US3310947A - Safety apparatus for tandem-connected rockets - Google Patents

Safety apparatus for tandem-connected rockets Download PDF

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US3310947A
US3310947A US513062A US51306265A US3310947A US 3310947 A US3310947 A US 3310947A US 513062 A US513062 A US 513062A US 51306265 A US51306265 A US 51306265A US 3310947 A US3310947 A US 3310947A
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rocket
aft
rockets
tandem
deflector plate
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US513062A
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George F Shryock
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/38—Safety devices, e.g. to prevent accidental ignition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the present invention relates generally to safety devices and more particularly to an improved safety device for preventing ignition of both the booster and sustainer rockets of a missile due to the accidental ignition of one of them.
  • the invention is an improvement over Patent No. 2,871,658 issued to William J. Keck on February 3, 1959, for Sustainer Exhaust Gas Deflector.
  • tandem rockets It is customary to store tandem rockets in an assembled condition but unarmed until ready for launching. With the forward and aft rockets assembled in the unarmed condition, a'ccidental ignition of one of them has resulted in ignition of the other.
  • an object of the present invention is to provide a safety device between forward and aft rockets which will effectively prevent the hot gases from one accidentally ignited rocket from acting on and igniting the other.
  • Another object of the present invention is to provide a safety device which will prevent the complete ignition of a plurality of rockets arranged in tandem by venting the hot gases from the accidentally ignited rocket to the atmosphere.
  • a further object of the present invention is the provision of a safety device which will prevent the complete ignition of a pair of rockets in tandem by providing an exhaust chamber of maximized volume between the two rockets for receiving and discharging flames and hot gases from one of the rockets in the event of accidental ignition thereof.
  • Yet another object of the present invention is the provision of a safety device which will prevent the complete ignition of a pair of rockets by deflecting flames and hot gases from one accidentally ignited rocket into the atmosphere without contacting or igniting the other rocket.
  • FIG. 1 is an elevation showing a tandem rocket arrangement embodying the present invention
  • FIG. 2 is an enlarged vertical section view of the safety device of the present invention in its normal position between the forward and aft rockets and taken along the longitudinal axis of the assembled missile;
  • FIG. 3 is a view similar to FIG. 2 showing the safety device when the forward rocket is accidentally ignited
  • FIG. 4 is a view similar to FIG. 2 showing the safety device when the aft rocket is accidentally ignited
  • FIG. 5 is a perspective of the deflector plate of the present invention.
  • the invention consists of a device for use with a plurality of rocket systems, a pair of rockets being shown for the purpose of simplifying the disclosure of the invention.
  • the rocket assemblies or systems illustrated herein are connected in tandem with the safety device of the present invention therebetween such that the hot gases from an accidental ignition of one of the rockets are prevented from coming in contact with and igniting the other rocket.
  • the device consists of an adapter for connecting the rockets in tandem and having an exhaust chamber formed therein for receiving the exhaust gases of an accidentally ignited rocket and for venting such exhaust gases to the atmosphere.
  • an insulated deflector plate which is movable along a plurality of guide rods from a first position, where the exhaust from the accidentally ignited aft rocket can be vented to the atmosphere, to a second position, where the exhaust from the accidentally ignited forward rocket can be vented to the atmosphere.
  • the tandem rocket arrangement illustrated in FIG. 1 comprises a forward rocket 10 and an raft rocket 12-which are of conventional construction and design and an adapter 14- connecting the forward and aft rockets in tandem.
  • the adapter 14- is of unitary construction and consists of an aft cylindrical section 16 having a portion which fits into and is attached to the forward end 18 of the aft rocket 12.
  • Forward of the cylindrical section 16 is a frusto-conical section 20 provided with a series of equally spaced vent ports 22 having vent plugs 24 therein.
  • Forward of the frusto-conical section 20 is a forward cylindrical section 26 adapted to be attached to the aft end 28 of the forward rocket 10.
  • a retaining ring 30 Within the adapter at the junction of the frusto-conical section 20 and the forward cylindrical section 26, there is attached a retaining ring 30. Attached to and projecting forward from the forward head 40 of the aft rocket there are provided three parallel guide rods symmetrically arranged around the longitudinal axes of the rockets. The opposite ends of the guide rods terminate adjacent the retaining ring 30.
  • a deflector plate 42 is slidably mounted on the guide rods 38.
  • the deflector has an annular base 50, an annular hub 52 projecting from the base, and a conical deflecting portion 54 projecting from the hub. Projecting radially outwardly from the base of the deflector plate are three tabs 56, each having a guide aperture therein for slidably receiving the guide rod respective thereto whereby the deflector plate is adapted to be slidably mounted on the guide rods.
  • Insulation 46 is provided on both faces of conical portion 54.
  • An annular channel 58 is formed in the outer periphery of hub 52 which receives an O-ring seal 62.
  • the deflector plate 42 is normally positioned, as shown in FIG.
  • the aft rocket igniter 66 is centrally positioned in the aft rocket head 40 by a two position locking device 70, as described in Patent No. 2,871,658.
  • a two position locking device 70 In the safe position the igniter is held in place by three shear washers 72 such that upon the accidental ignition of the aft rocket the igniter 66 will be forced out of the forward head 40 thus shearing washers 72.
  • the shoulder rlng'74 securely holds the igniter in position.
  • Slidably mounted on guide rods 38 is an igniter ring 76 which is attached to the forward surface of igniter 66 and which is forced forwardly along guide rods 38 by the forward motion of igniter 66. Ring 76 will thus evenly distribute the pressure on the rear face of deflector plate 42 and will ensure that the deflector plate will effectively seal off the interior of the forward section of the adapter.
  • the interior of the aft section of the adapter bounded by deflector plate 42 and forward head 40 forms an exhaust chamber 76 which receives the exhaust gases from either accidentally ignited rocket and vents it to the atmosphere through the vent ports 22 after the vent plugs 24 Patented Mar. 28, 1967 practiced otherwise than as of the adapter c'auses clips 64 to fail and the deflector plate is forced aft along guide rods 38 by the blast of the forward rocket.
  • the deflector plate protects the aft rocket igniter 66 from contact with the exhaust of the forward rocket and allows the exhausts to be vented to the atmosphere through ports 22 in adapter 14.
  • the igniter is forced forwardly out of forward head 40 and moves the ring 76 into contact with the rear face of the deflector plate.
  • the forward interior portion of the adapter will be sealed oil and the exhaust gases from the aft rocket will be vented to the atmosphere through ports 22 in the adapter.
  • the pressure of the exhaust gases from the aft rocket will hold both the ring 76 against the deflector plate 42 and the igniter 66 against ring 76 until the aft rocket has been completely burned.
  • a safety device for preventing the complete ignition of tandem-connected rockets due to the accidental ignition of one rocket comprising adapter means for connecting a pair of rockets in fore and aft tandem formation and having a plurality of vent ports therein; a deflector plate movable along a guided path within the adapter from a first to a second position; said deflector plate in the first position being forward of the vent ports in the adapter, whereby the flames and gases occasioned by an accidental ignition of the aft rocket will be diverted through the vent ports and into the atmosphere; and said deflector in the second position being aft of the vent ports, whereby the flames and gases occasioned by an accidental ignition of the forward rocket will 'be diverted through the vent ports into the atmosphere.
  • a safety device as defined in claim 1 including an exhaust chamber defined by
  • said exhaust chamber being adapted to receive the flames and gases caused by an accidental ignition of either forward or aft rockets before the flames and gases are diverted through the vent ports to the atmosphere.
  • structure providing the guide path comprises a plurality of parallel guide rods extending between the finst and second position;
  • said deflector plate includes means for cooperating with said guide rods to permit the guided movement of said deflector plate between the first and second positions.
  • a safety device as defined in claim 4 including a ring slidably mounted on said guide rod-s, said ring normally positioned at the aft portion of said guide rods and movable along said rods to a position contacting said deflector plate upon the occurrence of an accidental ignition of the aft rocket.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Emergency Lowering Means (AREA)

Description

March 1%? G. F. SHRYOCK 3,319,947
SAFETY APPARATUS FOR TANDEM-CONNECTED ROCKETS Filed Dec. 10, 1965 2 Sheets-Sheet 1 A NV ENTOR BY Z i {Z ATTORNEY Mfih 2, 1%? e. F. SHRYOCK 3310,47
SAFETY APPARATUS FOR TANDEM-CONNECTED ROCKETS Filed Dec. 1.0, 1965 2 Sheets-Sheet 2 United States Patent 3,310,947 @AFETY APPARATUS FOR TANDEM-CONNECTED ROCKETS George F. Shryock, Cumberland, Md., assignor to the United States of America as represented by the Secretary of the Navy Filed Dec.,10, 1965, Ser. No. 513,062 6 Claims. (Cl. 60-225) The present invention relates generally to safety devices and more particularly to an improved safety device for preventing ignition of both the booster and sustainer rockets of a missile due to the accidental ignition of one of them. The invention is an improvement over Patent No. 2,871,658 issued to William J. Keck on February 3, 1959, for Sustainer Exhaust Gas Deflector.
It is customary to store tandem rockets in an assembled condition but unarmed until ready for launching. With the forward and aft rockets assembled in the unarmed condition, a'ccidental ignition of one of them has resulted in ignition of the other.
Accordingly, an object of the present invention is to provide a safety device between forward and aft rockets which will effectively prevent the hot gases from one accidentally ignited rocket from acting on and igniting the other.
Another object of the present invention is to provide a safety device which will prevent the complete ignition of a plurality of rockets arranged in tandem by venting the hot gases from the accidentally ignited rocket to the atmosphere.
A further object of the present invention is the provision of a safety device which will prevent the complete ignition of a pair of rockets in tandem by providing an exhaust chamber of maximized volume between the two rockets for receiving and discharging flames and hot gases from one of the rockets in the event of accidental ignition thereof.
Yet another object of the present invention is the provision of a safety device which will prevent the complete ignition of a pair of rockets by deflecting flames and hot gases from one accidentally ignited rocket into the atmosphere without contacting or igniting the other rocket.
Other objects, advantages and novel features of the present invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings wherein:
FIG. 1 is an elevation showing a tandem rocket arrangement embodying the present invention;
FIG. 2 is an enlarged vertical section view of the safety device of the present invention in its normal position between the forward and aft rockets and taken along the longitudinal axis of the assembled missile;
FIG. 3 is a view similar to FIG. 2 showing the safety device when the forward rocket is accidentally ignited;
FIG. 4 is a view similar to FIG. 2 showing the safety device when the aft rocket is accidentally ignited; and
FIG. 5 is a perspective of the deflector plate of the present invention.
Generally the invention consists of a device for use with a plurality of rocket systems, a pair of rockets being shown for the purpose of simplifying the disclosure of the invention. The rocket assemblies or systems illustrated herein are connected in tandem with the safety device of the present invention therebetween such that the hot gases from an accidental ignition of one of the rockets are prevented from coming in contact with and igniting the other rocket. The device consists of an adapter for connecting the rockets in tandem and having an exhaust chamber formed therein for receiving the exhaust gases of an accidentally ignited rocket and for venting such exhaust gases to the atmosphere. In cooperation with the exhaust chamber there is provided an insulated deflector plate which is movable along a plurality of guide rods from a first position, where the exhaust from the accidentally ignited aft rocket can be vented to the atmosphere, to a second position, where the exhaust from the accidentally ignited forward rocket can be vented to the atmosphere.
The tandem rocket arrangement illustrated in FIG. 1 comprises a forward rocket 10 and an raft rocket 12-which are of conventional construction and design and an adapter 14- connecting the forward and aft rockets in tandem. The adapter 14- is of unitary construction and consists of an aft cylindrical section 16 having a portion which fits into and is attached to the forward end 18 of the aft rocket 12. Forward of the cylindrical section 16 is a frusto-conical section 20 provided with a series of equally spaced vent ports 22 having vent plugs 24 therein. Forward of the frusto-conical section 20 is a forward cylindrical section 26 adapted to be attached to the aft end 28 of the forward rocket 10.
Within the adapter at the junction of the frusto-conical section 20 and the forward cylindrical section 26, there is attached a retaining ring 30. Attached to and projecting forward from the forward head 40 of the aft rocket there are provided three parallel guide rods symmetrically arranged around the longitudinal axes of the rockets. The opposite ends of the guide rods terminate adjacent the retaining ring 30.
A deflector plate 42 is slidably mounted on the guide rods 38. The deflector has an annular base 50, an annular hub 52 projecting from the base, and a conical deflecting portion 54 projecting from the hub. Projecting radially outwardly from the base of the deflector plate are three tabs 56, each having a guide aperture therein for slidably receiving the guide rod respective thereto whereby the deflector plate is adapted to be slidably mounted on the guide rods. Insulation 46 is provided on both faces of conical portion 54. An annular channel 58 is formed in the outer periphery of hub 52 which receives an O-ring seal 62. The deflector plate 42 is normally positioned, as shown in FIG. 2, within the opening of ring 30 with the O-ring sealing otf communication between the forward and aft section of the adapter. The deflector plate is held in this position by a plurality of flat frangible metal clips 64 secured to deflector plate 42 and overlapping plate 30.
The aft rocket igniter 66 is centrally positioned in the aft rocket head 40 by a two position locking device 70, as described in Patent No. 2,871,658. In the safe position the igniter is held in place by three shear washers 72 such that upon the accidental ignition of the aft rocket the igniter 66 will be forced out of the forward head 40 thus shearing washers 72. In the locked position the shoulder rlng'74 securely holds the igniter in position. Slidably mounted on guide rods 38 is an igniter ring 76 which is attached to the forward surface of igniter 66 and which is forced forwardly along guide rods 38 by the forward motion of igniter 66. Ring 76 will thus evenly distribute the pressure on the rear face of deflector plate 42 and will ensure that the deflector plate will effectively seal off the interior of the forward section of the adapter.
The interior of the aft section of the adapter bounded by deflector plate 42 and forward head 40 forms an exhaust chamber 76 which receives the exhaust gases from either accidentally ignited rocket and vents it to the atmosphere through the vent ports 22 after the vent plugs 24 Patented Mar. 28, 1967 practiced otherwise than as of the adapter c'auses clips 64 to fail and the deflector plate is forced aft along guide rods 38 by the blast of the forward rocket. In the aft position, the deflector plate protects the aft rocket igniter 66 from contact with the exhaust of the forward rocket and allows the exhausts to be vented to the atmosphere through ports 22 in adapter 14. If the aft rocket 12 is inadvertently ignited, the igniter is forced forwardly out of forward head 40 and moves the ring 76 into contact with the rear face of the deflector plate. The forward interior portion of the adapter will be sealed oil and the exhaust gases from the aft rocket will be vented to the atmosphere through ports 22 in the adapter. The pressure of the exhaust gases from the aft rocket will hold both the ring 76 against the deflector plate 42 and the igniter 66 against ring 76 until the aft rocket has been completely burned.
Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be specifically described. What is claimed is: 1. A safety device for preventing the complete ignition of tandem-connected rockets due to the accidental ignition of one rocket comprising adapter means for connecting a pair of rockets in fore and aft tandem formation and having a plurality of vent ports therein; a deflector plate movable along a guided path within the adapter from a first to a second position; said deflector plate in the first position being forward of the vent ports in the adapter, whereby the flames and gases occasioned by an accidental ignition of the aft rocket will be diverted through the vent ports and into the atmosphere; and said deflector in the second position being aft of the vent ports, whereby the flames and gases occasioned by an accidental ignition of the forward rocket will 'be diverted through the vent ports into the atmosphere. 2. A safety device as defined in claim 1 including an exhaust chamber defined by the interior of said adapter means bounded by the forward end of the aft rocket and said deflector plate in the first position;
said exhaust chamber being adapted to receive the flames and gases caused by an accidental ignition of either forward or aft rockets before the flames and gases are diverted through the vent ports to the atmosphere.
3. A safety device as defined in claim 2 wherein said deflector plate in the second position covers an igniter of the aft rocket.
4. A safety device as defined in claim 3 wherein structure providing the guide path comprises a plurality of parallel guide rods extending between the finst and second position; and
said deflector plate includes means for cooperating with said guide rods to permit the guided movement of said deflector plate between the first and second positions.
5. A safety device as defined in claim 4 including a ring slidably mounted on said guide rod-s, said ring normally positioned at the aft portion of said guide rods and movable along said rods to a position contacting said deflector plate upon the occurrence of an accidental ignition of the aft rocket.
6. A safety device as defined in claim 5 wherein said deflector plate includes a conical portion with insulation means disposed on both sides thereof; and said deflector plate is held in the first position by frangible metal clips.
References Cited by the Examiner UNITED STATES PATENTS 2,775,201 12/1956 Conway 102-49 2,829,491 4/ 1958 Teague 225 X 2,871,658 2/1959 Keck 60225 X 3,038,303 6/1962 Gose 60223 X 3,084,506 4/1963 Floyd et al. 60-225 CARLTON R. CROYLE, Primary Examiner.

Claims (1)

1. A SAFETY DEVICE FOR PREVENTING THE COMPLETE IGNITION OF TANDEM-CONNECTED ROCKETS DUE TO THE ACCIDENTAL IGNITION OF ONE ROCKET COMPRISING ADAPTER MEANS FOR CONNECTING A PAIR OF ROCKETS IN FORE AND AFT TANDEM FORMATION AND HAVING A PLURALITY OF VENT PORTS THEREIN; A DEFLECTOR PLATE MOVABLE ALONG A GUIDED PATH WITHIN THE ADAPTER FROM A FIRST TO A SECOND POSITION; SAID DEFLECTOR PLATE IN THE FIRST POSITION BEING FORWARD OF THE VENT PORTS IN THE ADAPTER, WHEREBY THE FLAMES AND GASES OCCASIONED BY AN ACCIDENTAL IGNITION OF THE AFT ROCKET WILL BE DIVERTED THROUGH THE VENT PORTS AND INTO THE ATMOSPHERE; AND SAID DEFLECTOR IN THE SECOND POSITION BEING AFT OF THE VENT PORTS, WHEREBY THE FLAMES AND GAGES OCCASIONED BY AN ACCIDENTAL IGNITION OF THE FORWARD ROCKET WILL BE DIVERTED THROUGH THE VENT PORTS INTO THE ATMOSPHERE.
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0335761A1 (en) * 1988-03-30 1989-10-04 AEROSPATIALE Société Nationale Industrielle Airborne vehicle with at least one releasable propulsion unit
US5245927A (en) * 1992-04-28 1993-09-21 Northrop Corporation Dual-tandem unmanned air vehicle system
US6293503B1 (en) * 1998-01-30 2001-09-25 D. Andy Beal Space Launch system with pressure reduction devices between stages
US10222189B2 (en) * 2016-07-22 2019-03-05 Raytheon Company Stage separation mechanism and method

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2775201A (en) * 1951-08-31 1956-12-25 British Messier Ltd Safety devices for apparatus containing stored pressure energy
US2829491A (en) * 1954-09-02 1958-04-08 Bendix Aviat Corp Two-stage liquid fuel rocket
US2871658A (en) * 1957-12-23 1959-02-03 William J Keck Sustainer exhaust gas deflector
US3038303A (en) * 1958-01-02 1962-06-12 Robert O Gose Thrust termination in solid propellant rockets
US3084506A (en) * 1961-04-06 1963-04-09 Floyd J F Rabardy Fire extinguisher for a rocket motor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2775201A (en) * 1951-08-31 1956-12-25 British Messier Ltd Safety devices for apparatus containing stored pressure energy
US2829491A (en) * 1954-09-02 1958-04-08 Bendix Aviat Corp Two-stage liquid fuel rocket
US2871658A (en) * 1957-12-23 1959-02-03 William J Keck Sustainer exhaust gas deflector
US3038303A (en) * 1958-01-02 1962-06-12 Robert O Gose Thrust termination in solid propellant rockets
US3084506A (en) * 1961-04-06 1963-04-09 Floyd J F Rabardy Fire extinguisher for a rocket motor

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0335761A1 (en) * 1988-03-30 1989-10-04 AEROSPATIALE Société Nationale Industrielle Airborne vehicle with at least one releasable propulsion unit
FR2629583A1 (en) * 1988-03-30 1989-10-06 Aerospatiale AIRCRAFT EQUIPPED WITH AT LEAST ONE LARGEABLE PROPELLER
US4903605A (en) * 1988-03-30 1990-02-27 Aerospatiale Societe Nationale Industrielle Air missile provided with at least one releasable power unit
US5245927A (en) * 1992-04-28 1993-09-21 Northrop Corporation Dual-tandem unmanned air vehicle system
US6293503B1 (en) * 1998-01-30 2001-09-25 D. Andy Beal Space Launch system with pressure reduction devices between stages
US10222189B2 (en) * 2016-07-22 2019-03-05 Raytheon Company Stage separation mechanism and method
US10514241B1 (en) * 2016-07-22 2019-12-24 Raytheon Company Stage separation mechanism and method

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