EP0448437A1 - Verbesserungen an Leitwerken mit ausspreizbaren Flügeln - Google Patents
Verbesserungen an Leitwerken mit ausspreizbaren Flügeln Download PDFInfo
- 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- Withdrawn
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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.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
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)
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)
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)
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 Nürnberg | Munition mit Drallbremse |
-
1990
- 1990-03-09 FR FR9003033A patent/FR2659433B1/fr not_active Expired - Fee Related
-
1991
- 1991-03-05 EP EP91400595A patent/EP0448437A1/de not_active Withdrawn
Patent Citations (8)
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 Nürnberg | Munition mit Drallbremse |
Cited By (11)
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 |
---|---|
FR2659433A1 (fr) | 1991-09-13 |
FR2659433B1 (fr) | 1992-05-15 |
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Legal Events
Date | Code | Title | Description |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
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AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): BE CH DE GB IT LI SE |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 19920326 |