CH316189A - Missile with launcher for the same - Google Patents
Missile with launcher for the sameInfo
- Publication number
- CH316189A CH316189A CH316189DA CH316189A CH 316189 A CH316189 A CH 316189A CH 316189D A CH316189D A CH 316189DA CH 316189 A CH316189 A CH 316189A
- Authority
- CH
- Switzerland
- Prior art keywords
- plate
- missile
- rocket
- launching device
- outlet ends
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/048—Means for imparting spin to the rocket before launching
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Description
<B>Rakete mit</B> Abschusseinrichtung <B>für dieselbe</B> Gegenstand vorliegender Erfindung ist eine Rakete mit Abschusseinrichtung für die selbe, die mit Vorteil in Panzern, Flugzeugen usw. zur Anwendung gelangt.
Der Erfin dungsgegenstand ist dadurch gekennzeichnet, dass das hintere Ende des Abschussrohres durch einen drehbar gelagerten Teller abge schlossen ist., in welchem Gaskanäle angeord net sind, welche von der Auflageseite der Rakete her um 18!6 ' zurückgebogen sind und an ihrem Austrittsende schräg in bezug auf die Rohrexe verlaufen, und zwar derart, dass beim Absehuss dem Teller eine Drehbewegung erteilt wird.
In der beiliegenden Zeichnung ist eine beispielsweise Ausführungsform des Erfin dungsgegenstandes schematisch in einem teil weisen Längsschnitt dargestellt.
In der Zeichnung bezeichnet 1 die Ra_ trete, die zum Abschuss in einem glatten Ab schussrohr 2 untergebracht ist, das seinerseits beispielsweise in einem nicht dargestellten Panzer eingebaut sein kann. Die Rakete 1 ist an ihrem hintern Ende in an sich bekannter Weise mit einer Leitführung 3 versehen, in welcher schräg zur Längsachse verlaufende, düsenförmige Bohrungen 4 angebracht sind. Die schräggestellten Bohrungen 4 dienen dazu, dass nach einem Lösen von einem Teller 5 die Gase durch die Düsen 4 strömen kön nen und der Rakete weiterhin ein Drall er teilt wird.
Die Rakete ruht vor dem Ab schuss auf dem Teller 5, der auf einem Ku- gellager 6, zum Beispiel ein Wälzd@rucklager, drehbar gelagert und mit einer Kopfschraube 5' versehen ist. Im Teller 5 sind Gaskanäle 7 vorgesehen, die dazu dienen, aus dem hintern Ende 8: der Rakete 1 austretende Verbren nungsgase um 1'80 umzulenken und sie durch das Rohr 2 nach vorn austreten zu lassen.
Die Austrittsenden 711 der Gaskanäle 7, die mit der Bohrung des Abschussrohres 2@, ver bunden sind, verlaufen schräg in bezug auf eine senkrecht zur Rohrachse verlaufende Ebene, so dass die austretenden Gase eine Drehung des Tellers herbeiführen. Auf diese Weise wird erreicht, dass der Rakete 1 be reits ein Drall erteilt wird, solange sie noch auf dem Teller 5. ruht..
Um die Rakete 1 mit dem Teller 5 zu kup peln, können hierfür geeignete Mittel vorge sehen sein. Beispielsweise ist: in der Zeich nung schematisch ein Kupplungsbolzen 9 an gedeutet, der in den Teller 5 eingeschraubt ist und in eine, eine Verengerung aufweisende Bohrung 10 der Leitführung 3 eintritt. Die Verengerung kann durch federnde Metall streifen oder dergleichen gebildet sein, so dass die Rakete den Teller 5 verlassen. kann, so bald der Rückstoss eine gewisse Höhe erreicht hat.
Gegenüber den Austrittsenden 7 X der Gas kanäle 7 sind Rippen 11 vorgesehen, die zur Lenkung der Verbrennungsgase dienen.
Schliesslich können zusätzliche, nicht ge zeichnete, bekannte Mittel vorgesehen sein, die die Rakete mit dem -Teller 5, kuppeln, bis die erstere eine bestimmte Rotationsgeschwindig- keit erreicht hat. Es sind vorzugsweise noch Mittel vorgesehen, um die Düsen -I nach dem Abschuss der Rakete automatisch zu schliessen. In den an die Leitführung 3 anschliessenden Wandteilen des feststehenden Rohres 2: können zum Beispiel Walzen- oder Nadellager 12 an geordnet sein, wie dies punktiert, angedeutet ist.
<B> Rocket with </B> launching device <B> for the same </B> The object of the present invention is a rocket with </B> launching device for the same, which is advantageously used in tanks, aircraft, etc.
The subject of the invention is characterized in that the rear end of the launch tube is closed by a rotatably mounted plate, in which gas ducts are arranged, which are bent back from the support side of the rocket by 18! 6 'and at their exit end obliquely in run in relation to the tube axes, in such a way that the plate is given a rotary movement when it is shot.
In the accompanying drawing, an example embodiment of the invention is shown schematically in a partial longitudinal section.
In the drawing, 1 denotes the Ra_ step, which is housed for launching in a smooth shot tube 2, which in turn can be installed, for example, in a tank, not shown. The rocket 1 is provided at its rear end in a manner known per se with a guide guide 3 in which nozzle-shaped bores 4 running obliquely to the longitudinal axis are made. The inclined bores 4 serve that after loosening a plate 5, the gases can flow through the nozzles 4 and the rocket continues to share a twist.
Before being fired, the rocket rests on the plate 5, which is rotatably mounted on a ball bearing 6, for example a roller thrust bearing, and is provided with a head screw 5 '. In the plate 5 gas ducts 7 are provided, which serve to divert combustion gases emerging from the rear end 8 of the rocket 1 by 1'80 and to let them exit through the pipe 2 to the front.
The outlet ends 711 of the gas channels 7, which are connected to the bore of the launch tube 2 @, run obliquely with respect to a plane perpendicular to the tube axis, so that the escaping gases cause a rotation of the plate. In this way it is achieved that the rocket 1 is already given a twist as long as it is still resting on the plate 5. ..
In order to couple the rocket 1 with the plate 5, suitable means can be provided for this purpose. For example: in the drawing, a coupling bolt 9 is schematically indicated, which is screwed into the plate 5 and enters a bore 10 of the guide 3 that has a constriction. The constriction can be formed by resilient metal strips or the like, so that the rocket leaves the plate 5. as soon as the recoil has reached a certain level.
Opposite the outlet ends 7 X of the gas channels 7 ribs 11 are provided, which serve to direct the combustion gases.
Finally, additional known means, not shown, can be provided which couple the rocket to the plate 5 until the former has reached a certain rotational speed. Means are preferably also provided to automatically close the nozzles -I after the rocket has been launched. In the wall parts of the stationary tube 2 adjoining the guide guide 3: for example, roller or needle bearings 12 can be arranged, as indicated by dotted lines.
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH316189T | 1953-05-07 |
Publications (1)
Publication Number | Publication Date |
---|---|
CH316189A true CH316189A (en) | 1956-09-30 |
Family
ID=4496286
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CH316189D CH316189A (en) | 1953-05-07 | 1953-05-07 | Missile with launcher for the same |
Country Status (1)
Country | Link |
---|---|
CH (1) | CH316189A (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2996880A (en) * | 1958-10-14 | 1961-08-22 | Texaco Experiment Inc | Reaction propulsion system and rocket |
US3015992A (en) * | 1958-02-25 | 1962-01-09 | Short Brothers & Harland Ltd | Launching means for rocket-propelled missiles |
DE1121979B (en) * | 1959-11-09 | 1962-01-11 | Karl Kaesmeier Dipl Ing | Device for the spin stabilization of a rocket |
DE1142532B (en) * | 1960-03-11 | 1963-01-17 | Short Brothers & Harland Ltd | Launching device, especially for steerable rocket projectiles |
DE1180277B (en) * | 1958-03-11 | 1964-10-22 | Hans Wimmer | Launching device for space and long-range missiles |
DE1294265B (en) * | 1962-11-29 | 1969-04-30 | Mb Associates Corp | Hand-held missile launcher |
US4173919A (en) * | 1977-12-12 | 1979-11-13 | General Dynamics Corporation | Two-way rocket plenum for combustion suppression |
US5542333A (en) * | 1983-08-15 | 1996-08-06 | Hughes Missile Systems Company | Undersea vehicle ejection from capsules |
US5837919A (en) * | 1996-12-05 | 1998-11-17 | The United States Of America As Represented By The Secretary Of The Navy | Portable launcher |
US6079310A (en) * | 1996-12-05 | 2000-06-27 | The United States Of America As Represented By The Secretary Of The Navy | Portable launcher |
US6283005B1 (en) | 1998-07-29 | 2001-09-04 | The United States Of America As Represented By The Secretary Of The Navy | Integral ship-weapon module |
RU2781118C1 (en) * | 2021-11-12 | 2022-10-05 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Design of the tail compartment of a sea-launched ballistic missile |
-
1953
- 1953-05-07 CH CH316189D patent/CH316189A/en unknown
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3015992A (en) * | 1958-02-25 | 1962-01-09 | Short Brothers & Harland Ltd | Launching means for rocket-propelled missiles |
DE1150908B (en) * | 1958-02-25 | 1963-06-27 | Short Brothers & Harland Ltd | Launch device for holding a rocket propelled projectile |
DE1180277B (en) * | 1958-03-11 | 1964-10-22 | Hans Wimmer | Launching device for space and long-range missiles |
US2996880A (en) * | 1958-10-14 | 1961-08-22 | Texaco Experiment Inc | Reaction propulsion system and rocket |
DE1121979B (en) * | 1959-11-09 | 1962-01-11 | Karl Kaesmeier Dipl Ing | Device for the spin stabilization of a rocket |
DE1142532B (en) * | 1960-03-11 | 1963-01-17 | Short Brothers & Harland Ltd | Launching device, especially for steerable rocket projectiles |
DE1294265B (en) * | 1962-11-29 | 1969-04-30 | Mb Associates Corp | Hand-held missile launcher |
US4173919A (en) * | 1977-12-12 | 1979-11-13 | General Dynamics Corporation | Two-way rocket plenum for combustion suppression |
US5542333A (en) * | 1983-08-15 | 1996-08-06 | Hughes Missile Systems Company | Undersea vehicle ejection from capsules |
US5837919A (en) * | 1996-12-05 | 1998-11-17 | The United States Of America As Represented By The Secretary Of The Navy | Portable launcher |
US6079310A (en) * | 1996-12-05 | 2000-06-27 | The United States Of America As Represented By The Secretary Of The Navy | Portable launcher |
US6283005B1 (en) | 1998-07-29 | 2001-09-04 | The United States Of America As Represented By The Secretary Of The Navy | Integral ship-weapon module |
RU2781118C1 (en) * | 2021-11-12 | 2022-10-05 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Design of the tail compartment of a sea-launched ballistic missile |
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