JPH01254496A - Seat device - Google Patents
Seat deviceInfo
- Publication number
- JPH01254496A JPH01254496A JP63082262A JP8226288A JPH01254496A JP H01254496 A JPH01254496 A JP H01254496A JP 63082262 A JP63082262 A JP 63082262A JP 8226288 A JP8226288 A JP 8226288A JP H01254496 A JPH01254496 A JP H01254496A
- Authority
- JP
- Japan
- Prior art keywords
- head
- pilot
- signal
- aircraft
- head part
- 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
- 230000001133 acceleration Effects 0.000 abstract description 7
- 239000012530 fluid Substances 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 3
- 230000006378 damage Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 210000002303 tibia Anatomy 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/02—Supports or holding means for living bodies
- B64D25/04—Seat modifications
-
- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/10—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer with simulated flight- or engine-generated force being applied to aircraft occupant
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Theoretical Computer Science (AREA)
- Business, Economics & Management (AREA)
- Physics & Mathematics (AREA)
- Educational Administration (AREA)
- Educational Technology (AREA)
- General Physics & Mathematics (AREA)
- Emergency Management (AREA)
- Seats For Vehicles (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、例えば航空機などの座席装置の構造に１する
。DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention is applied to the structure of a seat device for an aircraft, for example.
第４図は従来の航空機で使用されている射出用座席装置
の側面図である。図に於いて、操縦者１０頭部を保護す
るヘッドレスト３け座席本体２に固定されている。操縦
者１は航空機を操縦するとき通常は前方に位置する計器
や外界の状況を確認する几めに頭部をヘッドレスト３か
ら離して前傾姿勢をとっている。FIG. 4 is a side view of an ejection seat device used in a conventional aircraft. In the figure, three headrests are fixed to the seat body 2 to protect the head of an operator 10. When piloting an aircraft, the pilot 1 usually leans forward with his head away from the headrest 3 in order to check the instruments located in front of him and the situation in the outside world.
上記のような従来の座席装置に於いて、航空機の機動或
いは気流の擾乱などによシ操縦者ＩＫ加速度が負荷され
ると支えのない頭部は保持が困難で、特に照準操作など
精密な戦闘機動を要する場合に誤差が生じ易く、また頭
部の振れによる頚骨損傷、風防ガラスなどとの衝突によ
る゛負傷が考えられる。In conventional seat systems such as those mentioned above, it is difficult to hold the unsupported head when the pilot's IK acceleration is applied due to aircraft maneuvers or airflow disturbances, especially during precision combat operations such as aiming operations. Errors are likely to occur when maneuver is required, and injuries may occur due to tibia damage due to head shaking or collision with windshields, etc.
これを防止するためにヘッドレスト３を前方に突き出し
た構造にすることも考えられるが、通常の状況下に於い
てはヘッドレスト３が頭部の直後にあると操縦者１０頭
部の可動範囲を狭隘にすることは否めず、特に緊急時に
座席本体２に設置された脱出用推進機構１０により脱出
を図る場合に推進力線１０′と背骨が平行になっていな
いと背骨や頚骨を損傷する恐れが大きいなどの問題を抱
えている。In order to prevent this, it is possible to make the headrest 3 protrude forward, but under normal circumstances, if the headrest 3 is located directly behind the head, the range of motion of the operator's 10 head will be narrowed. Especially in case of an emergency, when trying to escape using the evacuation propulsion mechanism 10 installed in the seat body 2, if the line of propulsive force 10' and the spine are not parallel, there is a risk of damaging the spine and tibia. There are problems such as large size.
本発明に係る座席装置は上記の課題を解決し安全性の高
い座席構造を得ることを目的にしており、操縦者の頭部
の位置を検出するセンサを有する頭部位置検出器と、該
頭部位置検出器からの信号に基づきアクチュエータによ
シ座席本体から上記操縦者の頭部に向けて進退可能に設
けられたヘッドレストとを備えてなる構成を特徴として
いる。The seat device according to the present invention aims to solve the above-mentioned problems and obtain a highly safe seat structure, and includes a head position detector having a sensor for detecting the position of the operator's head, and The present invention is characterized by a structure including a headrest that is provided so as to be movable forward and backward from the seat body toward the operator's head using an actuator based on a signal from a position detector.
即ち、本発明に係る座席装置に於いては頭部位置検出装
置によりアクチュエータと連動して前後に移動するヘッ
ドレストが設けられており、常に操縦者の頭部の直後に
ヘッドレストを位置させることができ、これｋより航空
機の機動などにより操縦者に加速度が負荷されたとき操
縦者の頭部が容易に保護され得る。That is, the seat device according to the present invention is provided with a headrest that moves back and forth in conjunction with an actuator using a head position detection device, so that the headrest can always be positioned immediately behind the operator's head. , this allows the pilot's head to be easily protected when acceleration is applied to the pilot due to aircraft maneuvering or the like.
本発明の実施例を第１図乃至第３図に基づき説明する。 Embodiments of the present invention will be described based on FIGS. 1 to 3.
なお、図中第４図に於ける部材と共通の部材には第４図
に於ける符号と共通の符号を付して説明を省略する。第
１図および第２図は本発明の一実施例に係る座席装置の
側面図である。図に於いて、本実施例に係る座席装置は
第１図に示すように座席本体２に前後に移動可能なヘッ
ドレスト３が設置され、このヘッドレスト３に例えば光
センサ、磁気センサなどの距離測定センサによる頭部位
置検出器４が取り付けられておシ、ヘッドレスト３の後
方にはヘッドレスト３を前後に移動させるアクチュエー
タ５が連接されている。航空機の機動によシ加速度が生
じると、第２図に示すように別に設けた加速度センサ６
からの信号が信号制御器７１Ｃ出力される。すると、信
号制御器７は頭部位置検出器４によって得られ次操縦者
１とヘッドレスト３との距離に応じた出力信号を制御バ
ルブ８に出力し、作動源１５からアクチュエータ５に作
動流体が適宜給排されてヘッドレスト３が前後に移動し
、操縦者１の頭部の直後にヘッドレスト３が位置してこ
の関係が保持される。１６は電源である。加速度センサ
６からの出力がなくなるか或いは一定値以下になった場
合にはヘッドレスト３が後退する。また、緊急の脱出時
には図示しない脱出用システムからの指令信号９により
ヘッドレスト３を後退させるとともに１脱出用推進機構
１０によって座席本体２を射出させる。In the figure, members common to those in FIG. 4 are given the same reference numerals as those in FIG. 4, and explanations thereof will be omitted. 1 and 2 are side views of a seat device according to an embodiment of the present invention. In the figure, the seat device according to the present embodiment has a headrest 3 that is movable back and forth on the seat body 2, as shown in FIG. A head position detector 4 is attached, and an actuator 5 for moving the headrest 3 back and forth is connected to the rear of the headrest 3. When acceleration occurs due to aircraft maneuvering, an acceleration sensor 6 installed separately as shown in FIG.
A signal from the signal controller 71C is output. Then, the signal controller 7 outputs an output signal obtained by the head position detector 4 and corresponding to the distance between the next pilot 1 and the headrest 3 to the control valve 8, and the actuating fluid is appropriately supplied from the actuating source 15 to the actuator 5. The headrest 3 moves back and forth as it is fed and removed, and the headrest 3 is positioned immediately behind the head of the operator 1, and this relationship is maintained. 16 is a power source. When the output from the acceleration sensor 6 disappears or becomes less than a certain value, the headrest 3 moves backward. In addition, in the event of an emergency escape, the headrest 3 is moved backward by a command signal 9 from an escape system (not shown), and the seat body 2 is ejected by the escape propulsion mechanism 10.
なお、このようなシステムの融通性を大幅に向上させる
ために頭部位置検出器４は頭部が一定距離以上離れた場
合、即ち最大距離計測／制御範囲を外れた場合は一旦ヘ
ッドレスト３を後退させるか或いはその位置を保持させ
、制御範囲に入ったら再び制御を開始する機能を信号制
御器７にもたせる。または、第３図に示すように頭部位
置検出器４は操縦者１０頭部およびヘッドレスト３にそ
れぞれ送信器１１、受信器１２を設けてこれにより送受
信を行わせ、頭部が送受信視野外になつ念場合は信号制
御器７によシヘッドレスト３の後退或いはその位置を保
持させ、視野内に入ったら再制御を開始するようにして
制御の確実性を期す。または、ヘッドレスト３に例えば
頭部圧によりＰＵＳＨ−ＯＮおよびＰＵＳＨ−ＯＦＦを
繰シ返す型式のロータリスイッチなどの圧力センサ１３
を併用し、頭部位置検出器４による信号をオーバライド
してヘッドレスト３を頭部圧により移動可能にする。ま
たは、このシステムに切換スイッチ１４を設置し、
。Furthermore, in order to greatly improve the flexibility of such a system, the head position detector 4 temporarily moves the headrest 3 back when the head moves beyond a certain distance, that is, when it is out of the maximum distance measurement/control range. The signal controller 7 is provided with a function to control the signal or to hold the position, and to start control again when it enters the control range. Alternatively, as shown in FIG. 3, the head position detector 4 can transmit and receive signals by providing a transmitter 11 and a receiver 12 on the head of the pilot 10 and the headrest 3, respectively, so that the head is out of the field of view for transmitting and receiving. In case of emergency, the signal controller 7 causes the headrest 3 to move backward or maintain its position, and once the headrest 3 comes within the field of view, the control is restarted to ensure the reliability of the control. Alternatively, a pressure sensor 13 such as a rotary switch of the type that repeatedly turns PUSH-ON and PUSH-OFF depending on the head pressure on the headrest 3 may be used.
is used in combination, the signal from the head position detector 4 is overridden, and the headrest 3 is made movable by head pressure. Alternatively, a changeover switch 14 is installed in this system,
.
この切換スイッチ１４に例えば自動、手動、後退の３ポ
ジシヨンを設けて自動は頭部位置検出器４或いは送受信
器１１．１２による自動制御モード、手動は頭部圧セン
サ１３による手動モード、後退は後退位置に於ける固定
モードなどとし、運用の拡張性を図ることも可能である
。For example, the changeover switch 14 is provided with three positions: automatic, manual, and backward, and automatic is an automatic control mode using the head position detector 4 or transmitter/receiver 11.12, manual is a manual mode using the head pressure sensor 13, and backward is a backward mode. It is also possible to expand the operation by using a fixed mode at a certain location.
本発明に係る座席装置は前記の通シ構成されているので
ヘッドレストを常に操縦者の頭部の直後に位置させるこ
とができ、操縦者の頭部の保持が容易で安全性が向上す
るとともに、航空機の機動中に正確な照単操作が可能で
航空機の運用が格段に向上するなどの効果が奏せられる
。Since the seat device according to the present invention has the above-mentioned through-hole configuration, the headrest can always be positioned immediately behind the operator's head, making it easy to hold the operator's head and improving safety. It is possible to perform precise aiming operations while the aircraft is maneuvering, which has the effect of significantly improving aircraft operation.
第１図は本発明の一実施例に係る座席装置の側面図、第
２図はそのブロック図、第３図は本発明の他の実施例に
保る座席装置の一部を示す側面図、第４図は従来の座席
装置の側面図である。
１・・・操縦者、′２・・・座席本体、３・・・ヘッド
レスト、４・・・頭部位置検出器、５・・・アクチュエ
ータ、７・・・信号制御器、８・・・制御バルブ、１１
・・・頭部位置検出送信器、１２・・・頭部位置検出器
信器、１３・・・圧力センサ、１４・・・切換スイッチ
、１５・・・作動源、１６・・・電源。
代理人 弁理士 坂 間 暁 （外２名）、 差１
図FIG. 1 is a side view of a seat device according to an embodiment of the present invention, FIG. 2 is a block diagram thereof, and FIG. 3 is a side view showing a part of a seat device according to another embodiment of the present invention. FIG. 4 is a side view of a conventional seat device. DESCRIPTION OF SYMBOLS 1... Pilot, '2... Seat body, 3... Headrest, 4... Head position detector, 5... Actuator, 7... Signal controller, 8... Control valve, 11
... Head position detection transmitter, 12 ... Head position detector signal, 13 ... Pressure sensor, 14 ... Changeover switch, 15 ... Operation source, 16 ... Power supply. Agent: Patent attorney Akira Sakama (2 others), difference: 1
figure
Claims (1)
検出器と、該頭部位置検出器からの信号に基づきアクチ
ュエータにより座席本体から上記操縦者の頭部に向けて
進退可能に設けられたヘツドレストとを備えてなること
を特徴とする座席装置。A head position detector having a sensor for detecting the position of the operator's head; and an actuator capable of moving forward and backward from the seat body toward the operator's head based on a signal from the head position detector. A seat device comprising: a head rest;
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63082262A JPH01254496A (en) | 1988-04-05 | 1988-04-05 | Seat device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63082262A JPH01254496A (en) | 1988-04-05 | 1988-04-05 | Seat device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH01254496A true JPH01254496A (en) | 1989-10-11 |
Family
ID=13769551
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63082262A Pending JPH01254496A (en) | 1988-04-05 | 1988-04-05 | Seat device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01254496A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5252070A (en) * | 1990-07-10 | 1993-10-12 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Helmet loader for flight simulation |
| JP2006160152A (en) * | 2004-12-09 | 2006-06-22 | Toyota Boshoku Corp | Headrest control device |
| JP2006182276A (en) * | 2004-12-28 | 2006-07-13 | Toyota Boshoku Corp | Headrest control device |
| WO2007069289A1 (en) * | 2005-12-12 | 2007-06-21 | Aisin Seiki Kabushiki Kaisha | Vehicle seat |
| US7963598B2 (en) | 2004-12-09 | 2011-06-21 | Toyota Boshoku Kabushiki Kaisha | Head rest control systems |
| GB2538010A (en) * | 2010-07-30 | 2016-11-02 | Martin-Baker Aircraft Co Ltd | A headrest assembly |
-
1988
- 1988-04-05 JP JP63082262A patent/JPH01254496A/en active Pending
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5252070A (en) * | 1990-07-10 | 1993-10-12 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Helmet loader for flight simulation |
| JP2006160152A (en) * | 2004-12-09 | 2006-06-22 | Toyota Boshoku Corp | Headrest control device |
| US7963598B2 (en) | 2004-12-09 | 2011-06-21 | Toyota Boshoku Kabushiki Kaisha | Head rest control systems |
| JP2006182276A (en) * | 2004-12-28 | 2006-07-13 | Toyota Boshoku Corp | Headrest control device |
| JP4675621B2 (en) * | 2004-12-28 | 2011-04-27 | トヨタ紡織株式会社 | Headrest control device |
| WO2007069289A1 (en) * | 2005-12-12 | 2007-06-21 | Aisin Seiki Kabushiki Kaisha | Vehicle seat |
| JPWO2007069289A1 (en) * | 2005-12-12 | 2009-05-21 | アイシン精機株式会社 | Vehicle seat |
| US7866745B2 (en) | 2005-12-12 | 2011-01-11 | Aisin Seiki Kabushiki Kaisha | Vehicle seat |
| GB2538010A (en) * | 2010-07-30 | 2016-11-02 | Martin-Baker Aircraft Co Ltd | A headrest assembly |
| GB2538010B (en) * | 2010-07-30 | 2018-03-21 | Martin Baker Aircraft Co Ltd | A headrest assembly |
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