US2684570A - Rocket-engine and reaction-motor missile - Google Patents

Rocket-engine and reaction-motor missile Download PDF

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Publication number
US2684570A
US2684570A US166594A US16659450A US2684570A US 2684570 A US2684570 A US 2684570A US 166594 A US166594 A US 166594A US 16659450 A US16659450 A US 16659450A US 2684570 A US2684570 A US 2684570A
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US
United States
Prior art keywords
missile
rocket
fuel
engine
combustion
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
US166594A
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English (en)
Inventor
Nordfors Kurt Martin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Saab Bofors AB
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Bofors AB
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 Bofors AB filed Critical Bofors AB
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Publication of US2684570A publication Critical patent/US2684570A/en
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    • H—ELECTRICITY
    • H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N—ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N60/00—Superconducting devices
    • H10N60/01—Manufacture or treatment
    • H10N60/0912—Manufacture or treatment of Josephson-effect devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/105—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines using a solid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • 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
    • Y—GENERAL 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00—Power plants
    • Y10S60/917—Solid fuel ramjet using pulverized fuel

Definitions

  • the present invention relates to an improvement in missiles of this class that in combination with a generally similar engine there is embodied auxiliary propulsion means of so-ca'lled rocket characteristics whereby the missile may be launched from a gun or the like at lower initial or muzzle velocity and then attain the velocity requisite for operation of the rain jet engine under the impulse of a rocket charge ⁇ carried inside the missile; after the exhaustion of such charge the ram jet is automatically brought into pla-y to further propel the missile at the velocity then attained or a higher one until exhaustion of the ram jet-fuel or arrival at a target, whichever rst occurs.
  • Another object is to provide a projectile or missile of the character aforesaid wherein the pressures generated by the combustion of the rocket fuel automatically maintain theram jet engine air intake port closed during flight until exhaustion of the rocket fuel and then allow the said port to open for intake'of air to support combustion of the ram jet fuel and thereby supply .further impulse to the travel of the missile.
  • Fig. l is an axial section partly in elevation of a missile embodying the invention as it appears prior to its discharge from a gun or the like;
  • Fig. 2 is a corresponding View showing the missile as it appears in flight after exhaustion of the rocket fuel and upon initiation of the operation of its contained ram jet engine.
  • the missile illustrated therein comprises an outer casing or shell i of generally cylindrical form within which is coaxially disposed an inner body 2 which may carry a bursting charge or the like.
  • the leading end of the outer casing is curved inwardly and :feathered as at 3 for snug engagement with the substantially conoidal nose fl of the inner body 2 and adapted to form therewith an annular port 5 when the casing l and body 2 are moved axially relatively to each other from the relative positions shown in Fig. l to those shown in Fig. 2.
  • the inner surface of the outer casing and the outer surface of the inner body are substantially cylindrical and form between them a combustion chamber 6 the walls of which initially are dened by a layer 'l of rocket fuel overlying a subjacent layer 8 of ram jet fuel which may be applied in any suitable manner to the opposed walls of the casing and body.
  • these parts are formed to provide an exhaust nozzle 9 the conformation of which is appropriately designed to produce a reaction impelling the missile forward as combustion products are discharged through it at high velocity.
  • the outer casing at a suitable position is desirably provided with an annular sealing or packing ring I I] adapted for cooperation with the bore of a gun barrel or other suitable launching mechanism to prevent escape through said bore around the missile of the gases emanating from the initial propulsive charge while it is in the bore, the ring also serving to impart axial rotation to the missile in the ordinary manner if the bore is riiled.
  • the missile is initially charged into the gun or other launching apparatus in the condition shown in Fig. l, that is, with port 5 closed by tight engagement of nose ll of the inner body with feathered edge 3 of the outer casing, and this gas seal combined with the seal between the missile as a whole and the gun barrel aiforded by packing ring l0 enables the full propulsive ⁇ effect of the launching charge to react against muzzle of the firing mechanism a discharge of combustion products through port 9 resulting from combustion of rocket fuel l imparts additional impetus to the missile and further accelerates its flight, resultant pressure in the combustion chamber retaining an effective seal between the leading feathered edge 3 0f the outer casing and nose d of the body until exhaustion of the rocket fuel. ⁇ Thereafter, upon decline of this pressure the atmospheric air pressure on nose ll tends to retard the inner body and permit the outer casing to move forwardly relatively thereto, admitting air under pressure to combustion chamber 6 through the now open port 5.
  • the ram jet fuel 8 is thereupon ignited and products of its combustion are discharged at high velocity through exhaust nozzle i3 which is so designed as to afford a larger opening during the ram jet operation than during combustion of the rocket fuel as a result of the above described relative axial movement of the parts.
  • the missile is therefore further propelled by the action of the ram jet to greatly increase its range and velocity as compared with comparable missiles depending for their range entirely upon the propulsive force imparted by the initial charge of the gun or other launching device.
  • the missile described herein is of course adapted to be operated with the aid of liquid or gaseous as well as solid fuel or any desired combination of fuels in these several phases and since the rocket fuel requires no air to support its combustion it is obvious the entire space between the outer casing and inner wall may entirely be filled with this and other fuel, consumption of the rocket fuel during the initial stage of flight evacuating space for the passage of air through the interior of the outer casing during subsequent ram jet operation.
  • means may be provided for holding the front and rear portions of the inner body in coaxial relation with the outer shell while permitting their relative axial movement, for example, a plurality of radial stays fixed to the inner body, slidably engaging the inner wall of the outer shell and where the rear stays are preferably arranged to engage the constricted rear portion of said wall adjacent the exhaust nozzle or some other suitable abutment at maximum operative open position of i it will be understood I do not desire or intend .i
  • a missile comprising coaxial relatively movable parts including a substantially cylindrical hollow outer casing having a constriction at its forward end and a substantially cylindrical inner body having a conoidal nose of greater maximum diameter than the minimum diameter of said constriction cooperative with said constriction to provide an annular port adapted to be closed by relative axial movement of the parts,
  • said ram jet engine fuel comprises a layer of combustible material proximate the inner wall of thc casing between said port and said nozzle and said rocket-engine fuel comprises material adapted for selfsust'aining combustion proximate the inner surface of said rst material whereby in flight of the missile internal pressure generated by combustion of said last mentioned material reacts against said parts to maintain said port closed and on decrease in said pressure reaction of atmospheric pressure against said conoidal nose effects relative movement of said parts to open said port for passage of atmospheric air under pressure therethrough to support combustion of the first mentioned material.
  • said ram jet engine fuel comprises a combustible material forming layers adherent respectively to the opposed surfaces of said parts within the missile and said rocket-engine fuel comprises materiai adapted for self-sustaining combustion interposed between opposed surfaces of said layers whereby in iiight of the missile internal pressure generated by combustion of said last mentioned material reacts against said parts to maintain said port closed and on decrease in said pressure reaction of atmospheric pressure against said conoidal nose effects relative movement of said parts to open said port for passage of atmospheric air under pressure therethrough to support combustion of the first mentioned material.
  • a missile comprising coaxial relatively movable parts including a substantially cylindrical hollow outer casing having a constriction at its forward end and a substantially cylindrical inner body having a conoidal nose normally engaged therewith adjacent its zone of maximum diameter, said maximum diameter being greater than the minimum diameter of said constriction, the rear ends of said parts defining between them a discharge nozzle, ram jet fuel disposed in the casing intermediate said nose and said nozzlek and rocket-engine fuel likewise in the casing proximate the ram jet fuel whereby following discharge of the missile and subsequent combustion of the rocket-engine fuel the parts remain in normal position but thereafter move axially relative to each other to simultaneously open a passage for air between the nose of the body and the forward end of the casing and enlarge the effective area of the discharge nozzle preparatory to combustion of the ram jet fuel.

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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)
  • Manufacturing & Machinery (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
US166594A 1949-06-16 1950-06-07 Rocket-engine and reaction-motor missile Expired - Lifetime US2684570A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE286895X 1949-06-16
SE669014X 1949-07-07

Publications (1)

Publication Number Publication Date
US2684570A true US2684570A (en) 1954-07-27

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US166594A Expired - Lifetime US2684570A (en) 1949-06-16 1950-06-07 Rocket-engine and reaction-motor missile
US166593A Expired - Lifetime US2684629A (en) 1949-06-16 1950-06-07 Reaction-motor missile

Family Applications After (1)

Application Number Title Priority Date Filing Date
US166593A Expired - Lifetime US2684629A (en) 1949-06-16 1950-06-07 Reaction-motor missile

Country Status (5)

Country Link
US (2) US2684570A (enrdf_load_stackoverflow)
BE (2) BE496372A (enrdf_load_stackoverflow)
CH (2) CH286895A (enrdf_load_stackoverflow)
FR (2) FR1020174A (enrdf_load_stackoverflow)
GB (2) GB669008A (enrdf_load_stackoverflow)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1025215B (de) * 1955-11-07 1958-02-27 Max Koppe Dr Rer Pol Dr Rer Na Strahltriebwerk fuer unbemannte und bemannte Flugkoerper jeder Art
US2840322A (en) * 1952-09-23 1958-06-24 Rolls Royce Air intake for aircraft power plant installations
US2883829A (en) * 1955-01-24 1959-04-28 Curtiss Wright Corp Rocket engine convertible to a ramjet engine
US2906094A (en) * 1954-04-14 1959-09-29 Glenn H Damon Fuel and rapid ignition apparatus for ignition of fuel in ram jets and rockets
US2926613A (en) * 1955-05-23 1960-03-01 Phillips Petroleum Co Composite rocket-ram jet fuel
US2990682A (en) * 1951-11-07 1961-07-04 Gen Electric Fuel charge
US3069300A (en) * 1954-12-30 1962-12-18 Glenn H Damon Boron containing fuel and fuel igniter for ram jet and rocket
DE1144060B (de) * 1960-08-04 1963-02-21 Daimler Benz Ag Verbundtriebwerk fuer Flugzeuge
US3115008A (en) * 1959-02-03 1963-12-24 Cohen William Integral rocket ramjet missile propulsion system
US3218974A (en) * 1964-03-24 1965-11-23 Samms Adolphus Air breathing booster
US3726219A (en) * 1970-03-24 1973-04-10 Us Navy Integral propellant case ramjet projectile
US3974648A (en) * 1968-08-19 1976-08-17 United Technologies Corporation Variable geometry ramjet engine
US4651523A (en) * 1984-10-06 1987-03-24 Rolls-Royce Plc Integral rocket and ramjet engine
US5363766A (en) * 1990-02-08 1994-11-15 The United States Of America As Represented By The Secretary Of The Army Remjet powered, armor piercing, high explosive projectile
US6058846A (en) * 1998-06-03 2000-05-09 Lockhead Martin Corporation Rocket and ramjet powered hypersonic stealth missile having alterable radar cross section
US20080041265A1 (en) * 2006-07-10 2008-02-21 Geswender Chris E Methods and Apparatus for Missile Air Inlet
US20090229241A1 (en) * 2008-03-07 2009-09-17 Haight Stephen D Hybrid missile propulsion system with reconfigurable multinozzle grid
US20110314791A1 (en) * 2010-06-25 2011-12-29 Haynes Jeffrey D Method for combustion system
WO2019211716A1 (fr) * 2018-05-02 2019-11-07 Nexter Munitions Projectile propulsé par statoréacteur

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2811829A (en) * 1952-12-04 1957-11-05 Alfred A Topinka Ram jet employing carbon layer of insulation for solid carbon propellant
US2799987A (en) * 1952-12-31 1957-07-23 Edward F Chandler Solid fuel ramjet projectiles
US2989922A (en) * 1953-02-17 1961-06-27 Marvin H Greenwood Ramjet propulsion device
US2912820A (en) * 1953-07-31 1959-11-17 Quentin R Whitmore Combined ram jet and rocket engine
US2948112A (en) * 1953-12-14 1960-08-09 Kenneth W Smith Combined rocket and ram-jet engine
US3903802A (en) * 1955-08-26 1975-09-09 Us Army Shell construction sealing washer
US2936710A (en) * 1956-01-03 1960-05-17 Curtiss Wright Corp High mach deceleration device
US3048009A (en) * 1956-06-21 1962-08-07 Phillips Petroleum Co Rocket motor
US2977879A (en) * 1957-09-18 1961-04-04 Atlantic Res Corp Rocket projectile
DE1213760B (de) * 1962-06-30 1966-03-31 Rheinmetall Gmbh Hohlladungsgeschoss mit Eigenantrieb
US3220181A (en) * 1962-11-08 1965-11-30 Texaco Experiment Inc Split-flow solid fuel ramjet
US4135449A (en) * 1975-06-20 1979-01-23 Rheinmetall Gmbh Projectile for attacking small targets
US4338783A (en) * 1975-09-04 1982-07-13 The United States Of America As Represented By The Secretary Of The Air Force Two-stage hypersonic ramjet
US4052846A (en) * 1976-01-08 1977-10-11 The United States Of America As Represented By The Secretary Of The Navy Baffled combustion chamber
FR2666850B1 (fr) * 1978-08-04 1994-09-09 Onera (Off Nat Aerospatiale) Perfectionnements apportes aux propulseurs de type statoreacteur.
US4745740A (en) * 1982-09-30 1988-05-24 The Boeing Company Velocity controller for ramjet missile and method therefor
DE10158277A1 (de) * 2001-11-20 2003-05-28 Mieczyslaw Milewski Einrichtung zur Einstellung der Aerodynamik der Raketen

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR779655A (fr) * 1934-01-02 1935-04-10 Procédé de transformation de l'énergie calorifique en énergie cinétique ou potentielle
FR50033E (fr) * 1938-07-05 1939-11-10 Procédé de transformation de l'énergie calorifique en énergie cinétique ou potentielle
US2419866A (en) * 1941-02-11 1947-04-29 Wilson Walter Gordon Aerial torpedo
GB590177A (en) * 1944-07-17 1947-07-10 Hydran Products Ltd Improvements in or relating to projectiles of the rocket type
US2446266A (en) * 1946-02-23 1948-08-03 Thomas L Cummings Jet propelled helicopter rotor
US2540594A (en) * 1946-08-23 1951-02-06 Lockheed Aircraft Corp Ram jet engine having variable area inlets

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB293594A (en) * 1925-12-19 1928-08-16 Benjamin Charles Carter Improvements in or relating to apparatus for burning liquid or gaseous fuel and in the application thereof to internal combustion turbines, turbo-airscrews, projectiles, rockets and the like

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR779655A (fr) * 1934-01-02 1935-04-10 Procédé de transformation de l'énergie calorifique en énergie cinétique ou potentielle
FR50033E (fr) * 1938-07-05 1939-11-10 Procédé de transformation de l'énergie calorifique en énergie cinétique ou potentielle
US2419866A (en) * 1941-02-11 1947-04-29 Wilson Walter Gordon Aerial torpedo
GB590177A (en) * 1944-07-17 1947-07-10 Hydran Products Ltd Improvements in or relating to projectiles of the rocket type
US2446266A (en) * 1946-02-23 1948-08-03 Thomas L Cummings Jet propelled helicopter rotor
US2540594A (en) * 1946-08-23 1951-02-06 Lockheed Aircraft Corp Ram jet engine having variable area inlets

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990682A (en) * 1951-11-07 1961-07-04 Gen Electric Fuel charge
US2840322A (en) * 1952-09-23 1958-06-24 Rolls Royce Air intake for aircraft power plant installations
US2906094A (en) * 1954-04-14 1959-09-29 Glenn H Damon Fuel and rapid ignition apparatus for ignition of fuel in ram jets and rockets
US3069300A (en) * 1954-12-30 1962-12-18 Glenn H Damon Boron containing fuel and fuel igniter for ram jet and rocket
US2883829A (en) * 1955-01-24 1959-04-28 Curtiss Wright Corp Rocket engine convertible to a ramjet engine
US2926613A (en) * 1955-05-23 1960-03-01 Phillips Petroleum Co Composite rocket-ram jet fuel
DE1025215B (de) * 1955-11-07 1958-02-27 Max Koppe Dr Rer Pol Dr Rer Na Strahltriebwerk fuer unbemannte und bemannte Flugkoerper jeder Art
US3115008A (en) * 1959-02-03 1963-12-24 Cohen William Integral rocket ramjet missile propulsion system
DE1144060B (de) * 1960-08-04 1963-02-21 Daimler Benz Ag Verbundtriebwerk fuer Flugzeuge
US3218974A (en) * 1964-03-24 1965-11-23 Samms Adolphus Air breathing booster
US3974648A (en) * 1968-08-19 1976-08-17 United Technologies Corporation Variable geometry ramjet engine
US3726219A (en) * 1970-03-24 1973-04-10 Us Navy Integral propellant case ramjet projectile
US4651523A (en) * 1984-10-06 1987-03-24 Rolls-Royce Plc Integral rocket and ramjet engine
US5363766A (en) * 1990-02-08 1994-11-15 The United States Of America As Represented By The Secretary Of The Army Remjet powered, armor piercing, high explosive projectile
US6058846A (en) * 1998-06-03 2000-05-09 Lockhead Martin Corporation Rocket and ramjet powered hypersonic stealth missile having alterable radar cross section
US20080041265A1 (en) * 2006-07-10 2008-02-21 Geswender Chris E Methods and Apparatus for Missile Air Inlet
US7851733B2 (en) * 2006-07-10 2010-12-14 Raytheon Company Methods and apparatus for missile air inlet
US8344304B2 (en) 2006-07-10 2013-01-01 Raytheon Company Methods and apparatus for missile air inlet
EP2038601A4 (en) * 2006-07-10 2013-02-20 Raytheon Co METHODS AND APPARATUS FOR MISSILE AIR INPUT
US20090229241A1 (en) * 2008-03-07 2009-09-17 Haight Stephen D Hybrid missile propulsion system with reconfigurable multinozzle grid
US8117847B2 (en) 2008-03-07 2012-02-21 Raytheon Company Hybrid missile propulsion system with reconfigurable multinozzle grid
US20110314791A1 (en) * 2010-06-25 2011-12-29 Haynes Jeffrey D Method for combustion system
WO2019211716A1 (fr) * 2018-05-02 2019-11-07 Nexter Munitions Projectile propulsé par statoréacteur
FR3080912A1 (fr) * 2018-05-02 2019-11-08 Nexter Munitions Projectile propulse par statoreacteur

Also Published As

Publication number Publication date
CH286895A (de) 1952-11-15
BE496772A (enrdf_load_stackoverflow) 1950-11-03
US2684629A (en) 1954-07-27
GB669014A (en) 1952-03-26
FR1020174A (fr) 1953-02-03
CH287258A (de) 1952-11-30
GB669008A (en) 1952-03-26
FR1020175A (fr) 1953-02-03
BE496372A (enrdf_load_stackoverflow) 1950-10-02

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