US1102653A - Rocket apparatus. - Google Patents

Rocket apparatus. Download PDF

Info

Publication number
US1102653A
US1102653A US1913792707A US1102653A US 1102653 A US1102653 A US 1102653A US 1913792707 A US1913792707 A US 1913792707A US 1102653 A US1102653 A US 1102653A
Authority
US
United States
Prior art keywords
rocket
apparatus
rotation
tube
explosive
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
Inventor
Robert H Goddard
Original Assignee
Robert H Goddard
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Robert H Goddard filed Critical Robert H Goddard
Priority to US1913792707 priority Critical patent/US1102653A/en
Application granted granted Critical
Publication of US1102653A publication Critical patent/US1102653A/en
Anticipated expiration legal-status Critical
Application status is Expired - Lifetime legal-status Critical

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/74Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/76Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
    • F02K9/763Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with solid propellant
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00Power plants
    • Y10S60/915Collection of goddard patents
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00Machine element or mechanism
    • Y10T74/12Gyroscopes
    • Y10T74/1218Combined

Description

R. H. GODDARD.

ROCKET APPARATUS.

APPLICATION FILED oo'r.1, 1913.

Patented July 7, 1914.

ROBERT H. GODDARD, OF WORCESTER, MASSACHUSETTS.

ROCKET APPARATUS.

Specification. of Letters Patent.

Patented July 7, 1914.

Application led October 1, 1913. Serial No. 792,707.

To all whoml it may concern:

Be it known that I, ROBERT H. GoDDAnD,

. a citizen of the United Sta-tes, residing at Worcester', in the county of Worcester and State of Massachusetts, have invented a newand useful Rocket Apparatus, of which the following is a specification.

This invention relates to a rocketuapiparatus and particularly to a form of such apparatus adapted to transport photographlc or other recordin heights. Certam features of the inventlon are also applicable to\ the display of signals or to the projection of explosives.

Mathematical analysis shows that in any rocket apparatus of given mass, the necessary propelling charge varies according to` an expression in vhichthe percentage of the heat energy of the charge which is transformed to kinetic energy' enters. in an exponential relation. Hence, any increase 1n the eiiciency in the transformation results in greatly increased velocity of the appa-4 ratus hand also permits a reduction in the amoun of explosive used.

It is y ne ofthe objects of my invention-to provide a rocket apparatus in which the transformation above mentioned is perfrmed with great efficiency whereby the velocity and' range of flight are greatly in-I means for maintaining the speed of rotation thus attained; and to provide means for so supporting the recording apparatus within the rocket that said apparatus shall not par` take of the rotation of the rocket apparatus as a whole.

With these objlects in view my invention comprises certain devices, arrangements and combination of parts which will be herein'- after described and more fully set forth in the appended claims. l

A preferred form of my invention is shown in the drawings in which-4 Figure 1 is a longitudinal view, partly in.

instruments to extreme tube 11.

section,` of my rocket apparatus as a whole: Fig. 2 1s an enlarged longitudinal sectional vlew ofthe head of the apparatus: Figs. 3 and 4 are enlarged transverse sectional views taken alon the lines 3 3 and 4 4 respectively, in Fig.` 1: andFig. 5 is a vertlcal elevation of a frame work from which the apparatus maybe fired, drawn to a reduce scale. v

Referring to Fig. l, the rocket apparatus comprises a primary rocket having acasing contamln a combustion chamber 10 from whlch epends an elongated tapered The explosive material is indicated as a plurality of disks 12 secured within the chamber 10 by a, casting 13. The disks 12 are preferably formed of a series of materials having progressively increasing rates of combust-ion so that as each disk is ignited it burns with increased rapidity and keeps the pressure in `the chamber 10 constant, for which specic pressure the tapered tube 11 is designed. Similar results may be attained by using the explosive in a single mass of progressively varying comf position in place of the plurality of disks herek shown, and this construction is also within the scope of my invention. In the ordinary forms of rocket apparatus, the gases of combustion are discharged through an opening at the rear of theapparatus but I have discovered that by providing the elongated tapered tube 11, I am able to greatly increase the etliciencyof the device. The tube is shown in the form of a truncated cone of slight taper and the length of the tube should be not less than three times as great as its longest diameter, while a greater ratio than this will often be necessary to obtain satisfactory results. This construction takes advantage of the expansion of the gases as they .pass through the tube and also allowsthe combustion vof the gases to be completed before they nally issue from the tube. By experimentally determining the best proportions for the tube 11, a maximum percentage of the heat energy ofthe disks 12 may be transformed into kinetic energy. A fuse lft'is indicated which extends downwardly Within the tube 11 and provides means by which the disks may be ignited.

In order to provide the necessary speed of rotation of the apparatus so that it may produce rot-ation of the ap aratus.

To provide for ignitingt eseveral charges 16 simultaneously, I arrangeI withinl the outer surface of each charge a ne metal la- "ment or heating element 17, these filaments being all connected in series by wires 18 with a battery 19 and a key 2U. The closing of the key 20 sends a current throughthe wires.'

18 which instantaneously raises the temperature of the filaments 17 and simultaneously,

ignites the several charges 16. The exploL sive force of the gases from the material 16 forces the filaments 17 and the` wires 18 out of the tubes 15 so that they can not thereafter interfere with the rotation or iight of.y

the apparatus. l

In order that this preliminary rotation may be conveniently produced, I provide the;

vertical framework 21 shown in Fig. 5 in which the rocket is supported upon ball bearings 22 and 23. Ater the charges 16 have been ignited and the desired speed of= rotation has been attained, the fuse 14 may be lighted and the flight of the rocket will commence.

In order that the apparatus carried by the rocket may be 'given a further flight after the propelling charge of the main apparatus.

has been substantially consumed, I provide; an elongated tubular projection or firingl tube 24 at the forward extremity of the cast- .,10- ing 13.- -Within this tube I provide an auxil viary rocket comprising a combustion cham-l ber 25 ha'ving a rearwardly extendedA tapered` tube 26 an'd containing a plurality of disks of explosive material 27, these parts being substantially similar to the corresponding parts in the main apparatus but constructed on a somewhatreduced scale.

A fuse 28iextends from the explosive ma-;

y'terial 27 through an opening in thec'astingx 13 and projects a short distance into the last. disk 12 of explosive material in the 'chamber 10. Thus when the propelling) charge in the main rocket apparatus "is su stantially exhausted, the fuse 28 will be ignited and the firing tube 2 4 will act as a gun from which the'* auxiliary rocket will be projected for much .less weight .than the com further Hight. As the auxiliar rocket is of j ined weight of'l'sthefprimary land 1 auxiliary rockets, a giveiamount ofjexplosive in the auxiliary rocket will givev a much greater increase in Hight than vthe-same 4alnount of explosive wollltld produce if burned in the primary (eti: l .4 Y. y

.if Tofprovde for thel speed-of if rotation of the auxiliary emparatus,y which will have been somewhat reduced by the fric; tion of the atmosphere during the Hight, I provide in the vhead 29 of the auxiliary rocket a plurality of transverse backwardly curved tubes or recesses 30, similar to the recesses 15 shown in Fig. 3. The recesses 30 arey provided with explosive charges 31 and within the recesses are also mounted a series of small tubes 32. extending inwardly to the axis of the apparatus where the unite and are further extended downwar ly `into the explosive charge 27 These tubes are filled with a rapidly burning compound which is ignited when the explosivev char-ge 27 has been consumed to a predetermined point and by which the charges 31 are thereafter igl nited to increase or restore the speed of rotation of the auxiliary rocket.`

Within the apparatus head 29 is pivotally mounted a support 33 upon which in turn is mounted any desired form of recording apparatus. In the particular embodiment of my invention shown in the drawings this apparatus is indicated as a camera 34. The

head 29 is provided with a series of openinlgs'-y 35 separated by narrow su ports 36. y speed of rotation of the head) is so great that the passage of the-supports 36 iii front of the camera does not interfere with the taking of photographs thereby. In order that the sup ort 33 may not partakeof the rotation of t e'head 29, I provide within the supporta roscope 37 mounted in bearings 38 upon said support and to provide Ithe high'initial speed of rotation nec` essary for the operation of the gyroscope, I construct'the, latter asl the armature of a threefphase induction Jnotor having `field coils 39, mounted on a frame 4() also secured to the support 33. The field coils are connected to wires 41 secured within an insulating plug 42 in thesuplport 33. lVires 43 maybe introduced throug an opening 44 in the head 29 and caused to make contact with the wires 41 in the .plug 42, the wires 43 being 'connected to anymsuitable source of threephase current. 'en the gyroscope has attained lthe requisite speedof rotation, the wires 43 ma be withdrawn and the opening '44 may be c osedrwith the screw 45 shownin Fig. 1.

In order that the apparatus" may be brought back to earth without damage thereto, a parachute arrangement may be provided but as such arrangements arev well .known and form no part of my invention, I

have omitted the same from the drawings for the sake of showing other features more clearly. It is also within the scope of my invention to provide the auxiliary rocket with a firing tube from which a third rocket may be discharged and to continue this arrangement to any -desired extent. Several eatures ofmy invention. are also applicable to a structure in Which the apparatus head is secured directly to the casting 13, the auxiliary rocket being omitted, and this construction I also consider within the scope of my invention.

The operation of my device has been clearly indicated in the preceding description but may be brieiy restated as follows:

apparatus a high speed of rotation and when this has been attained the fuse 14 may be ignited to start the rocket on its Hight. When the apparatus as a Whole has been projected to a considerable height and the propelling charge 12 has been substantially exhausted, the fuse 28 will be ignited which in turn will ignite the charge 27 resulting in the firing of the auxiliary rocket from the tube 24. When the charge 27 is partially consumed, the explosive material 31 in the tubes will be ignited to increase the speed of rotation of the auxiliary rocket. While the rocket as a whole and the auxiliary rocket revolve at a high speed of rotation, the effect of the gyroscope is to AVmaintain the support 33 in the same relative position in which it commenced the iight so that the camera 34 may be di,- rected before the flight in any desired direction and will retain that direction throughout the flight.

While a preferred form of my invention is shown in the drawings, it is obvious that many changes may be made in the construction herein shown without departing from the spirit and scope of my invention and I do not wish to be limited to the details herein disclosed, but

What I do claim is 1. In a rocket apparatus, in combination, a primary rocket, comprising a combustion chamber and a iring tube, a secondary rocket mounted in said irinfg tube, and means for firing said secondary rocket when the explosive in the primary rocket is substantially consumed.

2. In a rocket apparatus, in combination, a combustion chamber containing an explosive and a rearwardly extended tapered tube connected with said chamber through which the gaseous products of combustion are discharged, said tube beingin the form of a truncatedcone of slight taper and having its length equal to not less than three times its longest diameter.

3. In a rocket apparatus, in combination, a primary rocket having a firing tube, a secondary rocket mounted in said firing tube, and adapted to be ired therefrom, means in said primary rocket for causing initial rotation of said rockets, and means in said secondary rocket for thereafter maintaining said secondary rocket in rotation.

4. In a rocket apparatus, in combination, a casing, means in said casing for propelling said rocket apparatus, and additional means in said casing for rotating said apparatus, said latter means comprising ay plurality of substantially radial transverse tubes back- Wardly curved with relation to the direction of rotation of the rocket apparatus and containing explosive material to ether with heating elements embedded therein by which the explosive material in all of the may be iired simultaneously. 5. In av rocket, in combination, means for producing initial rotation of the rocket, a casing, a chamber therein containing a charge of propelling explosive, a plurality ,of substantially radial curved tubes in f said casing also containing an explosive, and iring means connecting said explosivesl by which the explosive in the radial/tubes is ignited when the propelling explosive is consumed to a predetermined extent and acts to restore the initial speed of rotation of the rocket.

6. A rocket having in combination a combustion chamber, an apparatus head containing a support for the apparatus, means for rotating the rocket, and means to prevent rotation of' the apparatus support.

7. In a rocket apparatus, the combination,

a combustion chamber and an apparatus head, said head containing a pivotally mounted support for the apparatus and having a lgyroscope mounted thereon by which Y thesupport may be restrained from rotation with the head.

8. In a rocket', in combination, an apparatus head, a support forthe apparatus pivotally mounted within the head, a gyroscope mounted upon the support, and means for imparting a high initial speed of rotation to said gyroscope.

In testimon whereof I have hereunto set my hand, in t e presence of two subscribing witnesses.

ROBERT H. GODDARD. Witnesses:

FRANCIS W. HIxoN, C. FoRREs'r WEssoN.

tubes

US1913792707 1913-10-01 1913-10-01 Rocket apparatus. Expired - Lifetime US1102653A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US1913792707 US1102653A (en) 1913-10-01 1913-10-01 Rocket apparatus.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US1913792707 US1102653A (en) 1913-10-01 1913-10-01 Rocket apparatus.

Publications (1)

Publication Number Publication Date
US1102653A true US1102653A (en) 1914-07-07

Family

ID=3170849

Family Applications (1)

Application Number Title Priority Date Filing Date
US1913792707 Expired - Lifetime US1102653A (en) 1913-10-01 1913-10-01 Rocket apparatus.

Country Status (1)

Country Link
US (1) US1102653A (en)

Cited By (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2442528A (en) * 1943-11-20 1948-06-01 Aerial Products Inc Rocket device
US2447200A (en) * 1943-09-03 1948-08-17 Aerojet Engineering Corp Exhaust nozzle for rocket motors
US2468795A (en) * 1944-10-11 1949-05-03 Winters Starling Flare
US2479829A (en) * 1943-10-23 1949-08-23 Daniel And Florence Guggenheim Rotating combustion chamber with continuous rearward discharge
US2563265A (en) * 1943-09-21 1951-08-07 Aerojet Engineering Corp Rocket motor with solid propellant and propellant charge therefor
US2596644A (en) * 1946-12-10 1952-05-13 Us Sec War Automatically detachable flashless nozzle for rockets
US2623465A (en) * 1949-02-15 1952-12-30 Brandt Soc Nouv Ets Projectile
US2644396A (en) * 1948-10-01 1953-07-07 United Aircraft Corp Aerial missile
US2724237A (en) * 1946-03-05 1955-11-22 Clarence N Hickman Rocket projectile having discrete flight initiating and sustaining chambers
US2745347A (en) * 1951-07-06 1956-05-15 Armstrong Whitworth Co Eng Self-projected missiles
US2748703A (en) * 1948-04-27 1956-06-05 Wilbur H Goss Rocket type launching carriage for ordnance missile
US2750887A (en) * 1952-01-31 1956-06-19 Stanley J Marcus Motor mechanism for missiles
US2766581A (en) * 1950-06-30 1956-10-16 Curtiss Wright Corp Ram jet engine
US2776622A (en) * 1947-05-27 1957-01-08 Robert Roger Aime Device for attaching auxiliary rockets to a flying machine
US2783138A (en) * 1944-04-11 1957-02-26 Aerojet General Co Propellant compositions
US2792784A (en) * 1950-10-27 1957-05-21 Bristol Aeroplane Co Ltd Prime movers
US2804823A (en) * 1955-05-13 1957-09-03 Jablansky Louis Multiple unit projectile
US2821922A (en) * 1953-08-24 1958-02-04 Lawrence W Brown Rocket toy and launcher therefor
US2824711A (en) * 1950-03-22 1958-02-25 Henry H Porter Vehicle for testing control systems at supersonic speeds
US2892410A (en) * 1946-04-03 1959-06-30 David H Sloan Ram jet projectile
US2898856A (en) * 1951-07-06 1959-08-11 Armstrong Whitworth Co Eng Self-projected missiles
US2938430A (en) * 1954-05-17 1960-05-31 North American Aviation Inc Screw retained spin rocket
US2945442A (en) * 1958-01-02 1960-07-19 Barnet R Adelman Explosive separation device
US2960034A (en) * 1947-12-01 1960-11-15 Jr Carl W Besserer Launching carriage for jet-propelled missiles
US2995939A (en) * 1953-03-23 1961-08-15 Max M Munk Mercury gyroscope
US2998771A (en) * 1955-04-01 1961-09-05 Lloyd G Mosier Projectiles
US3000597A (en) * 1951-08-15 1961-09-19 Alfred J Bell Rocket-propelled missile
US3013494A (en) * 1957-08-09 1961-12-19 Chanut Pierre Louis Jean Guided missile
US3017836A (en) * 1958-08-28 1962-01-23 Phillips Petroleum Co Rocket motor
US3026772A (en) * 1958-02-03 1962-03-27 Phillips Petroleum Co Cargo launcher
US3029734A (en) * 1958-10-02 1962-04-17 Phillips Petroleum Co Separation of stages in a staged rocket
US3067681A (en) * 1960-01-04 1962-12-11 Telecomputing Corp Guided missile
US3088273A (en) * 1960-01-18 1963-05-07 United Aircraft Corp Solid propellant rocket
DE1150303B (en) * 1959-01-13 1963-06-12 Soc Tech De Rech Ind Missile with shaped charge
US3106162A (en) * 1959-05-08 1963-10-08 John P Hagerty Nose cooling means for missiles
US3110261A (en) * 1957-07-29 1963-11-12 Walters Arthur Gwynfryn Rocket projectiles
US3124072A (en) * 1964-03-10 Missile propulsion
US3125955A (en) * 1964-03-24 Toy rocket motor
US3137232A (en) * 1959-03-04 1964-06-16 Andras Julius Space exploration rocket
US3143048A (en) * 1959-03-16 1964-08-04 Rand Corp Photographic apparatus
US3158100A (en) * 1963-03-04 1964-11-24 Data Corp Rocket propelled reconnaissance vehicle
US3167016A (en) * 1956-07-30 1965-01-26 Dehavilland Aircraft Canada Rocket propelled missile
US3251267A (en) * 1963-06-18 1966-05-17 Emerson Electric Co Spin rocket and launcher
US3262266A (en) * 1964-08-31 1966-07-26 James F Howison Rocket interstage adapter
US3274772A (en) * 1963-07-16 1966-09-27 Gen Motors Corp Continuously staged rocket construction
DE977712C (en) * 1957-03-03 1968-08-08 Franz Rudolf Dipl-Ing Thomanek With a lined shaped charge equipped with Flugkoerper rocket engine
US3396920A (en) * 1959-12-30 1968-08-13 Nasa Usa Apparatus for changing the orientation and velocity of a spinning body traversing a path
US3397638A (en) * 1961-03-08 1968-08-20 Mb Assoc Rocket launcher
US3434426A (en) * 1956-11-30 1969-03-25 Jay W De Dapper Combined ignitor and propellent grain
US3754725A (en) * 1968-04-30 1973-08-28 Us Navy Auxiliary rocket apparatus for installation on a missile to impart a roll moment thereto
US5974939A (en) * 1994-05-02 1999-11-02 Lockhead Martin Corporation Modular launch pad system
US20080173020A1 (en) * 2006-12-04 2008-07-24 Firestar Engineering, Llc Spark-integrated propellant injector head with flashback barrier
US20090133788A1 (en) * 2007-11-09 2009-05-28 Firestar Engineering, Llc Nitrous oxide fuel blend monopropellants
US20100205933A1 (en) * 2008-12-08 2010-08-19 Greg Mungas Regeneratively cooled porous media jacket
US20100275577A1 (en) * 2006-12-04 2010-11-04 Firestar Engineering, Llc Rocket engine injectorhead with flashback barrier
US20110008739A1 (en) * 2009-07-07 2011-01-13 Firestar Engineering, Llc Detonation wave arrestor
US20110180032A1 (en) * 2010-01-20 2011-07-28 Firestar Engineering, Llc Insulated combustion chamber
US20110219742A1 (en) * 2010-03-12 2011-09-15 Firestar Engineering, Llc Supersonic combustor rocket nozzle
US8572946B2 (en) 2006-12-04 2013-11-05 Firestar Engineering, Llc Microfluidic flame barrier

Cited By (67)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3125955A (en) * 1964-03-24 Toy rocket motor
US3124072A (en) * 1964-03-10 Missile propulsion
US2447200A (en) * 1943-09-03 1948-08-17 Aerojet Engineering Corp Exhaust nozzle for rocket motors
US2563265A (en) * 1943-09-21 1951-08-07 Aerojet Engineering Corp Rocket motor with solid propellant and propellant charge therefor
US2479829A (en) * 1943-10-23 1949-08-23 Daniel And Florence Guggenheim Rotating combustion chamber with continuous rearward discharge
US2442528A (en) * 1943-11-20 1948-06-01 Aerial Products Inc Rocket device
US2783138A (en) * 1944-04-11 1957-02-26 Aerojet General Co Propellant compositions
US2468795A (en) * 1944-10-11 1949-05-03 Winters Starling Flare
US2724237A (en) * 1946-03-05 1955-11-22 Clarence N Hickman Rocket projectile having discrete flight initiating and sustaining chambers
US2892410A (en) * 1946-04-03 1959-06-30 David H Sloan Ram jet projectile
US2596644A (en) * 1946-12-10 1952-05-13 Us Sec War Automatically detachable flashless nozzle for rockets
US2776622A (en) * 1947-05-27 1957-01-08 Robert Roger Aime Device for attaching auxiliary rockets to a flying machine
US2960034A (en) * 1947-12-01 1960-11-15 Jr Carl W Besserer Launching carriage for jet-propelled missiles
US2748703A (en) * 1948-04-27 1956-06-05 Wilbur H Goss Rocket type launching carriage for ordnance missile
US2644396A (en) * 1948-10-01 1953-07-07 United Aircraft Corp Aerial missile
US2623465A (en) * 1949-02-15 1952-12-30 Brandt Soc Nouv Ets Projectile
US2824711A (en) * 1950-03-22 1958-02-25 Henry H Porter Vehicle for testing control systems at supersonic speeds
US2766581A (en) * 1950-06-30 1956-10-16 Curtiss Wright Corp Ram jet engine
US2792784A (en) * 1950-10-27 1957-05-21 Bristol Aeroplane Co Ltd Prime movers
US2745347A (en) * 1951-07-06 1956-05-15 Armstrong Whitworth Co Eng Self-projected missiles
US2898856A (en) * 1951-07-06 1959-08-11 Armstrong Whitworth Co Eng Self-projected missiles
US3000597A (en) * 1951-08-15 1961-09-19 Alfred J Bell Rocket-propelled missile
US2750887A (en) * 1952-01-31 1956-06-19 Stanley J Marcus Motor mechanism for missiles
US2995939A (en) * 1953-03-23 1961-08-15 Max M Munk Mercury gyroscope
US2821922A (en) * 1953-08-24 1958-02-04 Lawrence W Brown Rocket toy and launcher therefor
US2938430A (en) * 1954-05-17 1960-05-31 North American Aviation Inc Screw retained spin rocket
US2998771A (en) * 1955-04-01 1961-09-05 Lloyd G Mosier Projectiles
US2804823A (en) * 1955-05-13 1957-09-03 Jablansky Louis Multiple unit projectile
US3167016A (en) * 1956-07-30 1965-01-26 Dehavilland Aircraft Canada Rocket propelled missile
US3434426A (en) * 1956-11-30 1969-03-25 Jay W De Dapper Combined ignitor and propellent grain
DE977712C (en) * 1957-03-03 1968-08-08 Franz Rudolf Dipl-Ing Thomanek With a lined shaped charge equipped with Flugkoerper rocket engine
US3110261A (en) * 1957-07-29 1963-11-12 Walters Arthur Gwynfryn Rocket projectiles
US3013494A (en) * 1957-08-09 1961-12-19 Chanut Pierre Louis Jean Guided missile
US2945442A (en) * 1958-01-02 1960-07-19 Barnet R Adelman Explosive separation device
US3026772A (en) * 1958-02-03 1962-03-27 Phillips Petroleum Co Cargo launcher
US3017836A (en) * 1958-08-28 1962-01-23 Phillips Petroleum Co Rocket motor
US3029734A (en) * 1958-10-02 1962-04-17 Phillips Petroleum Co Separation of stages in a staged rocket
DE1150303B (en) * 1959-01-13 1963-06-12 Soc Tech De Rech Ind Missile with shaped charge
US3137232A (en) * 1959-03-04 1964-06-16 Andras Julius Space exploration rocket
US3143048A (en) * 1959-03-16 1964-08-04 Rand Corp Photographic apparatus
US3106162A (en) * 1959-05-08 1963-10-08 John P Hagerty Nose cooling means for missiles
US3396920A (en) * 1959-12-30 1968-08-13 Nasa Usa Apparatus for changing the orientation and velocity of a spinning body traversing a path
US3067681A (en) * 1960-01-04 1962-12-11 Telecomputing Corp Guided missile
US3088273A (en) * 1960-01-18 1963-05-07 United Aircraft Corp Solid propellant rocket
US3397638A (en) * 1961-03-08 1968-08-20 Mb Assoc Rocket launcher
US3158100A (en) * 1963-03-04 1964-11-24 Data Corp Rocket propelled reconnaissance vehicle
US3251267A (en) * 1963-06-18 1966-05-17 Emerson Electric Co Spin rocket and launcher
US3274772A (en) * 1963-07-16 1966-09-27 Gen Motors Corp Continuously staged rocket construction
US3262266A (en) * 1964-08-31 1966-07-26 James F Howison Rocket interstage adapter
US3754725A (en) * 1968-04-30 1973-08-28 Us Navy Auxiliary rocket apparatus for installation on a missile to impart a roll moment thereto
US5974939A (en) * 1994-05-02 1999-11-02 Lockhead Martin Corporation Modular launch pad system
US6321631B1 (en) * 1994-05-02 2001-11-27 Lockhead Martin Corporation Modular launch pad system
US8572946B2 (en) 2006-12-04 2013-11-05 Firestar Engineering, Llc Microfluidic flame barrier
US20080173020A1 (en) * 2006-12-04 2008-07-24 Firestar Engineering, Llc Spark-integrated propellant injector head with flashback barrier
US20100275577A1 (en) * 2006-12-04 2010-11-04 Firestar Engineering, Llc Rocket engine injectorhead with flashback barrier
US8230672B2 (en) 2006-12-04 2012-07-31 Firestar Engineering, Llc Spark-integrated propellant injector head with flashback barrier
US8230673B2 (en) 2006-12-04 2012-07-31 Firestar Engineering, Llc Rocket engine injectorhead with flashback barrier
US20090133788A1 (en) * 2007-11-09 2009-05-28 Firestar Engineering, Llc Nitrous oxide fuel blend monopropellants
US20100205933A1 (en) * 2008-12-08 2010-08-19 Greg Mungas Regeneratively cooled porous media jacket
US8413419B2 (en) 2008-12-08 2013-04-09 Firestar Engineering, Llc Regeneratively cooled porous media jacket
US20110146231A1 (en) * 2009-07-07 2011-06-23 Firestar Engineering, Llc Tiered Porosity Flashback Suppressing Elements for Monopropellant or Pre-Mixed Bipropellant Systems
US8858224B2 (en) 2009-07-07 2014-10-14 Firestar Engineering, Llc Detonation wave arrestor
US20110005194A1 (en) * 2009-07-07 2011-01-13 Firestar Engineering, Llc Flashback shut-off
US20110008739A1 (en) * 2009-07-07 2011-01-13 Firestar Engineering, Llc Detonation wave arrestor
US20110005195A1 (en) * 2009-07-07 2011-01-13 Firestar Engineering, Llc Aluminum porous media
US20110180032A1 (en) * 2010-01-20 2011-07-28 Firestar Engineering, Llc Insulated combustion chamber
US20110219742A1 (en) * 2010-03-12 2011-09-15 Firestar Engineering, Llc Supersonic combustor rocket nozzle

Similar Documents

Publication Publication Date Title
Miller et al. Green rocket propulsion by reaction of Al and Mg powders and water
US3282216A (en) Nose cone and tail structures for an air vehicle
Zhang et al. A MEMS-based solid propellant microthruster with Au/Ti igniter
US1920075A (en) Cartridge for guns and ordnances
US2344957A (en) Pistol rocket
US4726279A (en) Wake stabilized supersonic combustion ram cannon
US8082725B2 (en) Electro-dynamic swirler, combustion apparatus and methods using the same
Bowden et al. Initiation and growth of explosion in liquids and solids
US2114214A (en) Self-propelling projectile
US2433943A (en) Operation of jet propulsion motors with nitroparaffin
Kogarko et al. Investigation of spherical detonation of gas mixtures
Rex Interference effects during burning in air for stationary n-heptane, ethyl alcohol, and methyl alcohol droplets
US2711630A (en) Rockets
US5429030A (en) Hybrid electrothermal light gas gun and method
US2926566A (en) Device for accelerating the ignition of the propellant for a projectile
US2987875A (en) Ramjet power plants for missiles
US4722261A (en) Extendable ram cannon
Lewis Centrifugal-force effects on combustion
US3948175A (en) Warhead
US2724237A (en) Rocket projectile having discrete flight initiating and sustaining chambers
US2411552A (en) Turbine apparatus
EP0248340A2 (en) Projectile launching system
US3049080A (en) Rockets and rocket-borne distress signals
US2206057A (en) Rocket projectile
US3635030A (en) Device for producing burnable gases for thrust engines