| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 261 | Conformable weapons platform | US885255 | 1997-06-30 | US5988567A | 1999-11-23 | Robert Henry Wille |
| A conformable weapons platform (52) has a cavity (60) in a skin of an aircraft. A weapon launching system (62) is contained in the cavity (60). A pair of elastomer doors (56, 58) are attached to a perimeter of the cavity. | ||||||
| 262 | Aircraft based sensing, detection, targeting, communications and response apparatus | US731684 | 1996-10-17 | US5927648A | 1999-07-27 | Richard Lawrence Ken Woodland |
| The system and apparatus of this invention provides for a rapidly loaded, palletized, non-dedicated fixed or rotary wing aircraft based, manned observation, sensor launch system, with self-powered sensing and targeting pod, multi-frequency antenna array, and with C4I analysis and control capabilities. The system may be used to deploy and manipulate autonomous and remote control vehicles, for the purpose of recovering and protecting persons in peril; containing/remediating toxic spills; sensing/detection; fire fighting; ship towing; or surface based refueling and support. Although not the primary purpose, this system can also be used for to support an offensive weapons system which could be used to selectively eliminate various targets with a standoff delivery capability. The system and apparatus of the present invention is generally comprised of a removable pallet assembly adapted for loading into, and mounting to the floor of, the interior of the aircraft; a seating assembly moveably mounted to the pallet assembly; an integrated door assembly retractably mounted to the pallet assembly and adapted fit into an opening in the aircraft upon removal of the aircraft side door member, the integrated door assembly having a door frame defining a periphery; at least one remote sensing pod retractably attached to the door frame adapted for deployment from the interior of the aircraft to the exterior of the aircraft; at least one radar member retractably attached to the door frame adapted for deployment from the interior of the aircraft to the exterior of the aircraft; at least one antenna array retractably attached to the door frame adapted for deployment from the interior of the aircraft to the exterior of the aircraft; and control means for coordinating the members and functions of the apparatus. | ||||||
| 263 | Aircraft support plank mounting of 30 mm machine guns | US812756 | 1997-03-06 | US5767436A | 1998-06-16 | Paul H. Sanderson; Charles E. Rostocil |
| An elongated support plank structure longitudinally extends transversely through the cabin area of a helicopter and has outer end portions projecting outwardly beyond opposite sides of the helicopter. A pair of 30 mm machine guns are mounted on the plank end portions and are supplied with belted ammunition from magazine boxes mounted on the plank within the cabin area via flexible feed chutes interconnected between the magazine boxes and interiorly rollered feed adapters interconnected between the outer ends of the feed chutes and the inlets of the machine gun feeder mechanisms. The 30 mm machine guns are secured to the outer plank end portions by specially designed mounting structures each having a cradle portion with axis-adjustable roller assemblies that engage the gun and essentially preclude lateral movement thereof relative to the cradle, but permit roller-guided longitudinal gun recoil movement, during firing of the gun. During firing of the gun, the gun moves longitudinally relative to fixed position recoil pin portions of the mounting structure and resiliently transfers its longitudinal recoil and counter recoil forces to such pin portions. Each cradle is gimbal-supported within a mounting structure securable to one of the plank ends, and a bore sight adjustment subassembly is interconnected between the mounting structure and the cradle and is used to pivotally adjust the cradle relative to the mounting structure about two mutually perpendicular axes to thereby adjust the elevation and azimuth bore sight settings of the gun. | ||||||
| 264 | Device for signature reduction | US680606 | 1996-07-16 | US5732904A | 1998-03-31 | Ulrich Rieger |
| A device for the sensor signature reduction of cargo to be dropped from the air comprises a covering that essentially completely surrounds the cargo, which is made of a flexible material having a surface that reflects the expected radar radiation, wherein it is provided with openings for the inlet of ram air. | ||||||
| 265 | Double truss structural armor component | US569414 | 1995-12-06 | US5654518A | 1997-08-05 | Steven K. Dobbs |
| A double truss structural armor component includes a first face sheet, an intermediate sheet opposing the first face sheet, a first truss core member sandwiched between the first face sheet and the intermediate sheet, a second face sheet opposing the intermediate sheet, a second truss core member sandwiched between the second face sheet and the intermediate sheet, and laminate materials disposed within interior flutes of the first and second truss core members. The first tress core member has a flute axis. The second truss core member has a flute axis which is oriented in a range of about 45.degree. to 90.degree. from the flute axis of the first truss core member. Thus, a biaxially redundant load path is formed. The first and second face sheets, the intermediate sheet, and the first and second truss core members are formed of high toughness, high strength titanium alloys. The laminate materials which are within the interior flutes of the truss core members are bonded to portions of the flutes that are adjacent to the intermediate sheet. The laminate materials have high energy of break properties. During impact of a ballistic fragment, one of the face sheets slows down the fragment and flattens and further fragments the fragment. When the resulting fragments impact the laminate materials, their energies are absorbed by the laminate materials by high strain deformation of the laminate materials in biaxial directions. Thus, the fragments are brought to rest and are prevented from penetrating the other face sheet. During impact of a blast wave, the energy wave is partially absorbed by one of the face sheets, deforming and transferring load to the truss core members. These members deform in a buckling mode in biaxial directions, thereby absorbing the blast energy in a spring-like manner, preventing fracture of the other face sheet. | ||||||
| 266 | Apparatus and methods for mounting a weaponry support plank on the cabin area floor of a helicopter | US417922 | 1995-04-06 | US5517895A | 1996-05-21 | Paul H. Sanderson |
| A longitudinally central portion of a weaponry support plank is secured to the cabin area floor of a McDonnell Douglas 500/530 helicopter using a support and reinforcing system associated with forwardly and rearwardly disposed pairs of stiffening ribs anchored to the top side of the floor. Opposite end portions of the front and rear rib pairs are removed and are laterally enclosed in and anchored to elongated reinforcing structures each having opposite ends generally aligned with the opposite ends of its associated shortened rib. End members are anchored to the floor at the opposite ends of each pair of shortened ribs and are also anchored to the opposite ends of their associated reinforcing structure. Two front support strut members have upper sides fixedly secured in a spaced relationship to a front side edge of the central plank portion, and two rear support strut members have sides fixedly secured in a spaced relationship to the rear side edge of the central plank portion. The undersides of the support strut members are removably and pivotally secured to the end members by expansion pins extending along axes transverse to the stiffening ribs. In an alternate embodiment of the support and reinforcing system the front support strut members are provided with rearwardly projecting extension portions that are anchored to reinforced opposite end portions of the central floor stiffening rib. | ||||||
| 267 | Feed chute-to-gun ammunition belt guide adapter for machine guns | US374879 | 1995-01-10 | US5461963A | 1995-10-31 | Paul H. Sanderson |
| Belted ammunition of either the "ball" or the shorter "SLAP" type is supplied through a flexible feed chute to a 7.62 mm mini machine gun using a specially configured feed adapter interconnected between the outlet end of the feed chute and the inlet of the gun feeder mechanism. The feed adapter, through which the ammunition passes into the gun feed mechanism, is provided with at least one internal roller around which the ammunition belt operatively passes. The roller has a side surface contour with a sloped shoulder portion which complementarily engages the sloping shoulders of the individual ammunition rounds passing around the roller. This complementary shoulder engagement longitudinally indexes the rounds within the adapter and limits undesirable longitudinal shifting of the rounds therein. In one embodiment thereof the adapter is connected to an aircraft plank-mounted mini gun and permits the ammunition belt to be routed over the gun, turned downwardly, and then bent sharply back into the gun's feeder mechanism without tending to cause ammunition jamming at the feed mechanism due to the sharp belt bend. In a second embodiment thereof the feed adapter is connected to a pintle-mounted mini gun and serves to provide improved vertical pivoting clearance between the gun and an aircraft door or window sill structure upon which the gun-supporting pintle apparatus is mounted. In a third embodiment thereof the feed adapter is connected to a pintle-mounted gun slidably mounted on a pivotable support arm member extending outwardly through an aircraft side door opening. | ||||||
| 268 | Distributed station armament system | US416644 | 1989-10-03 | US5036466A | 1991-07-30 | Frank Fitzgerald; William H. Ackerman, Jr. |
| An armament system for use with a plurality of different types of stores, and comprising a central unit and a plurality of distributed stations. The central unit holds a plurality of store specific application programs, and each of the plurality of store types is associated with one of the store specific application programs. Moreover, each of the store specific application programs is adapted to control the transmission of data between a store of an associated type and one of the distributed stations. The central unit is adapted to control the operation of the armament system and the transmission of data between the central unit and the distributed stations, and to transmit any of the store specific application programs to any of the distributed stations of the armament system. | ||||||
| 269 | Device for rapid fixing and removal of a loader to and from an aircraft carrying device | US686820 | 1984-12-27 | US4601445A | 1986-07-22 | Didier A. Duclos; Pierre F. Coutin |
| A device for rapidly positioning and removing a loader in and from a carrying device on an aircraft, comprising a lever in the form of a horse shoe or stirrup having a cross leg between two side legs which support the loader and which are pivotably mounted to the carrying device at their ends opposite the cross leg, whereas this latter carries a single screw for fixing to the carrying device, actuation of this lever being facilitated by previously automatically latching the loader to the bottom of the carrying device. | ||||||
| 270 | Stores handling apparatus and system | US214875 | 1980-12-10 | US4473200A | 1984-09-25 | Martin A. Deady |
| A stores handling apparatus for moving and positioning stores relative a parked aircraft to facilitate loading thereof comprises a beam member (21) having releasable coupling means (22) near each end for attachment of at least one stores carrying trolley (23) and so that each trolley projects substantially parallel to the beam member. Means such as rollers (24) or wheels (33) provide for movement of the beam member along a surface, and guide means (25) are adapted in operation for engagement with guide means (39) formed in a trackway (38) on the surface.In operation, the stores handling apparatus is used in combination with an aircraft moving apparatus operable to align an aircraft on the trackway and, preferably, of a type comprising a trolley (50) movable along the same trackway.The apparatus and system of this invention is particularly suited for use in the moving and positioning of stores relative an aircraft parked on the deck of a ship. | ||||||
| 271 | Weapons system for the ballistic and guided attack on multiple targets, especially by an aircraft | US49595 | 1979-06-18 | US4307650A | 1981-12-29 | Manfred Kuesters; Werner Lehmann |
| The present weapons system enables an aircraft to attack simultaneously a urality of targets in an aimed, guided manner by a like plurality of small missiles or projectiles. For this purpose the missiles are carried in a rotatable drum type platform comprising respective launching tubes. The firing control system of the aircraft includes a computer which takes into account automatically the target coordinates and other data for selecting that missile which is most suitable for a particular target, whereby the rotatable platform requires a minimum of rotation for aiming the missile with a proper lead factor at the respective target. The missile is then automatically fired without any need of the aircraft heading toward the target. | ||||||
| 272 | Laminated container | US538045 | 1975-01-02 | US3949894A | 1976-04-13 | Theodore A. Underwood |
| Laminated container suitable for containing high-temperature lubricating oil which comprises a rigid container having adhered to its outer surface a laminate of outwardly successive adherent laminae comprising a first lamina of rubbery polyfluorohydrocarbon, second lamina of flexible multiple layers of coated textile fabric and, if desired, a third outer rigid lamina of multiple layers of polymer-encapsulated glass fibers. | ||||||
| 273 | Aircraft carried constant density munition dispensing system | US43317674 | 1974-01-14 | US3916760A | 1975-11-04 | SEWELL CLINTON J; FRINDELL GUY H; CAMPAGNUOLO CARL; VOLLBRACHT PAUL |
| A munition dispensing system responsive to aircraft speed for dropping munitions at a constant ground distance spacing independent of aircraft speed variation. An air-driven generator produces an a.c. voltage linearly proportional to the airspeed. The generator output is converted to a varying d.c. voltage which controls the frequency of an oscillator to produce a series of pulses with frequency linearly proportional to airspeed. These pulses are used to control the dispensing of munition at selectable ground distance spacings which is maintained regardless of airspeed.
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| 274 | Safe aircraft ammunition container | US44670174 | 1974-02-28 | US3911787A | 1975-10-14 | SEIBEL CHARLES M |
| Aircraft ammunition is loaded nose-down in an ejectable container that is attached to the bottom of the aircraft external to primary aircraft structure, to minimize peril in the event of explosion of the ammunition.
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| 275 | Ordnance alignment and loading apparatus | US42853373 | 1973-12-26 | US3911786A | 1975-10-14 | SCHEETZ FRANK L; BUCK FRANCIS E; SHEPARD WILLIAM B |
| Apparatus for automatic final alignment and latching of ordnance to aircraft including a pair of diagonally opposed pin and cone sets demountably attached to the ordnance and aircraft respectively, lug and latch sets similarly attached, and a pair of inflatable bags supporting a platform on which the ordnance rests. Upon completion of approximate alignment, a lifting force is imparted to the weapons by inflation of the bags, causing smooth mating of the pins and cones and final fastening of the lugs and latches.
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| 276 | Fire control system | US30350172 | 1972-11-03 | US3803974A | 1974-04-16 | EVEREST C; VOZNICK H |
| A fire control system that can be readily installed with minimum change on existing aircraft, actually tests all weapon positions and stores a number of status words representing the current state of the various weapon positions. Upon occurence of a selected number of firing conditions such as firing interval, remaining quantity of a salvo to be fired and the fire command, the system will automatically extract from the store of weapon status words, one word corresponding to an unfired weapon of selected type. The extracted word is automatically sent to the weapon firing station in a time division multiplexing arrangement that shares a single communication channel among fire command, test command and sensed status words. Although the system will automatically select an unfired weapon of a chosen type, the pilot is provided with a complete display of status of all weapons and a remaining stores display indicating the total remaining weapons of the respective types. Comparison of a commanded word with the actual status of a given weapon position is employed to provide the pilot with a hung ordnance alarm.
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| 277 | Modular airborne launcher | US3750530D | 1971-10-04 | US3750530A | 1973-08-07 | CORDS E |
| Missile-launching apparatus for mounting on aircraft which enables conversion in the field between several configurations and which facilitates loading of missile containers in cramped locations. The apparatus includes a launching module having a central beam and a missile launcher on either side of the beam, the beam having mounts on its upper end for attachment to an aircraft bomb rack and mounted on its lower end for supporting another almost identical module. Each launcher includes a bulkhead at its front end, a debris tube at its rear end, and a gate at its center for receiving a missile-holding container. The missile container can be installed in a sideward direction by fully opening the gate, or in a front or rearward direction by pivoting open the bulkhead or debris tube. An arming handle is provided which sequentially moves a shear pin in the container to free the missile for launching, and then connects an electrical connector to the missile container.
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| 278 | Weapons control system | US3499363D | 1969-01-21 | US3499363A | 1970-03-10 | LAURO MICHAEL J |
| 279 | Electrical connector socket | US16231561 | 1961-12-21 | US3107966A | 1963-10-22 | ROBERT BONHOMME FRANCOIS |
| 280 | Airplane construction | US35765940 | 1940-09-20 | US2346809A | 1944-04-18 | WOODS ROBERT J |
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