JP2855837B2 - Aircraft pilot's device for preventing spatial dysfunction - Google Patents
Aircraft pilot's device for preventing spatial dysfunctionInfo
- Publication number
- JP2855837B2 JP2855837B2 JP26152190A JP26152190A JP2855837B2 JP 2855837 B2 JP2855837 B2 JP 2855837B2 JP 26152190 A JP26152190 A JP 26152190A JP 26152190 A JP26152190 A JP 26152190A JP 2855837 B2 JP2855837 B2 JP 2855837B2
- Authority
- JP
- Japan
- Prior art keywords
- bladder
- pressing
- aircraft
- pilot
- attitude
- 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 - Fee Related
Links
Landscapes
- Regulating Braking Force (AREA)
- Measurement Of The Respiration, Hearing Ability, Form, And Blood Characteristics Of Living Organisms (AREA)
Description
【発明の詳細な説明】 （産業上の利用分野） 本発明は、航空機パイロットが空間識失調状態に陥る
のを防止する装置に関する。Description: TECHNICAL FIELD The present invention relates to an apparatus for preventing an aircraft pilot from falling into a state of spatial dysfunction.
（従来の技術） 従来、航空機パイロットによる機体姿勢の認識は、計
器、太陽、地平線等によってパイロットに与えられる視
覚情報に基づくものであった。(Prior Art) Conventionally, the recognition of the aircraft attitude by an aircraft pilot has been based on visual information given to the pilot by an instrument, the sun, the horizon, or the like.
（発明が解決しようとする課題） 例えば、雲の中を飛行するような場合には、パイロッ
トは太陽や地平線等によっては航空機姿勢を認識できな
いため、空間識失調状態に陥ることがある。このような
空間識失調状態においては、パイロットは錯乱状態にな
って心理的に計器からの視覚情報を信用できなくなり、
計器からの視覚情報がパイロットの錯乱状態を一層助長
させ、墜落事故につながる場合もある。(Problems to be Solved by the Invention) For example, when flying in the clouds, the pilot cannot recognize the attitude of the aircraft due to the sun, the horizon, or the like, so that the pilot may fall into a state of spatial sensation. In such a state of spatial insufficiency, the pilot becomes confused and cannot psychologically trust the visual information from the instrument,
Visual information from the instrument can further aggravate the pilot's confusion and lead to a crash.
（課題を解決するための手段） 本発明は、航空機の姿勢をパイロットに体感情報とし
て与えることで、空間識失調状態に陥るのを防止する装
置を提供することを目的とする。(Means for Solving the Problems) It is an object of the present invention to provide a device for preventing a pilot from falling into a state of spatial inconsistency by giving an attitude of an aircraft to a pilot as bodily sensation information.
本発明の特徴とするところは、航空機の操縦席に着座
したパイロットを複数位置から押圧する押圧手段と、こ
の押圧手段による各押圧位置での押圧量検知手段と、航
空機の姿勢検知手段と、航空機の姿勢に対するパイロッ
トの押圧位置と押圧量とが予め定めた関係となるよう
に、前記各検知手段からの検知信号により前記押圧手段
を作動させる制御手段とを備えている点にある。The features of the present invention include a pressing unit that presses a pilot seated in a cockpit of an aircraft from a plurality of positions, a pressing amount detecting unit at each pressing position by the pressing unit, an aircraft attitude detecting unit, and an aircraft. And control means for operating the pressing means in response to a detection signal from each of the detecting means so that the pilot pressing position and the pressing amount with respect to the attitude of the pilot have a predetermined relationship.
（作 用） 本発明の構成によれば、航空機の姿勢は姿勢検知手段
により検知され、押圧手段によるパイロットの各押圧位
置での押圧量は押圧量検知手段により検知される。そし
て、各検知手段からの検知信号が制御手段に送られる
と、制御手段は、パイロットの押圧位置と押圧量とが、
航空機の姿勢に対して予め定められた関係になるよう
に、押圧手段を作動させる。これによりパイロットは、
航空機の姿勢に応じて定められた押圧位置と押圧量とで
押圧され、体感により航空機の姿勢を認識できる。(Operation) According to the configuration of the present invention, the attitude of the aircraft is detected by the attitude detecting means, and the pressing amount of the pilot at each pressing position by the pressing means is detected by the pressing amount detecting means. Then, when the detection signal from each detection means is sent to the control means, the control means, the pressing position and the pressing amount of the pilot,
The pressing means is operated so as to have a predetermined relationship with the attitude of the aircraft. This allows the pilot to:
Pressing is performed at a pressing position and pressing amount determined according to the attitude of the aircraft, and the attitude of the aircraft can be recognized based on the bodily sensation.
（実施例） 以下、図面を参照して本発明の実施例を説明する。(Example) Hereinafter, an example of the present invention is described with reference to drawings.
第１図及び第２図に示す航空機の操縦席１は、座部２
と背凭部３とを備えている。その座部２には第１ブラダ
４、第２ブラダ５及び第３ブラダ６が左右幅方向に並列
して内蔵され、背凭部３には第４ブラダ７、第５ブラダ
８及び第６ブラダ９が左右幅方向に並列して内蔵されて
いる。The cockpit 1 of the aircraft shown in FIGS.
And a backrest 3. A first bladder 4, a second bladder 5, and a third bladder 6 are built in the seat portion 2 in parallel in the left-right width direction, and a fourth bladder 7, a fifth bladder 8, and a sixth bladder are mounted on the backrest portion 3. 9 are built in parallel in the left-right width direction.
各ブラダ4,5,6,7,8,9はそれぞれ独立したパイプ10を
介して高圧空気源11と接続されている。その各パイプ10
にはそれぞれ圧力制御弁12が介在されている。この圧力
制御弁12は作動機構13により作動されることで、高圧空
気源11から送り出される空気圧力を調節する。この圧力
調節により、各ブラダ4,5,6,7,8,9は内圧が変化して膨
張あるいは収縮を行う。これにより、操縦席１に着座し
たパイロットは６つの各ブラダ位置から、ブラダ内圧に
応じた量だけ押圧されることになる。Each of the bladders 4, 5, 6, 7, 8, 9 is connected to a high-pressure air source 11 via an independent pipe 10. That each pipe 10
Are each provided with a pressure control valve 12. The pressure control valve 12 is actuated by an actuation mechanism 13 to adjust the air pressure sent from the high-pressure air source 11. By this pressure adjustment, the bladders 4, 5, 6, 7, 8, 9 change their internal pressures and expand or contract. Thus, the pilot seated on the cockpit 1 is pressed from each of the six bladder positions by an amount corresponding to the bladder internal pressure.
また、各パイプ10にはそれぞれ、ブラダ4,5,6,7,8,9
と圧力制御弁12との間に圧力センサ14が介在されてい
る。各圧力センサ14により各ブラダ4,5,6,7,8,9の内圧
が検知されることで、各ブラダ4,5,6,7,8,9のそれぞれ
の内圧に応じたパイロットの押圧量が検知される。Each pipe 10 has a bladder 4,5,6,7,8,9
A pressure sensor 14 is interposed between the pressure sensor 12 and the pressure control valve 12. By detecting the internal pressure of each bladder 4,5,6,7,8,9 by each pressure sensor 14, the pilot pressure corresponding to each internal pressure of each bladder 4,5,6,7,8,9 is obtained. The amount is detected.
また、航空機には姿勢検知手段15が備えられている。
この姿勢検知手段15は、例えば直交３軸方向の航空機の
加速度を測定することで姿勢を検知するもの、あるいは
操縦杆の作動方向から姿勢を検知するもの等が用いられ
る。Further, the aircraft is provided with attitude detecting means 15.
As the attitude detecting means 15, a means for detecting the attitude by measuring the acceleration of the aircraft in, for example, three orthogonal axes, or a means for detecting the attitude from the operating direction of the control rod is used.
そして、航空機の姿勢に対するパイロットの押圧位置
と押圧量とが予め定めた関係となるように、圧力センサ
14及び姿勢検知手段15からの検知信号により各ブラダ4,
5,6,7,8,9の内圧を制御する制御手段16が備えられてい
る。Then, the pressure sensor is set so that the pilot pressing position and the pressing amount with respect to the attitude of the aircraft have a predetermined relationship.
Each bladder 4, according to the detection signal from 14 and attitude detection means 15,
Control means 16 for controlling the internal pressure of 5, 6, 7, 8, 9 is provided.
この制御手段16は、本実施例では中央処理装置17と、
記憶装置18と、入出力装置19とを備えたマイクロコンピ
ュータとされている。そして、その入出力装置19を介し
て圧力センサ14及び姿勢検知手段15からの検知信号が中
央処理装置17に入力され、記憶装置18に記憶された制御
プログラムに従って処理がなされ、入出力装置19を介し
てドライバー13に制御信号が出力される。This control means 16 includes a central processing unit 17 in this embodiment,
The microcomputer is provided with a storage device 18 and an input / output device 19. Then, detection signals from the pressure sensor 14 and the attitude detection means 15 are input to the central processing unit 17 via the input / output device 19, and processing is performed in accordance with the control program stored in the storage device 18. A control signal is output to the driver 13 via the controller 13.
ここで、その制御プログラムにおける航空機の姿勢に
対するパイロットの押圧位置と押圧量との関係は次の通
りとされている。Here, the relationship between the pilot pressing position and the pressing amount with respect to the attitude of the aircraft in the control program is as follows.
すなわち、水平姿勢では各ブラダ4,5,6,7,8,9の膨張
量は最小とされる。That is, in the horizontal posture, the amount of expansion of each bladder 4, 5, 6, 7, 8, 9 is minimized.
そして、右旋回をするような場合に機体右側が下向と
なる姿勢では、第３ブラダ６と第６ブラダ９とが膨張し
てパイロットの左大腿部と左背面とを押圧し、また、水
平姿勢からの機体傾き角が大きい程に第３ブラダ６と第
６ブラダ９は大きく膨張し、機体右側が鉛直下向となっ
た時にその押圧量が最大となる。Then, in a posture in which the right side of the aircraft faces downward when making a right turn, the third bladder 6 and the sixth bladder 9 expand and press the pilot's left thigh and the left rear, and The third bladder 6 and the sixth bladder 9 expand greatly as the inclination angle of the body from the horizontal posture increases, and the amount of pressing becomes maximum when the right side of the body is vertically downward.
左旋回をするような場合に機体左側が下方となる姿勢
では、第１ブラダ４と第４ブラダ７とが膨張してパイロ
ットの右大腿部と右背面とを押圧し、また、水平姿勢か
らの機体傾き角が大きい程に第１ブラダ４と第４ブラダ
７は大きく膨張し、機体左側が鉛直下向となった時にそ
の押圧量が最大となる。In a posture where the left side of the fuselage faces downward when making a left turn, the first bladder 4 and the fourth bladder 7 expand and press the right thigh and the right back of the pilot. The larger the tilt angle of the body, the larger the first bladder 4 and the fourth bladder 7 expand, and the amount of pressing becomes maximum when the left side of the body is vertically downward.
上昇をする場合に機首が上向となる姿勢では、第１ブ
ラダ4,、第２ブラダ５及び第３ブラダ６が膨張してパイ
ロットの大腿部全体を押圧し、また、水平姿勢からの機
体傾き角が大きい程に第１ブラダ４、第２ブラダ５及び
第３ブラダ６は大きく膨張し、機首が鉛直上向となった
時にその押圧量が最大となる。In a posture in which the nose is upward when climbing, the first bladder 4, the second bladder 5, and the third bladder 6 expand and press the entire thigh of the pilot. The first bladder 4, the second bladder 5, and the third bladder 6 expand greatly as the body inclination angle increases, and the pressing amount becomes maximum when the nose is vertically upward.
下降をする場合に機首が下向となる姿勢では、第４ブ
ラダ７、第５ブラダ８及び第６ブラダ９が膨張してパイ
ロットの背面全体を押圧し、また、水平姿勢からの機体
傾き角が大きい程に第４ブラダ７、第５ブラダ８及び第
６ブラダ９は大きく膨張し、機首が鉛直下向となった時
にその押圧量が最大となる。In a posture in which the nose is downward when descending, the fourth bladder 7, the fifth bladder 8, and the sixth bladder 9 expand and press the entire rear surface of the pilot, and the aircraft tilt angle from the horizontal posture Is larger, the fourth bladder 7, the fifth bladder 8, and the sixth bladder 9 are greatly expanded, and the amount of pressing becomes maximum when the nose is vertically downward.
機体の上面が下向となる背面飛行状態では、第２ブラ
ダ５及び第５ブラダ８が膨張してパイロットの両大腿部
中央と背面中央とを押圧し、また、機体の上面が鉛直方
向に対し下向に傾く角度が大きい程に第２ブラダ５及び
第５ブラダ８は大きく膨張し、機体の上面が完全に下向
となった水平姿勢においてその押圧量が最大となる。In the rear flight state in which the upper surface of the aircraft is downward, the second bladder 5 and the fifth bladder 8 expand and press the center of both the thighs and the rear of the pilot, and the upper surface of the aircraft is in the vertical direction. On the other hand, the larger the downward tilt angle, the more the second bladder 5 and the fifth bladder 8 expand, and the amount of pressing becomes maximum in the horizontal posture in which the upper surface of the body is completely downward.
また、航空機の姿勢が上記各姿勢の複合した姿勢であ
る場合は、各姿勢に対応したブラダが膨張してパイロッ
トを押圧する。例えば、機体左側が下向となると共に、
機種が上向となる姿勢では、第１ブラダ４、第２ブラダ
５、第３ブラダ６及び第４ブラダ７が膨張してパイロッ
トを押圧する。Further, when the attitude of the aircraft is a combined attitude of the above attitudes, the bladder corresponding to each attitude expands and presses the pilot. For example, while the left side of the aircraft is facing down,
When the model is in the upward position, the first bladder 4, the second bladder 5, the third bladder 6, and the fourth bladder 7 expand and press the pilot.
上記構成によれば、圧力センサ14により各ブラダ4,5,
6,7,8,9の内圧、すなわちパイロットの各押圧位置での
押圧量が検知され、姿勢検知手段15により航空機の姿勢
が検知されると、その検知信号は制御手段16に入力され
る。According to the above configuration, each of the bladders 4, 5,
When the internal pressures of 6, 7, 8, and 9, that is, the amount of pressure at each of the pressing positions of the pilot are detected, and the attitude of the aircraft is detected by the attitude detecting means 15, the detection signal is input to the control means 16.
この制御手段16は、検知時点での各押圧位置での押圧
量を、その検知時点での航空機姿勢に対して予め定めた
各押圧位置での押圧量と比較し、その偏差に応じた制御
信号を圧力制御弁12の作動機構13に出力する。これによ
り圧力制御弁12が作動され、各ブラダ4,5,6,7,8,9は内
圧が調節されることにより、航空機姿勢に対するパイロ
ットの押圧位置と押圧量とが前記予め定めた関係となる
ように膨張あるいは収縮する。The control means 16 compares the pressing amount at each pressing position at the time of detection with the pressing amount at each pressing position predetermined with respect to the aircraft attitude at the time of detection, and a control signal corresponding to the deviation. Is output to the operating mechanism 13 of the pressure control valve 12. Thereby, the pressure control valve 12 is operated, and each bladder 4, 5, 6, 7, 8, 9 adjusts the internal pressure, so that the pressing position and the pressing amount of the pilot with respect to the aircraft attitude are in accordance with the predetermined relationship. It expands or contracts to become.
上記実施例によれば、パイロットはブラダ4,5,6,7,8,
9により、航空機の姿勢に応じて予め定められた押圧位
置と押圧量とで押圧され、体感により航空機姿勢を認識
できるので、空間識失調状態に陥るのが防止される。According to the above embodiment, the pilots are bladders 4, 5, 6, 7, 8,
According to 9, the aircraft is pressed at a predetermined pressing position and pressing amount according to the attitude of the aircraft, and the attitude of the aircraft can be recognized by the bodily sensation.
なお、本発明は上記実施例に限定されるものではな
い。The present invention is not limited to the above embodiment.
例えば、ブラダの数を増加させたり配置を変更するこ
とで、パイロットによる航空機姿勢の認識をより正確に
行なったり、ブラダの数を減少させてコストの低減を図
ってもよい。For example, by increasing the number of bladders or changing the arrangement, the pilot may more accurately recognize the aircraft attitude, or the number of bladders may be reduced to reduce the cost.
また、押圧手段としてブラダを用いるものを例示した
が、例えば複数の油圧シリンダを用い、その油圧シリン
ダを伸縮させることでパイロットを押圧するようにし、
伸縮量を調節することで押圧量を調節するようにしても
よい。In addition, although the example using a bladder as the pressing means is illustrated, for example, a plurality of hydraulic cylinders are used, and the pilot is pressed by expanding and contracting the hydraulic cylinders.
The amount of pressing may be adjusted by adjusting the amount of expansion and contraction.
また、押圧量検知手段として圧力センサ14を例示した
が、例えば、押圧手段であるブラダの膨張位置や油圧シ
リンダの伸縮位置を検知する位置センサを用いてもよ
い。Further, although the pressure sensor 14 has been illustrated as the pressing amount detecting means, for example, a position sensor for detecting the expansion position of the bladder or the expanding / contracting position of the hydraulic cylinder as the pressing means may be used.
（発明の効果） 本発明によれば、パイロットは航空機の姿勢に応じて
予め定められた押圧位置と押圧量とで押圧されるので、
体感により航空機姿勢を認識でき、雲の中を飛行するよ
うな場合でも空間識失調状態に陥ることが防止される。(Effect of the Invention) According to the present invention, the pilot is pressed at a predetermined pressing position and pressing amount according to the attitude of the aircraft,
It is possible to recognize the attitude of the aircraft based on the bodily sensation, and it is possible to prevent the user from falling into a state of spatial inconsistency even when flying in the clouds.
第１図は本発明の実施例に係る空間識失調防止装置の構
成説明用平面図、第２図は操縦席の構成説明用側断面図
である。 （１）……操縦席、（４）（５）（６）（７）（８）
（９）……ブラダ、（14）……圧力センサ、（15）……
姿勢検知手段、（16）……制御手段。FIG. 1 is a plan view for explaining the configuration of a space sickness prevention device according to an embodiment of the present invention, and FIG. 2 is a side sectional view for explaining the configuration of a cockpit. (1) ... cockpit, (4) (5) (6) (7) (8)
(9) bladder, (14) pressure sensor, (15)
Attitude detection means, (16) ... control means.
───────────────────────────────────────────────────── フロントページの続き (56)参考文献 特開 平２−303998（ＪＰ，Ａ) 特開 平２−246899（ＪＰ，Ａ) 特開 平１−254496（ＪＰ，Ａ) 特開 平１−148697（ＪＰ，Ａ) 特開 平３−258694（ＪＰ，Ａ) 実開 昭63−148600（ＪＰ，Ｕ) (58)調査した分野(Int.Cl.6，ＤＢ名) B64D 10/00 B64D 11/06 B64D 25/00 - 25/06──────────────────────────────────────────────────続 き Continuation of the front page (56) References JP-A-2-303998 (JP, A) JP-A-2-246899 (JP, A) JP-A-1-254496 (JP, A) JP-A-1- 148697 (JP, A) JP-A-3-258694 (JP, A) JP-A-63-148600 (JP, U) (58) Fields investigated (Int. Cl. 6 , DB name) B64D 10/00 B64D 11 / 06 B64D 25/00-25/06
Claims (1)
数位置から押圧する押圧手段と、この押圧手段による各
押圧位置での押圧量検知手段と、航空機の姿勢検知手段
と、航空機の姿勢に対するパイロットの押圧位置と押圧
量とが予め定めた関係となるように、前記各検知手段か
らの検知信号により前記押圧手段を作動させる制御手段
とを備えていることを特徴とする航空機パイロットの空
間識失調防止装置。1. A pressing means for pressing a pilot seated in a cockpit of an aircraft from a plurality of positions, a pressing amount detecting means at each pressing position by the pressing means, an attitude detecting means of the aircraft, and a pilot for the attitude of the aircraft. Control means for operating the pressing means in response to a detection signal from each of the detecting means so that the pressing position and the pressing amount of the airplane have a predetermined relationship. Prevention device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26152190A JP2855837B2 (en) | 1990-09-28 | 1990-09-28 | Aircraft pilot's device for preventing spatial dysfunction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26152190A JP2855837B2 (en) | 1990-09-28 | 1990-09-28 | Aircraft pilot's device for preventing spatial dysfunction |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH04138996A JPH04138996A (en) | 1992-05-13 |
| JP2855837B2 true JP2855837B2 (en) | 1999-02-10 |
Family
ID=17363060
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP26152190A Expired - Fee Related JP2855837B2 (en) | 1990-09-28 | 1990-09-28 | Aircraft pilot's device for preventing spatial dysfunction |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2855837B2 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7243945B2 (en) | 1992-05-05 | 2007-07-17 | Automotive Technologies International, Inc. | Weight measuring systems and methods for vehicles |
| US7976060B2 (en) | 1995-06-07 | 2011-07-12 | Automotive Technologies International, Inc. | Seat load or displacement measuring system for occupant restraint system control |
| US7779956B2 (en) | 1995-06-07 | 2010-08-24 | Automotive Technologies International, Inc.. | Vehicular seats with weight sensing capability |
| US7387183B2 (en) | 1995-06-07 | 2008-06-17 | Automotive Technologies International, Inc. | Weight measuring systems and methods for vehicles |
| US20070135982A1 (en) | 1995-06-07 | 2007-06-14 | Automotive Technologies International, Inc. | Methods for Sensing Weight of an Occupying Item in a Vehicular Seat |
| US7762582B2 (en) | 1995-06-07 | 2010-07-27 | Automotive Technologies International, Inc. | Vehicle component control based on occupant morphology |
| US7766383B2 (en) | 1998-11-17 | 2010-08-03 | Automotive Technologies International, Inc. | Vehicular component adjustment system and method |
| US7900736B2 (en) | 1995-06-07 | 2011-03-08 | Automotive Technologies International, Inc. | Vehicular seats with fluid-containing weight sensing system |
-
1990
- 1990-09-28 JP JP26152190A patent/JP2855837B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH04138996A (en) | 1992-05-13 |
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