GB1291589A - Missile - Google Patents
MissileInfo
- Publication number
- GB1291589A GB1291589A GB53250/69A GB5325069A GB1291589A GB 1291589 A GB1291589 A GB 1291589A GB 53250/69 A GB53250/69 A GB 53250/69A GB 5325069 A GB5325069 A GB 5325069A GB 1291589 A GB1291589 A GB 1291589A
- Authority
- GB
- United Kingdom
- Prior art keywords
- missile
- fins
- recess
- fin
- axis
- 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
- 230000000717 retained effect Effects 0.000 abstract 1
- 230000000087 stabilizing effect Effects 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
1291589 Missile fins; war rocket BOFORS AB 30 Oct 1969 [1 Nov 1968] 53250/69 Headings F3A and F3C A guided missile or rocket, comprises a plurality of circumferential stabilizing fins 2, Fig. 1, each of which, in their working position, is engaged with an end portion 7, in a recess 6 in the missile body, the fins being pivoted about an axis 4 in a carrier 3 which is also pivoted about an axis 5, whereby, before launching, the axis 4 lies outside the missile body with the fins lying in a folded position alongside the missile body. The fins can be moved manually to the working position before launching the missile or, if launched from a tube 9, Fig. 2, are moved by inertia and air pressure or spring means as the missile leaves the launching tube. The fin is guided into the recess by a surface 11 and is stopped when a shoulder 8 engages a stop in the recess. The fin is retained in its working position by a catch or by the fin or carrier being wedged into a narrowed portion of the recess. Means are also provided for retaining the fins in the folded position.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SE14844/68*A SE325802B (en) | 1968-11-01 | 1968-11-01 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1291589A true GB1291589A (en) | 1972-10-04 |
Family
ID=20299762
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB53250/69A Expired GB1291589A (en) | 1968-11-01 | 1969-10-30 | Missile |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US3627233A (en) |
| BE (1) | BE741130A (en) |
| CH (1) | CH505361A (en) |
| DE (1) | DE1954953C3 (en) |
| FR (1) | FR2022395A1 (en) |
| GB (1) | GB1291589A (en) |
| NL (1) | NL160384B (en) |
| NO (1) | NO123481B (en) |
| SE (1) | SE325802B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3790104A (en) * | 1973-03-12 | 1974-02-05 | Us Navy | High/low aspect ratio dual-mode fin design |
| FR2356118A1 (en) * | 1976-06-25 | 1978-01-20 | Europ Propulsion | EMPENNAGE FOR PROJECTILE |
| DE2841773C2 (en) * | 1978-09-26 | 1984-07-12 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Pivoting arrangement of the tail unit, especially in the case of missiles or projectiles |
| AU524255B2 (en) * | 1978-12-29 | 1982-09-09 | Commonwealth Of Australia, The | Deployable wing |
| SE433882B (en) * | 1979-10-09 | 1984-06-18 | Bofors Ab | FALL-OUT FINE FOR A WINDOW STABILIZED AMMUNITION UNIT IN THE FORM OF A GRANATE |
| US4588146A (en) * | 1984-03-29 | 1986-05-13 | The United States Of America As Represented By The Secretary Of The Army | Biaxial folding lever wing |
| IL101730A (en) * | 1992-04-30 | 1995-12-31 | Israel State | Moving body such as missile having wings erectable upon acceleration |
| US8438977B2 (en) | 2008-12-25 | 2013-05-14 | Lockheed Martin Corporation | Projectile having deployable fin |
| US11754379B2 (en) * | 2018-03-23 | 2023-09-12 | Simmonds Precision Products, Inc. | Space saving wing stowage |
| CN112985190A (en) * | 2021-04-13 | 2021-06-18 | 西安航天动力技术研究所 | Volute spiral spring type folding missile wing unfolding mechanism |
-
1968
- 1968-11-01 SE SE14844/68*A patent/SE325802B/xx unknown
-
1969
- 1969-10-24 US US869101A patent/US3627233A/en not_active Expired - Lifetime
- 1969-10-27 NL NL6916191.A patent/NL160384B/en not_active IP Right Cessation
- 1969-10-28 CH CH1606169A patent/CH505361A/en not_active IP Right Cessation
- 1969-10-29 NO NO4285/69A patent/NO123481B/no unknown
- 1969-10-30 GB GB53250/69A patent/GB1291589A/en not_active Expired
- 1969-10-31 FR FR6937535A patent/FR2022395A1/fr not_active Withdrawn
- 1969-10-31 BE BE741130D patent/BE741130A/xx unknown
- 1969-10-31 DE DE1954953A patent/DE1954953C3/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| BE741130A (en) | 1970-04-01 |
| US3627233A (en) | 1971-12-14 |
| NO123481B (en) | 1971-11-22 |
| NL6916191A (en) | 1970-05-06 |
| DE1954953A1 (en) | 1970-06-18 |
| DE1954953C3 (en) | 1976-01-08 |
| CH505361A (en) | 1971-03-31 |
| NL160384B (en) | 1979-05-15 |
| FR2022395A1 (en) | 1970-07-31 |
| SE325802B (en) | 1970-07-06 |
| DE1954953B2 (en) | 1975-05-28 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed [section 19, patents act 1949] | ||
| PCNP | Patent ceased through non-payment of renewal fee |