CN119240038A - A distributed dual-redundant hydraulic energy system for UAV landing gear - Google Patents
A distributed dual-redundant hydraulic energy system for UAV landing gear Download PDFInfo
- Publication number
- CN119240038A CN119240038A CN202411532160.0A CN202411532160A CN119240038A CN 119240038 A CN119240038 A CN 119240038A CN 202411532160 A CN202411532160 A CN 202411532160A CN 119240038 A CN119240038 A CN 119240038A
- Authority
- CN
- China
- Prior art keywords
- main
- module
- landing gear
- brake
- auxiliary
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000003921 oil Substances 0.000 claims description 63
- 238000006243 chemical reaction Methods 0.000 claims description 19
- 230000009977 dual effect Effects 0.000 claims description 10
- 239000013589 supplement Substances 0.000 claims description 3
- 239000010720 hydraulic oil Substances 0.000 claims description 2
- 230000007246 mechanism Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U60/00—Undercarriages
- B64U60/40—Undercarriages foldable or retractable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
本申请提供一种无人机起落架分布式双余度液压能源系统，属于无人机刹车系统技术领域，该系统包括：主能源模块、辅助能源模块、起落架收放与限位模块和刹车执行模块，所述主能源模块分别连接所述辅助能源模块、起落架收放与限位模块和刹车执行模块，所述辅助能源模块分别连接所述起落架收放与限位模块和刹车执行模块；当液压能源系统正常工作时，所述主能源模块为辅助能源模块补压，同时对起落架收放与限位模块的起落架收放作动筒及限位锁作动筒和主起刹车的供压；当主能源模块故障时，辅助能源模块对起落架收放与限位模块的起落架收放作动筒及限位锁作动筒和主起刹车的供压。本申请可解决全电飞机无液压源的问题，克服了系统的可靠性问题。
The present application provides a distributed dual-redundancy hydraulic energy system for a UAV landing gear, belonging to the technical field of UAV brake systems, the system includes: a main energy module, an auxiliary energy module, a landing gear retraction and limit module and a brake execution module, the main energy module is respectively connected to the auxiliary energy module, the landing gear retraction and limit module and the brake execution module, the auxiliary energy module is respectively connected to the landing gear retraction and limit module and the brake execution module; when the hydraulic energy system is working normally, the main energy module replenishes the pressure for the auxiliary energy module, and at the same time supplies pressure to the landing gear retraction and limit module's landing gear retraction and limit actuator cylinder and limit lock actuator cylinder and the main brake; when the main energy module fails, the auxiliary energy module supplies pressure to the landing gear retraction and limit actuator cylinder and limit lock actuator cylinder and the main brake of the landing gear retraction and limit module. The present application can solve the problem of no hydraulic source for all-electric aircraft and overcome the reliability problem of the system.
Description
Technical Field
The application belongs to the technical field of aircraft landing gears, and particularly relates to an unmanned aerial vehicle landing gear distributed dual-redundancy hydraulic energy system.
Background
The landing gear system of the unmanned aerial vehicle is used as an important functional system of the aircraft, has important influence on the taking-off and landing safety, and the parts needing to be actuated in the system comprise landing gear and cabin doors, limiting locks, front wheel turning mechanisms, wheel braking devices and the like. The large unmanned aerial vehicle actuating energy with a hydraulic system mostly adopts an airplane centralized hydraulic source as a driving energy, and long hydraulic pipelines are used for connecting hydraulic components and hydraulic actuators with various functions to finally drive all parts to act. However, because the hydraulic accessories have leakage and pipeline along pressure loss during operation, and the movement speed is regulated by using a throttle valve during landing gear actuation, a large amount of energy is consumed in the forms of leakage, pipeline loss and throttle heating, the energy utilization rate of hydraulic actuation is low, and meanwhile, if the unmanned aerial vehicle is faced with an unmanned aerial vehicle without a concentrated hydraulic source, the airplane cannot realize the functions of the unmanned aerial vehicle by using the existing mature and reliable hydraulic actuators, hydraulic brakes and other hydraulic elements, but the full-electric unmanned aerial vehicle without the hydraulic source can avoid the adverse factors although adopting a multi-electric technology, the current electric brake technology is still immature when being applied to the landing gear of the domestic large unmanned aerial vehicle, and the electric actuators cannot realize emergency functions which must be considered during the design of the airplane such as emergency release.
Disclosure of Invention
The application aims to provide a distributed dual-redundancy hydraulic energy system for an unmanned aerial vehicle landing gear, which aims to solve or alleviate at least one problem in the background art.
The technical scheme of the application is that the unmanned aerial vehicle landing gear distributed dual-redundancy hydraulic energy system comprises a main energy module, an auxiliary energy module, a landing gear retraction and limiting module and a brake execution module, wherein the main energy module is respectively connected with the auxiliary energy module, the landing gear retraction and limiting module and the brake execution module, and the auxiliary energy module is respectively connected with the landing gear retraction and limiting module and the brake execution module;
when the hydraulic energy system works normally, the main energy module supplements pressure for the auxiliary energy module, and simultaneously presses a landing gear retraction actuator cylinder, a limiting lock actuator cylinder and a main brake of the landing gear retraction and limiting module;
when the main energy module fails, the auxiliary energy module presses the landing gear retraction actuator cylinder of the landing gear retraction and limiting module, the limiting lock actuator cylinder and the main brake.
In an alternative embodiment of the application, the main energy module comprises an oil tank assembly, an oil return assembly, a motor pump set, a main pressure control assembly and a main accumulator, wherein one end of the oil tank assembly is sequentially connected with the motor pump set and the main pressure control module, the other end of the oil tank assembly is connected with the oil return assembly, and the main accumulator is connected with the main pressure control module.
In an alternative embodiment of the present application, the auxiliary energy module includes an oil collecting bottle, an auxiliary pressure control assembly, an auxiliary accumulator and a check valve, wherein the oil collecting bottle and the auxiliary accumulator are respectively connected to the auxiliary pressure control assembly, the auxiliary accumulator is used for pressurizing the oil collecting bottle, and the check valve is arranged between the auxiliary pressure control assembly and the main pressure control assembly, so that hydraulic oil can flow unidirectionally from the main energy module to the auxiliary energy module.
In an alternative embodiment of the application, the landing gear retraction and limiting module comprises a landing gear conversion valve, a landing gear selection valve, a front lifting retraction actuator cylinder, a first main lifting retraction actuator cylinder, a second main lifting retraction actuator cylinder, a limiting lock conversion valve, an upper lock and a lower lock;
One end of the landing gear conversion valve is respectively connected with 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 with the front lifting retraction actuator cylinder, the first main lifting retraction actuator cylinder and the second main lifting retraction actuator cylinder through the landing gear selection valve;
one end of the limit lock conversion valve is respectively connected with 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 of the limit lock conversion valve is respectively connected with the upper lock and the lower lock through the limit lock conversion valve.
In an alternative embodiment of the present application, the brake execution module includes a first brake control assembly, a second brake control assembly, a first brake selection valve, a second brake selection valve, a first main wheel brake and a second main wheel brake;
The first brake control assembly and the first brake selection valve are sequentially connected to the first main wheel brake and used for braking the first main wheel; the second brake control assembly and the second brake selection valve are sequentially connected to a second main wheel brake for braking the second main wheel;
the first brake selection valve is connected with the second brake selection valve and is connected to an auxiliary pressure control assembly of the auxiliary energy module, and the first brake control assembly and the second brake control assembly are connected to a main pressure control assembly and an oil return assembly of the main energy module respectively.
In an alternative embodiment of the application, the primary energy module is designed integrally with the auxiliary energy module.
In an alternative embodiment of the present application, the main pressure control component of the main energy module, the auxiliary pressure control component of the auxiliary energy module and the check valve are integrated into a whole to form an integrated pressure control component;
The oil tank assembly of the main energy module is connected with the motor pump set and the integrated pressure control assembly through oil pipes, the main pressure accumulator of the main energy module and the auxiliary pressure accumulator of the auxiliary energy module are integrally installed to the inherited pressure control assembly through pipelines, and the oil tank assembly, the motor pump set, the integrated pressure control assembly, the main pressure accumulator and the auxiliary pressure accumulator are integrated on a bearing structure.
The distributed dual-redundancy hydraulic energy system for the landing gear of the unmanned aerial vehicle provided by the application adopts a distributed hydraulic source, wherein the distributed hydraulic source comprises a main energy module and an auxiliary energy module, the main energy module and the auxiliary energy module are integrated, when the main energy module fails, the auxiliary energy module automatically intervenes to realize dual redundancy of the energy system, meanwhile, the problem that an all-electric aircraft does not have a hydraulic source can be solved, the reliability problem of the hydraulic energy system is solved, the main energy module and the auxiliary energy module integrally adopt an integrated scheme, the problems of overlong hydraulic pipelines, high energy efficiency, high failure rate, large weight and the like of the traditional aircraft are solved, the modular design is integrally utilized, and the modules can be separately installed, so that the installation problem of a space structure is solved.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
Fig. 1 is a frame diagram of a distributed dual redundancy hydraulic energy system for an unmanned aerial vehicle landing gear.
Fig. 2 is a schematic diagram of the integration of a main energy module and an auxiliary energy module in the present application.
Reference numerals:
100-hydraulic energy system
10-Main energy Module
11-Tank assembly
12-Oil return assembly
13-Motor pump set
14-Main pressure control assembly
15-Main accumulator
20-Auxiliary energy module
21-Oil collecting bottle
22-Auxiliary pressure control assembly
23-Auxiliary pressure accumulator
24-One-way valve
30-Landing gear retracting and limiting module
31-Landing gear switching valve
32-Landing gear selection flap
33-Front-lifting retractable actuator cylinder
34-First main jack
35-Second main jack
36-Limit lock conversion valve
37-Limit lock conversion valve
38-Upper lock
39-Lower lock
40-Brake execution module
41-First brake control Assembly
42-Second brake control assembly
43 First brake select valve
44-Second brake select valve
45-First main wheel brake
46-Second main wheel brake
200-Integrated pressure control Assembly
300-Bearing structure
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The application provides an unmanned aerial vehicle landing gear distributed dual-redundancy hydraulic energy system, which is used for solving the problems of long centralized hydraulic source pipeline, low efficiency, poor safety and heavy weight of an airplane and the problem that a full-electric airplane cannot use a mature hydraulic braking technology and an emergency problem of a landing gear retraction hydraulic actuator in the prior art.
As shown in fig. 1, the unmanned aerial vehicle landing gear distributed dual-redundancy hydraulic energy system 100 provided by the application comprises a main energy module 10, an auxiliary energy module 20, a landing gear retraction and limiting module 30 and a brake executing module 40.
The main energy module 10 comprises an oil tank assembly 11, an oil return assembly 12, a motor pump set 13, a main pressure control assembly 14 and a main pressure accumulator 15, wherein the front end of the oil tank assembly 11 is sequentially connected with the motor pump set 13 and the main pressure control module 14, the front end of the oil tank assembly 11 is connected with the oil return assembly 12 and is used for realizing stable hydraulic energy output of output pressure oil after the motor pump set 13 absorbs oil through the main pressure control module 14, and the main pressure accumulator 15 is connected to the oil tank assembly 11 through the motor pump set 13 and the main pressure control module 14 and is used for boosting the oil tank.
The auxiliary energy module 20 comprises an oil collecting bottle 21, an auxiliary pressure control assembly 22, an auxiliary pressure accumulator 23 and a one-way valve 24, wherein the oil collecting bottle 21 is connected with the auxiliary pressure control assembly 22, auxiliary pressure oil realizes stable hydraulic energy output through the auxiliary pressure control assembly 22, and the auxiliary pressure accumulator 23 is connected with the oil collecting bottle 21 through the auxiliary pressure control assembly 22 and is used for pressurizing the oil collecting bottle 21. A check valve 24 is provided between the auxiliary pressure control assembly 22 and the main pressure control assembly 14 so that pressurized oil can only flow from the main energy module 10 to the auxiliary energy module 20.
The landing gear retracting and limiting module 30 comprises a landing gear switching valve 31, a landing gear selecting valve 32, a front-lifting retracting and releasing actuator cylinder 33, a first main-lifting retracting and releasing actuator cylinder 34, a second main-lifting retracting and releasing actuator cylinder 35, a limiting lock switching valve 36, a limiting lock switching valve 37, an upper lock 38 and a lower lock 39, wherein the landing gear switching valve 31 is respectively connected with the front-lifting retracting and releasing actuator cylinder 33, the first main-lifting retracting and releasing actuator cylinder 34 and the second main-lifting retracting and releasing actuator cylinder 35 through the landing gear selecting valve 32, and the limiting lock switching valve 36 is respectively connected with the upper lock 38 and the lower lock 39 through the limiting lock switching valve 37. The front end of the landing gear conversion valve 31 is respectively connected with 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 changeover valve 36 are respectively connected to the main pressure control assembly 14 of the main power source module 10 and the auxiliary pressure control assembly 22 of the auxiliary power source module 2.
The brake execution module 40 includes a first brake control assembly 41, a second brake control assembly 42, a first brake selection valve 43, a second brake selection valve 44, a first main wheel brake 45, and a second main wheel brake 46, the first brake control assembly 41 and the first brake selection valve 43 being sequentially connected to the first main wheel brake 45 for braking the first main wheel (i.e., the left main wheel), and the second brake control assembly 42 and the second brake selection valve 44 being sequentially connected to the second main wheel brake 46 for braking the second main wheel (i.e., the right main wheel). The first brake selection valve 43 is connected to the second brake selection valve 44 and to the auxiliary pressure control assembly 22, and the first brake control assembly 41 and the second brake control assembly 42 are connected to the main pressure control assembly 14 and the oil return assembly 12 of the main power module 10, respectively, to form an oil supply and return flow path.
The output pressure of the main energy source module 10 is divided into four paths, wherein the first path is the front end of the auxiliary accumulator 23 connected to the auxiliary energy source module 20 through the one-way valve 24 to realize the pressure compensation of the auxiliary energy source, the second path is the front lifting and retracting actuator 33, the first lifting and retracting actuator 34 and the second lifting and retracting actuator 35 which are connected to the main pressure control module 14 through the landing gear switching valve 31 and the landing gear selecting valve 32 of the landing gear retraction and limiting module 30 to realize the pressure supply of each landing gear retraction actuator, the third path is the main pressure control module 14 is connected to the upper lock 38 and the lower lock 39 through the limiting lock switching valve 36 and the limiting lock switching valve 37 to realize the pressure supply of the limiting lock actuator, and the fourth path is the main pressure control module 14 is connected to the first lifting wheel brake 45 and the second lifting wheel brake 46 through the first brake control module 41, the first brake selecting valve 43 and the second brake controlling module 42 and the second brake selecting valve 44 respectively to realize the pressure supply of the main brake.
The output pressure of the auxiliary energy module 20 is divided into three paths, and the auxiliary pressure control assembly 22 is respectively connected to the connection node of the main pressure control assembly 14 of the main energy module 10 and the landing gear converting valve 31 of the landing gear retraction and limiting module 30, the connection node of the main pressure control assembly 14 and the limiting lock converting valve 36 and the connection node of the first brake selecting valve 43 and the second brake selecting valve 44, so that the pressure supply of each landing gear retraction actuator, each limiting lock actuator and the brake is realized.
When the main energy module 10 fails, the landing gear conversion valve 31 and the limit lock conversion valve 36 are automatically switched to the auxiliary energy module 20 for pressure supply so as to ensure that the landing gear and the limit lock normally work, and the main brake is switched to the auxiliary energy module 20 for working in an emergency braking state through the corresponding brake selection valve.
When the hydraulic energy system is started, the main energy module 10 automatically supplements pressure for the auxiliary energy module 10 in real time through the one-way valve 24, and the normal operation of the auxiliary energy module 20 is not affected when the main energy module 10 fails, so that the overall safety and reliability of the system are improved.
In the preferred embodiment of the application, the main energy module 10 and the auxiliary energy module 20 are integrally designed to realize stable and reliable pressure energy control and output, and the hydraulic pipeline can be greatly shortened and the number of joints can be reduced, so that the energy consumption loss and the oil leakage risk can be effectively reduced.
As shown in fig. 2, the integrated design schematic diagram of the main energy module 10 and the auxiliary energy module 20 in the application is shown, the oil tank assembly 11 is provided with an oil tank pressure accumulator 111, the oil tank pressure accumulator 111 is connected with the oil tank assembly 11 through a pipeline to realize the preliminary pressurization of the oil tank, the main pressure control assembly 14 of the main energy module 10 is integrated with the auxiliary pressure control assembly 22 and the check valve 24 of the auxiliary energy module 20 to form an integrated pressure control assembly 200, the oil tank assembly 11 is connected with the motor pump set 13 and the integrated pressure control assembly 200 through an oil pipe to realize the output of pressure oil output after the oil absorption of the motor pump set 13 through the integrated pressure control assembly 200, the main pressure accumulator 15 of the main energy module 10 and the auxiliary pressure accumulator 23 of the auxiliary energy module 20 are connected with the integrated pressure control assembly 200 through a pipeline, and the oil tank assembly 11, the motor pump set 13, the integrated pressure control assembly 200, the oil tank pressure accumulator 111, the main pressure accumulator 15 and the auxiliary pressure accumulator 23 are integrated on the bearing structure 300. When the main energy module 10 fails, the auxiliary energy module 20 can be automatically connected to work, so that dual redundancy of the energy system is realized, and finally, the dual redundancy is respectively supplied to each hydraulic actuating mechanism of the landing gear of the unmanned aerial vehicle through the actuating mechanism control assembly.
When the hydraulic energy system works, a pressure gauge can be arranged on each accumulator to detect pressure signals, a deflation valve load and a liquid level gauge can be arranged on the oil tank assembly 11 to keep the oil tank pressure and detect the oil tank liquid level, the motor pump unit 13 can supply power through a power supply and regulate the pressure through a valve group, an electromagnetic valve can be arranged on the integrated pressure control assembly to control oil reversing, the pressure sensor monitors the pressure of each subsystem, and a control valve and a sensor which are arranged on the actuating mechanism control assembly in class are used for realizing control feedback and output pressure and oil flow regulation.
In some embodiments of the present application, the main energy module 10 and the auxiliary energy module 20 may be configured as a rectangle as a whole, and may be further installed in the fuselage floor partition, so as to save space in the cabin of the aircraft, each component adopts a modular design, and each module is connected through a pipeline, and may also be flexibly split and installed according to the structure form in the fuselage, so as to optimize the installation space in the fuselage.
The distributed dual-redundancy hydraulic energy system for the landing gear of the unmanned aerial vehicle provided by the application adopts a distributed hydraulic source, wherein the distributed hydraulic source comprises a main energy module and an auxiliary energy module, the main energy module and the auxiliary energy module are integrated, when the main energy module fails, the auxiliary energy module automatically intervenes to realize dual redundancy of the energy system, meanwhile, the problem that an all-electric aircraft does not have a hydraulic source can be solved, the reliability problem of the hydraulic energy system is solved, the main energy module and the auxiliary energy module integrally adopt an integrated scheme, the problems of overlong hydraulic pipelines, high energy efficiency, high failure rate, large weight and the like of the traditional aircraft are solved, the modular design is integrally utilized, and the modules can be separately installed, so that the installation problem of a space structure is solved.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The unmanned aerial vehicle landing gear distributed dual-redundancy hydraulic energy system is characterized by comprising a main energy module, an auxiliary energy module, a landing gear retraction and limiting module and a brake execution module, wherein the main energy module is respectively connected with the auxiliary energy module, the landing gear retraction and limiting module and the brake execution module, and the auxiliary energy module is respectively connected with the landing gear retraction and limiting module and the brake execution module;
when the hydraulic energy system works normally, the main energy module supplements pressure for the auxiliary energy module, and simultaneously presses a landing gear retraction actuator cylinder, a limiting lock actuator cylinder and a main brake of the landing gear retraction and limiting module;
when the main energy module fails, the auxiliary energy module presses the landing gear retraction actuator cylinder of the landing gear retraction and limiting module, the limiting lock actuator cylinder and the main brake.
2. The unmanned aerial vehicle landing gear distributed dual-redundancy hydraulic energy system of claim 1, wherein the main energy module comprises an oil tank assembly, an oil return assembly, a motor pump set, a main pressure control assembly and a main accumulator, one end of the oil tank assembly is sequentially connected with the motor pump set and the main pressure control module, the other end of the oil tank assembly is connected with the oil return assembly, and the main accumulator is connected with the main pressure control module.
3. The unmanned aerial vehicle landing gear distributed dual redundancy hydraulic energy system of claim 2, wherein the auxiliary energy module comprises an oil collection bottle, an auxiliary pressure control assembly, an auxiliary accumulator and a check valve, the oil collection bottle and the auxiliary accumulator are respectively connected to the auxiliary pressure control assembly, the oil collection bottle is pressurized by the auxiliary accumulator, and the check valve is arranged between the auxiliary pressure control assembly and the main pressure control assembly, so that hydraulic oil flows unidirectionally from the main energy module to the auxiliary energy module.
4. The unmanned aerial vehicle landing gear distributed dual redundancy hydraulic energy system of claim 3, wherein the landing gear retraction and limiting module comprises a landing gear conversion valve, a landing gear selection valve, a front-lift retraction actuator, a first main lift retraction actuator, a second main lift retraction actuator, a limiting lock conversion valve, an upper lock and a lower lock;
One end of the landing gear conversion valve is respectively connected with 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 with the front lifting retraction actuator cylinder, the first main lifting retraction actuator cylinder and the second main lifting retraction actuator cylinder through the landing gear selection valve;
one end of the limit lock conversion valve is respectively connected with 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 of the limit lock conversion valve is respectively connected with the upper lock and the lower lock through the limit lock conversion valve.
5. The unmanned aerial vehicle landing gear distributed dual redundancy hydraulic energy system of claim 4, wherein the brake actuation module comprises a first brake control assembly, a second brake control assembly, a first brake selection valve, a second brake selection valve, a first master wheel brake, and a second master wheel brake;
The first brake control assembly and the first brake selection valve are sequentially connected to the first main wheel brake and used for braking the first main wheel; the second brake control assembly and the second brake selection valve are sequentially connected to a second main wheel brake for braking the second main wheel;
the first brake selection valve is connected with the second brake selection valve and is connected to an auxiliary pressure control assembly of the auxiliary energy module, and the first brake control assembly and the second brake control assembly are connected to a main pressure control assembly and an oil return assembly of the main energy module respectively.
6. The unmanned aerial vehicle landing gear distributed dual redundancy hydraulic energy system of any of claims 1 to 5, wherein the primary energy module is designed integrally with the auxiliary energy module.
7. The unmanned aerial vehicle landing gear distributed dual redundancy hydraulic energy system of claim 6, wherein the main pressure control assembly of the main energy module is integrated with the auxiliary pressure control assembly of the auxiliary energy module and the check valve to form an integrated pressure control assembly;
The main energy module oil tank assembly is connected with the motor pump set and the integrated pressure control assembly through oil pipes, the main accumulator of the main energy module and the auxiliary accumulator of the auxiliary energy module are integrally arranged on the integrated pressure control assembly through pipelines, and the oil tank assembly, the motor pump set, the integrated pressure control assembly, the main accumulator and the auxiliary accumulator are integrated on a bearing structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411532160.0A CN119240038A (en) | 2024-10-30 | 2024-10-30 | A distributed dual-redundant hydraulic energy system for UAV landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411532160.0A CN119240038A (en) | 2024-10-30 | 2024-10-30 | A distributed dual-redundant hydraulic energy system for UAV landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN119240038A true CN119240038A (en) | 2025-01-03 |
Family
ID=94019966
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411532160.0A Pending CN119240038A (en) | 2024-10-30 | 2024-10-30 | A distributed dual-redundant hydraulic energy system for UAV landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119240038A (en) |
-
2024
- 2024-10-30 CN CN202411532160.0A patent/CN119240038A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2020063090A1 (en) | Brake system having two independent control functions and method for controlling same | |
| CN102092472A (en) | Self-energy feeding type brake device for airplanes | |
| RU2544251C2 (en) | Aircraft control system | |
| US11440639B2 (en) | Aircraft with distributed hydraulic system | |
| CN103569352B (en) | For producing the method for hydraulic power, the application of hybrid power control unit and drive system in aircraft | |
| CN202213715U (en) | A multi-electric configuration of a hydraulic energy system of a civil aircraft | |
| CN103803063A (en) | Self-energy feedback type brake apparatus-based airplane braking system and control method thereof | |
| CN211281453U (en) | Hydraulic swing-reducing oil circuit system for turning front wheels of airplane | |
| CN106672217A (en) | Architecture of landing gear control system of aircraft | |
| CN111071436B (en) | Mechanical-hydraulic aircraft front wheel turning anti-swing system | |
| CN107140189A (en) | A kind of power-by-wire remaining is from energy regenerative brake gear | |
| CN119240038A (en) | A distributed dual-redundant hydraulic energy system for UAV landing gear | |
| EP3556652B1 (en) | Electro-hydrostatic brake control | |
| CN111824100A (en) | An Active Braking System Applied in Unmanned Formula Racing | |
| US12179728B2 (en) | Braking system | |
| CN105836112A (en) | Novel hydraulic brake system for aircraft | |
| CN119018122A (en) | Integrated electro-hydraulic brake system based on dual-core dual-control EPB and its working method | |
| CN106257060B (en) | Non-similar redundancy electric steering device | |
| CN220165686U (en) | Electric control type combined support leg control valve and support leg hydraulic system | |
| CN110588959A (en) | Local hydraulic source braking system of airplane | |
| CN217320329U (en) | Braking system and vehicle | |
| CN218564043U (en) | High-precision hydraulic system of transporting and hanging integrated vehicle | |
| CN112962710B (en) | Hydraulic system of excavator, excavator and power sharing machine group | |
| CN114321041A (en) | Airborne energy storage hydraulic system and method for electric energy hydraulic bidirectional conversion | |
| CN110562230A (en) | Novel line control hydraulic braking device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |