ES2120584T5 - DRIVE SYSTEM FOR AERODYNAMIC TIMON AND SYSTEMS FOR AIRCRAFT PILOTING. - Google Patents

Abstract

THE PRESENT INVENTION REFERS TO A DRIVING SYSTEM (1) TO BRING AN AERODYNAMIC TIMON (G) IN ONE OR ANOTHER OF THE TWO ACTIVE, STABLE AND OPPOSITE POSITIONS ONE OF THE OTHER REGARDING A NEUTRAL POSITION. ACCORDING TO THE INVENTION, THIS DRIVING SYSTEM INCLUDES: TWO ELECTROMAGNETIC COILS (A, B) PROPOSED ON A FIXED SUPPORT (2), ONE FACING THE OTHER; . A MOBILE PALETTE (P) ONE OF WHOSE EXTREME (4) IS ELASTICALLY FIXED TO SUCH FIXED SUPPORT (2), AND THE OTHER END (6) IS AVAILABLE BETWEEN SUCH COILS (A, B) AND IS SUSPECTABLE TO BE ATTRACTED FOR EACH OF SUCH COILS; Y . A MOBILE ELEMENT (7) SOLIDARY OF SUCH PALETTE (P) AND WHICH CARRIED SAID TIMON AERODYNAMIC (G). - AIRCRAFT PILOTING.

Description

Drive system for aerodynamic rudder and systems for aircraft piloting.

Descriptive memory

The present invention relates to a system of drive for aerodynamic helm, as well as systems for piloting of piloted aircraft on a par by rudders aerodynamics, which involve at least one such system of drive

It is known that aircraft piloting, in particularly guided bombs or missiles, by means of rudders aerodynamic means, to be precise, that the systems of These aerodynamic rudders have some well defined properties. The reliability of these systems of drive, in particular, must be extremely high, in particularly when they are intended for military applications where any inaccuracy in piloting could have irremediable consequences To this end, said systems of drive must, in particular, achieve performance by torque and very high response times.

The present invention is intended to facilitate a simple, low cost drive system and a very reduced aging, which is capable of satisfying requirements mentioned above.

To this end, according to the invention, the system of drive to bring an aerodynamic rudder to one or the other of two active, stable and opposite positions of each other in relation to a neutral position, said rudder being mounted rotational aerodynamic on a fixed support, with said drive system two electromagnetic coils arranged in said fixed support, the one in relation to the other to make turn said aerodynamic rudder in opposition to media action elastic, being remarkable that said drive system It also includes:

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a mobile pallet, one of whose ends is elastically fixed to said support fixed, by intermediation of a spring sheet, so that, in neutral position of the rudder, said movable vane and said foil of spring are orthogonal, and whose other end is arranged between said coils and is likely to be attracted to each of said coils; Y

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a mobile element supportive of said paddle and bearing said helm aerodynamic.

Thus, thanks to the invention, the switching of the aerodynamic helm of one of its stable active positions to the another is obtained simply by activating said coils electromagnetic, which causes the blade to move mobile that drives the switching of said aerodynamic rudder.

It will be noted that the patent GB-A-1 057 863 whose exposure forms the base of the preamble of independent claim 1, describes a drive system to bring a helm aerodynamic at one or the other of two active positions and stable, said aerodynamic rudder being mounted rotatably on a fixed support that said system involves a single coil electromagnetic associated to said helm, arranged in said support fixed and acting directly on said rudder (without interposition of paddle), to make it rotate in opposition to the action of a spring, so that said rudder can adopt (exclusively, without neutral position) one or the other of two extreme positions.

It will be noted that the elements that constitute said drive system according to the present invention are little Numerous and low cost. Therefore, on the one hand, the price of manufacture of the drive system according to the invention is low and, on the other hand, the volume of the drive system is extremely small, which is very advantageous for your use in small aircraft, for example light missiles

Advantageously, said mobile element is constituted by a rotating tree.

It will also be noted that, thanks to the use of said spring sheet and said electromagnetic coils, said drive system according to the invention has some high performance at the same time and in response times.

The present invention also relates to a system for piloting an aircraft piloted at least at par by two aerodynamic rudders, such a system of piloting at least one drive system as described previously.

The invention relates more particularly to a pilot system of an aircraft in self-rotation that it has two aerodynamic rudders arranged symmetrically with relation to the body of the latter. This pilot system can especially to be used in multi-mission and anti-aircraft missiles lightweight, characterized by high speed and mass reduced after launch. An effective pilot only You need small-sized aerodynamic rudders.

Each of said aerodynamic rudders can be operated by an individual drive system according to the invention and said aerodynamic rudders are directed, so synchronously, symmetrically in relation to the body of the aircraft, by the simultaneous activation of a coil of each of said individual drive systems.

As a variant, said rudders are operated by a common drive system, said system comprising common drive a supplementary mobile element identical to said mobile and solidarity element with said vane in one position symmetrical in relation to that of said mobile element, carrying said moving element one of such aerodynamic rudders and carrying said supplementary mobile element the other of the aforementioned rudders aerodynamic

This pilot system is particularly appropriate for very small aircraft, in particular minimisiles, whose reduced volume does not allow the provision of several drive systems, and whose aerodynamic rudders of restricted surface are subject to forces relatively weak and can thus be triggered by a single drive system

Pilot systems, with one or two systems of actuation, as described above, and that they have two aerodynamic rudders with two stable positions each one, symmetrically driven, synchronously, are liable to adopt one or the other of two positions of piloting, depending on the common stable position in which they find said aerodynamic rudders.

According to the invention, when the force module of pilot is equal to f in each of these two positions of piloting, such a piloting system is notable because, to obtain in a turn of rotation of the aircraft an average force of F1 module pilot driven according to a defined direction, is successively switched:

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in one of those pilot positions for a time corresponding to a 2S angle of a circle that represents the duration of a rotation turn of the aircraft; Y

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in the other position of piloting during the remainder of said rotation lap, checking the angle 2S the relation | sinS | = (\ pi / 2f) .F1 and behaving as bisector said defined address.

Thus, the driving force is easily obtained desired and this simply by putting the pilot system, during respective times more or less long, in one or the other of said pilot positions. For example, to obtain a medium strength of maximum F1 pilot value 2f / \ pi, just put said system, during a half-turn of rotation, in one of said pilot positions, and during the other half-turn of rotation, in the other pilot position, so that S = \ pi / 2.

However, the preceding switching mode It presents an inconvenience when looking for a driving force very weak. Indeed, the drive system that allows the switching presents a time threshold corresponding to its time of response. Therefore, it is impossible to obtain a 2S angle corresponding to a duration less than this time threshold.

Advantageously, in order to remedy this inconvenient and to obtain, in a rotation turn of the aircraft, an average pilot force of module F2 directed according to a defined direction, said pilot system is successively commutated:

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in one of those pilot positions for two non-successive periods that correspond respectively to two angles 2S1 and 2S2 of a circle which represents the duration of a rotation lap of the aircraft; Y

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in the other position of piloting during the remainder of said rotation turn, being said opposite angles S1 and S2, behaving as the same bisector said defined address and verifying the relationship | sinS1-sinS2 | = (\ pi / 2f) .F2.

Thus, it is possible to obtain pilot forces module as weak as desired, minimizing the difference between angles S1 and S2. This pilot system allows, by consequently get both very weak driving forces as an important pilot forces and is particularly Well suited to multi-mission missiles.

The present invention also relates to a piloting system of an aircraft with four rudders aerodynamics arranged around said aircraft so evenly spaced.

According to the invention, one such pilot system, which is particularly adapted to a large missile air-to-ground or to a glider pump with maneuver limited is notable because the increasingly opposite rudders are identical and because each of them is powered by a system individually operated according to the invention.

Advantageously, said pilot system is equipped with a drive device designed to direct the activation of the electromagnetic coils of the different individual drive systems, which include:

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a guidance system that determines the orders of balancing, nodding and winking; Y

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a computer, which receives these orders and determines the activation of the Different electromagnetic coils.

It will be deduced from the figures in the attached drawing how the invention can be realized. In these figures, references identical designate similar elements.

Figure 1 is a partial perspective view of a drive system according to the invention.

Figure 2 shows, schematically, the pilot system of an aircraft, which has two rudders aerodynamics powered by two drive systems separated.

Figure 3 shows, schematically, the pilot system of an aircraft with two rudders aerodynamics powered by the same drive system.

Figure 4 illustrates the generation of a force side of piloting, according to a first principle of piloting.

Figure 5 illustrates the generation of a force side of piloting, according to a second principle of piloting.

Figure 6 is the synoptic scheme of the system of piloting an aircraft with four rudders aerodynamic

It will be noted that, in Figures 1, 2, 3 and 6, the rudders are schematically represented in the form of pallets

The drive system 1, according to the invention and represented in figure 1, it is intended to operate a rudder aerodynamic G represented partially and schematically in this figure.

According to the invention, said system of drive 1 has two identical electromagnetic coils A and B arranged in relation to each other on a fixed support 2, may be fixed on the body of an aircraft (no represented). Said coils A and B are activatable independently, by means of a control system (no represented).

Said drive system 1 involves also a mobile vane P fixed elastically by one of its ends 4 on the fixed support 2, by means of a spring sheet 5 integral at the same time with said end 4 and said support 2. To this effect, said spring sheet 5 is embedded at its ends opposite, at the same time on said fixed support 2 and at the end 4 of the vane P. The other (free) end 6 of the vane P is disposed between said coils A and B. When coils A and B do not are activated, the mobile vane P is in a medium plane pi, partially represented in mixed lines in Figure 1, equidistant from said coils A and B, parallel to the internal faces respective 8 and 9 of the latter and orthogonal with the sheet of spring 5.

The activation of one or the other of said coils causes the displacement of the vane P, by rotation around an X-X axis defined by the intersection  of the middle plane π and of the spring sheet 5, so that the free end 6 of the vane P comes into contact with the coil which is activated and remains in this position while this coil is activated

On the other hand, a mobile element, in this case a rotary shaft 7 is laterally connected with said vane P at the level of end 4 of the latter, coaxially with the axis X-X

Said rotating shaft 7 carries the helm aerodynamic G arranged parallel to the vane P and represented in continuous strokes in its neutral position in figure 1.

Consequently, said helm G is integral with the displacement of the free end 6 of the vane P between the coils A and B.

Thus, according to the invention, said aerodynamic rudder G can be taken to one of the two active, stable and opposite 10 and 11, partially represented by strokes discontinuous in figure 1, namely:

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in position active stable 10 that forms an angle + \ Theta in relation to the neutral position, when coil A is activated and that the end free 6 of the pallet P is in contact with it; Y

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in position active stable 11 that forms an angle - \ Theta in relation to the neutral position, when coil B is activated and that the end Free 6 is in contact with the latter.

The aerodynamic rudder switching G of one of their active positions stable to each other is then obtained by the inversion of the activation of the coils.

The drive system 1 according to the invention it can be used in a pilot system 12 of an aircraft 14 in self-rotation around its Y-Y axis, whose body 13 is shown in figure 2, partially and in shape schematic Said aircraft 14 is piloted in tandem by two identical G1 and G2 aerodynamic rudders, arranged so symmetric in relation to the Y-Y axis. Each one of said aerodynamic rudders G1 and G2 is driven by a system of drive 1 individually and synchronously, so that these rudders are always in the same pilot plane. For this purpose, the coils A of each of the two systems of Drive 1 are activated at the same time. The same thing happens with the coils B.

Thus, the pilot system 12 can take two different pilot positions, namely:

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a first position of pilotage, when the vanes P are in contact with the coils A and then the aerodynamic rudders G1 and G2 meet respectively in positions 15 and 16 partially represented in dashed lines in figure 2 and forming a angle + \ Theta with the middle position represented; Y

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a second position of pilotage, when the vanes P are in contact with the coils B and then the aerodynamic rudders G1 and G2 meet respectively in positions 17 and 18 partially represented in dashed lines and that forming an angle - \ Theta with the middle position represented.

Depending on whether the pilot system 12 is in one or the other of these pilot positions, it generates two pilot forces of the same module, directed according to the same Z-Z address (perpendicular to directions X-X and Y-Y) but of meaning opposite.

In another embodiment, as is represented in figure 3, the pilot system 20 involves a drive system only 1 to operate both rudders aerodynamic G1 and G2.

For this purpose, the drive system 1 it has two opposite trees 7, arranged laterally in the vane P, on both sides of the spring sheet 5, according to the X-X direction, and which respectively carry said aerodynamic rudders G1 and G2. Like the pilot system 12 of Figure 2, the pilot system 20 can adopt two different piloting positions:

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a first position of pilotage, when the vane P is in contact with the coil A and that the aerodynamic rudders G1 and G2 are respectively in positions 15 and 16; Y

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a second position of pilotage, when the vane P is in contact with the coil B and that the aerodynamic rudders G1 and G2 are then found respectively in positions 17 and 18.

The piloting of the aircraft 14 in self-rotation is performs in the same way for the two pilot systems 12 and 20 described above. For this purpose, in a round of rotation, the pilot system 12 or 20 is successively switched in its two pilot positions, thus spawning in every moment a steering force of module f, steering Z-Z, and whose meaning depends, at a given time, on the pilot position used at this time.

According to a first pilot principle, such as is schematically illustrated in figure 4, the system of pilot 12 or 20 is held in a first pilot position for a time corresponding to an angle 2S of a circle C, which represents the duration of a rotation lap of the aircraft, then it is switched to the other pilot position during the rest of the time of said rotation lap.

Said first pilot position generates, in successive moments, in circle C, along the arc of circle defined by angle 2S, radial forces of equal module f (such as those represented at points 21), while that the second pilot position generates pilot forces of the same module f but in the opposite direction (such as represented in points 22).

However, as the aircraft revolves over itself same, these opposing forces engendered during the rotation present additional effects on a lap so that, for a rotation turn, an average force of F1 pilot of module F1 = (2 / \ pi) .f. | sinS | directed according to Ox bisector of angle 2S.

It will be noted, however, that this force of F1 piloting always remains superior to a minimum force. In In effect, the drive system has a temporary threshold corresponding to your response time that depends in particular of the stiffness of the spring sheet 5, of the strength and of the inductance of coils A and B and the inertia of the system drive Therefore, the angle S is always greater than an angle Smin, such as Smin = \ Phi \ tau / 2 where \ Phi represents the rotation speed of the aircraft and ta the time threshold of the drive system, and therefore the driving force F1 is always superior to a minimum force Fmin = (2 / \ pi) .f. | Sin (Smin) |.

According to a second pilot principle, such as the schematically illustrated in figure 5, the system of pilot 12 or 20 is switched in the same pilot position for two times corresponding respectively to two angles 2S1 and 2S2 in circle C and defined so that these angles 2S1 and 2S2 are opposite and have the same bisector L-L. The rest of the rotation, corresponding with two identical α and β angles, the pilot system It is switched in the other pilot position.

\underdots{f}

.|sinS1-sinS

\hbox{\underdot{2}|,}

dirigida a lo largo de la bisectriz común L-L de los ángulos 2S1 y 2S2.The pilot forces generated at angles 2S1 and 2S2, in an identical pilot position, but for two opposite positions of the aircraft around its YY axis, have opposite effects. The same occurs with the effects produced at the angles α and β. However, since said angles? And? Are identical, the effects produced along their common bisector (not shown) are annulled, which does not occur with angles 2S1 and 2S2 (when they are different, as represented ). Thus, a mean driving force F2, which only depends on the angles S1 and S2, of the module F2 = (2 / \ pi) is obtained in a rotation rotation of the aircraft.

 \ underdots {f} 

. | sinS1-sinS

 \ hbox {\ underdot {2} |,} 

directed along the common bisector LL of angles 2S1 and 2S2.

This second pilot principle is particularly suitable for obtaining F2 pilot forces of restricted module, since it is possible to make the difference | sinS1-sinS2 | become as weak as you you want, using maximum angles S1 and S2 of each other.

The drive system 1 according to the invention it can also be used in a pilot system 25, such as schematically represented in figure 6, for pilot a relatively heavy aircraft, for example a missile large air-ground or a glider pump with limited maneuver, by means of four aerodynamic rudders G3, G4, G5 and G6.

These aerodynamic rudders G3, G4, G5 and G6, each operated by an individual drive system 1, are arranged around the aircraft (not shown), being 90º apart, so that, on the one hand aerodynamic rudders G3 and G5 that are identical and, on the other hand, the aerodynamic rudders G4 and G6 that are identical, are symmetrically arranged in relation to the axis of said aircraft.

The piloting of said aircraft is carried out modifying the activation of electromagnetic coils A and B of the different drive systems 1 and therefore the position of the corresponding aerodynamic rudders.

For this purpose, said pilot system 25 is equipped with an on-board drive device 26, which behaves:

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a guidance system 27 which determines the balancing, nodding and yaw orders; Y

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a computer 28 that receives these orders through a link 29, which determines the activation of electromagnetic coils A and B of the systems of drive 1 associated to each of the aerodynamic rudders G3, G4, G5 and G6 and that drive said coils A and B by means of the links 30 to 33.

Claims (9)

1. Drive system (1) for bringing an aerodynamic rudder (G) to one or the other of the two active, stable and opposite positions of one another in relation to a neutral position, said aerodynamic rudder being mounted (G) on a fixed support (2), said actuation system (1) comprising two electromagnetic coils (A, B) arranged in said fixed support (2), one in relation to the other, to rotate said aerodynamic rudder in opposition to the action of elastic means, characterized in that said drive system (1) also includes:

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a mobile pallet (P) one (4) of whose ends is elastically fixed to said support fixed (2), by intermediation of a spring sheet (5), so that, in neutral position of the helm, said mobile vane (P) and said spring sheet (5) are orthogonal, and whose other end (6) is disposed between said coils (A, B) and is likely to be attracted for each of said coils; Y

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 a mobile element (7) in solidarity with said palette (P) and bearing said      aerodynamic rudder (G).

2. Drive system according to claim 1, characterized in that said mobile element is constituted by a rotating shaft (7). 3. System for piloting an aircraft piloted on par by at least two aerodynamic rudders (G1, G2, G3, G4, G5, G6), characterized in that it comprises at least one drive system (1) according to one of claims 1 and 2. 4. System for piloting an aircraft in self-rotation, which involves two identical aerodynamic rudders (G1, G2) symmetrically arranged in relation to the body of this last, according to claim 3, characterized in that each of said aerodynamic rudders (G1, G2) is driven by an individual drive system (1) and because said aerodynamic rudders (G1, G2) are synchronously driven symmetrically in relation to the body of the aircraft, by the simultaneous activation of a coil of each of said individual drive systems. 5. System for piloting an aircraft in self-rotation, which involves two identical aerodynamic rudders (G1, G2) symmetrically arranged in relation to its body last, according to claim 3, characterized in that said rudders (G1, G2) are driven by a common drive system (1) with said common drive system (1) comprising a supplementary mobile element (7) identical to said mobile element (7) and integral with said vane in a symmetrical position relative to that of said mobile element, said mobile element carrying one of said aerodynamic rudders and said supplementary mobile element carrying the other of said aerodynamic rudders. 6. System according to one of claims 4 or 5, for the piloting of an aircraft, which involves two rudders aerodynamic, with two stable active positions each, actuated symmetrically, synchronously and putting, in function of the common stable position in which they are found, said pilot system in one of two pilot positions, the modulus of the driving force being equal to f in each of said pilot positions, characterized in that, in order to obtain in a rotation rotation of the aircraft an average pilot force of module F1 directed in a defined direction (Ox), it is successively switched:

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in one of those pilot positions for a time corresponding to a 2S angle of a circle (C) representing the duration of a turn of rotation of the aircraft; Y

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in the other position of piloting during the remainder of said rotation turn, the angle 2S that verifies the relationship | sinS | = (\ pi / 2f) .F1 and what it means as a bisector said defined direction (Ox).

7. System according to one of claims 4 or 5, for the piloting of an aircraft, which involves two rudders aerodynamics with two stable active positions each, actuated symmetrically, synchronously and that puts, in function of the stable position in which they are, said system in one of the two pilot positions, the module being of the piloting force equal to f in each of said positions of piloting, characterized in that, in order to obtain an average pilot force of module F2 directed in a defined direction (LL) in a rotation rotation of the aircraft, it is successively switched:

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in one of those pilot positions for two non-successive periods corresponding respectively to two angles 2S1 and 2S2 of a circle (C) representing the duration of a rotation turn of The aircraft; Y

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in the other position of piloting during the remainder of said rotation turn, being said opposite angles S1 and S2, behaving as same bisector said defined address (L-L) and verifying the relationship | sinS1-sinS2 | = (\ pi / 2f) .F2.

8. System according to claim 3, for piloting an aircraft, which has four aerodynamic rudders (G3, G4, G5, G6) arranged evenly spaced around said aircraft, characterized in that the increasingly opposite rudders are identical and that each of said rudders is driven by an individual drive system (1). 9. System for piloting an aircraft according to claim 8, characterized in that it is provided with a drive device (26) intended to drive the activation of the electromagnetic coils (A, B) of the different individual drive systems, which includes:

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a guidance system (27), which determines the balancing, nodding and yaw orders; Y

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a computer (28), that receives these orders and determines the activation of Different electromagnetic coils.