Distributed dual-redundancy hydraulic energy system for undercarriage of unmanned aerial vehicle

Abstract

The invention provides an unmanned aerial vehicle undercarriage distributed dual-redundancy hydraulic energy system, and belongs to the technical field of unmanned aerial vehicle braking systems.The system comprises a main energy module, an auxiliary energy module, an undercarriage folding, unfolding and limiting module and a braking execution module; the main energy module is connected with the auxiliary energy module, the undercarriage folding and unfolding and limiting module and the brake execution module. The auxiliary energy module is connected with the undercarriage folding and unfolding and limiting module and the brake execution module. When the hydraulic energy system works normally, the main energy module supplements pressure to the auxiliary energy module and supplies pressure to an undercarriage folding and unfolding actuating cylinder, a limiting lock actuating cylinder and a main brake of the undercarriage folding and unfolding and limiting module at the same time; when the main energy module breaks down, the auxiliary energy module supplies pressure to an undercarriage folding and unfolding actuating cylinder, a limiting lock actuating cylinder and a main brake of the undercarriage folding and unfolding and limiting module. The problem that an all-electric aircraft does not have a hydraulic source can be solved, and the reliability problem of a system is solved.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft landing gear, and in particular, relates to a distributed dual-redundant hydraulic energy system for unmanned aerial vehicle landing gear. Background Art

[0002] As an important functional system of an aircraft, the landing gear system of a UAV has a significant impact on the safety of take-off and landing. The parts that need to be actuated in the system include: landing gear and cabin door, limit lock, front wheel turning mechanism and wheel brake device, etc. The actuation energy of large UAVs with hydraulic systems mostly uses the aircraft's centralized hydraulic source as the driving energy. Long hydraulic pipelines connect various functional hydraulic components and hydraulic actuators, and ultimately drive the various parts to move. However, due to leakage and pressure loss along the pipeline when the hydraulic accessories are working, and the need to use a throttle valve to adjust the movement speed when the landing gear is actuated, a large amount of energy is consumed in the form of leakage, pipeline loss and throttling heat generation, and the energy utilization rate of hydraulic actuation is low. At the same time, if it is faced with a UAV without a centralized hydraulic source, the aircraft cannot use the existing mature and reliable hydraulic actuators and hydraulic brakes and other hydraulic components to achieve its functions. Although the use of multi-electric technology can avoid these unfavorable factors for all-electric UAVs without hydraulic sources, the current application of electric brake technology on the landing gear of large domestic UAVs is still immature, and electric actuators cannot achieve emergency functions such as emergency release that must be considered during aircraft design. Summary of the invention

[0003] The purpose of the present application is to provide a distributed dual-redundancy hydraulic energy system for a UAV landing gear to solve or alleviate at least one problem in the background technology.

[0004] The technical solution of the present application is: a distributed dual-redundancy hydraulic energy system for a UAV landing gear, comprising: a main energy module, an auxiliary energy module, a landing gear retracting and limiting module and a brake execution module, wherein the main energy module is respectively connected to the auxiliary energy module, the landing gear retracting and limiting module and the brake execution module, and the auxiliary energy module is respectively connected to the landing gear retracting and limiting module and the brake execution module;

[0005] When the hydraulic energy system is working normally, the main energy module supplements the pressure of the auxiliary energy module, and at the same time supplies pressure to the landing gear retraction and extension actuator cylinder and the limit lock actuator cylinder of the landing gear retraction and extension and limit module and the main brake;

[0006] When the main energy module fails, the auxiliary energy module supplies pressure to the landing gear retraction and extension actuator and limit lock actuator of the landing gear retraction and extension and limit module and the main brake.

[0007] In an optional embodiment of the present application, the main energy module includes a fuel tank assembly, an oil return assembly, a motor pump group, a main pressure control assembly and a main accumulator. One end of the fuel tank assembly is connected to the motor pump group and the main pressure control module in sequence, and the other end of the fuel tank assembly is connected to the oil return assembly. The main accumulator is connected to the main pressure control module.

[0008] In an optional embodiment of the present application, the auxiliary energy module includes an oil collecting bottle, an auxiliary pressure control assembly, an auxiliary accumulator and a one-way valve. The oil collecting bottle and the auxiliary pressure accumulator are respectively connected to the auxiliary pressure control assembly, and the oil collecting bottle is pressurized by the auxiliary accumulator. The one-way valve is arranged between the auxiliary pressure control assembly and the main pressure control assembly to allow the hydraulic oil to flow unidirectionally from the main energy module to the auxiliary energy module.

[0009] In an optional embodiment of the present application, the landing gear retraction and limit module includes a landing gear conversion valve, a landing gear selection valve, a front lifting and retraction actuator, a first main lifting and retraction actuator, a second main lifting and retraction actuator, a limit lock conversion valve, a limit lock conversion valve, an upper lock and a lower lock;

[0010] One end of the landing gear conversion valve is respectively connected to the oil return assembly and the main pressure control assembly of the main energy module, the auxiliary pressure control assembly of the auxiliary energy module, and the first brake control assembly and the second brake control assembly of the brake execution module, and the other end of the landing gear conversion valve is respectively connected to the front lifting and retracting actuator cylinder, the first main lifting and retracting actuator cylinder and the second main lifting and retracting actuator cylinder through the landing gear selection valve;

[0011] One end of the limit lock conversion valve is respectively connected to the main pressure control component of the main energy module and the auxiliary pressure control component of the auxiliary energy module, and the other end is respectively connected to the upper lock and the lower lock through the limit lock conversion valve.

[0012] In an optional embodiment of the present application, the brake execution module includes a first brake control component, a second brake control component, a first brake selection valve, a second brake selection valve, a first main starting wheel brake and a second main starting wheel brake;

[0013] The first brake control assembly and the first brake selection valve are sequentially connected to the first main starter wheel brake for braking the first main starter wheel; the second brake control assembly and the second brake selection valve are sequentially connected to the second main starter wheel brake for braking the second main starter wheel;

[0014] The first brake selection valve is connected to the second brake selection valve and connected to the auxiliary pressure control component of the auxiliary energy module. The first brake control component and the second brake control component are connected and respectively connected to the main pressure control component and the oil return component of the main energy module.

[0015] In an optional implementation manner of the present application, the main energy module and the auxiliary energy module are designed in an integrated manner.

[0016] In an optional embodiment of the present application, the main pressure control component of the main energy module is integrated with the auxiliary pressure control component and the one-way valve of the auxiliary energy module to form an integrated pressure control component;

[0017] The oil tank assembly of the main energy module is connected to the motor pump group and the integrated pressure control assembly through an oil pipe. The main accumulator of the main energy module and the auxiliary accumulator of the auxiliary energy module are integrated and installed to the inherited pressure control assembly through pipelines. The oil tank assembly, motor pump group, integrated pressure control assembly, main accumulator and auxiliary accumulator are integrated on the bearing structure.

[0018] The distributed dual-redundancy hydraulic energy system for the UAV landing gear provided in the present application adopts a distributed hydraulic source, which includes two sets of main and auxiliary energy modules. The main and auxiliary energy sets are integrated into a design. When the main energy module fails, the auxiliary energy module automatically intervenes to achieve dual redundancy of the energy system. At the same time, it can solve the problem of all-electric aircraft without hydraulic source and overcome the reliability problem of the hydraulic energy system. The main and auxiliary energy modules adopt an integrated solution as a whole, which solves the problems of traditional aircraft hydraulic pipelines being too long, low energy efficiency, high failure rate, and heavy weight. The overall modular design is used, and the modules can be installed separately, solving the problem of spatial structure installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0020] Figure 1 This is a framework diagram of the distributed dual-redundant hydraulic energy system for the UAV landing gear of this application.

[0021] Figure 2 This is a schematic diagram of the integration of the main energy module and the auxiliary energy module in this application.

[0022] Reference numerals:

[0023] 100-Hydraulic Energy System

[0024] 10-Main Energy Module

[0025] 11-Oil tank assembly

[0026] 12-Oil return assembly

[0027] 13-Motor pump set

[0028] 14-Main pressure control assembly

[0029] 15-Main accumulator

[0030] 20-Auxiliary Energy Module

[0031] 21-Oil collecting bottle

[0032] 22-Auxiliary pressure control assembly

[0033] 23-Auxiliary accumulator

[0034] 24-Check valve

[0035] 30-Landing gear retraction and limit module

[0036] 31-Landing gear conversion valve

[0037] 32-Landing gear selector valve

[0038] 33-Front lifting and retracting actuator

[0039] 34-First main lifting and retracting actuator

[0040] 35-Second main lifting and retracting actuator

[0041] 36-Limit lock conversion valve

[0042] 37-Limit lock conversion valve

[0043] 38-Upper lock

[0044] 39-Lower lock

[0045] 40-Brake actuator module

[0046] 41-First brake control assembly

[0047] 42-Second brake control assembly

[0048] 43-First brake selector valve

[0049] 44-Second brake selector valve

[0050] 45-First main starter wheel brake

[0051] 46-Second main starter wheel brake

[0052] 200-Integrated Pressure Control Assembly

[0053] 300-Bearing structure DETAILED DESCRIPTION

[0054] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0055] The present application provides a distributed dual-redundant hydraulic energy system for UAV landing gear, which is used to solve the problems of long centralized hydraulic source pipelines, low efficiency, poor safety and heavy weight in the prior art for aircraft, and the problem that all-electric aircraft cannot use mature hydraulic brake technology and landing gear retraction and extension hydraulic actuator emergency problems.

[0056] like Figure 1 As shown, the distributed dual-redundancy hydraulic energy system 100 for the UAV landing gear provided in the present application includes: a main energy module 10, an auxiliary energy module 20, a landing gear retraction and limit module 30 and a brake execution module 40.

[0057] The main energy module 10 includes an oil tank assembly 11, an oil return assembly 12, a motor pump group 13, a main pressure control assembly 14 and a main accumulator 15. The front end of the oil tank assembly 11 is connected to the motor pump group 13 and the main pressure control module 14 in sequence. The front end of the oil tank assembly 11 is connected to the oil return assembly 12, which is used to realize that the motor pump group 13 outputs pressure oil after sucking oil and realizes stable hydraulic energy output through the main pressure control module 14. The main accumulator 15 is connected to the oil tank assembly 11 through the motor pump group 13 and the main pressure control module 14 for pressurizing the oil tank.

[0058] The auxiliary energy module 20 includes an oil collecting bottle 21, an auxiliary pressure control assembly 22, an auxiliary accumulator 23 and a one-way valve 24. The oil collecting bottle 21 is connected to the auxiliary pressure control assembly 22. The auxiliary pressure oil realizes stable hydraulic energy output through the auxiliary force control assembly 22. The auxiliary accumulator 23 is connected to the oil collecting bottle 21 through the auxiliary pressure control assembly 22 to increase the pressure of the oil collecting bottle 21. The one-way valve 24 is arranged between the auxiliary pressure control assembly 22 and the main pressure control assembly 14, so that the pressure oil can only flow from the main energy module 10 to the auxiliary energy module 20.

[0059] The landing gear retracting and limiting module 30 includes a landing gear conversion valve 31, a landing gear selection valve 32, a front lifting and retracting cylinder 33, a first main lifting and retracting cylinder 34, a second main lifting and retracting cylinder 35, a limiting lock conversion valve 36, a limiting lock conversion valve 37, an upper lock 38 and a lower lock 39. The landing gear conversion valve 31 is connected to the front lifting and retracting cylinder 33, the first main lifting and retracting cylinder 34 and the second main lifting and retracting cylinder 35 through the landing gear selection valve 32, and the limiting lock conversion valve 36 is connected to the upper lock 38 and the lower lock 39 through the limiting lock conversion valve 37. The front end of the landing gear conversion valve 31 is respectively connected to the oil return assembly 12 and the main pressure control assembly 14 of the main energy module 10, the auxiliary pressure control assembly 22 of the auxiliary energy module 2, and the first brake control assembly 41 and the second brake control assembly 42 of the brake execution module 40. The front ends of the limit lock conversion valve 36 are respectively connected to the main pressure control component 14 of the main energy module 10 and the auxiliary pressure control component 22 of the auxiliary energy module 2.

[0060] The brake execution module 40 includes a first brake control component 41, a second brake control component 42, a first brake selection valve 43, a second brake selection valve 44, a first main starting wheel brake 45 and a second main starting wheel brake 46. The first brake control component 41 and the first brake selection valve 43 are sequentially connected to the first main starting wheel brake 45 for braking the first main starting wheel (i.e., the left main starting wheel); the second brake control component 42 and the second brake selection valve 44 are sequentially connected to the second main starting wheel brake 46 for braking the second main starting wheel (i.e., the right main starting wheel). The first brake selection valve 43 is connected to the second brake selection valve 44 and is connected to the auxiliary pressure control component 22. The first brake control component 41 and the second brake control component 42 are connected and are respectively connected to the main pressure control component 14 and the return oil component 12 of the main energy module 10 to form an oil supply and return flow path.

[0061] The output pressure of the main energy module 10 is divided into four routes. The first route is that the main pressure control component 14 is connected to the front end of the auxiliary accumulator 23 of the auxiliary energy module 20 through the one-way valve 24 to realize the auxiliary energy pressure compensation; the second route is that the main pressure control component 14 is connected to the front start-up and retraction cylinder 33, the first main start-up and retraction cylinder 34 and the second main start-up and retraction cylinder 35 through the landing gear conversion valve 31 and the landing gear selection valve 32 of the landing gear retraction and limit module 30 to realize the pressure supply of each landing gear retraction cylinder; the third route is that the main pressure control component 14 is connected to the upper lock 38 and the lower lock 39 through the limit lock conversion valve 36 and the limit lock conversion valve 37 to realize the pressure supply of the limit lock actuator; the fourth route is that the main pressure control component 14 is connected to the first main starter wheel brake 45 and the second main starter wheel brake 46 through the first brake control component 41, the first brake selection valve 43 and the second brake control component 42, the second brake selection valve 44 respectively to realize the pressure supply of the main brake.

[0062] The output pressure of the auxiliary energy module 20 is divided into three paths, and its auxiliary pressure control component 22 is respectively connected to the connection node between the main pressure control component 14 of the main energy module 10 and the landing gear conversion valve 31 of the landing gear retraction and limit module 30, the connection node between the main pressure control component 14 and the limit lock conversion valve 36, and the connection node between the first brake selection valve 43 and the second brake selection valve 44, so as to realize the pressure supply of each landing gear retraction actuator cylinder, limit lock actuator cylinder and brake.

[0063] The main energy module supplies pressure when the landing gear retraction and extension actuator cylinder, the limit lock actuator cylinder and the main brake are working normally. When the main energy module 10 fails, the landing gear conversion valve 31 and the limit lock conversion valve 36 automatically switch to the auxiliary energy module 20 for pressure supply to ensure the normal operation of the landing gear and the limit lock. The main brake is switched to the auxiliary energy module 20 through the corresponding brake selection valve and works in an emergency brake state.

[0064] When the hydraulic energy system is started, the main energy module 10 automatically replenishes the pressure for the auxiliary energy module 10 in real time through the one-way valve 24. When the main energy module 10 fails, it will not affect the normal operation of the auxiliary energy module 20, thereby improving the overall safety and reliability of the system.

[0065] In the preferred embodiment of the present application, the main energy module 10 and the auxiliary energy module 20 are integrated into one to achieve stable and reliable pressure energy control and output, which can greatly shorten the hydraulic pipeline and reduce the number of joints, thereby effectively reducing energy consumption loss and oil leakage risks.

[0066] like Figure 2 The figure shows a schematic diagram of the integrated design of the main energy module 10 and the auxiliary energy module 20 in the present application. The oil tank assembly 11 itself has an oil tank accumulator 111. The oil tank accumulator 111 and the oil tank assembly 11 are connected by a pipeline to achieve initial pressurization of the oil tank; the main pressure control assembly 14 of the main energy module 10 and the auxiliary pressure control assembly 22 and the one-way valve 24 of the auxiliary energy module 20 are integrated into one to form an integrated pressure control assembly 200. The oil tank assembly 11 is connected to the motor pump group 13 and the integrated pressure control assembly 200 by an oil pipe to achieve hydraulic energy output through the integrated pressure control assembly 200 after the motor pump group 13 absorbs oil. The main accumulator 15 of the main energy module 10 and the auxiliary accumulator 23 of the auxiliary energy module 20 are connected to the integrated pressure control assembly 200 by a pipeline. The oil tank assembly 11, the motor pump group 13, the integrated pressure control assembly 200 and the oil tank accumulator 111, the main accumulator 15, and the auxiliary accumulator 23 are integrated on the bearing structure 300. When the main energy module 10 fails, the auxiliary energy module 20 will automatically switch to work to achieve dual redundancy of the energy system, and finally supply power to each hydraulic actuator of the UAV landing gear through the actuator control component.

[0067] When the hydraulic energy system is working, a pressure gauge can be installed on each accumulator to detect the pressure signal, an air bleed valve and a liquid level gauge can be installed on the oil tank assembly 11 to maintain the oil tank pressure and detect the oil tank liquid level, the motor pump group 13 adjusts the pressure through power supply and valve group, a solenoid valve can be installed on the integrated pressure control assembly to control the oil reversing, and a pressure sensor monitors the pressure of each subsystem; the actuator control assembly is equipped with control valves and sensors to realize control feedback and output pressure and oil flow regulation.

[0068] In some embodiments of the present application, the main energy module 10 and the auxiliary energy module 20 can be constructed into a rectangle as a whole, and then can be installed in the fuselage floor partition to save space in the aircraft cabin. Each component adopts a modular design, and the modules are connected by pipes. They can also be flexibly split and installed according to the internal structure of the fuselage to optimize the internal installation space of the fuselage.

[0069] The distributed dual-redundancy hydraulic energy system for the UAV landing gear provided in the present application adopts a distributed hydraulic source, which includes two sets of main and auxiliary energy modules. The main and auxiliary energy sets are integrated into a design. When the main energy module fails, the auxiliary energy module automatically intervenes to achieve dual redundancy of the energy system. At the same time, it can solve the problem of all-electric aircraft without hydraulic source and overcome the reliability problem of the hydraulic energy system. The main and auxiliary energy modules adopt an integrated solution as a whole, which solves the problems of traditional aircraft hydraulic pipelines being too long, low energy efficiency, high failure rate, and heavy weight. The overall modular design is used, and the modules can be installed separately, solving the problem of spatial structure installation.

[0070] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A distributed dual-redundancy hydraulic energy system for a drone landing gear, characterized in that: include: A main energy module, an auxiliary energy module, a landing gear retracting and limiting module and a brake execution module, wherein the main energy module is respectively connected to the auxiliary energy module, the landing gear retracting and limiting module and the brake execution module, and the auxiliary energy module is respectively connected to the landing gear retracting and limiting module and the brake execution module; When the hydraulic energy system is working normally, the main energy module supplements the pressure of the auxiliary energy module, and at the same time supplies pressure to the landing gear retraction and extension actuator cylinder and the limit lock actuator cylinder of the landing gear retraction and extension and limit module and the main brake; When the main energy module fails, the auxiliary energy module supplies pressure to the landing gear retraction and extension actuator and limit lock actuator of the landing gear retraction and extension and limit module and the main brake.

2. The distributed dual-redundancy hydraulic energy system for the landing gear of an unmanned aerial vehicle according to claim 1, characterized in that: The main energy module includes a fuel tank assembly, an oil return assembly, a motor pump group, a main pressure control assembly and a main accumulator. One end of the fuel tank assembly is connected to the motor pump group and the main pressure control module in sequence, and the other end of the fuel tank assembly is connected to the oil return assembly. The main accumulator is connected to the main pressure control module.

3. The distributed dual-redundancy hydraulic energy system for the landing gear of a UAV as claimed in claim 2, characterized in that: The auxiliary energy module includes an oil collecting bottle, an auxiliary pressure control component, an auxiliary accumulator and a one-way valve. The oil collecting bottle and the auxiliary accumulator are respectively connected to the auxiliary pressure control component. The oil collecting bottle is pressurized by the auxiliary accumulator. The one-way valve is arranged between the auxiliary pressure control component and the main pressure control component to allow the hydraulic oil to flow from the main energy module to the auxiliary energy module in one direction.

4. The distributed dual-redundancy hydraulic energy system for the landing gear of a UAV as claimed in claim 3, characterized in that: The landing gear retraction and limit module includes a landing gear conversion valve, a landing gear selection valve, a front lifting and retraction actuator cylinder, a first main lifting and retraction actuator cylinder, a second main lifting and retraction actuator cylinder, a limit lock conversion valve, a limit lock conversion valve, an upper lock and a lower lock; One end of the landing gear conversion valve is respectively connected to the oil return assembly and the main pressure control assembly of the main energy module, the auxiliary pressure control assembly of the auxiliary energy module, and the first brake control assembly and the second brake control assembly of the brake execution module, and the other end of the landing gear conversion valve is respectively connected to the front lifting and retracting actuator cylinder, the first main lifting and retracting actuator cylinder and the second main lifting and retracting actuator cylinder through the landing gear selection valve; One end of the limit lock conversion valve is respectively connected to the main pressure control component of the main energy module and the auxiliary pressure control component of the auxiliary energy module, and the other end is respectively connected to the upper lock and the lower lock through the limit lock conversion valve.

5. The distributed dual-redundancy hydraulic energy system for the landing gear of an unmanned aerial vehicle according to claim 4, characterized in that: The brake execution module includes a first brake control component, a second brake control component, a first brake selection valve, a second brake selection valve, a first main starting wheel brake and a second main starting wheel brake; The first brake control assembly and the first brake selection valve are sequentially connected to the first main starter wheel brake for braking the first main starter wheel; The second brake control assembly and the second brake selection valve are sequentially connected to the second main starter wheel brake for braking the second main starter wheel; The first brake selection valve is connected to the second brake selection valve and connected to the auxiliary pressure control component of the auxiliary energy module. The first brake control component and the second brake control component are connected and respectively connected to the main pressure control component and the oil return component of the main energy module.

6. The distributed dual-redundancy hydraulic energy system for the landing gear of a UAV according to any one of claims 1 to 5, characterized in that: The main energy module and the auxiliary energy module are designed to be integrated.

7. The distributed dual-redundancy hydraulic energy system for the landing gear of a UAV as claimed in claim 6, characterized in that: The main pressure control component of the main energy module is integrated with the auxiliary pressure control component and the one-way valve of the auxiliary energy module to form an integrated pressure control component; The oil tank assembly of the main energy module is connected to the motor pump group and the integrated pressure control assembly through an oil pipe. The main accumulator of the main energy module and the auxiliary accumulator of the auxiliary energy module are integrated and installed in the integrated pressure control assembly through pipelines. The oil tank assembly, motor pump group, integrated pressure control assembly, main accumulator and auxiliary accumulator are integrated on the bearing structure.

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