CN201132607Y - Arrangement of flight control hydraulic source for airplane - Google Patents
Arrangement of flight control hydraulic source for airplane Download PDFInfo
- Publication number
- CN201132607Y CN201132607Y CNU2007203103024U CN200720310302U CN201132607Y CN 201132607 Y CN201132607 Y CN 201132607Y CN U2007203103024 U CNU2007203103024 U CN U2007203103024U CN 200720310302 U CN200720310302 U CN 200720310302U CN 201132607 Y CN201132607 Y CN 201132607Y
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- pressure source
- control
- flight
- hydraulic
- aileron
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- Expired - Lifetime
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Abstract
The utility model relates to a configuration of a flight-control hydraulic-pressure source on an airplane. The configuration of the flight-control hydraulic-pressure source comprises a left system pressure source, a right system pressure source and a flight-control system pressure source which are respectively single pressure systems. The left system pressure source is connected with an elevator and an aileron control strengthener which are positioned at the left side of the airplane; the right system pressure source is connected with the elevator and the aileron control strengthener which are positioned at the right side of the airplane; the flight-control system pressure source is connected with the elevators and the aileron control strengtheners, which are positioned at the left and the right sides of the airplane. The configuration of the flight-control hydraulic-pressure source has the advantages that when the circumstances that two engines go wrong or a flight-control hydraulic-pressure system and a right hydraulic-pressure system are leaked at the same time in the airplane occur, aileron strengtheners and an elevator actuator still have a set of hydraulic-pressure sources for supplying auxiliary force, so as to ensure the completion of the flying assignments.
Description
Technical field
The utility model relates to a kind of configuration that flies to control hydraulic power source of aircraft.
Background technology
Flight control system and aircraft flight safety are closely related, the flight control system that has servo-unit generally need dispose many cover hydraulic power sources, to guarantee when one overlaps hydraulic system fails, by standby hydraulic power source work, guarantee the flight control system normal operation, guarantee flight safety.At present, fly to control the hydraulic power source configuration and constitute the hydraulic booster that a cover hydraulic power source normally offers aircraft evelvator and aileron and arranged on left and right sides simultaneously.When hydraulic system pressure source and right general hydraulic system pressure source occurring flying to control and reveal simultaneously, after aileron servo-unit and elevator booster all transfer mechanical rigid rod to, aerodynamic loading on the rudder face is all born by chaufeur, sharply increase when the vertical and horizontal actuating force has hydraulic booster, directly influence aerial mission and finish.
Summary of the invention
The purpose of this utility model provides a kind of when flying to control hydraulic system pressure source and right general hydraulic system pressure source when revealing simultaneously, the configuration that flies to control hydraulic power source of a kind of aircraft that servo-unit still can normally be handled.Technical solution of the present utility model is, the configuration that flies to control hydraulic power source by three of left system pressure source, right system pressure source and flight control system pressure sources independently the pressure source system form, system pressure source, a left side is connected with elevating rudder, the aileron control servo-unit in aircraft left side, right system pressure source is connected with elevating rudder, the aileron control servo-unit on aircraft right side, and elevating rudder, the aileron control servo-unit of flight control system pressure source and aircraft and arranged on left and right sides join.The advantageous effect that the utlity model has, the utility model has overcome when aircraft and two engine breakdowns occur or fly to control hydraulic efficiency pressure system and right hydraulic efficiency pressure system when revealing simultaneously, aileron servo-unit and elevator booster still have a cover hydraulic power source that power-assisted is provided, and guarantee that aerial mission finishes.The utility model adopts by a cover reserve liquid potential source and gives aileron, the servo-unit voltage supply of elevator-control system left side; Another set of reserve liquid potential source is given the configuration of aileron, the servo-unit voltage supply of elevator-control system right side, and aileron, elevator-control system right side servo-unit are by flying to control hydraulic efficiency pressure system as main hydraulic power source, and right general hydraulic efficiency pressure system is as the reserve liquid potential source;
Aileron, elevator-control system left side servo-unit are by flying to control hydraulic efficiency pressure system as main hydraulic power source, left side hydraulic efficiency pressure system is as the reserve liquid potential source, flying to control hydraulic system fault and right hydraulic system fault when taking place simultaneously, the servo-unit after reconfiguring still can be worked as usual, and actuating force also can be accepted.
Description of drawings
Fig. 1 is the existing configuration structure scheme drawing of the utility model;
Fig. 2 is the utility model configuration structure scheme drawing.
The specific embodiment
The configuration that flies to control hydraulic power source by 3 three in left system pressure source 1, flight control system pressure source 2 and right system pressure source independently the pressure source system form, left system pressure source 1 is connected with elevator booster 5, the left side aileron servo-unit 6 in aircraft left side.Flight control system pressure source 2 joins with the elevating rudder and the and arranged on left and right sides aileron servo-unit of aircraft and arranged on left and right sides.Right system pressure source 3 is connected with the elevator booster 7 on aircraft right side, the aileron servo-unit 8 on right side.
Flying to control hydraulic system pressure source 2 is that the main of flight control system elevator booster 5,7 and aileron servo- unit 6,8 used pressure source, with left and right hydraulic system pressure source 1,3 as its standby pressure source.
Be provided with the master cock 4 of flight control system aileron servo-unit and elevator booster in the driving compartment.Master cock flies to control the interior hydraulic buttery valve of hydraulic efficiency pressure system and the break-make of left system and right system emergency voltage supply electromagnetic valve, connects master cock 4, flies to control hydraulic power source 2 promptly to 6,8 and two elevator booster 5,7 voltage supply of two aileron servo-units.Aloft master cock 4 is connected under flight and the normal circumstances, after flying to control hydraulic power source 2 faults, 1 emergent elevator booster 5,6 voltage supply of aileron servo-unit to the left of hydraulic system pressure source, a left side, 3 emergent elevator booster 7,8 voltage supply of aileron servo-unit to the right of right hydraulic system pressure source.
Claims (1)
1. the configuration that flies to control hydraulic power source of an aircraft, it is characterized in that, the configuration that flies to control hydraulic power source by three of left system pressure source, right system pressure source and flight control system pressure sources independently the pressure source system form, system pressure source, a left side is connected with elevating rudder, the aileron control servo-unit in aircraft left side, right system pressure source is connected with elevating rudder, the aileron control servo-unit on aircraft right side, and elevating rudder, the aileron control servo-unit of flight control system pressure source and aircraft and arranged on left and right sides join.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007203103024U CN201132607Y (en) | 2007-12-11 | 2007-12-11 | Arrangement of flight control hydraulic source for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007203103024U CN201132607Y (en) | 2007-12-11 | 2007-12-11 | Arrangement of flight control hydraulic source for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201132607Y true CN201132607Y (en) | 2008-10-15 |
Family
ID=40060881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007203103024U Expired - Lifetime CN201132607Y (en) | 2007-12-11 | 2007-12-11 | Arrangement of flight control hydraulic source for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201132607Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103818546A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Operating power steering system for airplane hydraulic control |
| CN105620730A (en) * | 2015-02-28 | 2016-06-01 | 北京航空航天大学 | Airplane hydraulic system layout based on hydraulic and power-by-wire boosting and energy storing devices |
-
2007
- 2007-12-11 CN CNU2007203103024U patent/CN201132607Y/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103818546A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Operating power steering system for airplane hydraulic control |
| CN105620730A (en) * | 2015-02-28 | 2016-06-01 | 北京航空航天大学 | Airplane hydraulic system layout based on hydraulic and power-by-wire boosting and energy storing devices |
| CN105620730B (en) * | 2015-02-28 | 2017-09-22 | 北京航空航天大学 | Plane hydraulic system layout based on hydraulic pressure and power-by-wire boosting energy storage device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: XI'AN AIRCRAFT INTERNATIONAL CORPORATION Free format text: FORMER OWNER: SHAANXI AIRCRAFT INDUSTRY (GROUP) CORPORATION LTD. Effective date: 20121011 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20121011 Address after: 723213 box 34, Shaanxi, Hanzhoung Patentee after: Xi'an aircraft, international aviation manufacturing, Limited by Share Ltd, Hanzhoung aircraft branch Address before: 723213 mailbox, Hanzhoung, Shaanxi, 34 Patentee before: Shaanxi aircraft industry (Group) Co., Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20081015 |