JPH01168596A - Lifting vector modifier - Google Patents
Lifting vector modifierInfo
- Publication number
- JPH01168596A JPH01168596A JP32624687A JP32624687A JPH01168596A JP H01168596 A JPH01168596 A JP H01168596A JP 32624687 A JP32624687 A JP 32624687A JP 32624687 A JP32624687 A JP 32624687A JP H01168596 A JPH01168596 A JP H01168596A
- Authority
- JP
- Japan
- Prior art keywords
- aircraft
- rudder
- cylinder
- roll angle
- range
- 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
- 239000013598 vector Substances 0.000 title description 2
- 239000003607 modifier Substances 0.000 title 1
- 239000003381 stabilizer Substances 0.000 claims abstract description 4
- 230000004075 alteration Effects 0.000 abstract 1
- 230000002079 cooperative effect Effects 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 abstract 1
- 230000005484 gravity Effects 0.000 description 4
- 241000272517 Anseriformes Species 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
Landscapes
- Vehicle Body Suspensions (AREA)
Abstract
Description
【発明の詳細な説明】
（イ）産業上の利用分野
この発明は航空機の運動性の向上，機体の重量を軽くす
ることに関する。DETAILED DESCRIPTION OF THE INVENTION (a) Industrial Application Field This invention relates to improving the maneuverability of an aircraft and reducing the weight of the aircraft.
（ロ）従来の技術
尾翼または尾翼とカナード翼を組み合わせたものまたは
主翼についているフラップや補助翼などを使って航空機
の運動を制御していた。(b) Conventional technology The motion of the aircraft was controlled using the tail or a combination of tail and canard wings, or flaps and ailerons attached to the main wings.
（ハ）発明が解決しようとする問題点
この装置は舵４を図２のように適切な角にして，別々に
または同時に図３のように筒５を適切なロール角にする
ことによって従来の航空機に比べ運動性を高めることが
できる。(C) Problems to be Solved by the Invention This device can be improved by setting the rudder 4 at an appropriate angle as shown in Fig. 2, and separately or simultaneously setting the cylinder 5 at an appropriate roll angle as shown in Fig. 3. It can improve maneuverability compared to aircraft.
また胴体は飛行中，胴体そのものの重量などで胴体端部
が曲げられるので従来は構造でおぎなっていたため機体
重量が重くなっていたが，この装置を設置し作動させる
ことによって，胴体にかかる荷重を空力的に肩代りさせ
て構造を軽くすることができる。Additionally, during flight, the ends of the fuselage are bent due to the weight of the fuselage itself, so conventionally the fuselage was covered with a structure, making the aircraft heavier. By installing and operating this device, the load on the fuselage can be reduced. The structure can be made lighter by aerodynamically shifting it.
（ニ）問題点を解決するための手段
この発明を図面にもとづいて説明すると，図１において
舵４の角度はアクチュエータ２で図２のように変えられ
る。(d) Means for Solving Problems The present invention will be explained based on the drawings. In FIG. 1, the angle of the rudder 4 can be changed by the actuator 2 as shown in FIG. 2.
その舵４の可動範囲およそ±４５°。図１でモータ１を
含まない以左の筒５がモータ１によって回転する。筒５
のロール角の可動範囲は±３６０°。The movable range of the rudder 4 is approximately ±45°. In FIG. 1, the cylinder 5 on the left that does not include the motor 1 is rotated by the motor 1. Tube 5
The roll angle movable range is ±360°.
（ホ）作用
だから舵４の角度と筒５のロール角はパイロットが望む
姿勢にするために舵４の可動範内で別々にまたは同時に
任意の角度にすることができる。(E) Because of the operation, the angle of the rudder 4 and the roll angle of the cylinder 5 can be set to arbitrary angles separately or simultaneously within the movable range of the rudder 4 in order to obtain the attitude desired by the pilot.
（ヘ）実施例
ａ．図３のようにこの装置を機首先端部分に使用した場
合
現用戦闘機では機体の重心から機首までの距離と機体に
重心から尾翼の圧力中心までの距離の比は１．４〜２．
０：１である．すなわち安定板３と舵４の合計面積が尾
翼の面積に比べて小さく，揚力が小さくても回転力が大
きいので機体の動揺を早く停めることができる。(F) Example a. When this device is used at the tip of the nose as shown in Figure 3, in a modern fighter jet, the ratio of the distance from the center of gravity of the aircraft to the nose and the distance from the center of gravity of the aircraft to the pressure center of the tail is 1.4 to 2.
The ratio is 0:1. That is, the total area of the stabilizer plate 3 and the rudder 4 is smaller than the area of the tail, and even if the lift force is small, the rotational force is large, so that the vibration of the aircraft can be stopped quickly.
また図４のような揚力が得られるように筒５のロール角
と舵４の角度を決めることによって旋回率を高めること
ができる。Further, the turning rate can be increased by determining the roll angle of the cylinder 5 and the angle of the rudder 4 so that the lift shown in FIG. 4 is obtained.
ｂ．図５のようにこの装置を機首先端部分と尾翼を廃し
た部分に使用した場合
舵４によってつくり出される揚力を利用して胴体にかか
る荷重を空力的に肩代りすることによって構造を軽くす
ることができ，その結果機体の重量を軽くすることがで
きる。b. As shown in Figure 5, when this device is used at the tip of the aircraft's nose and the part where the tail has been removed, the structure is lightened by aerodynamically offloading the load on the fuselage using the lift generated by the rudder 4. As a result, the weight of the aircraft can be reduced.
特に大型機には効果的である。This is especially effective for large aircraft.
また，この２つの装置の揚力ベクトルを機体の回転力が
ゼロになるように制御すれば，機体の重心に関係ない運
動性が向上する。Furthermore, if the lift vectors of these two devices are controlled so that the rotational force of the aircraft becomes zero, maneuverability regardless of the center of gravity of the aircraft will be improved.
（ト）発明の効果
本発明の装置を図３のように機首先端部分や図５のよう
にこの装置を２ついっしょに設置し作動させた航空機は
，機体の重心を中心とした，または機体の重心に関係な
い上下方向，左右方向，斜め方向の運動性が向上できる
。(G) Effects of the Invention Aircraft in which the device of the present invention is installed and operated at the tip of the nose as shown in Fig. 3 or two devices together as shown in Fig. This improves maneuverability in vertical, horizontal, and diagonal directions, regardless of the aircraft's center of gravity.
また特に図５のように使用した場合，胴体にかかる荷重
をこの装置が空力的に肩代りできるので構造を軽くでき
，機体全体の重量を軽減できる。In addition, especially when used as shown in Figure 5, this device can aerodynamically take over the load on the fuselage, making the structure lighter and reducing the overall weight of the aircraft.
図１はこの発明の装置の断面図を示すものである。
図２は舵４の角度の変化を表わす。
図３．図４はこの装置を機首先端部分に使用したとき，
図５はこの装置を機首先端部分と尾翼を廃した部分に同
時に使用したときのようすを示す。
１…モータ
２…アクチュエータ
３…安定板
４…舵
５…筒FIG. 1 shows a cross-sectional view of the device of the invention. FIG. 2 shows changes in the angle of the rudder 4. Figure 3. Figure 4 shows when this device is used at the nose tip.
Figure 5 shows the situation when this device is used simultaneously on the nose tip and the tail section. 1... Motor 2... Actuator 3... Stabilizer plate 4... Rudder 5... Tube
Claims (1)
ール角を変えられる筒（５）を持ち、それに安定板（３
）と舵（４）からなる翼がついている装置。1 It does not rotate intermittently like a propeller, but has a cylinder (5) that can change the roll angle, and a stabilizer plate (3).
) and a rudder (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32624687A JPH01168596A (en) | 1987-12-23 | 1987-12-23 | Lifting vector modifier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32624687A JPH01168596A (en) | 1987-12-23 | 1987-12-23 | Lifting vector modifier |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH01168596A true JPH01168596A (en) | 1989-07-04 |
Family
ID=18185627
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP32624687A Pending JPH01168596A (en) | 1987-12-23 | 1987-12-23 | Lifting vector modifier |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01168596A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7672765B2 (en) * | 2006-01-12 | 2010-03-02 | Gm Global Technnology Operations, Inc. | Enhanced roll stability indicator for vehicle rollover control |
-
1987
- 1987-12-23 JP JP32624687A patent/JPH01168596A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7672765B2 (en) * | 2006-01-12 | 2010-03-02 | Gm Global Technnology Operations, Inc. | Enhanced roll stability indicator for vehicle rollover control |
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