JPH02287100A - Missile guiding device - Google Patents

Abstract

PURPOSE:To guide a missile along the shortest trajectory by a method wherein a solar orientation calculation part for performing a calculation in reference to a clock with a calendar, a trajectory calculating part, a guidance control part and an infra-red ray image guidance device are provided. CONSTITUTION:A solar orientation calculation part 1 may calculate a solar orientation angle in reference to a time and date of a missile launching and an inputted target position. A trajectory calculation part 2 may set the shortest trajectory capable of guiding the missile with the sun being placed at back in reference to the inputted launching direction, the target position and the minimum rotating radius capable of launching missile. A guidance control part 3 may guide the missile on a set path. An infra-red ray image guiding device 4 may output a guiding signal to the control part 3 by applying a lock-on to the target. With such an arrangement above, it is possible to supplement a disadvantage of the infra-red ray imaging system and to realize a discrimination of the type of ship, a discrimination of the guiding part, and a target discrimination function such as a decoy discrimination or the like.

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a method for guiding a flying object using an infrared imaging method (guiding a ship or the like).

[Conventional technology]

As shown in Figure 2, the conventional projectile guidance system allows the projectile to fly toward the target based on the target position and launch direction manually input during launch, regardless of the solar direction at that time. When it got close, it used an infrared image guidance device to search for the target, lock on to it (fix its sights on the target), and guide the projectile toward the target.

[Problem to be solved by the invention]

Conventionally, the path to attack the projectile's target was determined by the direction in which the projectile was launched and the target location.
When searching with an infrared image guidance system, depending on the direction of the sun, backlighting or near-backlight conditions often occurred. In this case, since the guided side of the target is in the shade, the temperature of that side is low and less infrared energy is emitted from the target. Therefore, in the conventional device, the lock-on distance of the infrared image guidance device that detects the infrared proboscis emitted from the target is shortened, which is disadvantageous in terms of the flying object guidance performance. The silhouette of the target is also clearly visible [K cannot be detected, and target identification functions such as paddy type identification, guided part identification, and decoy identification (identification of false buns) through image processing, which are characteristics of the infrared imaging method, cannot be fully utilized. There are many cases.

[Means to solve the problem]

A spacecraft hm device according to the present invention includes a solar azimuth calculation unit 1 that calculates a sun azimuth from a target position (latitude, longitude) inputted at the time of launch and a clock with a calendar, and a target position inputted from the solar azimuth and the target position inputted at the time of launch. a flight path calculation unit 2 that calculates the shortest flight path that can be guided from the launch direction with the sun at the back; and a guidance control unit 3 that guides the projectile to fly on the flight path. 1. From the moment you enter the guidance route with the sunlight behind you, search for the entire target and target it.
It is characterized by comprising an infrared image guidance device 4 that calculates a guidance signal for guiding a flying object to a target.

[Effect]

Harnessing the sun to improve target lock-on distance and target identification for projectiles. In other words, in order to always guide the projectile to the side that is illuminated by sunlight regardless of the launch location, direction, or target location, the projectile is equipped with a built-in calendar clock that records the date, time, and target location at the time of launch. A solar azimuth calculation section that calculates the sun's azimuth from latitude and longitude) and a flight path calculation section that sets the shortest flight path with the sun behind you when searching for a target immediately after launch. launch point, launch direction,
Depending on the relative relationship between the target position and the direction of the sun, the flying object can be automatically guided along the shortest flight path that allows for guidance with the sun at the back when searching for the target. - At night when sunlight is not available, guidance will be conducted in the same way as before.

〔Example〕

An entire embodiment of the invention is shown in FIG.

1A, the solar azimuth calculation unit 1 calculates the solar azimuth (horizontal plane) v8 from the date and time of the launch of the flying object and the target position (latitude, longitude) input from the outside at the time of launch according to a predetermined formula. calculate.

In the flight path calculation unit 2, the PS, the launch direction Vfo input from the outside curve at the time of launch, and the target position (XT,
XT, ) and the minimum possible turning radius r of the projectile
1. From RL, set the shortest flight route that you can guide with Tai1rei at your back. Figure 1 shows an example of a flight route. In this figure, P, 3 is the target.

The point is a distance R away from the target position in the sun direction, where R is the minimum distance required for lock-on. P,2 and P,3 are the points of contact between the circles and a straight line that is tangent to both the circle of radius r1 tracing the launch point and the circle of radius r+ passing through P,3. The guidance control unit 3 guides the flying object to fly on a set flying route. The infrared image guidance device 4 starts searching from P, 3, locks on to the target, and outputs a guidance signal to the guidance side assembly section 3.

〔Effect of the invention〕

As described above, since the present invention is provided with a solar azimuth calculation unit that incorporates δj゛ when a calendar is attached, the lock-on distance is increased by guiding the target with the sun at the back, which is a disadvantage of the infrared imaging method. In addition, by clearly detecting the silhouette of the target, the target identification functions such as rice type identification, 4-part identification, and decoy identification, which are characteristics of the infrared imaging method, can be maximized.

[Brief explanation of drawings]

FIG. 1 is a block diagram of an embodiment of the present invention and a diagram showing an example of a flight route, and FIG. 2 is a diagram showing a conventional example. Engineering... Sun direction 3↑ Santo, 2... Flying route 81
calculation section, 3... guidance control section, 4... infrared image guidance device. rl, r 2--e Shira"1Rt+1-a6+
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Claims (1)

[Claims] A solar azimuth calculation unit (1) that calculates the sun azimuth from the target position (latitude, longitude) input at the time of launch and a clock with a calendar; Flight route calculation section (which calculates the shortest flight route that can be guided by
2), a guidance control unit (3) that guides the flying object to fly on the flight path, and a guidance control unit (3) that searches for a target and flies to the target from the moment it enters the guidance path with sunlight behind it. Infrared image guidance device (
4) A flying object guidance device comprising: