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Publication numberUS3908933 A
Publication typeGrant
Publication dateSep 30, 1975
Filing dateJun 26, 1956
Priority dateJun 26, 1956
Publication numberUS 3908933 A, US 3908933A, US-A-3908933, US3908933 A, US3908933A
InventorsBeams Jesse W, Goss Wilbur H, Porter Henry H, Roberts Richard B, Selvidge Harner, Tuve Merle Antony
Original AssigneeUs Navy
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Guided missile
US 3908933 A
Abstract
1. An aerial missile including, in combination, an airframe comprising a plurality of connected body assemblies having duct sections defining a duct extending throughout the length of the body and having a wall, said wall providing an inlet, a diffuser communicating with the inlet, a combustion chamber communicating with the diffuser and an exit nozzle communicating with the combustion chamber, a cowl lip connecting the forwardmost body assembly and the wall of the forwardmost duct section at their corresponding forward ends, wings on the airframe and mounted for rocking movement about their root axes, longitudinally spaced partitions surrounding the duct wall and defining a compartment, an explosive charge in the compartment and surrounding the duct, a fuze system for the charge, and means mounted on one of the partitions and operable for imparting rocking movement to the wings.
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Description  (OCR text may contain errors)

United States Patent [191 Goss et al.

1 51 Sept. 30, 1975 1 GUIDED MISSILE [73] Assignee: The United States of America as represented by the Secretary of the Navy, Washington, DC.

[22] Filed: June 26, 1956 [21] App]. No.: 594,067

[52] US. Cl 244/321; 60/270 [51] Int. Cl. F42B 15/02 158] Field of Search 244/14. 3.21; 114/201;

[56] References Cited UNITED STATES PATENTS 2.459.009 1/1949 Wallis 244/36 2.557.401 6/1951 Agins 244/311 2.603.434 7/1952 Merrill. 244/114 2.690.314 9/1954 Porter 244/311 2.744.697 5/1956 Van Allen.. 244/3.15 2745.095 5/1956 Stoddard... 244/3.l3

2.769.601 1 1/1956 Hagopian 244/14 2.818.914 1/1958 Thomann ct a1 114/20 2.82-1.71 1 3/1958 Porter 244/321 2.873.074 2/1959 Harris et a1. 244/321 2.915.747 12/1959 Segerstrum 343/73 FUEL ensssumzmou 22a JAILFIPE [$8 COMBUSTOR [B TRACKING FLARE HOLDER [D 2002 BEAM RIDING WAVE GUIDE 2030 TELEMETERING NOTCR ANTENNAE I78 I FIN [/7 a 54 gr: 144 28g 2.996.707 8/1961 Hirsch 343/73 OTHER PUBLICATIONS TMa-l9852/to39B-1A-9, Depts. of Army & Air Force, Mar. 1953, pp. 218232.

Radar Guided Missile, Wireless World, Feb. 1956, pp. 67-70.

Primary E.\'aminerVerlin R. Pendegrass Attorney. Agent, or FirmR. S. Sciascia; J. S. Lacey; W. G. Finch EXEMPLARY CLAIM 1. An aerial missile including, in combination, an airframe comprising a plurality of connected body assemblies having duct sections. defining a duct extending throughout the length of the body and having a wall. said wall providing an inlet. a diffuser communicating with the inlet, acombustion chamber communicating with the diffuser and an exit nozzle communicating with the combustion chamber, a cowl lip connecting the forwardmost body assembly and the wall of the forwardmost duet section at their corresponding forward ends. wings on the airframe and mounted for rocking movement about their root axes. longitudinally spaced partitions surrounding the duct wall and defining a compartment, an explosive charge in the compartment and surrounding the duct, 21 fuze system for the charge, and means mounted on one of the partitions and operable for imparting rocking movement to the wings.

Claims, Drawing Figures STATIC PRESSURE PROBE I26 FUEL TANK "ZLDRAULIC SVS 2Z0 STEERING INTELLSYS. 212

, rt ist cou rggt CONTROL svstsm 2/4 $225,? FUZE svs'rsu- 5 POWER svsrsu z/s WING I13 ,runamz AIR INYAKE srnur 4 FETY a mums/.52 mums marzmuz I24 muznmmr RA" PRESSURE PROBE I28 US. Patent Sept. 30,1975 Sheet3of59 3,908,933

m T N E V m ATTORNEY wmw vmw US. Patent Sept.30,1975 Sheet40f59 3,908,933

I NVENTOR ATTORNEY US. Patent Sept. 30,1975 Sheet50f59 3,908,933

U.S. Patent Sept.30,1975 Sheet90f59 3,908,933

FIG. 12.

532 gllllfi llllig A 0,

mull") I if FUEL INLET -FROM FUEL SHUT-OFF VALVE //4" STEEL LOCKING BALLS 722 PREc'sloN SPRING 0 cowsmm' TORQUE THUMB scar-1w *wmw VALVE PENING SPRING 7/8 LOCKING GROOVE 738-FOR OPEN POSITION 4 725$ OPEN Pas/7,0

INVENTOR FUEL SHUT-OFF VALVE ATTORNEY US. Patent Sept. 30,1975 Sheet 10 0f59 3,908,933

FIG/4.

NITROGEN FLOW CONTROL UNIT Fuel Pressurizafl'an System 560 SURGE PREVENTATIVE PISTON 44.9

FRO/"NITROGEN TANK 448 580 x k k 21%HMHHHHHHHH Tumm- RA M PRESSURE IN VENTOR ATTORNEY US. Patent S apt. 30,1975

308 FIG. /6.

HYDRAULIC SYSTEM (Packag/ng Arrangemenf) FORWARD ACCUMULATOR BOD! STATIC PRESSURE LINE FUEL SHUT-OFF VALVE wme LOCK FILTERS TORQUE MOTOR FILL PLUG RETUR V HYDRAULEJEST CONNEfTIONS I LOOK TEST CONNECTIONS HYDRAULIC PRESSURE GAGE HYDRAULIC SUMP FQRWA R0 Sheet 12 of 59 PILOT REGULATOR I382 wme ACTUATOR wms ACTUATOR I C WING /I2 1-.

IN VENTOR ATTORNEY U..S. Patent Sept. 30,1975 Sheet 13 0f 59 FIG. [7

HYDRAULIC SYSTEM (Packag/ng Arrangement) HYDRAULIC SUMP TURBINE A R INTAKE wms ACTUATOR I I I 1 I383 WING ACTUATOR O WING LOCK I40 Ts/QESEER ACCUMULATOR E I922 FILTER HYDRAULIC PUMP INVENTOR ATTORNEY US. Patent Sapt.30,1975 Sheet 14 of59 3,908,933

FIG. 18. E0

HYDRAU LIG SYSTEM (Packaging Arrangemenl} NITROGEN SUPPLY FOR FUEL PRESSURIZATION BLADDERS MANIFOLD HYDRAULIC PUMP I390 TURBINE AIR INTAKE c WING //4 l.

wme LOCK WING ACTUATOR TRANSFER VALVE 4 cnzcx VALVE ggg ROLL RATE GYRO I820 THREE WAY SOLENOID 450 cNEcK VALVE I385 8 206/ wme ACTUATOR A a 5 RATE GYROS 308 FROM RAM AIR AT TURBINE FUEL PUMP IN VENTOR ATTORNEY US. Patent Sept .30,1975 Sheet 15 0f59 3,908,933

FIG. [9.

HYDRAULIC SYSTEM (Packaging Arrangement) I384 wms ACTUATOR TO FUEL PRESSURIZATION BLADDERS MANIFOLD TORQUE MOTOR A 8 8 RATE GYROS WAY SOLENOID VALVE TORQUE MOTOR 1 CHECK VALVE I TRANSFER VALVE I C WING [I5 L WING ACTUATOR FUEL REGULATOR FUEL PUMP TO RAM PRESSURE PROBE INVENTOR ATTORNEY US Patent Sept. 30,1975 Sheet 16 of 59 FROM NITROGEN SUPPLY WING 1/4 NOTE:

FOR PURPOSE OF CLARITY THE FLEXIBLE FLUID LINES SUPPLYING THE HYDRAULIC WING AGTUATORS HAVE D W Y F L w n m w M E N U A E L m T B U A WING //3 WING [/2 INVENTOR ATTORNEY wme RETAINING SLEEVE 34/ FIG. 2/.

US Patsnt Sept. 30,1975 Sheet 18 of59 3,908,933

US. Patent Sept. 30,1975 Sheet 19 of 59 3,908,933

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2459009 *May 25, 1946Jan 11, 1949Vickers Armstrongs LtdAircraft body and wing arrangement
US2557401 *Jan 10, 1945Jun 19, 1951Arma CorpRemote control apparatus
US2603434 *Sep 28, 1945Jul 15, 1952Grayson MerrillPilotless aircraft
US2690314 *Dec 15, 1949Sep 28, 1954Us NavyLong-range guided athodyd
US2744697 *Jun 25, 1952May 8, 1956James A Van AllenCosmic ray altimeter
US2745095 *Sep 4, 1947May 8, 1956Stoddard James VRadiant energy control system for missile guidance
US2769601 *Aug 18, 1950Nov 6, 1956Northrop Aircraft IncAutomatic radio control system
US2818914 *Feb 26, 1954Jan 7, 1958Mach Tool Works OerlikonSystem of containers for at least two liquids and a pressure gas
US2824711 *Mar 22, 1950Feb 25, 1958Porter Henry HVehicle for testing control systems at supersonic speeds
US2873074 *Oct 9, 1953Feb 10, 1959Sperry Rand CorpFlight control system
US2915747 *Oct 5, 1950Dec 1, 1959Raytheon CoEcho ranging system
US2996707 *Jul 26, 1954Aug 15, 1961Hazeltine Research IncRadar control system
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4745740 *Feb 24, 1986May 24, 1988The Boeing CompanyVelocity controller for ramjet missile and method therefor
US4757960 *Mar 27, 1986Jul 19, 1988Centre National D'etudes SpatialesLost-fluid hydraulic actuation system
US5325302 *Sep 23, 1991Jun 28, 1994Bvr Technologies, Ltd.GPS-based anti-collision warning system
US6267326Aug 9, 1999Jul 31, 2001The Boeing CompanyUniversal driver circuit for actuating both valves and ordnances
US6588968 *Mar 5, 2001Jul 8, 2003Astrium GmbhApparatus for releasably interconnecting structural components of rotational symmetry
US7161545 *Apr 19, 2005Jan 9, 2007Benq CorporationEmbedded antenna device
US7347644 *Aug 4, 2005Mar 25, 2008Tuf-Tite, Inc.Multi-use adapter ring for stackable riser components for on-site waste systems
US7767944Mar 7, 2007Aug 3, 2010Raytheon CompanyPiezoelectric fiber, active damped, composite electronic housings
US7770333Oct 15, 2004Aug 10, 2010Tuf-Tite, Inc.Adapter ring for on-site waste treatment or drainage systems
US7802376 *Nov 4, 2005Sep 28, 2010Huettlin HerbertApparatus for treating particulate material
US8049148Jun 25, 2010Nov 1, 2011Raytheon CompanyMissile airframe and structure comprising piezoelectric fibers and method for active structural response control
US8341963 *Mar 3, 2008Jan 1, 2013Lfk-Lenkflugkoerpersysteme GmbhValve control unit for ramjet propulsion system as well as guided missile having such a valve control unit
US20120227409 *Mar 8, 2011Sep 13, 2012Bruce ParadiseAircraft fuel system cooling flow device
CN102765471BJul 2, 2012Jul 16, 2014江西洪都航空工业集团有限责任公司一种导弹翼面根肋与舱段纵梁一体化结构
WO2010002373A1 *Jul 2, 2008Jan 7, 2010Raytheon CompanyPiezoelectric fiber, active damped, composite electronic housings
WO2010006724A2 *Jul 8, 2009Jan 21, 2010Diehl Bgt Defence Gmbh & Co. KgSolid-propellant rocket motor
Classifications
U.S. Classification244/3.21, 60/768
International ClassificationF42B10/00, F41G7/20, F23R3/00, H01Q1/27, F41F3/04, F42B12/30, F02K9/95, F02K9/00, F41G7/00, F02K7/00, F23R3/60, H01Q1/28, F02K7/18, F42B10/64, F42B12/02, F41F3/00, F02C7/22
Cooperative ClassificationF23R3/60, F02C7/22, F42B12/30, F02K9/95, F02K7/18, F42B10/64, H01Q1/281, F41G7/20, F41G7/008, F41F3/04
European ClassificationF23R3/60, F41G7/20, H01Q1/28B, F42B10/64, F02K7/18, F41F3/04, F42B12/30, F02K9/95, F41G7/00G, F02C7/22