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JPH0926300A - Wing stretching mechanism of missile - Google Patents

Wing stretching mechanism of missile

Info

Publication number
JPH0926300A
JPH0926300A JP17340095A JP17340095A JPH0926300A JP H0926300 A JPH0926300 A JP H0926300A JP 17340095 A JP17340095 A JP 17340095A JP 17340095 A JP17340095 A JP 17340095A JP H0926300 A JPH0926300 A JP H0926300A
Authority
JP
Japan
Prior art keywords
wing
flying
force
missile
opening
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.)
Granted
Application number
JP17340095A
Other languages
Japanese (ja)
Other versions
JP3532661B2 (en
Inventor
Toshinori Yugawa
俊則 湯川
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Toshiba Corp
Original Assignee
Toshiba Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Toshiba Corp filed Critical Toshiba Corp
Priority to JP17340095A priority Critical patent/JP3532661B2/en
Publication of JPH0926300A publication Critical patent/JPH0926300A/en
Application granted granted Critical
Publication of JP3532661B2 publication Critical patent/JP3532661B2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Abstract

PROBLEM TO BE SOLVED: To realize secure operation control by disposing a rotary shaft of a wing body inclined so as for it to be stretched in the direction of flying with respect to the axis of a missile, structure body. SOLUTION: A rotary shaft 12 of a wing body 11 is rotatably disposed on a missile 10 having an inclination angle α expanding in the direction of flying with respect to the axis of the missile. Further, a spring structure 13 is assembled such that a biassing force is applied in the opening direction of the wing, and the spring mechanism is folded and accommodated at an expansion position and is mounted on a shooting bench. Once the missile 10 is shot, a biassing force of the spring mechanism 13 is applied in the direction of the expansion of the wing, and simultaneously relative air following the flying is applied to the wing body 11 at an incident angle βwith respect to the machine axis whereby the insident angle β is reduced by the inclination angle α of the rotary shaft 12 of the wing body 11, and force preventing rotating force in the expansion direction is correspondingly produced. Accordingly, only with the biassing force capable of cancellation of the foregoing force secure wing expansion operation of the wing body 11 is ensured, and hence the spring mechanism 13 is miniaturized and further highly reliable secure wing expansion operation is ensured.

Description

【発明の詳細な説明】Detailed Description of the Invention

【0001】[0001]

【発明の属する技術分野】この発明は、例えば対空ミサ
イル等の飛翔体に係り、特にその開閉式の尾翼等の翼を
所定の位置に開くのに用いられる開翼機構に関する。
BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a projectile such as an anti-aircraft missile, and more particularly to an opening wing mechanism used to open a wing such as an open / close tail fin to a predetermined position.

【0002】[0002]

【従来の技術】従来、この種の飛翔体の開翼機構におい
ては、図3及び図4に示すように翼本体1の回転軸2を
飛翔体本体3に対して機体軸と略平行に配設し、この回
動軸2には、開翼用のばね機構4が組付けられる。そし
て、この飛翔体本体3は、ばね機構4の付勢力に抗して
図示しない発射台に装着される。3飛翔体本体が発射台
(図示せず)から発射されて飛翔を開始すると、飛翔体
本体3の翼本体1は、ばね機構4により閉位置から開位
置に回動付勢されて飛翔体本体3の所定の位置に配置さ
れ、該飛翔体本体3の安定飛翔等に供される。
2. Description of the Related Art Conventionally, in a wing opening mechanism for a flying body of this type, as shown in FIGS. 3 and 4, the rotary shaft 2 of the wing body 1 is arranged substantially parallel to the body axis of the flying body 3. A spring mechanism 4 for opening the blade is attached to the rotating shaft 2. Then, the projectile body 3 is mounted on a launch pad (not shown) against the biasing force of the spring mechanism 4. 3 When the flying body main body is launched from a launch pad (not shown) and starts flying, the wing body 1 of the flying body main body 3 is rotationally biased from the closed position to the open position by the spring mechanism 4 and is thus propelled. 3 is provided at a predetermined position, and is used for stable flight of the flying body 3 and the like.

【0003】ところが、上記飛翔体の開翼機構では、翼
本体1の確実な開動作を実現するのに、飛翔時に、飛翔
体本体3に加わる横風等の外乱を考慮して、そのばね機
構4の付勢力を比較的大きく設定しなければならないた
めに、動作制御の信頼性を高めると、大形となると共
に、重量の増加を招くという問題を有する。特に、係る
問題は、飛翔体の高速化を図るような場合、重量の軽量
化が強く要求されることで重大である。
However, in the above-described flying body wing opening mechanism, in order to realize the reliable opening operation of the wing body 1, the spring mechanism 4 is provided in consideration of the disturbance such as a side wind applied to the flying body body 3 during flight. Since it is necessary to set the urging force of No. 2 to be relatively large, there is a problem that if the reliability of operation control is increased, the size becomes large and the weight is increased. In particular, such a problem is serious because the weight is strongly required to be reduced in order to increase the speed of the flying object.

【0004】[0004]

【発明が解決しようとする課題】以上述べたように、従
来の飛翔体の開翼機構では、信頼性の高い動作制御を実
現すると、大形となると共に、重量が重くなるという問
題を有する。この発明は上記の事情に鑑みてなされたも
ので、構成簡易にして、確実な動作制御を実現し得、且
つ小形・軽量化の促進を図り得るようにした飛翔体の開
翼機構を提供することを目的とする。
As described above, the conventional wing opening mechanism for a flying object has a problem that it becomes large in size and heavy in weight when realizing highly reliable operation control. The present invention has been made in view of the above circumstances, and provides a wing opening mechanism for a flying object, which has a simple structure, can realize reliable operation control, and can promote miniaturization and weight reduction. The purpose is to

【0005】[0005]

【課題を解決するための手段】この発明は、飛翔体本体
に設けられ、機体軸に対して飛翔方向に広がるように傾
斜された回動軸を有し、前記飛翔体本体の飛翔前に閉位
置を司る開閉自在な翼本体を備えて飛翔体の開翼機構を
構成した。
According to the present invention, there is provided a flying body main body, which has a rotating shaft tilted so as to spread in a flight direction with respect to a body axis, and is closed before the flying of the flying body main body. An open / close mechanism for the flying object was constructed with a wing body that controls the position.

【0006】上記構成によれば、翼本体には、該翼本体
の回動軸の傾斜をαとすると、αによる開翼方向の回動
力が加わることにより、これに開動作を妨げる相対風が
入射角βで翼本体に加わった場合でもβによる開翼動作
を妨げる力は、αの効果によって相殺され、開方向の回
動を妨げる力は、(β−α)によるものへと低減でき
る。ここで、α>βの状態となるようにせしめれば、
(β−α)は、負、すなわち開翼方向の回動力が勝るこ
とにより、翼本体の確実な開翼動作が可能となる。
According to the above construction, when the inclination of the rotation axis of the blade body is α, the rotating force in the blade opening direction due to α is applied to the blade body, so that relative wind that impedes the opening operation is applied to the blade body. Even when applied to the blade main body at the incident angle β, the force that interferes with the blade opening operation due to β is canceled by the effect of α, and the force that interferes with the rotation in the opening direction can be reduced to that due to (β−α). Here, if it is set so that α> β,
(Β−α) is negative, that is, the turning force in the opening direction is superior, so that the opening operation of the blade body can be reliably performed.

【0007】また、この発明は、飛翔体本体に設けら
れ、機体軸に対して飛翔方向に広がるように傾斜された
回動軸を有し、前記飛翔体本体の飛翔前に閉位置を司る
開閉自在な翼本体と、この翼本体を開方向に付勢し、前
記飛翔体本体が飛翔された状態で前記翼本体を開翼する
付勢手段とを備えて飛翔体の開翼機構を構成した。
Further, according to the present invention, there is provided a main body of the flying body, which has a rotating shaft tilted so as to spread in the flying direction with respect to the axis of the body, and which opens and closes the closed position before the flying of the main body of the flying body. A wing opening mechanism for a flying object was configured by including a free wing main body and an urging means that urges the wing main body in the opening direction and opens the wing main body in a state where the flying body main body is flying. .

【0008】上記構成によれば、翼本体は、相対風が飛
翔体本体の機体軸に対して入射角βで翼本体に加わった
場合、翼本体の回動軸の傾斜角をαとすると、翼本体の
回動軸の傾斜角αだけ入射角βが軽減された状態とな
り、開方向の回動を妨げる力は、(β−α)だけとな
る。従って、(β−α)だけ開方向に付勢力を与えるだ
けで、翼本体の確実な開翼動作が可能となり、付勢手段
の小形化を図ったうえで、信頼性の高い確実な開翼動作
が実現される。
According to the above construction, when relative wind is applied to the wing body at an incident angle β with respect to the body axis of the flying body main body, the inclination angle of the rotation axis of the wing body is α The incident angle β is reduced by the inclination angle α of the rotation axis of the blade body, and the force that prevents the rotation in the opening direction is only (β−α). Therefore, only by applying an urging force in the opening direction by (β-α), the wing body can be reliably opened, and the urging means can be downsized and the blade can be released reliably and reliably. The operation is realized.

【0009】[0009]

【発明の実施の形態】以下、この発明の実施の形態につ
いて、図面を参照して詳細に説明する。図1及び図2は
この発明の一実施の形態に係る飛翔体の開翼機構を示す
もので、飛翔体本体10には、翼本体11の回動軸12
が機体軸に対して飛翔方向に広がった傾斜角αを有して
回動自在に配設される。この翼本体11は、その回動軸
12にばね機構13が開方向に付勢力が付与するように
組付け配置され、このばね機構13の付勢力に抗して飛
翔体本体10の閉位置に折畳み収容されて図示しない発
射台に装着される。
Embodiments of the present invention will be described below in detail with reference to the drawings. 1 and 2 show a wing opening mechanism for a flying object according to an embodiment of the present invention. The flying object main body 10 includes a rotary shaft 12 of a wing main body 11.
Is rotatably arranged with an inclination angle α that spreads in the flight direction with respect to the body axis. The wing body 11 is assembled and arranged so that the spring mechanism 13 applies an urging force to the rotating shaft 12 in the opening direction, and the wing body 11 is placed at the closed position of the projectile body 10 against the urging force of the spring mechanism 13. It is folded and accommodated and mounted on a launch pad (not shown).

【0010】上記構成において、飛翔体本体10は、上
記発射台(図示せず)にばね機構13の付勢力に抗して
翼本体11を閉方向に折畳んだ状態で装着される。そし
て、飛翔体本体10は、上記発射台(図示せず)から発
射されると、その翼本体11にばね機構13の付勢力が
開方向に付与される。同時に、翼本体11には、飛翔に
伴う相対風が付与される。この相対風は、回動軸12の
傾斜角αの作用により、開方向の回動力となって翼本体
11に付与され、ばね機構13による付勢力と協働して
該翼本体11を開位置に回動する。
In the above structure, the flying body 10 is mounted on the launch pad (not shown) with the wing body 11 folded in the closing direction against the biasing force of the spring mechanism 13. When the projectile body 10 is launched from the launch pad (not shown), the urging force of the spring mechanism 13 is applied to the wing body 11 in the opening direction. At the same time, the wing body 11 is provided with relative wind accompanying the flight. This relative wind is applied to the blade main body 11 as a rotational force in the opening direction by the action of the inclination angle α of the rotary shaft 12, and cooperates with the biasing force of the spring mechanism 13 to open the blade main body 11 in the open position. Turn to.

【0011】そして、相対風が飛翔体本体10の機体軸
に対して入射角βで加わった場合には、翼本体11の回
動軸12の傾斜角αだけ入射角βが軽減された状態とな
り、その(β−α)だけ開方向に回動力を妨げる力が発
生されたのと同様の作用を奏する。そのため、ばね機構
13の付勢力としては、(β−α)だけ開方向に回動力
を妨げる力を打消すことが可能な付勢力を与えるだけ
で、翼本体11の開翼動作が行われる。
When the relative wind is applied to the airframe axis of the flying body 10 at the incident angle β, the incident angle β is reduced by the inclination angle α of the rotating shaft 12 of the wing body 11. , And (β-α) produces the same effect as the force that impedes the turning force in the opening direction is generated. Therefore, as the urging force of the spring mechanism 13, the wing opening operation of the wing body 11 is performed only by providing the urging force capable of canceling the force that impedes the turning force in the opening direction by (β−α).

【0012】このように、上記飛翔体の開翼機構は、翼
本体11の回動軸12を飛翔体本体10に、機体軸に対
して飛翔方向に広がるように傾斜させて配設して、この
翼本体11をばね機構13で開方向に付勢するように構
成した。
As described above, in the wing opening mechanism of the flying body, the rotating shaft 12 of the wing body 11 is arranged on the flying body body 10 so as to be inclined with respect to the body axis in the flying direction. The wing body 11 is configured to be biased in the opening direction by the spring mechanism 13.

【0013】これによれば、相対風が飛翔体本体10の
機体軸に対して入射角βで翼本体11に加わった場合、
翼本体11の回動軸12の傾斜角αだけ入射角βが軽減
された状態となり、その(β−α)だけ開方向に回動力
を妨げる力が発生される。従って、(β−α)だけ開方
向に回動力を妨げる力を打消すことが可能な付勢力を与
えるだけで、翼本体11の確実な開翼動作が可能とな
り、ばね機構13の小形化を図ったうえで、信頼性の高
い確実な開翼動作が実現される。
According to this, when the relative wind is applied to the wing body 11 at the incident angle β with respect to the body axis of the flying body 10,
The incident angle β is reduced by the inclination angle α of the rotating shaft 12 of the blade body 11, and a force that impedes the turning force in the opening direction is generated by (β−α). Therefore, the wing body 11 can be reliably opened by only providing the biasing force capable of canceling the force that impedes the rotational force in the opening direction by (β−α), and the spring mechanism 13 can be downsized. After achieving this, reliable and reliable opening operation is realized.

【0014】なお、上記実施例では、翼本体11の回動
軸12にばね機構13を組付け配置するように構成した
場合で説明したが、これに限ることなく、例えば、相対
風の入射角βが回動軸12の傾斜角αより小さく設定可
能な場合には、ばね機構13を設けなくとも信頼性の高
い開翼動作が可能となる。
In the above embodiment, the case where the spring mechanism 13 is assembled and arranged on the rotary shaft 12 of the blade body 11 has been described, but the invention is not limited to this, and for example, the incident angle of relative wind can be set. When β can be set smaller than the inclination angle α of the rotating shaft 12, highly reliable blade opening operation can be performed without providing the spring mechanism 13.

【0015】さらに、回動軸12の傾斜角αは、翼本体
11に加わる慣性力を開翼を促進する回動力として作用
せしめられる。すなわち、飛翔体本体10に加わる前向
きの飛翔方向加速度が存在する場合、翼本体11には、
翼本体質量と飛翔方向加速度の積で示される大きさの慣
性力Fが飛翔体方向加速度と逆方向に発生するが、この
慣性力Fの回動軸と直角な成分Fsinαが開翼方向の
回動力として開翼の促進に作用する。
Further, the inclination angle α of the rotating shaft 12 causes the inertial force applied to the blade main body 11 to act as a turning force for promoting the blade opening. That is, when there is a forward flight direction acceleration applied to the flying body 10,
An inertial force F having a magnitude represented by the product of the wing body mass and the flight direction acceleration is generated in the direction opposite to the flight body direction acceleration, and a component Fsinα of the inertia force F perpendicular to the rotation axis is the rotational force in the opening direction. It acts as a power source to promote the opening of wings.

【0016】よって、この発明は、前述の相対風の入射
角の軽減効果のみ着目した実施の形態に限ることなく、
上記の慣性力による開翼の促進作用を積極的に利用する
ことも可能である。
Therefore, the present invention is not limited to the above-described embodiment in which only the effect of reducing the incident angle of the relative wind is focused.
It is also possible to positively utilize the above-mentioned action of promoting the blade opening by the inertial force.

【0017】例えば翼本体11にウエイト部材を取付け
て、翼本体11の質量を増大させ、この結果、増大する
翼本体11の慣性力を積極的に利用して開翼を実現する
ように構成しても良い。この場合には、ウエイト部材
は、例えば翼本体11の開翼動作に連動して開位置で翼
本体11から離脱するように構成される。これにより、
ウエイト部材による質量増加としては、飛翔初期のみと
なることで、飛翔特性に悪影響を及ぼすことなく、しか
も、開翼動作の信頼性の点においても、より有効な効果
が期待される。
For example, a weight member is attached to the wing body 11 to increase the mass of the wing body 11, and as a result, the increased inertial force of the wing body 11 is positively used to realize the opening blade. May be. In this case, the weight member is configured to separate from the wing body 11 at the open position in conjunction with the wing body 11 opening operation. This allows
Since the mass increase due to the weight member is only in the initial stage of flight, a more effective effect is expected in terms of the reliability of the opening operation without adversely affecting the flight characteristics.

【0018】なお、ウエイト部材の離脱手段としては、
翼本体11の開翼動作時の衝撃を利用したり、飛翔時の
空気抵抗を利用したり、あるいは空力加熱で発生する熱
量を利用して行うことが可能である。よって、この発明
は、上記実施の形態に限ることなく、その他、この発明
の要旨を逸脱しない範囲で種々の実施の形態を実施し得
ることは勿論である。
As a means for removing the weight member,
It is possible to use the impact when the wing body 11 is opened, the air resistance during flight, or the amount of heat generated by aerodynamic heating. Therefore, it is needless to say that the present invention is not limited to the above-described embodiment, and various other embodiments can be implemented within the scope not departing from the gist of the present invention.

【0019】[0019]

【発明の効果】以上詳述したように、この発明によれ
ば、構成簡易にして、確実な動作制御を実現し得、且つ
小形・軽量化の促進を図り得るようにした飛翔体の開翼
機構を提供することができる。
As described above in detail, according to the present invention, the structure of the flying wing of the flying object is simplified, the reliable operation control can be realized, and the miniaturization and the weight reduction can be promoted. A mechanism can be provided.

【図面の簡単な説明】[Brief description of drawings]

【図1】この発明の一実施の形態に係る飛翔体の開翼機
構の概念を示した図。
FIG. 1 is a diagram showing the concept of a wing opening mechanism for a flying object according to an embodiment of the present invention.

【図2】図1を前面側より見た状態を示した図。FIG. 2 is a diagram showing a state in which FIG. 1 is viewed from the front side.

【図3】従来の飛翔体の開翼機構の概念を示した図。FIG. 3 is a view showing the concept of a conventional wing opening mechanism for a flying object.

【図4】図3の前面側より見た状態を示した図。FIG. 4 is a diagram showing a state viewed from the front side of FIG.

【符号の説明】[Explanation of symbols]

10…飛翔体本体。 11…翼本体。 12…回動軸。 13…ばね機構。 10 ... the flying body. 11 ... Wing body. 12 ... Rotation axis. 13 ... Spring mechanism.

Claims (4)

【特許請求の範囲】[Claims] 【請求項1】 飛翔体本体に設けられ、機体軸に対して
飛翔方向に広がるように傾斜された回動軸を有し、前記
飛翔体本体の飛翔前に閉位置を司る開閉自在な翼本体を
具備した飛翔体の開翼機構。
1. A wing body which is provided in a flying body and has a rotating shaft tilted so as to spread in a flight direction with respect to a body axis, and which can be opened and closed to control a closed position before the flying of the flying body. A wing opening mechanism for a flying object.
【請求項2】 飛翔体本体に設けられ、機体軸に対して
飛翔方向に広がるように傾斜された回動軸を有し、前記
飛翔体本体の飛翔前に閉位置を司る開閉自在な翼本体
と、 この翼本体を開方向に付勢し、前記飛翔体本体が飛翔さ
れた状態で前記翼本体を開翼する付勢手段とを具備した
飛翔体の開翼機構。
2. A wing body, which is provided on the flying body main body, has a rotating shaft tilted so as to spread in a flight direction with respect to an axis of the aircraft, and can be opened and closed to control a closed position before the flying of the flying body main body. And a wing opening mechanism for urging the wing main body in the opening direction to open the wing main body in a state in which the main body of the flying body is flown.
【請求項3】 前記翼本体には、ウエイト部材が設けら
れることを特徴とする請求項1又は2記載の飛翔体の開
閉機構。
3. The aircraft opening / closing mechanism according to claim 1, wherein a weight member is provided on the wing body.
【請求項4】 前記ウエイト部材は、前記翼本体に対し
て閉位置で結合され、前記翼本体の司る開位置において
離脱されることを特徴とする請求項3記載の飛翔体の開
翼機構。
4. The wing opening mechanism for a flying vehicle according to claim 3, wherein the weight member is coupled to the wing body at a closed position and is separated at an open position controlled by the wing body.
JP17340095A 1995-07-10 1995-07-10 Flying mechanism of flying object Expired - Fee Related JP3532661B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP17340095A JP3532661B2 (en) 1995-07-10 1995-07-10 Flying mechanism of flying object

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP17340095A JP3532661B2 (en) 1995-07-10 1995-07-10 Flying mechanism of flying object

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