JPH0943095A - Simple fast landing-on-water test device - Google Patents
Simple fast landing-on-water test deviceInfo
- Publication number
- JPH0943095A JPH0943095A JP21415195A JP21415195A JPH0943095A JP H0943095 A JPH0943095 A JP H0943095A JP 21415195 A JP21415195 A JP 21415195A JP 21415195 A JP21415195 A JP 21415195A JP H0943095 A JPH0943095 A JP H0943095A
- Authority
- JP
- Japan
- Prior art keywords
- guide mechanism
- launching
- servo
- test piece
- water
- 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
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は船舶の船首部に衝撃
的な水圧が加わる際の現象や、人工衛星からの回収物が
空中から水中に高速で着水、潜入する際の現象を調査、
解明する試験装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention investigates a phenomenon when a shocking water pressure is applied to a bow portion of a ship, and a phenomenon when a recovered material from an artificial satellite is landed or infiltrated into the water at high speed from the air,
It relates to a test device to be elucidated.
【０００２】[0002]
【従来の技術】図５〜６を参照し従来例について説明す
る。図５は従来形試験装置のうち比較的低速域で使用さ
れるものの構成図であり、図６は同じく比較的高速域で
使用される着水装置の構成説明図である。なお物体が空
中から水中へ高速で着水し潜入する際の現象は複雑であ
り、従来より専門の設備を使用して調査が行われている
が、それらの専用設備の特徴は水深の深い水槽と、高い
天井の建屋をそなえていることである。2. Description of the Related Art A conventional example will be described with reference to FIGS. FIG. 5 is a configuration diagram of a conventional test device used in a relatively low speed region, and FIG. 6 is a configuration explanatory diagram of a water landing device similarly used in a relatively high speed region. It should be noted that the phenomenon when an object lands underwater at a high speed from the air and infiltrates at high speed is complicated, and investigations have been conducted using specialized equipment from the past. That is, it has a building with a high ceiling.
【０００３】次に図５と図６の従来形着水装置の作用に
ついて説明する。図５において天井９から垂下されたロ
ープ１６に連結された供試体８は、ロープ１６が切断さ
れると自由落下し水槽１７の水面１に着水、潜入し、水
槽１７の底面２に敷設された緩衝材１５によって受止め
られる。この型の試験装置では供試体８を減速させるた
め水深の深い水槽１７が必要とされている。Next, the operation of the conventional water landing device shown in FIGS. 5 and 6 will be described. In FIG. 5, the sample 8 connected to the rope 16 hanging from the ceiling 9 falls freely when the rope 16 is cut, lands on the water surface 1 of the water tank 17, infiltrates, and is laid on the bottom surface 2 of the water tank 17. It is received by the cushioning material 15. In this type of test apparatus, a water tank 17 having a deep water depth is required to decelerate the specimen 8.
【０００４】図６の試験装置では、供試体８は発射筒１
１内の頂部に仮止めされているサーボ１０ａに緩く嵌設
されている。該発射筒１１の頂部には、電磁弁１３を介
して図示しない高圧空気源に連通している高圧ゴムホー
ス１４が接続されている。このような状態に構成された
電磁弁１３を開くと、供試体８が嵌設されているサーボ
１０ａは高圧空気により発射筒１１内を底部側に向って
発射される。In the test apparatus shown in FIG. 6, the specimen 8 is the launch tube 1
It is loosely fitted to a servo 10a that is temporarily fixed to the top of the inside of 1. A high-pressure rubber hose 14, which communicates with a high-pressure air source (not shown) via an electromagnetic valve 13, is connected to the top of the firing cylinder 11. When the solenoid valve 13 configured in such a state is opened, the servo 10a in which the sample 8 is fitted is fired by high-pressure air in the firing cylinder 11 toward the bottom side.
【０００５】従って該サーボ１０ａは発射筒３の底部出
口部に配設されたサーボ止め１０ｂと衝突して急停止す
るが、該サーボに緩く嵌設されていた供試体８はサーボ
１０ａから離脱して高速で発射され、水面に着水して潜
入する。この際の観察及び計測により、着水時と潜入時
の諸現象の解明や、資料となる多くのデータが得られ
る。Therefore, the servo 10a collides with the servo stopper 10b arranged at the bottom outlet of the firing barrel 3 and suddenly stops, but the specimen 8 loosely fitted to the servo is separated from the servo 10a. It is launched at high speed and sneaks into the water surface. By observing and measuring at this time, it is possible to clarify various phenomena at the time of landing and infiltration and to obtain a lot of data to be used as data.
【０００６】[0006]
【発明が解決しようとする課題】前記のように従来形の
高速試験装置では、水深の深い水槽１７と天井の高い建
屋が必要である。又図６に示すようなものでは、供試体
８を高速発射させるのが目的であるが、その際、供試体
８と同時に該供試体８を嵌設しているサーボ１０ａをも
加速する必要がある。そのため加速される物体の重量が
大きくなる。As described above, the conventional high-speed test apparatus requires the water tank 17 with a deep water depth and the building with a high ceiling. In the case of the one shown in FIG. 6, the purpose is to fire the test piece 8 at high speed, but at that time, it is necessary to accelerate the test piece 8 and the servo 10a in which the test piece 8 is fitted. is there. Therefore, the weight of the object to be accelerated becomes large.
【０００７】従って供試体８の発射時にはサーボ止め１
０ｂによりサーボ１０ａの運動のエネルギを瞬時に吸収
することが必要となる。このため該サーボ止めは破損し
易くなるので、破損を防止するためにはその機構が大が
かりになる問題点がある。Therefore, when the test piece 8 is fired, the servo stop 1
It is necessary to instantly absorb the energy of motion of the servo 10a by 0b. For this reason, the servo stop is easily damaged, and there is a problem in that the mechanism is large in scale in order to prevent the damage.
【０００８】即ち供試体８を発射するとき該供試体が嵌
設されているサーボ１０ａは、高圧空気により発射筒１
１内を底部側へ向って発射され、該発射筒の底部出口に
配設されたサーボ止め１０ｂによってサーボ１０ａは止
められ、緩く嵌設されている供試体８はサーボ１０ａか
ら離脱し高速で発射されるが、供試体８とサーボ１０ａ
の嵌設方法が難しく、安定した射入姿勢を得るには多大
の時間を要する等の問題がある。又高圧空気源としては
圧力容器など比較的規模の大きい設備が必要となる。That is, when the test piece 8 is fired, the servo 10a in which the test piece is fitted is driven by the high pressure air to the firing cylinder 1
1 is fired toward the bottom side, the servo 10a is stopped by the servo stop 10b arranged at the bottom outlet of the firing cylinder, and the loosely fitted specimen 8 is released from the servo 10a and fired at high speed. However, the test piece 8 and the servo 10a
However, there is a problem that it takes a lot of time to obtain a stable shooting posture. Further, as a high pressure air source, a relatively large-scale facility such as a pressure vessel is required.
【０００９】本発明の目的は発射圧力が小さく軽量でも
従来と同様の効果が得られる簡易高速着水試験装置を提
供するにある。An object of the present invention is to provide a simple high-speed water landing test device which has the same effect as the conventional one even if the firing pressure is small and the weight is light.
【００１０】[0010]
【課題を解決するための手段】本発明の簡易高速着水試
験装置は、供試体が着水する水槽と、供試体を発射する
ための発射筒と、該発射筒を支持する水槽側壁上に置か
れた支持台と、発射時に該発射筒内部に高圧を発生させ
る高圧発生装置と、発射筒下部に設置されたガイド機構
止め部と、発射筒内部に供試体と同一の横断面形状を持
ちガイド止め機構と接触して設置されたガイド機構と、
該ガイド機構上部に仮止めされ発射時に水面に向って発
射される供試体とを有してなることを特徴としている。SUMMARY OF THE INVENTION A simple high-speed water landing test apparatus of the present invention comprises a water tank on which a test piece lands, a launching tube for launching the test piece, and a water tank side wall supporting the launching tube. It has a support stand placed on it, a high-pressure generator that generates high pressure inside the launch tube at the time of launching, a guide mechanism stop part installed at the bottom of the launch tube, and the same cross-sectional shape as the sample inside the launch tube. A guide mechanism installed in contact with the guide stop mechanism,
It is characterized in that it has a specimen temporarily fixed to the upper part of the guide mechanism and is ejected toward the water surface at the time of ejection.
【００１１】[0011]
【発明の実施の形態】本発明の簡易高速着水試験装置の
概念を図１によって示す。水面１を有する水槽の側壁２
に支持台５を設け発射筒３を設置する。発射筒３の内部
には供試体８のガイド機構４ａが発射筒底部のガイド機
構止め４ｂで止められている。又発射筒３の頂部には、
電磁弁６を介して高圧ゴムホース７が接続され、その他
端には図示しない圧縮空気源が接続されている。BEST MODE FOR CARRYING OUT THE INVENTION The concept of a simple high-speed water landing test apparatus of the present invention is shown in FIG. Side wall 2 of an aquarium having a water surface 1
The support base 5 is provided in the above and the launch tube 3 is installed. The guide mechanism 4a of the specimen 8 is fixed inside the firing barrel 3 by a guide mechanism stopper 4b at the bottom of the firing barrel. Also, on the top of the firing barrel 3,
A high-pressure rubber hose 7 is connected via a solenoid valve 6, and a compressed air source (not shown) is connected to the other end.
【００１２】次に供試体８の概略を図２で説明する。供
試体８は供試体の本体８ａと供試体の安定翼８ｂとから
構成されている。該供試体の安定翼８ｂは空中姿勢を安
定化するものであり、空中から高速で着水する装置には
例外なく取り付けられている。Next, the outline of the specimen 8 will be described with reference to FIG. The test piece 8 is composed of a main body 8a of the test piece and a stabilizer wing 8b of the test piece. The stabilizer wings 8b of the test piece are for stabilizing the aerial posture, and are installed without exception in a device for landing water from the air at high speed.
【００１３】ガイド機構４ａの詳細を図３に示す。該ガ
イド機構４ａの中央部には供試体８ａの断面より若干大
きい程度の孔が加工され、また供試体の安定翼８ｂの高
さ、幅に相当する溝が加工されている。Details of the guide mechanism 4a are shown in FIG. A hole having a size slightly larger than the cross section of the specimen 8a is machined in the central portion of the guide mechanism 4a, and a groove corresponding to the height and width of the stabilizing blade 8b of the specimen is machined.
【００１４】次に供試体８ａとガイド機構４ａの仮止め
方法を図４に示す。ガイド機構４ａの頂部の安定翼の溝
に相当する部分に接着テープ９を貼付し、供試体８の安
定翼８ｂの高さと幅の上面部分が接着テープ９により仮
止めされている。なお供試体８は（５〜１０）ｇ程度の
重さだから接着テープ９で十分止まり、又これ位の力で
止めないと発射できない。Next, FIG. 4 shows a method of temporarily fixing the specimen 8a and the guide mechanism 4a. An adhesive tape 9 is attached to a portion corresponding to the groove of the stabilizing blade at the top of the guide mechanism 4a, and the upper surface portion of the height and width of the stabilizing blade 8b of the sample 8 is temporarily fixed by the adhesive tape 9. Since the sample 8 weighs about (5 to 10) g, it cannot be fired unless it is stopped with the adhesive tape 9 and is stopped with such a force.
【００１５】この種の発射装置による発射速度は、発射
圧力が供試体８にする仕事と、それにより供試体８が得
る運動のエネルギとが等しいことから得られる。 即ち （Ｗ／２ｇ）Ｖ2 ＝ΔＰＳＬ 従って Ｖ＝（△ＰＳＬ×２ｇ／Ｗ）1/2 但しＶ：発射速度 ｍ／ｓ、 Ｓ：加速される物体
の最大断面積 ｃｍ2 Ｌ：加速距離 ｍ、 △Ｐ：発射圧力 ｋｇ／ｃ
ｍ2 ｇ：重力の加速度 ｍ／ｓ2 、Ｗ：加速される物体の総
重量 ｋｇThe firing speed of this type of launching device is obtained from the fact that the firing pressure equals the work to be performed on the test piece 8 and the energy of motion obtained by the test piece 8. That is, (W / 2g) V 2 = ΔPSL Therefore, V = (ΔPSL × 2g / W) 1/2 where V is the firing speed m / s, S is the maximum cross-sectional area of the accelerated object cm 2 L is the acceleration distance m , ΔP: Firing pressure kg / c
m 2 g: acceleration of gravity m / s 2 , W: total weight of the object to be accelerated kg
【００１６】[0016]
【発明の効果】本発明では加速される物体は供試体８の
みであるが、従来例ではこれに加えてサーボ１０ａが付
属している。従って本発明では最大断面積Ｓ及び総重量
Ｗが従来例に較べ格段に小さくなるので、同一の発射速
度を得るための発射圧力が小さくてよくなり、発射装置
全体が小型化をはかることが容易となり、且つ使用圧力
も小さいので安全上も有利である。According to the present invention, the object to be accelerated is only the specimen 8, but in the conventional example, in addition to this, the servo 10a is attached. Therefore, in the present invention, the maximum cross-sectional area S and the total weight W are significantly smaller than those in the conventional example, so that the firing pressure for obtaining the same firing speed may be small, and it is easy to downsize the entire firing apparatus. Also, since the operating pressure is small, it is advantageous in safety.
【００１７】従来例では加速されたサーボ１０ａを止め
るのにサーボ止め１０ｂが必要であった。サーボ止め１
０ｂでは高速化された供試体８付きのサーボ１０ａのう
ちサーボ１０ａのみを瞬時に止める必要があり、大きな
力がサーボ止め１０ｂに作用し故障発生率が多かった。
また故障を防止するには、装置をより大きくすることが
必要であったが、本発明ではこのようなサーボ止めは不
要であり小型化が図られる。In the conventional example, the servo stop 10b is required to stop the accelerated servo 10a. Servo stop 1
In 0b, only the servo 10a among the servos 10a with the speed-up specimen 8 needed to be stopped instantaneously, and a large force acted on the servo stop 10b, resulting in a high failure rate.
Further, in order to prevent the failure, it was necessary to make the device larger, but in the present invention, such a servo stop is not necessary and the size can be reduced.
【００１８】又従来例では供試体８が発射されるのは、
サーボ１０ａがサーボ止め１０ｂに止められた瞬間であ
るため、安定した発射姿勢を得るのは容易でない。本発
明では発射初期の姿勢が不安定であるとしても、ガイド
機構４ａを通過する間に姿勢が安定化され、計画どおり
の空中姿勢を得ることができる。In the conventional example, the specimen 8 is fired as follows.
Since it is the moment when the servo 10a is stopped by the servo stop 10b, it is not easy to obtain a stable firing posture. In the present invention, even if the posture at the initial stage of launch is unstable, the posture is stabilized while passing through the guide mechanism 4a, and the aerial posture as planned can be obtained.
【図１】本発明の第１実施例に係る発射装置の概念図。FIG. 1 is a conceptual diagram of a launching device according to a first embodiment of the present invention.
【図２】同供試体の概念図。FIG. 2 is a conceptual diagram of the test piece.
【図３】同ガイド機構の概念図。FIG. 3 is a conceptual diagram of the guide mechanism.
【図４】同ガイド機構と供試体の仮止め方法の概念図。FIG. 4 is a conceptual diagram of the guide mechanism and a temporary fixing method of the specimen.
【図５】従来形着水試験装置のうち比較的低速域で使用
されるものの構成説明図。FIG. 5 is a structural explanatory view of a conventional water landing test device used in a relatively low speed range.
【図６】同上の装置のうち比較的高速域で使用されるも
のの構成説明図。FIG. 6 is a structural explanatory view of one of the above-mentioned devices used in a relatively high speed range.
１…水面、２…水槽側壁、３…発射筒、４ａ…ガイド機
構、４ｂ…ガイド機構止め部、５…支持台、６…電磁
弁、７…高圧ゴムホース、８…供試体、８ａ…供試体本
体、８ｂ…供試体の安定翼、９…接着テープ、１７…水
槽。DESCRIPTION OF SYMBOLS 1 ... Water surface, 2 ... Water tank side wall, 3 ... Launching cylinder, 4a ... Guide mechanism, 4b ... Guide mechanism stop, 5 ... Support stand, 6 ... Solenoid valve, 7 ... High pressure rubber hose, 8 ... Main body, 8b ... Stabilizer blade of specimen, 9 ... Adhesive tape, 17 ... Water tank.
Claims (1)
するための発射筒と、該発射筒を支持する水槽側壁上に
置かれた支持台と、発射時に該発射筒内部に高圧を発生
させる高圧発生装置と、発射筒下部に設置されたガイド
機構止め部と、発射筒内部に供試体と同一の横断面形状
を持ちガイド機構止め部と接触して設置されたガイド機
構と、該ガイド機構上部に仮止めされ発射時に水面に向
って発射される供試体とを有してなる簡易高速着水試験
装置。1. A water tank on which a test piece lands, a launching tube for launching the test piece, a support placed on a side wall of the water tank for supporting the launching tube, and a high pressure inside the launching tube at the time of launching. A high pressure generating device, a guide mechanism stopper installed at the bottom of the launch tube, and a guide mechanism installed inside the launch tube in contact with the guide mechanism stop having the same cross-sectional shape as the sample. A simple high-speed water landing test device comprising a specimen temporarily fixed to the upper part of the guide mechanism and launched toward the water surface at the time of launch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21415195A JP3219648B2 (en) | 1995-07-31 | 1995-07-31 | Simple high-speed landing test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21415195A JP3219648B2 (en) | 1995-07-31 | 1995-07-31 | Simple high-speed landing test equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0943095A true JPH0943095A (en) | 1997-02-14 |
| JP3219648B2 JP3219648B2 (en) | 2001-10-15 |
Family
ID=16651074
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP21415195A Expired - Fee Related JP3219648B2 (en) | 1995-07-31 | 1995-07-31 | Simple high-speed landing test equipment |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3219648B2 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300655A (en) * | 2014-07-25 | 2016-02-03 | 北京强度环境研究所 | Paddle-swing-type liquid disturbance device for outflow test |
| CN106932171A (en) * | 2017-04-29 | 2017-07-07 | 吉林大学 | A kind of across medium ROV enters water and water outlet test system |
| CN108088638A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of fuselage skin dampening experimental rig |
| CN111207906A (en) * | 2020-01-15 | 2020-05-29 | 天津大学 | Continuous determination method for local atomization rain intensity of multi-working-condition discharge flow under low-pressure environment |
-
1995
- 1995-07-31 JP JP21415195A patent/JP3219648B2/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300655A (en) * | 2014-07-25 | 2016-02-03 | 北京强度环境研究所 | Paddle-swing-type liquid disturbance device for outflow test |
| CN106932171A (en) * | 2017-04-29 | 2017-07-07 | 吉林大学 | A kind of across medium ROV enters water and water outlet test system |
| CN108088638A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of fuselage skin dampening experimental rig |
| CN111207906A (en) * | 2020-01-15 | 2020-05-29 | 天津大学 | Continuous determination method for local atomization rain intensity of multi-working-condition discharge flow under low-pressure environment |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3219648B2 (en) | 2001-10-15 |
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