JPH08133189A - Wheel steering system for aircraft - Google Patents
Wheel steering system for aircraftInfo
- Publication number
- JPH08133189A JPH08133189A JP26972294A JP26972294A JPH08133189A JP H08133189 A JPH08133189 A JP H08133189A JP 26972294 A JP26972294 A JP 26972294A JP 26972294 A JP26972294 A JP 26972294A JP H08133189 A JPH08133189 A JP H08133189A
- Authority
- JP
- Japan
- Prior art keywords
- aircraft
- steering
- landing
- wheel
- ground
- 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.)
- Withdrawn
Links
Landscapes
- Steering Control In Accordance With Driving Conditions (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、地上操舵輪のほか降着
輪も方向可変とした航空機用車輪操向システムに関す
る。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft wheel steering system in which not only the ground steering wheels but also the landing wheels are variable in direction.
【０００２】[0002]
【従来の技術】図２は従来の航空機用車輪操向システム
の概略構成を示すブロック図である。従来の航空機用車
輪操向システムは、地上操舵輪のみが方向可変であり、
降着輪は全て方向固定である。従って、操向システムと
しては図２に示すように、ステアリング装置１が発する
ステアリング指令に基づいて操向装置２が作動し、地上
操舵輪３の向きを変えるものとなっている。2. Description of the Related Art FIG. 2 is a block diagram showing a schematic configuration of a conventional aircraft wheel steering system. In the conventional aircraft wheel steering system, only the ground steering wheels can change direction,
All landing wheels are fixed in direction. Therefore, as the steering system, as shown in FIG. 2, the steering device 2 operates based on the steering command issued by the steering device 1 to change the direction of the ground steering wheels 3.
【０００３】[0003]
【発明が解決しようとする課題】上記した、従来の航空
機用車輪操向システムには下記の欠点があった。 （１）降着輪が方向固定となっているため、航空機は、
横風着陸を行なう場合には風上に機首を向けて滑走路に
接近し、着陸寸前に機軸を滑走路方向に一致させる必要
がある。また、横風離陸を行なう場合には、離陸直後に
機首を滑走路方向から風上方向へ向ける必要がある。こ
のため離着陸時の操縦が難しく、横風離着陸時における
事故発生の要因となっていた。 （２）地上操舵を行なう場合、前輪等の地上操舵輪のみ
が方向可変で、降着輪は方向固定であるため、小回りが
できず、方向転換時に広い場所を必要とする。The conventional aircraft wheel steering system described above has the following drawbacks. (1) Since the landing wheels are fixed in the direction,
When making a crosswind landing, it is necessary to approach the runway with the nose facing upwind and to align the machine axis with the runway direction just before landing. In addition, when carrying out crosswind takeoff, it is necessary to direct the nose from the runway direction to the windward direction immediately after takeoff. For this reason, it was difficult to maneuver during takeoff and landing, which caused an accident during crosswind takeoff and landing. (2) When performing ground steering, only the ground steered wheels such as the front wheels can change the direction and the landing wheels have a fixed direction. Therefore, a small turn is not possible and a wide space is required when changing the direction.
【０００４】本発明の目的は、下記の航空機用車輪操向
システムを提供することにある。 (a) 横風離着陸時等における機体操縦が容易で、安全性
確保上きわめて有用な航空機用車輪操向システム。 (b) 降着輪の操向制御により、小回りが可能で、狭い場
所での方向転換が容易な航空機用車輪操向システム。An object of the present invention is to provide the following aircraft wheel steering system. (a) A wheel steering system for aircraft, which is extremely useful for ensuring safety because the aircraft can be easily maneuvered when taking off and landing in a crosswind. (b) A steering wheel control system for the landing wheel that enables a small turn and makes it easy to change direction in a narrow space.
【０００５】[0005]
【課題を解決するための手段】上記課題を解決し目的を
達成するために、本発明の航空機用車輪操向システム
は、以下の如く構成されている。 （１）本発明の航空機用車輪操向システムは、航空機の
降着輪の向きを可変操作する操向装置と、前記航空機の
離着陸時を含む飛行中においては前記降着輪が機体の進
行方向を向くように前記操向装置を制御する第１の制御
手段と、前記航空機の地上操舵中においては降着輪がス
テアリング指令に基づいて所要方向を向くように前記操
向装置を制御する第２の制御手段とから構成されてい
る。 （２）本発明の航空機用全輪操向システムは、上記
（１）に記載のシステムであって、かつ航空機が飛行中
であるか地上操舵中であるかを検知し、検知情報に応じ
て前記第１の制御手段と前記第２の制御手段とを自動的
に切換える装置を備えている。In order to solve the above problems and achieve the object, an aircraft wheel steering system of the present invention is configured as follows. (1) In the aircraft wheel steering system of the present invention, a steering device that variably operates the direction of the landing wheels of the aircraft, and the landing wheels face the traveling direction of the airframe during flight including takeoff and landing of the aircraft. And a second control means for controlling the steering device so that the landing wheels face a desired direction based on a steering command during ground steering of the aircraft. It consists of and. (2) The all-wheel steering system for an aircraft of the present invention is the system according to (1) above, detects whether the aircraft is in flight or is on the ground, and responds to the detection information. It is provided with a device for automatically switching between the first control means and the second control means.
【０００６】[0006]
【作用】上記手段（１）（２）を講じた結果、それぞれ
次のような作用が生じる。 （１）本発明の航空機用車輪操向システムにおいては、
離着陸時において降着輪を機体の進行方向へ向けること
ができる。このため、横風離着陸時に機軸を風上に向け
たままの機体姿勢で離着陸することが可能となる。した
がって、滑走路走行中において機軸と滑走路方向とを一
致させるための操作が不要となる。かくして横風離着陸
時における機体操縦が容易となり、その結果パイロット
の技量不足による事故発生を未然に防止できる。また、
地上操舵中においては、ステアリング指令に従い降着輪
が所要方向を向くので、地上操舵輪との共働により、小
回りが可能となり、狭い場所での方向転換が容易とな
る。 （２）本発明の航空機用車輪操向システムにおいては、
航空機が地上操舵状態から飛行状態へ移行すると、切換
え装置が働いて操向装置は第１の制御手段により制御さ
れる。また、航空機が飛行状態から地上操舵状態へ移行
すると、切換え装置が働いて操向装置は第２の制御手段
により制御される。つまり、切換え装置によって自動切
換えが行なわれる為、手動操作による操作ミスがなく、
安定かつ確実な制御を行なえる。As a result of taking the above measures (1) and (2), the following effects occur. (1) In the aircraft wheel steering system of the present invention,
It is possible to direct the landing wheel to the direction of flight of the aircraft during takeoff and landing. For this reason, it becomes possible to take off and land with the aircraft attitude with the axis of the aircraft facing upwind during crosswind takeoff and landing. Therefore, it is not necessary to perform an operation for matching the axle with the direction of the runway during traveling on the runway. Thus, it becomes easy to control the aircraft during crosswind takeoff and landing, and as a result, accidents due to insufficient pilot skills can be prevented. Also,
During the ground steering, the landing wheels are directed in the required direction in accordance with the steering command. Therefore, a small turn is possible in cooperation with the ground steering wheels, and the direction can be easily changed in a narrow place. (2) In the aircraft wheel steering system of the present invention,
When the aircraft shifts from the ground-steering state to the flying state, the switching device operates and the steering device is controlled by the first control means. Further, when the aircraft shifts from the flight state to the ground steering state, the switching device operates and the steering device is controlled by the second control means. In other words, since the switching device performs automatic switching, there is no operational error due to manual operation,
Stable and reliable control can be performed.
【０００７】[0007]
【実施例】図１は本発明の一実施例に係る航空機用車輪
操向システム１０の構成を示すブロック図である。図１
に示すように、フライトコンピュータ等を含む航法装置
１１からは進行方向情報Ｓ１ａおよび機体姿勢情報Ｓ１
ｂ等が発せられる。ステアリング装置１２からはステア
リング指令Ｓ２が発せられる。航法装置１１からの各情
報Ｓ１ａ、Ｓ１ｂ、およびステアリング装置１２からの
指令Ｓ２は、切換操作器１３からの切換信号Ｓ３によっ
て切換え動作する切換スイッチ１４を介して制御装置１
５へ選択的に入力する。制御装置１５は、切換スイッチ
１４を介して入力する入力信号Ｓ４と操向装置１６から
の操輪フィードバック信号Ｓ６とを受け、操向装置１６
に対して操輪指令Ｓ５を出力する。操向装置１６は、方
向可変な如く設けられた降着輪１７を操向駆動すると共
に、操輪フィードバック信号Ｓ６を制御装置１５へ与え
る。なお切換操作器１３は、地上センサ等にて航空機が
地上操舵中であることを自動検知し、検知情報に基づい
て切換信号Ｓ３を送出するものとなっている。1 is a block diagram showing the configuration of an aircraft wheel steering system 10 according to an embodiment of the present invention. FIG.
As shown in FIG. 1, the navigation device 11 including a flight computer and the like provides information on the traveling direction S1a and the attitude information S1 of the body.
b, etc. are emitted. A steering command S2 is issued from the steering device 12. The respective information S1a and S1b from the navigation device 11 and the command S2 from the steering device 12 are transmitted via the changeover switch 14 which is operated by the changeover signal S3 from the changeover operation device 13 to the control device 1
Selectively input to 5. The control device 15 receives the input signal S4 input via the changeover switch 14 and the wheel steering feedback signal S6 from the steering device 16, and receives the steering device 16
In response to this, a wheel manipulating command S5 is output. The steering device 16 steers and drives the landing wheels 17 provided so as to be variable in direction, and at the same time, provides a steering feedback signal S6 to the control device 15. The switching operator 13 automatically detects that the aircraft is on the ground by a ground sensor or the like, and sends a switching signal S3 based on the detection information.
【０００８】上記の如く構成された本実施例の装置は次
のように作動する。航空機が飛行中（離着陸時も含む）
である場合は、切換スイッチ１４は第１入力端Ｔ１側に
切換っている。従ってこの場合は、航法装置１１からの
進行方向情報Ｓ１ａ、機体姿勢情報Ｓ１ｂが切換スイッ
チ１４を介して制御装置１５へ入力信号Ｓ４として入力
する。そうすると、制御装置１５は操向装置１６からの
操輪フィードバック信号Ｓ６との比較結果に基づいて、
降着輪１７が機体進行方向を向くような操輪指令Ｓ５を
操向装置１６へ供給する。このため操向装置１６は機軸
の向きの如何に拘らず降着輪１７が機体進行方向を向く
ように操向駆動する。The apparatus of this embodiment constructed as described above operates as follows. Aircraft in flight (including during takeoff and landing)
In the case of, the changeover switch 14 is changed over to the first input terminal T1 side. Therefore, in this case, the traveling direction information S1a and the body attitude information S1b from the navigation device 11 are input as input signals S4 to the control device 15 via the changeover switch 14. Then, the control device 15, based on the comparison result with the wheel steering feedback signal S6 from the steering device 16,
The steering wheel 16 is supplied with a steering command S5 such that the landing wheels 17 face the traveling direction of the machine. Therefore, the steering device 16 steers and drives the landing wheels 17 so as to face the traveling direction of the machine body regardless of the direction of the machine shaft.
【０００９】航空機が着陸したのち地上操舵中に移行す
ると、切換操作器１３から切換信号Ｓ３が送出され、切
換スイッチ１４に与えられる。このため切換スイッチ１
４は第２入力端Ｔ２側に切換えられる。従ってこの場合
は、ステアリング装置１２からのステアリング指令Ｓ２
が切換スイッチ１４を介して制御装置１５へ入力信号Ｓ
４として入力する。そうすると、制御装置１５は上記ス
テアリング指令Ｓ２に基づいた操輪指令Ｓ５を操向装置
１６へ与える。このため操向装置１６は、降着輪１７が
ステアリング情報に基づいた所定の向きとなるように操
向駆動する。When the aircraft makes a landing and then shifts to the ground steering mode, a switching signal S3 is sent from the switching operator 13 and given to the changeover switch 14. Therefore, the changeover switch 1
4 is switched to the second input terminal T2 side. Therefore, in this case, the steering command S2 from the steering device 12
Input signal S to control device 15 via changeover switch 14.
Enter as 4. Then, the control device 15 gives a steering command S5 to the steering device 16 based on the steering command S2. Therefore, the steering device 16 steers and drives the landing wheels 17 so as to have a predetermined direction based on the steering information.
【００１０】なお切換スイッチ１４の切換え動作が、パ
イロット指令に基づいて行なわれるようにしてもよい。 （実施例のまとめ）実施例に示された航空機用車輪操向
システムの構成および作用効果をまとめると次の通りで
ある。 ［１］実施例に示された航空機用車輪操向システム１０
は、航空機の降着輪１７の向きを可変操作する操向装置
１６と、前記航空機の離着陸時を含む飛行中においては
降着輪１７が機体の進行方向を向くように操向装置１６
を制御する第１の制御手段（１１、１５）と、前記航空
機の地上操舵中においては降着輪１７がステアリング指
令Ｓ２に基づいて所要方向を向くように操向装置１６を
制御する第２の制御手段（１２、１５）とを備えてい
る。The changeover operation of the changeover switch 14 may be performed based on a pilot command. (Summary of Embodiments) The configuration and operational effects of the aircraft wheel steering system shown in the embodiments are summarized as follows. [1] Wheel steering system 10 for aircraft shown in the embodiment
The steering device 16 for variably operating the direction of the landing wheel 17 of the aircraft, and the steering device 16 for directing the landing wheel 17 in the traveling direction of the airframe during flight including takeoff and landing of the aircraft.
And a second control for controlling the steering device 16 so that the landing wheels 17 face a required direction based on the steering command S2 during the ground steering of the aircraft. And means (12, 15).
【００１１】したがって、上記航空機用車輪操向システ
ム１０においては、離着陸時において降着輪１７を機体
の進行方向へ向けることができる。このため、横風離着
陸時に機軸を風上に向けたままの機体姿勢で離着陸する
ことが可能となる。したがって、滑走路走行中において
機軸と滑走路方向とを一致させるための操作が不要とな
る。かくして横風離着陸時における機体操縦が容易とな
り、その結果パイロットの技量不足による事故発生を未
然に防止できる。また地上操舵中においては、ステアリ
ング指令Ｓ２に従い降着輪１７が所要方向を向くので、
地上操舵輪との共働により、小回りが可能となり、狭い
場所での方向転換が容易となる。 ［２］実施例に示された航空機用車輪操向システム１０
は、上記［１］に記載のシステムであって、かつ航空機
が飛行中であるか地上操舵中であるかを検知し、検知情
報に応じて前記第１の制御手段（１１、１５）と前記第
２の制御手段（１２、１５）とを自動的に切換える切換
え装置（１３、１４）を備えている。Therefore, in the above-described aircraft wheel steering system 10, the landing wheels 17 can be oriented in the traveling direction of the airframe during takeoff and landing. For this reason, it becomes possible to take off and land with the aircraft attitude with the axis of the aircraft facing upwind during crosswind takeoff and landing. Therefore, it is not necessary to perform an operation for matching the axle with the direction of the runway during traveling on the runway. Thus, it becomes easy to control the aircraft during crosswind takeoff and landing, and as a result, accidents due to insufficient pilot skills can be prevented. Further, since the landing wheel 17 faces the required direction in accordance with the steering command S2 during the ground steering,
By cooperating with the ground steering wheel, a small turn is possible and it becomes easy to change the direction in a narrow space. [2] Wheel steering system 10 for aircraft shown in the embodiment
Is the system according to the above [1], and detects whether the aircraft is in flight or on the ground, and according to the detection information, the first control means (11, 15) and the A switching device (13, 14) for automatically switching between the second control means (12, 15) is provided.
【００１２】したがって上記航空機用車輪操向システム
１０においては、航空機が地上操舵状態から飛行状態へ
移行すると、切換え装置（１３、１４）が働いて操向装
置１６は第１の制御手段（１１、１５）により制御され
る。また、航空機が飛行状態から地上操舵状態へ移行す
ると、切換え装置（１３、１４）が働いて操向装置１６
は第２の制御手段（１２、１５）により制御される。つ
まり切換え装置（１３、１４）によって自動切換えが行
なわれる為、手動操作による操作ミスがなく、安定かつ
確実な制御を行なえる。Therefore, in the above-described aircraft wheel steering system 10, when the aircraft shifts from the ground steering state to the flight state, the switching devices (13, 14) operate and the steering device 16 causes the first control means (11, 15). Further, when the aircraft shifts from the flight state to the ground steering state, the switching devices (13, 14) operate to operate the steering device 16
Are controlled by the second control means (12, 15). In other words, since automatic switching is performed by the switching device (13, 14), stable and reliable control can be performed without an operation error due to manual operation.
【００１３】[0013]
【発明の効果】本発明によれば、下記のシステムを提供
できる。 (a) 横風離着陸時等における機体操縦が容易で、安全性
確保上きわめて有用な航空機用車輪操向システム。 (b) 降着輪の操向制御により、小回りが可能で、狭い場
所での方向転換が容易な航空機用車輪操向システム。According to the present invention, the following system can be provided. (a) A wheel steering system for aircraft, which is extremely useful for ensuring safety because the aircraft can be easily maneuvered when taking off and landing in a crosswind. (b) A steering wheel control system for the landing wheel that enables a small turn and makes it easy to change direction in a narrow space.
【図１】本発明の一実施例に係る航空機用車輪操向シス
テムの構成を示すブロック図。FIG. 1 is a block diagram showing the configuration of an aircraft wheel steering system according to an embodiment of the present invention.
【図２】従来例における航空機用車輪操向システムの構
成を示すブロック図。FIG. 2 is a block diagram showing a configuration of a conventional aircraft wheel steering system.
１…ステアリング装置 ２…操向装置 ３…地上操舵輪 １０…航空機用車輪
操向システム １１…航法装置 １２…ステアリン
グ装置 １３…切換操作器 １４…切換スイッ
チ １５…制御装置 １６…操向装置 １７…降着輪 Ｔ１…第１入力端 Ｔ２…第２入力端 Ｓ１ａ…進行方向情
報 Ｓ１ｂ…機体姿勢情報 Ｓ２…ステアリ
ング指令 Ｓ３…切換信号 Ｓ４…入力信号 Ｓ５…操輪指令 Ｓ６…操輪フィー
ドバック信号DESCRIPTION OF SYMBOLS 1 ... Steering device 2 ... Steering device 3 ... Ground steering wheel 10 ... Aircraft wheel steering system 11 ... Navigation device 12 ... Steering device 13 ... Changeover operation device 14 ... Changeover switch 15 ... Control device 16 ... Steering device 17 ... Landing wheel T1 ... First input end T2 ... Second input end S1a ... Traveling direction information S1b ... Aircraft attitude information S2 ... Steering command S3 ... Switching signal S4 ... Input signal S5 ... Wheel steering command S6 ... Wheel steering feedback signal
Claims (2)
装置と、 前記航空機の離着陸時を含む飛行中においては前記降着
輪が機体の進行方向を向くように前記操向装置を制御す
る第１の制御手段と、 前記航空機の地上操舵中においては降着輪がステアリン
グ指令に基づいて所要方向を向くように前記操向装置を
制御する第２の制御手段と、 を備えたことを特徴とする航空機用車輪操向システム。1. A steering device for variably operating the direction of a landing wheel of an aircraft, and controlling the steering device such that the landing wheel faces the traveling direction of the airframe during flight including takeoff and landing of the aircraft. A first control means, and a second control means for controlling the steering device so that the landing wheels face a required direction based on a steering command during the ground steering of the aircraft. Wheel steering system for aircraft.
かを検知し、検知情報に応じて第１の制御手段と第２の
制御手段とを自動的に切換える装置を備えていることを
特徴とする請求項１に記載の航空機用車輪操向システ
ム。2. A device for detecting whether the aircraft is in flight or on the ground and automatically switching between the first control means and the second control means according to the detection information. The wheel steering system for an aircraft according to claim 1, wherein:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26972294A JPH08133189A (en) | 1994-11-02 | 1994-11-02 | Wheel steering system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26972294A JPH08133189A (en) | 1994-11-02 | 1994-11-02 | Wheel steering system for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH08133189A true JPH08133189A (en) | 1996-05-28 |
Family
ID=17476259
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP26972294A Withdrawn JPH08133189A (en) | 1994-11-02 | 1994-11-02 | Wheel steering system for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH08133189A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6671588B2 (en) | 2001-12-27 | 2003-12-30 | Toyota Jidosha Kabushiki Kaisha | System and method for controlling traveling direction of aircraft |
| JP2009298290A (en) * | 2008-06-13 | 2009-12-24 | National Institute Of Advanced Industrial & Technology | Drift flight stabilization flight machine |
| WO2010150760A1 (en) | 2009-06-22 | 2010-12-29 | 三菱重工業株式会社 | Steering angle control system for aircraft |
| WO2012137578A1 (en) | 2011-04-02 | 2012-10-11 | 住友精密工業株式会社 | Landing gear of flight vehicle |
| JP6256898B1 (en) * | 2017-07-25 | 2018-01-10 | 竹中 正次 | Crosswind landing safety device |
| WO2018051474A1 (en) * | 2016-09-15 | 2018-03-22 | 住友精密工業株式会社 | Aircraft steering control apparatus |
-
1994
- 1994-11-02 JP JP26972294A patent/JPH08133189A/en not_active Withdrawn
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6671588B2 (en) | 2001-12-27 | 2003-12-30 | Toyota Jidosha Kabushiki Kaisha | System and method for controlling traveling direction of aircraft |
| JP2009298290A (en) * | 2008-06-13 | 2009-12-24 | National Institute Of Advanced Industrial & Technology | Drift flight stabilization flight machine |
| WO2010150760A1 (en) | 2009-06-22 | 2010-12-29 | 三菱重工業株式会社 | Steering angle control system for aircraft |
| JP2011001023A (en) * | 2009-06-22 | 2011-01-06 | Japan Aerospace Exploration Agency | Steering angle control system for aircraft |
| CN102803069A (en) * | 2009-06-22 | 2012-11-28 | 三菱重工业株式会社 | Steering Angle Control System For Aircraft |
| US8874285B2 (en) | 2009-06-22 | 2014-10-28 | Mitsubishi Heavy Industries, Ltd. | Steering angle control system for aircraft |
| WO2012137578A1 (en) | 2011-04-02 | 2012-10-11 | 住友精密工業株式会社 | Landing gear of flight vehicle |
| US8894005B2 (en) | 2011-04-02 | 2014-11-25 | Sumitomo Precision Products Co., Ltd. | Landing gear assembly of aircraft |
| WO2018051474A1 (en) * | 2016-09-15 | 2018-03-22 | 住友精密工業株式会社 | Aircraft steering control apparatus |
| JP6256898B1 (en) * | 2017-07-25 | 2018-01-10 | 竹中 正次 | Crosswind landing safety device |
| JP2019025923A (en) * | 2017-07-25 | 2019-02-21 | 竹中 正次 | Cross-wind landing safety device |
| US10640201B2 (en) | 2017-07-25 | 2020-05-05 | Norikazu TAKENAKA | Safety device for landing in crosswind |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 20020115 |