EP0628783B1 - Betätigungssystem für einen aerodynamischen Ruder und Luftfahrzeugführungssystem - Google Patents

Betätigungssystem für einen aerodynamischen Ruder und Luftfahrzeugführungssystem Download PDF

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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
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EP
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Prior art keywords
steering
control surfaces
aerodynamic control
airborne vehicle
positions
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Expired - Lifetime
Application number
EP94401101A
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English (en)
French (fr)
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EP0628783A1 (de
EP0628783B2 (de
Inventor
Jean-Baptiste Ansaldi
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.)
Aerospatiale Matra
Original Assignee
Airbus Group SAS
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    • 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.

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  • 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)

Claims (11)

  1. Betätigungssystem (1), durch das ein aerodynamisches Ruder (G) in die eine oder andere von zwei stabilen Wirkstellungen versetzt werden kann, wobei das aerodynamische Ruder (G) drehbar an einem festen Halter (2) angebracht ist und das System eine elektromagnetische Spule (A oder B) hat, die am festen Halter (2) angeordnet ist und das aerodynamische Ruder entgegen der Wirkung elastischer Mittel verdrehen kann, dadurch gekennzeichnet, daß es umfaßt:
    eine zusätzliche elektromagnetische Spule (B oder A), die am festen Halter (2) gegenüber der ersten elektromagnetischen Spule (A oder B) angeordnet ist;
    einen beweglichen Anker (P), der mit einem Ende (4) elastisch am festen Halter (2) angebracht ist und dessen anderes Ende (6) zwischen den Spulen (A,B) angeordnet ist und von jeder Spule angezogen werden kann, so daß die beiden stabilen Wirkstellungen bezogen auf eine neutrale Stellung einander gegenüberliegen; und
    ein bewegliches Element (7), das mit dem Anker (P) verbunden ist und an dem sich das aerodynamische Ruder (G) befindet.
  2. Betätigungssystem nach Anspruch 1,
    dadurch gekennzeichnet, daß das bewegliche Element aus einer Drehwelle (7) besteht.
  3. Betätigungssystem nach einem der Ansprüche 1 oder 2,
    dadurch gekennzeichnet, daß der bewegliche Anker (P) elastisch mittels eines Federblatts (5) am Halter angebracht ist.
  4. Betätigungssytem nach Anspruch 3,
    dadurch gekennzeichnet, daß der bewegliche Anker (P) und das Federblatt (5) in der neutralen Ruderstellung senkrecht zueinander angeordnet sind.
  5. System zur Führung eines drehmomentgeführten Luftfahrzeugs mit mindestens zwei aerodynamischen Rudern (G1, G2, G3, G4, G5, G6),
    dadurch gekennzeichnet, daß es mindestens ein Betätigungssystem (1) nach einem der Ansprüche 1 bis 4 hat.
  6. System zur Führung eines Luftfahrzeugs mit Eigendrehung mit zwei identischen aerodynamischen Ruder (G1,G2), die symmetrisch an dessen Körper angeordnet sind, gemäß Anspruch 5,
    dadurch gekennzeichnet, daß jedes aerodynamische Ruder (G1,G2) durch ein individuelles Betätigungssystem (1) betätigt wird, und dadurch, daß die aerodynamischen Ruder (G1,G2) synchron symmetrisch zum Körper des Luftfahrzeugs durch die gleichzeitige Aktivierung einer Spule jedes der getrennten Betätigungssysteme gesteuert werden.
  7. System zur Führung eines Luftfahrzeugs mit Eigendrehung mit zwei identischen aerodynamischen Rudern (G1,G2), die symmetrisch zu dessen Körper angeordnet sind, gemäß Anspruch 5,
    dadurch gekennzeichnet, daß die Ruder (G1,G2) durch ein gemeinsames Betätigungssystem (1) betätigt werden, wobei das gemeinsame Betätigungssystem (1) ein zusätzliches bewegliches Element (7) hat, das mit dem beweglichen Element (7) identisch ist, und mit dem Anker in einer zu der des beweglichen Elements symmetrischen Stellung verbunden ist, wobei sich am beweglichen Element ein aerodynamisches Ruder und am zusätzlichen beweglichen Element das andere aerodynamische Ruder befindet.
  8. System nach einem der Ansprüche 6 oder 7 zur Führung eines Luftfahrzeugs mit zwei aerodynamischen Rudern mit jeweils zwei stabilen Wirkstellungen, die symmetrisch synchron betätigt werden und das Führungssystem entsprechend der gemeinsamen stabilen Stellung, in der sie sich befinden, in eine von zwei Führungsstellungen versetzen, wobei der Modul der Führungskraft in jeder Führungsstellung gleich f ist,
    dadurch gekennzeichnet, daß dieses, um während einer Umdrehung des Luftfahrzeugs eine mittlere Führungskraft mit dem Modul F1 nach einer bestimmten Richtung (Ox) zu erhalten, nacheinander wie folgt geschaltet wird:
    in die eine Führungsstellung während einer Zeit, die einem Winkel 2S eines Kreises (C) entspricht, der die Dauer einer Umdrehung des Luftfahrzeugs darstellt; und
    in die andere Führungsstellung während der restlichen Umdrehung, wobei der Winkel 2S die Beziehung |sinS| = (π/2f).F1 erfüllt und als Winkelhalbierende die bestimmte Richtung (Ox) hat.
  9. System nach einem der Ansprüche 6 oder 7 zur Führung eines Luftfahrzeugs mit zwei aerodynamischen Rudern mit jeweils zwei stabilen Wirkstellungen, die symmetrisch synchron betätigt werden und das System entsprechend der stabilen Stellung, in der sie sich befinden, in eine von zwei Führungsstellungen versetzen, wobei der Modul der Führungskraft in jeder Führungsstellung gleich f ist, dadurch gekennzeichnet, daß dieses, um während einer Umdrehung des Luftfahrzeugs eine mittlere Führungskraft mit dem Modul F2 nach einer bestimmten Richtung (L-L) zu erzielen, nacheinander wie folgt geschaltet wird:
    in die eine Führungsstellung während zwei nicht aufeinanderfolgender Zeiträume, die jeweils den beiden Winkeln 2S1 und 2S2 eines Kreises (C) entsprechen, der die Dauer einer Umdrehung des Luftfahrzeugs darstellt; und
    in die andere Führungsstellung während der restlichen Umdrehung, wobei die Winkel S1 und S2 einander entgegengesetzt sind, als Winkelhalbierende die bestimmte Richtung (L-L) haben und die Beziehung |sinS1-sinS2| = (π/2f).F2 erfüllen.
  10. System nach Anspruch 5 zur Führung eines Luftfahrzeugs mit vier aerodynamischen Rudern (G3, G4, G5, G6), die in einheitlichem Abstand zueinander um das Luftfahrzeug herum angeordnet sind, dadurch gekennzeichnet, daß die jeweils einander entgegengesetzten Ruder identisch sind und daß jedes der Ruder durch ein individuelles Betätigungssystem (1) betätigt wird.
  11. System zur Führung eines Luftfahrzeugs nach Anspruch 10, dadurch gekennzeichnet, daß es mit einer Steuervorrichtung (26) zur Steuerung der Aktivierung der elektromagnetischen Spulen (A,B) der einzelnen individuellen Betätigungssysteme versehen ist, das umfaßt:
    ein Lenksystem (27) zur Bestimmung der Roll-, Nick- und Gierbefehle; und
    einen Rechner (28), an den die Befehle gelangen und der die Aktivierung der einzelnen elektromagnetischen Spulen bestimmt.
EP19940401101 1993-06-07 1994-05-18 Betätigungssystem für einen aerodynamischen Ruder und Luftfahrzeugführungssystem Expired - Lifetime EP0628783B2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9306779 1993-06-07
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.

Publications (3)

Publication Number Publication Date
EP0628783A1 EP0628783A1 (de) 1994-12-14
EP0628783B1 true EP0628783B1 (de) 1998-08-12
EP0628783B2 EP0628783B2 (de) 2003-08-27

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EP19940401101 Expired - Lifetime EP0628783B2 (de) 1993-06-07 1994-05-18 Betätigungssystem für einen aerodynamischen Ruder und Luftfahrzeugführungssystem

Country Status (5)

Country Link
EP (1) EP0628783B2 (de)
DE (1) DE69412366T3 (de)
ES (1) ES2120584T5 (de)
FR (1) FR2706200B1 (de)
NO (1) NO307434B1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010005350A1 (en) 2008-07-07 2010-01-14 Saab Ab Rudder machinery

Citations (1)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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

Patent Citations (1)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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
EP0628783A1 (de) 1994-12-14
NO942092L (no) 1994-12-08
ES2120584T5 (es) 2004-04-16
FR2706200B1 (fr) 1995-08-11
NO307434B1 (no) 2000-04-03
NO942092D0 (no) 1994-06-06
EP0628783B2 (de) 2003-08-27
ES2120584T3 (es) 1998-11-01
DE69412366T3 (de) 2004-03-25
DE69412366D1 (de) 1998-09-17
DE69412366T2 (de) 1999-03-04
FR2706200A1 (fr) 1994-12-16

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