JP2743560B2 - Synthetic aperture radar device - Google Patents
Synthetic aperture radar deviceInfo
- Publication number
- JP2743560B2 JP2743560B2 JP2190299A JP19029990A JP2743560B2 JP 2743560 B2 JP2743560 B2 JP 2743560B2 JP 2190299 A JP2190299 A JP 2190299A JP 19029990 A JP19029990 A JP 19029990A JP 2743560 B2 JP2743560 B2 JP 2743560B2
- Authority
- JP
- Japan
- Prior art keywords
- synthetic aperture
- aperture radar
- aircraft
- information
- resolution
- 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.)
- Expired - Fee Related
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- Radar Systems Or Details Thereof (AREA)
Description
【発明の詳細な説明】 〔産業上の利用分野〕 本発明は合成開口レーダに関し,特に搭載移動プラッ
トフォームが慣性航法装置を装備しない小型機を利用し
て運用する合成開口レーダ装置に関する。Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a synthetic aperture radar, and more particularly, to a synthetic aperture radar apparatus that is operated using a small-sized aircraft that does not have an inertial navigation device mounted on a moving platform.
〔従来の技術〕 慣性航法装置を搭載した大型航空機,人工衛星等の飛
翔体を移動プラットフォームとして利用する合成開口レ
ーダ装置はよく知られている。この合成開口レーダ装置
による飛翔体の進行方向と垂直な距離方向の分解能δr
は,(1)式のように表わされ,距離分解能δrは主に
信号帯域幅Δfに反比例する。2. Description of the Related Art Synthetic aperture radar devices using a flying object such as a large aircraft or artificial satellite equipped with an inertial navigation device as a moving platform are well known. Resolution δ r in the direction of distance perpendicular to the direction of flight of the flying object by this synthetic aperture radar device
Is (1) expressed as equation, the distance resolution [delta] r mainly inversely proportional to the signal bandwidth Delta] f.
δr=C/2・2.8/π・1/Δf・1/cosθ ……(1) C:電波伝搬速度,Δf:信号帯域幅, θ:仰角 また,飛翔体の進行方向の平行な方位分解能δaは,
(2)式のように表わされる。δ r = C / 2 · 2.8 / π · 1 / Δf · 1 / cosθ (1) C: radio wave propagation velocity, Δf: signal bandwidth, θ: elevation angle, and parallel azimuth resolution in the traveling direction of the flying object δ a will,
It is expressed as in equation (2).
δa≒D/2=V/fD ……(2) D:アンテナの実開口,v:航空機の速度 fD:ドップラー帯域幅 (1),(2)式から明らかなように,合成開口レー
ダ装置は,航空機の動揺が大きい場合,θ,v,fDが大き
く影響を受けるため,δr,δaが一定しないという問題
や,甚だしい場合には画像が欠落するという原理的問題
がある。従来は,この問題を解決するため,航空機等に
慣性航法装置を搭載して動揺を非常に小さくするととも
に,同時に姿勢誤差データを記録し,画像再生時に補正
する方式を取っていた。δ a ≒ D / 2 = V / f D (2) D: real aperture of antenna, v: speed of aircraft f D : Doppler bandwidth As is clear from equations (1) and (2), synthetic aperture The radar system has a problem that δ r and δ a are not constant because the θ, v, and f D are greatly affected when the aircraft sway is large, and there is a fundamental problem that the image is missing in severe cases. . Conventionally, in order to solve this problem, an inertial navigation device is mounted on an aircraft or the like to minimize the sway, and at the same time, the attitude error data is recorded and corrected at the time of image reproduction.
上述した従来の合成開口レーダ装置では,搭載プラッ
トホームとしての飛翔体に非常に高度の姿勢安定精度が
要求されるため,姿勢安定度の悪い航空機及び姿勢誤差
データを持たない航空機では,原理的に高品質な合成開
口レーダ画像を得ることは不可能であるという問題点が
あった。In the above-mentioned conventional synthetic aperture radar system, a very high attitude stability accuracy is required for the flying object as a mounting platform. There is a problem that it is impossible to obtain a high quality synthetic aperture radar image.
本発明の合成開口レーダ装置は,小型航空機に搭載し
人工衛星を利用して自己の位置を測定する位置測定装置
から情報を受けつつ、小型航空機の姿勢安定度に対応し
た距離分解能および包囲分解能の低下にもとづいてもた
らされるターゲット情報の劣化を補償しうる程度に送信
電波のビーム幅を拡げるとともにパルス繰返し周波数を
高くして運用する構成を有する。The synthetic aperture radar system of the present invention receives information from a position measurement device which is mounted on a small aircraft and measures its own position using an artificial satellite, and obtains a distance resolution and a surrounding resolution corresponding to the attitude stability of the small aircraft. It has a configuration in which the beam width of the transmission radio wave is widened and the pulse repetition frequency is increased to such an extent that the degradation of the target information caused by the decrease can be compensated.
また,本発明の合成開口レーダ装置は,前記位置測定
装置から受ける情報は,前記小型航空機の位置,速度お
よび高度に関する情報を含むものとした構成を有する。Further, the synthetic aperture radar device of the present invention has a configuration in which the information received from the position measurement device includes information on the position, speed, and altitude of the small aircraft.
次に,本発明について図面を参照して説明する。 Next, the present invention will be described with reference to the drawings.
第1図は本発明の一実施例の構成図である。第1図に
示す実施例は,セスナ機等の小型機に搭載し,人工衛星
を利用して位置/速度/高度等の情報を取得する位置測
定装置(Global Positioning System)6と,合成開口
レーダ装置10を備えて成る。また,合成開口レーダ装置
10は,送信パルスを発生する送信部1と,地上からの受
信パルスを受信する受信部2と,送,受信パルスの送受
信を行なうSAR(Synthetic Aperture Radar,合成開口レ
ーダ)アンテナ3と,受信部2の出力を信号処理して出
力信号12を出力する信号処理部5と,位置測定装置6の
出力する位置/速度/高度情報9にもとづいて送信部5
の送信条件の設定制御を行なうとともに,信号処理部4
の信号処理に供する制御部5とを備えて成る。FIG. 1 is a configuration diagram of one embodiment of the present invention. The embodiment shown in FIG. 1 is mounted on a small machine such as a Cessna machine and uses a position measuring device (Global Positioning System) 6 for acquiring information such as position / velocity / altitude using an artificial satellite, and a synthetic aperture radar device. Comprising 10. Also, synthetic aperture radar system
Reference numeral 10 denotes a transmitting unit 1 for generating a transmitting pulse, a receiving unit 2 for receiving a receiving pulse from the ground, a SAR (Synthetic Aperture Radar) antenna 3 for transmitting and receiving a transmitting and receiving pulse, and a receiving unit. A signal processing unit 5 for processing the output of the second unit 2 to output an output signal 12, and a transmitting unit 5 based on position / velocity / altitude information 9 output by the position measuring device 6
Control of the transmission condition of the signal processing unit 4
And a control unit 5 for performing the above signal processing.
第2図は本発明の動作を説明するための動作概念図で
ある。以下,第1図の実施例の動作の説明に先立ち,先
ず本発明の動作の原理について説明する。FIG. 2 is an operation conceptual diagram for explaining the operation of the present invention. Before describing the operation of the embodiment shown in FIG. 1, the principle of the operation of the present invention will be described first.
第2図において,13は航空機が自分の位置/高度/速
度等に関するデータを入手するための複数の人工衛星で
ある。進行方向Lに沿って進行する航空機17では,人工
衛星3からの電波を受信し処理することにより上述した
データを得る。航空機17から地上に向って放射される合
成開口レーダの電流は,従来のものと比して広いビーム
幅のアジマスビーム幅14と,高いパルス繰返し周波数,
従って送信パルス間隔15の狭い送信パルス16となってい
る。このようにして,広いアジマスビーム幅14により,
ターゲット18を従来より長い時間観測できるため,航空
機17が多少動揺してもターゲット18に関する情報は十分
得られる。また,高いパルス繰返し周波数の送信パルス
16を採用することで,航空機17の動揺に精度よく追従す
ることができる。本発明の主要なポイントは,合成開口
データの受信データにできるだけ多くの航空機の動揺情
報を取り込むことである。In FIG. 2, reference numeral 13 denotes a plurality of artificial satellites for the aircraft to obtain data on its own position / altitude / speed and the like. The aircraft 17 traveling in the traveling direction L receives the radio waves from the artificial satellite 3 and processes them to obtain the above-described data. The current of the synthetic aperture radar radiated from the aircraft 17 to the ground is higher than the conventional one, with an azimuth beam width 14 having a wider beam width, a higher pulse repetition frequency,
Therefore, the transmission pulse 16 has a narrow transmission pulse interval 15. In this way, with a wide azimuth beam width 14,
Since the target 18 can be observed for a longer time than before, sufficient information on the target 18 can be obtained even if the aircraft 17 slightly shakes. Also, transmission pulses with high pulse repetition frequency
By adopting the 16, it is possible to accurately follow the fluctuation of the aircraft 17. The main point of the present invention is to incorporate as much aircraft motion information as possible into the received synthetic aperture data.
ふたたび第1図に戻って実施例の説明を続行する。 Returning to FIG. 1, the description of the embodiment will be continued.
送信部1は,合成開口レーダ装置10の送信パルスを発
生し,SARアンテナ3から地上に向けて放射する。地上か
ら反射した受信パルスは,SARアンテナ3で受信され受信
部2で所定のレベルまで増幅された後,信号処理部4で
A/D変換及びレンジ(距離)/アジマス(方位)圧縮等
が施され出力信号12として出力される。The transmitting unit 1 generates a transmission pulse of the synthetic aperture radar device 10 and radiates it from the SAR antenna 3 toward the ground. The received pulse reflected from the ground is received by the SAR antenna 3 and amplified to a predetermined level by the receiving unit 2, and then is received by the signal processing unit 4.
A / D conversion, range (distance) / azimuth (azimuth) compression, and the like are performed and output as an output signal 12.
また,人工衛星13からの受信電波8は受信アンテナ7
に入力し,位置測定装置6で処理して位置/速度/高度
情報6が求められ,この情報は画像処理するのに十分な
スピードで制御部5に出力される。The received radio wave 8 from the artificial satellite 13 is transmitted to the receiving antenna 7
The position / velocity / altitude information 6 is obtained by processing by the position measuring device 6, and this information is output to the control unit 5 at a speed sufficient for image processing.
制御部5では,こうして提供された高度情報等から所
望の分解能等を確保するのに必要な最適なパルス繰返し
周波数を設定し,この情報を供給するパルス繰返し切替
制御信号11を送信部1に出力する。また位置/速度/高
度情報9は信号処理部4にも入力され,信号処理部4で
の処理に直接利用されるかもしくは出力信号12のデータ
に添付される。The control unit 5 sets an optimum pulse repetition frequency necessary to secure a desired resolution or the like from the altitude information or the like provided in this way, and outputs a pulse repetition switching control signal 11 for supplying this information to the transmission unit 1. I do. The position / velocity / altitude information 9 is also input to the signal processing unit 4 and used directly for processing in the signal processing unit 4 or attached to the data of the output signal 12.
以上説明したように本発明は、人工衛星を利用した位
置測定装置を備えてアンテナビーム幅を広くとり、パル
ス繰返し周波数を高くすることにより、受信したSAR画
像から姿勢誤差情報を入手することが可能となり、姿勢
安定度の悪い小型航空機に搭載したSARでも高品質の画
像が得られるという効果がある。As described above, the present invention is capable of obtaining attitude error information from a received SAR image by providing a position measuring device using an artificial satellite, increasing the antenna beam width, and increasing the pulse repetition frequency. Thus, there is an effect that a high-quality image can be obtained even with a SAR mounted on a small aircraft having poor attitude stability.
第1図は本発明の一実施例の構成図,第2図は本発明の
動作概念図である。 1……送信部,2……受信部,3……SARアンテナ,4……信
号処理部,5……制御部,6……位置測定装置,7……受信ア
ンテナ,8……受信電波,9……位置/速度/高度情報,10
……合成開口レーダ装置,11……パルス繰返し切替制御
信号,12……出力信号,13……人工衛星,14……アジマス
ビーム幅,15……送信パルス間隔,16……送信パルス,17
……航空機,18……ターゲット。FIG. 1 is a block diagram of an embodiment of the present invention, and FIG. 2 is a conceptual diagram of the operation of the present invention. 1 ... transmitter, 2 ... receiver, 3 ... SAR antenna, 4 ... signal processor, 5 ... controller, 6 ... position measuring device, 7 ... receiver antenna, 8 ... received radio wave, 9 …… Position / velocity / altitude information, 10
... Synthetic aperture radar device, 11 ... Pulse repetition switching control signal, 12 ... Output signal, 13 ... Satellite, 14 ... Azimuth beam width, 15 ... Transmission pulse interval, 16 ... Transmission pulse, 17
…… Aircraft, 18 …… Target.
Claims (1)
己の位置を測定する位置測定装置から小型航空機の位
置、速度、高度の情報を受けつつ、小型航空機の姿勢安
定度に対応した距離分解能および方位分解能の低下にも
とづいてもたらされるターゲット情報の劣化を補償しう
る程度に送信電波のビーム幅を拡げるとともにパルス繰
返し周波数を高くして運用することを特徴とする合成開
口レーダ装置。1. A distance corresponding to the attitude stability of a small aircraft while receiving information on the position, speed, and altitude of the small aircraft from a position measuring device mounted on the small aircraft and measuring its own position using an artificial satellite. A synthetic aperture radar apparatus characterized in that a beam width of a transmission radio wave is widened and a pulse repetition frequency is increased so as to be able to compensate for the deterioration of target information caused by a decrease in resolution and azimuth resolution.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2190299A JP2743560B2 (en) | 1990-07-18 | 1990-07-18 | Synthetic aperture radar device |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2190299A JP2743560B2 (en) | 1990-07-18 | 1990-07-18 | Synthetic aperture radar device |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH0476482A JPH0476482A (en) | 1992-03-11 |
JP2743560B2 true JP2743560B2 (en) | 1998-04-22 |
Family
ID=16255855
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2190299A Expired - Fee Related JP2743560B2 (en) | 1990-07-18 | 1990-07-18 | Synthetic aperture radar device |
Country Status (1)
Country | Link |
---|---|
JP (1) | JP2743560B2 (en) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH07110377A (en) * | 1993-10-12 | 1995-04-25 | Nec Corp | Radar target searching device |
US5432520A (en) * | 1993-10-18 | 1995-07-11 | Hughes Aircraft Company | SAR/GPS inertial method of range measurement |
JP2008162152A (en) * | 2006-12-28 | 2008-07-17 | Totsuya Echo:Kk | Reply postal card with tack seals and printed matter |
KR101958547B1 (en) * | 2017-04-14 | 2019-03-14 | 연세대학교 산학협력단 | System and method for altitude estimation of synthetic aperture radar using single path and single antenna |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS54161293A (en) * | 1978-06-09 | 1979-12-20 | Mitsubishi Electric Corp | Clutter removal system |
JPS61193088A (en) * | 1985-02-22 | 1986-08-27 | Nec Corp | Synthetic aperture radar equipment |
JPS61284686A (en) * | 1985-06-12 | 1986-12-15 | Japan Radio Co Ltd | Gps navigation device |
-
1990
- 1990-07-18 JP JP2190299A patent/JP2743560B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
JPH0476482A (en) | 1992-03-11 |
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