EP0448437A1 - Verbesserungen an Leitwerken mit ausspreizbaren Flügeln - Google Patents

Verbesserungen an Leitwerken mit ausspreizbaren Flügeln Download PDF

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Publication number
EP0448437A1
EP0448437A1 EP91400595A EP91400595A EP0448437A1 EP 0448437 A1 EP0448437 A1 EP 0448437A1 EP 91400595 A EP91400595 A EP 91400595A EP 91400595 A EP91400595 A EP 91400595A EP 0448437 A1 EP0448437 A1 EP 0448437A1
Authority
EP
European Patent Office
Prior art keywords
fins
machine
stabilizer according
flight
rotation
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.)
Withdrawn
Application number
EP91400595A
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English (en)
French (fr)
Inventor
Alain Boely
Gérard Joset
Michel Maxel
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0448437A1 publication Critical patent/EP0448437A1/de
Withdrawn legal-status Critical Current

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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
    • F42B10/16—Wrap-around fins

Definitions

  • the present invention relates to empennages comprising a plurality of fins regularly distributed around the periphery of a machine and articulated around axes oriented longitudinally. It relates more particularly to the combined opening of these fins.
  • the empennages with deployable fins provide a satisfactory response to the problems of storage, carrying, firing or ejection of missiles, ammunition or submunitions, as well as to aerodynamic requirements.
  • the fact that the fins are articulated around longitudinally oriented axes offers the advantage of being able to accommodate them in the caliber of the machine.
  • French patent application n ° 87 09454 in the name of the present plaintiff, relates to deployable tail units of the type defined above, in which each fin is able to pivot, in conjunction with the others, from a folded position to a deployed position thanks to pivoting means comprising an annular ring which can rotate around the axis of revolution of the machine, means for transmitting the rotation movement of the ring in pivoting movement of the wings, and setting means in rotation of the ring.
  • pivoting means comprising an annular ring which can rotate around the axis of revolution of the machine, means for transmitting the rotation movement of the ring in pivoting movement of the wings, and setting means in rotation of the ring.
  • These empennages are "all or nothing" systems, that is to say that the fins are capable of occupying in a controlled manner only the closed position or the fully open position, and that the passage between the two positions is almost instantaneous. Therefore, they cannot be used other than for the function for which they were designed, namely to ensure stability in flight.
  • a tail unit comprises a plurality of fins 2 distributed around the periphery of a machine 1 and articulated on axes Y-Y oriented longitudinally.
  • the fins are in even number to be diametrically opposite two by two, so that the aerodynamic forces on each in the direction of opening or closing are compensated by the aerodynamic forces exerted on the opposite fin.
  • the closed position they are completely housed in the caliber of machine 1.
  • Each fin 2 has at its base a pinion 2a centered on the axis Y-Y and meshed around the periphery of a ring 3, itself centered on the longitudinal axis or axis of revolution X-X of the machine 1.
  • the ring 3 is connected to the shaft 4a of a torque motor 4 which has the function of driving it in rotation between a first angular position corresponding to the closing of the fins and a second angular position corresponding to their complete opening.
  • the motor 4 also has the function of ensuring the maintenance of the ring 3 in any intermediate angular position, to which corresponds an identical partial opening position of all the fins, as illustrated in broken lines at Fig. 2.
  • the motor 4 is mounted on the longitudinal axis of the machine 1, and the ring 3 is toothed on its internal periphery, its connection with the shaft 4a being established by a pinion 5 carried by the latter and an intermediate pinion 6.
  • the torque motor 4 is controlled from a control unit 7 of the machine, the electrical junction comprising, for example , rotary contacts 8.
  • the tail unit is integrated into the machine 1, namely that the fins 2, the ring 3, the engine 4 and the transmission means 5, 6 are mounted on the body of the machine 1.
  • the empennage can be used to fulfill two functions in a distinct manner: in one case, to influence the trajectory of a non-animated craft in flight with a rotational movement on itself; in the other case, on a machine driven by such a rotational movement on itself, ensure at the end of the flight the braking and stopping of this movement (skewing).
  • the progressive opening control of the fins by means of the motor 4 can be preprogrammed as a function of flight time only, or, preferably, as a function of flight criteria, the processing of which takes place in unit 7
  • the movement of the fins is capable of being controlled either in the direction of opening or in the direction of closing, just as the fins can be immobilized for any given period in intermediate open position.
  • the system thus used makes it possible in particular to grant the drag as a function of the flight speed, by deploying minimal fins from the departure of the machine when the speed is high, and increasing as the speed decreases. It also allows control to a certain extent the length of the trajectory, for example according to the flight conditions.
  • the tail In the application to "despinning", the tail remains closed until the terminal flight phase.
  • the instant of its entry into play can be, as in the previous case, preprogrammed as a function of the flight time, or else determined as a function of flight criteria treated in unit 7. From this instant, the opening fins 2 is controlled so as to be progressive as the speed of rotation decreases, failing which the tail unit would be unable to withstand without breaking the significant aerodynamic starting forces exerted on the fully deployed fins.
  • the tail unit of the invention compared to a deploying tail unit of the "all or nothing" type mentioned above, and which would include fins dimensioned small enough to withstand full opening to the aerodynamic starting forces, the tail unit of the invention, by the progressive opening of the fins as the rotational speed decreases, ensures a much faster "skidding".
  • the possibility offered by the invention to use the same empennage indifferently to one or the other of the two functions described above, since none requires its own characteristic (such as dimensioning characteristic fins) relative to each other. This gives an obvious advantage from a manufacturing point of view.
  • Fig. 3 the empennage which comprises the same elements as previously, arranged in the same way, is no longer mounted on the body 1 of the machine, but in a tail block 1b free to rotate about the axis XX relative to the actual body 1a of the machine, by means of bearings 9.
  • the rotary contacts 8 which were only preferred in the example of embodiment of FIG. 1 are here necessary for controlling the motor 4 from the unit 7.
  • This arrangement makes the empennage usable to influence in a controlled way the trajectory of a machine, which is animated in flight by a rotational movement on itself: at the start, the whole of the machine is ie the main body 1a and the tail block 1b, is animated by this rotational movement on itself.
  • the empennage accomplishes the "destining" of the only tail block 1b by progressive opening of the fins 2.
  • the empennage can operate as previously explained with regard to the craft of the Fig. 1, that is to say to influence the trajectory of the craft 1 in a preprogrammed manner as a function of the flight time, or else as a function of flight criteria processed in unit 7.
  • Clutch means can also be provided between the tail block 1b and the body 1a, controllable from the unit 7. These clutch means then make it possible to "strip" the body 1a in the following manner : at a given instant in the terminal flight phase, the fins 2 are retracted, at least partially, then the clutch means are actuated, which has the effect of putting the tail block 1b back into rotation, together with the body 1a. Following this, the fins 2 are gradually redeployed to carry out the "peeling" of the entire body 1a and the tail block 1b. Consequently, in this embodiment, the tail is able to perform successively in a machine rotating on itself the two above-mentioned functions of influencing the trajectory and of stopping the rotation on itself of the 'contraption.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
EP91400595A 1990-03-09 1991-03-05 Verbesserungen an Leitwerken mit ausspreizbaren Flügeln Withdrawn EP0448437A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9003033A FR2659433B1 (fr) 1990-03-09 1990-03-09 Perfectionnements a des empennages a ailettes deployables.
FR9003033 1990-03-09

Publications (1)

Publication Number Publication Date
EP0448437A1 true EP0448437A1 (de) 1991-09-25

Family

ID=9394575

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91400595A Withdrawn EP0448437A1 (de) 1990-03-09 1991-03-05 Verbesserungen an Leitwerken mit ausspreizbaren Flügeln

Country Status (2)

Country Link
EP (1) EP0448437A1 (de)
FR (1) FR2659433B1 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5927643A (en) * 1997-11-05 1999-07-27 Atlantic Research Corporation Self-deploying airfoil for missile or the like
WO2002079716A1 (en) * 2001-03-20 2002-10-10 Bofors Defence Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
DE102006022248B3 (de) * 2006-05-12 2007-11-08 Lfk-Lenkflugkörpersysteme Gmbh Vorrichtung an Wickelflügeln eines Flugkörpers
CN105129082A (zh) * 2015-09-01 2015-12-09 湖南云顶智能科技有限公司 用于无人机的螺旋桨收折装置
EP3111157A4 (de) * 2014-02-26 2017-09-27 Israel Aerospace Industries Ltd. Rippeneinsatzsystem
RU2732370C1 (ru) * 2020-02-27 2020-09-16 Акционерное общество "Брянский химический завод имени 50-летия СССР" Вращающаяся ракета

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2642693C2 (ru) * 2016-04-21 2018-01-25 Акционерное общество "Новосибирский завод искусственного волокна" Сверхзвуковой реактивный снаряд

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1467684A (fr) * 1966-02-09 1967-01-27 Aerojet General Co Dispositif et procédé de commande des pales de giration de fusées et autres engins auto-propulsés
US3563495A (en) * 1969-02-03 1971-02-16 Us Air Force Power operated folding wing for rockets and missiles
US3695177A (en) * 1964-09-17 1972-10-03 Us Navy Air brake for airborne missiles
WO1981000908A1 (en) * 1979-09-27 1981-04-02 K Andersson Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized
US4296895A (en) * 1979-01-15 1981-10-27 General Dynamics Corporation Fin erection mechanism
US4588145A (en) * 1983-08-15 1986-05-13 General Dynamics Pomona Division Missile tail fin assembly
EP0236552A1 (de) * 1985-12-18 1987-09-16 The State Of Israel, Ministry Of Defence, Israel Military Industries Bündelgeschoss-Granate mit Einrichtung zur Drallverminderung
DE8703985U1 (de) * 1987-03-17 1988-07-14 Diehl Gmbh & Co, 8500 Nuernberg, De

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3695177A (en) * 1964-09-17 1972-10-03 Us Navy Air brake for airborne missiles
FR1467684A (fr) * 1966-02-09 1967-01-27 Aerojet General Co Dispositif et procédé de commande des pales de giration de fusées et autres engins auto-propulsés
US3563495A (en) * 1969-02-03 1971-02-16 Us Air Force Power operated folding wing for rockets and missiles
US4296895A (en) * 1979-01-15 1981-10-27 General Dynamics Corporation Fin erection mechanism
WO1981000908A1 (en) * 1979-09-27 1981-04-02 K Andersson Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized
US4588145A (en) * 1983-08-15 1986-05-13 General Dynamics Pomona Division Missile tail fin assembly
EP0236552A1 (de) * 1985-12-18 1987-09-16 The State Of Israel, Ministry Of Defence, Israel Military Industries Bündelgeschoss-Granate mit Einrichtung zur Drallverminderung
DE8703985U1 (de) * 1987-03-17 1988-07-14 Diehl Gmbh & Co, 8500 Nuernberg, De

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5927643A (en) * 1997-11-05 1999-07-27 Atlantic Research Corporation Self-deploying airfoil for missile or the like
WO2002079716A1 (en) * 2001-03-20 2002-10-10 Bofors Defence Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
US7104497B2 (en) 2001-03-20 2006-09-12 Bae Systems Bofors Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
US7487934B2 (en) 2001-03-20 2009-02-10 Bae Systems Bofors Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
DE102006022248B3 (de) * 2006-05-12 2007-11-08 Lfk-Lenkflugkörpersysteme Gmbh Vorrichtung an Wickelflügeln eines Flugkörpers
EP1855076A1 (de) 2006-05-12 2007-11-14 LFK-Lenkflugkörpersysteme GmbH Wickelflügeln eines Flugkörpers
EP3111157A4 (de) * 2014-02-26 2017-09-27 Israel Aerospace Industries Ltd. Rippeneinsatzsystem
US9989338B2 (en) 2014-02-26 2018-06-05 Israel Aerospace Industries Ltd. Fin deployment system
CN105129082A (zh) * 2015-09-01 2015-12-09 湖南云顶智能科技有限公司 用于无人机的螺旋桨收折装置
CN105129082B (zh) * 2015-09-01 2018-07-27 湖南云顶智能科技有限公司 用于无人机的螺旋桨收折装置
RU2732370C1 (ru) * 2020-02-27 2020-09-16 Акционерное общество "Брянский химический завод имени 50-летия СССР" Вращающаяся ракета

Also Published As

Publication number Publication date
FR2659433B1 (fr) 1992-05-15
FR2659433A1 (fr) 1991-09-13

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