US3588004A - Missile with brake flaps - Google Patents

Missile with brake flaps Download PDF

Info

Publication number
US3588004A
US3588004A US755526A US3588004DA US3588004A US 3588004 A US3588004 A US 3588004A US 755526 A US755526 A US 755526A US 3588004D A US3588004D A US 3588004DA US 3588004 A US3588004 A US 3588004A
Authority
US
United States
Prior art keywords
flap
hub
missile
wedge
flaps
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
US755526A
Other languages
English (en)
Inventor
Xaver Suter
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.)
Rheinmetall Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Application granted granted Critical
Publication of US3588004A publication Critical patent/US3588004A/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

Definitions

  • a latch member secures the flap in the operating position from any lifting off from the stop.
  • a wedgeshaped member is arranged between the missile body and a cylindrical hub on the flap so that when the flap is lifted off the stop the friction between the hub and the wedge-shaped member urges the wedge-shaped member in between the body and the hub.
  • a spring urges the wedge-shaped member between the body and the hub.
  • the invention relates to a missile with brake flaps which can be swung out of a normal position into an operating position against an adjustable stop.
  • the object of the present invention is to avoid this drawback and to create a missile in which the flaps cannot be pulled off the said stop.
  • the missile according to the invention is characterized by the fact that latch members are arranged which secure the flaps in any operating position from being lifted off the stop.
  • FIG. I shows an axial longitudinal cross section; on the right-hand side the section is made through the axis of a folded-in fin and a flap in the normal position, while in the left half the section is taken through the middle of a flap and fin and flap in the swung-out position.
  • FIG. 2 shows a cross section along the line VIVI of FIG. I, in which the fin and flap are in the swung-out position on the left side and in the normal position on the right.
  • FIG. 3 is a diagrammatic representation of the hub portion of FIG. 1 in the normal position
  • FIG. 4 is a diagrammatic representation of the hub portion of FIG. 1 in its operating position.
  • the brake flaps 30 are adapted to pivot around axes 29, which are arranged in the region of the rear part of folding fin I3 of the empennage.
  • the forked hub portions 58 (supported on axes 29) of the flaps 30 engage in grooves 59, arranged in a flange 60 of the nozzle body 3.
  • the front part of flange 60 is offset with respect to the rear part and provided with a backward-extending extension 79, which terminates in a frontal area 55 which supports the hubs of fins 13.
  • a thread on which the adjusting ring 62 is screwed and which can be shifted by turning in the axial direction.
  • the flaps 30 lie with the surfaces 80 (FIG. 4) of their hub portions in a plane perpendicular to the longitudinal axis of the rocket (see FIG. 1) in which also the rear surface of flange 60, forming the stop for setting ring 62, is situated, the braking action will be at the maximum.
  • a wedge-shaped latch member 67 indicated in FIG. 1, together with the hub portion 58 of a flap 30 is shown on an enlarged scale in FIGS. 3 and 4.
  • a notch 68 is cut out from the front in said wedge-shaped latch member 67, which tapers from front to back.
  • One end 70 of another spiral spring 69, which is wound around the spring 65 is supported on the surface 72 of the latch member 67 bordering the notch 68.
  • the other end 71 of the spring 69 rests on the surface 73 (on the outside with respect to the axis of the rocket) of the latch member 67 and presses same against the bottom 74 of slot 59 in the nozzle body 3/
  • the latch member 67 is pressed backwards through the end 70 of the pretensioned spring 69,
  • the axis of rotation O of a flap 30 does not coincide with the axis P of the cylindrical surface 76, which forms the rounded end of the hub portion 58.
  • the surface 73 of the latch member 67 is tangent to this cylinder 76 along a line A.
  • the two parallel axes O and P which are at a certain distance from each other, lie in a plane which, in the inactive position of the flap 30 (FIG. 3) intersects thecylinder 76 along the line B and forms an angle of 45 to the plane perpendicular to the axis of the rocket.
  • a plane 77 containing the axis of rotation O intersects the surface 73 of the latch member 67, to which it is perpendicular, along a line C.
  • a cylinder 78 (indicated in dotted lines in the drawing), the axis of which coincides with the axis 0 and its radius isequal to the distance A0 of the axis 0 from the tangent A, intersects the cylinder 76 along a line E.
  • Another cylinder 79 (shown in dotted lines) surrounding O and having the radius OB, intersects the plane 77 along a line D.
  • the distance of that part of the cylinder 76, which lies between A and E, from the axis 0 is greater than the distance of cylinder 78 from this same axis, the greatest distance between these two cylindrical surfaces 76 and 78 occurring in the plane which contains the axis 0 and the line B.
  • the cylinder 76 runs along a line, designated as G, in the plane surface 80 of the hub portion 58. The distance of the cylinder 76 from the axis of rotation 0 decreases continuously from B to G.
  • This embodiment operates in the following manner:
  • the fins 13 are opened by the springs 19.
  • the hub portions 17 are supported on the frontal flange portion 79 of the nozzle body 3, whereby the fins 13 are locked. Since the fins 13 are axially displaced when opening, the earns 25 of the comoving bolts 24 slide over the slots 66 in the flaps 30. The latter are thereby released and swung by springs 65 around the axes 29 into the operating position, in which they are supported on the setting ring 62 (see FIG. 1).
  • the entire range of action of the flaps 30, determined by the limit positions of the setting ring 62, is bounded by the position of said flaps as shown on the left in FIG. 1, and also by a position completely swung back at 180 to the inactive position.
  • the range of action of the flaps 30 is shifted to the rear region of the fin 13, which is an advantage insofar as the stabilizing effect of the empennage cannot be undesirably affected by the stream around the flaps.
  • Another advantage of this arrangement lies in the fact that the aerodynamic braking forces, which also have a stabilizing effect uponthe rocket, in
  • the latching member 67 of course also acts in the same manner in any other predetermined operating position of the flap.
  • centrifugal forces act upon the flaps 30. These forces solicit the flaps when in their operative position, to turn in the opposite direction to the aerodynamic forces, that is (as seen in FIG. 4) clockwise.
  • the latch members 67 now prevent the flaps 30 from being turned away from the setting ring by the centrifugal forces when the speed of the rocket decreases and therefore the aerodynamic forces are reduced.
  • a missile comprising a body, a brake flap having a cylindrical hub movable on said body from a normal position into an operating position, a continuously adjustable stop against which said flap impinges when in said operating position and a continuously adjustable latch member cooperating with said flap to secure said flap in said operating position from lifting off from said stop.
  • said latch member comprises a wedge-shaped member arranged between said body and said cylindrical hub so that when said flap is lifted off said stop the friction between said hub and said wedge-shaped member urges said wedge-shaped member in between said body and said hub.
  • a missile comprising a body, a brake flap having a cylindrical hub movable on said body from a normal position into an operating position, an adjustable stop against which said flap impinges when in said operating position, and a latch member securing said flap in said operating position from lifting off from said stop comprising a wedge-shaped member arranged between said body and said cylindrical hub so that when said flap is lifted off said stop the friction between said hub and said wedge-shaped member urges said wedge-shaped member in between said body and said hub.
  • a missile according to claim 2 wherein said hub has a borehole arranged eccentrically with respect to its cylindrical surface, and the swivel axis of said flap is arranged in said borehole.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Braking Arrangements (AREA)
  • Carbon And Carbon Compounds (AREA)
US755526A 1967-09-11 1968-08-27 Missile with brake flaps Expired - Lifetime US3588004A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1266767A CH480613A (de) 1967-09-11 1967-09-11 Geschoss mit Bremsflügeln

Publications (1)

Publication Number Publication Date
US3588004A true US3588004A (en) 1971-06-28

Family

ID=4385265

Family Applications (1)

Application Number Title Priority Date Filing Date
US755526A Expired - Lifetime US3588004A (en) 1967-09-11 1968-08-27 Missile with brake flaps

Country Status (10)

Country Link
US (1) US3588004A (de)
JP (1) JPS4836800B1 (de)
AT (1) AT283963B (de)
BE (1) BE720312A (de)
CH (1) CH480613A (de)
DE (1) DE1728140B1 (de)
FR (1) FR1597485A (de)
GB (1) GB1213505A (de)
NL (1) NL6812960A (de)
SE (1) SE352729B (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4295617A (en) * 1979-10-02 1981-10-20 The United States Of America As Represented By The Secretary Of The Army Selectable drag brakes for rocket range control
US4327886A (en) * 1972-11-30 1982-05-04 The United States Of America As Represented By The Secretary Of The Navy Integral rocket ramjet missile
WO1987002963A1 (en) * 1985-11-14 1987-05-21 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
US4717093A (en) * 1985-08-12 1988-01-05 Grumman Aerospace Corporation Penguin missile folding wing configuration
US5143320A (en) * 1989-12-12 1992-09-01 Societe Nationale Industrielle Et Aerospatiale Spoiler torque controlled supersonic missile
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
US5762291A (en) * 1996-10-28 1998-06-09 The United States Of America As Represented By The Secretary Of The Army Drag control module for stabilized projectiles
KR101234218B1 (ko) 2010-06-25 2013-02-18 국방과학연구소 비행체의 날개장치 및 이를 구비하는 비행체
US20130056578A1 (en) * 2011-09-05 2013-03-07 Michael Alculumbre Projectile
CN103389010A (zh) * 2012-05-07 2013-11-13 刘应杰 尾段为翼片无间隙固定及耳销轴不受力的火箭弹
US10401134B2 (en) * 2015-09-29 2019-09-03 Nexter Munitions Artillery projectile with a piloted phase

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1523963A (en) * 1976-02-26 1978-09-06 Hawker Siddeley Dynamics Ltd Method and means for auxiliary control of vehicle direction
DE4119613C2 (de) * 1991-06-14 1997-03-27 Diehl Gmbh & Co Flugkörper mit ausklappbaren Leiteinrichtungen

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2465401A (en) * 1943-09-23 1949-03-29 Leslie A Skinner Rocket fin assembly
FR1191519A (fr) * 1958-02-13 1959-10-20 Hotchkiss Brandt Empennage déployant pour projectile d'artillerie
NL295319A (de) * 1960-07-11

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4327886A (en) * 1972-11-30 1982-05-04 The United States Of America As Represented By The Secretary Of The Navy Integral rocket ramjet missile
US4295617A (en) * 1979-10-02 1981-10-20 The United States Of America As Represented By The Secretary Of The Army Selectable drag brakes for rocket range control
US4717093A (en) * 1985-08-12 1988-01-05 Grumman Aerospace Corporation Penguin missile folding wing configuration
WO1987002963A1 (en) * 1985-11-14 1987-05-21 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
US4691880A (en) * 1985-11-14 1987-09-08 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
US5143320A (en) * 1989-12-12 1992-09-01 Societe Nationale Industrielle Et Aerospatiale Spoiler torque controlled supersonic missile
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
US5762291A (en) * 1996-10-28 1998-06-09 The United States Of America As Represented By The Secretary Of The Army Drag control module for stabilized projectiles
KR101234218B1 (ko) 2010-06-25 2013-02-18 국방과학연구소 비행체의 날개장치 및 이를 구비하는 비행체
US8525089B2 (en) 2010-06-25 2013-09-03 Agency For Defense Development Wing device and flight vehicle having the same
US20130056578A1 (en) * 2011-09-05 2013-03-07 Michael Alculumbre Projectile
US9115965B2 (en) * 2011-09-05 2015-08-25 Michael Alculumbre Projectile
CN103389010A (zh) * 2012-05-07 2013-11-13 刘应杰 尾段为翼片无间隙固定及耳销轴不受力的火箭弹
CN103389010B (zh) * 2012-05-07 2015-07-22 刘应杰 尾段为翼片无间隙固定及耳销轴不受力的火箭弹
US10401134B2 (en) * 2015-09-29 2019-09-03 Nexter Munitions Artillery projectile with a piloted phase
US10788297B2 (en) * 2015-09-29 2020-09-29 Nexter Munitions Artillery projectile with a piloted phase

Also Published As

Publication number Publication date
AT283963B (de) 1970-08-25
FR1597485A (de) 1970-06-29
GB1213505A (en) 1970-11-25
CH480613A (de) 1969-10-31
DE1728140B1 (de) 1972-05-04
NL6812960A (de) 1969-03-13
SE352729B (de) 1973-01-08
JPS4836800B1 (de) 1973-11-07
BE720312A (de) 1969-02-17

Similar Documents

Publication Publication Date Title
US3588004A (en) Missile with brake flaps
US3598345A (en) Rocket with folding fins and braking device
US4334657A (en) Device for fin-stabilized shell or the like
US2923241A (en) Folding stabilizing fins
US2494026A (en) Projectile
US2793591A (en) Fin arrangement for a projectile
US2788744A (en) Projectile for mortar
US4029018A (en) Sabot for subcalibre projectile
US3127838A (en) Retractable blade tail unit for projectiles
US3790104A (en) High/low aspect ratio dual-mode fin design
US4119037A (en) Carrier projectiles for ejectable payloads
DE10015514A1 (de) Flügelstabilisiertes Geschoß
US3921937A (en) Projectile or rocket preferably with unfolded tail unit
US3053184A (en) Gas ejecting nozzle and projectile stabilizing fins for a self-propelled projectile
US4534294A (en) Fin-stabilized projectile with propellant cage
JPH0411798B2 (de)
US2980370A (en) Flying body for supersonic speed
US4209146A (en) Device for extensible fin blade on shell or the like
DE3122320A1 (de) Drallstabilisierter uebungsflugkoerper
US3347492A (en) Projectile with a rearwardly directed steering tube
US3031967A (en) Fin arrangement for projectiles
US4641802A (en) Projectile stabilization system
US3880383A (en) Control flap unit for projectiles or rockets
US5481980A (en) Releasable sabot for a subcaliber projectile
US3146711A (en) Shaped charge with rotational insert