EP0601912B1 - Systèmes de vérins à trois positions de fonctionnement stables - Google Patents
Systèmes de vérins à trois positions de fonctionnement stables Download PDFInfo
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- EP0601912B1 EP0601912B1 EP19930402891 EP93402891A EP0601912B1 EP 0601912 B1 EP0601912 B1 EP 0601912B1 EP 19930402891 EP19930402891 EP 19930402891 EP 93402891 A EP93402891 A EP 93402891A EP 0601912 B1 EP0601912 B1 EP 0601912B1
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- European Patent Office
- Prior art keywords
- pistons
- pairs
- piston
- stable
- nozzle
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- 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.)
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
- F15B11/08—Servomotor systems without provision for follow-up action; Circuits therefor with only one servomotor
- F15B11/12—Servomotor systems without provision for follow-up action; Circuits therefor with only one servomotor providing distinct intermediate positions; with step-by-step action
- F15B11/121—Servomotor systems without provision for follow-up action; Circuits therefor with only one servomotor providing distinct intermediate positions; with step-by-step action providing distinct intermediate positions
- F15B11/123—Servomotor systems without provision for follow-up action; Circuits therefor with only one servomotor providing distinct intermediate positions; with step-by-step action providing distinct intermediate positions by means of actuators with fluid-operated stops
Definitions
- the present invention relates to a three-cylinder system stable operating positions, allowing an organ or a group of organs associated with said occupying system, in turn, three stable operating positions.
- a system cylinders capable of acting on the position of an organ and comprising at least two pairs of a first and a second displaceable pistons, said pairs of pistons being housed in at least one jack body and capable of occupying, under the action of a fluid pressure from a fluid supply and exercising, either simultaneously on said first pistons of said couples, a position similar for which said organ is in a position neutral stable, the first pistons of said couples having limited and identical displacement strokes to act symmetrically on said organ, ie only on the first and second pistons of either of said couples, a position antagonistic to that of the latter, for which said member is in a deflected position stable, the corresponding second piston continuing its course of displacement until entrainement said organ in the corresponding stable deflected position.
- the object of the present invention is to remedy these disadvantages.
- the system of cylinders of the type recalled above is characterized in that said member is integral with a rotary connection mechanism, in that the two pairs of pistons act on said mechanism rotary link respectively on either side of its axis of rotation, and in that said pairs of pistons are arranged orthogonally to said axis of rotation.
- the two pairs of pistons act on the organ to be maneuvered by through a rotary link mechanism (lifter, lever, ...), integral with said member, and they are then arranged respectively on either side of the axis of rotation either parallel to each other or obliquely.
- a rotary link mechanism lifter, lever, ...), integral with said member, and they are then arranged respectively on either side of the axis of rotation either parallel to each other or obliquely.
- the first pistons of said couples have displacement strokes limited and identical to act symmetrically on said organ, when the fluid pressure is exerted on both couples, while when the pressure is on one torques, the corresponding second piston continues its displacement race until entrainement said organ in the corresponding stable deflected position. So at the position identical of said pistons of the couples corresponds the position stable neutral of said organ, and at each of the positions piston pair antagonists, one with respect to the other, corresponds to one of the two stable deviated positions of said organ.
- said first and said second pistons of each couple can be accommodated in parallel in rooms respective housed in said body and connected to said fluid supply.
- the first pistons of said pairs are then located, in relation to said body, more towards the outside of the latter than the latter pistons, guaranteeing a neutral position of the organ, perfectly stable.
- said first and said second pistons of each couple can be arranged coaxially with each other in the same chamber, formed in said body and connected to said supply fluidics.
- said second piston of each couple is concentrically housed and sliding in said first stroke piston limited, which in turn is concentrically and sliding, in said chamber of the body and the bottom is provided with an opening for movement, by the supply fluid, of said second piston.
- each pair of pistons can be arranged in a separate cylinder body, connected to said fluid supply.
- the first pistons of said couples have displacement strokes zero when the fluid pressure is exerted on each couple, and limited antagonistic races when the fluid pressure is exerted on one of said pairs, causing the simultaneous displacement and in abutment of the second opposite torque piston.
- the first two pistons of the couples are advantageously shaped as a single double piston connected said member and around which are slidably mounted and in opposition with said second pistons, the assembly formed by said double piston and said second pistons being capable of sliding in two coaxial chambers and opposite of said body, connected to said supply fluidics.
- the stable neutral position of said organ is given by a fixed position, at zero stroke, of the piston double, while each of the stable deviated positions of said member is given by a movement with limited travel double piston in one direction (and therefore displacements respective positive and negative of the first coaxial pistons formed by the double piston) causing displacement correspondent of the second opposite piston, in abutment, marking said deviated, stable position of said organ.
- said double piston may consist of a central shoulder of which two extend respectively identical rods forming said first pistons and carrying, slidingly, said second pistons. So, when the pressure is exerted on the two transverse faces end of said rods, the double piston is stationary in position, while the second pistons are in stop, and when the pressure is exerted only on one of the faces of said rods, the double piston moves in the corresponding direction by driving the second piston pushed by the shoulder in abutment, while the other second piston remains fixed.
- said double piston can consist of a median rod extended respectively by heads forming the first pistons and terminated by external annular flanges, said second pistons of the couples being slidably mounted around said respective heads, in the two respective chambers of said body.
- the cylinder system of the invention can have applications multiples from the moment it is necessary to stably mark different positions of an organ.
- the cylinder system which is controllable from the flow gas delivered by the generator, is connected, via a binding mechanism on which can act said pairs of pistons, to a movable member associated with said nozzle and capable of occupying, depending on the position of the pairs of pistons of said system, a position stable, neutral or deviated, with respect to said nozzle, likely to modify the direction of exit of said flow gaseous.
- Figure 1 shows, in section, a first embodiment of said cylinder system according to the invention in a position for which the organ to be controlled occupies a stable neutral position.
- FIG. 2 is a side view, partially in section, of said system of FIG. 1.
- Figure 3 shows, in section, said cylinder system in a position for which said organ then occupies a stable deviated position.
- Figure 4 illustrates in section a second embodiment of said cylinder system in a position for which the organ to be controlled is in a stable neutral position.
- Figure 5 is a section of said member along the line V-V of Figure 4.
- Figure 6 is a cross section of said member according to the line VI-VI of figure 5.
- Figure 7 shows in section the cylinder system of the Figure 4 in a position for which the organ occupies one of the two stable deflected positions.
- Figure 8 is a section of said member similar to that of Figure 6, but in the chosen position.
- Figure 9 illustrates a section of a third mode of realization of said jack system of the invention, in a position for which the member to be controlled, similar to that of FIG. 1, occupies a stable neutral position.
- FIG. 10 is a side view, partially in section, of said system of FIG. 9.
- FIG. 11 illustrates in section said system of FIG. 9, in a position for which said organ occupies a stable deviated position.
- FIG. 12 represents, in section, a fourth mode of realization of said cylinder system, in a position for which the organ is in stable neutral position.
- Figure 13 is a section of said system along the line XIII-XIII of figure 12.
- FIG. 14 represents, in section, said system of the Figure 12 in a position for which said member is in stable deflected position.
- Figure 15 shows, in section, the cylinder system Figure 12 applied, in this case, to another organ occupying a stable neutral position.
- Figure 16 is a section of said system along the line XVI-XVI of figure 15.
- Figure 17 shows, in section, the driving system said member in a stable deviated position.
- Figures 18 and 19 illustrate in section a fifth mode realization of said cylinder system, respectively in positions for which the organ is in position stable neutral and in stable deflected position.
- the cylinder system of the invention is intended, from a in general, to act on an organ (or a group of organs) to mark different specific positions of operation.
- the cylinder system 1 shown in Figures 1 to 3 aims, in the illustrated application, the command an aerodynamic surface such as a control surface G, around an axis A, relative to the structure S of an aircraft, such than an airplane or a missile, in order to be able to modify its path.
- an aerodynamic surface such as a control surface G
- the system 1 comprises, according to the invention, two identical pairs 2 and 3 of displaceable pistons, respectively made up of first pistons 4 and 5, and second pistons 6 and 7.
- These pairs 2 and 3 of pistons 4-6 and 5-7 are housed in a cylinder body 8 fixed to the structure said aircraft as shown schematically on the Figure 2, and they are, in this application, arranged symmetrically to each other, with respect to the axis of pivoting A of the control surface G.
- the first and second pistons of each pair 2 and 3 are arranged in parallel.
- first pistons 4 and 5 of the couples are housed, sliding, in respective identical chambers 8A of said body, while the second pistons 6 and 7 couples are housed, in a sliding way, in respective identical chambers 8B of the body, different from rooms 8A.
- the two rooms 8A and 8B of each couple 2 and 3 pistons communicate with each other through a corresponding connection 8C formed in the body and connected to a fluid supply 9.
- first pistons 4 and 5 of the pairs are located, relative to the cylinder body 8, more towards the outside thereof than the second pistons 6 and 7. Furthermore, the first pistons 4 and 5 are capable of sliding in the chambers 8A according to identical strokes c , limited by corresponding shoulders 8D arranged in the body 8 and against which are likely to be applied external annular flanges 4A and 5A provided on the pistons. As for the second pistons 6 and 7, they have identical displacement strokes c 1, greater than the displacement strokes c of the first pistons. Obviously, the sliding of the pistons, by their external edges, in their respective chambers is effected with sealing.
- an ML link mechanism such as a lifter P provides the connection between said pairs 2 and 3 and the governs G. More particularly, the lifter P is mounted in the middle around said axis A and the pairs of pistons are likely to act respectively on both sides of the spreader orthogonally to axis A. The latter is worn, as shown in Figure 2, in its central part by the structure S, while one of the ends A1 of the axis is engaged in the control surface G and that its other end A2, around which said spreader is mounted P, is engaged in a clevis 8E secured to the body.
- the fluid supply 9 is controllable by any appropriate means and that it can be hydraulic, pneumatic or issue, in the case of a missile for example, by the gas jet emitted by the propellant and which is then used through distributors controllable not shown, connected to the rooms of pistons, to act on the control surface.
- the supply 9 is controlled to send a fluid pressure into the chambers 8A and 8B of said pairs of pistons, via the conduits 8C.
- This has the effect of causing the simultaneous output of the first pistons 4 and 5 which act identically and symmetrically on the two arms of the lifter P relative to the pivot axis A.
- the sliding of the pistons 4 and 5 occurs on the whole of their strokes c until the shoulders 4A and 5A apply here against the stops 8D of the body 8.
- the first pistons 4 and 5 being in abutment, the second pistons 6 and 7 cannot continue their respective strokes but s '' also apply symmetrically against the arms of the lifter P.
- the supply 9 is controlled so, for example, to be held in the direction of the couple 2 of pistons and cut off in the direction of the couple 3 of pistons .
- This action on the fluid supply 9 breaks the stable equilibrium position of the control surface G, via the spreader P, since then, the pressure having dropped in the couple 3 of pistons, the second piston 8 of the first couple 2 can continue its movement over its entire travel c 1 by rotating the lifter P, which results in the intermediary of the axis A, by a pivoting of the control surface G by a corresponding angle ⁇ , and therefore by a change in direction of the path of the airplane or missile.
- the cylinder system 1 thus guarantees three positions marked, stable, of the rudder.
- the second embodiment of the jack system 1, illustrated in Figures 4 to 8, is substantially similar to previous, since couples 2 and 3 are made up of similar pistons 4-6, 5-7 arranged in parallel in similar chambers 8A, 8B.
- couples 2 and 3 pistons are respectively arranged in two bodies of structurally identical cylinders 8.1 and 8.2, independent one of the other. Bedrooms 8A and 8B of each couple of pistons are also connected to the fluid supply there common 9.
- the two cylinders bodies 8.1 and 8.2 are fixed to the same structure, not shown on the figures.
- the actuator system 1 can act on a member such as, in this case, a rotary distributor D.
- the two bodies 8.1 and 8.2 are arranged, in this example, oblique to each other to be able to act, by pairs 2 and 3 of pistons, on both sides of said lever L in order to rotate it about its axis A one way or the other.
- the pivoting lever L which defines the ML linking mechanism between the cylinders and the member to be controlled, is connected to the latter by a toothed sector Sd formed at its periphery and meshing with a pinion Pi provided coaxially at the end of the rotary piston Pr distributor D.
- This piston Pr is housed, in the usual way, in a fixed sleeve M and it includes, in this case, three radial passages Pp1, Pp2 and Pp3 angularly spaced each other and likely to cooperate with passages radial Pm1, Pm2 and Pm3 formed in the sleeve M.
- the rotary piston Pr of the distributor remains in a stable neutral position for which the central passages Pp1 and Pm1 of the rotary piston and the sleeve are aligned, as shown in FIGS. 5 and 6, while the passages Pp2 and Pp3 are offset from the passages Pm2 and Pm3 of the sleeve.
- this rotary distributor D is arranged in a lateral nozzle of a missile, as will be seen more particularly in the applications shown in FIGS. 12 to 17, said stable position which it occupies does not affect the trajectory of said missile .
- the second piston 7 continues to slide in the chamber 8B on a total stroke c 1 causing, on the one hand, the angular pivoting of the lever L around the axis A and, on the other hand, the simultaneous re-entry of the pistons 4 and 6 of the first couple 2 in their respective chambers 8A and 8B under lever action.
- the angular displacement of the latter causes, via the toothed sector connection Sd - pinion Pi, the rotation of a corresponding angle of the rotary piston Pr relative to the fixed sleeve M of the distributor D.
- This rotation is reflected, in this case, by aligning the passages Pp2 and Pm2 of the distributor, while the other passages Pp1 and Pp3 are closed.
- the distributor then occupies one of its two pivoted, stable positions, obtained by an antagonistic position of the pairs of pistons 2 and 3 of said system and making it possible, in this application, to deflect the gas jet passing through the lateral nozzle.
- FIG. 9 A third embodiment of said system of jacks 1, according to the invention, is illustrated in Figures 9 to 11.
- the system 1 is intended for controlling a control surface G around its axis A, through an ML binding mechanism such as the spreader P previously described.
- the actuator system 1 therefore comprises two couples 2 and 3 of pistons, arranged symmetrically to each other in a body 8, with respect to the axis A connecting the control surface to the spreader, and carried by the structure S of the aircraft and the yoke 18E of said system 1.
- the first and second pistons, respectively 14 and 16 of couple 2 and 15 and 17 of couple 3 are arranged coaxially with each other.
- the second pistons 16 and 17 of said couples are slidably housed in the first corresponding annular pistons 14 and 15, which are, at in turn, slidably mounted in bedrooms respective 18A, 18B of the body 8, which are in communication with the fluid supply 9 by pipes 18C.
- an orifice 14A, 15A is formed in the bottom 14B, 15B of each first piston 14 and 15 to set communication of the fluid pressure with the second piston 16 and 17 correspondent.
- the marking of the three positions (one neutral and two deviated), capable of being occupied by the control surface G under the action of said system of jacks 1, is carried out in a manner substantially analogous to what has been described above.
- the stable neutral position of the control surface G, illustrated in FIG. 1 is obtained by sending the fluid pressure, coming from the controllable supply 9, into the two chambers 18A, 18B of the cylinder body 8.
- a fourth embodiment of said system of jacks 1, according to the invention, is shown with reference to the figures 12 to 14 and it is intended, in an application preferential, to the nozzle orientation control side of a missile to allow its piloting.
- the actuator system 1 comprises a body 8 provided a central axial passage 28 which is terminated at its ends by two coaxial chambers 28A and 28B, and in which are housed the two pairs 2 and 3 of pistons.
- the first pistons 24 and 25 couples are advantageously formed by a single piston double 29 consisting of a central shoulder 29A and two identical rods 29B, 29C, respectively extending from one side and on the other, said shoulder capable of sliding along of the internal wall of said passage 28.
- the double piston 29 can thus be assimilated to the first pistons represented in Figures 1 and 4 and joined by their shoulders.
- the second pistons 26 and 27 of the torques are then annular to be mounted concentrically, slidingly and sealed, around said respective rods 29B and 29C of the double piston 29. It can be seen in FIG. 12 that the length of the second pistons 26,27 is identical to that of rods 29B, 29C and that the external diameter of the second pistons 26,27 is substantially identical to that of the shoulder central 29A of the double piston 29, to slide the along the inner wall of said axial passage 29A.
- the second pistons 26, 27 terminate on the side opposite to the central shoulder of the single piston, by flanges respective annulars 26A, 27A which open into the corresponding chambers 28A, 28B of the body 8 and which are, on Figure 1, in abutment against respective shoulders 28D each formed by the change in body section between the axial passage 28 and the corresponding chamber 28A, 28B.
- the transverse face 29D and 29E of each rod comes substantially flush with the corresponding rim 26A, 27A.
- the couples 2 and 3 are, in this fourth embodiment, in opposition to each other, the couple 2 corresponding to the rod 29B and at the shoulder 29A, forming the first piston 24, and to the second piston 26, and the torque 3 corresponding to the rod 29C and the shoulder 29A, then forming the first piston 25, and the second piston 27.
- coaxial chambers 28A and 28B are in communication, via 28C conduits, with the power supply fluidics 9 which may include two controllable distributors, not shown, connected respectively to the rooms and in which some of the hot gases can be transported from the propellant.
- the power supply fluidics 9 which may include two controllable distributors, not shown, connected respectively to the rooms and in which some of the hot gases can be transported from the propellant.
- FIGS. 12 and 13 there is shown diagrammatically, in FIGS. 12 and 13, one of the side nozzles T usually distributed around of said missile.
- the organ to be maneuvered, by means of the cylinders 1, is defined in this case by a skirt J substantially frustoconical and swivel mounted relative to the nozzle T around an axis A orthogonal to the geometric axis X-X of this one.
- the skirt J surrounds the end of the nozzle T for extend beyond its downstream end and allow, by its pivoting, the deflection of the gas jet leaving the nozzle.
- the ML link mechanism, connecting the tapered skirt J to the cylinder system 1, is defined by an AR shaft, parallel to axis A and crossing right through the shoulder central 29A of the double piston 29, perpendicular to this one.
- the AR shaft is then received in two grooves oblong, identical and opposite 28E, formed in the body 8 to engage, by one of its ends AR1 which emerges from the body, in a fork F provided
- the double piston 29 thus retains a state fixed, maintained by the pressure exerted identically on its transverse faces, so that the connecting shaft AR, secured to the central shoulder 29A of the double piston, also remains stationary, as does the tapered skirt J with respect to the nozzle T.
- the skirt therefore occupies a neutral position stable, given by the system of cylinders 1 whose torques 2 and 3 act, ultimately, in opposition to each other, so the displacement strokes of the first pistons are zero. Consequently, the flow of the gas jet in the nozzle T is not affected.
- the fluid pressure gas jet is maintained for example in the chamber 28B, the corresponding dispenser being open, while that it is emptied in the other room, the dispenser correspondent then being closed.
- the second piston 26 concentric with the rod 29B moves in the chamber 28A with a corresponding stroke through the central shoulder 29A of the double piston to come into abutment against the bottom 28F, while the connecting shaft AR, integral of said central shoulder, then also slides with a stroke c to come into the corresponding bottom of the oblong grooves 28E of the body 8.
- the second piston 27 concentrically surrounding the rod 29C it remains stationary, since it is in abutment by its rim annular 27A against the corresponding shoulder of the body.
- this last train by its engagement in the range F of the skirt J, the pivoting of an angle ⁇ thereof by relation to the geometric axis X-X of the nozzle T, around axis A.
- the pressure being maintained in chamber 28B, the tapered skirt J is in a deflected position stable, shown in Figure 14 and by which the jet gas leaving the nozzle T is deflected by the skirt, modifying then the trajectory of the missile.
- the pairs 2 and 3 of pistons have an antagonistic operation from one another.
- the rod 29B or first piston of the couple 2 has moved by a stroke c , negative with respect to the neutral position of FIG. 12, while the rod 29C or second piston of the couple 3 has moved d 'an identical but positive course c .
- the second piston 26 of the pair 2 has slid by the same displacement stroke, while the second piston 27 has retained the same position, its stroke being zero.
- the double piston acts as a displacement piston for said member, and the second pistons act as a stop marking the stable positions of said member.
- the cylinder system 1, illustrated in FIGS. 15 to 17, has the same structure and functioning as fourth embodiment of said system previously described. However, its application is somewhat different, although belonging to the same technical field, since it consists in controlling the position of a flap V placed in the lateral nozzle T of a missile to deflect from it the gas jet and, therefore, its trajectory.
- the flap V is mounted integral with an axis of pivot A which passes through the nozzle and to which are attached two identical and spaced flanges F1 and F2 engaging respectively, by forks F3, in the ends protruding AR1 from the AR tree, which in this case emerge from the two grooves 28E of the body 8.
- the latter is linked to axis A by a clevis 28F on either side of which are located the flanges F1, F2.
- the connecting shaft AR undergoes a translation movement, for example to the left in FIG. 17, consequently sliding on a stroke c of the double piston, causing the pivoting of the axis A by an angle ⁇ through the flanges and, therefore, the angular deflection of the flap V in the nozzle T.
- the flow of the jet gas is then modified so as to orient the missile on another trajectory.
- a fifth embodiment of the jack system 1 is illustrated with reference to FIGS. 18 and 19, to be intended, there too, when controlling the orientation of a nozzle T, but of the flexible stop type, i.e. connected to the structure S of the missile by a joint with metal sheets and with AF elastomer.
- a double piston 39 makes office of first pistons 34.35 of couples 2 and 3, and it consists of a central rod 39A, crossing the passage axial 38D of the partition, and two heads 39B, 39C, extending respectively on each side said rod and arranged in rooms 38A, 38B.
- Each head is additionally terminated by an external annular flange 39D, 39E and, around said heads of the double piston, are respectively mounted, concentrically and slidingly, the second pistons 36 and 37 of said couples.
- each second piston is in turn likely to slide from the rooms 38A and 38B respectively, and each has a flange external annular 36A, 37A ensuring lateral guidance the along the internal wall which delimits each chamber, and able to come into axial abutment against an internal shoulder 38E, 38F ending the open chambers and along which the second piston is guided.
- the piston head 39B and 39C double, forming the first piston 34 and 35, and the second piston 36 and 37 of each couple 2 and 3 are thus mounted in opposition to each other with respect to the common rod 39A double piston.
- the link mechanism ML is defined by a rigid connecting rod B, one end of which is linked, around an axis A, to that of the nozzle T, while the other end of the connecting rod B ends in a ball joint R which is mounted in the corresponding head 39C of the piston double 39 while being held in it by a ring threaded advantageously constituting the annular flange 39E of said head 39C.
- the two opposite chambers 38A, 38B of the body are connected, by 38G conduits provided therein, to a power supply fluidic 9, of identical type to that previously described, that is to say comprising controllable distributors.
- the fluid pressure from the gas jet is maintained in the chamber 38B of the body, while it is cut, by closing the corresponding distributor, in the other chamber 38A, it pushes the double piston 39 to the right in FIG. 19, by acting on the transverse face 39G of the head 39C.
- This moves relative to the second piston 37 which is held in abutment against the shoulder 38F of the chamber, and it slides with a stroke c , limited by the contact of the transverse face 39F of the opposite head 39B against the transverse partition 38C.
- the heads of the double piston have an antagonistic operation since the head 39C linked to the connecting rod B advances by a stroke c , while the other head 39B moves back from said stroke c .
- the second piston 37 concentric with the head 39C remains fixed in position, while the other second piston 36, concentric with the head 39B, slides with an identical stroke c , by the action of the annular rim 39D of the head, to abut against the central partition 38C and immobilize the double piston in position.
- the axial displacement of the double piston 39 has the effect, by through the rigid connecting rod B, to make rotate the nozzle by an angle ⁇ relative to the center of pivoting C thereof, around its articulation AF at flexible stop, as shown in figure 19.
- the nozzle T therefore occupies a stable deviated position, printed by the cylinder system.
- the X-X axis of the nozzle being deflected, the missile trajectory is changed.
- the system cylinders according to the invention allows three stable states or positions of an organ for controlling missiles, in particular, either by first and second pistons, the first pistons of the couples ensuring the stable neutral position of said member and the second pistons ensuring respectively the stable deviated positions of said organ, either by a single double piston and second pistons, the double piston ensuring the displacements, zero or limited, of said member and the second pistons marking the stable positions of said organ.
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Description
Claims (10)
- Système de vérins, susceptible d'agir sur la position d'un organe et comprenant au moins deux couples (2,3) d'un premier (4,5;14,15;24,25;34,35) et d'un second (6,7;16,17;26,27;36,37) pistons déplaçables, lesdits couples de pistons étant logés dans au moins un corps de vérin (8) et étant susceptibles d'occuper, sous l'action d'une pression fluidique issue d'une alimentation fluidique (9) et s'exerçant, soit simultanément sur lesdits premiers pistons desdits couples, une position semblable pour laquelle ledit organe est dans une position neutre stable, les premiers pistons desdits couples (2,3) ayant des courses de déplacement limitées et identiques pour agir symétriquement sur ledit organe, soit uniquement sur le premier et le second pistons de l'un ou de l'autre desdits couples, une position antagoniste de celle de ces derniers, pour laquelle ledit organe est dans une position déviée stable, le second piston correspondant poursuivant sa course de déplacement jusqu'à entraíner ledit organe dans la position déviée stable correspondante,
caractérisé en ce que ledit organe est solidaire d'un mécanisme de liaison rotatif (ML), en ce que les deux couples (2,3) de pistons agissent sur ledit mécanisme de liaison rotatif respectivement de part et d'autre de son axe de rotation (A), et en ce que lesdits couples de pistons sont disposés orthogonalement audit axe de rotation. - Système selon la revendication 1,
caractérisé en ce que lesdits couples (2,3) de pistons sont agencés en parallèle l'un par rapport à l'autre. - Système selon la revendication 1,
caractérisé en ce que lesdits couples (2,3) de pistons sont agencés en oblique l'un par rapport à l'autre. - Système selon l'une quelconque des revendications 1 à 3,
caractérisé en ce que ledit premier (4-5) et ledit second (6-7) pistons de chaque couple (2 et 3) sont logés en parallèle dans des chambres respectives (8A-8B) ménagées dans ledit corps (8) et reliées à ladite alimentation fluidique (9). - Système selon la revendication 4,
caractérisé en ce que les premiers pistons (4,5) desdits couples, à courses limitées identiques, sont situés, par rapport audit corps (8), plus vers l'extérieur de ce dernier que les seconds pistons (6-7). - Système selon l'une quelconque des revendications 1 à 3,
caractérisé en ce que ledit premier (14-15) et ledit second (16-17) pistons de chaque couple (2 et 3) sont disposés coaxialement l'un par rapport à l'autre dans une même chambre (18A-18B), ménagée dans ledit corps et reliée à ladite alimentation fluidique. - Système selon la revendication 6,
caractérisé en ce que ledit second piston (16-17) de chaque couple est logé de façon concentrique et coulissante dans ledit premier piston (14-15) à course limitée, qui est à son tour logé, de façon concentrique et coulissante, dans ladite chambre (18A-18B) du corps et dont le fond (14B-15B) est pourvu d'un orifice (14A-15A) pour le déplacement, par l'alimentation fluidique, dudit second piston. - Système selon la revendication 4 ou 6,
caractérisé en ce que chaque couple (2 et 3) de pistons est agencé dans un corps de vérin distinct (8.1-8.2) relié à ladite alimentation fluidique (9). - Système selon l'une des revendications 1 à 8,
caractérisé en ce que lesdits couples (2,3) de pistons sont structurellement identiques et sont disposés symétriquement l'un par rapport à l'autre. - Aéronef, tel que notamment un missile, comportant un générateur de gaz auquel est relié au moins une tuyère latérale susceptible de modifier la trajectoire dudit aéronef,
caractérisé en ce qu'il comprend au moins un système de vérins tel que défini sous l'une des revendications précédentes, et qui est commandable à partir de flux gazeux délivré par le générateur, ledit système de vérins (1) étant relié, par l'intermédiaire d'un mécanisme de liaison (ML) sur lequel peuvent agir lesdits couples (2 et 3) de pistons, à un organe mobile associé à ladite tuyère et susceptible d'occuper, en fonction de la position des couples de pistons dudit système, une position stable, neutre ou déviée, par rapport à ladite tuyère, susceptible de modifier la direction de sortie dudit flux gazeux.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9214837 | 1992-12-09 | ||
FR9214837A FR2698920B1 (fr) | 1992-12-09 | 1992-12-09 | Système de vérins à trois positions de fonctionnement stables. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0601912A1 EP0601912A1 (fr) | 1994-06-15 |
EP0601912B1 true EP0601912B1 (fr) | 1999-06-16 |
Family
ID=9436391
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19930402891 Expired - Lifetime EP0601912B1 (fr) | 1992-12-09 | 1993-11-30 | Systèmes de vérins à trois positions de fonctionnement stables |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0601912B1 (fr) |
DE (1) | DE69325346T2 (fr) |
FR (1) | FR2698920B1 (fr) |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1070928B (de) * | 1959-12-10 | Sienuens-'Schuckertwerke Aktiengesellschaft, Berlin und Erlangen | Betätigungseinrichtung mit Antrieb durch ein Druckmittel | |
US3152520A (en) * | 1961-04-05 | 1964-10-13 | Gen Dynamics Corp | Three position actuator |
FR1395635A (fr) * | 1964-01-27 | 1965-04-16 | Nord Aviation | Vérin à pression de fluide à trois positions stables |
FR1427446A (fr) * | 1964-03-16 | 1966-02-04 | Servo-moteur pour des transmissions à commande mécanique, etc. | |
JPS52121879A (en) * | 1976-04-05 | 1977-10-13 | Nippon Air Brake Co | Device for determining position |
US4318271A (en) * | 1980-01-14 | 1982-03-09 | Thiokol Corporation | Igniter and gas generator for rocket motor |
JP2762089B2 (ja) * | 1989-01-13 | 1998-06-04 | 曙ブレーキ工業株式会社 | 三位置位置決め油圧シリンダー |
-
1992
- 1992-12-09 FR FR9214837A patent/FR2698920B1/fr not_active Expired - Fee Related
-
1993
- 1993-11-30 EP EP19930402891 patent/EP0601912B1/fr not_active Expired - Lifetime
- 1993-11-30 DE DE1993625346 patent/DE69325346T2/de not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
FR2698920A1 (fr) | 1994-06-10 |
DE69325346T2 (de) | 1999-10-14 |
DE69325346D1 (de) | 1999-07-22 |
EP0601912A1 (fr) | 1994-06-15 |
FR2698920B1 (fr) | 1995-02-17 |
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