CN201694388U - No-power source logical-control braking system of helicopter - Google Patents
No-power source logical-control braking system of helicopter Download PDFInfo
- Publication number
- CN201694388U CN201694388U CN2010292510145U CN201029251014U CN201694388U CN 201694388 U CN201694388 U CN 201694388U CN 2010292510145 U CN2010292510145 U CN 2010292510145U CN 201029251014 U CN201029251014 U CN 201029251014U CN 201694388 U CN201694388 U CN 201694388U
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- brake
- logic
- helicopter
- selector valve
- braking
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- Valves And Accessory Devices For Braking Systems (AREA)
Abstract
The utility model belongs to the technical field of plane hydraulic control, which relates to a hydraulic system of a helicopter for a driver to realize respective braking through logical-control priority at both sides. The hydraulic system comprises a left-foot pedal, a right-foot pedal, a left logic selective valve, a right logic selective valve and a braking device, wherein the left-foot pedal is connected with two inlets of the left logic selective valve; the right-foot pedal is connected with two inlets of the right logic selective valve; the outlets of the left logic selective valve and the right logic selective valve are both connected with the braking device; and the braking device is connected with a machine-wheel braking disk. The utility model cancels a power source device, reduces accumulaters, safety valves, braking distributing valves and pressure switches, and newly increases logic selective valves. Thus, the utility model enables the helicopter to firstly realize no-power source braking and dual-side driver's respective control, and can make priority distinguishing.
Description
Technical field
The utility model belongs to the aircraft technical field of hydraulic, and being related to helicopter provides a kind of bilateral chaufeur to realize the helicopter passive delivery logic control brake system of brake respectively by logic control priority.
Background technology
Existing helicopter brake system, a class is the bilateral brake system of pneumatic type propulsion source or hydraulic efficiency power unit.Its typical structure comprises: provide the propulsion source pump of brake pressure to connect energy storage, safety valve, brake distributing valve inlet and pressure switch simultaneously, and brake distributing valve control mouthful connecting pin pedal, the outlet of brake distributing valve connects brake gear, no Logic Priority level.Another kind of is the one-sided brake of fluid pressure type passive delivery, and the oil pocket behind the stretcher is by hydraulic hose direct connection brake gear.Because in the passive delivery brake gear, under static state, hydraulic oil is by the logical atmosphere of deflation hole, relying on pin to step on the moving piston of trying hard to recommend of generation moves hydraulic oil, therefore can't utilize T-pipe joint directly two brake lines and the mode that connects to be formed the bilateral brake system, otherwise the side fluid that touches on the brake will overflow from the opposite side pore.
Summary of the invention
The purpose of this utility model is: a kind of later-model passive hydraulic logic control system is provided, is used for helicopter passive delivery brake system, brake respectively and side chaufeur brake priority level height at ground bilateral chaufeur to satisfy helicopter.
The technical solution of the utility model is: this brake system comprises left foot pedal, right steps, left logic selector valve, right logic selector valve, brake gear, two inlets of left foot pedal and left logic selector valve join, two inlets of right steps and right logic selector valve join, the outlet of left side logic selector valve and right logic selector valve is all joined with brake gear, and brake gear and wheel braking dish join.
The utility model has the advantages that: the utility model has been cancelled power source, has reduced energy storage, has reduced safety valve, has reduced the brake distributing valve, has reduced pressure switch, has increased the logic selector valve newly.Make helicopter realize that first passive delivery brake and bilateral chaufeur control respectively and can carry out prioritization.
Description of drawings
Fig. 1: hydraulic logical control systematic schematic diagram;
Fig. 2: hydraulic control system mechanism example schematic.
The specific embodiment
Below the utility model is described in further details.Referring to Fig. 1,2, this hydraulic efficiency pressure system comprises left foot pedal 1, right steps 6, left logic selector valve 2, right logic selector valve 7, brake gear 3, left foot pedal 1 joins with two inlets of left logic selector valve 2, two inlets of right steps 6 and right logic selector valve 7 join, the outlet of left side logic selector valve 2 and right logic selector valve 7 is all joined with brake gear 3, and brake gear 3 joins with the wheel braking dish.The hydraulic services that the utility model comprises is seen Fig. 1.The logic selector valve with the brake system control just, change realization between the copilot and control brake respectively, and guarantee that a side chaufeur has high priority.
Working process of the present utility model is: chaufeur is stepped on brake pedal 1, the moving brake pedal inner chamber hydraulic oil of trying hard to recommend that pin is stepped on moves to the brake gear direction, hydraulic oil enters through selector valve 3 one side entrances, discharges from outlet, produces pressure the most at last in corresponding sealing brake gear.By selector valve 3, to brake gear 4 voltage supply, skipper 5, copilot 4 all can be implemented brake function separately, and the brake pressure value depends on that chaufeur acts on the power on the stretcher.
When copilot 4 needs to take over the brake control and touches on the brake, only need step on gently and chaufeur homonymy (left foot or right crus of diaphragm) brake pedal, can make hydraulic oil enter the opposite side inlet of logic selector valve 2, cut off the skipper simultaneously and lead to the oil circuit of brake disc, thereby realize the adapter of brake authority and realize brake function.
Claims (1)
1. helicopter passive delivery logic control brake system, it is characterized in that, this hydraulic efficiency pressure system comprises left foot pedal (1), right steps (6), left logic selector valve (2), right logic selector valve (7), brake gear (3), left foot pedal (1) joins with two inlets of left logic selector valve (2), two inlets of right steps (6) and right logic selector valve (7) join, the outlet of left side logic selector valve (2) and right logic selector valve (7) is all joined with brake gear (3), and brake gear (3) joins with wheel braking dish (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010292510145U CN201694388U (en) | 2010-02-08 | 2010-02-08 | No-power source logical-control braking system of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010292510145U CN201694388U (en) | 2010-02-08 | 2010-02-08 | No-power source logical-control braking system of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201694388U true CN201694388U (en) | 2011-01-05 |
Family
ID=43395630
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010292510145U Expired - Fee Related CN201694388U (en) | 2010-02-08 | 2010-02-08 | No-power source logical-control braking system of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201694388U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102092472A (en) * | 2011-01-20 | 2011-06-15 | 北京航空航天大学 | Self-energy feeding type brake device for airplanes |
| CN103234500A (en) * | 2013-03-29 | 2013-08-07 | 中国科学院自动化研究所 | Brake displacement measuring device for unmanned dynamic delta wing and calibration method thereof |
| CN104340362A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic training braking system for aircraft |
-
2010
- 2010-02-08 CN CN2010292510145U patent/CN201694388U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102092472A (en) * | 2011-01-20 | 2011-06-15 | 北京航空航天大学 | Self-energy feeding type brake device for airplanes |
| CN103234500A (en) * | 2013-03-29 | 2013-08-07 | 中国科学院自动化研究所 | Brake displacement measuring device for unmanned dynamic delta wing and calibration method thereof |
| CN103234500B (en) * | 2013-03-29 | 2015-05-06 | 中国科学院自动化研究所 | Brake displacement measuring device for unmanned dynamic delta wing and calibration method thereof |
| CN104340362A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic training braking system for aircraft |
| CN104340362B (en) * | 2013-08-05 | 2016-09-14 | 哈尔滨飞机工业集团有限责任公司 | Airplane hydraulic pressure coach's brake system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110105 Termination date: 20150208 |
|
| EXPY | Termination of patent right or utility model |