JPH01260299A - Missile equipped with fore wing and rear wing - Google Patents
Missile equipped with fore wing and rear wingInfo
- Publication number
- JPH01260299A JPH01260299A JP8532588A JP8532588A JPH01260299A JP H01260299 A JPH01260299 A JP H01260299A JP 8532588 A JP8532588 A JP 8532588A JP 8532588 A JP8532588 A JP 8532588A JP H01260299 A JPH01260299 A JP H01260299A
- Authority
- JP
- Japan
- Prior art keywords
- wing
- missile
- motion
- fore
- wings
- 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
- 230000004044 response Effects 0.000 abstract description 10
- 230000001133 acceleration Effects 0.000 abstract description 5
- 230000004043 responsiveness Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、高い運動応答性を持たせるために前翼と後翼
とを操舵するようにした飛しよう体に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a flying object whose front wings and rear wings are steered to provide high motion responsiveness.
従来の飛しよう体は、第３図に示すように前翼２のみ（
第３図（Ａ） ） 、後翼４のみ（第３図＠）、または
主翼６のみ（第３図０）を操舵することによって機体運
動を制御していた。The conventional flying body has only the front wing 2 (as shown in Fig. 3).
Figure 3 (A) ), aircraft motion was controlled by steering only the rear wing 4 (Figure 3 @) or only the main wing 6 (Figure 3 0).
上記従来飛しよう体のうち前翼操舵及び後翼操舵の飛し
よう体は、それぞれ第４図（６）、（ハ）に示すような
運動の応答遅れがあった。これは、操＃ｅＲに発生する
揚力と、その揚力によって機体が回転し迎角をとること
で発生する揚力との重ね合わせにより機体が運動するか
らである。Among the above-mentioned conventional flying bodies, the front-wing steered flying bodies and the rear-wing steered flying bodies had a delay in motion response as shown in FIGS. 4(6) and 4(c), respectively. This is because the aircraft moves due to the superposition of the lift generated during maneuver #eR and the lift generated when the aircraft rotates and takes an angle of attack.
また、主翼操舵の場合には、機体回転運動の発生は小さ
く応答遅れは小さいが、大きな主翼を可動させる操舵機
構が必要となる。このことは、機体重量を増加させ、引
いては機体応答を悪化させることとなる。Furthermore, in the case of main wing steering, although the occurrence of body rotational motion is small and the response delay is small, a steering mechanism that moves a large main wing is required. This increases the weight of the aircraft, which in turn worsens the aircraft response.
本発明は、上記の問題点を解消させるものでより高い運
動応答性を得て、高い運動特性をもった飛しよう体を提
供しようとするものである。The present invention aims to solve the above-mentioned problems and to provide a flying body with higher motion responsiveness and high motion characteristics.
本発明は、前翼と後翼とを備えた飛しよう体において、
上記前翼と後翼とを独立に作動させる操舵装置を設けた
。The present invention provides a flying body having a front wing and a rear wing.
A steering device is provided to operate the front wing and the rear wing independently.
機体運動を行う場合、前翼と後翼とを機体回転運動が生
じないように操舵装置によって作動させる。これにより
、機体回転運動が生じない状態で機体運動が行なわれ、
機体回転運動によって生ずる応答遅れがなくなる。When performing aircraft movement, the front wings and rear wings are operated by a steering device so that no rotational movement of the aircraft occurs. As a result, the aircraft motion is performed without any rotational motion of the aircraft,
The response delay caused by the rotational movement of the aircraft body is eliminated.
本発明の一実施例を第１図によって説明する。 An embodiment of the present invention will be described with reference to FIG.
１は飛しよう体でそれぞれ４枚の前翼２と後翼３とを備
えている。４ａ及び４ｂは、飛しよう体１中の前翼部と
後翼部に設けられた前翼と後翼の操舵装置である。７は
前翼２前方にある制御装置であって、配線８ａ、８ｂに
よって制御装置７に接続された操舵装［４ａ、４ｂが制
御されるようになっている。５は飛しよう体１の縦軸中
央部から後部にわたって配置された推進装置であって、
後翼の操舵装置４ｂは、飛しよう体１内に推進装置５の
周りに円環状に設けられている。また、本実施例では、
制御装置７によって両操舵装置４ａ、４ｂが独立に制御
されるようになっている。1 is a flying body each having four front wings 2 and four rear wings 3. 4a and 4b are front wing and rear wing steering devices provided in the front wing section and the rear wing section of the flying body 1. Reference numeral 7 denotes a control device located in front of the front wing 2, which controls steering equipment [4a, 4b] connected to the control device 7 through wiring 8a, 8b. 5 is a propulsion device arranged from the center of the vertical axis to the rear of the flying body 1,
The rear wing steering device 4b is provided in the flying body 1 in an annular shape around the propulsion device 5. Furthermore, in this example,
Both steering devices 4a and 4b are independently controlled by the control device 7.
上記の構成をもつ本実施例では、制御装置７によって操
舵装置４ａ、４ｂを制御することによって、同操錠装置
？ｔｔ４＆、４ｂＫよって作動される前翼２及び後翼３
が、それぞれ独立に作動される。これによって、飛しよ
う体の機体に機軸と直角方向に加速度を与える場合には
、前翼２及び後翼３を機体の回転運動が生じない方向に
それぞれ独立に同時に操舵させることによって、必要な
機軸と直角方向の加速度を飛しよう体１に与えることが
できる。この上うＫして飛しよう体の機体回転運動が生
じない状態で飛しよう体の機体運動を行なうことができ
る。In this embodiment having the above-mentioned configuration, the control device 7 controls the steering devices 4a and 4b, thereby controlling the locking device. Forward wing 2 and rear wing 3 operated by tt4&, 4bK
are operated independently. As a result, when applying acceleration to the aircraft body in a direction perpendicular to the aircraft axis, the front wing 2 and the rear wing 3 are independently and simultaneously steered in a direction that does not cause rotational motion of the aircraft body. An acceleration in the direction perpendicular to can be applied to the flying body 1. In addition, it is possible to carry out the body motion of the flying body in a state where no rotational motion of the flying body occurs.
従って、本実施例では、機体回転運動によって引き起さ
れる運動応答遅れが除去され、第２図に示すように従来
の飛しよう体に比して良好な応答性を得ることができる
。Therefore, in this embodiment, the motion response delay caused by the rotating motion of the aircraft body is eliminated, and as shown in FIG. 2, it is possible to obtain better responsiveness than the conventional flying body.
本発明は、飛しよう体機体に機軸と直角方向に加速度を
付与させたい場合、前翼及び後翼を機体回転運動が生じ
ない方向に同時にそれぞれ独立に作動して操舵させるこ
とによって、機体回転運動を起すことなく機軸の直角方
向の加速度をうろことができ、機体回転運動によって引
き起こされる運動応答遅れを除去することができる。こ
れによって飛しよう体に良好な応答性を与えることがで
き、速い回避運動を行なう目榛に対しても十分追従でき
、最終的に高い命中精度を得ることができる。In the present invention, when it is desired to apply acceleration to a flying body in a direction perpendicular to the aircraft axis, the front wing and the rear wing are operated simultaneously and independently in a direction in which no rotational motion of the aircraft occurs. It is possible to increase the acceleration in the direction perpendicular to the machine axis without causing any turbulence, and it is possible to eliminate the motion response delay caused by the machine body rotational motion. As a result, it is possible to give the flying object good responsiveness, and it is possible to sufficiently follow the target that performs fast evasive movements, and ultimately to obtain high accuracy.
第１Ｎは本発明の一実施例の説明図で同図（勾は正面図
、同図（均は側面図、第２図は同実施例の機体応答を示
す線図、第３図（６）、＠、０はそれぞれ従来の飛しよ
う体の説明図、第４図は従来の飛しよう体の前翼裸錠型
と後翼操舵型のものにおける機体応答を示す線図である
。
１・・・飛しよう体、 ２・・・前謔、３・・・後
翼、 ４ａ、４ｂ・・・操舵装置、５・・・推進装置、
７・・・制御装置。
３１図
第２区No. 1N is an explanatory diagram of an embodiment of the present invention. , @, and 0 are explanatory diagrams of conventional flying bodies, respectively, and Fig. 4 is a diagram showing the airframe response of conventional flying bodies of the front wing locking type and the rear wing steering type. 1.・Flying body, 2... Front wing, 3... Rear wing, 4a, 4b... Steering device, 5... Propulsion device,
7...Control device. Figure 31 Ward 2
Claims (1)
を特徴とする前翼と後翼とを備えた飛しよう体。A flying object having a front wing and a rear wing, characterized by being equipped with a steering device that operates the front wing and the rear wing independently.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8532588A JPH01260299A (en) | 1988-04-08 | 1988-04-08 | Missile equipped with fore wing and rear wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8532588A JPH01260299A (en) | 1988-04-08 | 1988-04-08 | Missile equipped with fore wing and rear wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH01260299A true JPH01260299A (en) | 1989-10-17 |
Family
ID=13855475
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8532588A Pending JPH01260299A (en) | 1988-04-08 | 1988-04-08 | Missile equipped with fore wing and rear wing |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01260299A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11624594B1 (en) | 2020-03-31 | 2023-04-11 | Barron Associates, Inc. | Device, method and system for extending range and improving tracking precision of mortar rounds |
-
1988
- 1988-04-08 JP JP8532588A patent/JPH01260299A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11624594B1 (en) | 2020-03-31 | 2023-04-11 | Barron Associates, Inc. | Device, method and system for extending range and improving tracking precision of mortar rounds |
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