JPS63180598A - Take-off flare out control system - Google Patents
Take-off flare out control systemInfo
- Publication number
- JPS63180598A JPS63180598A JP1270587A JP1270587A JPS63180598A JP S63180598 A JPS63180598 A JP S63180598A JP 1270587 A JP1270587 A JP 1270587A JP 1270587 A JP1270587 A JP 1270587A JP S63180598 A JPS63180598 A JP S63180598A
- Authority
- JP
- Japan
- Prior art keywords
- control
- flaps
- takeoff
- signal
- take
- 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
- 230000000694 effects Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Landscapes
- Earth Drilling (AREA)
- Cyclones (AREA)
- Gas Separation By Absorption (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
［産業上の利用分野］
本発明は航空機の離陸において、離陸引起しを容易にし
、強いては離陸を容易にすることができる縦コントロー
ル舵面とフラップの連動制御による離陸引起し制御方式
に関する。[Detailed Description of the Invention] [Industrial Application Field] The present invention provides a take-off system using interlocking control of longitudinal control surfaces and flaps that can facilitate take-off triggering and even facilitate take-off. Regarding a raising control method.
［従来の技術］
従来の航空機の離陸においては、フラップは一定位置に
固定されており、縦コントロール舵面の動きに連動して
、フラップの上げ下げを実施していなかった。[Prior Art] When a conventional aircraft takes off, the flaps are fixed at a fixed position, and the flaps are not raised or lowered in conjunction with the movement of the longitudinal control surface.
そのため、十分な離陸引起し能力を得るため、大きな縦
コントロール舵面を必要としていた。Therefore, a large longitudinal control surface was required in order to obtain sufficient take-off pulling ability.
［発明が解決しようとする問題点］
上述したように従来の航空機は、離陸において縦コント
ロール舵面とフラップを連動させた制御を行っていない
ので、十分な離陸引起し能力を得るため、大きな縦コン
トロール舵面を必要としていた。[Problems to be Solved by the Invention] As mentioned above, conventional aircraft do not control the vertical control surface and flaps in conjunction with each other during takeoff, so in order to obtain sufficient takeoff triggering ability, a large vertical It needed a control surface.
この発明は従来のものが持つ以上のような問題点を解決
するため、離陸において縦コントロール舵面とフラップ
を連動して制御することで、離陸を容易にし、縦コント
ロール舵面の大きさを最適化することを目的とする。In order to solve the above-mentioned problems of conventional devices, this invention makes takeoff easier and optimizes the size of the vertical control surface by controlling the vertical control surface and flaps in conjunction during takeoff. The purpose is to
［問題点を解決するための手段］
この発明は航空機の離陸において、縦コントロール舵面
の動きと連動して、フラップの上げ下げを制御するもの
である。[Means for Solving the Problems] The present invention controls the raising and lowering of flaps in conjunction with the movement of a longitudinal control surface during takeoff of an aircraft.
［作 用］
航空機の離陸において、引起し開始時に縦コントロール
舵面の動きと連動してフラップを」二げることで縦コン
トロール舵面の引起し能力を補い、離陸時にフラップを
下げることで、必要な揚力を得る制御を実施することで
離陸を容易にし、縦コントロール舵面の大きさを最適化
する。[Function] During takeoff of an aircraft, the flaps are lowered in conjunction with the movement of the vertical control surface at the start of hoisting to compensate for the pulling ability of the vertical control surface, and by lowering the flaps at the time of takeoff, By implementing control to obtain the necessary lift, takeoff is facilitated and the size of the longitudinal control surface is optimized.
［実施例コ
この発明の実施例を第１図により説明する。第１図にお
いて、１０はこの発明の構成要素をなすフラップ連動制
御部であり、同制御部１０により、離陸の際に、縦コン
トロール舵面とフラップを連動させた制御を行なう。即
ち、縦コントロール舵面の舵角制御信号１とフラップ舵
角制御信号２は、その両者を関係付ける制御信号３によ
り、離陸引起し時には舵コントロール舵面の動きに連動
してフラップが上がり、離陸時にはフラップが下がる制
御となっている。[Example] An example of the present invention will be explained with reference to FIG. In FIG. 1, reference numeral 10 denotes a flap interlocking control section which is a component of the present invention, and the control section 10 performs interlocking control of the longitudinal control surface and the flaps during takeoff. That is, the rudder angle control signal 1 of the longitudinal control rudder surface and the flap rudder angle control signal 2 are controlled by the control signal 3 that associates them both, and when the takeoff is triggered, the flaps are raised in conjunction with the movement of the rudder control rudder surface, and the flaps are raised during takeoff. The flaps are sometimes controlled to lower.
以上のフラップ制御により、離陸引起し時に、縦コント
ロール舵面の引起し能力を補い、離陸時にフラップを下
げることで必要な揚力を得ることができる。By controlling the flaps as described above, it is possible to supplement the lifting ability of the longitudinal control surface during takeoff and lower the flaps during takeoff to obtain the necessary lift.
また縦コントロール舵面の制御信号１は、パイロット操
舵信号４、迎角信号５、姿勢角信号６、ピッチ角速度信
号７、重心位置信号８等の一部または全部を含んだもの
よりなる。Further, the control signal 1 for the longitudinal control surface includes a part or all of a pilot steering signal 4, an angle of attack signal 5, an attitude angle signal 6, a pitch angular velocity signal 7, a center of gravity position signal 8, and the like.
［発明の効果］
以上のようにこの発明によれば、離陸引起し時、縦コン
トロール舵面の動きと連動してフラップを上げる制御を
行うことで、縦コントロール舵面の離陸引起し能力を補
い引起しを容易にし、また離陸時にはフラップを下げ、
必要な揚力を得ることで、離陸を容易にするという効果
が得られる。よって、縦コントロール舵面の大きさを最
適化できる効果がある。[Effects of the Invention] As described above, according to the present invention, by performing control to raise the flaps in conjunction with the movement of the vertical control surface during takeoff triggering, the takeoff triggering ability of the vertical control surface is supplemented. It makes it easier to pull up, and lowers the flaps during takeoff.
Obtaining the necessary lift has the effect of making takeoff easier. Therefore, there is an effect that the size of the longitudinal control control surface can be optimized.
第１図はこの発明の実施例としての制御ブロック図であ
る。
１・・・縦コントロール舵面舵角制御信号、２・・・フ
ラップ舵角制御信号、３・・・縦コントロール舵角に関
係したフラップ舵角制御信号、４・・・パイロット操舵
信号、５・・・迎角信号、６・・・姿勢角信号、７・・
・ピッチ角速度信号、８・・・重心位置信号、９・・・
フラップ位置選択信号、１０・・・フラップ連動制御部
。FIG. 1 is a control block diagram as an embodiment of the present invention. 1... Longitudinal control control surface rudder angle control signal, 2... Flap rudder angle control signal, 3... Flap rudder angle control signal related to longitudinal control rudder angle, 4... Pilot steering signal, 5...・Angle of attack signal, 6... Attitude angle signal, 7...
・Pitch angular velocity signal, 8... Center of gravity position signal, 9...
Flap position selection signal, 10...Flap interlock control section.
Claims (1)
ロール舵面の動きと連動してフラップを上げ離陸時にフ
ラップを下げるフラップ連動制御手段を有してなること
を特徴とした離陸引起し制御方式。In the takeoff control of an aircraft, a takeoff pulling control system characterized by having a flap interlocking control means that raises the flaps in conjunction with the movement of a longitudinal control surface at the start of pulling, and lowers the flaps at the time of takeoff. .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1270587A JPS63180598A (en) | 1987-01-22 | 1987-01-22 | Take-off flare out control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1270587A JPS63180598A (en) | 1987-01-22 | 1987-01-22 | Take-off flare out control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63180598A true JPS63180598A (en) | 1988-07-25 |
Family
ID=11812826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1270587A Pending JPS63180598A (en) | 1987-01-22 | 1987-01-22 | Take-off flare out control system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63180598A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS599399A (en) * | 1982-07-05 | 1984-01-18 | Mitsubishi Heavy Ind Ltd | Supporting structure of aluminum spherical tank |
| JPS61188299A (en) * | 1985-02-15 | 1986-08-21 | グラマン エアロスペース コーポレーシヨン | Automatic camber controller and control method |
| JPS61282198A (en) * | 1985-06-08 | 1986-12-12 | 内海 正文 | Usage on take-off of flap for aircraft |
-
1987
- 1987-01-22 JP JP1270587A patent/JPS63180598A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS599399A (en) * | 1982-07-05 | 1984-01-18 | Mitsubishi Heavy Ind Ltd | Supporting structure of aluminum spherical tank |
| JPS61188299A (en) * | 1985-02-15 | 1986-08-21 | グラマン エアロスペース コーポレーシヨン | Automatic camber controller and control method |
| JPS61282198A (en) * | 1985-06-08 | 1986-12-12 | 内海 正文 | Usage on take-off of flap for aircraft |
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