EP0132199B1 - Hydraulischer Verteiler für die Steuerung eines Luftfahzeuges - Google Patents
Hydraulischer Verteiler für die Steuerung eines Luftfahzeuges Download PDFInfo
- Publication number
- EP0132199B1 EP0132199B1 EP84401466A EP84401466A EP0132199B1 EP 0132199 B1 EP0132199 B1 EP 0132199B1 EP 84401466 A EP84401466 A EP 84401466A EP 84401466 A EP84401466 A EP 84401466A EP 0132199 B1 EP0132199 B1 EP 0132199B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- plug
- sleeve
- liner
- aircraft
- lever
- 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
Links
- 239000012530 fluid Substances 0.000 claims abstract description 13
- 238000007789 sealing Methods 0.000 claims description 5
- 101001017827 Mus musculus Leucine-rich repeat flightless-interacting protein 1 Proteins 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000000295 complement effect Effects 0.000 description 1
- 230000000135 prohibitive effect Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F15B9/00—Servomotors with follow-up action, e.g. obtained by feed-back control, i.e. in which the position of the actuated member conforms with that of the controlling member
- F15B9/02—Servomotors with follow-up action, e.g. obtained by feed-back control, i.e. in which the position of the actuated member conforms with that of the controlling member with servomotors of the reciprocatable or oscillatable type
- F15B9/08—Servomotors with follow-up action, e.g. obtained by feed-back control, i.e. in which the position of the actuated member conforms with that of the controlling member with servomotors of the reciprocatable or oscillatable type controlled by valves affecting the fluid feed or the fluid outlet of the servomotor
- F15B9/10—Servomotors with follow-up action, e.g. obtained by feed-back control, i.e. in which the position of the actuated member conforms with that of the controlling member with servomotors of the reciprocatable or oscillatable type controlled by valves affecting the fluid feed or the fluid outlet of the servomotor in which the controlling element and the servomotor each controls a separate member, these members influencing different fluid passages or the same passage
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/8593—Systems
- Y10T137/86493—Multi-way valve unit
- Y10T137/86574—Supply and exhaust
- Y10T137/86638—Rotary valve
- Y10T137/86646—Plug type
Definitions
- the present invention relates to a hydraulic distributor intended to equip an aircraft control, in particular the flaps or "spoilers" of the wings of an aircraft which are used to control the turns thereof, or as air brakes during of the landing.
- a device is thus produced with "position copying", which requires, when the distributor is not integrated into the actuator, an extremely bulky and complicated system of links and intermediate articulation axes to transmit the order to feedback of the servo position, after a pilot control maneuver.
- a four-way servo-control distributor performing a function of this type and comprising a central plug and a rotor surrounding the plug, but the realization of which is complicated and bulky.
- a body is provided in three parts, two end parts and an intermediate ring, the plug and the rotor being arranged concentrically with respect to each other at the level of the intermediate ring. and extending respectively through one of the end parts of the body, by two shafts which are therefore arranged on either side of the body.
- the object of the invention is to provide a servo-control with a position feedback device which does not present a prohibitive bulk, and the production of which is simplified compared to known systems.
- the invention provides for using a double distributor comparable to that described in patent FR-A 2 460 435 (EP-A 0 021 977).
- This front four-way hydraulic distributor has two use chambers and is equipped with a safety device guaranteeing the continuity of the normal operation of the distributor, in the event of seizure or blockage of its central control valve.
- This distributor therefore includes a central plug rotatably mounted in a fixed fur housed in a body, and connected at one end to a control device, and an annular jacket interposed rotatably between the plug and the fur, bores for the pressure entry and the outlet of a hydraulic fluid being drilled in the fur and in the jacket, as well as passages on the periphery of the plug to ensure the circulation of the hydraulic fluid from one bore to the other of the fur passing through those of the shirt when the bushel turns.
- one end of the sleeve projects outside the body on the side of the latter where said end of the plug already projects and it is integral in rotation with a lateral lever, transverse to the axis of the plug. and associated with a summing device constituting a feedback control, capable of gradually bringing back, via the aforementioned lever, the liner to its initial angular position relative to the plug, after rotation of the latter by a predetermined angle.
- the invention transforms the safety jacket of the distributor of the aforementioned patent FR-A2460435 into an element fulfilling a completely different function, since this jacket then constitutes the terminal element of a position feedback device.
- this solution avoids the implementation of bulky and complicated systems corresponding to rods and joints, to replace them with a single distributor that is compact and simple to produce.
- the device shown diagrammatically in FIG. 1 is a hydraulic servo-control of a part 1 articulated on a fixed axis 2, and which can for example be a flap or "spoiler" of an aircraft wing.
- This servo-control comprises a linkage 3 driven by an electric motor not shown, and which can control the rotation of the central plug 4 of a hydraulic distributor 5 connected to a jack 6 whose annular chamber is permanently under pressure, and whose the rod is articulated on the pivoting flap 1.
- the control of the distributor 5 can also be obtained mechanically, by a linkage 7, in a known manner.
- the linkages 3 and 7 form a "summator" 8 of a control loop 9 connecting the shutter 1 to the distributor 5.
- the control loop 9 including the summing device 8 constitutes a “position copying” device after an order from the pilot who has triggered a rotation of the plug 4 by a determined angle and the subsequent tilting of the flap 1.
- This copying device automatically returns a sleeve 11 coaxial with the plug 4 in the distributor 5 to its initial angular position relative to the plug 4, in order to stabilize the flap 1 in its new position.
- the distributor according to the invention shown in detail in Figures 2 to 4, has a structure derived from that of the distributor of the above-mentioned French patent 2,460,435.
- This hydraulic distributor 35 comprises a central plug 12 rotatably mounted in a fixed fur 13 coaxial with this plug, and an annular jacket 14 also coaxial with the plug 12, interposed rotatably between the latter and the fur 13. The latter is secured to a body 15 with interposition of a tubular sealing part 16.
- the plug 12 has on its periphery two recesses 29a, 29b, diametrically opposite and which extend over equal angular sectors.
- the bores 19, 21, 22 open outwardly into an annular gap 10 which communicates with a pipe 30 (FIG. 3) for supplying pressurized hydraulic fluid, this fluid being evacuated from the distributor by an outlet 31 formed in the body 15.
- the rotary jacket 14 protrudes over a determined length 1 outside the body 15 on the same side as the plug, and its external protruding part 14a is rotationally integral with a lateral lever 32 ( Figures 3 and 4).
- the lever 32 has a toothed end sector 33 engaged with a toothed wheel 34 of a summing device such as 8 ( Figure 1), intended to ensure the copying of the position angle of the plug 12 by the sleeve 14, and this by means of the operating lever 32.
- the distributor 35 is fixed on a support 36 carrying an axis 37 on which a lever 38 is articulated, on which is in turn articulated the arm 18 for controlling the rotation of the plug 12.
- a lever 38 is also articulated an arm 41 capable of being driven in translation by a motor member 42, thanks to the invention. All these various elements can be arranged on the same support face 36.
- the rotary jacket 14 is mounted on a ball bearing 40 and on needle bearings 43, the latter being interposed between the jacket 14 and the fur 13.
- the bearing 40 is interposed between the liner 14 and a tubular part 44 fixed to the body 15 by bolts 45.
- Another ball bearing 46 is interposed between the liner 14, the plug 12 and an annular shoulder 47 of the latter.
- This tubular part 51 is integral in rotation with the plug 12 and the arm 18, by means of teeth or complementary fingers 51 a.
- the part 51 could be integral in rotation with the jacket 14.
- Hydraulic fluid under pressure enters the distributor 35 through the bores 19, 23, and 26.
- the valve 12 is oriented so as to stop the fluid in the recesses 29a, 29b, which do not communicate not with the openings 27, 28. If now the pilot of the aircraft gives the distributor 35, by means of the control members 42, 41, 38, 18 an order which drives the plug 12 in rotation in the anti-direction AR schedule (arrows in Figure 2), the passages 29a, 29b establish communication between the bores 19, 23, 26 on the one hand, and 27, 25, 21 on the other hand, so that the hydraulic fluid flows towards its first use through the bores 21, following the path indicated by the arrows in solid lines in FIG. 2.
- the flap or “spoiler” of the aircraft tilts at an angle which increases as long as the order of rotation of the plug 12 is maintained and the fluid can flow from the bores 19 to the bores 21
- the position feedback device comprising the adder triggers the rotation of the toothed wheel 34 in the direction which makes the lever 32 and consequently the jacket 14 rotate so that this the latter rotates in the same direction as the plug 12, the movement of which it thus "follows", with a certain time lag.
- the invention is not limited to the embodiment described and may include variant embodiments.
- the fact of copying the angular position of the plug 12 by securing the liner 14 with a lever such as 32 of the servo-control summator considerably reduces the size and complexity of the device which would be necessary if the 'we had adopted a more classic solution.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Servomotors (AREA)
- Multiple-Way Valves (AREA)
- Fluid-Pressure Circuits (AREA)
Claims (3)
Servosteuerungsvorrichtung für ein Luftfahrzeug, dadurch gekennzeichnet, dass diese einen auf einem Träger (36) befestigten Verteiler (25) nach einem der Ansprüche 1 und 2 aufweist, wobei die Verteilernabe (12) mit einem auf einem Hebel (38) gelenkig angeordneten Arm (18) fest verbunden ist, wobei dieser Hebel auf einem Träger (36) gelenkig angeordnet ist und darauf ein mit den Motorteilen verbundenes Teil (41) gelenkig angeordnet ist, während der mit einem Ende des Verteilermantels (14) fest verbundene Hebel (32) an seinem entgegengesetzten Ende einen mit einem gezahnten Bereich (34) einer Summiervorrichtung (8) in Eingriff stehenden gezahnten Abschnitt (33) aufweist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8311714 | 1983-07-13 | ||
FR8311714A FR2549167B1 (fr) | 1983-07-13 | 1983-07-13 | Distributeur hydraulique destine a equiper une commande d'aeronef |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0132199A1 EP0132199A1 (de) | 1985-01-23 |
EP0132199B1 true EP0132199B1 (de) | 1988-02-17 |
Family
ID=9290819
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP84401466A Expired EP0132199B1 (de) | 1983-07-13 | 1984-07-10 | Hydraulischer Verteiler für die Steuerung eines Luftfahzeuges |
Country Status (5)
Country | Link |
---|---|
US (1) | US4905572A (de) |
EP (1) | EP0132199B1 (de) |
JP (1) | JPH0629601B2 (de) |
DE (1) | DE3469380D1 (de) |
FR (1) | FR2549167B1 (de) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB9217865D0 (en) | 1992-08-21 | 1992-10-07 | Unilever Plc | Monitoring method |
GB9217808D0 (en) | 1992-08-21 | 1992-10-07 | Unilever Plc | Advisory method |
GB9217864D0 (en) | 1992-08-21 | 1992-10-07 | Unilever Plc | Monitoring method |
US7141212B2 (en) | 1993-11-12 | 2006-11-28 | Inverness Medical Switzerland Gmbh | Reading devices and assay devices for use therewith |
DE19536553A1 (de) * | 1995-09-30 | 1997-04-03 | Eckehart Schulze | Elektrohydraulische Steuerventilanordnung |
FR2747174B1 (fr) * | 1996-04-03 | 1998-07-10 | Samm Societe D Applic Des Mach | Distributeur hydraulique pour servocommandes d'aeronefs, notamment helicopteres |
DE69626016T2 (de) | 1996-09-27 | 2004-01-08 | Inverness Medical Switzerland Gmbh | Test-Kit und Vorrichtungen |
DE19733031C2 (de) * | 1997-07-31 | 2000-10-26 | Mercedes Benz Lenkungen Gmbh | Servoventil |
US11998266B2 (en) | 2009-10-12 | 2024-06-04 | Otsuka Medical Devices Co., Ltd | Intravascular energy delivery |
CN103759043B (zh) * | 2014-01-02 | 2016-08-17 | 武汉船用机械有限责任公司 | 一种转阀 |
CZ2014591A3 (cs) * | 2014-08-29 | 2015-09-02 | Peveko, Spol. S R.O. | Vícecestný ventil pro řízení toku kapalných nebo plynných médií |
US11168578B2 (en) * | 2018-09-11 | 2021-11-09 | Pratt & Whitney Canada Corp. | System for adjusting a variable position vane in an aircraft engine |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1729173A (en) * | 1924-12-31 | 1929-09-24 | Cie Electromecanique | Servo-motor-controlled unclutching device for internal-combustion engines |
GB630092A (en) * | 1941-12-27 | 1949-10-05 | Sperry Gyroscope Co Inc | Improvements in or relating to positional control systems |
US2431759A (en) * | 1944-03-30 | 1947-12-02 | Westinghouse Air Brake Co | Stabilizer for pressure fluid servomotors |
US2490509A (en) * | 1945-01-26 | 1949-12-06 | Hydraulic Engineering Co Inc | Rotary follow valve |
US2728404A (en) * | 1951-04-16 | 1955-12-27 | Adolphe C Peterson | Power steering using hydraulic motors |
US3254674A (en) * | 1964-08-04 | 1966-06-07 | Airoyal Engineering Company | Rotary servo valve |
GB1119991A (en) * | 1966-02-10 | 1968-07-17 | Airoyal Engineering Company | Rotary servo valve |
JPS5260598U (de) * | 1975-10-31 | 1977-05-02 | ||
FR2460435A1 (fr) * | 1979-07-03 | 1981-01-23 | Applic Mach Motrices | Distributeur hydraulique, destine notamment a equiper des servo-commandes d'avions et d'helicopteres |
JPS5736802U (de) * | 1981-04-30 | 1982-02-26 |
-
1983
- 1983-07-13 FR FR8311714A patent/FR2549167B1/fr not_active Expired
-
1984
- 1984-07-10 EP EP84401466A patent/EP0132199B1/de not_active Expired
- 1984-07-10 DE DE8484401466T patent/DE3469380D1/de not_active Expired
- 1984-07-13 JP JP59145891A patent/JPH0629601B2/ja not_active Expired - Lifetime
-
1986
- 1986-05-09 US US06/862,194 patent/US4905572A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JPH0629601B2 (ja) | 1994-04-20 |
JPS6084402A (ja) | 1985-05-13 |
DE3469380D1 (en) | 1988-03-24 |
US4905572A (en) | 1990-03-06 |
EP0132199A1 (de) | 1985-01-23 |
FR2549167B1 (fr) | 1988-01-29 |
FR2549167A1 (fr) | 1985-01-18 |
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