US3684215A - Missile - Google Patents

Missile Download PDF

Info

Publication number
US3684215A
US3684215A US41373A US3684215DA US3684215A US 3684215 A US3684215 A US 3684215A US 41373 A US41373 A US 41373A US 3684215D A US3684215D A US 3684215DA US 3684215 A US3684215 A US 3684215A
Authority
US
United States
Prior art keywords
missile
fuel
fuel charges
space
charges
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
US41373A
Other languages
English (en)
Inventor
Gunnar Jacobson
Olof Bertil Olsson
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
Original Assignee
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
Application granted granted Critical
Publication of US3684215A publication Critical patent/US3684215A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • 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
    • F02K9/70—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using semi- solid or pulverulent propellants
    • 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

Definitions

  • the invention concerns a missile, in particular a guided missile, having stabilizing wings and a solid fuel propulsion motor.
  • the fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile.
  • the portion of the interior of the missile between the two fuel charges consists of an empty space, into which the fuel charges deliver their combustion gases and which is surrounded by an annular member forming the external shell of the missile between the two fuel charges and comprising the jet nozzles for the propulsion motor.
  • the two fuel charges have such relative sizes and locations in the missile that their common gravity center coincides substantially with the total gravity center of the missile.
  • the stabilizing wings are attached to the annular member comprising the jet nozzles and are located circumferentially between said jet nozzles.
  • the present invention is related to missiles and in particular guided missiles having a solid fuel or powder propulsion motor and stabilizing wings for stabilizing the missile in its flight.
  • the aerodynamic pressure center of the missile must be located rearwards from but comparatively close to the gravity center of the missile. This means that the stabilizing wings of the missile should be located close to the gravity center of the missile.
  • the fuel charge of the propulsion motor should also be located in the missile so as to have its gravity center close to or coinciding with the total resulting gravity center of the missile.
  • the outer shell or wall of the missile is generally made as thin as possible in order to obtain a low weight and a small total external diameter of the missile.
  • the stabilizing wings attached to the external shell of the missile are subject to very considerable forces, however, wherefore the fastening members for the stabilizing wings and the portion of the missile shell supporting these fastening members must be dimensioned to have a considerable strength. If the stabilizing wings are to be located at the portion of the missile where also the fuel charge of the propulsion motor is located, the fastening means for the wings must consequently project into the internal space in the missile where the fuel charge of the propulsion motor should be located, or alternatively the total external diameter of the missile must be increased so as to give sufficient space for the fastening means for the stabilizing wings.
  • the latter alternative is very disadvantageous, as it impairs very seriously the aerodynamic properties of the missile and also causes an increase of the maximum external diameter of the missile, which in its turn causes that a launching tube for the missile must have a correspondingly large diameter.
  • the radial space necessary for the fastening members for the stabilizing wings is especially large if, as in most cases, it shall be possible to fold the wings to a position close to the external surface of the missile in order to reduce the necessary space for the missile when being stored and transported and to make it possible to tire the missile through a launching tube.
  • the propulsion motor must be provided with a plurality of jet nozzles which are equally spaced around the missile so as to have their openings in the circumferential surface of the missile and which are pointed obliquely rearwards relative the intended direction of flight of the missile. If these jet nozzles produce equally large thrusts, the total resulting thrust will coincide with the symmetry axis of the missile and be directed through the gravity center of the missile, whereby the propulsion motor will not produce any moments which tend to tip the missile or displace it from its path and which must be compensated for by the guide means of the missile.
  • the jet nozzles of the propulsion motor should preferably be located comparatively close to the gravity center of the missile, whereby the tilting moment upon the missile becomes comparatively small if the jet nozzles should not produce equally large thrusts.
  • the nozzles must be located in such a manner that the combustion gases ejected from the nozzles do not produce any aerodynamic disturbances upon the missile or give cause to any other damages upon the missile.
  • the nozzles shall not have their openings located in front of the stabilizing wings.
  • jet nozzles of the propulsion motor should be located substantially at the same portion of the missile where, as mentioned above, also the stabilizing wings as well as the fuel charge of the propulsion motor should be located. It is obvious that this makes the design of the missile still more complicated with respect to the location of the stabilizing wings, the fuel charge of the propulsion motor and the jet nozzles of the motor.
  • the principal object of the invention is therefore to provide an improved missile, in particular a guided missile, having such a design that all the above mentioned demands with respect to the location of the stabilizing wings, the fuel charge of the solid fuel propulsion motor and the jet nozzles of the propulsion motor are satisfied.
  • An unguided missile having a solid fuel propulsion motor is known in the prior art (the French patent specification 839 861 in which the fuel of the propulsion motor is divided into two portions or charges, which are disposed axially spaced in the missile so as to deliver their combustion gases to jet nozzles mounted in an annular member forming the external shell of the missile between the two fuel charges.
  • the principal object is to obtain such a location of the bursting or service charge of the missile that the gravity center of this service charge coincides with or is located very close to the total gravity center of the missile.
  • the service charge is located between the two propellent fuel charges of the propulsion motor so as to fill substantially completely the interior of the missile between the two propellent fuel charges.
  • the solid propellent fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile so as to deliver their combustion gases to jet nozzles mounted in an annular member forming the external shell of the missile between the two fuel charges.
  • the missile according to the invention is characterized in that the two propellent fuel charges have such relative sizes and locations that their common gravity center substantially coincides with the total gravity center of the missile, that the portion of the interior of the missile surrounded by said annular member comprising the jet nozzles constitutes an empty space into which said two fuel charges deliver their combustion gases in common, and that the stabilizing wings are attached to said annular body circumferentially between the jet nozzles.
  • the solid propellent fuel of the propulsion motor and not the service charge of the missile is arranged and located so as to have its gravity center coinciding with the total gravity center of the missile.
  • the portion of the interior of the missile between the two propellent fuel charges consists of an empty space, whereby it is very easy to provide very large flow areas for the combustion gases from the fuel charges to the jet nozzles and additionally sufficient space is available also for large jet nozzles.
  • the annular member comprising the jet nozzle sufficient dimensions and strength and such a shape that the stabilizing wings can be mounted on this member without any increase of the external diameter of the missile being necessary.
  • FIG. 1 shows by way of example an embodiment of a missile according to the invention.
  • the drawing shows in axial section only the portion of the missile comprising the propulsion motor of the missile and the stabilizing wings and the jet nozzles of the propulsion motor; the axial sections in the upper half and the lower half of the drawing respectively being taken along different planes in such a manner that the upper half of the drawing shows an axial section through a jet nozzle for the propulsion motor, whereas the lower half of the drawing shows an axial section containing one of the stabilizing wings of the missile.
  • the missile illustrated by way of example in the drawing has the intended direction of flight indicated by an arrow 1 and is provided with a solid fuel propulsion motor, the solid fuel of which is divided into two separate portions or charges 2 and 3. These two fuel charges are located axially spaced in the missile so as to be separated by an internal space 4 in the missile surrounded by the external shell of the missile.
  • the two fuel charges 2 and 3 are provided to deliver their combustion gases to this space 4 and have in conventional manner conical recesses or bores 2a and 3a respectively facing the space 4.
  • annular member 5 The portion of the external shell of the missile surrounding the empty space 4 consists of an annular member 5.
  • this annular member 5 may, without any intrusion upon the necessary space for the fuel charges 2 and 3 for the propulsion motor and without any increase of the total external diameter of the missile, be given such dimensions and strength and such a shape that it can support not only the jet nozzles 7 of the propulsion motor (only one being shown in the drawing) but also the stabilizing wings 6 of the missile (only one being shown in the drawing).
  • the missile according to the invention illustrated by way of example in the drawing is provided with four stabilizing wings 6 equally spaced around the missile and with four jet nozzles 7 for the propulsion motor also equally spaced around the missile.
  • the stabilizing wings 6 and the propulsion nozzles 7 are located alternatingly in the circumferential direction around the missile.
  • the annular member 5 supporting the stabilizing wings 6 and the motor nozzles 7 is preferably formed with recesses 8 in which the motor nozzles 7 and the support member 9 for the stabilizing wings 6 are located so that no parts of the motor nozzles 7 or the support members 9 for the wings project radially outside the external circumferential surface of the missile.
  • the support member 9 for the stabilizing wings 6 are designed to permit the wings to be folded to a position close to the external surface of the missile and therefore require a considerable space, in particular in the radial direction.
  • the central portion 4a of the space 4, to which the fuel charges 2 and 3 deliver their combustion gases, must only be sufficiently large to provide a sufficient flow area for the combustion gases from the fuel charge 3 to the nonles 7.
  • the recesses 8 in the annular member 5 may consist of a separate recess for each motor nozzle 7 and each wing bracket 9 respectively or alternatively consist of a single annular recess extending continuously and circumferentially around the member 5 and containing all motor nozzles 7 and wing brackets 9.
  • the invention makes it possible, without any increase of the maximal external diameter of the missile being necessary, to locate the stabilizing wings 6 as well as the motor nozzles 7 in the desired position close to the gravity center of the missile and at the same time to locate the gravity center of the solid fuel of the propulsion motor, that is the common gravity center of the two fuel charges 2 and 3, so as to coincide with or be very close to the total gravity center of the missile.
  • the stabilizing wings 6 and the motor nozzles 7 are located very close to each other in a very space saving manner, the gas jets from the nozzles will not hit the stabilizing wings and consequently will not damage these or give cause to any aerodynamic disturbances upon the missile.
  • a missile comprising:
  • a solid fuel propulsion motor including two separate fuel charges disposed axially spaced apart within said shell to define a space therein, said fuel charges delivering their combustion gases directly to said space between the fuel charges;
  • said fuel charges having relative sizes and locations within said shell such that the common center of gravity thereof substantially coincides with the total center of gravity of the missile and relative rates of burning such that their common center of gravity remains substantially stationary relative the with said empty space and their outlet ends are missile during the burning of the charges and said located outside of the shell;

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
US41373A 1969-06-06 1970-05-28 Missile Expired - Lifetime US3684215A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE08063/69A SE340417B (de) 1969-06-06 1969-06-06

Publications (1)

Publication Number Publication Date
US3684215A true US3684215A (en) 1972-08-15

Family

ID=20273043

Family Applications (1)

Application Number Title Priority Date Filing Date
US41373A Expired - Lifetime US3684215A (en) 1969-06-06 1970-05-28 Missile

Country Status (10)

Country Link
US (1) US3684215A (de)
JP (1) JPS4810360B1 (de)
BE (1) BE751547A (de)
CH (1) CH508863A (de)
DE (1) DE2027371C3 (de)
FR (1) FR2049166B1 (de)
GB (1) GB1311747A (de)
NL (1) NL161255C (de)
NO (1) NO125748B (de)
SE (1) SE340417B (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4645139A (en) * 1981-06-04 1987-02-24 Societe Nationale Industrielle Aeropatiale Procedure for steering a low-speed missile, weapon system and missile for implementation of the procedure
US5326049A (en) * 1992-04-30 1994-07-05 State Of Israel - Ministry Of Defense Rafael-Armament Development Authority Device including a body having folded appendage to be deployed upon acceleration
US8079308B1 (en) * 1988-10-12 2011-12-20 Aerospatiale Societe Nationale Industrielle Ramjet engine incorporating a tubular structure and a missile propelled by a ramjet engines of this type
US8350200B1 (en) * 2009-03-26 2013-01-08 Lockheed Martin Corporation Passive aerosurface adjustment for static margin management
CN108562195A (zh) * 2018-01-12 2018-09-21 北京航空航天大学 一种便于调整的模块化配重装置及火箭

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2463909B1 (fr) * 1979-08-17 1985-10-25 Thomson Brandt Procede de pilotage et de guidage d'un missile, et missile equipe de moyens de mise en oeuvre de ce procede
FR2500149B1 (fr) * 1981-02-17 1985-12-06 Poudres & Explosifs Ste Nale Chargement propulsif biregime a canal en trompette comportant une section en etoile
GB2172383B (en) * 1981-06-04 1987-08-12 Aerospatiale Guided missile system

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2489953A (en) * 1940-09-04 1949-11-29 Burney Charles Dennistoun Projectile operating with rocket propulsion
US2503271A (en) * 1945-02-06 1950-04-11 Clarence N Hickman Rocket projectile
US2816721A (en) * 1953-09-15 1957-12-17 Taylor Richard John Rocket powered aerial vehicle
US3013494A (en) * 1957-08-09 1961-12-19 Chanut Pierre Louis Jean Guided missile
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2489953A (en) * 1940-09-04 1949-11-29 Burney Charles Dennistoun Projectile operating with rocket propulsion
US2503271A (en) * 1945-02-06 1950-04-11 Clarence N Hickman Rocket projectile
US2816721A (en) * 1953-09-15 1957-12-17 Taylor Richard John Rocket powered aerial vehicle
US3013494A (en) * 1957-08-09 1961-12-19 Chanut Pierre Louis Jean Guided missile
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4645139A (en) * 1981-06-04 1987-02-24 Societe Nationale Industrielle Aeropatiale Procedure for steering a low-speed missile, weapon system and missile for implementation of the procedure
US8079308B1 (en) * 1988-10-12 2011-12-20 Aerospatiale Societe Nationale Industrielle Ramjet engine incorporating a tubular structure and a missile propelled by a ramjet engines of this type
US5326049A (en) * 1992-04-30 1994-07-05 State Of Israel - Ministry Of Defense Rafael-Armament Development Authority Device including a body having folded appendage to be deployed upon acceleration
US8350200B1 (en) * 2009-03-26 2013-01-08 Lockheed Martin Corporation Passive aerosurface adjustment for static margin management
CN108562195A (zh) * 2018-01-12 2018-09-21 北京航空航天大学 一种便于调整的模块化配重装置及火箭
CN108562195B (zh) * 2018-01-12 2019-05-24 北京航空航天大学 一种便于调整的模块化配重装置及火箭

Also Published As

Publication number Publication date
NL161255B (nl) 1979-08-15
JPS4810360B1 (de) 1973-04-02
GB1311747A (en) 1973-03-28
BE751547A (fr) 1970-11-16
FR2049166B1 (de) 1974-05-24
NL7007998A (de) 1970-12-08
SE340417B (de) 1971-11-15
CH508863A (de) 1971-06-15
NL161255C (nl) 1980-01-15
NO125748B (de) 1972-10-23
FR2049166A1 (de) 1971-03-26
DE2027371A1 (de) 1970-12-10
DE2027371B2 (de) 1979-05-03
DE2027371C3 (de) 1980-01-03

Similar Documents

Publication Publication Date Title
US4676136A (en) Apparatus for recoilless firing of projectiles from a lauching tube
US6293091B1 (en) Axisymmetrical annular plug propulsion system for integrated rocket/ramjet or rocket/scramjet
US4444117A (en) Stacked tube submunition dispenser
US3879942A (en) Partition for rocket engines
US3167016A (en) Rocket propelled missile
JP2795537B2 (ja) ミサイルの横方向スラスト集合体
US2503271A (en) Rocket projectile
US3684215A (en) Missile
IL82200A (en) Method and apparatus for launching a projectile at hypersonic velocity
US3790104A (en) High/low aspect ratio dual-mode fin design
US5513571A (en) Airbreathing propulsion assisted gun-launched projectiles
US5078336A (en) Spin-stabilized missile with plug nozzle
US4063415A (en) Apparatus for staged combustion in air augmented rockets
US4964339A (en) Multiple stage rocket propelled missile system
WO2003016849A2 (en) Method and apparatus for testing engines
US3439613A (en) Self-propelled hollow charge having concave liner with propellant contained therein
US2946261A (en) Peripheral nozzle spinner rocket
US4481886A (en) Hollow charge
US4611540A (en) Mortar ammunition
US4886223A (en) Projectile with spin chambers
CN101113882B (zh) 一种降低弹体激波阻力的弹体结构及方法
US6213023B1 (en) Base bleed unit
US2941469A (en) Projectile construction
US3881416A (en) Choked flechette weapon system
US3610093A (en) Recoilless gun