| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Apparatus for operatively supporting a machine gun | US09684827 | 2000-10-10 | US06286411B1 | 2001-09-11 | Paul H. Sanderson |
| A machine gun and associated armament apparatus, including an ammunition box for supplying belted ammunition to the gun, are exteriorly supported on a landing gear sponsor tow plate of a helicopter, adjacent a cabin area gunner's window, using a specially designed pintle support structure. The machine gun is horizontally rotatable about a vertical azimuth rotation axis which is forwardly tilted and substantially parallel to the similarly tilted rotor mast axis. The gun's upward firing elevation angle is limited to 1.5 degrees when the gun is pointed forwardly. However, due to the forward tilting of the gun's azimuth rotation axis, its maximum upward firing elevation angle automatically increases as the gun is swung rearwardly, thereby desirably increasing the gun's firing range to the side and rear of the helicopter while at the same time automatically maintaining the bullet path of the forwardly pointed gun safely below the forwardly drooped operational rotor tip path. A flare dispenser and a specially designed casing and link catching structure are also exteriorly supported adjacent the gunner's window. The external mounting of the gun and associated armament apparatus frees up cabin space, permits the gunner's window to be closed with the gun in a ready position, and permits a .50 caliber machine gun to be used as an alternative to either a 7.62 mm mini-gun or a single barrel 7.62 mm machine gun adjacent the gunner's window. | ||||||
| 22 | Rotatable pintle arm assembly for supporting a machine gun | US09250520 | 1999-02-16 | US06250196B1 | 2001-06-26 | Paul H. Sanderson |
| A central support plank section is transversely secured to the floor of a helicopter cabin area at exterior side wall door openings on opposite sides of the cabin area. Specially designed pintle arm assemblies are rotationally secured to opposite ends of the central support plank sections, with each of the pintle arm assemblies underlying and operatively supporting a cabin door area machine gun. Each pintle arm assembly is pivotable about a vertical axis in a manner permitting its machine gun to be horizontally swung into the cabin area to a stowed orientation therein, and is provided with a lock ring/detent structure that permits the pintle assembly to be quickly and easily locked in a selectively variable horizontal rotational orientation. An inboard post portion of the pintle arm assembly is rotatably secured to the central plank section by a specially designed securement structure that substantially reduces both rotational friction and horizontal and vertical “play” of the post portion at its juncture with the central plank section. An outboard post portion of the pintle arm assembly is spaced apart from the inboard post portion and is removably and rotatably connectable to its associated machine gun. In three disclosed embodiments thereof, the outboard post portion is (1) permanently secured to the balance of the pintle arm assembly, (2) a straight cylindrical post member removably received in a socket portion of the assembly, and (3) a tapered cylindrical post member removably received in a correspondingly tapered socket portion of the assembly. | ||||||
| 23 | Plank-based external aircraft armament/cargo carrying apparatus with pivotable outer end portions foldable into the aircraft cabin area | US09250787 | 1999-02-16 | US06241185B1 | 2001-06-05 | Paul H. Sanderson |
| Armament/cargo support apparatus for an aircraft includes a central support plank member transversely secured to a bottom side of a helicopter cabin area at door openings formed in forwardly and outwardly sloping opposite horizontal outer wall portions of the helicopter. The outer ends of the central plank member are inwardly offset from the opposite outer helicopter wall portions and have outer end surfaces which are parallel to such outer wall portions. Auxiliary plank sections are pivotally secured to the outer ends of the central plank section and are pivotable about axes parallel to the sloping helicopter outer side wall portions, between first positions in which they are folded onto top sides of the central plank section within the cabin area, and second positions in which the auxiliary plank sections extend outwardly beyond opposite sides of the helicopter. Front and rear support panel structures are secured to front and rear side edge portions of the auxiliary plank sections for pivotal movement relative thereto between cargo carrying positions in which they extend transversely to the central support plank sections, and folded orientations in which the front and rear support panel structures on each auxiliary plank section may be pivoted toward one another to be folded into the cabin area with their associated auxiliary plank section. Each end of the central plank section is supportingly securable to an external fuel tank. | ||||||
| 24 | Gyroscopic boresight alignment system and apparatus | US3731543D | 1972-01-28 | US3731543A | 1973-05-08 | GATES R |
| An improved system is provided for determining boresight misalignments of equipment, such as guns, radar antennas, cameras, gunsights, rocket launch rails, and the like, of carrier-based aircraft. The system of the invention utilizes intertial sensors which respond to the rotational rates of the aircraft carrier itself, and which use such rates as signal sources for the determination of angular boresight misalignments with respect to the armament data reference line of the particular aircraft. The system of the invention comprises a master sensor unit which contains two gyroscopes, and which is mounted on the aircraft during the test in position to extend along the armament data reference line. The system also includes a remote sensor unit which contains a single gyroscope, and which is mounted during the test on the actual equipment whose boresight misalignment is to be measured with respect to the aforesaid armament data reference line. The system of the invention compares the angular rates of the aircraft at the data line and at the equipment boresight axis to determine any misalignments of the boresight axis with respect to a parallel relationship with the armament data line.
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| 25 | Compatible missile/aircraft configuration | US3468501D | 1967-08-29 | US3468501A | 1969-09-23 | BAUM CLEOPHAS PHILEMON |
| 26 | Method and apparatus for launching rockets | US9210461 | 1961-02-27 | US3094896A | 1963-06-25 | CARSON JR RALPH C; GRILLO SALVATORE J; JANSEN TOR W |
| 27 | Movable jaw gun enclosure | US50759855 | 1955-05-11 | US2843022A | 1958-07-15 | BONNETTE RENE W; TASSIE ROBERT B |
| 28 | Movable slot closures | US23875851 | 1951-07-26 | US2811201A | 1957-10-29 | REID JR JAMES W |
| 29 | Air flow restrictor for gun port | US23022251 | 1951-06-06 | US2738710A | 1956-03-20 | ALLEN JOHN H |
| 30 | Aircraft gun sight mounting | US5653648 | 1948-10-26 | US2569819A | 1951-10-02 | ODILON LOBELLE MARCEL JULES |
| 31 | Aircraft armament assembly | US59497545 | 1945-05-21 | US2559727A | 1951-07-10 | MEYER EDWARD J |
| 32 | Gyrostabilizing system | US62106945 | 1945-10-08 | US2553786A | 1951-05-22 | REDEMSKE RALPH F |
| 33 | Adjustable chair for gunners | US67092746 | 1946-05-20 | US2453208A | 1948-11-09 | DUPLESSIS RENE E |
| 34 | Hydraulic remote operating system | US42461241 | 1941-12-27 | US2445765A | 1948-07-27 | EDWARD DAWSON; WATKINS FREDERIC M; SCHUH JR CHARLES N |
| 35 | Gunner's turret for aircraft | US52323044 | 1944-02-21 | US2439878A | 1948-04-20 | VILLEPIGUE JULIUS G |
| 36 | Power-operated aircraft gun turret | US41629041 | 1941-10-24 | US2434653A | 1948-01-20 | HOLSCHUH CARL G; WARNER LESTER C |
| 37 | Clamp structure | US50732143 | 1943-10-22 | US2426498A | 1947-08-26 | FRANKLIN HUBERT F |
| 38 | Aircraft gun mount | US47989943 | 1943-03-20 | US2409405A | 1946-10-15 | TROTTER JOHN C |
| 39 | Remote control system | US49760043 | 1943-08-06 | US2405678A | 1946-08-13 | CLIFTON WAHLBERG ERIC |
| 40 | Turret construction | US44260742 | 1942-05-12 | US2392106A | 1946-01-01 | SUTTON HARRY A |
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