GB489618A - Improvements in hydraulic vibration dampers mounted on aircraft - Google Patents
Improvements in hydraulic vibration dampers mounted on aircraftInfo
- Publication number
- GB489618A GB489618A GB2556/37A GB255637A GB489618A GB 489618 A GB489618 A GB 489618A GB 2556/37 A GB2556/37 A GB 2556/37A GB 255637 A GB255637 A GB 255637A GB 489618 A GB489618 A GB 489618A
- Authority
- GB
- United Kingdom
- Prior art keywords
- reservoir
- liquid
- chambers
- damper
- rings
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/10—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using liquid only; using a fluid of which the nature is immaterial
- F16F9/14—Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect
- F16F9/16—Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect involving only straight-line movement of the effective parts
- F16F9/18—Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect involving only straight-line movement of the effective parts with a closed cylinder and a piston separating two or more working spaces therein
- F16F9/20—Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect involving only straight-line movement of the effective parts with a closed cylinder and a piston separating two or more working spaces therein with the piston-rod extending through both ends of the cylinder, e.g. constant-volume dampers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
489,618. Hydraulic vibration - dampers; stuffing-boxes. BECHEREAU, L., and CARROUEE, R. Jan. 28, 1937, No. 2556. Convention date, Jan. 30; 1936. [Class 108 (iii)] [Also in Group XXVI] In a hydraulic vibration-damper, particularly for use on aircraft, comprising one or more closed chambers completely filled with liquid, a part or parts formed in the wall or walls of the chamber or chambers, or the surrounding wall or walls of the chamber or chambers, is or are constituted by flexible or elastic material for compensating for the variations in volume, due to the variations in temperature, of the liquid enclosed in the damper. The vibration-damper shown in Fig. 1, of the type described in Specification 461,353, comprises a reservoir 1 with end stuffing- boxes through which passes the rod 2 of a piston reciprocable in a cylinder 4 housed in the reservoir, the cylinder being slidable .on the rod 2 between two stops 16 which it engages alternately to establish communication between the reservoir and one of the two working chambers of the cylinder. Vibrations are damped by restricted flow of liquid past the piston. The liquid-expansion compensating device comprises a flexible sleeve 30 surrounding, and fixed at its edges to, a part of the reservoir having one or more orifices 31. A metal sheath 32 may protect the sleeve. In another construction, Fig. 2, the reservoir 1 communicates through end orifices 23 with flexible chambers 24, 25, e.g. of corrugated rubber tubing. The reservoir may be dispensed with and the expansible chambers connected by a single conduit. For damping vibrations of an aircraft aileron, the arrangements of a vibration-damper or dampers according to the invention are similar to the vibrationdamper arrangements shown in Figs. 11, 12 of Specification 461,353. The Specification as open to inspection under Sect. 91 comprises also the vibrationdamper construction shown in Fig. 1 (Cancelled) which is similar to that described above with reference to Fig. 1, vibrations being damped, however, in addition to a restricted liquid flow past the piston, by flow through an auxiliary conduit 5 regulated by a thermostatically-controlled valve 6 by which changes in the viscosity of the liquid due to changes in temperature are compensated for. The reservoir communicates through orifices 8 with the piston-rod stuffing-boxes which contain rubber &c. packing-rings 10, 11 pressed against the rod by a spring 13 acting through a sleeve 14 on metallic annular members 12 bearing on the rings., On expansion of the liquid in the damper the rings 10, 11 yield against the action of the spring 13, the pressure of which is adjustable by means of a cap 15 which screws on the end of the reservoir and maintains the parts in alignment. In modifications, (a) the rings are enclosed in an annular member formed integral with the sleeve 14; (b) another spring acts on the rings in opposition to or in conjunction with the spring 13; and (c) an annular, flexible membrane is provided inside the cap 15 to prevent leakage and to assist in absorbing excessive expansion of the liquid. In the construction shown in Fig. 5 (Cancelled) the membrane 21 only is adapted to compensate for liquid expansion and for this purpose is in communication with the reservoir through channels 22 and the orifices 8. Another construction, without liquid-expansion compensating means, is also described in which the working cylinder is stationary and spring pressed annular valves effect communication between the cylinder working chambers and the 'reservoir. This subject-matter does not appear in the Specification as accepted.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR489618X | 1936-01-30 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB489618A true GB489618A (en) | 1938-07-28 |
Family
ID=8904270
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2556/37A Expired GB489618A (en) | 1936-01-30 | 1937-01-28 | Improvements in hydraulic vibration dampers mounted on aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB489618A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1994013975A1 (en) * | 1992-12-15 | 1994-06-23 | Honeywell Inc. | Rigid volume viscous damper |
DE102006030315A1 (en) * | 2006-06-30 | 2008-01-17 | Airbus Deutschland Gmbh | High-lift system on the wing of an aircraft |
WO2011147571A3 (en) * | 2010-05-26 | 2012-02-02 | Airbus Operations Gmbh | A device for an adjustable flap of a wing |
WO2014060705A2 (en) * | 2012-10-18 | 2014-04-24 | Ratier Figeac | Device for assisting the operation of an aircraft door |
CN109264003A (en) * | 2018-09-04 | 2019-01-25 | 西北工业大学 | A kind of thrust converter of pulse-knocking engine |
-
1937
- 1937-01-28 GB GB2556/37A patent/GB489618A/en not_active Expired
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1994013975A1 (en) * | 1992-12-15 | 1994-06-23 | Honeywell Inc. | Rigid volume viscous damper |
US8398019B2 (en) | 2006-06-30 | 2013-03-19 | Airbus Operations Gmbh | Adjusting device for adjusting a high-lift flap and airfoil wing comprising such an adjusting device |
DE102006030315A1 (en) * | 2006-06-30 | 2008-01-17 | Airbus Deutschland Gmbh | High-lift system on the wing of an aircraft |
US9573676B2 (en) | 2010-05-26 | 2017-02-21 | Airbus Operations Gmbh | Device for an adjustable flap of a wing |
CN103097241A (en) * | 2010-05-26 | 2013-05-08 | 空中客车运作有限责任公司 | A device for an adjustable flap of a wing |
CN103097241B (en) * | 2010-05-26 | 2016-07-13 | 空中客车运作有限责任公司 | Device for the adjustable wing flap of the wing |
WO2011147571A3 (en) * | 2010-05-26 | 2012-02-02 | Airbus Operations Gmbh | A device for an adjustable flap of a wing |
WO2014060705A2 (en) * | 2012-10-18 | 2014-04-24 | Ratier Figeac | Device for assisting the operation of an aircraft door |
FR2997151A1 (en) * | 2012-10-18 | 2014-04-25 | Ratier Figeac Soc | DAMPER WITH RELATIVE SPRING FUNCTION |
WO2014060705A3 (en) * | 2012-10-18 | 2014-07-10 | Ratier Figeac | Device for assisting the operation of an aircraft door |
US9969482B2 (en) | 2012-10-18 | 2018-05-15 | Ratier Figeac | Device for assisting the operation of an aircraft door |
CN109264003A (en) * | 2018-09-04 | 2019-01-25 | 西北工业大学 | A kind of thrust converter of pulse-knocking engine |
CN109264003B (en) * | 2018-09-04 | 2021-11-12 | 西北工业大学 | Thrust converter of pulse detonation engine |
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