JPH05116689A - Aircraft fuel tank cast away device - Google Patents
Aircraft fuel tank cast away deviceInfo
- Publication number
- JPH05116689A JPH05116689A JP27968291A JP27968291A JPH05116689A JP H05116689 A JPH05116689 A JP H05116689A JP 27968291 A JP27968291 A JP 27968291A JP 27968291 A JP27968291 A JP 27968291A JP H05116689 A JPH05116689 A JP H05116689A
- Authority
- JP
- Japan
- Prior art keywords
- fuel tank
- aircraft
- falling
- detecting
- drop
- 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- Withdrawn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
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、航空機の燃料タンクを
投棄する装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for dumping an aircraft fuel tank.
【０００２】[0002]
【従来の技術】航空機において、落下燃料タンクを用い
る場合があるが、図４に示すように、この落下燃料タン
ク１には、図４に示すように、その後端に固定フィン１
２が設けられていた。2. Description of the Related Art In an aircraft, a falling fuel tank may be used. As shown in FIG. 4, the falling fuel tank 1 has a fixed fin 1 at its rear end as shown in FIG.
Two were provided.
【０００３】[0003]
【発明が解決しようとする課題】前記従来の航空機の落
下燃料タンクは、通常同タンク内の燃料が消費された時
に航空機から投棄される。しかし、空になった落下燃料
タンクの重量は非常に小さいために、投棄特性が悪い。
従って、固定フィンをもつ前記の従来の落下燃料タンク
では、母機である航空機から切離して投棄することが困
難であって、残燃料量及び航空機の機速と加速度が制限
された範囲にある場合しか落下燃料タンクの投棄を行う
ことができなかった。The conventional drop fuel tank of an aircraft is normally discarded from the aircraft when the fuel in the tank is consumed. However, since the weight of the emptied falling fuel tank is very small, the dumping property is poor.
Therefore, it is difficult for the conventional dropping fuel tank having fixed fins to be cut off from the mother aircraft and dumped, and only when the remaining fuel amount and the aircraft speed and acceleration of the aircraft are in the limited range. The dropping fuel tank could not be dumped.
【０００４】本発明は、以上の問題点を解決することが
できる航空機の燃料タンク投棄装置を提供しようとする
ものである。The present invention is intended to provide an aircraft fuel tank dumping apparatus capable of solving the above problems.
【０００５】[0005]
【課題を解決するための手段】本発明の航空機の燃料タ
ンク投棄装置は、落下燃料タンクに設けられた迎角が可
変な可動フィン、前記落下燃料タンク内の残燃料量の検
出装置と機体速度の検出装置と機体加速度の検出装置、
及び前記各検出装置の信号が入力され前記落下燃料タン
クの可動フィンの迎角を制御する制御器よりなる。SUMMARY OF THE INVENTION An aircraft fuel tank dumping apparatus according to the present invention comprises a movable fuel fin provided in a falling fuel tank, the angle of attack of which is variable, a remaining fuel amount detecting apparatus in the falling fuel tank, and a vehicle speed. Detection device and airframe acceleration detection device,
And a controller that receives signals from the detection devices and controls the angle of attack of the movable fins of the falling fuel tank.
【０００６】[0006]
【作用】本発明では、落下燃料タンクを投棄する直前
に、落下燃料タンク内の残燃料量及び航空機の機速と加
速度が検知され、これらの信号が制御器に入力される。
制御器は、これら信号に基づいて燃料タンクを投棄する
のに最適な迎角となるように落下燃料タンクの可動フィ
ンを制御することによって、落下燃料タンクは航空機よ
り円滑に投棄される。従って、落下燃料タンク内の残燃
料量及び航空機の機速と加速度の制限を受けることな
く、落下燃料タンクを円滑に投棄することが可能であ
る。In the present invention, immediately before the dropping fuel tank is dumped, the remaining fuel amount in the dropping fuel tank and the aircraft speed and acceleration are detected, and these signals are input to the controller.
Based on these signals, the controller controls the movable fins of the falling fuel tank so that the angle of attack is optimum for dumping the fuel tank, so that the falling fuel tank is smoothly dumped from the aircraft. Therefore, it is possible to smoothly dump the falling fuel tank without being restricted by the remaining fuel amount in the falling fuel tank and the aircraft speed and acceleration of the aircraft.
【０００７】[0007]
【実施例】本発明の第１の実施例を、図１及び図２によ
って説明する。図示しない航空機の主翼の下側等に搭載
される落下燃料タンク１の後端には、可動フィン２が設
けられている。３，４はそれぞれ航空機の機体に設けら
れた速度計と加速度計（Ｇメーター）であり、５は航空
機の機体又は落下燃料タンク１に設けられた落下燃料タ
ンク１の残燃料量を検出する落下燃料タンク燃料計であ
り、これらの信号は航空機の機体に設けられた制御器６
へ入力されるようになっている。同制御器６は、前記の
信号に基づいてモーター７を駆動し、同モーター７によ
って落下燃料タンク１の可動フィン２を動かしてその迎
角を適当な値に設定するようになっている。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIGS. A movable fin 2 is provided at the rear end of the falling fuel tank 1 mounted on the lower side of the main wing of an aircraft (not shown). Reference numerals 3 and 4 are a speedometer and an accelerometer (G meter) provided on the aircraft body, respectively, and 5 is a drop for detecting the remaining fuel amount of the fall fuel tank 1 provided on the aircraft body or the falling fuel tank 1. Fuel tank Fuel gauge, these signals are provided by the controller 6 on the aircraft fuselage.
It is designed to be input to. The controller 6 drives the motor 7 based on the above-mentioned signal, and moves the movable fin 2 of the falling fuel tank 1 by the motor 7 to set the angle of attack to an appropriate value.
【０００８】本実施例では、速度計３、加速度計４、及
び、落下燃料タンク燃料計５により、航空機の機速と加
速度，及び落下燃料タンク内の残燃料量が検知され、こ
れらの信号が制御器６に入力され、制御器６はこれら信
号をもとに落下燃料タンク１の投棄に最適な可動フィン
２の迎角を設定し、機体又は落下燃料タンク１に設けら
れたモーター７を駆動することにより可動フィン２を動
かす。In this embodiment, the speedometer 3, the accelerometer 4, and the falling fuel tank fuel gauge 5 detect the aircraft speed and acceleration, and the remaining fuel amount in the falling fuel tank, and these signals are sent. Based on these signals, the controller 6 sets the optimum angle of attack of the movable fins 2 for dumping the falling fuel tank 1, and drives the motor 7 provided in the airframe or the falling fuel tank 1. By doing so, the movable fin 2 is moved.
【０００９】なお、制御器６にはあらかじめ、計算、風
洞試験、及び飛行試験等で得られた最適迎角設定のため
に必要なデータがインプットされている。The controller 6 is preliminarily input with data necessary for setting the optimum angle of attack obtained by calculation, wind tunnel test, flight test and the like.
【００１０】通常、落下燃料タンク１を航空機より投棄
する場合は、同落下燃料タンク１内の燃料が消費されて
軽量になっているために、落下燃料タンク１の投棄特性
が悪化している。Normally, when the drop fuel tank 1 is discarded from an aircraft, the fuel in the drop fuel tank 1 is consumed and the weight is reduced, so that the drop characteristic of the drop fuel tank 1 is deteriorated.
【００１１】本実施例では、以上説明したように、落下
燃料タンク１内の残燃料量、即ち同落下燃料タンク１の
重量、及び航空機の機速と加速度を検出し、これに基づ
いて落下燃料タンク１の後端の可動フィン２の迎角を最
適値に設定しているために、落下燃料タンク１には適切
なピッチング・モーメントが与えられ、航空機の飛行状
態及び落下燃料タンク１内の残燃料量に制約を受けるこ
となく落下燃料タンク１を円滑に航空機より投棄するこ
とができる。In the present embodiment, as described above, the remaining fuel amount in the falling fuel tank 1, that is, the weight of the falling fuel tank 1 and the aircraft speed and acceleration of the aircraft are detected, and the falling fuel is detected based on this. Since the angle of attack of the movable fins 2 at the rear end of the tank 1 is set to an optimum value, an appropriate pitching moment is given to the falling fuel tank 1, and the flight condition of the aircraft and the remaining fuel inside the falling fuel tank 1 are given. The falling fuel tank 1 can be smoothly dumped from the aircraft without being restricted by the fuel amount.
【００１２】本発明の第２の実施例を、図３によって説
明する。前記第１の実施例では、モーター７は１個で、
そのため可動フィン２の迎角は左、右フィンで同じであ
った。本第２の実施例が、前記第１の実施例と異る点
は、モーターを右舷可動フィン１０を動かす右舷モータ
ー８と左舷可動フィン１１を動かす左舷モーター９の２
個設け、これらのモーター８，９を制御器６によって駆
動するようにし、左、右の可動フィン１０，１１の迎角
を各々独立に変えることができるようにした。A second embodiment of the present invention will be described with reference to FIG. In the first embodiment, there is one motor 7,
Therefore, the angle of attack of the movable fin 2 was the same for the left and right fins. The second embodiment is different from the first embodiment in that the starboard motor 8 moves the starboard movable fin 10 and the port motor 9 moves the portside movable fin 11.
Individually provided, these motors 8 and 9 are driven by the controller 6 so that the angles of attack of the left and right movable fins 10 and 11 can be independently changed.
【００１３】前記の第１の実施例では、落下燃料タンク
１のピッチング・モーメントだけをコントロールしてい
たのに対し、本第２の実施例では、左右の可動フィン１
０，１１を制御することによって、ピッチング・モーメ
ントと共にローリング・モーメントもコントロールする
ことができ、より広い範囲で落下燃料タンク１の投棄を
行うことができる。In the first embodiment described above, only the pitching moment of the falling fuel tank 1 was controlled, whereas in the second embodiment, the left and right movable fins 1 are controlled.
By controlling 0 and 11, the rolling moment as well as the pitching moment can be controlled, and the dropping fuel tank 1 can be dumped in a wider range.
【００１４】[0014]
【発明の効果】以上説明したように、本発明によれば落
下燃料タンクを投棄することができる残燃料量及び航空
機の機速と加速度の範囲を拡大することができ、航空機
の機動性が大幅に向上すると共に、投下燃料タンクの投
棄時の安全性の向上にも寄与することができる。As described above, according to the present invention, it is possible to expand the remaining fuel amount that can drop the falling fuel tank and the range of the aircraft speed and acceleration, and to greatly improve the maneuverability of the aircraft. It is possible to contribute to the improvement of safety at the time of dumping the dropped fuel tank.
【図１】本発明の第１の実施例の概念図である。FIG. 1 is a conceptual diagram of a first embodiment of the present invention.
【図２】同第１の実施例に係る機能ブロック図である。FIG. 2 is a functional block diagram according to the first embodiment.
【図３】本発明の第２の実施例の機能ブロック図であ
る。FIG. 3 is a functional block diagram of a second embodiment of the present invention.
【図４】従来の航空機の落下燃料タンクの概念図であ
る。FIG. 4 is a conceptual diagram of a conventional falling fuel tank of an aircraft.
１ 落下燃料タンク ２ 可動フィン ３ 速度計 ４ 加速度計 ５ 落下燃料タンク燃料計 ６ 制御器 ７ モーター ８ 左舷モーター ９ 右舷モーター １０ 右舵可動フィン １１ 左舵可動フィン 1 Falling Fuel Tank 2 Movable Fins 3 Speedometer 4 Accelerometer 5 Falling Fuel Tank Fuel Gauge 6 Controller 7 Motor 8 Portside Motor 9 Starboard Motor 10 Right Rudder Movable Fin 11 Left Rudder Movable Fin
Claims (1)
な可動フィン、前記落下燃料タンク内の残燃料量の検出
装置と機体速度の検出装置と機体加速度の検出装置、及
び前記各検出装置の信号が入力され前記落下燃料タンク
の可動フィンの迎角を制御する制御器よりなることを特
徴とする航空機の燃料タンク投棄装置。1. A movable fin provided in a falling fuel tank with a variable angle of attack, a device for detecting the amount of residual fuel in the falling fuel tank, a device for detecting a machine speed, a device for detecting a machine acceleration, and each of the detecting devices. Is input to the fuel tank dumping device for an aircraft, which comprises a controller for controlling the angle of attack of the movable fin of the falling fuel tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP27968291A JPH05116689A (en) | 1991-10-25 | 1991-10-25 | Aircraft fuel tank cast away device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP27968291A JPH05116689A (en) | 1991-10-25 | 1991-10-25 | Aircraft fuel tank cast away device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH05116689A true JPH05116689A (en) | 1993-05-14 |
Family
ID=17614404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP27968291A Withdrawn JPH05116689A (en) | 1991-10-25 | 1991-10-25 | Aircraft fuel tank cast away device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH05116689A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3489148A1 (en) * | 2017-11-23 | 2019-05-29 | The Boeing Company | Fuel systems and methods for an aerial vehicle |
| JP2020006812A (en) * | 2018-07-09 | 2020-01-16 | 日本Ｆｃ企画株式会社 | aircraft |
| DE102009057878B4 (en) | 2009-12-11 | 2024-01-25 | Airbus Defence and Space GmbH | Method for controlling a vehicle and dropping a load from a vehicle |
-
1991
- 1991-10-25 JP JP27968291A patent/JPH05116689A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009057878B4 (en) | 2009-12-11 | 2024-01-25 | Airbus Defence and Space GmbH | Method for controlling a vehicle and dropping a load from a vehicle |
| EP3489148A1 (en) * | 2017-11-23 | 2019-05-29 | The Boeing Company | Fuel systems and methods for an aerial vehicle |
| US10866594B2 (en) | 2017-11-23 | 2020-12-15 | The Boeing Company | Fuel systems and methods for an aerial vehicle |
| JP2020006812A (en) * | 2018-07-09 | 2020-01-16 | 日本Ｆｃ企画株式会社 | aircraft |
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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: 19990107 |