US3908933A

US3908933A - Guided missile

Info

Publication number: US3908933A
Application number: US594067A
Authority: US
Inventors: Wilbur H Goss; Henry H Porter; Richard B Roberts; Merle Antony Tuve; Jesse W Beams; Harner Selvidge
Original assignee: US Department of Navy
Current assignee: US Department of Navy
Priority date: 1956-06-26
Filing date: 1956-06-26
Publication date: 1975-09-30
Anticipated expiration: 1992-09-30

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.

Description

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

Claims

2. An aerial missile as recited in claim 1, wherein said means includes a plurality of hydraulically operated wing actuators, one of said actuators being provided for each said wing, a source of hydraulic fluid under pressure connected to said actuators, means for controlling flow of fluid to said actuators in response to an electrical signal, and links mechanically connecting the actuators to the wings.

3. In combination with an aerial missile having an airframe including a center body assembly, wings mounted for rocking movement on said body assembly, and means for boosting the missile to supersonic speed; hydraulically operated means within the missile and operable for imparting movement to the wings, said hydraulically operated means including a source of hydraulic fluid, a pump, a plurality of wing actuators, a turbine for operating the pump, means for supplying air under pressure to the turbine during flight of the missile, linkages connecting the actuators with the wings, valve means for controlling fluid flow to the actuators, and electrically operated means for controlling the valve means.

4. In combination with an aerial missile having an airframe comprising connected body assemblies, wings mounted for rocking movement on one of the body assemblies, guidance apparatus in the missile and producing electrical voltages representing missile position errors, and booster means for accelerating the missile to supersonic speed; hydraulically operated means within the missile and operable for imparting movement to the wings, said means including a source of hydraulic fluid under pressure within the missile, a pump, a plurality of wing actuators, a turbine for operating the pump, means for supplying air under pressure to the turbine during flight of the missile, linkages connecting the actuators with the wings, valve means for controlling fluid flow to the actuators, and electrically operated means connected with the guidance apparatus and responsive to said electrical voltages for controlling said valve means, whereby said actuators will be operated by said fluid flow for shifting the wings to correct for said position errors.

5. The combination recited in claim 3, including means for locking the wings during operation of the booster means, said wing locking means being releasable upon termination of operation of the booster means.

6. The combination recited in claim 3, including additionally means for locking the wings during operation of the booster means, said wing locking means including a cylinder mounted in the missile adjacent each wing, said wing having a recess, a locking pin having a piston movable in the cylinder, a spring normally urging one end of the pin into the recess for locking the wing, a solenoid operated valve, fluid connections between the solenoid operated valve, the cylinder and the hydraulic means, a source of electric power for the solenoid valve, and means for connecting said electric power source to the solenoid of the solenoid operated valve for opening said valve upon separation of the booster means from the missile whereby fluid will flow to the cylinder for shifting the piston against the compression of the spring and withdrawIng the locking pin from the recess for unlocking the wing.

7. The combination recited in claim 6, including additionally means operable for releasing the wings, whereby said wings may be detached from the body assembly.

8. In an aerial missile having an airframe and a body assembly, and wings mounted for rocking movement on the body assembly; means for mounting said wings for quick detachment from the body assembly, said means including a wing mounting bulkhead in the body assembly for each wing, a wing retaining sleeve in the bulkhead, each said wing having a spar mounted in the sleeve, a bearing rotatably connecting the sleeve with the bulkhead, tongues on the sleeve, and latches on the body assembly and engageable with the tongues.

9. The combination recited in claim 4, wherein said last mentioned means includes torque motors for said valve means, each of said torque motors comprising an armature, and a pair of coils surrounding the armature, said armature being movable in one direction by energization of one of said coils and being movable in the opposite direction by energization of the other of said coils.

10. The combination recited in claim 4, wherein said missile airframe includes an inner body mounted within the forwardmost body assembly at its forward end, and said hydraulically operated means includes an accumulator mounted in said inner body.

11. An aerial missile including, in combination, an airframe including forward, center, and aft body assemblies each having a wall defining a duct section, said assemblies being connected in alignment whereby the duct sections thereof will define a continuous duct extending throughout the length of the missile, the wall of the duct being shaped to define an inlet, a diffuser, and an exit nozzle, and a combustor in the duct within the center and aft body assemblies and including an outer shroud, a central can within the outer shroud, a pilot fuel injector assembly surrounding the central can at its forward end and fuel supply means extending into the combustor and connected to the pilot fuel injector assembly.

12. An aerial missile as recited in claim 11, including additionally fuel injector means in the central can, a source of fuel in the missile and positioned about the center body assembly, means connecting the fuel source with the fuel injector means, and fuel igniter means in the combustor.

13. A hydraulic system for a missile having a movable wing and a duct, comprising, a pump in the missile, a turbine in the missile and operable by airflow passing through the duct during flight of the missile, a wing actuator in the missile and including a cylinder, a piston in the cylinder and having a piston rod, linkage means connecting the piston rod to the wing, means connecting the wing actuator to the pump, a source of hydraulic fluid for the pump, the cylinder and for said last mentioned means, said pump forcing said fluid through said last mentioned means into said cylinder for shifting said piston and rod whereby said linkage will be moved for moving the wing, and means connected between said last mentioned means and said cylinder for controlling fluid flow to the cylinder in response to an electric signal.

14. A hydraulic system as recited in claim 13, wherein said fluid flow controlling means comprises a transfer valve, and a torque motor operatively connected with the valve.

15. A hydraulic system as recited in claim 13, including additionally means for locking the wing prior to operation of the turbine and pump.

16. A hydraulic system as recited in claim 13, wherein the wing is formed with a recess at its root end, and including additionally means for locking the wing against movement prior to operation of the turbine and pump, said last mentioned means including a cylinder, a locking pin having a piston movable in the cylinder, and a spring urging the pin into the recess.

17. In a missile having an airframe including a body, and wings mounted for rocking movement on the airframe; a hydraulic system in the missile and operative for imparting rocking movements to said wings, comprising, a turbine in the airframe, a pump driven by the turbine, a sump, a pair of accumulators, hydraulic fluid in the system, wing actuators operatively connected with the wings, one said actuator being provided for each wing and each said actuator including a cylinder, a piston in the cylinder and means connecting the piston with the wing; fluid conductor means, and electrically operated valve means, said fluid conductor means being connected between the pump, accumulators, sump, wing actuators and valve means, operation of the pump causing fluid flow to the actuator cylinders under control of said valve means.

18. The structure recited in claim 17, wherein said electrically operated valve means includes a transfer valve, and a torque motor for operating the transfer valve.

19. In an aerial missile having an airframe comprising a plurality of connected body assemblies each having a duct section, said duct sections defining a continuous duct for the missile, said continuous duct including a diffuser, a combustion chamber and an exit nozzle; a combustor in the combustion chamber and including an outer shroud, a central can mounted axially within the outer shroud, a pilot fuel injector assembly mounted within the upstream end portion of the outer shroud and surrounding the upstream end of the central can and fuel supply means mounted axially of the combustion chamber and connected to the pilot fuel injector assembly.

20. A combustor for an aerial missile, comprising, an outer shroud, a central can mounted axially within the outer shroud, a pilot fuel injector assembly mounted within the outer shroud and surrounding a portion of the central can, and fuel distribution means extending into the combustor axially of the shroud assembly and connected to the pilot fuel injector assembly.

21. A combustor as recited in claim 20, including igniter means extending into the outer shroud in the vicinity of the fuel distribution means.

22. A combustor for an aerial missile, comprising, a frusto-conical outer shroud, a central can mounted in the outer shroud, a pilot fuel injector assembly mounted concentrically within the outer shroud, pilot fuel injector means connected with the pilot fuel injector, main fuel injector means, and means mounting the pilot injector means and main injector means in spaced relation to each other within the shroud.

23. A combustor for an aerial missile, comprising, a frusto-conical outer shroud having a downstream end presented away from a fluid flow, a central can within the outer shroud, a pilot fuel injector assembly mounted concentrically within the upstream end portion of the shroud and surrounding one end of the central can, fuel distribution means connected to the pilot fuel injector assembly near one end thereof, main fuel injector means within the pilot fuel injector assembly and extending downstream of the pilot fuel injector means assembly, fuel supply means for said pilot fuel injector assembly and for said main fuel injector means, and igniter means mounted in the shroud upstream of the pilot fuel injector means.

24. In combination with a aerial missile having an airframe having a diffuser, a combustor in the airframe downstream of the diffuser, and fuel injector means in the combustor; a fuel system comprising a fuel tank, first fuel pressurization means in the missile and connected with the tank for initially pressurizing fuel in the tank, a second fuel pressurization means in the missile for pressurizing fuel in the tank during flight of the missile and after decay of pressure from said first fuel pressurization means to a predetermined value, said second fuel pressurization means including a scoop mounted to receive air flow passing through the diffuser during missile flight, a pump, a turbine connected with the pump for driving said pump, means connecting the pump with the scoop, and means for connecting thE pump with the fuel injector means, operation of the pump supplying fuel to the injector means during flight of the missile.

25. The combination recited in claim 24 including additionally fuel regulator means connected with the pump, said last mentioned means and the fuel injector means.