CN114313302B - High-reliability aeroengine power housing opening actuation system and method - Google Patents
High-reliability aeroengine power housing opening actuation system and method Download PDFInfo
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- CN114313302B CN114313302B CN202111592212.XA CN202111592212A CN114313302B CN 114313302 B CN114313302 B CN 114313302B CN 202111592212 A CN202111592212 A CN 202111592212A CN 114313302 B CN114313302 B CN 114313302B
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Abstract
The invention belongs to the field of hydraulic pressure, and discloses a high-reliability opening and actuating system and method for an aircraft engine power housing, wherein the system comprises a controller, a motor pump, a control valve, an actuator and a follow-up stay rod; an actuator and a follow-up supporting rod are arranged under each fan cover and each reverse thrust cover, the controller is connected with and controls the motor pump, and the motor pump drives each actuator to work through the control valve and struts the corresponding fan cover or the reverse thrust cover respectively, and the follow-up supporting rod stretches and supports the corresponding fan cover or the reverse thrust cover in a follow-up mode. The technical scheme of the high-reliability aeroengine power housing opening actuation can solve the problems of difficulty in manually opening the fan housing and thrust reverser when the large engine needs ground maintenance; the invention combines a plurality of supporting modes, has high reliability and solves the potential safety hazard.
Description
Technical Field
The invention belongs to the field of hydraulic pressure, relates to a high-reliability aero-engine power housing opening actuation technical scheme, and particularly relates to a high-reliability aero-engine power housing opening actuation system and method.
Background
The fan cover and the thrust reverser of the large aircraft engine are heavier, and can not be opened in a manual mode when the engine is maintained on the ground, so that a set of actuating system is required to prop the fan cover and the thrust reverser open, and a maintainer can maintain or repair the engine on the ground. In the open state of the fan housing and the thrust reverser housing, the actuation system must have a high reliability to ensure the safety of maintenance personnel, preventing equipment damage.
The traditional technical scheme is that an actuating cylinder is matched with a manual supporting rod, the actuating cylinder is used for supporting the fan cover and the reverse thrust cover, and then the manual supporting rod is used for supporting the fan cover and the reverse thrust cover.
The above conventional technical solution has the following disadvantages: firstly, in the process, the actuator cylinder needs to continuously press, so that the manual support rod can be manually installed, two persons are needed to cooperate to complete the operation, one person continuously controls the actuator cylinder, and the other person installs the manual support rod; the second problem is the problem of safety, namely the supporting is accomplished by the manual bracing piece to the strut state of fan housing and thrust reverser's of traditional technical scheme entirely, does not have the insurance measure, and maintenance personal work is in fan housing and thrust reverser below, if the manual bracing piece goes out the problem and will bring very big potential safety hazard.
Disclosure of Invention
The purpose of the invention is that: in order to solve the problems, the invention provides a high-reliability opening actuation system and a high-reliability opening actuation method for a power housing of an aeroengine, which are used for opening a fan housing and a thrust reverser during ground maintenance of a large engine, can solve the problem that the fan housing and the thrust reverser are difficult to manually open during ground maintenance and maintenance of the large engine, and has high reliability.
The technical scheme of the invention is as follows:
a high-reliability aeroengine power housing opening actuating system comprises a controller, a motor pump, a control valve, an actuator and a follow-up stay rod; an actuator and a follow-up supporting rod are arranged under each fan cover and each reverse thrust cover, the controller is connected with and controls the motor pump, and the motor pump drives each actuator to work through the control valve and struts the corresponding fan cover or the reverse thrust cover respectively, and the follow-up supporting rod stretches and supports the corresponding fan cover or the reverse thrust cover in a follow-up mode.
Further, the actuator is an actuator with a locking function, when the stay bar of the actuator rises to the highest position, the stay bar of the actuator falls back to be limited, and at the moment, the actuator is kept in a unfolding state under no hydraulic support.
Further, the fan cover also comprises a manual stay bar, and when each fan cover is completely unfolded, the manual stay bar is arranged for auxiliary support.
Further, the manual stay bar is of a telescopic structure, and a mechanical lock is arranged in the manual stay bar.
Further, the fan cover is divided into a left fan cover and a right fan cover, the reverse thrust cover is divided into a left reverse thrust cover and a right reverse thrust cover, and the controller is provided with four corresponding control buttons corresponding to support control of different fan covers and reverse thrust covers.
Further, the motor pump is respectively connected with the actuators of the left fan cover, the right fan cover, the left reverse thrust cover and the right reverse thrust cover through four control valves, and the four control valves are independently controlled by four control buttons of the controller.
Further, the motor in the motor pump is an alternating current asynchronous motor.
Further, an oil outlet of the motor pump is provided with a safety valve.
A method for starting an actuating system of a power housing of an aeroengine with high reliability includes the steps of starting a power supply of a controller, starting a motor pump, starting an actuator of the fan housing in sequence, starting the actuator of a reverse thrust housing after the fan housing is completely opened and fixed, and finishing the opening and fixing of the reverse thrust housing.
The invention has the advantages that:
1. the technical scheme of the high-reliability aeroengine power housing opening actuation can solve the problems of difficulty in manually opening the fan housing and thrust reverser when the large engine needs ground maintenance;
2. through the combination of multiple supporting modes, the device has high reliability and solves the potential safety hazard.
Drawings
FIG. 1 is a schematic illustration of a highly reliable aircraft engine power nacelle opening actuation solution of the present invention;
the device comprises a 1-controller, a 2-motor pump, a 3-oil tank, a 4-fan control valve, a 5-back thrust control valve, a 6-follow-up stay bar, a 7-actuator and an 8-manual stay bar.
Detailed Description
This section is an embodiment of the present invention for explaining and explaining the technical solution of the present invention.
A high-reliability aeroengine power housing opening actuating system comprises a controller 1, a motor pump 2, a control valve, an actuator 7 and a follow-up stay bar 8; an actuator 7 and a follow-up supporting rod 8 are arranged under each fan cover and each reverse thrust cover, the controller 1 is connected with and controls the motor pump 2, the motor pump 2 respectively drives each actuator 7 to work through a control valve and supports the corresponding fan cover or the reverse thrust cover, and the follow-up supporting rod 8 supports the corresponding fan cover or the reverse thrust cover to extend and support in a follow-up mode.
The actuator 7 is an actuator having a locking function, and when the stay of the actuator 7 rises to the highest position, the stay of the actuator 7 is restrained from falling back, and at this time, the actuator 7 is kept in a deployed state without hydraulic support.
The fan cover also comprises a manual stay bar 9, and when each fan cover is completely unfolded, the manual stay bar 9 is arranged for auxiliary support.
The manual stay bar 8 is of a telescopic structure, and a mechanical lock is arranged inside the manual stay bar 8.
The fan covers are divided into a left fan cover and a right fan cover, the reverse thrust cover is divided into a left reverse thrust cover and a right reverse thrust cover, and the controller 1 is provided with four corresponding control buttons corresponding to the support control of different fan covers and reverse thrust covers.
The motor pump 2 is connected with the actuators 7 of the left fan housing, the right fan housing, the left thrust reverser housing and the right thrust reverser housing respectively through four control valves, and the four control valves are independently controlled by four control buttons of the controller 1.
The motor in the motor pump 2 is an ac asynchronous motor.
The oil outlet of the motor pump 2 is provided with a safety valve.
A method for starting an actuating system of a power housing of an aeroengine with high reliability includes the steps of starting a power supply of a controller, starting a motor pump, starting an actuator of the fan housing in sequence, starting the actuator of a reverse thrust housing after the fan housing is completely opened and fixed, and finishing the opening and fixing of the reverse thrust housing.
The invention is further described in detail below with reference to the drawings.
As shown in fig. 1, a high-reliability aeroengine power housing opening and actuating technical scheme comprises a controller 1, a motor pump 2, an oil tank 3, a fan housing control valve 4, a back-thrust control valve 5, a follow-up stay bar 6, a fan housing actuator 7, a manual stay bar 8, a back-thrust actuator 7, a left fan housing button, a right fan housing button, a left back-thrust housing button and a right back-thrust housing button; the follow-up stay bar 6 consists of a shell component and a piston component, and a locking mechanism is integrated in the follow-up stay bar, so that the piston component can be locked when the follow-up stay bar is in a complete extending state; the thrust reverser actuator 7 consists of a shell component and a piston component, wherein a locking/unlocking mechanism is integrated in the thrust reverser actuator, and the piston component can be locked/unlocked in a fully extended state; the controller 1 receives switch signal instructions of a left fan cover button, a right fan cover button, a left reverse push cover button and a right reverse push cover button and controls the start and stop of the motor pump 2, the on-off of the fan cover control valve 4 and the on-off of the reverse push control valve 5; the motor pump 2 sucks working medium such as hydraulic oil from the oil tank 3, pressurizes the working medium to a high pressure, and sends the working medium to the fan housing control valve 4 and the thrust reverser control valve 5; the fan cover control valve 4 controls the oil ports of the fan cover actuators 7 of the left fan cover and the right fan cover to switch between a high-pressure working medium and a low-pressure working medium, so that the fan cover actuators extend and retract under the action of external load; the reverse thrust control valve 4 controls the oil ports of the reverse thrust actuators 9 on the left reverse thrust and the right reverse thrust to switch between a high-pressure working medium and a low-pressure working medium, so that the extension of the reverse thrust actuators and the retraction under the action of external load are realized; one end of the follow-up stay bar 6 is hinged with a load left fan cover, a load right fan cover, a load left reverse pushing and a load right reverse pushing, and the other end of the follow-up stay bar is hinged with an engine case; one end of the fan cover actuator 7 is hinged with the left and right load fan covers, and the other end is hinged with the engine case; one end of the thrust reverser 7 is hinged with the load in a left thrust reverser and a right thrust reverser, and the other end is hinged with the engine case; one end of the manual stay bar 8 is hinged with the load left fan cover and the load right fan cover, and the other end is hinged with the engine case.
The motor in the motor pump 2 adopts an alternating current asynchronous motor;
the oil outlet of the motor pump 2 is provided with a safety valve;
a safety valve is arranged at the oil inlet of the thrust reverser actuator 7;
the fan cover is started first, and then the reverse thrust is started.
A high-reliability aeroengine power housing opening actuation technical scheme comprises the following opening working processes:
first, powering up the controller 1;
secondly, pressing a left fan cover button/a right fan cover button, electrifying the motor pump 2 and the fan cover electromagnetic valve 4, enabling high-pressure oil to enter the fan cover actuator 7, and driving the fan cover actuator 7 to extend out;
thirdly, when the fan cover actuator 7 extends to the limit position, the follow-up stay rod 6 connected with the left fan cover/the right fan cover is pulled to extend to the limit position and locked;
fourthly, releasing the left fan cover button/the right fan cover button, powering off the motor pump 2 and the fan cover electromagnetic valve 4, enabling the fan cover actuator 7 to return oil under low pressure, slightly retracting the fan cover actuator 7 under the action of the gravity of the fan cover, and mechanically locking the inside of the actuator;
fifthly, installing a manual stay bar 8;
step six, pressing a left thrust button/a right thrust button, electrifying the motor pump 2 and the thrust solenoid valve 5, and enabling high-pressure oil to enter the thrust actuator 7 to drive the thrust actuator 7 to extend;
seventh, when the reverse thrust actuator 7 extends to the limit position, the follow-up stay bar 6 connected with the reverse thrust is pulled to extend to the limit position and locked;
and eighth step, releasing the left thrust button/right thrust button, powering off the motor pump 2 and the thrust solenoid valve 5, enabling the thrust actuator 7 to return oil under low pressure, slightly retracting the thrust actuator 7 under the action of thrust gravity, and locking the mechanical lock inside the actuator.
A high-reliability aeroengine power housing opening and actuating technical scheme comprises the following closing working procedures:
first, powering up the controller 1;
step two, the follow-up stay bar 6 connected with the reverse pushing is unlocked manually;
thirdly, pressing a left back push button/a right back push button, wherein a back push actuator 7 fully extends out, and the internal mechanical lock is unlocked;
fourthly, releasing the left thrust button and the right thrust button, powering off the motor pump 2 and the thrust solenoid valve 5, enabling the thrust actuator 7 to return oil under low pressure, and retracting the thrust actuator 7 under the action of thrust gravity;
fifth step, the manual stay bar 8 is unlocked manually;
sixthly, manually unlocking a follow-up stay bar 6 connected with the fan cover;
seventh, the left fan cover button/the right fan cover button is pressed, the motor pump 2 and the fan cover electromagnetic valve 4 are electrified, high-pressure oil enters the fan cover actuator 7, the fan cover actuator 7 is driven to extend, and the internal mechanical lock is unlocked;
and seventhly, releasing the left fan cover button/the right fan cover button, powering off the motor pump 2 and the fan cover electromagnetic valve 4, enabling the fan cover actuator 7 to return oil under low pressure, and retracting the fan cover actuator 7 under the action of the gravity of the fan cover.
Claims (7)
1. The high-reliability aeroengine power housing opening actuation system is characterized by comprising a controller (1), a motor pump (2), a control valve, an actuator (7) and a follow-up stay bar (6); an actuator (7) and a follow-up supporting rod (6) are arranged under each fan cover and each reverse thrust cover, the controller (1) is connected with and controls the motor pump (2), the motor pump (2) respectively drives each actuator (7) to work through a control valve and supports the corresponding fan cover or the reverse thrust cover, and the follow-up supporting rod (6) extends and supports the corresponding fan cover or the reverse thrust cover in a follow-up mode; the follow-up stay bar (6) consists of a shell component and a piston component, a locking mechanism is integrated in the follow-up stay bar, the piston component can be locked when the follow-up stay bar is in a complete extending state,
the actuator (7) is an actuator with a locking function, when the stay bar of the actuator (7) rises to the highest position, the stay bar of the actuator (7) is limited in falling back, and the actuator (7) is kept in a unfolding state under no hydraulic support; the oil port of the actuator (7) is switched between a high-pressure working medium and a low-pressure working medium, so that the extension and retraction of the fan cover actuator under the action of external load are realized;
the fan cover also comprises a manual stay bar (8), and when each fan cover is completely unfolded, the manual stay bar (8) is arranged for auxiliary support.
2. A highly reliable aeroengine power casing opening actuation system according to claim 1, characterized in that the manual stay (8) is of telescopic construction, the manual stay (8) being internally provided with a mechanical lock.
3. A highly reliable opening actuation system for an aircraft engine power housing according to claim 1, wherein the fan housing is divided into a left fan housing and a right fan housing, the thrust reverser is divided into a left thrust reverser and a right thrust reverser, and the controller (1) is provided with four corresponding control buttons corresponding to the support controls of the different fan housings and thrust reversers.
4. A highly reliable aircraft engine power casing opening actuation system according to claim 3, characterized in that the motor pump (2) is connected to the actuators (7) of the left fan casing, the right fan casing, the left thrust reverser casing and the right thrust reverser casing respectively by four control valves, which are controlled individually by four control buttons of the controller (1).
5. A highly reliable aircraft engine power cover opening actuation system according to claim 1, characterized in that the motor in the motor pump (2) is an ac asynchronous motor.
6. A highly reliable opening actuation system for an aircraft engine power housing according to claim 1, characterized in that the oil outlet of the motor pump (2) is provided with a safety valve.
7. A method for opening and actuating a high-reliability power outer cover of an aeroengine, which uses the high-reliability power outer cover opening and actuating system of the aeroengine according to any one of claims 1 to 6, and is characterized in that a power supply of a controller is turned on, a motor pump is started, an actuator of a fan cover is firstly started in sequence, and after the fan cover is completely opened and fixed, the actuator of a reverse thrust cover is opened and fixed, and the opening and the fixing of the reverse thrust cover are completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111592212.XA CN114313302B (en) | 2021-12-23 | 2021-12-23 | High-reliability aeroengine power housing opening actuation system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111592212.XA CN114313302B (en) | 2021-12-23 | 2021-12-23 | High-reliability aeroengine power housing opening actuation system and method |
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| Publication Number | Publication Date |
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| CN114313302A CN114313302A (en) | 2022-04-12 |
| CN114313302B true CN114313302B (en) | 2023-12-08 |
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| CN202111592212.XA Active CN114313302B (en) | 2021-12-23 | 2021-12-23 | High-reliability aeroengine power housing opening actuation system and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103158874A (en) * | 2011-12-08 | 2013-06-19 | 空中客车营运有限公司 | Substitution device for aircraft engine |
| CN109026436A (en) * | 2018-08-22 | 2018-12-18 | 中国商用飞机有限责任公司 | Reverse thrust actuation device and turbojet nacelle |
| CN112824663A (en) * | 2019-11-20 | 2021-05-21 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030044266A1 (en) * | 2001-08-31 | 2003-03-06 | Sieto Vandillen | Power rear door interface for a vehicle having a rear entry folding ramp |
| US7090165B2 (en) * | 2003-06-02 | 2006-08-15 | Rolls-Royce Plc | Aeroengine nacelle |
| FR2887301B1 (en) * | 2005-06-16 | 2007-08-31 | Aircelle Sa | ELECTRONIC CONTROL SYSTEM FOR NACELLE |
| US9239030B2 (en) * | 2012-09-19 | 2016-01-19 | United Technologies Corporation | Nacelle electrical locking system for leading edge of openable panel |
| US9988940B2 (en) * | 2013-03-14 | 2018-06-05 | United Technologies Corporation | Latching actuation mechanism for nacelle mounted latching system |
| FR3014842B1 (en) * | 2013-12-17 | 2017-12-01 | Sagem Defense Securite | TELESCOPIC ACTUATOR AND AIRCRAFT ENGINE COMPRISING SUCH ACTUATOR |
| EP3468873B1 (en) * | 2016-06-14 | 2021-05-05 | Airbus Canada Limited Partnership | System for and method of actuating an aircraft engine nacelle cowl |
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2021
- 2021-12-23 CN CN202111592212.XA patent/CN114313302B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103158874A (en) * | 2011-12-08 | 2013-06-19 | 空中客车营运有限公司 | Substitution device for aircraft engine |
| CN109026436A (en) * | 2018-08-22 | 2018-12-18 | 中国商用飞机有限责任公司 | Reverse thrust actuation device and turbojet nacelle |
| CN112824663A (en) * | 2019-11-20 | 2021-05-21 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
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| CN114313302A (en) | 2022-04-12 |
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