CN106762880A - A kind of airplane tail pillar hydraulic pressure folding and unfolding control system - Google Patents

A kind of airplane tail pillar hydraulic pressure folding and unfolding control system Download PDF

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Publication number
CN106762880A
CN106762880A CN201611239587.7A CN201611239587A CN106762880A CN 106762880 A CN106762880 A CN 106762880A CN 201611239587 A CN201611239587 A CN 201611239587A CN 106762880 A CN106762880 A CN 106762880A
Authority
CN
China
Prior art keywords
valve
hydraulic
tail
tail pillar
pillar
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.)
Pending
Application number
CN201611239587.7A
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Chinese (zh)
Inventor
李利
张雷
马军
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Xian Aircraft Design and Research Institute of AVIC
Original Assignee
Xian Aircraft Design and Research Institute of AVIC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Xian Aircraft Design and Research Institute of AVIC filed Critical Xian Aircraft Design and Research Institute of AVIC
Priority to CN201611239587.7A priority Critical patent/CN106762880A/en
Publication of CN106762880A publication Critical patent/CN106762880A/en
Pending legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15BSYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B11/00Servomotor systems without provision for follow-up action; Circuits therefor
    • F15B11/08Servomotor systems without provision for follow-up action; Circuits therefor with only one servomotor

Abstract

The invention discloses a kind of airplane tail pillar hydraulic pressure folding and unfolding control system, it is characterised in that including hydraulic oil-returning 1, hydraulic pressure oil 2, choke valve 3, hydraulic buttery valve 4, buffer 5, commutation valve 6, hydraulic oil lock 7, tail pillar retractable actuating cylinder 8;Wherein, throttled when buffer 5 puts down, be free direction when in receipts;Choke valve 3 is provided with before hydraulic buttery valve 4;Tail pillar is putting down pipeline setting hydraulic oil lock 7, prevent aircraft from being waved in handling goods, tail pillar puts down, hydraulic buttery valve 4 is powered, after high pressure liquid force feed flows through hydraulic buttery valve 4 from choke valve 3, enter the rodless cavity of tail pillar retractable actuating cylinder 8 through hydraulic oil lock 7 all the way, commutation valve 6 commutates all the way, so as to the rod chamber of tail pillar retractable actuating cylinder 8 and rodless cavity be linked up, the fluid of rod chamber causes counter-pressure and ensures that tail pillar steadily puts down;The principle of the invention is simple, can effectively improve use reliability and the life-span of tail corbeling.

Description

A kind of airplane tail pillar hydraulic pressure folding and unfolding control system
Technical field
The invention belongs to plane hydraulic system technical field, and in particular to a kind of airplane tail pillar hydraulic pressure folding and unfolding control system System.
Background technology
For the tail struts that machinery drives uplock, the movement of falling object of moment of unlocking can cause tail pillar to put down Fast retractable actuating cylinder pulling vacuum phenomenon, in pressure oil into that tail pillar can be caused to produce rebound phenomenon behind the chamber of pressurized strut two, easily Cause the damage of structure.
The content of the invention
Goal of the invention:For the problem that current airplane tail pillar hydraulic pressure extension and retraction system is present, it is proposed that a kind of airplane tail branch Post hydraulic pressure folding and unfolding control system
Technical scheme:A kind of airplane tail pillar hydraulic pressure folding and unfolding control system, it is characterised in that including hydraulic oil-returning 1, hydraulic pressure Pressure oil 2, choke valve 3, hydraulic buttery valve 4, buffer 5, commutate valve 6, hydraulic oil lock 7, tail pillar retractable actuating cylinder 8;Its In, throttled when buffer 5 puts down, it is free direction when in receipts;Choke valve 3 is provided with before hydraulic buttery valve 4;Tail pillar is putting down pipe Road sets hydraulic oil lock 7, prevents aircraft from being waved in handling goods, and tail pillar puts down, and hydraulic buttery valve 4 is powered, high pressure After hydraulic oil flows through hydraulic buttery valve 4 from choke valve 3,7 are locked into tail pillar retractable actuating cylinder 8 without bar through hydraulic oil all the way Chamber, all the way commutates commutation valve 6, so as to the rod chamber of tail pillar retractable actuating cylinder 8 and rodless cavity be linked up, the oil of rod chamber Liquid causes counter-pressure and ensures that tail pillar steadily puts down;
On tail pillar is received, hydraulic buttery valve 4 is powered, after high pressure liquid force feed flows through hydraulic buttery valve 4 from choke valve 3, through slow Rush device 5 and commutation valve 6 enters the rod chamber of tail pillar retractable actuating cylinder 8, rodless cavity of the oil return from tail pillar retractable actuating cylinder 8 Return line 1 is flowed back to through hydraulic oil lock 7 and hydraulic buttery valve 4, the piston of left and right shoe retractable actuating cylinder is moved down in oil pressure effect Move and receive left and right shoe.
Beneficial effect
The principle of the invention is simple, can effectively improve use reliability and the life-span of tail corbeling.
Brief description of the drawings
Fig. 1 is present system principle schematic.
Wherein, hydraulic oil-returning 1, hydraulic pressure oil 2, choke valve 3, hydraulic buttery valve 4, buffer 5, commutate valve 6, hydraulic pressure Oil lock 7, tail pillar retractable actuating cylinder 8.
Specific embodiment
The present invention is described in further details below.
As shown in figure 1, a kind of airplane tail pillar hydraulic pressure folding and unfolding control system of the invention, specifically includes hydraulic oil-returning 1, liquid Pressure pressure oil 2, choke valve 3, hydraulic buttery valve 4, buffer 5, commutate valve 6, hydraulic oil lock 7, tail pillar retractable actuating cylinder 8; Wherein, throttled when buffer 5 puts down, be free direction when in receipts;Choke valve 3 is provided with before hydraulic buttery valve 4;Tail pillar is putting down Pipeline sets hydraulic oil lock 7, prevents aircraft from being waved in handling goods, and tail pillar puts down, and hydraulic buttery valve 4 is powered, high After hydraulic fluid force feed flows through hydraulic buttery valve 4 from choke valve 3,7 are locked into tail pillar retractable actuating cylinder 8 without bar through hydraulic oil all the way Chamber, all the way commutates commutation valve 6, so as to the rod chamber of tail pillar retractable actuating cylinder 8 and rodless cavity be linked up, the oil of rod chamber Liquid causes counter-pressure and ensures that tail pillar steadily puts down;
On tail pillar is received, hydraulic buttery valve 4 is powered, after high pressure liquid force feed flows through hydraulic buttery valve 4 from choke valve 3, through slow Rush device 5 and commutation valve 6 enters the rod chamber of tail pillar retractable actuating cylinder 8, rodless cavity of the oil return from tail pillar retractable actuating cylinder 8 Return line 1 is flowed back to through hydraulic oil lock 7 and hydraulic buttery valve 4, the piston of left and right shoe retractable actuating cylinder is moved down in oil pressure effect Move and receive left and right shoe.

Claims (1)

1. a kind of airplane tail pillar hydraulic pressure folding and unfolding control system, it is characterised in that including hydraulic oil-returning (1), hydraulic pressure oil (2), choke valve (3), hydraulic buttery valve (4), buffer (5), commutation valve (6), hydraulic oil lock (7), tail pillar folding and unfolding start Cylinder (8);Wherein, throttled when buffer (5) puts down, be free direction when in receipts;Choke valve (3) is provided with before hydraulic buttery valve (4); Tail pillar is putting down pipeline setting hydraulic oil lock (7), prevents aircraft from being waved in handling goods, and tail pillar puts down, hydraulic pressure Magnetic valve (4) is powered, and after high pressure liquid force feed flows through hydraulic buttery valve (4) from choke valve (3), enters through hydraulic oil lock (7) all the way The rodless cavity of tail pillar retractable actuating cylinder (8), all the way will commutation valve (6) commutation, so as to by tail pillar retractable actuating cylinder (8) Rod chamber and rodless cavity are linked up, and the fluid of rod chamber causes counter-pressure and ensures that tail pillar steadily puts down;
On tail pillar is received, hydraulic buttery valve (4) is powered, after high pressure liquid force feed flows through hydraulic buttery valve (4) from choke valve (3), warp Buffer (5) and commutation valve (6) enter the rod chamber of tail pillar retractable actuating cylinder (8), and oil return is from tail pillar retractable actuating cylinder (8) rodless cavity flows back to return line (1) through hydraulic oil lock (7) and hydraulic buttery valve (4), left and right shoe retractable actuating cylinder Piston is moved under oil pressure effect and receives left and right shoe.
CN201611239587.7A 2016-12-28 2016-12-28 A kind of airplane tail pillar hydraulic pressure folding and unfolding control system Pending CN106762880A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201611239587.7A CN106762880A (en) 2016-12-28 2016-12-28 A kind of airplane tail pillar hydraulic pressure folding and unfolding control system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201611239587.7A CN106762880A (en) 2016-12-28 2016-12-28 A kind of airplane tail pillar hydraulic pressure folding and unfolding control system

Publications (1)

Publication Number Publication Date
CN106762880A true CN106762880A (en) 2017-05-31

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201611239587.7A Pending CN106762880A (en) 2016-12-28 2016-12-28 A kind of airplane tail pillar hydraulic pressure folding and unfolding control system

Country Status (1)

Country Link
CN (1) CN106762880A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110562475A (en) * 2019-09-06 2019-12-13 中国航空工业集团公司西安飞机设计研究所 control system of plane ejection traction rod

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS56131806A (en) * 1980-03-14 1981-10-15 Hitachi Constr Mach Co Ltd Oil hydraulic circuit for driving oil hydraulic cylinder
US6732513B2 (en) * 2001-09-28 2004-05-11 Kobelco Construction Machinery Co., Ltd. Rotating control circuit
CN103438037A (en) * 2013-08-06 2013-12-11 湖南星邦重工有限公司 Lifting and dropping action hydraulic system for scissor type aerial working trolley platforms
CN104500462A (en) * 2014-12-08 2015-04-08 徐州重型机械有限公司 Speed regulation device and crane superlift deploying control system
CN204739017U (en) * 2015-04-08 2015-11-04 吉林工商学院 Car lifts quick -witted hydraulic circuit
CN105134675A (en) * 2015-08-28 2015-12-09 中国铁建重工集团有限公司 Dual-power system of pumping mechanism of injection machine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS56131806A (en) * 1980-03-14 1981-10-15 Hitachi Constr Mach Co Ltd Oil hydraulic circuit for driving oil hydraulic cylinder
US6732513B2 (en) * 2001-09-28 2004-05-11 Kobelco Construction Machinery Co., Ltd. Rotating control circuit
CN103438037A (en) * 2013-08-06 2013-12-11 湖南星邦重工有限公司 Lifting and dropping action hydraulic system for scissor type aerial working trolley platforms
CN104500462A (en) * 2014-12-08 2015-04-08 徐州重型机械有限公司 Speed regulation device and crane superlift deploying control system
CN204739017U (en) * 2015-04-08 2015-11-04 吉林工商学院 Car lifts quick -witted hydraulic circuit
CN105134675A (en) * 2015-08-28 2015-12-09 中国铁建重工集团有限公司 Dual-power system of pumping mechanism of injection machine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110562475A (en) * 2019-09-06 2019-12-13 中国航空工业集团公司西安飞机设计研究所 control system of plane ejection traction rod

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Application publication date: 20170531

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