JPH0245393U

JPH0245393U -

Info

Publication number: JPH0245393U
Application number: JP11685488U
Authority: JP
Priority date: 1988-09-07
Filing date: 1988-09-07
Publication date: 1990-03-28

Description

[Brief explanation of drawings]

第１図は本考案の一実施例の飛しよう経路を示
す図でａは平面図、ｂは側面図、第２図は本実施
例の囮ミサイルの側面図、第３図は第２図のノー
ズ部分の拡大図、第４図はルネベルグレンズの原
理図、第５図はルネベルグレンズの比誘電率の変
化と比誘電率εとの関係線図、第６図は段階状に
比誘電率を変化させたルネベルグレンズの概念図
、第７図は従来例のミサイルによる被発見率の低
減手段を示す飛しよう経路の平面図である。１……レドーム、２……ルネベルグレンズ、３
……位置制御誘導部（含飛しよう経路プログラム
）、４……燃料タンク、５……主翼、６……エン
ジン、７……操舵翼、８……制御部、１０，２０
……母機、１３，２３……目標艦船、１１，２１
……囮ミサイル飛しよう経路、１２，２２……実
ミサイル飛しよう経路、２４……海面、３１……
囮部、３２……ボルト。 Fig. 1 is a diagram showing the flight path of an embodiment of the present invention, in which a is a plan view, b is a side view, Fig. 2 is a side view of the decoy missile of this embodiment, and Fig. 3 is the same as Fig. 2. An enlarged view of the nose part, Figure 4 is a diagram of the principle of Luneberg lenses, Figure 5 is a relationship diagram between the change in relative permittivity of Luneberg lenses and relative permittivity ε, and Figure 6 is a stepwise diagram of the relative permittivity. FIG. 7 is a conceptual diagram of a Luneberg lens with varying rates, and is a plan view of a flight path showing a means of reducing the detection rate of a conventional missile. 1...Radome, 2...Luneberg lens, 3
...Position control guidance unit (flying route program), 4...Fuel tank, 5...Main wing, 6...Engine, 7...Steering wing, 8...Control unit, 10, 20
...Mother aircraft, 13,23...Target ship, 11,21
...Decoy missile flight route, 12,22...Actual missile flight route, 24...Sea surface, 31...
Decoy part, 32...Bolt.

Claims

[Scope of utility model registration request]

The nose of the missile, which can control its position while flying, is equipped with a radome that allows radio waves to be input from at least the front, and a Luneberg lens that is installed inside the radome so that the incident radio waves can be reflected. A decoy missile characterized by