GB2177668A - Helicopter with missile supporting means - Google Patents
Helicopter with missile supporting means Download PDFInfo
- Publication number
- GB2177668A GB2177668A GB08520310A GB8520310A GB2177668A GB 2177668 A GB2177668 A GB 2177668A GB 08520310 A GB08520310 A GB 08520310A GB 8520310 A GB8520310 A GB 8520310A GB 2177668 A GB2177668 A GB 2177668A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuselage
- helicopter
- supporting means
- closure member
- missiles
- 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.)
- Withdrawn
Links
- 238000003491 array Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangement of rocket launchers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
- F41A23/20—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles for disappearing guns
-
- 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
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Toys (AREA)
Abstract
A helicopter includes missile supporting means movable from an operational position to a stowed position in which the missiles 17 are located within the confines of the helicopter fuselage. In one embodiment the missile supporting means is pivotally attached to the fuselage about a generally horizontal longitudinally extending hinge for movement through an opening in the fuselage between the operational and stowed positions. A closure member 16 is provided to automatically close the opening when the missile supporting means is in the closed position and conveniently the missile supporting means may be integral with the closure member. <IMAGE>
Description
SPECIFICATION
Helicopter with missile supporting means
This invention relates to a helicopter with missile supporting means.
It is known to provide a helicopter with missile supporting means in the form of fixed outriggers extending laterally from both sides of the fuselage and each adapted to carry a plurality of missiles.
Such outboard mountings have a large drag penalty and, since the missiles are transported in the open, considerable problems can occur as a result of vibration, icing and the effects of dust and dirt.
Accordingly, in one aspect the invention provides a helicopter including a fuselage and missile supporting means adapted to support a plurality of missiles in an operational position generally externally and parallel to the side of the fuselage, characterised in that said missile supporting means is moveable from said operational position to a stowed position wherein said missiles are located within the confines of said fuselage.
The missile supporting means may be attahced to the fuselage about a generally horizontal longitudinally extending hinge for pivotal movement through an opening in the fuselage between said operational and stowed positions.
Conveniently a closure member is provided and is adapted to close the opening in the fuselage when the missile supporting means is in the stowed position. Preferably said missile supporting means is movable in elevation when in said operational position.
In another aspect the invention provides a helicopter including a fuselage, an opening in the fuselage, a closure member pivotally mounted about a generally horizontal longitudinally extending axis to selectively close said opening, operating means for moving said closure member between said closed position and an open position exteriorly of said fuselage, and missile supporting means attached to said closure member to support a plurality of missiles so that when the closure member is open said missiles are supported in an operational longitudinally extending position generally parallel and to one side of the fuselage and when the closure member is moved to its closed position to close the opening the missiles are automatically located within the fuselage.
The closure member may be attached to said pivot through an actuator adapted when said closure member is in said open position to pivot said closure member and attached plurality of missiles through a limited arc of movement about a lateral generally horizontal axis.
The fuselage may include sidewalls which in cross section may extend downwardly and outwardly to a point of maximum fuselage width then downwardly and inwardly to join a generally horizontal lower position, said opening preferably being located in the downwardly and inwardly extending portion of the sidewall.
In yet another aspect the invention provides a helicopter including a fuselage having sidewalls which in cross section extend downwardly and outwardly to a point of maximum fuselage width then dowardly and inwardly to join a generally horizontal lower fuselage portion, openings in the downwardly and inwardly extending portions of said sidewalls, closure members pivotally mounted adjacent the points of maximum fuselage width about generally horizontal longitudinally extending axes, operating means for moving said closure members between a closed position and an open position and missile supporting means attached to a surface of each of said closure members so that in the open position the missiles are supported in an operational longitudinally extending position externally of the respective sidewall and in the closed position the openings in the sidewalls are automatically closed by the respective closure members and the missiles are located within the fuselage.
The invention will now be described by way of example only and with reference to the accompanying drawings in which:
Figure 1 is a side elevation of a helicopter including missile supporting means and constructed in accordance with one embodiment of the invention,
Figure 2 is a plan view of the helicopter of Figure 1,
Figure 3 is a front elevation of the helicopter of
Figure 1,
Figure 4 is a generally schematic fragmentary sectioned view taken along lines A-A of Figure 1 and showing the missile supporting means in an operational position, and
Figure 5 is a view similar to Figure 4 with the missile supporting means in a stowed position.
A helicopter 10 includes a fuselage 11 symmetrical about a vertical centreline 12 and including side walls 13 and a bottom portion 14. In the illustrated embodiment the sidewalls 13 extend in cross section outwardly and downwardly to a point of maximum fuselage width, then inwardly and downwardly to join with the generally horizontal bottom portion 14.
A missile supporting means generally indicated at 15 is located in a lower region of each of the fuselage sidewalls 13 and in an operational position, illustrated in Figures 1 and 2, extends generally longitudinally and parallel to the fuselage nd externally of the sidewalls 13. An opening 13a is provided in the inwardly and downwardly extending portion of each sidewall 13 in the vicinity of the missile supporting means 15 for a purpose now to be described with particular reference to Figures 4 and 5 which illustrate the missile supporting means 15 located on one of the sidewalls 13 only of the fuselage 11.
Missile supporting means 15 comprises a generally longitudinally extending closure member 16 which includes support means 31 on one surface thereof adapted to carry a plurality of longitudinally extending missiles 17, four such missiles being shown in the illustrated embodiment. The closure member 16 is movable between an open operational position of Figure 4, the closure mem ber 16 extends laterally and generally horizontally from the sidewall 13, the missiles depending from the closure member 16 so as to be located externally and generally parallel to the sidewall 13 of fuselage 11 in a conventional manner.
Closure member 16 is attached through an actuator 18 to a mounting flange 19 which is attached to the sidewall 13 at the upper edge of opening 13a adjacent the point of maximum fuselage width about a generally horizontal, longitudinally extending hinge 20. With the closure member 16 in the position shown in Figure 4, the actuator 18 is adapted to rotate the closure member 16 and the attached missiles 17 about a generally horizontal laterally extending axis 21 to provide selective control in elevation.
Operating means, generally indicated at 22, includes a first generally laterally extending fixed length lever 23 having an inner end pivotally attached to fuselage structure at 24 and its outer end pivotally attached at 25 to the outer end of a generally laterally extending hydraulic jack 26, shown extended in Figure 4, and one end of a second fixed length lever 27. The inner end of hydraulic jack 26 is pivotally attached to fuselage structure at position 28 that is vertically spaced apart from pivot 24.
The other end of second fixed length lever 27 is attached to a boss 29 formed integral with mounting flange 19 about a pivot 30 spaced-apart from hinge 20.
Thus, when located in the position of Figure 4 the missile supporting means 15 supports the missiles 17 longitudinally and parallel to the fuselage 11 in a conventional operational position externally of sidewall 13. Elevation control is provided by rotation of closure member 16 about axis 21 by the actuator 18, and an upward elevation position is illustrated in Figure 1.
After aligning the missile supporting means 15 with the opening 13a, retraction of the hydraulic jack 26 acts through the first and second fixed length levers 23 and 27 to pivot the closure member 16 about the hinge 20 to rotate the closure member 16 through opening 13a to its closed position in which its array of missiles 17 is automatically located in a stowed position illustrated in
Figure 5 in which the missiles 17 are confined totally within the cross sectional shape of the fuselage 11. In this respect it will be noted that is its closed position the external surface 16a of closure member 16 is shaped so as to automatically close the opening 13a in the sidewall 13 of fuselage 11, and is configured so as to conform with the remainder of the downwardly and inwardly sloping portion of the sidewall 13.
Thus, the present invention provides a helicopter including missile supporting means having a stowed position in which the missiles are located within the confines of the fuselage and in which openings 13a in the fuselage are automatically closed by the closure member 16. This is also illustrated in Figure 3 in which the missile supporting means 15 and attached missiles 17 are shown in broken line in the stowed position. There is therefore no drag penalty when the missile supporting means are in the stowed position thereby increasing the operational range of the helicopter and, since the missiles are protected during transport from inclement weather conditions, reliability is also improved.
The operating means 22 ensures rapid deployment of the missile supporting means 15 to a normal operational position illustrated in Figures 1, 2, 3, and 4, and control in elevation as illustrated in
Figure 1 is provided by actuator 18 to ensure maximum operational effectiveness. The respective missile supporting means 15 can be operated independantly between the operational and stowed positions.
Whilst one embodiment has been described and illustrated it will be understood that many modifications may be made without departing from the scope of the invention. For example, the missile supporting means can be adapted to carry different numbers and/or different arrays of missiles. The closure member 16 may be attached to actuator 18 through a releasable attachment so that different types of missile can be carried on individual closure members. The invention can be incorporated in helicopters having a fuselage of other cross-sectional shapes, for example, with a generally vertical sidewall and a radiussed portion joining the sidewall and the bottom surface. The missile supporting means can be adapted so as to pivot downwardly and outwardly from the stowed position to the operational position, and other suitable forms of operating means can be used to move the missile supporting means between the operational and stowed positions such as a generally horizontal laterally extending gantry along which the missile supporting means is moved by any suitable means such as gearing means or endless chain or belt means.
Claims (11)
1. A helicopter including a fuselage and missile supporting means adapted to support a plurality of missiles in an operational position generally externally and parallel to the side of the fuselage characterised in that said missile supporting means is movable from said operational position to a stowed position wherein said missiles are located within the confines of the fuselage.
2. A helicopter as claimed in Claim 1, further characterised in that the missile supporting means is attached to the fuselage about a generally horizontal longitudinally extending hinge for pivotal movement through an opening in the fuselage between said operational and stowed positions.
3. A helicopter as claimed in Claim 2, further characterised in that a closure member is provided and is adapted to close the opening in the fuselage when the missile supporting means is in said stowed position.
4. A helicopter as claimed in any preceding
Claim, further characterised in that said missile supporting means is movable in elevation when in said operational position.
5. A helicopter including a fuselage, an opening in the fuselage, a closure member pivotally mounted about a generally horizontal longitudinally extending axis to selectively close said opening, operating means for moving said closure member between said closed position and an open position exteriorly of said fuselage, and missile supporting means attached to said closure member to support a plurality of missiles so that when the closure member is open said missiles are supported in an operational longitudinally extending position generally parallel and to one side of the fuselage and when the closure member is moved to its closed position to close the opening the missiles are automatically located within the fuselage.
6. A helicopter as claimed in Claim 5, further characterised in that said closure member is attached to said pivot through an actuator adapted when said closure member is in said open position to pivot said closure member and attached plurality of missiles through a limited arc of movement about a lateral generally horizontal axis.
7. A helicopter as claimed in Claim 6, further characterised in that said closure member attachment is a releasable attachment whereby different types of missile can be carried on individual closure members.
8. A helicopter as claimed in Claim 5, further characterised in that said fuselage includes sidewalls which in cross section extend downwardly and outwardly to a point of maximum fuselage width then downwardly and inwardly to join a generally horizontal bottom portion, said opening being located in the downwardly and inwardly extending portion of the sidewall.
9. A helicopter including a fuselage having si- dewalls which in cross section extend downwardly and outwardly to a point of maximum fuselage width then downwardly and inwardly to join a generally horizontal bottom fuselage portion, openings in the downwardly and inwardly extending portions of said sidewalls, closure members pivotally mounted adjacent the points of maximum fuselage width about generally horizontal longitudinally extending axes, operating means for moving said closure members between a closed position and an open position and missile supporting means attached to each of said closure members so that in the open position of the closure members the missiles are supported in an operational longitudinally extending position externally of the respective sidewall and in the closed position the openings in the sidewalls are automatically closed by the respective closure members and the missiles are located within the fuselage.
10. A helicopter substantially as hereinbefore described with reference to the accompanying drawings.
11. Every novel feature and every novel combination of features disclosed herein.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB848422071A GB8422071D0 (en) | 1984-08-31 | 1984-08-31 | Helicopter with missile supporting means |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB8520310D0 GB8520310D0 (en) | 1986-10-15 |
| GB2177668A true GB2177668A (en) | 1987-01-28 |
Family
ID=10566099
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB848422071A Pending GB8422071D0 (en) | 1984-08-31 | 1984-08-31 | Helicopter with missile supporting means |
| GB08520310A Withdrawn GB2177668A (en) | 1984-08-31 | 1985-08-13 | Helicopter with missile supporting means |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB848422071A Pending GB8422071D0 (en) | 1984-08-31 | 1984-08-31 | Helicopter with missile supporting means |
Country Status (4)
| Country | Link |
|---|---|
| DE (1) | DE3532220A1 (en) |
| FR (1) | FR2587679A1 (en) |
| GB (2) | GB8422071D0 (en) |
| IT (1) | IT8548504A0 (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2665875A1 (en) * | 1990-08-17 | 1992-02-21 | Aerospatiale | Decoy launcher installation for aircraft |
| FR2712386A1 (en) * | 1993-11-12 | 1995-05-19 | Daimler Benz Ag | Smoke system of an armored vehicle. |
| EP0877707A4 (en) * | 1996-10-17 | 2002-01-23 | Bullock Roddy M | Aircraft based sensing, detection, targeting, communications and response apparatus |
| RU2192367C2 (en) * | 2000-03-06 | 2002-11-10 | Бороздин Сергей Валерьянович | External store for helicopter |
| RU2192988C2 (en) * | 2000-03-06 | 2002-11-20 | Бороздин Сергей Валерьянович | Helicopter external store system |
| RU2192987C2 (en) * | 2000-03-06 | 2002-11-20 | Бороздин Сергей Валерьянович | Helicopter |
| EP1950522A1 (en) * | 2007-01-25 | 2008-07-30 | Dassault Aviation | Decoy launch device for aircraft |
| WO2010123422A1 (en) | 2009-04-23 | 2010-10-28 | Saab Ab | Countermeasure arrangement |
| EP2052201A4 (en) * | 2006-08-16 | 2012-10-03 | Rafael Armament Dev Authority | Miniature missile |
| US8720829B2 (en) | 2009-04-23 | 2014-05-13 | Saab Ab | Closable counter-measure compartments for a dispenser unit |
| WO2014122464A1 (en) * | 2013-02-07 | 2014-08-14 | Mbda Uk Limited | A launch assembly for launching weapons from an air vehicle |
| EP2784433A1 (en) * | 2013-03-26 | 2014-10-01 | MBDA UK Limited | A launch assembly for launching weapons from an air vehicle |
| US20180319498A1 (en) * | 2006-10-26 | 2018-11-08 | Lone Star Ip Holdings, Lp | Weapon interface system and delivery platform employing the same |
| EP3909850A1 (en) * | 2020-05-11 | 2021-11-17 | Subaru Corporation | Rotary-wing aircraft |
| WO2023191754A1 (en) * | 2022-03-31 | 2023-10-05 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An attack aircraft with an ammunition rack protected by a movable cover |
| JP7543037B2 (en) | 2020-05-11 | 2024-09-02 | 株式会社Subaru | Rotorcraft |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2155704C1 (en) * | 1999-06-10 | 2000-09-10 | Открытое акционерное общество "Камов" | Combat helicopter |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB428934A (en) * | 1933-11-15 | 1935-05-15 | Hawker Aircraft Ltd | Improvements in or relating to bomb or like carrying and releasing gear for aircraft |
| GB580200A (en) * | 1935-07-03 | 1936-10-29 | Percy Salmon | Improvements in or relating to apparatus for dropping bombs and other bodies from aircraft |
| GB554434A (en) * | 1939-10-26 | 1943-07-05 | Blackburn Aircraft Ltd | Improvements in or relating to bomb gear for aircraft |
| GB578548A (en) * | 1939-10-27 | 1946-07-03 | Blackburn Aircraft Ltd | Improvements in the mounting of guns, machinery and the like on aircraft structures |
| GB791904A (en) * | 1954-12-13 | 1958-03-12 | Blackburn & Gen Aircraft Ltd | Improvements in or relating to doors or closure members for bomb bays or like spacesin the fuselage or wings of aircraft |
| GB877448A (en) * | 1954-04-02 | 1961-09-13 | Blackburn Aircraft Ltd | Improvements in or relating to doors or closure members for bomb bays or like spaces in the fuselages of aircraft |
| GB1560881A (en) * | 1976-05-14 | 1980-02-13 | British Aircraft Corp Ltd | Aircraft weapon mountings |
| GB2062816A (en) * | 1979-03-29 | 1981-05-28 | British Aerospace | Lift-generating stackable weapon |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2709947A (en) * | 1949-03-10 | 1955-06-07 | Bell Aircraft Corp | Aircraft and armament therefor |
| US2975676A (en) * | 1950-10-20 | 1961-03-21 | Chance Vought Corp | Missile launching systems for aircraft |
| AT198624B (en) * | 1955-07-21 | 1958-07-10 | Fiat Spa | Aircraft with an exchangeable weapon container |
| FR1154993A (en) * | 1955-07-21 | 1958-04-18 | Fiat Spa | Airplane comprising a quickly detachable container, forming part of its structure |
| DE3101729C2 (en) * | 1981-01-21 | 1985-02-07 | Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn | Missile launcher on a helicopter |
| DE3132568C2 (en) * | 1981-08-18 | 1983-10-06 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Suspension of a launch container on the weapon carrier of an aircraft |
-
1984
- 1984-08-31 GB GB848422071A patent/GB8422071D0/en active Pending
-
1985
- 1985-08-13 GB GB08520310A patent/GB2177668A/en not_active Withdrawn
- 1985-08-26 FR FR8512729A patent/FR2587679A1/en active Pending
- 1985-08-29 IT IT8548504A patent/IT8548504A0/en unknown
- 1985-09-10 DE DE19853532220 patent/DE3532220A1/en not_active Withdrawn
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB428934A (en) * | 1933-11-15 | 1935-05-15 | Hawker Aircraft Ltd | Improvements in or relating to bomb or like carrying and releasing gear for aircraft |
| GB580200A (en) * | 1935-07-03 | 1936-10-29 | Percy Salmon | Improvements in or relating to apparatus for dropping bombs and other bodies from aircraft |
| GB554434A (en) * | 1939-10-26 | 1943-07-05 | Blackburn Aircraft Ltd | Improvements in or relating to bomb gear for aircraft |
| GB578548A (en) * | 1939-10-27 | 1946-07-03 | Blackburn Aircraft Ltd | Improvements in the mounting of guns, machinery and the like on aircraft structures |
| GB877448A (en) * | 1954-04-02 | 1961-09-13 | Blackburn Aircraft Ltd | Improvements in or relating to doors or closure members for bomb bays or like spaces in the fuselages of aircraft |
| GB791904A (en) * | 1954-12-13 | 1958-03-12 | Blackburn & Gen Aircraft Ltd | Improvements in or relating to doors or closure members for bomb bays or like spacesin the fuselage or wings of aircraft |
| GB1560881A (en) * | 1976-05-14 | 1980-02-13 | British Aircraft Corp Ltd | Aircraft weapon mountings |
| GB2062816A (en) * | 1979-03-29 | 1981-05-28 | British Aerospace | Lift-generating stackable weapon |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2665875A1 (en) * | 1990-08-17 | 1992-02-21 | Aerospatiale | Decoy launcher installation for aircraft |
| FR2712386A1 (en) * | 1993-11-12 | 1995-05-19 | Daimler Benz Ag | Smoke system of an armored vehicle. |
| EP0877707A4 (en) * | 1996-10-17 | 2002-01-23 | Bullock Roddy M | Aircraft based sensing, detection, targeting, communications and response apparatus |
| RU2192367C2 (en) * | 2000-03-06 | 2002-11-10 | Бороздин Сергей Валерьянович | External store for helicopter |
| RU2192988C2 (en) * | 2000-03-06 | 2002-11-20 | Бороздин Сергей Валерьянович | Helicopter external store system |
| RU2192987C2 (en) * | 2000-03-06 | 2002-11-20 | Бороздин Сергей Валерьянович | Helicopter |
| US8664575B2 (en) | 2006-08-16 | 2014-03-04 | Rafael Advanced Defense Systems Ltd. | Miniature missile |
| EP2052201A4 (en) * | 2006-08-16 | 2012-10-03 | Rafael Armament Dev Authority | Miniature missile |
| US20180319498A1 (en) * | 2006-10-26 | 2018-11-08 | Lone Star Ip Holdings, Lp | Weapon interface system and delivery platform employing the same |
| EP1950522A1 (en) * | 2007-01-25 | 2008-07-30 | Dassault Aviation | Decoy launch device for aircraft |
| FR2911846A1 (en) * | 2007-01-25 | 2008-08-01 | Dassault Avions | DEVICE LAUNCHES LURES FOR AIRCRAFT |
| EP2422161A4 (en) * | 2009-04-23 | 2013-10-16 | Saab Ab | COUNTERMEASURE DEVICE |
| US8607682B2 (en) | 2009-04-23 | 2013-12-17 | Saab Ab | Countermeasure arrangement |
| US8720829B2 (en) | 2009-04-23 | 2014-05-13 | Saab Ab | Closable counter-measure compartments for a dispenser unit |
| WO2010123422A1 (en) | 2009-04-23 | 2010-10-28 | Saab Ab | Countermeasure arrangement |
| WO2014122464A1 (en) * | 2013-02-07 | 2014-08-14 | Mbda Uk Limited | A launch assembly for launching weapons from an air vehicle |
| EP2784433A1 (en) * | 2013-03-26 | 2014-10-01 | MBDA UK Limited | A launch assembly for launching weapons from an air vehicle |
| EP3909850A1 (en) * | 2020-05-11 | 2021-11-17 | Subaru Corporation | Rotary-wing aircraft |
| US12054243B2 (en) | 2020-05-11 | 2024-08-06 | Subaru Corporation | Rotary-wing aircraft |
| JP7543037B2 (en) | 2020-05-11 | 2024-09-02 | 株式会社Subaru | Rotorcraft |
| WO2023191754A1 (en) * | 2022-03-31 | 2023-10-05 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An attack aircraft with an ammunition rack protected by a movable cover |
| GB2631876A (en) * | 2022-03-31 | 2025-01-15 | Tusas Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An attack aircraft with an ammunition rack protected by a movable cover |
Also Published As
| Publication number | Publication date |
|---|---|
| IT8548504A0 (en) | 1985-08-29 |
| FR2587679A1 (en) | 1987-03-27 |
| GB8422071D0 (en) | 1986-10-01 |
| GB8520310D0 (en) | 1986-10-15 |
| DE3532220A1 (en) | 1987-05-14 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |