JPS63298000A - Missile - Google Patents
MissileInfo
- Publication number
- JPS63298000A JPS63298000A JP13224587A JP13224587A JPS63298000A JP S63298000 A JPS63298000 A JP S63298000A JP 13224587 A JP13224587 A JP 13224587A JP 13224587 A JP13224587 A JP 13224587A JP S63298000 A JPS63298000 A JP S63298000A
- Authority
- JP
- Japan
- Prior art keywords
- flying object
- aircraft
- parachute
- attitude
- flying
- 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
- 230000005484 gravity Effects 0.000 description 10
- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 230000000087 stabilizing effect Effects 0.000 description 5
- 230000006641 stabilisation Effects 0.000 description 4
- 238000011105 stabilization Methods 0.000 description 4
- 241000220317 Rosa Species 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 206010034719 Personality change Diseases 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
〔産業上の利用分野〕
この発明は飛行体に関し、特に気象観測や軍事上の目的
をもって飛行する飛行体の経路・姿勢を安定化する経路
・姿勢安定方式に関するものである。[Detailed Description of the Invention] [Field of Industrial Application] This invention relates to flying vehicles, and in particular to a path/attitude stabilization method for stabilizing the path/attitude of a flying vehicle for meteorological observation or military purposes. be.
従来技術の例として良く知られたパラシュートの姿勢安
定効果を第４図を用いて説明する。第４図において、ｌ
は観測機器等のロード、２はパラシュートのキャノピ−
１３はパラシュートの支持網、４は支持点、５はロード
の重心、６はキャノピ−２の空力中心である。The attitude stabilizing effect of a well-known parachute as an example of the prior art will be explained with reference to FIG. In Figure 4, l
2 is the load of observation equipment, etc., and 2 is the parachute canopy.
13 is a support network for the parachute, 4 is a support point, 5 is the center of gravity of the load, and 6 is the aerodynamic center of the canopy 2.
バラシェードでは、ロードの重心５に作用する重力１１
と、パラシェードの空力中心６に作用する抗力りとがそ
れぞれ支持点４を中心に反対方向に作用し、これにより
パラシュートの姿勢を鉛直に安定化させるモーメントを
作り出す、なお、ここでは説明の便宜上キャノピ−２お
よび支持網３に作用する重力、およびロード１に作用す
る抗力は省略している。In the rose shade, the gravity 11 acting on the load's center of gravity 5
and the drag force acting on the aerodynamic center 6 of the parashade act in opposite directions centering on the support point 4, thereby creating a moment that vertically stabilizes the attitude of the parachute. The gravitational force acting on the canopy 2 and the support net 3, and the drag force acting on the load 1 are omitted.
次にミサイルなど一般の飛行体の姿勢安定原理について
第５図（ａ）、 （ｂ）を用いて説明する。第５図にお
いて、７は飛行体、８は飛行体の機軸、９は飛行体の重
心、１０は空力中心である。飛行体７は一様流１１の中
にあるものとする。このとき一様流１１によって飛行体
が受ける力１２をｆとすると、これは空力中心１０に作
用する。一様流１１と機軸８のなす角度αを迎え角と呼
ぶ０重心９と空力中心１１の間の距離をΔＸとすれば、
空気力ｆは重心９のまわりにΔｘ ｓｉｎαのモーメン
トアームを有し、Ｍ−ｆΔｘｓｉｎαの頭下げモーメン
トを発生する。このように空気力学的に平衡状態（トリ
ム状態と呼ばれる）にある飛行体においては、迎え角α
が発生するとそれを打消すような方向にモーメントが働
き、進行方向が常に一様流１１の方向になるよう平衡す
る（これを風見安定と呼ぶ）、このためには重心９は常
に空力中心１０の前方になくてはならない、なお、ここ
では説明の便宜上、飛行体に作用する抗力、重力、揚力
は省略している。Next, the principle of stabilizing the attitude of general flying objects such as missiles will be explained using Figures 5 (a) and (b). In FIG. 5, 7 is the flying object, 8 is the axis of the flying object, 9 is the center of gravity of the flying object, and 10 is the aerodynamic center. It is assumed that the flying object 7 is in a uniform flow 11. At this time, if the force 12 exerted on the flying object by the uniform flow 11 is f, this acts on the aerodynamic center 10. The angle α between the uniform flow 11 and the aircraft axis 8 is called the angle of attack.0 If the distance between the center of gravity 9 and the aerodynamic center 11 is ΔX,
The aerodynamic force f has a moment arm of Δx sin α around the center of gravity 9 and produces a head-down moment of M−f Δx sin α. In this way, for a flying vehicle in an aerodynamically balanced state (called a trim state), the angle of attack α
When a moment occurs, a moment acts in a direction that cancels it, and equilibrium is maintained so that the traveling direction is always in the direction of the uniform flow 11 (this is called weathervane stability). To this end, the center of gravity 9 must always be aligned with the aerodynamic center 10 For convenience of explanation, the drag, gravity, and lift forces acting on the aircraft are omitted here.
次に飛行体の姿勢、経路を第３図を用いて説明する。飛
行体７を水平に速度■。で射出して、特に揚力を発生さ
せる制御を行なわなければ、重心加速度の作用により速
度ベクトルは次第に下方を向き、従って経路が下に向い
てくる。一様流の方向は速度ベクトルの逆方向になるの
で、もし飛行体が前記の風見安定を有せばその姿勢も次
第に下方を向く。Next, the attitude and path of the aircraft will be explained using FIG. The speed of the flying object 7 horizontally ■. If the jet is ejected with no particular control to generate lift, the velocity vector will gradually point downward due to the action of the acceleration of the center of gravity, and therefore the path will turn downward. Since the direction of the uniform flow is opposite to the velocity vector, if the flying object has the above-mentioned weathervane stability, its attitude will gradually turn downward.
このように従来の飛行体では時間の経過とともに速度ベ
クトルが下方を向き姿勢を水平に保つことができなかワ
た。また射出する方向が航空機の進行方向に沿っていれ
ば、はじめからトリム状態を実現できるが、発射機構上
の関係からそれができない場合や、また発射直後大きな
外乱モーメントを受ける場合など、飛行体が回転してし
まい、トリム状態になるまでに長時間かかり、かつ速度
を失ってしまう等の不具合があった。In this way, in conventional flying vehicles, the velocity vector turns downward over time, making it impossible to maintain a horizontal attitude. Furthermore, if the direction of ejection is along the direction of flight of the aircraft, it is possible to achieve a trim state from the beginning, but if this is not possible due to the launch mechanism, or if the aircraft is subjected to a large disturbance moment immediately after launch, the aircraft There were problems such as spinning, taking a long time to reach the trim state, and losing speed.
この発明は上記のような問題点を解決するためになされ
たもので、射出俊速やかに姿勢を安定し、かつ一定時間
その経路および姿勢を水平に近く維持することができる
飛行体を提供することを目的とする。This invention was made in order to solve the above-mentioned problems, and it is an object of the present invention to provide a flying object that can quickly stabilize its attitude during ejection, and maintain its path and attitude close to horizontal for a certain period of time. With the goal.
この発明に係る飛行体は、飛行体本体の後端に、飛行体
の射出により開傘して飛行体の飛行方向を安定させる小
型のバラシェードを取り付け、さらに上記飛行体本体の
後部に、飛行方向が上述の如く安定せられた後点火して
飛行体本体を加速させるロケットモータを搭載したもの
である。The flying object according to the present invention has a small rose shade attached to the rear end of the flying object body, which opens when the flying object is ejected and stabilizes the flight direction of the flying object, and further has a small rose shade attached to the rear end of the flying object body. It is equipped with a rocket motor that is ignited to accelerate the aircraft body after the direction has been stabilized as described above.
この発明においては、飛行体本体の後端に飛行体の射出
により開傘する小型のパラシュートを取り付け、さらに
飛行体本体を加速させるロケットモータを搭載したから
、射出直後にパラシュートを開傘して、前記に説明した
パラシュートの姿勢安定効果により瞬時に飛行体の姿勢
をその速度ベクトルの方向に安定させることができ、し
かもその直後パラシュートを切離してロケットモータを
点火して増速すれば、飛行体の失われた速度を回復でき
、一定時間水平に近い姿勢を維持できる。In this invention, a small parachute that opens when the flying object is ejected is attached to the rear end of the flying object, and a rocket motor that accelerates the flying object is installed, so that the parachute opens immediately after ejection. Due to the attitude stabilization effect of the parachute explained above, the attitude of the flying object can be instantly stabilized in the direction of its velocity vector.Moreover, if the parachute is immediately detached and the rocket motor is ignited to increase the speed, the flying object's attitude can be stabilized instantly. It can recover lost speed and maintain a near-horizontal posture for a certain period of time.
以下、この発明の一実施例を図について説明する。 An embodiment of the present invention will be described below with reference to the drawings.
第１図は本発明の一実施例による飛行体を示し、図にお
いて、７は飛行体本体、１３は飛行体本体７の後端に取
り付けられ飛行体の射出により開傘して飛行体の飛行方
向を安定させる小型のパラシュート、１４はパラシュー
ト１３の着脱部でこれは粘性抵抗を有するシリンダ内に
挿入されている。FIG. 1 shows a flying object according to an embodiment of the present invention. In the figure, 7 is the main body of the flying object, 13 is attached to the rear end of the main body 7 of the flying object, and when the flying object is ejected, the umbrella opens and the flying object flies. A small parachute 14 for stabilizing the direction is a detachable part of the parachute 13, which is inserted into a cylinder having viscous resistance.
１５は飛行体本体７の後部に搭載され飛行体本体７を加
速させるロケットモータで、その点火機構はパラシェー
ドの開傘シラツクを利用して機械的に、あるいは電気的
に行うものが考えられるが、このような機構はミサイル
その他で既に利用されているものもあり、特に新しいも
のではない。15 is a rocket motor that is mounted on the rear of the aircraft body 7 and accelerates the aircraft body 7, and its ignition mechanism may be operated mechanically or electrically using the opening mechanism of the parashade. This type of mechanism is already used in missiles and other devices, so it is not particularly new.
次に第２図を用いて作用効果について説明する。Next, the functions and effects will be explained using FIG. 2.
航空機１６から射出された飛行体７は、当初航空機の速
度ベクトルＶＩ＋射出時の速度ベクトルｖｔの合ベクト
ル■。の速度ベクトルを有しており、また姿勢は不安定
で回転している場合も考えられるが、パラシュート１３
が開傘すると瞬間的に姿勢はｖｏの方向に安定する。そ
の直後にパラシュート１３を切離し、更に増速するため
にロケットモータ１５に点火する。この後空気抵抗によ
る速度の減少、及び重心加速度により経路角及び姿勢は
漸次下方を向いてくるが、その間一定時間はぼ水平に近
い姿勢と経路角を保つことができる。The flying object 7 ejected from the aircraft 16 has a sum vector (■) of the initial velocity vector VI of the aircraft + the velocity vector VT at the time of ejection. The parachute 13 has a velocity vector of
When the umbrella opens, the posture becomes instantly stable in the vo direction. Immediately after that, the parachute 13 is separated and the rocket motor 15 is ignited to further increase the speed. After this, the path angle and attitude gradually turn downward due to the decrease in speed due to air resistance and the acceleration of the center of gravity, but during this period the almost horizontal attitude and path angle can be maintained for a certain period of time.
またこの姿勢及び経路の安定時間はロケットモータ１５
により与える速度を増せば長くなる。Also, the stabilization time of this attitude and path is the rocket motor 15
If the speed applied is increased, the length will be increased.
なお、パラシュート着脱部１４は、簡単には第１図に示
すような粘性抵抗を有するシリンダで良いが、これはパ
ラシュート１３の開傘シリンダを利用して、機械的にあ
るいはｔ磁的にパラシュートが飛行体本体７から゛離脱
するようにしてもよい。The parachute attaching/detaching section 14 may simply be a cylinder having viscous resistance as shown in FIG. It may also be configured to separate from the aircraft body 7.
以上のように、この発明に係る飛行体によれば、飛行体
本体の後端に、飛行体の射出により開傘するパラシュー
トを取り付け、さらに飛行体本体の後部に、飛行体本体
を加速させるロケットモータを搭載したので、簡単な機
構により射出後一定時間その経路及び姿勢を水平近くに
安定させて飛行することができる効果がある。As described above, according to the flying object of the present invention, a parachute that opens when the flying object is ejected is attached to the rear end of the flying object, and a rocket that accelerates the flying object is attached to the rear of the flying object. Since it is equipped with a motor, it has the effect of being able to fly by keeping its path and attitude stable near horizontal for a certain period of time after ejection using a simple mechanism.
第１図は本発明の一実施例による飛行体の構成の説明図
、第２図は上記実施例による射出飛行体の動作を示す図
、第３図は射出飛行体の経路及び姿勢変化を示す図、第
４図はパラシュートの姿勢安定効果を示す図、第５図は
一般の飛行体の姿勢安定原理を示す図である。
図において、７は飛行体本体、１３はパラシュート、１
４はパラシュートの着脱部、１５はロケットモータであ
る。
なお図中同一符号は同−又は相当部分を示す。FIG. 1 is an explanatory diagram of the configuration of a flying vehicle according to an embodiment of the present invention, FIG. 2 is a diagram showing the operation of the ejecting vehicle according to the above embodiment, and FIG. 3 is a diagram showing the path and attitude change of the ejecting vehicle according to the above embodiment. FIG. 4 is a diagram showing the attitude stabilizing effect of a parachute, and FIG. 5 is a diagram showing the principle of attitude stabilization of a general flying object. In the figure, 7 is the aircraft body, 13 is the parachute, 1
4 is a parachute attaching/detaching part, and 15 is a rocket motor. Note that the same reference numerals in the figures indicate the same or equivalent parts.
Claims (2)
開傘して飛行体の飛行方向を安定させる小型のパラシュ
ートと、 上記飛行体本体の後部に搭載され、飛行方向が上記の如
く安定せられた後点火して飛行体本体を加速させるロケ
ットモータとを備えたことを特徴とする飛行体。(1) In a flying vehicle ejected from an aircraft in the air, a small parachute is attached to the rear end of the flying vehicle body and opens upon ejection of the flying vehicle to stabilize the flight direction of the flying vehicle; A rocket motor is mounted on the rear of the aircraft and is ignited to accelerate the aircraft after the flight direction has been stabilized as described above.
ンダにより飛行体本体に取り付けられ、開傘後所定時間
経過した時に飛行体本体から離脱するものであることを
特徴とする特許請求の範囲第１項記載の飛行体。(2) The small parachute is attached to the aircraft body by a cylinder having viscous resistance, and is detached from the aircraft body after a predetermined time has elapsed after the parachute is opened. The aircraft described.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13224587A JPS63298000A (en) | 1987-05-28 | 1987-05-28 | Missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13224587A JPS63298000A (en) | 1987-05-28 | 1987-05-28 | Missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63298000A true JPS63298000A (en) | 1988-12-05 |
Family
ID=15076762
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP13224587A Pending JPS63298000A (en) | 1987-05-28 | 1987-05-28 | Missile |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63298000A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03113257U (en) * | 1990-01-25 | 1991-11-19 |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5440499A (en) * | 1977-09-03 | 1979-03-29 | Fuji Heavy Ind Ltd | Method of restoring unmanned aircraft |
-
1987
- 1987-05-28 JP JP13224587A patent/JPS63298000A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5440499A (en) * | 1977-09-03 | 1979-03-29 | Fuji Heavy Ind Ltd | Method of restoring unmanned aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03113257U (en) * | 1990-01-25 | 1991-11-19 |
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