CN103032403A - Airplane frame position control actuator - Google Patents
Airplane frame position control actuator Download PDFInfo
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- CN103032403A CN103032403A CN2012105792099A CN201210579209A CN103032403A CN 103032403 A CN103032403 A CN 103032403A CN 2012105792099 A CN2012105792099 A CN 2012105792099A CN 201210579209 A CN201210579209 A CN 201210579209A CN 103032403 A CN103032403 A CN 103032403A
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Abstract
The invention relates to an airplane frame position control actuator, which comprises a hydraulic control one-way valve, a first safety valve, a second safety valve, a one-way valve, a one-way damping valve, a damping valve, a hydraulic control direction valve, a barrel, a floating piston, a barrel cover and a piston rod, wherein the piston rod is arranged in the barrel; the floating piston is provided with two ends with unequal areas; the large end is arranged in the barrel; the small end is arranged in a cavity of the piston rod; the barrel cover is arranged outside the piston rod; a cavity A is formed by the floating piston and the piston rod in the barrel; a cavity B is formed by the barrel cover and the piston rod; and an oil port which is communicated with a landing gear put-down port DN and an oil port which is communicated with a landing gear pick-up port UP are arranged in the cavity A and the cavity B respectively. According to the airplane frame position control actuator, large-angle pick-up, put-down and locking functions of a landing gear frame can be realized, meanwhile, load follow-up is realized during landing slide of an airplane, proper dynamic buffer is provided, and loads of front and rear tires are balanced; and the airplane frame position control actuator is widely applied to a main landing gear system of a large-sized airplane and has obvious economic benefits.
Description
Technical field
The present invention relates to a kind of fluid control device, be specifically related to a kind of aircraft vehicle chord position and put the control actuator.
Background technique
Vehicle frame positioning control actuator is applicable to the large aircraft main landing gear system of multipoint mode layout, as shown in Figure 1, by adjusting the vehicle frame attitude, realize undercarriage pack up locking and alighting run the time load servo-actuated, suitable dynamic buffering is provided simultaneously.Introduce a kind of vehicle frame positioning control actuator with pooling feature among the US6279854B1, but be difficult to realize the main wide-angle draw-in and draw-off function that rises and falls.
Summary of the invention
Purpose of the present invention: for the problem that the wide-angle operation of landing gear can't be provided that exists in the prior art, the invention provides a kind of vehicle frame positioning control actuator that can realize that the vehicle frame pooling feature simultaneously can the wide-angle operation of landing gear.
Technological scheme of the present invention is: a kind of aircraft vehicle chord position is put the control actuator, comprises Pilot operated check valve (1), the first safety valve (2), the second safety valve (3), one-way valve (4), one-way damper valve (5), orifice valve (6), hydraulic control directional control valve (7), cylindrical shell (8), floating piston (9), cover (10) and piston rod (11); Piston rod (11) is installed in the cylindrical shell (8); Floating piston (9) has the two ends that area does not wait, and large end is installed in the cylindrical shell (8), and small end is installed in the cavity of piston rod (11); Piston rod (11) outside is equipped with cover (10); Floating piston (9) in the cylindrical shell (8) and piston rod (11) form cavity A, the cavity B that cover (10) and piston rod (11) form; Be respectively equipped with among cavity A, the cavity B and be communicated with the gear down hydraulic fluid port of interface DN and the hydraulic fluid port of gear up interface UP;
The hydraulic oil of plane hydraulic system enters and flows through one-way damper valve (5) behind the Pilot operated check valve (1) and enter cavity A through putting down interface DN, links to each other with the oil outlet of the first safety valve (2), the filler opening of the second safety valve (3), the control mouth of hydraulic control directional control valve (7) simultaneously; Interface UP enters one-way valve (4) to the hydraulic oil of plane hydraulic system, orifice valve (6) enters cavity B through packing up, the oil outlet that is connected the second safety valve (3) between one-way valve (4) and the orifice valve (6), one-way valve (4) are connected the first safety valve (2) filler opening with packing up between the interface UP; Cavity A links to each other with two load ends of hydraulic control directional control valve (7) respectively with cavity B.
Further, above-mentioned cylindrical shell (8) is provided with vent (13), and floating piston (9) is provided with hollow aperture (12), and communicates with vent (13).
Useful technique effect: the vehicle frame positioning control actuator that the present invention proposes can realize undercarriage vehicle frame wide-angle folding and unfolding lock function, when sliding, aircraft landing realizes that simultaneously load is servo-actuated, suitable dynamic buffering is provided, tyre load before and after the balance, be widely used in the main landing gear system of large aircraft, have obvious economic benefit.
Description of drawings
Fig. 1 is the landing gear structure schematic diagram;
Fig. 2 is structural representation of the present invention;
Fig. 3 is cylindrical shell of the present invention, floating piston and piston rod different operating view;
Wherein, 1: Pilot operated check valve, 2: the first safety valves, 3: the second safety valves, 4: one-way valve, 5: one-way damper valve, 6: orifice valve, 7: hydraulic control directional control valve, 8: cylindrical shell, 9: floating piston, 10: cover, 11: piston rod, 12: floating piston aperture, 13: cylindrical shell vent, 14: the first earrings, 15: the second earrings.
Embodiment
The present invention is described in further detail below in conjunction with Figure of description.
The vehicle frame position control comprises Pilot operated check valve 1, the first safety valve 2, the second safety valve 3, one-way valve 4, one-way damper valve 5, orifice valve 6, hydraulic control directional control valve 7, cylindrical shell 8, floating piston 9, cover 10 and piston rod 11; Piston rod 11 is installed in the cylindrical shell 8; Floating piston 9 has the two ends that area does not wait, and large end is installed in the cylindrical shell 8, and small end is installed in the cavity of piston rod 11, and piston rod 11 and floating piston 9 can move in cylindrical shell 8 like this; Piston rod 11 outsides are equipped with cover 10; Floating piston 9 in the cylindrical shell 8 and piston rod 11 form cavity A, the cavity B that cover 10 and piston rod 11 form; Be respectively equipped with among cavity A, the cavity B and be communicated with the gear down hydraulic fluid port of interface DN and the hydraulic fluid port of gear up interface UP;
The hydraulic oil of plane hydraulic system enters and flows through one-way damper valve 5 behind the Pilot operated check valve 1 and enter cavity A through putting down interface DN, links to each other with the oil outlet of the first safety valve 2, the filler opening of the second safety valve 3, the control mouth of hydraulic control directional control valve 7 simultaneously; Interface UP enters one-way valve 4, orifice valve 6 enters cavity B through packing up for the hydraulic oil of plane hydraulic system, is connected the oil outlet of the second safety valve 3 between one-way valve 4 and the orifice valve 6, and one-way valve 4 is connected the first safety valve 2 filler openings with packing up between the interface UP; Cavity A links to each other with two load ends of hydraulic control directional control valve 7 respectively with cavity B.
Under the effect of hydraulic coupling and load force, the large end of floating piston 9 can be in cylindrical shell 8 interior relative movement, and the small end of floating piston 9 can be in piston rod 11 interior relative movement, and piston rod can be in cylindrical shell 8 interior relative movement.
When reality connected, cylindrical shell 8 was provided with the first earrings 14, and piston rod 11 is provided with the second earrings 15 and links to each other with the bearing pin of vehicle frame respectively.
During gear up, pack up interface UP and connect the plane hydraulic system fuel feeding, put down interface DN and connect the plane hydraulic system oil return, hydraulic control directional control valve 7 is in the next, cut off the communication of cavity A and cavity B, pack up interface UP mesohigh oil and enter cavity B through one-way valve 4, orifice valve 6, the hydraulic coupling that acts on the piston rod 11 makes piston rod 11 be contracted to the left limit position, make the vehicle frame of undercarriage upper than wide-angle by the initial position receipts, extremely be similar to parallel position with undercarriage leg such as nearly 90 °; Behind gear up; when undercarriage hydraulic system charge oil pressure is closed; self-sealing pressure in the vehicle frame position control locks so far position with piston rod 11; as shown in Figure 3A; realize the auto-lock function of vehicle frame positioning control actuator; when the hydraulic fluid pressure in being enclosed in cavity B was subjected to external environment effect such as expanded by heating to cause pressure to raise, the second safety valve 3 had been opened the safety protection effect.
Gear down, put down interface DN welding system fuel feeding, pack up the oil return of interface UP welding system, hydraulic control directional control valve 7 is in upper, high pressure oil is through Pilot operated check valve 1, one-way damper valve 5 enters cavity A and cavity B simultaneously, floating piston 9 moves to left to spacing position, piston rod 11 moves to right because of the pressure official post piston rod 11 that difference in areas produces, make piston rod 11 be stretched to the right limit state, shown in Fig. 3 B, make undercarriage realize that the pre-determined tilt angle is to landing state, when piston rod 11 moves reciprocatingly under external force, one-way damper valve 5 is realized the balance of front and back tyre load with the follow-up motion of suitable damping control undercarriage vehicle frame, and Fig. 3 C has represented the maximum elongation state of vehicle frame position actuator.When the vehicle frame position control was subject to exceeding the compression shock of setting value, the first safety valve 2 was opened and is shielded.
In the undercarriage control working procedure, in order to make floating piston 9 and piston rod 11 not produce extra pressure, the high pressure that produces such as barometric pressure and because of the hydraulic oil internal leakage, above-mentioned cylindrical shell 8 is provided with vent 13, floating piston 9 is provided with hollow aperture 12, and communicate with vent 13, like this balance the pressure in the inoperative chamber.
The vehicle frame positioning control actuator that the present invention proposes can realize undercarriage vehicle frame pack up locking and alighting run the time load servo-actuated, suitable dynamic buffering is provided simultaneously, be widely used in the main landing gear system of large aircraft, have obvious economic benefit.
Claims (2)
1. an aircraft vehicle chord position is put the control actuator, it is characterized in that: comprise Pilot operated check valve (1), the first safety valve (2), the second safety valve (3), one-way valve (4), one-way damper valve (5), orifice valve (6), hydraulic control directional control valve (7), cylindrical shell (8), floating piston (9), cover (10) and piston rod (11); Piston rod (11) is installed in the cylindrical shell (8); Floating piston (9) has the two ends that area does not wait, and large end is installed in the cylindrical shell (8), and small end is installed in the cavity of piston rod (11); Piston rod (11) outside is equipped with cover (10); Floating piston (9) in the cylindrical shell (8) and piston rod (11) form cavity A, the cavity B that cover (10) and piston rod (11) form; Be respectively equipped with among cavity A, the cavity B and be communicated with the gear down hydraulic fluid port of interface DN and the hydraulic fluid port of gear up interface UP;
The hydraulic oil of plane hydraulic system enters and flows through one-way damper valve (5) behind the Pilot operated check valve (1) and enter cavity A through putting down interface DN, links to each other with the oil outlet of the first safety valve (2), the filler opening of the second safety valve (3), the control mouth of hydraulic control directional control valve (7) simultaneously; Interface UP enters one-way valve (4) to the hydraulic oil of plane hydraulic system, orifice valve (6) enters cavity B through packing up, the oil outlet that is connected the second safety valve (3) between one-way valve (4) and the orifice valve (6), one-way valve (4) are connected the first safety valve (2) filler opening with packing up between the interface UP; Cavity A links to each other with two load ends of hydraulic control directional control valve (7) respectively with cavity B.
2. will go 1 described aircraft vehicle chord position to put the control actuator according to right, it is characterized in that: cylindrical shell (8) is provided with vent (13), and floating piston (9) is provided with hollow aperture (12), and communicates with vent (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105792099A CN103032403A (en) | 2012-12-27 | 2012-12-27 | Airplane frame position control actuator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105792099A CN103032403A (en) | 2012-12-27 | 2012-12-27 | Airplane frame position control actuator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103032403A true CN103032403A (en) | 2013-04-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105792099A Pending CN103032403A (en) | 2012-12-27 | 2012-12-27 | Airplane frame position control actuator |
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| CN (1) | CN103032403A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104088858A (en) * | 2014-07-06 | 2014-10-08 | 上海宏信设备工程有限公司 | Power supply and hydraulic redundancy thread self-locking axial force compensation system |
| CN108266413A (en) * | 2017-12-15 | 2018-07-10 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Asymmetric Electric hydrostatic actuator based on pressure selection valve |
| CN108791823A (en) * | 2018-06-19 | 2018-11-13 | 中航飞机起落架有限责任公司 | A kind of undercarriage vehicle frame stablizes buffer unit and its control method |
| CN109204787A (en) * | 2018-10-25 | 2019-01-15 | 中航飞机起落架有限责任公司 | Vehicle frame folding and unfolding buffer unit and undercarriage |
| CN110821912A (en) * | 2019-11-12 | 2020-02-21 | 中航飞机起落架有限责任公司 | Single-acting tension cylinder air exchange system |
| CN116107293A (en) * | 2023-04-10 | 2023-05-12 | 商飞软件有限公司 | Civil aircraft flight control system actuation loop fault diagnosis system and diagnosis method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5284083A (en) * | 1991-11-26 | 1994-02-08 | Messier-Bugatti | System for powering the driving actuator of an aircraft undercarriage |
| US6279854B1 (en) * | 1999-04-29 | 2001-08-28 | The Boeing Company | Combined damper and truck positioner for landing gear |
| US6792844B1 (en) * | 1999-10-07 | 2004-09-21 | Honeywell Normalair-Garrett (Holdings) Limited | Hydraulic system for aircraft landing gear |
| CN201745747U (en) * | 2010-07-16 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Teletype turning system capable of preventing out of control of airplane |
| US20120091271A1 (en) * | 2005-08-04 | 2012-04-19 | Messier-Dowty Limited | Landing gear |
-
2012
- 2012-12-27 CN CN2012105792099A patent/CN103032403A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5284083A (en) * | 1991-11-26 | 1994-02-08 | Messier-Bugatti | System for powering the driving actuator of an aircraft undercarriage |
| US6279854B1 (en) * | 1999-04-29 | 2001-08-28 | The Boeing Company | Combined damper and truck positioner for landing gear |
| US6792844B1 (en) * | 1999-10-07 | 2004-09-21 | Honeywell Normalair-Garrett (Holdings) Limited | Hydraulic system for aircraft landing gear |
| US20120091271A1 (en) * | 2005-08-04 | 2012-04-19 | Messier-Dowty Limited | Landing gear |
| CN201745747U (en) * | 2010-07-16 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Teletype turning system capable of preventing out of control of airplane |
Non-Patent Citations (1)
| Title |
|---|
| 唐有才等: "飞机起落架液压系统的节能设计", 《机床与液压》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104088858A (en) * | 2014-07-06 | 2014-10-08 | 上海宏信设备工程有限公司 | Power supply and hydraulic redundancy thread self-locking axial force compensation system |
| CN104088858B (en) * | 2014-07-06 | 2016-05-18 | 上海宏信设备工程有限公司 | The screw thread self-locking profile shaft force compensating system of power supply and hydraulic pressure redundancy |
| CN108266413A (en) * | 2017-12-15 | 2018-07-10 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Asymmetric Electric hydrostatic actuator based on pressure selection valve |
| CN108791823A (en) * | 2018-06-19 | 2018-11-13 | 中航飞机起落架有限责任公司 | A kind of undercarriage vehicle frame stablizes buffer unit and its control method |
| CN109204787A (en) * | 2018-10-25 | 2019-01-15 | 中航飞机起落架有限责任公司 | Vehicle frame folding and unfolding buffer unit and undercarriage |
| CN110821912A (en) * | 2019-11-12 | 2020-02-21 | 中航飞机起落架有限责任公司 | Single-acting tension cylinder air exchange system |
| CN110821912B (en) * | 2019-11-12 | 2021-06-22 | 中航飞机起落架有限责任公司 | Single-acting tension cylinder air exchange system |
| CN116107293A (en) * | 2023-04-10 | 2023-05-12 | 商飞软件有限公司 | Civil aircraft flight control system actuation loop fault diagnosis system and diagnosis method |
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Application publication date: 20130410 |