EP0628783B1 - Système d'actionnement pour gouverne aérodynamique et systèmes pour le pilotage d'aéronefs - Google Patents
Système d'actionnement pour gouverne aérodynamique et systèmes pour le pilotage d'aéronefs Download PDFInfo
- Publication number
- EP0628783B1 EP0628783B1 EP94401101A EP94401101A EP0628783B1 EP 0628783 B1 EP0628783 B1 EP 0628783B1 EP 94401101 A EP94401101 A EP 94401101A EP 94401101 A EP94401101 A EP 94401101A EP 0628783 B1 EP0628783 B1 EP 0628783B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- steering
- control surfaces
- aerodynamic control
- airborne vehicle
- positions
- 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
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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
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
Definitions
- the present invention relates to an actuation system for aerodynamic control, as well as systems for the piloting of aircraft piloted in couple by control surfaces aerodynamic, comprising at least one such actuation system.
- the object of the present invention is to provide a system simple to operate, inexpensive and with very low aging, who is likely to meet the requirements previously mentioned.
- the switching of the control surface aerodynamics of one of its stable active positions at the other is obtained simply by activating said electromagnetic coils, causing displacement of the movable pallet causing the switching of said aerodynamic control.
- the document GB-A-1 057 863 describes a system actuation to bring an aerodynamic control surface into either of two active and stable positions, said aerodynamic control surface being rotatably mounted on a fixed support and said system comprising a single coil electromagnetic associated with said control surface, arranged on said fixed support and acting directly on said rudder (without interposition of pallet) to make it turn against the action of a spring, so that said control surface can take (exclusively, without position neutral) either of two extreme positions.
- the elements constituting said system actuation according to the present invention are few numerous and of limited cost. Therefore, on the one hand the manufacturing price of the actuation system in accordance with the invention is small and, on the other hand, the volume of the actuation system is extremely small, which is very advantageous for its use on aircraft of small size, for example light missiles.
- said movable element is constituted a rotating shaft and said movable pallet is fixed to the support by means of a spring leaf.
- said actuation system according to the invention has high performance in terms of torque and response time.
- the neutral position of the control surface corresponds at the middle position of said pallet between said electromagnetic coils and this middle position of the pallet is defined by the rest position of said blade spring.
- this middle position of the pallet the appropriate rigidity, it is advantageous that, in neutral position of the control surface, said movable pallet and said leaf spring are orthogonal.
- the present invention also relates to a system for piloting of an aircraft piloted in couple by at least two aerodynamic control surfaces, said control system comprising at least one actuation system like the one described previously.
- the invention relates, more particularly, to a system for piloting an aircraft in autorotation comprising two aerodynamic control surfaces arranged symmetrically with respect to to the body of the latter.
- This steering system can in particular be used on multi-mission and anti-aircraft missiles light, characterized by high speed and a low mass after launch. Steering in efficient torque only requires control surfaces aerodynamics of reduced size.
- Each of said aerodynamic control surfaces can be actuated by an individual actuation system in accordance with the invention and said aerodynamic control surfaces are controlled, synchronously, symmetrically with respect to to the body of the aircraft, by the simultaneous activation of a coil of each of said individual actuation systems.
- said control surfaces are actuated by a common actuation system, said actuation system common with identical additional mobile element said movable and integral element of said pallet in a symmetrical position with respect to that of said element mobile, said mobile element carrying one of said aerodynamic control surfaces and said additional mobile element carrying the other of said aerodynamic control surfaces.
- This control system is particularly suitable for very small aircraft, especially mini missiles, whose reduced volume does not allow the arrangement several actuation systems, including control surfaces aerodynamics of restricted surface are subjected to relatively low forces and can thus be operated by a single actuation system.
- Control systems with one or two actuation systems, such as those described above, and comprising two aerodynamic control surfaces with two stable positions each, actuated symmetrically synchronously, are susceptible to take either of two positions of steering, depending on the common stable position in which are said aerodynamic control surfaces.
- the desired steering force is easily obtained and this simply by putting the steering system, for respective periods of varying length, in either of said driving positions.
- the previous switching mode has a disadvantage when looking for a driving force very weak.
- the actuation system allowing the switching has a time threshold, corresponding to its response time. Therefore, it is impossible obtain a 2S angle corresponding to a duration less than this time threshold.
- the present invention also relates to a system for piloting an aircraft with four aerodynamic control surfaces arranged uniformly around said aircraft spaced.
- such a control system which is particularly suitable for a large air-to-ground missile or a planing bomb with limited maneuver, is remarkable in that that the opposite control surfaces are identical and in that each of them is actuated by a system individual actuation according to the invention.
- Figure 1 is a partial perspective view of a actuation system according to the invention.
- Figure 2 shows, schematically, the piloting an aircraft, comprising two aerodynamic control surfaces operated by two separate actuation systems.
- Figure 3 shows, schematically, the piloting an aircraft, comprising two aerodynamic control surfaces operated by the same actuation system.
- Figure 4 illustrates the generation of a lateral force of piloting, according to a first piloting principle.
- Figure 5 illustrates the generation of a lateral force of piloting, according to a second piloting principle.
- Figure 6 is the block diagram of the control system of an aircraft comprising four aerodynamic control surfaces.
- control surfaces are represented schematically in the form of pallets.
- the actuation system 1 is intended to actuate a aerodynamic control surface G partially shown and schematically in this figure.
- said actuation system 1 has two identical electromagnetic coils A and B arranged one opposite the other on a fixed support 2, which can be attached to the body of an aircraft (not shown). Said coils A and B can be activated independently, via a control system (not shown).
- Said actuation system 1 also includes a movable pallet P fixed elastically by one of its ends 4 on the fixed support 2, via a spring leaf 5 integral with both said end 4 and of said support 2.
- said blade of spring 5 is embedded by its opposite ends, at the times in said fixed support 2 and in the end 4 of the pallet P.
- the other (free) end 6 of pallet P is disposed between said coils A and B.
- a mobile element in this case a tree rotary 7, is secured laterally to said pallet P at level of the end 4 of the latter, coaxially with the X-X axis.
- Said rotary shaft 7 carries the aerodynamic control surface G arranged parallel to the pallet P and shown in solid lines in its neutral position in Figure 1.
- control surface G is integral with the displacement of the free end 6 of the pallet P between the coils A and B.
- the actuation system 1 can be used in a piloting system 12 of an aircraft 14 in autorotation around its Y-Y axis, which is shown on Figure 2, partially and schematically, the body 13.
- Said aircraft 14 is piloted in pairs by two control surfaces aerodynamics G1 and G2 identical, arranged so symmetrical about the Y-Y axis.
- Each of said control surfaces aerodynamic G1 and G2 is powered by a system actuation 1 individual, and this synchronously, so that said control surfaces are always in a same piloting plan.
- the coils A of each of the two actuation systems 1 are activated at the same time time. The same is true for coils B.
- control system 12 Depending on whether the control system 12 is in one or the other of said riding positions, it generates two piloting forces of the same module, directed according to the same Z-Z direction (perpendicular to X-X and Y-Y directions) but in the opposite direction.
- control system 20 comprises a single system actuation 1 to actuate the two aerodynamic control surfaces G1 and G2.
- the piloting of the aircraft 14 in autorotation is carried out in the same way for the two piloting systems 12 and 20 described above.
- the control system 12 or 20 is successively switched into its two control positions, thus generating at any time a control force of module f , of direction ZZ, and whose direction depends, at a given time, from the steering position used at that time.
- the control system 12 or 20 is maintained in a first piloting position for a period corresponding to an angle 2S of a circle C, representing the duration of one rotation of the aircraft, then is switched to the other driving position for the rest of the duration of said rotation.
- Said first piloting position generates, at successive instants, on the circle C, along the arc of the circle defined by the angle 2S, radial forces of the same module f (as represented at points 21), while that the second piloting position generates piloting forces of the same module f but of opposite direction (as represented at points 22).
- this F1 driving force always remains greater than a minimum force.
- the control system 12 or 20 is switched to the same driving position for two durations corresponding respectively to two angles 2S1 and 2S2 on circle C and defined so that these angles 2S1 and 2S2 are opposite and have the same bisector L-L.
- This second steering principle is particularly appropriate to obtain module driving forces F2 restricted, since it is possible to make the difference
- the actuation system 1 can also be used in a control system 25, such as shown schematically in Figure 6, to control relatively heavy aircraft, such as a large one air-to-ground missile or a maneuvering planar bomb, through four G3 aerodynamic control surfaces, G4, G5 and G6.
- relatively heavy aircraft such as a large one air-to-ground missile or a maneuvering planar bomb
- Said aerodynamic control surfaces G3, G4, G5 and G6, actuated each by an individual actuation system 1 are arranged around the aircraft (not shown), being each time separated by 90 °, so that, on the one hand the aerodynamic control surfaces G3 and G5 which are identical and, on the other hand, the aerodynamic control surfaces G4 and G6 which are identical, are arranged symmetrically with respect to the axis of said aircraft.
- the piloting of said aircraft is carried out by modifying the activation electromagnetic coils A and B of the different actuation systems 1, and therefore the position of the control surfaces corresponding aerodynamics.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Details Of Aerials (AREA)
- Train Traffic Observation, Control, And Security (AREA)
- Braking Arrangements (AREA)
Description
- une bobine électromagnétique supplémentaire agencée sur ledit support fixe, en regard de ladite bobine électromagnétique citée en premier ;
- une palette mobile dont l'une des extrémités est fixée élastiquement audit support fixe, et dont l'autre extrémité est disposée entre lesdites bobines et est susceptible d'être attirée par chacune desdites bobines, de sorte que les deux positions actives et stables sont opposées l'une de l'autre par rapport à une position neutre ; et
- un élément mobile solidaire de ladite palette et portant ladite gouverne aérodynamique.
- dans l'une desdites positions de pilotage pendant une durée correspondant à un angle 2S d'un cercle représentant la durée d'un tour de rotation de l'aéronef ; et
- dans l'autre position de pilotage pendant le reste dudit tour de rotation, l'angle 2S vérifiant la relation |sinS|=(π/2f).F1 et comportant comme bissectrice ladite direction définie.
- dans l'une desdites positions de pilotage pendant deux périodes non successives correspondant respectivement à deux angles 2S1 et 2S2 d'un cercle représentant la durée d'un tour de rotation de l'aéronef ; et
- dans l'autre position de pilotage pendant le reste dudit tour de rotation, lesdits angles S1 et S2 étant opposés, comportant comme même bissectrice ladite direction définie et vérifiant la relation |sinS1-sinS2|=(π/2f).F2.
- un système de guidage, déterminant les ordres de roulis, tangage et lacet ; et
- un calculateur, recevant lesdits ordres, et déterminant l'activation des différentes bobines électromagnétiques.
- dans la position active stable 10 qui fait un angle +Θ par rapport à la position neutre, lorsque la bobine A est activée et que l'extrémité libre 6 de la palette P se trouve au contact de celle-ci ; et
- dans la position active stable 11 qui fait un angle -Θ par rapport à la position neutre, lorsque la bobine B est activée et que l'extrémité libre 6 se trouve au contact de cette dernière.
- une première position de pilotage, lorsque les palettes P sont au contact des bobines A et qu'alors les gouvernes aérodynamiques G1 et G2 se trouvent respectivement dans des positions 15 et 16 partiellement représentées en traits interrompus sur la figure 2 et faisant un angle +Θ avec la position médiane représentée ; et
- une seconde position de pilotage, lorsque les palettes P sont au contact des bobines B et qu'alors les gouvernes aérodynamiques G1 et G2 se trouvent respectivement dans des positions 17 et 18 partiellement représentées en traits interrompus et faisant un angle -Θ avec la position médiane représentée.
- une première position de pilotage, lorsque la palette P est au contact de la bobine A et que les gouvernes aérodynamiques G1 et G2 se trouvent respectivement dans les positions 15 et 16 ; et
- une seconde position de pilotage, lorsque la palette P est au contact de la bobine B et que les gouvernes aérodynamiques G1 et G2 se trouvent alors respectivement dans les positions 17 et 18.
- un système de guidage 27 déterminant les ordres de roulis, de tangage et de lacet ; et
- un calculateur 28, recevant lesdits ordres par l'intermédiaire d'une liaison 29, déterminant l'activation des bobines électromagnétiques A et B des systèmes d'actionnement 1 associés à chacune des gouvernes aérodynamiques G3, G4, G5 et G6, et commandant lesdites bobines A et B par l'intermédiaire de liaisons 30 à 33.
Claims (11)
- Système d'actionnement (1) pour amener une gouverne aérodynamique (G) dans l'une ou l'autre de deux positions actives et stables, ladite gouverne aérodynamique (G) étant montée rotative sur un support fixe (2) et ledit système comportant une bobine électromagnétique (A ou B) agencée sur ledit support fixe (2) pour faire tourner ladite gouverne aérodynamique à l'encontre de l'action de moyens élastiques, caractérisé en ce qu'il comporte :une bobine électromagnétique (B ou A) supplémentaire agencée sur ledit support fixe (2), en regard de ladite bobine électromagnétique (A ou B) citée en premier ;une palette mobile (P) dont l'une (4) des extrémités est fixée élastiquement audit support fixe (2), et dont l'autre extrémité (6) est disposée entre lesdites bobines (A,B) et est susceptible d'être attirée par chacune desdites bobines, de sorte que les deux positions actives et stables sont opposées l'une de l'autre par rapport à une position neutre ; etun élément mobile (7) solidaire de ladite palette (P) et portant ladite gouverne aérodynamique (G).
- Système d'actionnement selon la revendication 1,
caractérisé en ce que ledit élément mobile est constitué d'un arbre rotatif (7). - Système d'actionnement selon l'une des revendications 1 ou 2,
caractérisé en ce que ladite palette mobile (P) est fixée élastiquement audit support par l'intermédiaire d'une lame de ressort (5). - Système d'actionnement selon la revendication 3,
caractérisé en ce que, en position neutre de la gouverne, ladite palette mobile (P) et ladite lame de ressort (5) sont orthogonales. - Système pour le pilotage d'un aéronef piloté en couple par au moins deux gouvernes aérodynamiques (G1, G2, G3, G4, G5, G6),
caractérisé en ce qu'il comporte au moins un système d'actionnement (1) selon l'une des revendications 1 à 4. - Système pour le pilotage d'un aéronef en autorotation, comportant deux gouvernes aérodynamiques identiques (G1,G2) agencées symétriquement par rapport au corps de ce dernier, selon la revendication 5,
caractérisé en ce que chacune desdits gouvernes aérodynamiques (G1,G2) est actionnée par un système d'actionnement (1) individuel et en ce que lesdites gouvernes aérodynamiques (G1,G2) sont commandées, de façon synchrone, symétriquement par rapport au corps de l'aéronef, par l'activation simultanée d'une bobine de chacun desdits systèmes d'actionnement individuels. - Système pour le pilotage d'un aéronef en autorotation, comportant deux gouvernes aérodynamiques identiques (G1,G2) agencées symétriquement par rapport au corps de ce dernier, selon la revendication 5,
caractérisé en ce que lesdites gouvernes (G1,G2) sont actionnées par un système d'actionnement (1) commun, ledit système d'actionnement (1) commun comportant un élément mobile supplémentaire (7) identique audit élément mobile (7) et solidaire de ladite palette dans une position symétrique par rapport à celle dudit élément mobile, ledit élément mobile portant l'une desdites gouvernes aérodynamiques et ledit élément mobile supplémentaire portant l'autre desdites gouvernes aérodynamiques. - Système selon l'une des revendications 6 ou 7, pour le pilotage d'un aéronef, comportant deux gouvernes aérodynamiques, à deux positions actives stables chacune, actionnées symétriquement de façon synchrone et mettant, en fonction de la position stable commune dans laquelle elles se trouvent, ledit système de pilotage dans l'une de deux positions de pilotage, le module de la force de pilotage étant égal à f dans chacune desdites positions de pilotage,
caractérisé en ce que, pour obtenir sur un tour de rotation de l'aéronef une force moyenne de pilotage de module F1 dirigée selon une direction définie (Ox), il est successivement commuté :dans l'une desdites positions de pilotage pendant une durée correspondant à un angle 2S d'un cercle (C) représentant la durée d'un tour de rotation de l'aéronef ; etdans l'autre position de pilotage pendant le reste dudit tour de rotation, l'angle 2S vérifiant la relation |sinS|=(π/2f).F1 et comportant comme bissectrice ladite direction définie (Ox). - Système selon l'une des revendications 6 ou 7, pour le pilotage d'un aéronef, comportant deux gouvernes aérodynamiques à deux positions actives stables chacune, actionnées symétriquement de façon synchrone, et mettant, en fonction de la position stable dans laquelle elles se trouvent, ledit système dans l'une de deux positions de pilotage, le module de la force de pilotage étant égal à f dans chacune desdites positions de pilotage,
caractérisé en ce que, pour obtenir sur un tour de rotation de l'aéronef une force moyenne de pilotage de module F2 dirigée selon une direction définie (L-L), il est successivement commuté :dans l'une desdites positions de pilotage pendant deux périodes non successives correspondant respectivement à deux angles 2S1 et 2S2 d'un cercle (C) représentant la durée d'un tour de rotation de l'aéronef ; etdans l'autre position de pilotage pendant le reste dudit tour de rotation, lesdits angles S1 et S2 étant opposés, comportant comme même bissectrice ladite direction définie (L-L) et vérifiant la relation |sinS1-sinS2|=(π/2f).F2. - Système selon la revendication 5, pour le pilotage d'un aéronef, comportant quatre gouvernes aérodynamiques (G3, G4, G5, G6) agencées de façon uniformément espacée autour dudit aéronef,
caractérisé en ce que les gouvernes à chaque fois opposées sont identiques et en ce que chacune desdites gouvernes est actionnée par un système d'actionnement (1) individuel. - Système pour le pilotage d'un aéronef selon la revendication 10,
caractérisé en ce qu'il est muni d'un dispositif de commande (26) destiné à commander l'activation des bobines électromagnétiques (A,B) des différents systèmes d'actionnement individuels, comportant :un système de guidage (27), déterminant les ordres de roulis, tangage et lacet ; etun calculateur (28), recevant lesdits ordres, et déterminant l'activation des différentes bobines électromagnétiques.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9306779A FR2706200B1 (fr) | 1993-06-07 | 1993-06-07 | Système d'actionnement pour gouverne aérodynamique et systèmes pour le pilotage d'aéronefs, comportant au moins un tel système d'actionnement. |
FR9306779 | 1993-06-07 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0628783A1 EP0628783A1 (fr) | 1994-12-14 |
EP0628783B1 true EP0628783B1 (fr) | 1998-08-12 |
EP0628783B2 EP0628783B2 (fr) | 2003-08-27 |
Family
ID=9447817
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19940401101 Expired - Lifetime EP0628783B2 (fr) | 1993-06-07 | 1994-05-18 | Système d'actionnement pour gouverne aérodynamique et systèmes pour le pilotage d'aéronefs |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0628783B2 (fr) |
DE (1) | DE69412366T3 (fr) |
ES (1) | ES2120584T5 (fr) |
FR (1) | FR2706200B1 (fr) |
NO (1) | NO307434B1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2310796B1 (fr) * | 2008-07-07 | 2014-04-16 | Saab AB | Mécanisme de volet de direction |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4143837A (en) * | 1976-06-08 | 1979-03-13 | Ab Bofors | Control device for missile or the like |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3204894A (en) * | 1962-06-29 | 1965-09-07 | Bofors Ab | Roll stabilizing system for an airborne device |
DE1298912B (de) * | 1965-12-10 | 1969-07-03 | Messerschmitt Boelkow Blohm | Schubvektorsteuerung fuer einen raketengetriebenen Flugkoerper mit mindestens einem Strahlablenker |
US4274610A (en) * | 1978-07-14 | 1981-06-23 | General Dynamics, Pomona Division | Jet tab control mechanism for thrust vector control |
DE3606835C2 (de) * | 1986-03-03 | 1997-03-27 | Diehl Gmbh & Co | Lenkeinrichtung für Projektile |
-
1993
- 1993-06-07 FR FR9306779A patent/FR2706200B1/fr not_active Expired - Fee Related
-
1994
- 1994-05-18 EP EP19940401101 patent/EP0628783B2/fr not_active Expired - Lifetime
- 1994-05-18 DE DE1994612366 patent/DE69412366T3/de not_active Expired - Lifetime
- 1994-05-18 ES ES94401101T patent/ES2120584T5/es not_active Expired - Lifetime
- 1994-06-06 NO NO942092A patent/NO307434B1/no not_active IP Right Cessation
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4143837A (en) * | 1976-06-08 | 1979-03-13 | Ab Bofors | Control device for missile or the like |
Non-Patent Citations (4)
Title |
---|
BOFORS BILL "Instructor Gunner Handbook", daté d'avril 1991, page de garde et pages 52 à 55 * |
BOFORS Supplément spécial de publicité pour la revue "International Defense Review 6/1998", pages 22 et 23 * |
Brochure "BOFORS Anti-Tank Missile System BILL Description Firing Unit", imprimé en 1987, pages 1 à 10 * |
Usage antérieur allégué d'un missile Anti-Tank BILL de la Société BOFORS (aucun document déposé) * |
Also Published As
Publication number | Publication date |
---|---|
EP0628783B2 (fr) | 2003-08-27 |
ES2120584T3 (es) | 1998-11-01 |
DE69412366T2 (de) | 1999-03-04 |
EP0628783A1 (fr) | 1994-12-14 |
NO942092L (no) | 1994-12-08 |
ES2120584T5 (es) | 2004-04-16 |
FR2706200A1 (fr) | 1994-12-16 |
NO942092D0 (no) | 1994-06-06 |
FR2706200B1 (fr) | 1995-08-11 |
NO307434B1 (no) | 2000-04-03 |
DE69412366D1 (de) | 1998-09-17 |
DE69412366T3 (de) | 2004-03-25 |
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Legal Events
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