CN105620770A - Propeller feathering control method - Google Patents
Propeller feathering control method Download PDFInfo
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- CN105620770A CN105620770A CN201410591339.3A CN201410591339A CN105620770A CN 105620770 A CN105620770 A CN 105620770A CN 201410591339 A CN201410591339 A CN 201410591339A CN 105620770 A CN105620770 A CN 105620770A
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Abstract
The invention belongs to the technical field of propeller control and relates to a propeller feathering control method. A feathering control system comprises an automatic feathering system, a manual feathering system and an emergency feathering system. In order to guarantee that an engine can reliably conduct feathering parking when the engine breaks down and feathering parking needs to be conducted, the feathering control system is provided with a torque automatic feathering system and a negative-tension automatic feathering system. Under any condition, when the engine breaks down and feathering needs to be conducted, a driver can conduct manual feathering through a manual feathering button, and when both the automatic feathering system and the manual feathering system fail, the emergency feathering system is further arranged. Airplane hydraulic oil is introduced into the emergency feathering system, on one path, a feathering valve is opened to achieve feathering, and on the other path, an emergency parking valve is closed, and the engine is stopped. In order to improve the feathering efficiency under the engine on-fire condition, a fireproof handle and the feathering systems are in cross linkage, the fireproof handle is lifted up so that oil supply of the engine can be cut off, and propeller feathering can be achieved as well.
Description
Technical field
The invention belongs to propeller and control technical field, relate to the feathering control method of a kind of propeller.
Background technology
For being provided with the aircraft of variable-distance propeller, propeller is a critical system along blade control system, and the reliability along blade control system is most important to the safety of aircraft. Propeller feathering controls generally have autofeather, artificial feathering and emergent feathering, once there is engine ignition, must make electromotor feathering, otherwise, can produce bigger negative pulling force before fire extinguishing. Therefore, blow out of an engine handle and propeller feathering system carry out crosslinking be a kind of simple and direct, effectively design. The feathering system of propeller aeroplane domestic at present does not cross-link with fire prevention handle, and during engine ignition, pilot needs first feathering to stop, then draws fire prevention handle, and this technical scheme delays the optimal performance time.
Summary of the invention
It is an object of the invention to: provide a kind of propeller along blade control system, when engine failure, realize electromotor feathering safely and reliably and stop; Both automatically feathering can have been realized, it is also possible to manually realize artificial feathering or emergent feathering.
The technical scheme is that
A kind of propeller is along blade control system, including autofeather, artificial feathering and three subsystems of emergency feathering. In order to ensure when engine breakdown needs feathering to stop, electromotor can reliably stop by feathering, system is provided with moment of torsion autofeather and negative pulling force autofeather two overlaps autofeather system, when autofeather and artificial feathering all lost efficacy, is additionally provided with emergent feathering system. Emergent feathering system uses aircraft hydraulic oil to open feathering valve, it is achieved feathering.
Advantages of the present invention and beneficial effect: the present invention can realize the automatization of propeller sequence, be simultaneously provided with manual backup, and achieve the crosslinking with fire prevention system, improves the efficiency that in engine ignition situation, propeller feathering stops.
Wherein autofeather controls to have two kinds of mutual independent triggering modes, when a kind of triggering mode lost efficacy, another kind of triggering mode realizes autofeather, it is provided that the safety that feathering controls. When autofeather triggers circuit malfunction and is unsatisfactory for autofeather trigger condition, it is possible to adopt manual feathering.
It is totally independent of autofeather and artificial feathering along blade control system, it is ensured that when autofeather and artificial feathering electrical malfunction, it is possible to be reliably achieved feathering and stop it addition, emergent.
System accuracy is high with reliability, under various fault ' conditions, all can be reliably achieved feathering and stop. The core operating principle of the present invention has already been through original reason test and installation verification experimental verification, has been applied in the design of certain project demonstrator propeller feathering system.
Accompanying drawing explanation
Fig. 1 is the workflow diagram of the present invention.
Detailed description of the invention
Below in conjunction with concrete accompanying drawing, the invention will be further described.
Engine breakdown needs feathering to stop, when gasoline throttle angle prepares more than angle at moment of torsion feathering, when torque pressure is less than moment of torsion oil pressure marginal value, moment of torsion autofeather sensor is connected, electrical system is controlled, it is achieved propeller feathering, engine cut-off by feathering. When Thrust Level Angel prepares angle more than moment of torsion feathering, there is a moment of torsion oil pressure marginal value in electromotor, during lower than this marginal value, electromotor operation irregularity needs feathering to stop. Moment of torsion feathering prepares angle with moment of torsion oil pressure marginal value because electromotor is different and different, engine output torque and torque measuring mechanism determine.
If being unsatisfactory for above-mentioned condition, and gasoline throttle angle prepares more than angle at negative pulling force feathering, and the negative pulling force that propeller shaft produces exceedes negative pulling force marginal value, negative pulling force autofeather sensor is connected, electrical system is controlled, it is achieved propeller feathering, engine cut-off by feathering. It is different and different according to aircraft with negative pulling force marginal value that negative pulling force feathering prepares angle, and aircraft design unit is in order to ensure that an acceptable value is formulated in aircraft safety flight.
If being unsatisfactory for moment of torsion autofeather and negative pulling force autofeather trigger condition, artificial feathering button is manually placed in feathering position by pilot, it is achieved feathering stops; Or when passenger cabin electromotor instruction alarm parameter shows engine failure, when needing feathering to stop, passenger cabin electromotor instruction alarm parameter display electromotor does not have feathering and stops, this illustrates that now autofeather function lost efficacy, artificial feathering button is manually placed in feathering position by driver, it is achieved feathering stops. When engine ignition, pilot, without using artificial feathering button to make electromotor feathering stop, only need to directly mention fire extinguishing handle and can realize the parking of electromotor feathering.
After artificial feathering button is manually placed in feathering position or mentions fire prevention handle (during engine ignition) by pilot, passenger cabin electromotor instruction alarm parameter display electromotor does not have feathering and stops, illustrate that feathering controls electrical system and lost efficacy, emergent feathering button is manually placed in feathering position by pilot, realizes feathering parking by introducing plane hydraulic system hydraulic oil.
From accompanying drawing it can be seen that autofeather and artificial feathering have identical feathering to control electrical system, it is only that triggering mode is different. But emergent suitable blade control system is totally independent of autofeather and artificial feathering, it is ensured that when autofeather and artificial feathering electrical malfunction, is reliably achieved feathering and stops.
Claims (1)
1. a propeller feathering control method, is characterized by, described control method comprises the steps:
Step one: autofeather
Step 1: engine breakdown, when gasoline throttle angle prepares more than angle at moment of torsion feathering, when torque pressure is less than moment of torsion oil pressure marginal value, moment of torsion autofeather is connected;
Step 2: if being unsatisfactory for the condition of step 1, when throttle lever prepares more than angle at negative pulling force feathering, and the negative pulling force that propeller shaft produces exceedes negative pulling force marginal value, negative pulling force autofeather is connected;
Step 2: artificial feathering
If the trigger condition being unsatisfactory in step one autofeather, the artificial feathering button of driver's manual ON, it is achieved artificial feathering; Or during autofeather disabler, the artificial feathering button of driver's manual ON, it is achieved artificial feathering;
If engine ignition, driver need not connect artificial feathering button, directly mentions fire prevention handle and can realize feathering parking;
Step 3: emergent feathering
If after artificial feathering connection, electromotor does not have feathering to stop, driver needs the emergent feathering switch of manual ON, realizes feathering by introducing aircraft hydraulic oil and stops.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410591339.3A CN105620770A (en) | 2014-10-28 | 2014-10-28 | Propeller feathering control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410591339.3A CN105620770A (en) | 2014-10-28 | 2014-10-28 | Propeller feathering control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620770A true CN105620770A (en) | 2016-06-01 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410591339.3A Pending CN105620770A (en) | 2014-10-28 | 2014-10-28 | Propeller feathering control method |
Country Status (1)
| Country | Link |
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| CN (1) | CN105620770A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107200123A (en) * | 2017-04-21 | 2017-09-26 | 北京航空航天大学 | The control system and method for many rotor electric propeller feathering modes in a kind of combined type aircraft |
| CN108116685A (en) * | 2017-12-22 | 2018-06-05 | 中国航发南方工业有限公司 | Negative pulling force autofeather system trigger architecture |
| CN108177785A (en) * | 2017-12-07 | 2018-06-19 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of propeller autofeather control method based on state machine |
| FR3066472A1 (en) * | 2017-05-18 | 2018-11-23 | Safran Aircraft Engines | TURBOMACHINE MODULE COMPRISING A ROTOR WITH VARIABLE SHAFT BLADES |
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| GB1127856A (en) * | 1967-07-01 | 1968-09-18 | Rolls Royce | Improvements in or relating to power plants for aircraft |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107200123A (en) * | 2017-04-21 | 2017-09-26 | 北京航空航天大学 | The control system and method for many rotor electric propeller feathering modes in a kind of combined type aircraft |
| CN107200123B (en) * | 2017-04-21 | 2019-09-06 | 北京航空航天大学 | The control system and method for more rotor electric propeller feathering modes in a kind of combined type aircraft |
| FR3066472A1 (en) * | 2017-05-18 | 2018-11-23 | Safran Aircraft Engines | TURBOMACHINE MODULE COMPRISING A ROTOR WITH VARIABLE SHAFT BLADES |
| US10907486B2 (en) | 2017-05-18 | 2021-02-02 | Safran Aircraft Engines | Turbomachine module comprising a rotor supporting pitchable blades |
| CN108177785A (en) * | 2017-12-07 | 2018-06-19 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of propeller autofeather control method based on state machine |
| CN108116685A (en) * | 2017-12-22 | 2018-06-05 | 中国航发南方工业有限公司 | Negative pulling force autofeather system trigger architecture |
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