JPS6223260B2 - - Google Patents
Info
- Publication number
- JPS6223260B2 JPS6223260B2 JP54009830A JP983079A JPS6223260B2 JP S6223260 B2 JPS6223260 B2 JP S6223260B2 JP 54009830 A JP54009830 A JP 54009830A JP 983079 A JP983079 A JP 983079A JP S6223260 B2 JPS6223260 B2 JP S6223260B2
- Authority
- JP
- Japan
- Prior art keywords
- noise source
- temperature
- comparison
- antenna
- noise
- 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
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
- G01K11/006—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using measurement of the effect of a material on microwaves or longer electromagnetic waves, e.g. measuring temperature via microwaves emitted by the object
Landscapes
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Radiation Pyrometers (AREA)
- Geophysics And Detection Of Objects (AREA)
Description
【発明の詳細な説明】
この発明は人工衛星等の飛翔体に搭載してリモ
ートセンシングを行うDicke比較形マイクロ波放
射計の比較雑音源および温度校正用低雑音源の改
良に関するものである。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to improvements in a comparative noise source and a low noise source for temperature calibration of a Dicke comparative microwave radiometer mounted on a flying object such as an artificial satellite for remote sensing.
第１図は従来の人工衛星に搭載して地球表面の
物体から放射する電磁波を受信して地球環境のリ
モートセンシングを行うDicke比較形マイクロ波
放射計の一例である。図中、１は受信アンテナ、
２はスカイホーンと呼ばれる温度校正用低雑音
源、３は標準雑音源、４は比較雑音源、５は受信
機および６，７，８はそれぞれスイツチＡ，Ｂ，
Ｃである。一般に自然界の物体からは電磁波が放
射されており、放射の強度はその物体の輝度温度
と密接な関係がある。第１図の受信アンテナ１で
受信されるアンテナ温度ＴAは受信アンテナ１を
取りまく物体の輝度温度の分布ＴB（Ω）と受信
アンテナ１の利得関数Ｇ（Ω）とを用いて
ＴA＝１／４π∫∫Ｇ ４〓（Ω）ＴB（Ω）ｄΩ …(1)
で表される。ここでΩは立体角である。 Figure 1 is an example of a Dicke comparative microwave radiometer that is mounted on a conventional artificial satellite and receives electromagnetic waves emitted from objects on the earth's surface to remotely sense the earth's environment. In the figure, 1 is the receiving antenna,
2 is a low noise source for temperature calibration called a skyhorn, 3 is a standard noise source, 4 is a comparison noise source, 5 is a receiver, and 6, 7, 8 are switches A, B, respectively.
It is C. Generally, objects in the natural world emit electromagnetic waves, and the intensity of the radiation is closely related to the brightness temperature of the object. The antenna temperature T A received by the receiving antenna 1 in FIG . It is expressed as 1/4π∫∫ G 4 〓(Ω) T B (Ω) dΩ (1). Here Ω is the solid angle.
スイツチＡ６が側に接続されている場合、受
信されたアンテナ温度はＴAはスイツチＢ７に向
かう。スイツチＢ７はある瞬間には側に接続さ
れ、次の瞬間には側に接続される操作を数百Hz
で繰り返す。またスイツチＢ７の側には一定温
度T0の低雑音を発生するホーンアンテナから成
る比較雑音源４が接続されており、このスイツチ
切換操作に同期する受信機５内の同期検波器を通
して比較雑音源４の温度T0とアンテナ温度ＴAと
の差に比例する電圧Ｖが得られる。ただし、比較
雑音源４のホーンアンテナは常に宇宙の冷たい空
間に向けられているものとする。この場合、宇宙
の冷たい空間の輝度温度は周波数の関数として既
知の量であり、同時にホーンアンテナ自身の利得
関数も既知であるため、これらをもとにホーンア
ンテナのアンテナ温度T0を求めることができ
る。 If switch A6 is connected to the side, the received antenna temperature T A goes to switch B7. Switch B7 is connected to the side at one moment, and the operation at the next moment is several hundred Hz.
Repeat with In addition, a comparison noise source 4 consisting of a horn antenna that generates low noise at a constant temperature T 0 is connected to the switch B7 side, and the comparison noise source 4 is transmitted through a synchronous detector in the receiver 5 that is synchronized with the switch switching operation. A voltage V is obtained that is proportional to the difference between the temperature T 0 of No. 4 and the antenna temperature T A. However, it is assumed that the horn antenna of comparison noise source 4 is always directed toward the cold space of space. In this case, the brightness temperature of the cold space in space is a known quantity as a function of frequency, and at the same time, the gain function of the horn antenna itself is also known, so it is possible to calculate the antenna temperature T 0 of the horn antenna based on these. can.
マイクロ波放射計の観測機能を達成するために
は発生した電子Ｖをもとにアンテナ温度ＴAの値
を知ることが必要条件であり、この値は次の手順
を経ることによつて求めることができる。 In order to achieve the observation function of a microwave radiometer, it is necessary to know the value of the antenna temperature T A based on the generated electron V, and this value can be found by going through the following steps. I can do it.
まず、スイツチＡ６の接続を側から側に切
り換える。スイツチＣ８が側の時に温度校正用
低雑音源２からのアンテナ温度T1が、そして
側の時に標準雑音源３の雑音温度T2が受信機５
に導かれ、それぞれ比較雑音源４との温度差に比
例する電圧V1およびV2が受信機５内で発生す
る。ここで温度校正用低雑音源２のスカイホーン
は比較雑音源４のホーンアンテナと同様、常に宇
宙の冷たい空間に向けられているものとすれば比
較雑音源４の場合と同様にして受信機５の入力温
度T1を知ることができる。一方、標準雑音源３
の雑音温度も標準雑音源３に温度センサを取り付
け、それをモニタすることによつて受信機５の入
力温度T2を知ることができる。なお、T0＜T1＜
T2であればV1＜Ｖ＜V2の関係があり、T1，T2，
V1，V2およびＶがわかるとアンテナ温度ＴAは次
式から求まる。 First, change the connection of switch A6 from side to side. When the switch C8 is on the side, the antenna temperature T1 from the low noise source 2 for temperature calibration is on the side, and when the switch C8 is on the side, the noise temperature T2 of the standard noise source 3 is on the receiver 5.
, voltages V 1 and V 2 are generated in the receiver 5 which are each proportional to the temperature difference with the comparison noise source 4 . Assuming that the skyhorn of the low noise source 2 for temperature calibration is always directed toward the cold space of space, like the horn antenna of the comparison noise source 4, the receiver 5 The input temperature T 1 can be known. On the other hand, standard noise source 3
By attaching a temperature sensor to the standard noise source 3 and monitoring it, the input temperature T2 of the receiver 5 can be determined. Note that T 0 <T 1 <
If T 2 , there is a relationship of V 1 < V < V 2 , and T 1 , T 2 ,
When V 1 , V 2 and V are known, the antenna temperature T A can be found from the following equation.
ＴA＝Ｖ２Ｔ１−Ｖ１Ｔ２／Ｖ２−Ｖ１＋Ｔ２−Ｔ１
／Ｖ２−Ｖ１…(2)
なお、以上では便宜上スイツチ等RF回路の損
失は無いものと仮定して説明した。 T A =V 2 T 1 −V 1 T 2 /V 2 −V 1 +T 2 −T 1
/V 2 -V 1 (2) For the sake of convenience, the explanation above has been made on the assumption that there is no loss in the RF circuit such as a switch.
以上の説明からも明らかなように、従来の
Dicke比較形マイクロ波放射形においては比較雑
音源４と温度校正用低雑音源２とにそれぞれ別個
のホーンアンテナを使用しているため重量の増
加、ホーンアンテナ相互間の影響等が問題となる
欠点があつた。 As is clear from the above explanation, the conventional
The Dicke comparison type microwave radiation type uses separate horn antennas for the comparison noise source 4 and the temperature calibration low noise source 2, so there are disadvantages such as increased weight and mutual influence between the horn antennas. It was hot.
そこでこの発明においては比較雑音源と温度校
正用低雑音源とを共用することによつて上述の従
来の欠点を除去するようにしたものである。以下
図面によりこの発明の一実施例について説明す
る。 Therefore, in the present invention, the above-mentioned drawbacks of the conventional method are eliminated by sharing the comparative noise source and the low noise source for temperature calibration. An embodiment of the present invention will be described below with reference to the drawings.
第２図において、１は受信アンテナ、３は標準
雑音源、５は受信機、６，７，８はそれぞれスイ
ツチＡ，Ｂ，Ｃ、９は比較雑音源と温度校正用低
雑音源とを兼ねたホーンアンテナおよび１０は分
配器である。ホーンアンテナ９は太陽、月等の影
響を受けないような衛星構体面に取り付けられ、
常に宇宙の冷たい空間側にあるものとする。この
発明ではホーンアンテナ９は比較雑音源と温度校
正用低雑音源との両者を兼ねており、ホーンアン
テナ９からの雑音電波は分配器１０によつて分け
られた後、それぞれ所定の雑音源としての役目を
果たすことになる。このため従来のように２個の
ホーンアンテナを用いた場合に比べホーンアンテ
ナ相互間の影響が無くなる等の利点を有する。 In Fig. 2, 1 is a receiving antenna, 3 is a standard noise source, 5 is a receiver, 6, 7, and 8 are switches A, B, and C, respectively, and 9 serves as a comparison noise source and a low noise source for temperature calibration. 1 is a horn antenna and 10 is a distributor. The horn antenna 9 is attached to a surface of the satellite structure that is not affected by the sun, the moon, etc.
Assume that it is always on the cold side of space. In this invention, the horn antenna 9 serves as both a comparison noise source and a low noise source for temperature calibration, and after the noise radio waves from the horn antenna 9 are separated by the distributor 10, they are respectively used as predetermined noise sources. will play the role of Therefore, compared to the conventional case where two horn antennas are used, there is an advantage that there is no influence between the horn antennas.
以上では人工衛星を例にとつて説明したが、他
の飛翔体であつても差し支えない。 Although the above explanation uses an artificial satellite as an example, other flying objects may also be used.
以上述べたようにこの発明によれば１個のホー
ンアンテナで比較雑音源と温度校正用低雑音源と
が得られる効果を有する。 As described above, according to the present invention, one horn antenna has the effect of providing a comparison noise source and a low noise source for temperature calibration.
第１図は従来のマイクロ波放射計の説明図、第
２図はこの発明の一実施例を示す図であり、図中
１は受信アンテナ、２は温度校正用低雑音源、３
は標準雑音源、４は比較雑音源、５は受信機、
６，７，８はそれぞれスイツチＡ，Ｂ，Ｃ、９は
ホーンアンテナおよび１０は分配器である。
図中、同一部分または相当部分には同一符号を
付して示してある。
FIG. 1 is an explanatory diagram of a conventional microwave radiometer, and FIG. 2 is a diagram showing an embodiment of the present invention, in which 1 is a receiving antenna, 2 is a low noise source for temperature calibration, and 3 is a diagram showing an embodiment of the present invention.
is the standard noise source, 4 is the comparison noise source, 5 is the receiver,
6, 7, and 8 are switches A, B, and C, respectively; 9 is a horn antenna; and 10 is a distributor. In the figures, the same or corresponding parts are designated by the same reference numerals.
Claims (1)
と、一定温度T0の雑音を発生する比較雑音源
と、温度T1の雑音を発生する温度校正用低雑音
源と、温度T2（T1＜T2）の雑音を発生する標準雑
音源と、上記受信アンテナで受信された雑音アン
テナ温度ＴAと上記比較雑音源の温度T0との差に
比例する電圧、上記温度校正用低雑音源の温度
T1と上記比較雑音源の温度T0との差に比例する
電圧、および上記標準雑音源の温度T2と上記比
較雑音源の温度T0との差に比例する電圧を得る
受信機と、上記受信アンテナの受信出力と上記温
度校正用低雑音源あるいは上記標準雑音源の出力
とを切換えるスイツチと、このスイツチと上記受
信機との間に接続され、上記スイツチからの出力
と上記比較雑音源の出力とを切換えて上記受信機
に与えるスイツチとから構成され、人工衛星等の
飛翔体に搭載して使用されるマイクロ波放射計に
おいて、上記比較雑音源と上記温度校正用低雑音
源とを共用し、その雑音源としてホーンアンテナ
を用いるとともに、上記ホーンアンテナからの雑
音電波を比較雑音源と温度校正用低雑音源として
分配し、それぞれ分配された雑音電波を上記２つ
のスイツチを介して上記受信機へ与えるための分
配器を設けたことを特徴とするマイクロ波放射
計。1. A receiving antenna that receives electromagnetic waves from an object, a comparison noise source that generates noise at a constant temperature T 0 , a low noise source for temperature calibration that generates noise at a temperature T 1 , and a temperature T 2 (T 1 < T 2 ) A standard noise source that generates the noise, a voltage proportional to the difference between the noise antenna temperature T A received by the receiving antenna and the temperature T 0 of the comparison noise source, and the temperature of the low noise source for temperature calibration.
a receiver that obtains a voltage proportional to the difference between T 1 and the temperature T 0 of the comparison noise source, and a voltage proportional to the difference between the temperature T 2 of the standard noise source and the temperature T 0 of the comparison noise source; A switch is connected between the receiving output of the receiving antenna and the output of the low noise source for temperature calibration or the standard noise source, and the switch is connected between the switch and the receiver, and the switch is connected between the output of the receiving antenna and the output of the low noise source for temperature calibration or the standard noise source. In a microwave radiometer used onboard a flying object such as an artificial satellite, the comparative noise source and the low noise source for temperature calibration are In addition to using a horn antenna as the noise source, the noise radio waves from the horn antenna are distributed as a comparison noise source and a low noise source for temperature calibration, and the distributed noise radio waves are transmitted to the above two via the two switches. A microwave radiometer characterized in that it is provided with a distributor for feeding it to a receiver.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP983079A JPS55101828A (en) | 1979-01-31 | 1979-01-31 | Microwave radiometer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP983079A JPS55101828A (en) | 1979-01-31 | 1979-01-31 | Microwave radiometer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS55101828A JPS55101828A (en) | 1980-08-04 |
| JPS6223260B2 true JPS6223260B2 (en) | 1987-05-22 |
Family
ID=11731039
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP983079A Granted JPS55101828A (en) | 1979-01-31 | 1979-01-31 | Microwave radiometer |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS55101828A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0463465U (en) * | 1990-10-15 | 1992-05-29 |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110470403B (en) * | 2019-08-21 | 2020-05-08 | 国家卫星气象中心(国家空间天气监测预警中心) | Surface source lunar measurement calibration method suitable for foundation microwave radiometer |
-
1979
- 1979-01-31 JP JP983079A patent/JPS55101828A/en active Granted
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0463465U (en) * | 1990-10-15 | 1992-05-29 |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS55101828A (en) | 1980-08-04 |
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