WO2011061567A1 - Dispositivo reductor de vibraciones en la silla de los pilotos de helicópteros - Google Patents
Dispositivo reductor de vibraciones en la silla de los pilotos de helicópteros Download PDFInfo
- Publication number
- WO2011061567A1 WO2011061567A1 PCT/IB2009/055244 IB2009055244W WO2011061567A1 WO 2011061567 A1 WO2011061567 A1 WO 2011061567A1 IB 2009055244 W IB2009055244 W IB 2009055244W WO 2011061567 A1 WO2011061567 A1 WO 2011061567A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- bellows
- chair
- aircraft
- pilot
- helicopter
- Prior art date
Links
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- 238000013016 damping Methods 0.000 description 11
- 230000009467 reduction Effects 0.000 description 11
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- 206010053156 Musculoskeletal discomfort Diseases 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0696—Means for fastening seats to floors, e.g. to floor rails
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60N—SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- B60N2/00—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
- B60N2/24—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles
- B60N2/42—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats
- B60N2/4207—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats characterised by the direction of the g-forces
- B60N2/4242—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats characterised by the direction of the g-forces vertical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60N—SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- B60N2/00—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
- B60N2/24—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles
- B60N2/42—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats
- B60N2/427—Seats or parts thereof displaced during a crash
- B60N2/42727—Seats or parts thereof displaced during a crash involving substantially rigid displacement
- B60N2/42736—Seats or parts thereof displaced during a crash involving substantially rigid displacement of the whole seat
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60N—SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- B60N2/00—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
- B60N2/50—Seat suspension devices
- B60N2/501—Seat suspension devices actively controlled suspension, e.g. electronic control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60N—SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- B60N2/00—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
- B60N2/50—Seat suspension devices
- B60N2/504—Seat suspension devices attached to the base and the backrest
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60N—SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- B60N2/00—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
- B60N2/50—Seat suspension devices
- B60N2/52—Seat suspension devices using fluid means
- B60N2/525—Seat suspension devices using fluid means using gas
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0619—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with energy absorbing means specially adapted for mitigating impact loads for passenger seats, e.g. at a crash
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0689—Arrangements of seats, or adaptations or details specially adapted for aircraft seats specially adapted for pilots
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- the present invention relates to a device for reducing the vibrations that occur in the seat of helicopter pilots due to the movement of the blades of said aircraft.
- the chairs, the cyclic, the collective, the pedals and the control mechanisms transmit the vibrations directly to the pilot's body, which experiences endless sensations that can put the safety of the flight at risk, and that later with time, they cause health problems in the pilots, especially of the spine and back, which requires the investment of large amounts of money in physical treatments and in some cases the early withdrawal of flight personnel.
- the present invention provides a device that is based on a pneumatic system of low weight and cost, which counteracts the vibrations suffered by the pilot, since it neutralizes the movement of the chassis or the chair causing the vibration to be absorbed by a pneumatic ball and not transmitted to the body of the pilot.
- the helicopters have a considerable number of vibrations generated by various sources, ranging from simple vibrations caused by the effect of aerodynamic forces during the flight, such as aeroelastic and aeromechanical instabilities, to those of greater range generated by the engine and rotor .
- the effects caused by vibration are subdivided into two categories: effects produced by aerodynamic causes and effects produced by mechanical causes. All these effects bring repercussions in different classes, such as comfort and efficiency of the crew, fatigue of dynamic components and the structure of the device or the accuracy and efficiency of electronic equipment.
- the main rotor of the helicopter produces vibrations in ranges from 3 to 12 Hz and the frequency depends on the number of blades. This range is much smaller than that produced by the tail rotor, which induces vibrations between 20 and 25 Hz.
- the vibrations produced travel through the fuselage of the aircraft in the form of low frequency vibrations and adversely affect the controls of the helicopter, subsystem of operations and the comfort of the crew, especially in aircraft with two-rotor rotors, such as the UH-1 H helicopter.
- Vibrations can be defined as the oscillatory movements of solid body particles around their equilibrium point. Technologically it is almost impossible to build a machine that moves energy from one place to another without the operation being accompanied by vibrations of some kind. The larger the moving parts, the more likely there are to be vibrations that are usually accompanied by noise.
- the seat increased the peak of the amplitude of the vibration, that is, the seat has a clear negative effect on the pilot It occupies it.
- the Austrian Army reduced the maximum flight speed of the Bell 212 to 90 knots.
- the vibration frequencies in the pilot's chair are different and are related to the number of rotor blades, for example, the estimated value for a two-seater helicopter such as UH-1 H is 12 Hz.
- EP 1659309 discloses a damping device to reduce the vibrations that are produced by the movement of the rotors in a helicopter, where said apparatus includes a piston that moves in a hydraulic fluid within a damping chamber, the which resists the movement of the piston by means of the pressure of said fluid, which provides damping forces that act to oppose the movement of the piston thus reducing or canceling the vibrations produced by the rotors of the aircraft.
- the main disadvantage presented by the invention described in said document is based on the complexity of the damping system, since it is necessary to include a hydraulic fluid whose use is not advisable for a helicopter, since the chamber containing said fluid can suffer blows that can crack it by letting out the fluid and causing problems in the helicopter rotor.
- FIGURES DESCRIPTION OF THE FIGURES
- the invention can be understood in a better way by means of the figures, where each of the elements that make up the vibration reduction system in the pilot's chair are shown. of helicopters that you want to protect.
- the figures show the reference numbers assigned to each of the elements that make up that system.
- Figure 1 corresponds to a general view of the vibration reducing device of the present invention coupled to the chair seat of the aircraft.
- Figure 2 corresponds to a general front view of the vibration reducing device of the present invention coupled to the chair seat of the aircraft.
- Figure 3 corresponds to a general view of the pilot's chair without the vibration reducing device.
- Figure 4 corresponds to the pneumatic plane of the vibration reducing device.
- Figure 5 corresponds to a general scheme of the helicopter, the configuration of the transmission rotors and the vibrations to the pilot's chair.
- Figure 6 corresponds to the graph of recommendation of the maximum time to which a pilot should be exposed according to ISO 2631-1978.
- Figure 7 corresponds to a detailed view of the concentric cylinders of the chair adaptation mechanism of the device of the invention.
- Figure 8a corresponds to a top view of the bellows support structure to the helicopter chair.
- Figure 8b corresponds to a front view of the support structure of Figure 8a.
- Figure 9 corresponds to a general view of the safety and anchoring mechanism of the device of the invention for fixing the chair to the floor of the aircraft.
- Figure 10 corresponds to a detailed view of the safety and anchoring mechanism and the support structure of the bellows to the chair when said mechanism has not been activated.
- Figure 11 corresponds to a detailed view of the safety and anchoring mechanism and the support structure of the bellows to the chair when said mechanism has been activated.
- Figure 12 corresponds to a rear perspective view of the aircraft cabin with the vibration reduction device implemented without the pilot and copilot chairs.
- Figure 13 corresponds to a rear perspective view of the aircraft cabin with the vibration reduction device including the pilot and copilot chairs.
- the purpose of the vibration reduction device of the present invention is to isolate the pilot's seat of a helicopter from the ground of said aircraft, so that the rails on which the chair travels cease to behave as if they did part of the helicopter floor.
- a redesign of these rails is necessary so that they allow adapting a damping mechanism that does not limit the horizontal movement of the chair and does not interfere with the aircraft's control mechanisms, especially with the collective , which is located very close to the base structure of the chair.
- the vibration reduction device on the chairs of helicopter pilots comprises the following elements or parts:
- a pneumatic bellows (1) located under the structure of the helicopter chair, which acts as a damping system for the chair and lifts it on the floor of the aircraft, in order to counteract the vibrations generated by the rotors of the helicopter.
- a non-return valve (2) which ensures that the air in the bellows (1) is not returned, ensuring that the pressure of the bellows is maintained and the vibrations of the helicopter are canceled and are not transmitted to the pilot's chair.
- An solenoid valve or solenoid valve (3) is an solenoid valve or solenoid valve (3).
- a pump or compressor (5) to supply air to the bellows (1) through the non-return valve (2) and the pressure regulating valve (4).
- This pump or compressor (5) is controlled by means of the pressure regulating valve (4) in order to supply the bellows (1) with enough air to lift the chair depending on the weight and physical constitution of the pilot.
- a chair adaptation mechanism (6) that allows the vibration reduction device to be installed in the lower part of the pilot's chair, specifically with the chair attached to the rails (602).
- a safety mechanism (7) and anchorage to the floor which insulates the chair so that it does not rest directly on the ground of the aircraft in case of a sudden loss of air pressure in the bellows (1), which prevents the blow for said loss of pressure passes directly to the pilot's column through the chair.
- the vibration reducing device has a maximum height of 10 cm, since this is the distance from the floor of the cabin to the minimum height of the chair.
- the device must also withstand a minimum force of 1583.77 N, which is equivalent to the force exerted by the weight of the pilot and the chair.
- the vibration reducing device works with pressures not greater than 0.8 MPa, which is the maximum pressure resisted by the bellows (1).
- pressures not greater than 0.8 MPa, which is the maximum pressure resisted by the bellows (1).
- polyurethane hoses for pneumatic connections that withstand up to 1.2 MPa of pressure.
- These hoses have different outside diameter gauges and are made with very light synthetic materials and must be flexible to allow the formation of curvatures that do not affect the air flow, thus facilitating installation within the aircraft.
- the pneumatic bellows (1) is a simple round damping mechanism whose size varies according to the necessary specifications of the system to be damped.
- This type of bellows (1) has a weight that is between 800 and 1000g, preferably 900g and has two fixing surfaces, one upper (101) and one lower (102) preferably made of galvanized steel and an air inlet ( 103) to which the non-return valve (2) is connected, which prevents the fluid from being directed in the opposite direction, ensuring that the pneumatic bellows (1) has no air loss due to the force applied to it.
- the valve (2) is an unlocked non-return valve (2) that leaves open the possibility of suppressing the blockage by means of a pilot, ensuring that the device can be adjusted to the conditions of each pilot.
- These valves normally work with 8 mm diameter pipe, which would require a 1 ⁇ 4 quick fitting, so that the valve adapts to the desired pipe.
- the non-return valve (2) normally has flow at its inlet to allow air access to the bellows (1), but at the time of releasing its pressure in order to adjust the system to a lower pressure, It must have flow only by unlocking. This necessitates the use of valves (3) operated by pilot solenoids, with return by the action of a spring, 3/2 normally closed, which fulfill the function of the pneumatic control over the non-return valve (2).
- electrovalves or mechanically operated valves (3) can be used, which generate greater reliability and allow subsequent automation for other types of applications that are desired in the aircraft.
- solenoid valves (3) can be supplied with 24V, which is the voltage that the helicopter handles, the signal they emit enters the device through a simple and easy-to-operate actuator. Thus, it is required to control the direction of the air flow by the action of the non-return valve (2) in order to ensure that the bellows system (1) is stabilized at the desired pressure.
- Figure 4 shows how the valves (3) interact with the valve (2) and with the bellows (1). As can be seen, each of the solenoid valves (3) controls the air inlets towards the bellows (1) and is installed in such a way that one valve (3) controls the unlocking and the other controls the supply.
- the solenoid valve (3) When the solenoid valve (3) is activated, the air is allowed to reach the non-return valve (2), but not until it is unlocked, which causes the bellows (1) to reach equilibrium at the desired pressure, achieving system stability When performing the flight, the system does not interfere with any of the control controls of the aircraft and its installation is simple. If the bellows (1) are reset again at a lower pressure, only the valve (3) that controls the release of the anti-return (2) is activated, thereby releasing air from the bellows (1) To the environment.
- the system is powered by a pump or compressor (5), which is portable and handles pressures up to 2.07 MPa.
- a pump or compressor (5) which is portable and handles pressures up to 2.07 MPa.
- an accumulator that is incorporated in the compressor is normally used, which is responsible for compensating the oscillations of the pressure and serves as a reservoir that is used to cover compressed air consumption peaks, which It makes them suitable when it is necessary to have enough compressed air to feed the actuators that work by running fast cycles, such as the bellows (1) to be used in the damping mechanism.
- the bellows (1) When the bellows (1) are running at 0.8 MPa pressure, which is the maximum pressure allowed for their operation, they have a maximum volume of 0.8 L, so the use of a 5 L accumulator is preferred for supply the system without using the compressor (5), which achieves autonomy when the compressor (5) fails.
- the air flow entering the bellows (1) must be controlled by an electric pressure regulating valve (4), so that the air flow to the bellows (1) can be increased or decreased according to the requirements
- the vibration reducing device has a mechanism that allows to adjust the pressure of the air inlet towards the valves, which can be visualized with a pressure gauge.
- the implementation of the bellows (1) in the pilot's chair requires a modification of the rails that the support, which is achieved through a mechanism of adaptation to the chair (6).
- Said adaptation mechanism (6) is shown in Figures 8a and 8b and has four round cylinders (601) as a guide having a height between 2.5 and 3.5 cm, preferably 2.9 cm. These cylinders are manufactured in the same material as the chair and are connected directly to the rails (602) that support the pilot's chair ensuring its movement in the horizontal axis.
- cylinders (601) allow free movement of the chair on the safety and anchoring mechanism (7), as seen in Figure 10, on the vertical axis, but limit movement on any of the other axes and have accident insurance (7) that guarantees the stability of the chair in case of a possible collision.
- the rails (602) remain stable thanks to a structure formed by four cylinders (601), connected to four rods (606) located in an X-shape and connected by a central platform (607) to which the bellows (1 ) by two perforations (608) that work with bolts and similarly do not interfere with the connection of the non-return valves (2).
- the bellows (1) is located just in the middle of the vertices that dominate the rails and when it is in its maximum expansion, it separates the chair from the ground approximately 1.8 cm.
- the X structure is constructed with defined inclination angles such that when the bellows (1) is in its maximum expansion position the chair rises from the ground an approximate height of 1 cm. This elevation allows the chair to be detached from the ground for as long as possible, which reduces vibrations significantly.
- the cylinders (601) must allow maximum vertical movement of the chair, which will be subsequently controlled with the bellows (1) but must ensure that when the aircraft makes turns or varies its center of gravity, the cylinders (601) do not they lock with the guides, avoiding vertical displacement.
- a flexible bushing system is implemented, which is composed of two cylinders, one inside (603) and one outside (604) of the same length but of different diameters, located concentrically and With its matching ends. These cylinders (603, 604) are joined together by means of a third elastic rubber cylinder (605), which allows the inner cylinder (603) to have slight degrees of mobility in the three axes, thus preventing the System locks with guides.
- the outer cylinder (604) contains inside an elastomer cylinder (605) which allows a slight deformation in any of the directions. From these cylinders that make up the cylinder (601), the structure that houses the bellows is fastened, which is composed of four aluminum rods (606) located in the form of X, which are shown in Figures 8a and 8b.
- the safety mechanism (7) consists of basically four parts that are: a guide rail cylinder (705), which houses the rest of the elements inside it, the bolt support cylinder (706), which maintains the pin (701) in position ensuring that it triggers if the situation warrants, the pin (701) and the guide cylinder cover (703).
- the guide rail of the rails (705) is made of the same material as the rails and is responsible for ensuring that the chair does not suffer large longitudinal displacements.
- This guide cylinder (705) is attached to the floor of the cabin of the aircraft by means of four bolts that fix the entire structure to the helicopter.
- the cylinder (706) Inside the guide cylinder (705) must be placed the cylinder (706) whose main is to keep the pin (701) in the position indicated for its correct performance, for this reason it must have a height between 35 and 40 mm, preferably 38 mm.
- the bolt is divided into two parts, the pin (701) and its housing (703), which also corresponds to the cylinder cover (705, 706).
- the housing (703) can be seen in Figure 7 and is responsible for ensuring that the pin (701) is always ready to fire and to limit its movement only in one direction.
- the housing (703) in its rear part has a small vertical wall, which serves as a support point for the platelet that supports the pin (701), thus ensuring that the spring (702) that it has, works like a spring compression helical with a static load.
- This wall allows the spring (702) to have a maximum stroke between 12 and 18 mm, preferably 15 mm, which is equivalent to when the safety is activated by removing the pin (701).
- the safety mechanism (7) consists of a simple mechanism based on a pin (701) and a spring (702) like the one used in the door plates, which is located inside each of the guide cylinders (705, 706) of the rails of the structure of the pilot's chair.
- Figures 12 and 13 show the final installation of all the components of the vibration reduction device located under the pilot and co-pilot chairs, distributing the elements in such a way that they do not interfere with the fixed parts of the aircraft as are the cyclic (11), the collective (12) and the instrument panel (13).
- the bellows (1) can be filled with a fluid other than air, which can be another gas or a liquid substance.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
- Fluid-Damping Devices (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012125391/11A RU2504487C1 (ru) | 2009-11-20 | 2009-11-20 | Устройство для уменьшения вибрации кресла пилота вертолета |
CN200980163323.XA CN102858590B (zh) | 2009-11-20 | 2009-11-20 | 直升飞机飞行员座椅中的减振装置 |
EP09851398.9A EP2502782B1 (en) | 2009-11-20 | 2009-11-20 | Device for reducing vibrations in a helicopter pilot's seat |
ES09851398.9T ES2524942T3 (es) | 2009-11-20 | 2009-11-20 | Dispositivo reductor de vibraciones en la silla de los pilotos de helicopteros |
PCT/IB2009/055244 WO2011061567A1 (es) | 2009-11-20 | 2009-11-20 | Dispositivo reductor de vibraciones en la silla de los pilotos de helicópteros |
US13/510,834 US9061767B2 (en) | 2009-11-20 | 2009-11-20 | Vibrations reduction device in the chairs of helicopter pilots |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/IB2009/055244 WO2011061567A1 (es) | 2009-11-20 | 2009-11-20 | Dispositivo reductor de vibraciones en la silla de los pilotos de helicópteros |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011061567A1 true WO2011061567A1 (es) | 2011-05-26 |
Family
ID=44059249
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/IB2009/055244 WO2011061567A1 (es) | 2009-11-20 | 2009-11-20 | Dispositivo reductor de vibraciones en la silla de los pilotos de helicópteros |
Country Status (6)
Country | Link |
---|---|
US (1) | US9061767B2 (es) |
EP (1) | EP2502782B1 (es) |
CN (1) | CN102858590B (es) |
ES (1) | ES2524942T3 (es) |
RU (1) | RU2504487C1 (es) |
WO (1) | WO2011061567A1 (es) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014006475A1 (en) | 2012-07-03 | 2014-01-09 | Epar Sp. Z O. O. | A shock-absorbing vehicle chair |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3006668B1 (fr) | 2013-06-10 | 2015-06-26 | Eurocopter France | Siege anti crash et aeronef |
ES2755947T3 (es) | 2014-03-31 | 2020-04-24 | Vestas Wind Sys As | Estructura de góndola de turbina eólica |
EP3018056B1 (en) * | 2014-11-04 | 2017-05-31 | Fusioncopter Sp. z o.o | Aircraft seat |
RU2597042C1 (ru) * | 2015-05-27 | 2016-09-10 | Ооо "Сайен Кампэни" | Способ виброизоляции пилота вертолета и подвеска сиденья для реализации способа |
CN105129094B (zh) * | 2015-09-16 | 2017-11-17 | 航宇救生装备有限公司 | 一种飞机驾驶员座椅的可升降吸能底座 |
US10266080B2 (en) * | 2016-06-21 | 2019-04-23 | GM Global Technology Operations LLC | Seat track support damper |
CN108248868B (zh) * | 2017-12-18 | 2020-11-03 | 江西冠一通用飞机有限公司 | 一种通航飞机用飞行员座椅防撞保护装置 |
DE102018001802A1 (de) * | 2018-03-07 | 2019-09-12 | Eveline Kladov | Flugzeugsitzstabilisatoren |
US11124272B2 (en) * | 2019-11-11 | 2021-09-21 | Steering Solutions Ip Holding Corporation | System and method for vibration cancellation |
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- 2009-11-20 US US13/510,834 patent/US9061767B2/en not_active Expired - Fee Related
- 2009-11-20 RU RU2012125391/11A patent/RU2504487C1/ru not_active IP Right Cessation
- 2009-11-20 CN CN200980163323.XA patent/CN102858590B/zh not_active Expired - Fee Related
- 2009-11-20 EP EP09851398.9A patent/EP2502782B1/en not_active Not-in-force
- 2009-11-20 WO PCT/IB2009/055244 patent/WO2011061567A1/es active Application Filing
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Also Published As
Publication number | Publication date |
---|---|
US20120318920A1 (en) | 2012-12-20 |
US9061767B2 (en) | 2015-06-23 |
RU2504487C1 (ru) | 2014-01-20 |
EP2502782B1 (en) | 2014-08-27 |
EP2502782A4 (en) | 2014-01-08 |
RU2012125391A (ru) | 2013-12-27 |
CN102858590A (zh) | 2013-01-02 |
ES2524942T3 (es) | 2014-12-15 |
EP2502782A1 (en) | 2012-09-26 |
CN102858590B (zh) | 2015-09-30 |
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