JPS6050636B2 - human piloted aircraft - Google Patents
human piloted aircraftInfo
- Publication number
- JPS6050636B2 JPS6050636B2 JP17228681A JP17228681A JPS6050636B2 JP S6050636 B2 JPS6050636 B2 JP S6050636B2 JP 17228681 A JP17228681 A JP 17228681A JP 17228681 A JP17228681 A JP 17228681A JP S6050636 B2 JPS6050636 B2 JP S6050636B2
- Authority
- JP
- Japan
- Prior art keywords
- human
- yaw damper
- rudder
- aircraft
- operated
- 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
- 238000010586 diagram Methods 0.000 description 4
- 238000013016 damping Methods 0.000 description 1
Landscapes
- Mechanical Control Devices (AREA)
- Radio Relay Systems (AREA)
- Details Of Aerials (AREA)
Description
【発明の詳細な説明】
本発明は人力操縦航空機に関し、特にヨーダンパシステ
ム（ＹａｗＤａｍｐｅｒＳｙｓｔｅｍ）を改良した人力
操縦航空機に係る。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to human-piloted aircraft, and more particularly to a human-piloted aircraft having an improved Yaw Damper System.
従来、人力操縦航空機のヨーダンパは方向舵によって行
つていた。Traditionally, yaw damping in human-piloted aircraft has been performed using the rudder.
すなわち、第１図に示す如く、尾翼１後方の方向舵２の
駆動部として人力操縦系統のリール３を方向舵２の軸４
に設けている。また、図示しないヨーダンパコンピユー
タから指令されたヨーダンパアクチユエータ５によつて
駆動するヨーダンパ系統のリール６、７のうちの一方の
リール７を前記軸４に設けている。つまり、方向舵２の
軸４にリール３及びリール７の両者を設けた状態て方向
舵２を操舵している。この結果、離看陸後の片発停止時
のように方向舵２を大きく操作する必要がある時に、ヨ
ーダンパ系統の操舵力が人力操縦系統の操舵力と逆向き
であるような場合、パイロットはヨーダンパ系統の操舵
力に打勝つて操舵しなければならず、特に大きな操舵力
が必要てある。また、こうした人力操縦航空機では地上
走行時の方向操縦力に及ぼすヨーダンパ系統の操舵力の
影響を避けるために、地上走行時にヨーダンパ系統を切
断する機種が多いのが現状である。本発明は上記事情に
鑑みてなされたものであり、地上走行時を含み常時ヨー
ダンパ系統を作動し得るとともに、片発停止時等の方向
舵操舵力を軽減し得る人力操縦航空機を提供しようとす
るものである。That is, as shown in FIG.
It is set up in Further, one reel 7 of the reels 6 and 7 of the yaw damper system is provided on the shaft 4, which is driven by a yaw damper actuator 5 commanded from a yaw damper computer (not shown). That is, the rudder 2 is steered with both the reel 3 and the reel 7 provided on the shaft 4 of the rudder 2. As a result, when it is necessary to operate the rudder 2 significantly, such as during a one-engine stop after takeoff, if the steering force of the yaw damper system is in the opposite direction to the steering force of the human-powered control system, the pilot must use the yaw damper. It is necessary to overcome the steering force of the system, and a particularly large steering force is required. Furthermore, in order to avoid the influence of the steering force of the yaw damper system on the directional control force during taxiing, many of these human-operated aircraft models currently disconnect the yaw damper system during taxiing. The present invention has been made in view of the above circumstances, and it is an object of the present invention to provide a human-powered aircraft that can operate a yaw damper system at all times, including when taxiing, and can reduce rudder steering force when one engine is stopped. It is.
以下本発明の一実施例を第２図を参照して説明する。An embodiment of the present invention will be described below with reference to FIG.
図中１１は機体であり、この機体１１の後部上部には尾
翼１２が設けられている。In the figure, 11 is a fuselage, and a tail 12 is provided at the upper rear part of the fuselage 11.
更に尾翼１２後部には方向舵１３及びその上部にヨーダ
ンパ専用舵面１４が夫々独立して設けられている。ここ
で、方向舵１３は図示しない操縦ペダルの操作のみによ
り操縦され、またヨーダンパ専用舵面１４は図示しない
ヨーダンパコンピユータから指令されたヨーダンパアク
チユエータのみにより動作する。上述した構成によれば
、ヨーダンパ専用舵面１４は操縦ペダルの操作とは独立
してヨーダンパコンピユータの指令でのみ動作するので
、地上走行時を含み常時ヨーダンパ専用舵面１４を作動
することができる。Furthermore, a rudder 13 and a control surface 14 dedicated to a yaw damper are independently provided at the rear of the tail fin 12 and above the rudder 13, respectively. Here, the rudder 13 is operated only by operating a control pedal (not shown), and the yaw damper dedicated control surface 14 is operated only by a yaw damper actuator commanded from a yaw damper computer (not shown). According to the above-described configuration, the yaw damper-dedicated control surface 14 operates only by commands from the yaw damper computer independently of the operation of the control pedal, so the yaw damper-dedicated control surface 14 can be operated at all times, including when traveling on the ground.
またヨーダンパ系統の操舵力の影響を受けないので操縦
ペダルの操作により方向舵を操舵する場合、従来のよう
にヨーダンパ系統の・操舵力に打勝つて操舵する必要が
なく、人力による操舵力を軽減てきる。なお、本発明の
人力操縦航空機は第２図に示した構造に限らず、第３図
に示す如く機体１１後部下部にヨーダンパ専用舵面１４
″を設け、尾翼１２後部に人力のみにより操縦される方
向舵１３を設けた構造にしてもよい。In addition, since it is not affected by the steering force of the yaw damper system, when steering the rudder by operating the control pedal, there is no need to overcome the steering force of the yaw damper system as in the past, reducing the manual steering force. Ru. Note that the human-powered aircraft of the present invention is not limited to the structure shown in FIG. 2, and as shown in FIG.
'', and a rudder 13 that is operated only by human power may be provided at the rear of the tail fin 12.
以上詳述した如く本発明によれば常時ヨーダンパ系統を
作動し得るとともに、方向舵操舵力を軽減し得る人力操
縦航空機を提供できるものである。As described in detail above, according to the present invention, it is possible to provide a human-powered aircraft that can operate the yaw damper system at all times and can reduce the rudder steering force.
第１図は従来の人力操縦航空機の方向舵の操縦系統を示
す説明図、第２図は本発明の一実施例における人力操縦
航空機を示す概略図、第３図は本発明の他の実施例にお
ける人力操縦航空機を示す概略図である。
１１・・・・・・機体、１２・・・・・・尾翼、１３・
・・・・・方向舵、１４，１４″・・・・ヨーダンパ専
用舵面。FIG. 1 is an explanatory diagram showing the rudder control system of a conventional human-powered aircraft, FIG. 2 is a schematic diagram showing a human-powered aircraft according to an embodiment of the present invention, and FIG. 3 is a schematic diagram showing a human-powered aircraft according to another embodiment of the present invention. 1 is a schematic diagram showing a human-powered aircraft; FIG. 11... Airframe, 12... Tail, 13.
...Rudder, 14,14''...Control surface exclusively for yaw damper.
Claims (1)
御により動作するヨーダンパ専用舵面を夫々独立して設
けたことを特徴とする人力操縦航空機。1. A human-operated aircraft characterized by independently providing a rudder operated by human power and a dedicated control surface for a yaw damper operated by automatic control at the rear of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17228681A JPS6050636B2 (en) | 1981-10-28 | 1981-10-28 | human piloted aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17228681A JPS6050636B2 (en) | 1981-10-28 | 1981-10-28 | human piloted aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5873498A JPS5873498A (en) | 1983-05-02 |
| JPS6050636B2 true JPS6050636B2 (en) | 1985-11-09 |
Family
ID=15939107
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17228681A Expired JPS6050636B2 (en) | 1981-10-28 | 1981-10-28 | human piloted aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6050636B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102018215294A1 (en) | 2017-09-08 | 2019-03-14 | Mitutoyo Corporation | Method for controlling a shape measuring device |
| DE102018215286A1 (en) | 2017-09-08 | 2019-03-14 | Mitutoyo Corporation | Method for controlling a shape measuring device |
| DE102018215283A1 (en) | 2017-09-08 | 2019-03-14 | Mitutoyo Corporation | Method for controlling a shape measuring device |
-
1981
- 1981-10-28 JP JP17228681A patent/JPS6050636B2/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102018215294A1 (en) | 2017-09-08 | 2019-03-14 | Mitutoyo Corporation | Method for controlling a shape measuring device |
| DE102018215286A1 (en) | 2017-09-08 | 2019-03-14 | Mitutoyo Corporation | Method for controlling a shape measuring device |
| DE102018215283A1 (en) | 2017-09-08 | 2019-03-14 | Mitutoyo Corporation | Method for controlling a shape measuring device |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5873498A (en) | 1983-05-02 |
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