CN106828892A - Course of new aircraft electrohydraulic integration hatch door extension and retraction system - Google Patents

Abstract

The disclosure discloses an aircraft door retractable system, the system includes a local electro-hydraulic integrated package consisting of a motor, a hydraulic pump, a one-way valve, an accumulator, and a safety valve, and the local electro-hydraulic integrated package also includes a reversing Valves and hatch actuators. The main components of the system are concentrated near the aircraft door, and the system can be driven to work only by leading out cables from the on-board power supply. The present disclosure has forward-looking and good practicability, uses the power source to replace the hydraulic source, greatly reduces the number of pipelines in the aircraft on-board system, and improves the payload of the aircraft; the present disclosure also has good reliability and maintainability. Since the door actuation system is integrated near the aircraft door, there are few parts and low failure rate. The highly integrated module design is easy to disassemble and maintain. The present disclosure utilizes accumulator pressurization to increase the instantaneous working performance of the system. At the same time, electrical components such as motors and reversing valves are highly controllable and easy to control.

Description

A new aircraft electro-hydraulic integrated door retractable system

technical field

The disclosure belongs to the technical field of aircraft actuators, and in particular relates to an aircraft door retractable system.

Background technique

At present, the retractable and retractable actuator systems of aircraft doors all use the onboard centralized hydraulic source as the energy source, which is transmitted to the vicinity of the landing gear of the aircraft through long hydraulic pipelines. There are many and redundant systems near the landing gear, including door locks, recovery springs and other devices, resulting in a complex pipeline layout and a large number of parts near the landing gear.

With the development of aircraft technology, power-by-wire technology will definitely be one of the main research directions in the future. The electro-hydraulic integration of aircraft on-board systems is the transition from hydraulic on-board systems to fly-by-wire on-board systems, using a single power supply to replace multiple energy sources The mixed airborne energy greatly improves the energy utilization and reliability of the airborne system. As an important airborne actuator system, the aircraft door system is relatively mature in technology and widely used, but lacks room for development.

Contents of the invention

Based on this, the present disclosure discloses an aircraft door retractable system, which includes: a local electro-hydraulic integrated package, a reversing valve and a door actuator;

The local electro-hydraulic integrated package is used to provide power energy for the hatch door retractable system, and output high-pressure oil driven by the motor to drive the hatch door actuator to expand and contract.

The reversing valve is used to control the flow direction of the high-pressure oil, so that the hatch actuator works in an extended or retracted state;

The hatch actuator is used for opening and closing the landing gear hatch of the aircraft.

The present disclosure has the following beneficial effects:

(1) The present disclosure has forward-looking and good practicability, uses power supply instead of hydraulic source, greatly reduces the number of pipelines in the aircraft airborne system, and improves the payload of the aircraft

(2) The present disclosure has better reliability and maintainability. Since the door actuation system is integrated near the aircraft door, there are few parts and low failure rate. The highly integrated module design is easy to disassemble and maintain.

(3) The present disclosure has good system dynamics and controllability. Boosting the system with accumulators

Instant performance. At the same time, electrical components such as motors and reversing valves are highly controllable and easy to control.

Description of drawings

Fig. 1 is a schematic diagram of the structural principle of an aircraft door retractable system of the present disclosure;

FIG. 2 is a schematic layout diagram of an aircraft door retractable system of the present disclosure;

Fig. 3 is a schematic diagram of oil flow when the system of the present disclosure is working in an extended state;

Fig. 4 is a schematic diagram of oil flow when the system of the present disclosure works in a contracted state.

detailed description

The present disclosure will be further described below in conjunction with the accompanying drawings and implementation examples.

In one embodiment, the present disclosure discloses an aircraft door retractable system, which includes: a local electro-hydraulic package, a reversing valve, and a door actuator;

The local electro-hydraulic integrated package is used to provide power energy for the hatch door retractable system, and output high-pressure oil driven by the motor to drive the hatch door actuator to expand and contract.

The reversing valve is used to control the flow direction of the high-pressure oil, so that the hatch actuator works in an extended or retracted state;

The hatch actuator is used for opening and closing the landing gear hatch of the aircraft.

In this embodiment, the disclosure proposes to use the onboard power supply as the power source to drive the electro-hydraulic integrated actuation system integrated near the aircraft door to complete the retractable function of the door and replace the existing full hydraulic cabin of the aircraft Door retractable system. The purpose of the invention is to reduce the redundant hydraulic pipelines of the aircraft door retractable system, increase the payload of the aircraft, and improve the reliability of the system.

In one embodiment, the local electro-hydraulic integrated package includes: a motor, a hydraulic pump, a one-way valve, an accumulator, and a safety valve;

The motor drives the blades of the hydraulic pump to rotate to make the hydraulic pump work;

The hydraulic pump rotates under the drive of the motor, absorbs oil from the low-pressure oil port, and discharges oil from the high-pressure oil port, so as to output the required high-pressure oil for the system.

The one-way valve is used to prevent the oil liquid from the hatch actuator from flowing back into the hydraulic pump.

The accumulator is used to store energy, and is used to release the stored energy at the initial moment of operation of the system to overcome the static inertial force of the aircraft door;

The safety valve is used to conduct unloading when the working pressure of the hydraulic pump in the electro-hydraulic integrated package is greater than the rated value, so that the high-pressure oil port and the low-pressure oil port of the hydraulic pump are conducted, so that the excess working pressure is discharged from the high-pressure oil port. Flow to low pressure port.

More preferably, the accumulator is also used to replenish oil for the system.

In this embodiment, a local electro-hydraulic integrated package consisting of a motor, a hydraulic pump, a one-way valve, an accumulator, and a safety valve as shown in FIG. 1 , as well as a reversing valve and a hatch actuator. As shown in Figure 2, the main components of the system are concentrated near the aircraft door, and the system can be driven by simply leading out cables from the onboard power supply. When the aircraft door needs to work, the on-board power supply provides power for the entire system, and the motor works to drive the hydraulic pump to output high-pressure oil, which flows through the check valve. By controlling the port position of the reversing valve, the flow direction of the high-pressure oil is controlled, so that the hatch actuator works in the extended or contracted state. The role of the accumulator in the figure is to store energy and release the stored energy at the initial moment of system operation to overcome the static inertial force of the hatch; at the same time, the accumulator also has the function of replenishing oil for the system; when the working pressure or flow When it is greater than the rated value, the safety valve conducts and unloads to ensure the safe operation of the system.

In one embodiment, when the reversing valve works in the left position, the hatch actuator works in the extended state;

When the commutator works in the right position, the hatch actuator works in the retracted state;

When the commutator is in the neutral position, the door actuator is in a self-locking state.

In this implementation, as shown in Figure 3, the reversing valve works in the left position, and the hatch actuator works in the extended state, that is, the flow direction of the oil during the opening process of the hatch; Figure 4 shows that the reversing valve works in the right position, The door actuator works in the contracted state, which is the direction of oil flow during the door closing process. When the system is not working, cut off the connection with the onboard power supply, the reversing valve is in the neutral position, and the hatch actuator is in the self-locking state.

The description and application of the present disclosure herein are illustrative and are not intended to limit the scope of the present disclosure to the above-described embodiments. Variations and modifications of the embodiments disclosed herein are possible, and substitutions and equivalents for various components of the embodiments are known to those of ordinary skill in the art. It should be apparent to those skilled in the art that various substitutions and modifications are possible without departing from the spirit or essential characteristics of the present disclosure. Therefore, the present disclosure should not be limited to the content disclosed in the embodiments, and the protection scope of the present disclosure is subject to the scope defined in the claims.

Claims (4)

1. An aircraft door retractable system, characterized in that the system comprises: a local electro-hydraulic package, a reversing valve and a door actuator; The local electro-hydraulic integrated package is used to provide power energy for the hatch door retractable system, and output high-pressure oil driven by the motor to drive the hatch door actuator to expand and contract. The reversing valve is used to control the flow direction of the high-pressure oil, so that the hatch actuator works in an extended or retracted state; The hatch actuator is used for opening or closing the landing gear hatch of the aircraft. 2. The system according to claim 1, wherein the local electro-hydraulic integrated package includes: a motor, a hydraulic pump, a one-way valve, an accumulator, and a safety valve; The motor drives the blades of the hydraulic pump to rotate to make the hydraulic pump work; The hydraulic pump rotates under the drive of the motor, absorbs oil from the low-pressure oil port, and discharges oil from the high-pressure oil port, so as to output the required high-pressure oil for the system. The one-way valve is used to prevent the oil liquid from the hatch actuator from flowing back into the hydraulic pump. The accumulator is used to store energy, and is used to release the stored energy at the initial moment of operation of the system to overcome the static inertial force of the aircraft door; The safety valve is used to conduct unloading when the working pressure of the hydraulic pump in the electro-hydraulic integrated package is greater than the rated value, so that the high-pressure oil port and the low-pressure oil port of the hydraulic pump are conducted, so that the excess working pressure is discharged from the high-pressure oil port. Flow to low pressure port. 3. The system according to claim 2, characterized in that the accumulator is also used for supplementing the system with oil. 4. The system according to claim 1, characterized in that: when the reversing valve works in the left position, the hatch actuator works in the extended state; When the commutator works in the right position, the hatch actuator works in the retracted state; When the commutator is in the neutral position, the door actuator is in a self-locking state.