| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Tandem rocket launcher | US30489952 | 1952-08-18 | US2780143A | 1957-02-05 | GRAHAM CONNELLY L |
| 62 | nolan | US2731885D | US2731885A | 1956-01-24 | ||
| 63 | Rocket projector with adapter | US48164943 | 1943-04-02 | US2659274A | 1953-11-17 | LAURITSEN CHARLES C |
| 64 | Rocket discharger | US5797148 | 1948-11-02 | US2609730A | 1952-09-09 | BERGSTROM LARS O |
| 65 | ROCKET LAUNCH SYSTEM AND SUPPORTING APPARATUS | PCT/US2011000237 | 2011-02-10 | WO2011100053A3 | 2011-11-10 | CHIN HOWARD M; CARRAHA KIMBERLY A |
| A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two secondary and two tertiary cables and lifted by a lower hoist guided by the secondary cables. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance. | ||||||
| 66 | ADJUSTABLE BOMB CARRIER | PCT/US2010026736 | 2010-03-10 | WO2010107634A3 | 2010-11-11 | VAN LIEW JEFFREY W; BAILEY ROBERT A |
| According to one embodiment, an apparatus comprises a structural body, one or more attachment couplers, and an adjustable store coupler. The structural body comprises a cylindrical portion and one or more end portions (32a, 32b) coupled to the cylindrical portion. The attachment couplers are configured to be coupled to a bomb rack of an aircraft. The adjustable store coupler has attachment points (70) arranged in a substantially linear manner. The attachment points are configured to couple one or more store systems to the adjustable store coupler. | ||||||
| 67 | METHOD AND APPARATUS FOR FAST DEPLOYING AND RETRIEVING OF TOWED BODIES | PCT/US2004030842 | 2004-09-21 | WO2005030576A2 | 2005-04-07 | PECKHAM CHRISTOPHER M; GAY THOMAS E; LEPINE KEITH; ZAHORUIKO JOHN A; DEVLIN JOHN J; COLBY SCOTT |
| In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position. | ||||||
| 68 | DEVICE FOR CARRIAGE OF A WEAPON SYSTEM FOR TACTICAL TRANSPORT AIRCRAFT | PCT/EP2013053143 | 2013-02-17 | WO2013121031A3 | 2014-02-20 | GAILLARD PATRICK |
| The invention relates to a fire support device, in particular for a tactical transport airplane, which device comprises: a. an interface (331) for mechanical fixing adapted to a load carrying pylon, in particular of an aircraft; b. an interface (335) for electrical power connection; c. a munition (361); d. a sighting system (250); e. means (240) for firing said munition; f. a fire control emitter and a fire control receiver (340) and means for connection between said emitter and said receiver. | ||||||
| 69 | SMART TRANSLATOR BOX FOR AGM-65 AIRCRAFT "MAVERICK" ANALOG INTERFACE TO MIL-STD-1760 STORE DIGITAL INTERFACE | PCT/US2009054684 | 2009-08-21 | WO2010096090A3 | 2010-12-02 | CAMPBELL EDWARD H |
| A smart translator "SMARTX" box provides an aircraft outfitted with an analog AGM-65 ("Maverick") interface with the same "look and feel" and capability to use a store outfitted with a digital MIL-STD-1760 interface as if the aircraft was fully 1760 compliant without any modifications to the electronics or software of either the aircraft or store. | ||||||
| 70 | MUNITIONS CONTROL UNIT | PCT/US2008052295 | 2008-01-29 | WO2008121431A3 | 2008-11-27 | SITZMANN RICHARD L; PETERS RYAN J; HAGGH ALAN |
| A munitions control unit (30) for integrating existing electronics of a vehicle (10) with at least one weapon (22), wherein said existing vehicle electronics are not equipped to interface with the at least one weapon includes a first I/O interface (32) for communicating control signals with said vehicle (10), at least one second I/O interface (34a-34d, 35a-35b, 37) different from the first I/O interface (32), said at least one second I/O interface communicating control signals with said weapon (22), a processor (57) and memory (58) operatively coupled to said first and at least one second I/O interface, and reconfigurable logic stored in memory and executable by the processor. The reconfigurable logic is operative to enable the munitions control unit to interface with a plurality of vehicles having different interfaces. | ||||||
| 71 | MUNITIONS CONTROL UNIT | PCT/US2008052295 | 2008-01-29 | WO2008121431A2 | 2008-10-09 | SITZMANN RICHARD L; PETERS RYAN J; HAGGH ALAN |
| A munitions control unit (30) for integrating existing electronics of a vehicle (10) with at least one weapon (22), wherein said existing vehicle electronics are not equipped to interface with the at least one weapon includes a first I/O interface (32) for communicating control signals with said vehicle (10), at least one second I/O interface (34a-34d, 35a-35b, 37) different from the first I/O interface (32), said at least one second I/O interface communicating control signals with said weapon (22), a processor (57) and memory (58) operatively coupled to said first and at least one second I/O interface, and reconfigurable logic stored in memory and executable by the processor. The reconfigurable logic is operative to enable the munitions control unit to interface with a plurality of vehicles having different interfaces. | ||||||
| 72 | Universal aircraft rocket/missile launcher (UARML) and triple launcher adapter (TLA) | US687357 | 1991-04-18 | US5148734A | 1992-09-22 | Eugene V. Lilly |
| A missile launcher system for use on fixed and rotary wing aircraft to carry, arm and launch missiles and rockets. The apparatus includes a retention unit a support beam, a positive stop, an electrical interface, and a triple launcher adapter with adjustable support arms. The triple launcher adapter (TLA) is designed to accommodate three different sizes of rockets or missiles at one time. The adjustable support arms of the TLA can be unbolted and moved in or out to compensate for the various rocket and missile sizes and shapes. | ||||||
| 73 | Aircraft missile launcher sway brace apparatus | US157365 | 1988-02-17 | US4829876A | 1989-05-16 | David A. Witt |
| A saddle sway brace (90) having a channeled planar plate (94) engageable on a missile launcher platform surface (56). Angled planar plates (100, 102) provide load support for aircraft outrigger equipment. A webbed reenforcing network (110, 112) is engageable with notches (122, 124) in the missile launcher for load support and stability. | ||||||
| 74 | Air-carried missle launcher | US36320 | 1987-04-09 | US4802400A | 1989-02-07 | Dennis Griffin; Ronald F. Delves |
| A missile launcher is provided with pyrotechnically-operated means for jettisoning the missile. The missile is hung under a sub-rail latched to the underside of the main launcher body and upon operation of the jettisoning means the sub-rail/missile combination is slid rearwardly to disengage the latches after which the combination is given a downward thrust away from the launcher body, the thrust being imparted just forward of the collective center of gravity of the missile/launcher combination to cause its downward departure to be assisted by negative lift. The jettisoning means may consist of a lever and linkage actuated by a gas-operated piston-and-cylinder. | ||||||
| 75 | Pivotal mono wing cruise missile with wing deployment and fastener mechanism | US373086 | 1982-04-29 | US4493136A | 1985-01-15 | Frederick D. Groutage; Samuel N. Conjerti; Lockburn S. Shaw |
| A moveable wing aircraft including a quick release, attachment mechanism carrying the aircraft on a bomb rack or other carrier and a mechanism for deploying the moveable wing from its captive carry position to its extended free flight position are disclosed. The aircraft includes an elongate fuselage, a portion of the top surface of which is substantially flat in order to accommodate the moveable wing. The moveable wing is positionable between a captive carry position in which it is aligned with the longitudinal axis of the fuselage and an extended free flight position. The single, moveable wing is pivoted around a central point from its captive carry position to its extended free flight position such that it is substantially perpendicular to the aircraft fuselage. The quick release mechanism extends through apertures in the wing in its captive carry position and is spring biased to retract through the wing and into the aircraft fuselage when released from the bomb rack or other carrier. The deployment mechanism includes a spring loaded cable and pulley arrangement and serves to connect the moveable wing to the fuselage and to bias it from its captive carry position to its extended free flight position when activated upon release of the quick release mechanism. | ||||||
| 76 | Missile launcher | US141962 | 1980-04-21 | US4475436A | 1984-10-09 | Dennis R. Campbell |
| A rotatable support mounts a plurality of missile carrying missile launchers for rotation about a center axis. Each launcher mounts a plurality of missiles for rotation about an axis. The rotatable support is rotated to successively bring each missile launcher into a launch position. Each such launcher is rotated to successively bring each missile carried by it into a launch position. | ||||||
| 77 | Pivotal mono wing cruise missile with wing deployment and fastener mechanism | US372870 | 1982-04-29 | US4453426A | 1984-06-12 | Frederick D. Groutage; Samuel N. Conjerti; Lockburn S. Shaw |
| A moveable wing aircraft including a quick release, attachment mechanism carrying the aircraft on a bomb rack or other carrier and a mechanism for deploying the moveable wing from its captive carry position to its extended free flight position are disclosed. The aircraft includes an elongate fuselage, a portion of the top surface of which is substantially flat in order to accommodate the moveable wing. The moveable wing is positionable between a captive carry position in which it is aligned with the longitudinal axis of the fuselage and an extended free flight position. The single, moveable wing is pivoted around a central point from its captive carry position to its extended free flight position such that it is substantially perpendicular to the aircraft fuselage. The quick release mechanism extends through apertures in the wing in its captive carry position and is spring biased to retract through the wing and into the aircraft fuselage when released from the bomb rack or other carrier. The deployment mechanism includes a spring loaded cable and pulley arrangement and serves to connect the moveable wing to the fuselage and to bias it from its captive carry position to its extended free flight position when activated upon release of the quick release mechanism. | ||||||
| 78 | Airborne missile launcher | US344097 | 1982-01-29 | US4429611A | 1984-02-07 | Delbert J. Oldham; John A. Karish |
| An airborne missile launcher for air launching of man-portable, tube-launched missiles includes a central support frame with attachment means for detachable attachment to an aircraft or other launching platform, with a central frame member having a launch tube saddle support assembly at each side of the frame member with quick detachable clamp means and an alignment guide for quickly positioning and securing launch tubes into position with auto connecting means for automatically connecting the electronics control system and coolant gas to the launch tube assembly upon clamping the assembly into position. An aerodynamic shell encloses the support structure and includes a quick release cover for providing access to the tube clamp assemblies for loading and unloading launch tubes. | ||||||
| 79 | Tandem rocket launcher | US133756 | 1980-03-25 | US4342252A | 1982-08-03 | Allen C. Hagelberg; Clark E. Allardt |
| A tandem rocket launcher is provided by mounting plural rockets in an elongated launch tube with associated guide and launch equipment for each rocket. A conical shield is placed between the rockets which deflects exhaust gases generated by firing the forward rocket away from the rearward rocket. The shield is then removed by firing of the subsequent rocket or pivoting of two halves of the deflector away from the path of travel of the subsequent rocket. | ||||||
| 80 | Aircraft weapon mountings | US795626 | 1977-05-10 | US4106389A | 1978-08-15 | Gerald David Walley |
| An aircraft has a fuselage with a forward cockpit, an aft mounted fin, and an upper deck extending between the two, there being a weapon launcher assembly of elongated form with a forward end through which rocket propelled weapons are launched, a rearward end through which rocket exhaust is dissipated, and an upper deck extending between the two, the launcher being pivotable between a stowed position wherein it lies with its upper deck smoothly continuous with the upper deck of the fuselage and an extended weapon launch position wherein the weapons can be launched clear of the forward cockpit. | ||||||
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