A lightweight on-board hydraulic actuator system

Abstract

The present application relates to a kind of electric drive hydraulic pump systems for light and small aircraft, belong to aircraft design field.A kind of light airborne hydraulic actuator system, the system includes electric telescopic drive, main hydraulic actuator, landing gear retraction actuator;Electric telescopic drive provides power for main hydraulic actuator;Main hydraulic actuator is communicated with landing gear retraction actuator, and both constitute loop;Landing gear retraction actuator is connected with landing gear;When the hydraulic oil in main hydraulic actuator and landing gear retraction actuator is extruded to flow, landing gear retraction actuator drives landing gear to put down or collect up.The present application has the following advantages: 1, simplifies system, improves the reliability of system, reduces system weight;2, reasonable use of energy;3, in the case of motor actuator failure, system can still effectively put down landing gear, ensure flight safety.

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of electric drive hydraulic pump systems for light and small aircraft, belong to aircraft design field. BACKGROUND

[0002] Current airborne electric hydraulic pump is by motor, small plunger pump, accumulator and other components, this set of system is derived from foreign large aircraft backup hydraulic pump, however this set of system has the disadvantages of heavy weight, large volume, it is not very suitable for light and small aircraft. And the conventional electric drive actuator has a disadvantage, that is, once motor fails, it will lead to landing gear and other important components cannot be retracted, resulting in major flight safety accidents, therefore, people try to avoid using this electric motor direct drive electric actuator to retract landing gear and other important mechanisms, however, light and small aircraft need landing gear retraction function, and in the era of future all-electric aircraft, light and small aircraft will be in a dilemma when choosing landing gear retraction actuator. SUMMARY

[0003] The purpose of the present application is to provide a light airborne hydraulic actuator system with simple structure, high reliability and high safety.

[0004] In order to achieve the above purpose, the present application adopts the following technical scheme: a light airborne hydraulic actuator system, the system comprises an electric telescopic drive, a main hydraulic actuator and a landing gear retraction actuator; the electric telescopic drive provides power for the main hydraulic actuator; the main hydraulic actuator and the landing gear retraction actuator are in communication and form a loop; the landing gear retraction actuator is connected with the landing gear; when the hydraulic oil in the main hydraulic actuator and the landing gear retraction actuator is extruded to flow, the landing gear retraction actuator drives the landing gear to be lowered or retracted.

[0005] Preferably, the main hydraulic actuator divides its inner cavity into left oil cavity and right oil cavity by actuator piston pull rod arranged inside; the electric telescopic drive is connected with the actuator piston pull rod and drives it to move left or right.

[0006] Preferably, the landing gear retraction actuator divides its inner cavity into upper oil cavity and lower oil cavity by actuator cylinder piston pull rod arranged inside, and the actuator cylinder piston pull rod is connected with the landing gear.

[0007] Preferably, the upper oil cavity is in communication with the left oil cavity or the right oil cavity, and the lower oil cavity is in communication with the right oil cavity or the left oil cavity.

[0008] Further, it further includes an emergency oil discharge switch, which is used to communicate the lower oil cavity with the outside of the machine, when emergency landing gear is needed, the emergency oil discharge switch is opened, and the hydraulic oil in the lower oil cavity can be discharged outside the machine.

[0009] Preferably, the emergency oil discharge switch is connected with the lower oil chamber and the right oil chamber or the left oil chamber.

[0010] Further, the emergency landing gear releasing mechanism is further included, which comprises a compressed air pipe, an emergency landing gear releasing switch and a compressed air bottle; one end of the compressed air pipe is connected with the left oil chamber or the right oil chamber, and the other end is connected with the compressed air bottle through the emergency landing gear releasing switch; when the emergency landing gear releasing switch is opened, the compressed air bottle increases the pressure in the upper oil chamber, pushes the actuator piston rod to move downward, and drives the landing gear to be released.

[0011] Preferably, the number of the landing gear releasing actuators is multiple, and the landing gear releasing actuators are connected in parallel.

[0012] Design principle: the system drives the actuator directly through the torque motor, pushes the hydraulic actuator to generate a hydraulic driving force, the hydraulic oil in the hydraulic actuator enters the releasing actuator of the landing gear and other components, and drives the landing gear to move up and down. The system can also be connected in parallel with the emergency pneumatic system to ensure that the landing gear can be released in the case of motor failure, to ensure safe landing, and to make the weight of the aircraft system lightest. The system is suitable for light and small manned aircraft, especially for light and small all-electric aircraft.

[0013] Compared with the prior art, the present application has the following advantages:

[0014] 1. In the whole system, a large number of electromagnetic valves, reversing valves and other hydraulic accessories do not need to be added, so that the system is simplified, the reliability of the system is improved, and the weight of the system is reduced;

[0015] 2. Compared with the traditional hydraulic system, the motor drives the plunger pump to work, which can generate higher pressure, but requires the motor to work continuously, which wastes the energy on the aircraft. The motor of the present application can be turned on as needed, which reasonably utilizes the energy.

[0016] 3. Compared with the traditional electric actuator, the present application combines the advantages of the electric actuator and the hydraulic actuator, and in the case of failure of the motor actuator, the system can still effectively release the landing gear to ensure flight safety. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is the working principle diagram of the embodiment of the present application;

[0018] Figure 1 In the figure, 1, electric telescopic drive;

[0019] 2, main hydraulic actuator; 2-1, left oil chamber; 2-2, right oil chamber; 2-3, actuator piston rod; 2-4, left working oil pipe; 2-5, compressed air pipe; 2-6, right working oil pipe;

[0020] 3, landing gear retraction actuator; 3-1, upper oil chamber; 3-2, lower oil chamber; 3-3, actuator piston rod; 3-4, upper working oil pipe; 3-5, lower working oil pipe;

[0021] 4, compressed air bottle; 5, emergency landing gear release switch; 6, emergency oil discharge switch. DETAILED DESCRIPTION

[0022] It should be noted that in the embodiment, the terms "upper", "lower", "left", "right" and the like are for the purpose of simplifying the description or description according to the drawings, and do not constitute a limitation on the present application; in addition, in the embodiment, "connection", "communication" and the like can be direct connection, communication, or connection, communication through a certain element, of course, the "connection", "communication" and the like in the embodiment should be understood in accordance with the technical solution of the embodiment.

[0023] The following will be described in detail in combination with the drawings Figure 1 Further details of the present application: a light airborne hydraulic actuator system, comprising an electric telescopic drive 1, a main hydraulic actuator 2, a landing gear retraction actuator 3, a compressed air bottle 4, an emergency landing gear release switch 5, an emergency oil discharge switch 6; the electric telescopic drive 1 provides power for the main hydraulic actuator 2; the main hydraulic actuator 2 is in communication with the landing gear retraction actuator 3, and the two form a loop; the landing gear retraction actuator 3 is connected with the landing gear; when the hydraulic oil in the main hydraulic actuator 2 and the landing gear retraction actuator 3 is extruded to flow, the landing gear retraction actuator 3 drives the landing gear to be lowered or retracted.

[0024] The specific structure is as follows:

[0025] Among them, the main hydraulic actuator 2 includes left oil chamber 2-1, right oil chamber 2-2, actuator piston rod 2-3, left working oil pipe 2-4, right working oil pipe 2-6, compressed air pipe 2-5; the actuator piston rod 2-3 divides the inner cavity of the main hydraulic actuator 2 into left oil chamber 2-1 and right oil chamber 2-2; when the actuator piston rod 2-3 moves left and right in the main hydraulic actuator 2, the volume of the left oil chamber 2-1 and the right oil chamber 2-2 also changes accordingly; the left working oil pipe 2-4 is in communication with the left oil chamber 2-1, and the right working oil pipe 2-6 is in communication with the right oil chamber; the actuator piston rod 2-3 is connected with the electric telescopic drive 1; the compressed air pipe 2-5 is in communication with the left oil chamber 2-1;

[0026] The landing gear retraction and release actuator 3 comprises an upper oil chamber 3-1, a lower oil chamber 3-2, an actuator piston rod 3-3, an upper working oil pipe 3-4 and a lower working oil pipe 3-5; the actuator piston rod 3-3 divides the inner chamber of the landing gear retraction and release actuator 3 into the upper oil chamber 3-1 and the lower oil chamber 3-2; when the actuator piston rod 3-3 moves up and down in the landing gear retraction and release actuator 3, the volume of the upper oil chamber 3-1 and the lower oil chamber 3-2 changes accordingly; one end of the upper working oil pipe 3-4 is in communication with the upper oil chamber 3-1, and the other end is in communication with the left working oil pipe 2-4; one end of the lower working oil pipe 3-5 is in communication with the lower oil chamber 3-2, and the other end is in communication with the right working oil pipe 2-6; the actuator piston rod 3-3 is connected with the landing gear; of course, the system can have multiple landing gear retraction and release actuators 3 in parallel, and the structure and principle are the same;

[0027] The emergency oil discharge switch 6 can be in communication with the lower working pipe 3-5 and the right working pipe 2-6 to ensure normal operation of the system, and can also be in communication with the lower working pipe 3-5 and the outside of the machine to ensure emergency state; the hydraulic oil in the lower oil chamber 3-2 can be discharged to the outside of the machine through the lower working oil pipe 3-5 and the emergency oil discharge switch 6 to ensure emergency landing gear release.

[0028] As a preferred embodiment of the present embodiment, the compressed air pipe 2-5, the emergency landing gear release switch 5 and the compressed air bottle 4 are combined into an emergency landing gear release mechanism; one end of the compressed air pipe 2-5 is in communication with the left oil chamber 2-1, and the other end is in communication with the compressed air bottle 4 through the emergency landing gear release switch 5; when the emergency landing gear release switch 5 is opened, the compressed air bottle 4 increases the pressure in the upper oil chamber 3-1, pushes the actuator piston rod 3-3 to move downward, and drives the landing gear to release.

[0029] The system can conveniently realize hydraulic source landing gear for electric aircraft, and has the advantages of lightest system weight and high reliability. The specific use method is as follows:

[0030] When the landing gear needs to be released, the pilot connects the landing gear switch release position, and the electric telescopic drive 1 starts to drive the actuator piston rod 2-3 to move to the left side; the hydraulic oil in the left oil chamber 2-1 is squeezed, enters the upper oil chamber 3-1 of the landing gear retraction and release actuator 3 through the left working oil pipe 2-4 and the upper working oil pipe 3-4, the pressure in the upper oil chamber 3-1 increases, the actuator piston rod 3-3 moves downward, and the landing gear is released; at this time, the hydraulic oil in the lower oil chamber 3-2 is squeezed, enters the right oil chamber 2-2 through the lower working oil pipe 3-5 and the right working oil pipe 2-6, and the landing gear release action is completed.

[0031] When the landing gear needs to be retracted, the pilot turns on the landing gear switch retraction position, and the electric telescopic drive 1 starts to drive the actuator piston pull rod 2-3 to move to the right. The hydraulic oil in the right oil chamber 2-2 is squeezed and enters the lower oil chamber 3-2 through the lower working oil pipe 3-5 and the right working oil pipe 2-6. At this time, the hydraulic oil pressure in the lower oil chamber 3-2 increases, pushing the actuator piston pull rod 3-3 to move upwards, driving the landing gear to retract. At this time, the pressure in the upper oil chamber 3-1 increases, and the hydraulic oil inside enters the left oil chamber 2-1 through the upper working oil pipe 3-4 and the left working oil pipe 2-4, completing the landing gear retraction operation.

[0032] When the landing gear needs to be retracted, the pilot turns on the landing gear switch retraction position, and the electric telescopic drive 1 starts to drive the actuator piston pull rod 2-3 to move to the right. The hydraulic oil in the right oil chamber 2-2 is squeezed and enters the lower oil chamber 3-2 through the lower working oil pipe 3-5 and the right working oil pipe 2-6. At this time, the hydraulic oil pressure in the lower oil chamber 3-2 increases, pushing the actuator piston pull rod 3-3 to move upwards, driving the landing gear to retract. At this time, the pressure in the upper oil chamber 3-1 increases, and the hydraulic oil inside enters the left oil chamber 2-1 through the upper working oil pipe 3-4 and the left working oil pipe 2-4, completing the landing gear retraction operation.

[0033] The above embodiments are only preferred embodiments of the present application and do not constitute a limitation on the present application. The positional relationship between the main hydraulic actuator 2 and the landing gear retraction actuator 3 can be adjusted accordingly according to needs. Any extension, deformation, equivalent replacement, etc. made by ordinary skilled persons in the art without departing from the principles of the present application shall be included in the protection scope of the present application.

Claims

1. A lightweight on-board hydraulic actuator system, characterized by: The system comprises an electric telescopic driver, a main hydraulic actuator, a landing gear retracting and releasing actuator and an emergency landing gear releasing mechanism; the electric telescopic driver provides power for the main hydraulic actuator; the main hydraulic actuator and the landing gear retracting and releasing actuator are in communication and form a loop; the landing gear retracting and releasing actuator is connected with the landing gear; when the hydraulic oil in the main hydraulic actuator and the landing gear retracting and releasing actuator is extruded to flow, the landing gear retracting and releasing actuator drives the landing gear to be released or retracted; The main hydraulic actuator is divided into a left oil cavity and a right oil cavity by an actuator piston rod arranged inside; the electric telescopic driver is connected with the actuator piston rod and drives the actuator piston rod to move leftward or rightward; The landing gear retracting and releasing actuator is divided into an upper oil cavity and a lower oil cavity by an actuator cylinder piston rod arranged inside; the actuator cylinder piston rod is connected with the landing gear; The emergency landing gear releasing mechanism comprises a compressed air pipe, an emergency landing gear releasing switch and a compressed air bottle; one end of the compressed air pipe is in communication with the left oil cavity or the right oil cavity, and the other end is in communication with the compressed air bottle through the emergency landing gear releasing switch; when the emergency landing gear releasing switch is opened, the compressed air bottle increases the pressure in the upper oil cavity, drives the actuator cylinder piston rod to move downward and drives the landing gear to be released.

2. The lightweight on-board hydraulic actuator system of claim 1, wherein: The upper oil cavity is in communication with the left oil cavity or the right oil cavity, and the lower oil cavity is in communication with the right oil cavity or the left oil cavity.

3. The lightweight on-board hydraulic actuator system of claim 1, wherein: The emergency oil discharging switch is used to communicate the lower oil cavity with the outside of the machine; when the emergency landing gear needs to be released, the emergency oil discharging switch is opened, and the hydraulic oil in the lower oil cavity can be discharged to the outside of the machine.

4. The lightweight on-board hydraulic actuator system of claim 3, wherein: The emergency oil discharging switch communicates the lower oil cavity with the right oil cavity or the left oil cavity.

5. The lightweight on-board hydraulic actuator system of claim 1, wherein: The number of the landing gear retracting and releasing actuators is multiple, and the landing gear retracting and releasing actuators are in parallel.

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