JPH07128434A - Navigation equipment and aircraft - Google Patents
Navigation equipment and aircraftInfo
- Publication number
- JPH07128434A JPH07128434A JP5271071A JP27107193A JPH07128434A JP H07128434 A JPH07128434 A JP H07128434A JP 5271071 A JP5271071 A JP 5271071A JP 27107193 A JP27107193 A JP 27107193A JP H07128434 A JPH07128434 A JP H07128434A
- Authority
- JP
- Japan
- Prior art keywords
- aircraft
- radar
- frequency
- rcs
- effective reflection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
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- Radar Systems Or Details Thereof (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、ステルス性を持たない
機体でも、敵レーダに探知される確率を減少する航法装
置及び航空機に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a navigation device and an aircraft that reduce the probability of being detected by an enemy radar even if the aircraft does not have stealth characteristics.
【０００２】有効反射断面積（以下ＲＣＳと称す）と
は、受信アンテナの方向に、実際の目標と全く同じ電力
を反射させる等方向性反射体の面（完全導体の球の断面
積）である。式で表すと次のようになる。The effective reflection cross-sectional area (hereinafter referred to as RCS) is the surface of an isotropic reflector (cross-sectional area of a perfect conductor sphere) that reflects exactly the same power as the actual target in the direction of the receiving antenna. . The formula is as follows.
【０００３】σ＝４πＲ2 （Ｅｒ）2 ／（Ｅｉ）2 ここでσ＝有効反射断面積、Ｅｒ＝反射された電界強度
の絶対値、Ｅｉ＝照射される電界強度の絶対値を示す。Σ = 4πR 2 (Er) 2 / (Ei) 2 where σ = effective reflection sectional area, Er = absolute value of reflected electric field intensity, and Ei = absolute value of irradiated electric field intensity.
【０００４】飛行機，船舶、大地のような、我々が対象
と考える普通の目標物の有効反射断面積は、その物体
の、所謂物理的な面積と殆ど一致することはなく、その
物体が大きければ、その有効反射断面積も大きいであろ
う程度にしかいえない。これは、一般の目標物は複雑な
表面を持ち、それよりの反射波は、互いに干渉しあうた
めと考えられ、表面に生じている僅かな変化が、有効反
射断面積にかなりの変化を与えることになる。The effective reflection cross section of an ordinary target that we consider to be an object, such as an airplane, a ship, or the earth, almost does not match the so-called physical area of the object, and if the object is large, However, it can only be said that the effective reflection cross section will be large. This is because a general target has a complicated surface, and the reflected waves from the target interfere with each other, and a slight change in the surface causes a considerable change in the effective reflection cross section. It will be.
【０００５】従って、目標物を照射するレーダビームの
角度、目標物の動揺、即ちレーダビームと目標物との間
の相対変動により、その目標の有効反射断面積は大きく
変化するものである。Therefore, the effective reflection cross-sectional area of the target greatly changes due to the angle of the radar beam irradiating the target and the fluctuation of the target, that is, the relative fluctuation between the radar beam and the target.
【０００６】図６は周波数が１０ＧＨｚの場合の航空機
のＲＣＳの１例を示しており、（ａ）は、航空機の機首
を上方に９０度傾けた状態で３６０度方向のＲＣＳを示
し、（ｂ）は航空機の機首を上方に６０度傾けた状態で
３６０度方向のＲＣＳを示し、（ｃ）は航空機の機首を
上方に３０度傾けた状態で３６０度方向のＲＣＳを示
し、（ｄ）は航空機の機首を下方に１０度傾けた状態で
３６０度方向のＲＣＳを示したもので、何れも翼の方向
のＲＣＳは大きくなつている。FIG. 6 shows an example of the RCS of an aircraft when the frequency is 10 GHz, and (a) shows the RCS in the direction of 360 degrees with the nose of the aircraft tilted upward by 90 degrees, ( (b) shows the RCS in the direction of 360 degrees when the nose of the aircraft is tilted upward by 60 degrees, and (c) shows the RCS in the direction of 360 degrees when the nose of the aircraft is tilted upward by 30 degrees, ( d) shows the RCS in the direction of 360 degrees when the nose of the aircraft is tilted downward by 10 degrees, and in each case, the RCS in the direction of the wing is increasing.
【０００７】[0007]
【従来の技術】敵レーダに探知される確率を減少するに
は、従来は大きく分けて次の２つの技術がある。2. Description of the Related Art In order to reduce the probability of being detected by an enemy radar, conventionally there are the following two techniques.
【０００８】（１）電波妨害によって、敵レーダの機能
を低下するか、或いは欺瞞を行い探知，追尾の確率を低
くする電波対抗策〔以下ＥＣＭ（Ｅｌｅｃｔｏｎｉｃ
Ｃｏｕｎｔｅｒ Ｍｅａｓｕｒｅ）と称す〕を用いる方
法。(1) A radio wave countermeasure (hereinafter referred to as ECM (Electronic) which reduces the probability of detection or tracking by deception by deteriorating the function of an enemy radar due to radio wave interference.
[Counter Measure]]] is used.
【０００９】（２）敵レーダ波を散乱又は吸収し易い異
様な機体形状に設計されており、敵レーダに探知されな
いと言われているステルス機がある（機体全体のＲＣＳ
が低い）。(2) There is a stealth aircraft that is designed to have an unusual airframe shape that easily scatters or absorbs enemy radar waves, and is said not to be detected by enemy radar (RCS of the entire aircraft).
Is low).
【００１０】[0010]
【発明が解決しようとする課題】しかしながら、（１）
の方法では、電波を発射する為に、逆にその妨害電波を
探知，追尾されてしまう問題点、及び、ＥＣＣＭ（Ｅｌ
ｅｃｔｏｎｉｃ Ｃｏｕｎｔｅｒ Ｃｏｕｎｔｅｒ Ｍ
ｅａｓｕｒｅ）と呼ばれるＥＣＭを無効にする技術があ
り、電波妨害がきかない場合がある問題点がある。[Problems to be Solved by the Invention] However, (1)
In this method, since the radio wave is emitted, on the contrary, the interfering radio wave is detected and tracked, and the ECCM (El
ectonic Counter Counter M
There is a technique called "easeure" for invalidating the ECM, and there is a problem that radio wave interference may not be effective.
【００１１】（２）のステルス機では、開発製造に膨大
な費用がかかり、又機体形状に制限があり、運動性をか
なり犠牲にせねばならない問題点がある。本発明は、敵
レーダに探知される確率が少なく、開発製造に膨大な費
用がかからない航法装置及び該航法装置を搭載した航空
機の提供を目的としている。In the stealth machine of (2), there is a problem that the development and manufacturing cost is enormous, the shape of the machine body is limited, and the maneuverability must be sacrificed considerably. It is an object of the present invention to provide a navigation device which has a low probability of being detected by an enemy radar and which does not require enormous cost to develop and manufacture, and an aircraft equipped with the navigation device.
【００１２】[0012]
【課題を解決するための手段】図１は本発明の原理ブロ
ック図である。図１（Ａ）に示す如く、予め測定された
航空機自身の、レーダにて使用される各周波数での全方
位ＲＣＳを記憶するＲＣＳメモリ１と、レーダ波の到来
方向及び周波数を瞬時に識別するＥＳＭ２及び、レーダ
装置３と、該ＥＳＭ２により識別されたレーダ波の到来
方向に、識別された周波数の自航空機の最小有効反射断
面積方向を一致させるよう機体の向きを制御するか又は
該レーダ装置３にて識別された他航空機の方向に自航空
機の最小有効反射断面積方向を一致させるよう機体の向
きを制御する制御装置４とを有する構成にするか、或い
はレーダサイトが地上のみにある場合は、図１（Ｂ）に
示す如く、予めレーダサイトの位置及び周波数情報を記
憶したエリント情報メモリ５と、予め測定された航空機
自身の、レーダにて使用される各周波数での全方位有効
反射断面積（ＲＣＳ）を記憶するＲＣＳメモリ１と、該
エリント情報メモリ５に記憶されたレーダサイトの方向
に対し、該周波数での自航空機の最小有効反射断面積方
向とを一致させるよう機体の向きを制御する制御装置６
とを有する構成にする。FIG. 1 is a block diagram showing the principle of the present invention. As shown in FIG. 1 (A), an RCS memory 1 that stores pre-measured omnidirectional RCS at each frequency used by a radar of the aircraft itself and an arrival direction and frequency of a radar wave are instantly identified. The direction of the airframe is controlled so that the direction of arrival of the radar wave identified by the ESM2 and the radar device 3 and the direction of arrival of the radar wave identified by the ESM2 coincides with the direction of the minimum effective reflection cross-section of the own aircraft, or the radar device When the control device 4 controls the direction of the aircraft so that the direction of the minimum effective reflection cross-section of the own aircraft matches the direction of the other aircraft identified in 3 or the radar site is only on the ground. As shown in FIG. 1 (B), is used in the radar, which is the elite information memory 5 in which the position and frequency information of the radar site is stored in advance and the aircraft itself which is measured in advance. The RCS memory 1 for storing the omnidirectional effective reflection cross section (RCS) at the wave number, and the direction of the radar site stored in the elite information memory 5 with respect to the direction of the minimum effective reflection cross section of the aircraft at the frequency. Control device 6 for controlling the orientation of the aircraft so that
And a configuration having.
【００１３】[0013]
【作用】図１（Ａ）に示す、本発明によれば、レーダ波
をＥＳＭ２にて受信すれば、制御装置４にて、ＥＳＭ２
にて識別されたレーダ波の到来方向に、識別された周波
数の自航空機の最小ＲＣＳ方向とを一致させるように機
体の向きを制御するか、又はレーダ装置３を用いた場合
は、制御装置４にて、レーダ装置３にて識別された航空
機の方向に、自航空機の最小ＲＣＳ方向とを一致させる
ように機体の向きを制御するので、敵レーダによる自航
空機の探知確率を減少することが出来る。勿論開発製造
に膨大な費用がかかることはない。According to the present invention shown in FIG. 1A, when the radar wave is received by the ESM2, the controller 4 causes the ESM2 to
The direction of the airframe is controlled so that the arrival direction of the radar wave identified in step 3 is matched with the minimum RCS direction of the own aircraft of the identified frequency, or when the radar device 3 is used, the control device 4 Since the orientation of the aircraft is controlled so that the direction of the aircraft identified by the radar device 3 matches the minimum RCS direction of the aircraft, the probability of detection of the aircraft by enemy radar can be reduced. . Of course, the development and manufacturing does not require huge cost.
【００１４】レーダサイトが地上のみにある場合は、図
１（Ｂ）に示す、本発明によれば、制御装置６にて、エ
リント情報メモリ５に記憶されたレーダサイトの位置の
方向に対し、エリント情報メモリ５に記憶されたレーダ
サイトの周波数での自航空機の最小ＲＣＳ方向とを一致
させるように機体の向きを制御するので、敵レーダによ
る自航空機の探知確率を減少することが出来る。勿論開
発製造に膨大な費用がかかることはない。When the radar site is only on the ground, according to the present invention shown in FIG. 1 (B), the control device 6 controls the direction of the position of the radar site stored in the elite information memory 5, Since the orientation of the aircraft is controlled so as to match the minimum RCS direction of the aircraft at the frequency of the radar site stored in the elite information memory 5, the probability of detection of the aircraft by the enemy radar can be reduced. Of course, the development and manufacturing does not require huge cost.
【００１５】[0015]
【実施例】図２は本発明の実施例の航法装置のブロック
図、図３は本発明の他の実施例の航法装置のブロック
図、図４は１例の航空機のレーダに対しＲＣＳを最低方
向にした状態を示す図、図５は１例のレーダサイトのレ
ーダに対しＲＣＳを最低方向にした状態を示す図であ
る。2 is a block diagram of a navigation device according to an embodiment of the present invention, FIG. 3 is a block diagram of a navigation device according to another embodiment of the present invention, and FIG. FIG. 5 is a diagram showing a state in which the RCS is oriented in the lowest direction with respect to a radar at an example radar site.
【００１６】如何なる航空機においても、その形状に対
するＲＣＳは、見る方向によってその大きさが違ってく
る。又周波数特性を持つている。自航空機の３次元のＲ
ＣＳを、レーダに用いる周波数毎に測定しておき、その
ＲＣＳパターンを図２，図３のＲＣＳメモリ１に記憶し
ておく。In any aircraft, the size of the RCS for its shape varies depending on the viewing direction. It also has frequency characteristics. 3D R of own aircraft
CS is measured for each frequency used for radar, and the RCS pattern thereof is stored in the RCS memory 1 of FIGS. 2 and 3.
【００１７】図２のＥＳＭ２は、敵レーダよりの電波
（主として８ＭＨｚ〜１８ＭＨｚ）をアンテナを介して
受信する受信器１７、受信器１７にて受信した電波の到
来方位を見つける方位分析部８，受信した電波の周波数
を見つける周波数分析器９よりなり、ＥＳＭ２で見つけ
た敵レーダの方向及び周波数を制御装置４の計算機１４
に入力する。The ESM 2 shown in FIG. 2 is a receiver 17 for receiving radio waves (mainly 8 MHz to 18 MHz) from an enemy radar through an antenna, an azimuth analysis unit 8 for finding the arrival direction of the radio waves received by the receiver 17, and reception. The frequency analyzer 9 for finding the frequency of the radio wave that has been generated, and the computer 14 of the control device 4 for calculating the direction and frequency of the enemy radar found by the ESM2.
To enter.
【００１８】図２のレーダ装置３は、電波を発射すると
秘匿性が失われる為に、可能な限り電波を発射すること
は避け、敵レーダ方向を精密に測定する場合使用するも
ので、サーキュレータ又は送受切り替えスイッチ１０，
送信器１１，受信器１２、方位分析部１３よりなり、送
信器１１より発射した電波が敵航空機にて反射して帰っ
てきた電波を受信器１２で受信して、方位分析部１３に
入力し、求めた敵航空機の方向を制御装置４の計算機１
４に入力する。The radar device 3 of FIG. 2 loses concealment when it emits radio waves, so it is used to precisely measure the direction of an enemy radar by avoiding the emission of radio waves as much as possible. Transmission / reception switch 10,
The transmitter 11, the receiver 12, and the azimuth analysis unit 13 are provided. The radio wave emitted from the transmitter 11 is reflected by an enemy aircraft and returned to the azimuth analysis unit 13 and is received by the receiver 12. , The computer 1 of the control device 4 to the obtained direction of the enemy aircraft
Enter in 4.
【００１９】ＥＳＭ２にて敵レーダよりの電波を受信し
た時は、計算機１４では、ＥＳＭ２より入力した敵レー
ダの方向，周波数にて、ＲＣＳメモリ１に記憶している
内容より、該周波数の自航空機の最小ＲＣＳの方向を求
め、自動操縦装置１５に入力し、自動操縦装置１５に
て、レーダ波の到来方向に、自航空機の最小ＲＣＳの方
向を一致させるよう機体の状態情報送信部１６よりの情
報により、機体の向きを制御する。When the radio wave from the enemy radar is received by the ESM2, the computer 14 determines the direction and frequency of the enemy radar input from the ESM2 from the contents stored in the RCS memory 1 according to the frequency of the own aircraft. The minimum RCS direction of the aircraft is calculated and input to the autopilot device 15, and the autopilot device 15 controls the aircraft state information transmission unit 16 to match the direction of the radar wave arrival with the minimum RCS direction of the aircraft. The information controls the orientation of the aircraft.
【００２０】レーダ装置３にて、敵航空機の方向を求め
た時は、計算機１４では、ＲＣＳメモリ１に記憶してい
る内容より、レーダ装置３より入力した、一番使われる
敵レーダの周波数（例えば１０ＭＨｚ）の最小ＲＣＳの
方向を求め、自動操縦装置１５に入力し、自動操縦装置
１５にて、敵航空機の方向に、自航空機の最小ＲＣＳの
方向を一致させるよう機体の状態情報送信部１６よりの
情報により、機体の向きを制御する。When the radar device 3 obtains the direction of the enemy aircraft, the computer 14 determines from the contents stored in the RCS memory 1 that the frequency of the most used enemy radar input from the radar device 3 ( For example, the minimum RCS direction of 10 MHz) is obtained and input to the autopilot device 15, and the autopilot device 15 causes the aircraft state information transmission unit 16 to match the direction of the enemy aircraft with the minimum RCS direction of the own aircraft. The orientation of the aircraft is controlled by the information from
【００２１】戦闘機の場合の如く、対応を早くせねばな
らない時は、手動操縦装置１８側に切り替えるが、この
時は、デイスプレイ１７上に、敵レーダ方向と、計算機
１４で求めた自航空機の最小ＲＣＳの方向が同時に表示
され、方位のずれが一目で判るようになるので、手動操
縦で、機体の状態情報送信部１６よりの情報により、機
体の向きを、敵レーダ方向に自航空機の最小ＲＣＳの方
向を一致させるように機体の向きを制御する。When it is necessary to respond quickly, as in the case of a fighter plane, the manual control unit 18 is switched to, but at this time, the direction of the enemy radar on the display 17 and the own aircraft determined by the computer 14 are displayed. Since the direction of the minimum RCS is displayed at the same time, and the misalignment of the azimuth can be seen at a glance, the direction of the aircraft can be changed to the enemy radar direction by the information from the aircraft state information transmission unit 16 by manual operation. The orientation of the aircraft is controlled so that the RCS directions match.
【００２２】図５，図６には、敵レーダが、航空機に搭
載されている場合，地上のレーダサイトにある場合の、
敵レーダの方向に対しＲＣＳの最低方向にした状態を示
している。FIGS. 5 and 6 show the case where the enemy radar is mounted on the aircraft and at the ground radar site.
The state is shown in which the direction of the enemy radar is set to the lowest RCS direction.
【００２３】地上にあるレーダサイトは、移動しないの
で、電波を発射していない時は、ＥＳＭ２でも、レーダ
装置３にてもレーダサイトの位置を検出することは出来
ない。そこで、予めレーダサイトの位置及びレーダの周
波数情報を、図３のエリント情報メモリ５に記憶してお
き、計算機１９にて、エリント情報メモリ５及びＲＣＳ
メモリ１に記憶した内容より、該レーダサイトの位置に
対し、該周波数での自航空機の最小ＲＣＳの方向を求
め、自動操縦装置１５に入力し、自動操縦装置１５に
て、レーダサイトの方向に、自航空機の最小ＲＣＳの方
向を一致させるよう機体の状態情報送信部１６よりの情
報により、機体の向きを制御する。Since the radar site on the ground does not move, neither the ESM 2 nor the radar device 3 can detect the position of the radar site when no radio wave is emitted. Therefore, the position of the radar site and the frequency information of the radar are stored in advance in the elint information memory 5 of FIG. 3, and the computer 19 uses the elint information memory 5 and the RCS.
From the contents stored in the memory 1, the direction of the minimum RCS of the own aircraft at the frequency is calculated for the position of the radar site, and is input to the autopilot device 15. The orientation of the aircraft is controlled according to the information from the aircraft state information transmission unit 16 so that the direction of the minimum RCS of the aircraft is matched.
【００２４】手動にした場合は、デイスプレイ１７上
に、敵レーダサイトの方向と、計算機１４で求めた自航
空機の最小ＲＣＳの方向が同時に表示され、方位のずれ
が一目で判るようになるので、手動操縦で、機体の状態
情報送信部１６よりの情報により、機体の向きを、敵レ
ーダサイトの方向に自航空機の最小ＲＣＳの方向を一致
させるように機体の向きを制御する。In the case of manual operation, the direction of the enemy radar site and the direction of the minimum RCS of the own aircraft obtained by the computer 14 are simultaneously displayed on the display 17, and the deviation of the bearing can be seen at a glance. By manual operation, the orientation of the aircraft is controlled by the information from the aircraft state information transmission unit 16 so that the orientation of the aircraft matches the direction of the enemy radar site with the direction of the minimum RCS of the aircraft.
【００２５】敵のレーダに見つからずに飛行し、偵察，
爆撃などの戦闘を行うことを目的としたステレス機が開
発されている。これは敵のレーダ波を錯乱又は吸収する
ことにより、敵レーダに探知されないようにするもの
で、通常の戦闘機と比較して形状が異様である。Flying without being found by the enemy's radar, reconnaissance,
Steres aircraft have been developed for the purpose of conducting battles such as bombing. This is to prevent the radar wave from being detected by the enemy radar by confusing or absorbing the radar wave of the enemy, and the shape is strange as compared with a normal fighter.
【００２６】航空機の機体をステルス化（電波吸収体を
機体表面にコーディングしたもの又は錯乱し易い機体構
造を持つもの等）した上で、本発明の航法装置を搭載す
るとステルス性は更に向上する。The stealth property is further improved by mounting the navigation device of the present invention on the aircraft body made stealth (such as one having a radio wave absorber coated on the surface of the body or one having a body structure that is easily confused).
【００２７】又航空機の機体のある部分を何箇所かステ
レス化しておき、本発明の航法装置を搭載するとステル
ス性は向上する。又ＦＳーＸの如く、機首を進行方向と
別方向に向けた儘で飛べるＣＣＶ（Ｃｏｎｔｒｏｌ Ｃ
ｏｎｆｉｇｕｒｅｄ Ｖｅｈｉｃｌｅ）機に本発明の航
法装置を搭載すると、敵レーダ方向に機体の最小ＲＣＳ
方向を向けた儘飛行することが出来る。Further, if some part of the body of the aircraft is made to be steres and the navigation device of the present invention is mounted, the stealth property is improved. Also, like the FS-X, the CCV (Control C) allows the nose to fly in a direction different from the traveling direction.
When the navigation device of the present invention is mounted on an configured vehicle), the minimum RCS of the aircraft in the direction of the enemy radar
You can fly in the right direction.
【００２８】又敵の航空機或いはミサイル等に追跡され
ている場合に、振り切って逃げる為に、ＥＣＭと本発明
の航法装置を併用すれば、自航空機の残存確率が更に向
上する。If the ECM and the navigation system according to the present invention are used together in order to sway off and escape when being tracked by an enemy aircraft or missile, the survival probability of the own aircraft is further improved.
【００２９】[0029]
【発明の効果】以上詳細に説明せる如く本発明によれ
ば、開発製造に膨大な費用がかからず、敵レーダに探知
される確率を小さく出来る効果がある。As described in detail above, according to the present invention, it is possible to reduce the probability of being detected by an enemy radar without enormous cost for development and manufacturing.
【図１】は本発明の原理ブロック図、FIG. 1 is a block diagram of the principle of the present invention,
【図２】は本発明の実施例の航法装置のブロック図、FIG. 2 is a block diagram of a navigation device according to an embodiment of the present invention,
【図３】は本発明の他の実施例の航法装置のブロック
図、FIG. 3 is a block diagram of a navigation device according to another embodiment of the present invention,
【図４】は１例の航空機のレーダに対しＲＣＳを最低方
向にした状態を示す図、FIG. 4 is a diagram showing a state where the RCS is set to the lowest direction with respect to an example aircraft radar;
【図５】は１例のレーダサイトのレーダに対しＲＣＳを
最低方向にした状態を示す図、FIG. 5 is a diagram showing a state where the RCS is set to the lowest direction with respect to the radar of an example radar site,
【図６】は１例の航空機のＲＣＳを示す図である。FIG. 6 shows an example RCS of an aircraft.
１はＲＣＳメモリ、 ２はＥＳＭ、 ３はレーダ装置、 ４，６は制御装置、 ５はエリント情報メモリ、 ７，１２は受信器、 ８，１３は方位分析部、 ９は周波数分析部、 １０はサーキュレータ又は送受切り替えスイッチ、 １１は送信器、 １４，１９は計算機、 １５は自動操縦装置、 １６は機体の状態情報送信部、 １７はディスプレイ、 １８は手動操縦装置を示す。 1 is an RCS memory, 2 is an ESM, 3 is a radar device, 4 is a control device, 4 is a control device, 5 is an elite information memory, 7 is a receiver, 8 is an azimuth analysis unit, 9 is a frequency analysis unit, 10 is a A circulator or a transmission / reception changeover switch, 11 is a transmitter, 14 and 19 are computers, 15 is an autopilot device, 16 is a state information transmission unit of an aircraft, 17 is a display, and 18 is a manual pilot device.
Claims (4)
て使用される各周波数での全方位有効反射断面積（ＲＣ
Ｓ）を記憶するＲＣＳメモリ（１）と、レーダ波の到来
方向及び周波数を瞬時に識別する電子支援策装置（ＥＳ
Ｍ）（２）及び、レーダ装置（３）と、該電子支援策装
置（２）により識別されたレーダ波の到来方向に、識別
された周波数の自航空機の最小有効反射断面積方向を一
致させるよう機体の向きを制御するか又は該レーダ装置
（３）にて識別された他航空機の方向に自航空機の最小
有効反射断面積方向を一致させるよう機体の向きを制御
する制御装置（４）とを有することを特徴とする航法装
置。1. An omnidirectional effective reflection cross-section (RC) of each of the frequencies measured by the aircraft itself at each frequency used in radar.
RCS memory (1) for storing S) and an electronic assistance device (ES) for instantaneously identifying the arrival direction and frequency of a radar wave.
M) (2), the radar device (3), and the direction of arrival of the radar wave identified by the electronic assistance device (2) are matched with the direction of the minimum effective reflection cross-section of the own aircraft of the identified frequency. A controller (4) for controlling the orientation of the aircraft or for controlling the orientation of the aircraft so that the direction of the other aircraft identified by the radar device (3) matches the direction of the minimum effective reflection cross-section of the aircraft. A navigation device characterized by having.
い複数の処をステルス化した上で、請求項１記載の航法
装置を搭載したことを特徴とする航空機。2. An aircraft comprising the navigation apparatus according to claim 1, wherein a plurality of portions having a small effective reflection cross-sectional area of the airframe of the aircraft are stealthed, and the navigation device according to claim 1 is mounted.
ｕｒｅｄ Ｖｅｈｉｃｌｅ）機に請求項１記載の航法装
置を搭載したことを特徴とする航空機。3. CCV (Control Config)
An aircraft comprising the navigation device according to claim 1 mounted on a ured vehicle).
を記憶したエリント情報メモリ（５）と、予め測定され
た航空機自身の、レーダにて使用される各周波数での全
方位有効反射断面積（ＲＣＳ）を記憶するＲＣＳメモリ
（１）と、該エリント情報メモリ（５）に記憶されたレ
ーダサイトの方向に対し、該周波数での自航空機の最小
有効反射断面積方向とを一致させるよう機体の向きを制
御する制御装置（６）とを有することを特徴とする航法
装置。4. An elint information memory (5) in which the position and frequency information of a radar site are stored in advance, and an omnidirectional effective reflection cross-section (RCS) at each frequency of the aircraft itself, which is measured in advance, at each frequency. ) For storing the RCS memory (1) and the direction of the radar site stored in the elite information memory (5) so that the orientation of the aircraft matches the direction of the minimum effective reflection cross-section of the aircraft at the frequency. And a control device (6) for controlling the navigation device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5271071A JPH07128434A (en) | 1993-10-29 | 1993-10-29 | Navigation equipment and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5271071A JPH07128434A (en) | 1993-10-29 | 1993-10-29 | Navigation equipment and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH07128434A true JPH07128434A (en) | 1995-05-19 |
Family
ID=17494986
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5271071A Withdrawn JPH07128434A (en) | 1993-10-29 | 1993-10-29 | Navigation equipment and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH07128434A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0915323A (en) * | 1995-06-28 | 1997-01-17 | Fujitsu Ltd | Radar device |
| JP2003337167A (en) * | 2002-05-20 | 2003-11-28 | Mitsubishi Electric Corp | Radar wave reflection reducing apparatus |
| JP2013164303A (en) * | 2012-02-09 | 2013-08-22 | Mitsubishi Electric Corp | Antenna device |
| JP2014173932A (en) * | 2013-03-07 | 2014-09-22 | Mitsubishi Electric Corp | Antenna device |
| JP2017009530A (en) * | 2015-06-25 | 2017-01-12 | 三菱電機株式会社 | Antenna device |
| JP2018179707A (en) * | 2017-04-11 | 2018-11-15 | 三菱重工業株式会社 | Stealth deterioration region notification system, stealth deterioration region notification method and program |
| JP2019184367A (en) * | 2018-04-06 | 2019-10-24 | 三菱電機株式会社 | Guiding device |
| JP2019203786A (en) * | 2018-05-23 | 2019-11-28 | 三菱電機株式会社 | Antenna device and induction device |
-
1993
- 1993-10-29 JP JP5271071A patent/JPH07128434A/en not_active Withdrawn
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0915323A (en) * | 1995-06-28 | 1997-01-17 | Fujitsu Ltd | Radar device |
| JP2003337167A (en) * | 2002-05-20 | 2003-11-28 | Mitsubishi Electric Corp | Radar wave reflection reducing apparatus |
| JP2013164303A (en) * | 2012-02-09 | 2013-08-22 | Mitsubishi Electric Corp | Antenna device |
| JP2014173932A (en) * | 2013-03-07 | 2014-09-22 | Mitsubishi Electric Corp | Antenna device |
| JP2017009530A (en) * | 2015-06-25 | 2017-01-12 | 三菱電機株式会社 | Antenna device |
| JP2018179707A (en) * | 2017-04-11 | 2018-11-15 | 三菱重工業株式会社 | Stealth deterioration region notification system, stealth deterioration region notification method and program |
| JP2019184367A (en) * | 2018-04-06 | 2019-10-24 | 三菱電機株式会社 | Guiding device |
| JP2019203786A (en) * | 2018-05-23 | 2019-11-28 | 三菱電機株式会社 | Antenna device and induction device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 20010130 |