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 PDFInfo
- 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
Links
- 239000010720 hydraulic oil Substances 0.000 claims abstract description 16
- 239000003921 oil Substances 0.000 claims abstract description 15
- 239000007788 liquid Substances 0.000 claims abstract description 8
- 239000012530 fluid Substances 0.000 claims abstract description 3
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
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
- F15B11/08—Servomotor 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
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.
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
ID=58924007
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)
| 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)
| 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 |
-
2016
- 2016-12-28 CN CN201611239587.7A patent/CN106762880A/en active Pending
Patent Citations (6)
| 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)
| 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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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170531 |
|
| WD01 | Invention patent application deemed withdrawn after publication |