CN105620724B - Airplane hydraulic pressure layout system based on hydraulic energy storage device - Google Patents

Abstract

This application relates to an aircraft hydraulic system layout based on a hydraulic booster energy storage device, including: a spoiler aileron accumulator, used to drive the spoiler steering gear and aileron steering gear; used to drive the hatch actuator; the empennage accumulator is used to drive the rudder servo and the elevator servo respectively; among them, the spoiler aileron accumulator, the hatch accumulator and the empennage accumulator are all connected with the engine drive Pump connection to receive oil pressure input from an engine driven pump. The aircraft hydraulic system layout based on the hydraulic booster energy storage device of the present application can reduce the installed power of the aircraft.

Description

Aircraft hydraulic layout system based on hydraulic energy storage device

technical field

The present application relates to the field of hydraulic systems, in particular to an aircraft hydraulic system layout based on a hydraulic boost energy storage device.

Background technique

The aircraft hydraulic system is one of the main onboard systems of the aircraft. The control and actuators of the main control system and auxiliary control system of modern aircraft use hydraulic pressure as the energy source, and hydraulic actuators or hydraulic motors as the actuators. The aircraft hydraulic system refers to the complete set of devices on the aircraft that use oil as the working medium and rely on oil pressure to drive the actuator to complete specific manipulation actions. In order to ensure the reliability of the hydraulic system, especially to improve the reliability of the hydraulic power source of the flight control system, most modern aircraft are equipped with two (or more) independent hydraulic systems. They are respectively called public hydraulic system and power assist (manipulation) hydraulic system. For example, the hydraulic system of the Boeing 777 aircraft consists of three independent systems with a working pressure of 20.6MPa, which are used as the energy source for the flight control, lift device, thrust reverser and take-off and landing control system. In order to further improve the reliability of the hydraulic system, an emergency electric oil pump and a pneumatic pump are connected in parallel in the system. When the aircraft engine fails and the hydraulic system loses energy, the hydraulic system can continue to work by extending the emergency electric oil pump or extending the emergency pneumatic pump.

Aircraft hydraulic systems usually consist of the following components:

Pressure supply part: including main oil pump, emergency oil pump and accumulator. The main oil pump is installed on the transmission casing of the aircraft engine and driven by the engine. The accumulator is used to keep the whole system working smoothly.

Executive part: including cylinder, hydraulic motor and booster. Through them the pressure energy of the oil is converted into mechanical energy.

Control part: used to control the oil flow, pressure and movement direction of actuators in the system, including pressure valves, flow valves, directional valves and servo valves.

Auxiliary parts: the environmental conditions to ensure the normal operation of the system, and the components required to indicate the working state, including fuel tanks, conduits, oil filters, pressure gauges and radiators, etc.

The hydraulic system has the following advantages: small unit power and weight, high system transmission efficiency, simple and flexible installation, small inertia, fast dynamic response, wide control speed range, oil itself has a lubricating effect, and moving parts are not easy to wear.

As the main transmission system of modern aircraft, the hydraulic system plays an important role in ensuring the safe flight of the aircraft. The performance, stability and reliability of the hydraulic system directly affect the maneuverability and safety of the aircraft. In recent years, with the continuous improvement of the performance of military and civil aircraft, the aircraft hydraulic system has made great progress in configuration and layout. The overall aircraft puts forward more stringent requirements for the weight and volume of the hydraulic system, which forces the Develop in the direction of high pressure. Increasing the pressure of the hydraulic system can effectively reduce the weight of the system, reduce the volume of the aircraft, and improve the system response.

The pressure level of the aircraft hydraulic system is one of the most basic parameters of the aircraft hydraulic system. At present, the pressure levels of the aircraft hydraulic system are 21MPa, 28MPa, and 35MPa. At present, the improvement of the pressure level of the aircraft hydraulic system is achieved through the output of high-pressure hydraulic oil by the engine-driven pump (EDP). This method has the following disadvantages:

It is necessary to develop an engine-driven pump (EDP) with a high pressure level, and the requirements for the EDP are more stringent.

The hydraulic pipelines from the EDP to the steering gear are all high-pressure pipelines, and the requirements for the pipelines are more stringent.

EDP and piping need to withstand high pressure, resulting in thicker parts, which increase the weight of the aircraft.

Contents of the invention

A brief overview of the application is given below in order to provide a basic understanding of certain aspects of the application. It should be understood that this summary is not an exhaustive summary of the application. It is not intended to identify key or critical elements of the application, nor is it intended to limit the scope of the application. Its purpose is merely to present some concepts in a simplified form as a prelude to the more detailed description that is discussed later.

A main purpose of the present application is to provide an aircraft hydraulic system layout based on a hydraulic booster energy storage device, which can reduce the installed power of the aircraft.

According to one aspect of the present application, an aircraft hydraulic system layout based on a hydraulic booster energy storage device includes:

The spoiler aileron accumulator is used to drive the spoiler servo and aileron servo;

A door accumulator for driving the door actuator;

Empennage accumulator, used to drive the rudder servo and the elevator servo respectively;

Wherein, the spoiler aileron accumulator, the door accumulator and the empennage accumulator are all connected to the engine-driven pump for receiving oil pressure input from the engine-driven pump.

Adopt the layout of the aircraft hydraulic system based on the hydraulic boost energy storage device of the present application, increase the pressure level of the hydraulic system through the hydraulic boost energy storage device, and make the aircraft hydraulic system realize high pressure. The method of realizing high pressure is not through the engine-driven pump ( EDP) to output high-pressure hydraulic oil, but it is realized by a hydraulic booster energy storage device near the end of the valve-controlled steering gear. Moreover, the hydraulic boost energy storage device utilizes small continuous power input to realize high transient power actuation, reducing the installed power of the aircraft.

Description of drawings

The above and other objects, features and advantages of the present application will be more easily understood with reference to the following description of the embodiments of the present application in conjunction with the accompanying drawings. The components in the figures are only intended to illustrate the principles of the application. In the drawings, the same or similar technical features or components will be denoted by the same or similar reference numerals.

Fig. 1 is the schematic diagram of an embodiment of the layout of the aircraft hydraulic system based on the hydraulic booster energy storage device of the present application;

Fig. 2 is a structural diagram of an embodiment of each energy storage module in Fig. 1 .

Detailed ways

Embodiments of the present application are described below with reference to the drawings. Elements and features described in one drawing or one embodiment of the present application may be combined with elements and features shown in one or more other drawings or embodiments. It should be noted that representation and description of components and processes that are not relevant to the present application and known to those of ordinary skill in the art are omitted from the drawings and descriptions for the purpose of clarity.

Referring to FIG. 1 , it is a structural diagram of an embodiment of an aircraft hydraulic system layout based on a hydraulic booster energy storage device of the present application.

In this embodiment, the layout of the aircraft hydraulic system based on the hydraulic booster energy storage device includes:

The spoiler aileron accumulator 110 is used to drive the spoiler steering gear and the aileron steering gear;

The door accumulator 120 is used to drive the door actuator;

The empennage accumulator 140 is used to drive the rudder steering gear and the elevator steering gear respectively;

Wherein, the spoiler aileron accumulator 110 , the door accumulator 120 and the empennage accumulator 140 are all connected to the engine-driven pump for receiving oil pressure input from the engine-driven pump.

In one embodiment, in the layout of the aircraft hydraulic system based on the hydraulic booster energy storage device, the spoiler aileron accumulator 110 may include a left spoiler aileron for driving the left spoiler and the left aileron Energy storage module and right spoiler aileron energy storage module for driving right spoiler and right aileron.

The door accumulator 120 may include a left door energy storage module for driving a left door actuator and a right door energy storage module for driving a right door actuator.

The empennage accumulator 140 may include a rudder energy storage module for driving the rudder servo and an elevator energy storage module for driving the elevator servo.

In one embodiment, as shown in Figure 2, each energy storage module (i.e. left spoiler aileron energy storage module, right spoiler aileron energy storage module) Plate aileron energy storage module, left hatch energy storage module, right hatch energy storage module, rudder energy storage module and elevator energy storage module) may include electric motors, hydraulic pumps, accumulators and servo valves, respectively.

Wherein, the electric motor 1 is connected with the engine-driven pump for receiving oil pressure input from the engine-driven pump. The hydraulic pump 3 is connected to the output shaft of the motor 1 and is used to rotate driven by the motor 1 .

The servo valve 7 includes a control terminal, a first input terminal, a second input terminal, a first output terminal and a second output terminal, and the servo valve 7 is used to simultaneously control the first input terminal and the first output terminal based on an external control signal input to the control terminal The on/off of the terminal and the on/off of the second input terminal and the second output terminal. For example, when the external control signal instructs the servo valve 7 to be turned on, the first input end communicates with the first output end, and the second input end communicates with the second output end.

The hydraulic pump 3 includes an oil outlet and an oil inlet, the oil outlet is connected to the first input end of the servo valve 7 , and the oil inlet is connected to the second input end of the servo valve 7 . The accumulator 6 is connected to the oil passage between the oil outlet and the first input.

Preferably, each energy storage module may further include a one-way valve 5 connected between the accumulator 6 and the oil outlet of the hydraulic pump 3 . The one-way valve 5 is used to prevent the oil in the accumulator 6 from entering the hydraulic pump 3 .

Preferably, each energy storage module may further include a hydraulic motor 8 connected between the first output end and the second output end of the servo valve 7 .

The hydraulic motor 8 is used to perform hydraulic pressure on the left spoiler aileron, right spoiler aileron, left hatch, right hatch, rudder and elevator based on the hydraulic pressure output by the first output end and the second output end of the servo valve 7, respectively. action.

Preferably, the left spoiler aileron energy storage module, the right spoiler aileron energy storage module, the left cabin door energy storage module, the right cabin door energy storage module, the rudder energy storage module and the elevator energy storage module can also respectively include A safety valve 4 connected between the oil inlet and the oil outlet of the hydraulic pump. The safety valve 4 is used to open when the pressure difference between the oil inlet and the oil outlet is greater than a predetermined value.

Preferably, each energy storage module may further include a transmission device 2 , so that the hydraulic pump 3 is connected to the output shaft of the electric motor 1 via the transmission device 2 .

When each energy storage module of this application is working in the pressurized energy storage process, the servo valve 7 is closed, the motor 1 is working, and the hydraulic pump 3 is driven to rotate, and the hydraulic pump 3 converts the hydraulic fluid provided by the on-board oil tank into high-pressure oil. , through the one-way valve 5, and stored in the accumulator 6. Before the pressure sensor detects a high pressure state, the motor 1 keeps working at a small continuous power state. When the pressure sensor detects a high pressure state, the motor 1 reduces the speed and maintains a very low idle speed state to maintain the system high pressure state. At this point, the supercharging energy storage process ends.

When each energy storage module of the present application is working in the cabin door actuation process, the servo valve 7 is opened, the cabin door actuation requires a large transient flow rate, and the high-pressure oil stored in the accumulator 6 is released instantaneously to ensure Flow demand for door actuation. At this time, because the pressure of the accumulator 6 is released, the pressure sensor cannot detect the high pressure state, and the motor 1 keeps working at a small continuous power state until the accumulator 6 is fully charged and reaches a high pressure state.

The specific completion form of the aircraft hydraulic system layout based on the hydraulic booster energy storage device of the present application is as follows:

The left engine EDP and the right engine EDP output low-pressure hydraulic oil, which is transmitted to the steering gear through the aircraft pipeline. When it reaches the left and right spoilers, the spoiler aileron energy storage devices equipped with the left and right spoilers generate high-pressure hydraulic oil and send it to the steering gear. The left and right spoiler servos are sent to the left and right aileron servos at the same time.

The low-pressure hydraulic oil continues to be transmitted to the tail, and when it reaches the left and right hatches, the door energy storage devices configured on the left and right hatches generate high-pressure hydraulic oil and deliver it to the hatch actuators.

The low-pressure hydraulic oil continues to be transmitted to the tail, and when it reaches the left and right landing gears, the landing gear energy storage devices 130 configured on the left and right landing gears generate high-pressure hydraulic oil, which is delivered to the left and right landing gear actuators.

The low-pressure hydraulic oil continues to be transmitted to the tail, and reaches the left and right elevators and rudders. The empennage energy storage devices equipped with the left and right elevators and rudders generate high-pressure hydraulic oil, which is sent to the left and right elevators and rudders.

So far, the layout of the aircraft hydraulic system based on the hydraulic boost energy storage device is completed, and the pressure level of the aircraft hydraulic system is increased through the hydraulic boost energy storage device, so that the aircraft hydraulic system can achieve high pressure. The way to achieve high pressure is not to output high-pressure hydraulic oil through the engine-driven pump (EDP), but to achieve it through a hydraulic booster energy storage device near the end of the valve-controlled steering gear. Moreover, the hydraulic boost energy storage device utilizes small continuous power input to realize high transient power actuation, reducing the installed power of the aircraft.

The aircraft hydraulic system layout based on the hydraulic booster energy storage device of the present application has the following advantages:

The pressure level of the aircraft hydraulic system is increased through the hydraulic booster energy storage device, and there is no need to develop an engine-driven pump (EDP) with a high pressure level, which reduces the requirements for the EDP.

The hydraulic pipelines from the EDP to the hydraulic booster energy storage device in front of the steering gear are all low-pressure pipelines, which reduces the requirements for the pipelines and improves the vibration and leakage of the pipelines.

The EDP and piping are low-pressure parts, which do not require thick and high-pressure parts, which reduces the weight of the aircraft.

The pressure level of the hydraulic system is increased through the hydraulic booster energy storage device, so that the hydraulic system of the aircraft can be high-pressured, the power density of the steering gear is increased, and the size and weight of the steering gear are reduced, thereby reducing the weight of the aircraft.

The hydraulic boost energy storage device can use small continuous power input to realize high transient power actuation, which reduces the peak flow required for steering gear actuation, thereby reducing the peak flow and installed power of the aircraft.

Some embodiments of the present application have been described in detail above. As those of ordinary skill in the art can understand, all or any steps or components of the method and apparatus of the present application can be implemented in any computing device (including a processor, a storage medium, etc.) or a network of computing devices in the form of hardware, It can be realized by firmware, software or their combination, which can be realized by those of ordinary skill in the art by using their basic programming skills after understanding the content of this application, so no specific description is needed here.

Furthermore, it is obvious that any display device and any input device connected to any computing device, corresponding interfaces and control programs are undoubtedly used when the above description refers to possible external operations. In a word, the relevant hardware and software in the computer, computer system or computer network, and the hardware, firmware, software or their combination for realizing various operations in the foregoing methods of the present application constitute the equipment and its components of the present application.

Therefore, based on the above understanding, the purpose of this application can also be achieved by running a program or a group of programs on any information processing device. The information processing device may be a known general-purpose device. Therefore, the object of the present application can also be achieved only by providing a program product including program codes for realizing the method or device. That is to say, such a program product also constitutes this application, and a medium that stores or transmits such a program product also constitutes this application. Apparently, the storage or transmission medium may be any type of storage or transmission medium known to those skilled in the art or developed in the future, so it is not necessary to list all kinds of storage or transmission media here.

In the device and method of the present application, obviously, each component or each step can be decomposed, combined and/or recombined after decomposing. These decompositions and/or recombinations should be considered equivalents of this application. It should also be pointed out that the steps for executing the above series of processes can naturally be executed in chronological order according to the illustrated order, but it does not need to be executed in chronological order. Certain steps may be performed in parallel or independently of each other. Meanwhile, in the above description of the specific embodiments of the present application, the features described and/or shown for one embodiment can be used in one or more other embodiments in the same or similar manner. combination of features, or replace features in other embodiments.

It should be emphasized that the term "comprising/comprising" when used herein refers to the presence of a feature, element, step or component, but does not exclude the presence or addition of one or more other features, elements, steps or components.

Although the present application and its advantages have been described in detail, it should be understood that various changes, substitutions and alterations can be made hereto without departing from the spirit and scope of the application as defined by the appended claims. Moreover, the scope of the present application is not limited to the specific embodiments of the procedures, devices, means, methods and steps described in the specification. Those of ordinary skill in the art will readily appreciate from the disclosure of the present application that existing and future proposed embodiments that perform substantially the same function or obtain substantially the same results as the corresponding embodiments described herein can be used in accordance with the present application. The developed process, device, means, method or steps. Accordingly, the appended claims are intended to include within their scope such processes, means, means, methods or steps.

Claims (5)

1. An aircraft hydraulic system layout based on hydraulic pressure energy storage device that steps up, includes:

the spoiler energy accumulator is used for driving the spoiler steering engine and the aileron steering engine;

the cabin door energy accumulator is used for driving the cabin door actuator;

the tail wing energy storage device is used for respectively driving the rudder steering engine and the elevator steering engine;

the spoiler energy accumulator, the cabin door energy accumulator and the empennage energy accumulator are all connected with an engine-driven pump and used for receiving oil pressure input from the engine-driven pump;

the spoiler aileron energy storage device comprises a left spoiler aileron energy storage module used for driving the left spoiler and the left aileron and a right spoiler aileron energy storage module used for driving the right spoiler and the right aileron;

the cabin door energy storage device comprises a left cabin door energy storage module used for driving the left cabin door actuator and a right cabin door energy storage module used for driving the right cabin door actuator;

the empennage energy storage device comprises a rudder energy storage module used for driving a rudder steering engine and an elevator energy storage module used for driving an elevator steering engine;

left spoiler aileron energy storage module, right spoiler aileron energy storage module, left hatch door energy storage module, right hatch door energy storage module, rudder energy storage module and elevator energy storage module include respectively:

the system comprises a motor, a hydraulic pump, an accumulator and a servo valve;

wherein,

the electric motor is connected with the engine driven pump and is used for receiving oil pressure input from the engine driven pump;

the hydraulic pump is connected to an output shaft of the motor and is used for rotating under the driving of the motor;

the servo valve includes a control terminal, a first input terminal, a second input terminal, a first output terminal and a second output terminal, and is configured to simultaneously control on/off of the first input terminal and the first output terminal and on/off of the second input terminal and the second output terminal based on an external control signal input to the control terminal;

the hydraulic pump comprises an oil outlet and an oil inlet, the oil outlet is connected with a first input end of the servo valve, and the oil inlet is connected with a second input end of the servo valve;

the accumulator is connected to an oil path between the oil outlet and the first input end.

2. The hydraulic boost energy storage device-based aircraft hydraulic system layout according to claim 1, wherein the left spoiler flap energy storage module, the right spoiler flap energy storage module, the left door energy storage module, the right door energy storage module, the rudder energy storage module and the elevator energy storage module further comprise:

the one-way valve is connected between the energy accumulator and the oil outlet of the hydraulic pump;

the check valve is used for preventing oil in the accumulator from entering the hydraulic pump.

3. The hydraulic boost energy storage device-based aircraft hydraulic system layout according to claim 1, wherein the left spoiler flap energy storage module, the right spoiler flap energy storage module, the left door energy storage module, the right door energy storage module, the rudder energy storage module and the elevator energy storage module further comprise:

a hydraulic motor connected between the first output and the second output of the servo valve;

the cabin door hydraulic motor is used for respectively executing actions on the left spoiler aileron, the right spoiler aileron, the left cabin door, the right cabin door, the rudder and the elevator based on hydraulic pressure output by the first output end and the second output end of the servo valve.

4. The hydraulic boost energy storage device-based aircraft hydraulic system layout of claim 1, the left spoiler flap energy storage module, the right spoiler flap energy storage module, the left cabin door energy storage module, the right cabin door energy storage module, the rudder energy storage module and the elevator energy storage module further comprising:

the safety valve is connected between an oil inlet and an oil outlet of the hydraulic pump;

the safety valve is used for being opened when the pressure difference between the oil inlet and the oil outlet is larger than a preset value.

5. The hydraulic boost energy storage device-based aircraft hydraulic system layout according to any one of claims 1-4, wherein the left spoiler flap energy storage module, the right spoiler flap energy storage module, the left door energy storage module, the right door energy storage module, the rudder energy storage module and the elevator energy storage module further comprise a transmission device respectively;

the hydraulic pump is connected to an output shaft of the electric motor via the transmission.