JPS62879A - Electric wave and optical system composite seeker - Google Patents

Abstract

PURPOSE:To store antenna elements in an airframe by forming the reflection path of an electric wave by utilizing a light convergence path characteristic to an optical system seeker. CONSTITUTION:An infrared-light detector 43 equipped with a primary reflector 41, a secondary reflector 42, a reticle 44, a condenser lens 45, and an infrared- light detector 46 is united to constitute a gyro optical system. Two couples of antenna elements 31 of an electric wave system seeker 30, on the other hand, have their base ends arranged at the peripheral edge part of a luminous flux area and are united with the gyro optical system to constitute the horn antenna of a monopulse system. The reflection path of infrared light reaching the peripheral edge pat becomes the reflection path of the electric wave, so a radiation zone Z corresponding to respective antenna elements 31 is formed from the peripheral part of the primary reflector 41 and when the radio wave from a target crosses the zone Z, each couple of antenna elements 31 have a gain difference according to the azimuth angle and elevation or depression angle of the radio wave. Thus, the radio wave is transmitted or received as well as a system which have antenna elements arranged at the periphery of the head of the airframe.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a composite seeker that has both a radio wave seeker and an optical seeker, and particularly relates to a composite seeker used in a homing system for a rotating body missile or the like.

[Conventional technology]

A compound seeker emanates from the target. Alternatively, while detecting reflected radio waves and light (infrared light), the missile, etc. can be detected using a radio wave seeker.
-^1C no Poison - La 1 Notes The system mainly uses an optical seeker to track the aircraft, and the aircraft rotation type 1 missile is, for example, Aviation Week & 5.
It was introduced as a Ram missile in pace Technology (published December 11, 1978).
Additionally, an overview of radio wave seekers and optical seekers is explained in Introduction to Guided Weapons (November 25, 1980, published by the Defense Technology Association).

Figure 2 schematically shows the composite seeker in the R5i missile, where 1 is the missile body, 2 is the radome on the head of the aircraft, 10 is the radio seeker, and 20 is the optical seeker. Therefore, the missile flies while rolling at, for example, about 30 RPM.

In the radio seeker IO, 11 is one pair (two) or two pairs (four) of antenna elements protruding forward from around the head of the aircraft, and these antenna elements are used to configure a monopulse antenna. There is. 12 is an adder, 13 is a mixer, and 14 is a detection amplifier. When a radio wave from a target enters the radiation zone 21 of the antenna at an azimuth angle and an up/down angle relative to the coordinate system of the aircraft, the pair is A gain difference occurs between the antenna elements 11 . Adder 1
2 calculates the azimuth difference ΔX, the vertical difference Δy, and the sum Σ every moment based on the state of occurrence of this gain difference (differential mode). The mixer 13 calculates the azimuth angle error and the vertical angle error using this calculated value and the posture motion signal from the gyro as elements. The detection amplifier 14 processes this calculation result to generate an azimuth angle error signal δX' and an up/down angle error signal δy'.
is transmitted and input to the phase detector 15.

In the optical system seeker 20, 21 is a primary reflecting mirror with a concave reflecting surface, 22 is a secondary reflecting mirror with a flat reflecting surface, and 23 is an infrared light detector, which are integrated into a gyro optical system. It constitutes a system and is stably held by the rotation of the torquer 28.

The incident infrared light IR is reflected by the primary and secondary reflecting mirrors and is focused near the center of the primary reflecting mirror 21, focusing on a portion corresponding to the azimuth and up/down angle of the incident infrared light IH. tie,
In the infrared light detector 23.

24 is a reticle, 25 is a condenser lens, and 26 is an infrared light detector. The reticle 24 is placed at the focal point and rotated at the same speed as the gyro, and generates a modulated optical pulse according to the phase of the focal point. Focus the light upward. The detector 26 converts the modulated optical pulse into an electrical signal, and the detection amplifier 27 calculates the azimuth error δX'' and the vertical angle error δy'' based on this signal, and inputs the results to the phase detector 15. do. Then, the phase detector 15 receives these inputs δx',
δx#, and δ, I, δy# are processed to generate a steering angle signal δ.
Transmits X and δy.

[Problem that the invention seeks to solve]

By the way, in such conventional composite seekers, the antenna element protrudes outside the incident range of infrared light, which deteriorates the aerodynamic characteristics of the missile, etc., or prevents the antenna element from attaching to the launch tube. In order to prevent interference, there were problems such as the need to make the outer diameter of the aircraft larger than necessary.

Therefore, an object of the present invention is to prevent these antenna elements from protruding outside the aircraft body.

[Means of invention]

A means of the present invention that solves the above problems is that the antenna element is disposed at the periphery of the luminous flux area of the light condensed by one reflecting mirror.

[Effect]

According to the above means, the reflection path of infrared light from the periphery of the -order reflector to the periphery of the luminous flux area via the secondary reflection mirror also serves as the radio wave reflection path of the antenna disposed at this periphery. , it is possible to transmit or receive radio waves in the same manner as the conventional antenna element arranged around the head of the aircraft.

〔Example〕

In FIG. 1, 3 is the body of the Ram missile, 4 is a radome, and 30 and 40 are a radio wave seeker and an optical seeker, respectively, according to the present invention.

~Mu M -+lj, -ゝ----4 A
＾ +4 Ａう ＼ ＼ ＼ ＼ ＼ ＼ ＼ ＼ ＼ ＼ ＾↓Mirror, 42 is a secondary reflecting mirror, 43 is an infrared light detector comprising a reticle 44, a condensing lens 45, and an infrared light detector 46. , these are integrated to constitute a gyro optical system, and are stably held by the rotation of the torquer 48, as in the conventional case.

However, in this embodiment, the secondary reflecting mirror 42 is used as a convex mirror, and the luminous flux area focused on the central part of the primary reflecting mirror 41 is slightly expanded compared to the conventional one, and 49 is the front end of the infrared light detector 43. A condenser lens disposed in the reticle 44 condenses the infrared light reflected at the center of the luminous flux area and focuses it on the reticle 44. and reticle 4
4 generates a modulated optical pulse, the detector 46 converts this into an electrical signal, and the detection amplifier 47 receives this electrical signal and calculates the azimuth error δX" and the vertical angle error δy" as described above. This is the same as the conventional case.

In the radio wave seeker 30, reference numeral 31 denotes two pairs (four antenna elements), the base ends of which are arranged at the periphery of the luminous flux area to be integrated with the gyro optical system, and these antenna elements are arranged rearward. They extend oppositely to form a monopulse horn antenna. Therefore, since the reflection path of infrared light reaching the peripheral portion becomes the reflection path of radio waves, 1
A radiation zone Z corresponding to each antenna element 31 is formed from the periphery of the next reflector, and when radio waves from the target cross this zone, 6
The gain difference occurs between the paired antenna elements 31.

Thereafter, these gain differences are processed by the adder 32, the mixer 33, and the detection amplifier 34 to calculate the azimuth error δX' and the vertical angle error δy', and the phase detector 35 uses these calculation results and the optical Inputting the azimuth error δX" and the vertical angle error δy" from the system and transmitting the steering angle signals δX and δy is the same as in the conventional system, and in this case, the mixer 33 uses the calculated value ΔX of the adder 32. , Δy, Σ, and a signal of the relative attitude movement between the aircraft body 3 and the gyro optical system as calculation elements.

〔Effect of the invention〕

As explained above, in the present invention, the radio wave reflection path is formed by using the condensing path unique to the optical system seeker, so that the antenna element can be housed inside the fuselage. Therefore, the above-mentioned conventional problems caused by the protrusion of the antenna element can be solved.

[Brief explanation of drawings]

FIG. 1 is an explanatory diagram showing one embodiment of the present invention, and FIG. 2 is a diagram #1 of a conventional device. ! , 3...Airframe 10.30...Radio wave system seeker 11.31...Antenna element 20.40...Optical system seeker 21.41...Primary reflecting mirror 22.42...Secondary Reflector 23.43...Infrared light detector 24.44...Reticle 26.46...Infrared light detector IR...Infrared light

Claims (1)

[Claims] multiple antenna elements for configuring a radio wave seeker;
A radio wave system/optical system composite seeker, which is equipped with a condensing reflector for configuring an optical system seeker, and the antenna element is disposed at a peripheral portion of a luminous flux area of condensed light.