GB953836A - Improvements in missile launchers - Google Patents
Improvements in missile launchersInfo
- Publication number
- GB953836A GB953836A GB215363A GB215363A GB953836A GB 953836 A GB953836 A GB 953836A GB 215363 A GB215363 A GB 215363A GB 215363 A GB215363 A GB 215363A GB 953836 A GB953836 A GB 953836A
- Authority
- GB
- United Kingdom
- Prior art keywords
- catapult
- sled
- rocket
- cylinder
- missile
- 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.)
- Expired
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
Abstract
953,836. Rocket launchers; self-propelled missiles. M. M. COSLOWSKY. Jan. 17, 1963, No. 2153/63. Headings F3A and F3C. A rocket launcher 2 comprises guide rails 8 on a catapult 7 vertically pivotal at its rear 9, a sled 20 running on the rails and having means supporting, 41, and rotating, 4, a self-propelled finless missile 1. The spinning means comprises a hollow cylinder 23 mounted in housing 21 on annular bearings 26 and abutting a thrust bearing 28, the forward end of the cylinder having saw-teeth engaging complementary teeth 31 on the rear of the missile 1. An integral sprocket 34 on the cylinder engages an endless chain 40 driven by a motor 35 and sprocket-wheel 37, to rotate the cylinder, the motor being fixed to the sled 20. The rocket rests on balls in supports 41 and is held in position by rollers 45 in pivotal arms 44 which are released when the sled engages contact 52. The catapult 7 is raised and lowered by hydraulic cylinders 14 moving the frame 16, hinged to the catapult 7, forwards and backwards. The rocket is rotated, to the desired speed, the fuel is ignited, the catapult actuated and the hot gases emerging from exhaust nozzle 50 extending through the hollow cylinder 23 provide sufficient thrust to sustain the trajectory when the sled reaches the end of its travel. The base 5 of the launcher can be rotated horizontally by means not described.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB215363A GB953836A (en) | 1963-01-17 | 1963-01-17 | Improvements in missile launchers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB215363A GB953836A (en) | 1963-01-17 | 1963-01-17 | Improvements in missile launchers |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB953836A true GB953836A (en) | 1964-04-02 |
Family
ID=9734537
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB215363A Expired GB953836A (en) | 1963-01-17 | 1963-01-17 | Improvements in missile launchers |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB953836A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2146415A (en) * | 1983-09-10 | 1985-04-17 | British Aerospace | Launching device |
| CN109612327A (en) * | 2018-12-29 | 2019-04-12 | 湖北航天技术研究院总体设计所 | Missile electromagnetic emission system with Force transmission parts Yu engine integration structure |
-
1963
- 1963-01-17 GB GB215363A patent/GB953836A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2146415A (en) * | 1983-09-10 | 1985-04-17 | British Aerospace | Launching device |
| CN109612327A (en) * | 2018-12-29 | 2019-04-12 | 湖北航天技术研究院总体设计所 | Missile electromagnetic emission system with Force transmission parts Yu engine integration structure |
| CN109612327B (en) * | 2018-12-29 | 2021-06-29 | 湖北航天技术研究院总体设计所 | Missile electromagnetic launching system with force transmission component and engine integrated structure |
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