JPH01145700U - - Google Patents
Info
- Publication number
- JPH01145700U JPH01145700U JP3461788U JP3461788U JPH01145700U JP H01145700 U JPH01145700 U JP H01145700U JP 3461788 U JP3461788 U JP 3461788U JP 3461788 U JP3461788 U JP 3461788U JP H01145700 U JPH01145700 U JP H01145700U
- Authority
- JP
- Japan
- Prior art keywords
- aircraft
- compensator
- speed
- deviation
- sensor
- 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.)
- Pending
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 5
- 230000001133 acceleration Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 2
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Description
第1図はこの考案の一実施例によるフライトコ
ントロール装置を示す図、第2図は従来のフライ
トコントロール装置を示す図である。
1は機体、4〜7は補償器、9はセンサ。なお
、図中、同一符号は同一又は相当部分を示す。
FIG. 1 is a diagram showing a flight control device according to an embodiment of this invention, and FIG. 2 is a diagram showing a conventional flight control device. 1 is the fuselage, 4 to 7 are compensators, and 9 is a sensor. In addition, in the figures, the same reference numerals indicate the same or corresponding parts.
Claims (1)
装置において、機体速度Vおよび機体周辺の大気
密度ρと機体速度Vとの積ρVに相当する信号を
直接あるいは間接に検出するセンサと、フライト
コントロール装置に対する指令と機体の横加速度
信号との偏差を演算処理する第1の補償器と、機
体の姿勢角変化率信号を受け演算処理する第2の
補償器と、第1の補償器の出力と第2の補償器の
出力との偏差を演算処理する第3の補償器と、第
3の補償器の出力と機体の姿勢角変化率信号との
偏差を演算処理する第4の補償器を備え、上記4
つの補償器のゲイン及び時定数を、上記センサの
検出する機体速度Vあるいは積ρVに相当する信
号の関数によつて更新することを特徴とするフラ
イトコントロール装置。 A flight control system for an aircraft flying in the atmosphere includes a sensor that directly or indirectly detects a signal corresponding to the aircraft speed V and the product ρV of the air density ρ around the aircraft and the aircraft speed V, and a sensor that directly or indirectly detects a signal corresponding to the aircraft speed V and the product ρV of the air density ρ around the aircraft and the aircraft speed V, and a command to the flight control system. A first compensator that calculates and processes the deviation from the lateral acceleration signal of the aircraft, a second compensator that receives and processes the attitude angle change rate signal of the aircraft, and an output of the first compensator and a second compensation. a third compensator for calculating the deviation from the output of the aircraft; and a fourth compensator for calculating the deviation between the output of the third compensator and the attitude angle change rate signal of the aircraft;
A flight control device characterized in that the gain and time constant of the two compensators are updated by a function of a signal corresponding to the aircraft speed V or the product ρV detected by the sensor.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP3461788U JPH01145700U (en) | 1988-03-16 | 1988-03-16 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP3461788U JPH01145700U (en) | 1988-03-16 | 1988-03-16 |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH01145700U true JPH01145700U (en) | 1989-10-06 |
Family
ID=31261317
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP3461788U Pending JPH01145700U (en) | 1988-03-16 | 1988-03-16 |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH01145700U (en) |
-
1988
- 1988-03-16 JP JP3461788U patent/JPH01145700U/ja active Pending
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