JPH1194500A - Storage cover separation device of flying object - Google Patents
Storage cover separation device of flying objectInfo
- Publication number
- JPH1194500A JPH1194500A JP26163797A JP26163797A JPH1194500A JP H1194500 A JPH1194500 A JP H1194500A JP 26163797 A JP26163797 A JP 26163797A JP 26163797 A JP26163797 A JP 26163797A JP H1194500 A JPH1194500 A JP H1194500A
- Authority
- JP
- Japan
- Prior art keywords
- storage cover
- separation
- steering
- command signal
- thruster
- 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- Withdrawn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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/22—Missiles having a trajectory finishing below water surface
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B17/00—Rocket torpedoes, i.e. missiles provided with separate propulsion means for movement through air and through water
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
- F42B19/46—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means adapted to be launched from aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は水中航走体等を搭載
し、収納カバーを有する飛しよう体に適用される、飛し
よう体の収納カバー分離装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying object storage cover separating apparatus which is applied to a flying object having an underwater vehicle and a storage cover.
【０００２】[0002]
【従来の技術】従来の飛しよう体の収納カバー分離装置
を図９〜図１２により説明する。飛しよう体本体７は前
部に水中航走体５を搭載している。そして水中航走体５
は縦に２分割した収納カバー１で覆われている（図９、
図１０参照）。2. Description of the Related Art A conventional flying object storage cover separating apparatus will be described with reference to FIGS. The flying object body 7 has an underwater vehicle 5 mounted on its front. And underwater vehicle 5
Is covered by a vertically divided storage cover 1 (FIG. 9,
(See FIG. 10).
【０００３】収納カバーの前端部には分離用スラスタ２
が配置され、本体７のオートパイロット装置８につなが
れている。また基端には分離バンド６が配置され、同様
にオートパイロット装置につながれている。A separating thruster 2 is provided at the front end of the storage cover.
Are connected to the autopilot device 8 of the main body 7. A separation band 6 is disposed at the base end, and is similarly connected to an autopilot device.
【０００４】以上において、飛しよう中、所定の目標位
置で、オートパイロット装置から分離信号が分離用スラ
スタ２および分離バンド６に送られる。そして、分離バ
ンド６が解かれる。また同時に分離用スラスタ２の火薬
が点火爆発し、その力で収納カバー１の結合が解かれ
る。さらにその力が分離力となり収納カバー１を分離す
る（図１１、図１２参照）。In the above, during the flight, a separation signal is sent from the autopilot device to the separation thruster 2 and the separation band 6 at a predetermined target position. Then, the separation band 6 is unraveled. At the same time, the explosive of the separation thruster 2 ignites and explodes, and the coupling of the storage cover 1 is released by the force. Further, the force becomes a separating force and separates the storage cover 1 (see FIGS. 11 and 12).
【０００５】[0005]
【発明が解決しようとする課題】上記従来装置には次の
ような問題点があった。The above-mentioned conventional apparatus has the following problems.
【０００６】（１） 収納カバーを最初に開く時の分離
力は、収納カバーを周りの気流に抗して前方を開くた
め、大きいものが必要である。このためのスラスタ推薬
はかなりの量となりペイロードに影響する。(1) The separating force when the storage cover is first opened must be large because the storage cover is opened forward against the surrounding airflow. The thruster propellants for this can be significant and affect the payload.
【０００７】（２） 分離する時の飛しよう体の気流方
向に対する姿勢や速度により、空気力の働く方向や大き
さが変化する。そして、分離作動の確実性が低く、収納
カバーが搭載物に接触したり、うまく分離しない恐れが
ある。(2) The direction and magnitude of the aerodynamic force change depending on the attitude and speed of the flying object in the airflow direction at the time of separation. In addition, the reliability of the separation operation is low, and the storage cover may come into contact with the load or may not be separated well.
【０００８】[0008]
【課題を解決するための手段】本発明は上記課題を解決
するため次の手段を講ずる。The present invention employs the following means to solve the above-mentioned problems.
【０００９】すなわち、複数に縦分割された収納カバー
と、同収納カバーの前部に設けられ指令信号により作動
する分離用スラスタを有する飛しよう体の収納カバー分
離装置において、通常は飛しよう制御作動をするととも
に上記指令信号により分離作動する操舵翼を上記各収納
カバーに少くとも１つ設ける。That is, in a flying object storage cover separating apparatus having a plurality of vertically divided storage covers and a separation thruster provided in front of the storage cover and operated by a command signal, a flying control operation is usually performed. And at least one steering wing separated and operated by the command signal is provided in each of the storage covers.
【００１０】以上において、操舵翼は通常、飛しよう制
御作動をし、飛しよう体は所定のコースを飛しようす
る。目標場所で収納カバーを開くとき、指令信号により
分離用スラスタが作動する。そして収納カバーの結合が
解かれるとともに同指令信号により操舵翼が作動し、空
力的分離力が発生する。この分離力により各収納カバー
は収納物（搭載物）からそれぞれ遠ざかる方向に移動分
離される。[0010] In the above description, the steering wing normally performs a flying control operation, and the flying body flies on a predetermined course. When the storage cover is opened at the target location, the separation thruster is operated by the command signal. Then, the coupling of the storage cover is released, and the steering wing is operated by the command signal, thereby generating an aerodynamic separating force. Due to this separation force, each storage cover is moved and separated in a direction away from the storage object (load).
【００１１】このようにして各収納カバーは、収納物に
対して接触する恐れもなく確実に外方に移動分離する。
また分離用スラスタは、結合力を解放するだけの小型で
よいので、重量も軽く安価となる。In this way, each of the storage covers is reliably moved outward and separated without fear of contact with the stored items.
Further, since the separation thruster may be small enough to release the coupling force, it is light in weight and inexpensive.
【００１２】[0012]
（１） 本発明の実施の第１形態を図１〜図５により説
明する。なお、従来例で説明した部分は同一の番号をつ
け説明を省略し、この発明に関する部分を主体に説明す
る。(1) A first embodiment of the present invention will be described with reference to FIGS. The parts described in the conventional example are assigned the same reference numerals, and the description thereof will be omitted. The parts related to the present invention will be mainly described.
【００１３】図１と図２にて、縦に２分割された各収納
カバー１の前部の左右に操舵翼３ａ，３ｂをそれぞれ設
ける。各操舵翼３ａ，３ｂには図示省略の操舵装置があ
り、オートパイロット装置８につながれている。また分
離用スラスタ２ａは、小型化し、結合を解くことができ
るだけの力をだせるものにする。In FIGS. 1 and 2, steering wings 3a and 3b are provided on the left and right sides of the front portion of each of the storage covers 1 divided into two vertically. Each of the steering blades 3a and 3b has a steering device (not shown), which is connected to an autopilot device 8. In addition, the separation thruster 2a is reduced in size and has a force capable of releasing the connection.
【００１４】以上において、飛しよう体は、通常、オー
トパイロット装置８からの制御信号で、操舵翼３ａ，３
ｂは飛しよう制御作動をし、予定のコースを飛しようす
る。In the above, the flying object is usually controlled by the control signal from the autopilot device 8 to control the steering wings 3a, 3a.
b performs a flying control operation to fly a planned course.
【００１５】所定の目標場所に達すると、オートパイロ
ット装置８から指令信号が、分離用スラスタ２ａおよび
各操舵翼３ａ，３ｂに送られる。指令信号により分離用
スラスタ２ａが作動する。そして収納カバー１の結合が
解かれるとともに同指令信号により操舵翼３ａ，３ｂが
作動する。操舵翼３ａ，３ｂは図３、図４に示すよう
に、矢視方向に空気力が発生するように舵角がとられ
る。そして各収納カバー１は水中航走体５から遠ざかる
方向に移動分離される。When the vehicle reaches a predetermined target location, a command signal is sent from the autopilot device 8 to the separation thruster 2a and each of the steering blades 3a, 3b. The separation thruster 2a operates according to the command signal. Then, the coupling of the storage cover 1 is released, and the steering wings 3a and 3b are operated by the command signal. As shown in FIGS. 3 and 4, the steering wings 3a and 3b are steered so that air force is generated in the direction of the arrow. Each storage cover 1 is moved and separated in a direction away from the underwater vehicle 5.
【００１６】従って、従来装置のように、単純に収納カ
バー１の前方を分離用スラスタで開け、その後は前方か
らの気流の力で収納カバーを押し開くのに比べ、操舵翼
３ａ，３ｂの揚力を使うので、空気力の大きさ、働く方
向のばらつきが少い。このため、製造上の形状のばらつ
きによる空気力の大きさ、働く方向のばらつきの影響を
受けない。Therefore, as compared with the conventional apparatus, simply opening the front of the storage cover 1 with the separation thruster and then pushing the storage cover open by the force of the airflow from the front, the lift of the steering blades 3a and 3b is increased. Because of the use, there is little variation in the magnitude of the aerodynamic force and the working direction. Therefore, it is not affected by the magnitude of the aerodynamic force and the variation in the working direction due to the variation in the shape in manufacturing.
【００１７】同様に、収納カバー１分離時の飛しよう体
の姿勢の影響で、収納カバー１が受ける空気力の変動を
もカバーすることができる。Similarly, it is possible to cover the fluctuation of the aerodynamic force applied to the storage cover 1 under the influence of the attitude of the flying object when the storage cover 1 is separated.
【００１８】さらに収納カバー１の分離作動の確実化及
び分離後の収納カバー１の軌跡の推定精度も上がり、収
納カバー１が収納している搭載物に衝突しないような設
計がより容易である。Further, the separation operation of the storage cover 1 is ensured, and the accuracy of estimating the trajectory of the storage cover 1 after separation is improved.
【００１９】また、分離用スラスタ２ａは単に収納カバ
ー１の結合を解くだけで、収納カバー１を周りの高速の
気流に抗して押し開く必要がない。従って火薬量は少
く、取扱いは簡単で、収納カバー１が分離用スラスタ２
ａ作動時に受ける力も小さく、構造も軽量、簡単化され
る。Further, the separation thruster 2a merely disengages the storage cover 1 and does not have to push the storage cover 1 open against the surrounding high-speed airflow. Therefore, the amount of explosive is small, the handling is simple, and the storage cover 1 is used as the separation thruster 2.
a The force received during operation is small, and the structure is lightweight and simplified.
【００２０】上記では全操舵翼３ａ，３ｂを作動させた
が、図５に示すように、片方向側の操舵翼３ｂのみを作
動させるようにしてもよい。In the above description, all the steering blades 3a and 3b are operated. However, as shown in FIG. 5, only the one-side steering blade 3b may be operated.
【００２１】（２） 本発明の実施の第２形態を図６〜
図９により説明する。図６と図７に示すように、前記形
態に加え、各収納カバー１の後部にも、同様に操舵翼４
ａ，４ｂを設ける。各操舵翼３ａ，３ｂ，４ａ，４ｂは
前記とほぼ同様に作動する。そしてそれらの空力的分離
力により、各収納カバー１は図７に示すように、前後で
ほぼ同じように分離飛散する。(2) FIGS. 6 to 6 show a second embodiment of the present invention.
This will be described with reference to FIG. As shown in FIG. 6 and FIG. 7, in addition to the above-described embodiment, the steering
a and 4b are provided. Each of the steering blades 3a, 3b, 4a, 4b operates in substantially the same manner as described above. Then, due to their aerodynamic separation forces, each storage cover 1 is separated and scattered in substantially the same way before and after as shown in FIG.
【００２２】したがって、水中航走体５や飛しよう体本
体７への接触に対する安全性はより向上する。Therefore, safety against contact with the underwater vehicle 5 or the flying object body 7 is further improved.
【００２３】上記では全操舵翼３ａ，３ｂ，４ａ，４ｂ
を作動させたが、図８に示すように、片方向側の操舵翼
３ｂ，４ｂのみを作動させるようにしてもよい。In the above description, all the steering blades 3a, 3b, 4a, 4b
However, as shown in FIG. 8, only the steering wings 3b and 4b on one side may be operated.
【００２４】[0024]
【発明の効果】以上に説明したように本発明は次の効果
を奏する。As described above, the present invention has the following effects.
【００２５】分離用スラスタを小型化するとともに指令
信号により分離作動する操舵翼を各収納カバーに少くと
も１つ設けた。これにより、各収納カバーは、飛しよう
体の姿勢にほとんど影響されることなく、操舵翼の空気
力により分離される。したがって、搭載物に接触する恐
れもなく、確実に分離が可能となる。また、分離用スラ
スタが小型化し、軽量、安価となる。The thruster for separation is reduced in size and at least one steering wing which is separated by a command signal is provided on each storage cover. Thereby, each storage cover is separated by the aerodynamic force of the steering wing, almost without being influenced by the attitude of the flying object. Therefore, separation can be reliably performed without fear of contact with the load. Further, the size of the separation thruster is reduced, and the weight and the cost are reduced.
【図１】本発明の実施の第１形態の側面図である。FIG. 1 is a side view of a first embodiment of the present invention.
【図２】上記第１形態の部分断面図である。FIG. 2 is a partial cross-sectional view of the first embodiment.
【図３】上記第１形態の作用説明図である。FIG. 3 is an operation explanatory view of the first embodiment.
【図４】上記第１形態の作用説明図である。FIG. 4 is an operation explanatory view of the first embodiment.
【図５】上記第１形態の作用説明図である。FIG. 5 is an operation explanatory view of the first embodiment.
【図６】本発明の実施の第２形態の側面図である。FIG. 6 is a side view of a second embodiment of the present invention.
【図７】上記第２形態の部分断面図である。FIG. 7 is a partial sectional view of the second embodiment.
【図８】上記第２形態の作用説明図である。FIG. 8 is an operation explanatory view of the second embodiment.
【図９】従来例の側面図である。FIG. 9 is a side view of a conventional example.
【図１０】同従来例の部分断面図である。FIG. 10 is a partial sectional view of the conventional example.
【図１１】同従来例の作用説明図である。FIG. 11 is an operation explanatory view of the conventional example.
【図１２】同従来例の作用説明図である。FIG. 12 is an operation explanatory view of the conventional example.
１ 収納カプセル ２，２ａ 分離用スラスタ ３ａ，３ｂ，４ａ，４ｂ 操舵翼 ５ 水中航走体 ６ 分離バンド ７ 飛しよう体本体 ８ オートパイロット装置 DESCRIPTION OF SYMBOLS 1 Storage capsule 2, 2a Separation thruster 3a, 3b, 4a, 4b Steering wing 5 Underwater vehicle 6 Separation band 7 Flying body 8 Autopilot device
Claims (1)
納カバーの前部に設けられ指令信号により作動する分離
用スラスタを有する飛しよう体の収納カバー分離装置に
おいて、通常は飛しよう制御作動をするとともに上記指
令信号により分離作動する操舵翼を上記各収納カバーに
少くとも１つ設けてなることを特徴とする飛しよう体の
収納カバー分離装置。1. A flying object storage cover separation device having a plurality of vertically divided storage covers and a separation thruster provided at a front portion of the storage cover and operated by a command signal. And an at least one steering wing separated and operated by the command signal is provided in each of the storage covers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26163797A JPH1194500A (en) | 1997-09-26 | 1997-09-26 | Storage cover separation device of flying object |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26163797A JPH1194500A (en) | 1997-09-26 | 1997-09-26 | Storage cover separation device of flying object |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH1194500A true JPH1194500A (en) | 1999-04-09 |
Family
ID=17364671
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP26163797A Withdrawn JPH1194500A (en) | 1997-09-26 | 1997-09-26 | Storage cover separation device of flying object |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH1194500A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101195773B1 (en) | 2012-05-09 | 2012-11-05 | 국방과학연구소 | Cavitatation device of underwater moving body and underwater moving body having the same |
| CN102765471A (en) * | 2012-07-02 | 2012-11-07 | 江西洪都航空工业集团有限责任公司 | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile |
| JP2013040744A (en) * | 2011-08-19 | 2013-02-28 | Ihi Aerospace Co Ltd | Missile |
| CN114526648A (en) * | 2022-03-15 | 2022-05-24 | 哈尔滨工业大学 | Tail cover separating mechanism suitable for high-speed water entering |
-
1997
- 1997-09-26 JP JP26163797A patent/JPH1194500A/en not_active Withdrawn
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013040744A (en) * | 2011-08-19 | 2013-02-28 | Ihi Aerospace Co Ltd | Missile |
| KR101195773B1 (en) | 2012-05-09 | 2012-11-05 | 국방과학연구소 | Cavitatation device of underwater moving body and underwater moving body having the same |
| CN102765471A (en) * | 2012-07-02 | 2012-11-07 | 江西洪都航空工业集团有限责任公司 | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile |
| CN114526648A (en) * | 2022-03-15 | 2022-05-24 | 哈尔滨工业大学 | Tail cover separating mechanism suitable for high-speed water entering |
| CN114526648B (en) * | 2022-03-15 | 2022-10-21 | 哈尔滨工业大学 | Tail cover separating mechanism suitable for high-speed water inlet |
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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: 20041207 |