JPS6467600A - Guided missile - Google Patents
Guided missileInfo
- Publication number
- JPS6467600A JPS6467600A JP22562687A JP22562687A JPS6467600A JP S6467600 A JPS6467600 A JP S6467600A JP 22562687 A JP22562687 A JP 22562687A JP 22562687 A JP22562687 A JP 22562687A JP S6467600 A JPS6467600 A JP S6467600A
- Authority
- JP
- Japan
- Prior art keywords
- compound
- fins
- time
- stabilizer
- specified
- 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.)
- Pending
Links
Landscapes
- Circuit Breakers (AREA)
Abstract
PURPOSE: To enhance motion performance and aerodynamic stability while preventing mechanical interference with a mother machine by incorporating stabilizer fins in the body of a guided projectile and developing the fins by resilient energy stored in a tensile spring with a specified time lag after launching through a locking unit comprising a powder of time prolonging compound and output compound and a gas cylinder. CONSTITUTION: Resilient energy stored in a tensile spring 8 acts to develop stabilizer fins 3 through an arm 10 and gears 12, 13 but it is blocked by a locking unit 7 and the fins 3 are retained in a contained state. When a body 1 is launched from an aircraft, an ignition plug 18 fires a time prolonging compound 19 based on an electric signal at the time of launching and the time prolonging compound 19 fires an output compound 20 upon elapsing a specified combustion time. A piston 15 enters into ascending motion at that moment by the pressure of a large quantity of combustion gas generated from the output compound 20 and it is drawn out by a hole 16 made in the stabilizer fin 3. Since the quantity of the time prolonging compound 19 is selected, the fins are developed with a specified time lag after a projectile is launched from a mother machine.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP22562687A JPS6467600A (en) | 1987-09-09 | 1987-09-09 | Guided missile |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP22562687A JPS6467600A (en) | 1987-09-09 | 1987-09-09 | Guided missile |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS6467600A true JPS6467600A (en) | 1989-03-14 |
Family
ID=16832256
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP22562687A Pending JPS6467600A (en) | 1987-09-09 | 1987-09-09 | Guided missile |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS6467600A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH09159398A (en) * | 1995-12-01 | 1997-06-20 | Komatsu Ltd | Wing unit for airframe |
-
1987
- 1987-09-09 JP JP22562687A patent/JPS6467600A/en active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH09159398A (en) * | 1995-12-01 | 1997-06-20 | Komatsu Ltd | Wing unit for airframe |
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