range of SRM, a shout queue (24) indicating that the missile can be launched appears, and the pilot follows the instruction to set the target. The attack is possible.

[Problems to be solved by the invention]

However, in the conventional fire control system as described above,
If the target (25) is highly mobile, or if it is immediately out of the field of view of the HUD screen (20) due to flight conditions, it is quite easy even if the radar is tracking the target. I can't get chances to fire missiles. On the other hand, if you are being pursued by the opponent's aircraft, there is no choice but to take a method of avoiding the opponent's attack and occupying a favorable position while watching the movement of the opponent's aircraft with the rear view mirror (26). I got it.

The present invention has been made to solve such a problem, and enables an attack even when the target is largely out of the field of view of the HUD screen during an attack during air combat, and is pursued by an opponent aircraft from behind. In this case, give an optimal avoidance instruction,
Moreover, it is an object of the present invention to obtain a fire control system mounted on an aircraft that enables counter attack while avoiding it.

[Means for solving problems]

The fire control system according to the present invention is an optical sensor / tracker capable of turning in all directions under the fuselage of its own machine, capable of optically detecting and tracking a target in the turning portion and performing distance measurement to the target. It has a rotary launcher that is equipped with a single or multiple infrared detection or active radar homing missiles and is incorporated into a conventional fire control system.

[Action]

Since this invention has a turnable missile launcher, if the seeker of the missile captures the target, it will be possible to launch the missile in all directions without changing the direction of the aircraft, and without being restricted by the view of the HUD. It is possible to control fire based on target tracking data by radar or optical sensor / tracker. Furthermore, even when the opponent aircraft is chased from behind, it is possible to attack the opponent aircraft behind while performing optimal avoidance movements based on the optical sensor and tracker data.

〔Example〕

FIG. 1 is a system configuration diagram showing an embodiment of the present invention. (1), (3), (6), (9) to (11), (13).
~ (16) is exactly the same as the conventional fire control system. However, with respect to the central computer (5) and the display processor (6), a part of software or hardware may be modified or added by adding a new function. (7) is a rotary luncher (1
Attached to 8), it is an optical sensor tracker consisting of an optical image sensor and a laser rangefinder, and has the functions of detecting and tracking a target and measuring the distance to the target. (12) is an optical sensor data processor that processes the angle information, distance information and image data of the target tracked by the optical sensor tracker (7). (17) is a rotary launcher controller for controlling the drive of the rotary launcher (18) and the optical sensor tracker (7). Further, the rotary launcher (18) has the ability to suspend one or more infrared detection or active radar homing missiles (19), and is capable of turning in all directions. Show.

In FIG. 2, (19) is the above missile, (30) is the suspension part of the rotary tontier on the mother machine, (31) is the rotary part of the rotary launcher, and (32) is the optical sensor / tracker storage part. It is attached to the part (31). (33) is a launcher for the missile (19).

In the fire control system configured as described above,
The target (25) is the HUD screen (20) as shown in Fig. 3.
Even if the radar (1) or optical sensor / tracker (7) is tracking the target (25) even if it is out of the field of view, fire control calculation is continued and the ASE circle (23) and steering dot (21) Is displayed. Even if the steering dot (21) is not in the ASE circle (23), the rotary launcher (18) is turned in a predetermined direction by the fire control calculation and the target from the optical sensor tracker (7). Image (29) is the HUD screen (2
0). And the target (25) is the missile (1
When entering within the range of 9), a shout que (24) appears, indicating that the missile can be launched, and when the trigger of the stick (13) is pressed, the missile is launched.

On the other hand, when the opponent's aircraft is being pursued, as shown in FIG. 4, the symbol (28) and the image (29) showing the position of the opponent aircraft captured by the optical sensor and tracker (7) are displayed on the HUD screen (2
In addition to being displayed in 0), the central computer (5) calculates the optimal avoidance route from the change in the relative position between the own aircraft and the other aircraft, and the steering wheel indicating the steering direction of the own aircraft momentarily.
Since the dot (21) is shown, the pilot can avoid the maneuver by maneuvering the aircraft so that the steering dot (21) is at the center of the aircraft symbol (22), and the optical sensor tracker ( Based on the data of the target captured by 7), fire control calculation is performed, and the target (25) is missile (1
When entering within the range of 9), a shout kyu (27) appears just below the aircraft symbol (22), indicating that the missile (19) can be launched.

〔The invention's effect〕

As described above, the present invention provides a conventional fire control system, a rotary missile launcher system capable of rotating in all directions, and an optical sensor having a detecting and tracking function mounted on the swivel part of the rotary launcher. -By combining the Tracker system, it is possible to dramatically expand the target attack range during aerial combat and provide an aircraft fire control system that can optimally avoid the attack of the other aircraft.

[Brief description of drawings]

FIG. 1 is a system configuration diagram showing an embodiment of the present invention, FIG. 2 is a diagram showing an embodiment showing the configuration of a rotary launcher, and FIGS. 3 and 4 show the operation of the system of the present invention. FIG. 5 is a diagram showing a display example of a HUD for the purpose, FIG. 5 is a diagram showing a configuration example of the conventional fire control system, and FIG. 6 is a diagram showing a display example of the HUD showing the operation of the conventional system. In the figure, (7) is an optical sensor tracker, (12) is an optical sensor data processor, (17) is a rotary launcher controller, and (18) is a rotary launcher. In the drawings, the same or corresponding parts are designated by the same reference numerals.

Claims (1)

[Claims] 1. An optical sensor / tracker capable of suspending a single-shot or a plurality of infrared detection missiles or an active radar / homing / missile and optically capturing / tracking a target and performing distance measurement with the target. However, the rotary missile launcher that can turn in all directions and that can be mounted on the underside of the fuselage of the aircraft, and the rotary computer that controls the rotary drive of the missile launcher and the optical sensor tracker in a predetermined direction according to the instructions of the central computer. It has a launcher controller and a multi-brex data bus interface, and it processes the specifications and image data of the target detected and tracked by the optical sensor tracker and sends the target data to the central computer. It is equipped with an optical sensor data processor that can A fire control system for an aircraft.