Jet flow circulation empennage control system, empennage and aircraft

Abstract

The invention provides a jet circulation empennage control system, an empennage and an aircraft, and relates to the technical field of active flow control, and the jet circulation empennage control system comprises a circulation controller, a steering engine control module, an auxiliary power system, an empennage circulation control unit, an airflow monitoring sensor and an airflow valve. Compressed air is provided by an auxiliary power system of the aircraft, so that the weight of the aircraft can be reduced while yaw control and / or pitching control are / is realized, the number of parts of the whole aircraft is reduced, and the reliability of the system is improved. The aircraft does not need a hydraulic system with a complex structure any more, the weight of the aircraft is reduced, the consumption of fuel oil is reduced, and therefore the economical efficiency of the aircraft is improved. In addition, the take-off weight of the aircraft is reduced, the take-off and landing distance can be shortened, the effective load of the aircraft is improved, and therefore the overall flight performance of the aircraft is improved.

Description

Technical Field

[0001] The present application relates to the technical field of active flow control, and in particular to a jet circulation tail wing control system, a tail wing, and an aircraft. Background Art

[0002] The tail is located at the tail of the fuselage. Its main function is to control the pitch and yaw of the aircraft. It is an important part of maintaining the stability of the aircraft. The tail consists of a horizontal stabilizer and a vertical stabilizer. The horizontal stabilizer is composed of a horizontal stabilizer and an elevator. The horizontal stabilizer is used to maintain the stability of the aircraft's flight control, and the elevator is mainly used to control the pitch movement of the aircraft. The vertical stabilizer is composed of a vertical stabilizer and a rudder. The vertical stabilizer is used to maintain the lateral stability of the aircraft, and the rudder is used to deflect the aircraft to the left or right.

[0003] Civilian large transport aircraft mainly use the hydraulic system arranged inside the fuselage to drive the elevator and rudder to rotate to achieve pitch and yaw control. At present, the horizontal tail elevator and vertical tail rudder of civil large transport aircraft are mainly driven by the aircraft's hydraulic system. The hydraulic system mainly consists of two parts: hydraulic energy and hydraulic users. Hydraulic energy includes: (1) engine-driven pump as the main hydraulic energy; (2) electric pump, pneumatic pump, ram air turbine pump, accumulator, etc. as auxiliary and emergency energy; (3) hydraulic oil tank assembly for storing system oil; (4) oil tank pressurization system composed of air booster tank and self-supplied booster tank; (5) hydraulic oil filtration system for filtering impurities in the oil; (6) system safety valve; (7) radiator; (8) system display and warning accessories; (9) various valves for ground testing and maintenance, etc. Hydraulic users include control and drilling parts. The hydraulic user control part includes: (1) solenoid valves, manual control valves, hydraulic oil locks, reversing valves, and one-way valves that control the on and off of the oil circuit; (2) fixed and adjustable flow valves that control the flow of the oil circuit; (3) safety valves and pressure reducing valves that adjust the system pressure. The hydraulic user actuation part includes hydraulic motors, actuators, boosters, steering gears, etc. The entire hydraulic system is extremely complex, has many parts and components, is heavy, and is difficult to maintain. Civilian large transport aircraft are usually equipped with more than two sets of high-pressure hydraulic systems, which further increases the weight of the aircraft.

[0004] The aircraft hydraulic systems used in the mechanical control surfaces of the horizontal and vertical tails of existing large civil transport aircraft are complex in structure, heavy in weight, and difficult to maintain, which will greatly affect the performance indicators, service life, and economy of the aircraft. Summary of the invention

[0005] The present application provides a jet circulation tail wing control system, a tail wing, and an aircraft, which can achieve pitch control and yaw control while reducing the weight of the aircraft.

[0006] The present application provides a jet circulation tail wing control system, characterized in that it includes: Circulation controller, steering gear control module, auxiliary power system, tail circulation control unit, airflow monitoring sensor, airflow valve; The auxiliary power system is connected to the airflow valve through a pipeline, and the airflow valve is connected to the input port of the tail circulation control unit through a pipeline; the auxiliary power system is used to provide compressed air, and the tail circulation control unit is arranged at the trailing edge of the tail of the aircraft, and the tail circulation control unit is used to realize yaw control and / or pitch control of the aircraft under the action of compressed air; The airflow monitoring sensor is arranged on the connecting pipe between the auxiliary power system and the airflow valve, and the airflow monitoring sensor is connected to the circulation controller; The circulation controller, the servo control module and the airflow valve are connected in sequence, and the circulation controller is connected to the auxiliary power system; the circulation controller is used to control the auxiliary power system to turn on or off the air supply, and the circulation controller is also used to receive data sent by the airflow monitoring sensor and send a target opening to the servo control module, and the servo control module is used to drive the airflow valve according to the target opening.

[0007] In one embodiment of the present application, the tail circulation control unit includes a vertical tail circulation control unit and / or a horizontal tail circulation control unit, and the vertical tail circulation control unit and the horizontal tail circulation control unit are respectively connected to the airflow valve.

[0008] In one embodiment of the present application, the air flow valve is a pressure reducing valve.

[0009] In one embodiment of the present application, the tail wing circulation control unit includes a Coanda surface, a first cavity, a second cavity, a first jet outlet, and a second jet outlet. The first jet outlet and the second jet outlet are located on opposite sides of the Coanda surface. The first cavity is connected to the outside of the aircraft through the first jet outlet, and the second cavity is connected to the outside of the aircraft through the second jet outlet.

[0010] In one embodiment of the present application, the airflow monitoring sensor includes at least two of a flow sensor, a temperature sensor, and a pressure sensor.

[0011] In one embodiment of the present application, the servo control module includes a servo controller and a drive servo, the servo controller is used to receive the target opening sent by the circulation controller and determine the servo execution parameters, and the drive servo is used to drive the airflow valve according to the servo execution parameters.

[0012] In one embodiment of the present application, the circulation controller includes a programmable logic controller or a proportional integral derivative controller.

[0013] In one embodiment of the present application, the jet circulation tail wing control system further includes an alarm device, and the alarm device is connected to the circulation controller.

[0014] In order to achieve the above-mentioned purpose and other related purposes, the present application provides a tail wing, characterized in that the tail wing is provided with one or more of the aforementioned jet circulation tail wing control systems.

[0015] In order to achieve the above-mentioned purpose and other related purposes, the present application also provides an aircraft, characterized in that the aircraft includes a tail structure, and the tail structure is provided with one or more of the aforementioned jet circulation tail control systems.

[0016] As described above, the present application provides a jet circulation tail wing control system, tail wing, and aircraft, which have the following beneficial effects: A jet circulation tail control system in the present application includes a circulation controller, a steering gear control module, an auxiliary power system, a tail circulation control unit, an airflow monitoring sensor, and an airflow valve. The auxiliary power system of the aircraft provides compressed air, which can reduce the weight of the aircraft while achieving yaw control and / or pitch control, reduce the number of parts of the whole aircraft, and improve the system reliability. The aircraft no longer needs a complex hydraulic system, which reduces the weight of the aircraft and reduces the fuel consumption, thereby improving the economy of the aircraft. In addition, the reduction in the take-off weight of the aircraft can also shorten the take-off and landing distance, increase the payload of the aircraft, and thus improve the overall flight performance of the aircraft. The pneumatic control surface generated by the jet circulation tail control system can directly generate aerodynamic torque, without the influence of system delay and hinge torque system bandwidth caused by mechanical and hydraulic systems, thereby improving the system control capability and anti-interference characteristics, and improving the aircraft's ability to suppress airflow interference.

[0017] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings herein are incorporated into the specification and constitute a part of the specification, showing embodiments consistent with the present application, and together with the specification, are used to explain the principles of the present application. Obviously, the drawings described below are only some embodiments of the present application, and for those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative work. In the drawings: Figure 1is a schematic structural diagram of a jet circulation tail wing control system shown in an exemplary embodiment of the present application; Figure 2 It is a schematic structural diagram of a tail wing circulation control unit shown as an exemplary embodiment of the present application.

[0019] 110. Circulation controller; 120. Servo control module; 121. Servo controller; 122. Driving servo; 130. Auxiliary power system; 140. Tail circulation control unit; 141. Vertical tail circulation control unit; 142. Horizontal tail circulation control unit; 150. Airflow monitoring sensor; 160. Airflow valve; 200. Tail; a. Coanda surface; b. First cavity; c. Second cavity; d. First jet outlet; e. Second jet outlet. DETAILED DESCRIPTION

[0020] The following will describe the implementation methods of the present application with reference to the accompanying drawings and preferred embodiments. Those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be understood that the preferred embodiments are only for illustrating the present application, not for limiting the scope of protection of the present application.

[0021] It should be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application, and thus the drawings only show components related to the present application rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed at will, and the component layout may also be more complicated.

[0022] In the following description, a large number of details are discussed to provide a more thorough explanation of the embodiments of the present application. However, it is obvious to those skilled in the art that the embodiments of the present application can be implemented without these specific details. In other embodiments, well-known structures and devices are shown in the form of block diagrams rather than in detail to avoid making the embodiments of the present application difficult to understand.

[0023] See also Figure 1 , which is a schematic diagram of the structure of a jet circulation tail wing control system shown in an exemplary embodiment of the present application. The jet circulation tail wing control system may include: The circulation controller 110 , the steering gear control module 120 , the auxiliary power system 130 , the tail circulation control unit 140 , the airflow monitoring sensor 150 , and the airflow valve 160 .

[0024] The auxiliary power system 130 is connected to the airflow valve 160 through a pipeline, and the airflow valve 160 is connected to the input port of the tail circulation control unit 140 through a pipeline.

[0025] The auxiliary power system 130 is used to provide compressed air, and the tail circulation control unit 140 is arranged at the trailing edge of the tail of the aircraft. The tail circulation control unit 140 is used to achieve yaw control and / or pitch control of the aircraft under the action of compressed air. The compressed air can be transported to the tail circulation control unit 140 through a pipeline.

[0026] The embodiment of the present application replaces the control surface set at the trailing edge of the traditional aircraft by setting the tail circulation control unit 140 at the trailing edge of the aircraft tail. The tail circulation control unit 140 provided by the embodiment of the present application can provide aerodynamic control surfaces, which can directly generate aerodynamic torque without the system delay caused by mechanical and hydraulic systems and the influence of hinge torque system bandwidth, thereby improving the system control ability and anti-interference characteristics, improving the aircraft's ability to suppress airflow interference, and increasing the control system bandwidth.

[0027] It should be noted that the aerodynamic control surfaces generated by the jet circulation tail control system can directly generate aerodynamic torque, without the system delay caused by the mechanical and hydraulic systems and the influence of the hinge torque system bandwidth, which improves the system control capability and anti-interference characteristics, improves the aircraft's ability to suppress airflow interference, and increases the control system bandwidth.

[0028] The tail fin can also be called the tail device or tail structure of the aircraft. It is a key component used to control directional stability and maneuverability on the aircraft. The tail fin can include a horizontal stabilizer and a vertical stabilizer. The horizontal stabilizer is mainly used to control the pitch of the aircraft (i.e. the up and down movement of the nose). The vertical stabilizer is mainly used to control the yaw of the aircraft (i.e. the left and right rotation of the nose).

[0029] The tail circulation control unit 140 provided in the embodiment of the present application may include a vertical tail circulation control unit 141 and / or a horizontal tail circulation control unit 142 , and the vertical tail circulation control unit 141 and the horizontal tail circulation control unit 142 are respectively connected to the airflow valve 160 . Figure 1 In the jet circulation tail control system shown, the tail circulation control unit 140 may include a vertical tail circulation control unit 141 and a horizontal tail circulation control unit 142. When the tail circulation control unit 140 includes the vertical tail circulation control unit 141, the yaw control of the aircraft may be achieved; when the tail circulation control unit 140 includes the horizontal tail circulation control unit 142, the pitch control of the aircraft may be achieved.

[0030] The aircraft in the present application can be a large civil transport aircraft or a large passenger aircraft. The jet circulation tail control system is used on the vertical tail and the horizontal tail, and the main application objects are large civil transport aircraft or large passenger aircraft with conventional layout. The function of the jet circulation tail control system is to replace the mechanical control surface to perform large-angle attitude control (such as yaw and pitch control) during take-off or landing. When performing large-angle attitude control, the circulation control technology has a relatively large demand for bleed air volume. The embodiment of the present application provides compressed air through an auxiliary power system. The auxiliary power system (Auxiliary Power Unit, APU) is a small engine installed on the aircraft. The jet circulation tail control system provided in the embodiment of the present application does not need to add an air source to the aircraft, does not affect the performance of the engine, and does not increase the weight of the aircraft, and has good safety and economy. The APU is usually located at the tail of the aircraft and has an independent fuel supply system, which can continue to operate after the main engine of the aircraft is turned off.

[0031] It should be noted that the jet circulation tail control system uses the aircraft's own APU to provide compressed air. This solution does not require an additional air source on the aircraft, does not affect the performance of the engine, and does not increase the weight of the aircraft, and has good safety and economy. The APU is independent of the aircraft's engine. Supplying air to the circulation-controlled tail through the APU will not damage the structure of the aircraft engine and will not affect the thrust and efficiency of the aircraft engine. After adopting the jet circulation tail control system, the weight of the entire aircraft can be reduced by up to 30%.

[0032] The input port of the tail wing circulation control unit 140 is also the air supply port of the tail wing circulation control unit 140 .

[0033] The airflow monitoring sensor 150 is arranged on the connecting pipe between the auxiliary power system 130 and the airflow valve 160, and the airflow monitoring sensor 150 is connected to the circulation controller 110. The airflow monitoring sensor 150 can be used to monitor the gas flow characteristic data of the gas in the pipeline, and transmit the obtained gas flow characteristic data to the circulation controller 110, so that the circulation controller 110 can obtain the airflow valve opening according to the gas flow characteristic data and the received control instruction. The airflow monitoring sensor 150 is electrically connected to the circulation controller 110.

[0034] The circulation controller 110, the steering gear control module 120 and the airflow valve 160 are connected in sequence, and the circulation controller 110 is connected to the auxiliary power system 130. The circulation controller 110, the steering gear control module 120 and the airflow valve 160 are electrically connected in sequence, and the circulation controller 110 is electrically connected to the auxiliary power system 130.

[0035] Among them, the circulation controller 110 can be used to control the auxiliary power system 130 to turn on or off the air supply. The circulation controller 110 can also be used to receive data sent by the airflow monitoring sensor 150 and send a target opening to the servo control module 120. The servo control module 120 can be used to drive the airflow valve 160 according to the target opening so that the opening of the airflow valve 160 approaches or is equal to the target opening.

[0036] In one embodiment of the present application, the circulation controller 110 includes a programmable logic controller or a proportional integral differential controller. The programmable logic controller has a fast scanning cycle and processing capability, and can achieve real-time control. The proportional integral differential controller continuously adjusts the control signal according to the feedback data through closed-loop control to ensure that the output of the system is close to the set value, the system has a faster response speed, and the system has better stability.

[0037] In one embodiment of the present application, the air flow valve 160 can be a pressure reducing valve. A pressure reducing valve is a valve used to regulate and maintain the pressure of a fluid (usually a gas or liquid) in a system. The pressure reducing valve can reduce a higher inlet pressure to a desired lower outlet pressure and keep the outlet pressure stable. The pressure controlled by the pressure reducing valve is stable. The pressure reducing valve can stably reduce high-pressure gas to the desired low pressure, ensuring that the pressure of the jet control system is constant. The stable air pressure can ensure that the airflow speed and direction of the tail circulation control unit are more consistent, thereby improving the controllability and stability of the aircraft. The pressure reducing valve can reduce system instability caused by pressure fluctuations and improve the reliability and safety of the system. In addition, the pressure reducing valve is usually simple in structure and easy to maintain, which can reduce maintenance time and cost.

[0038] See also Figure 2 , which is a schematic diagram of the structure of a tail wing circulation control unit shown in an exemplary embodiment of the present application. Figure 2 It can be seen that the tail circulation control unit 140 may include a Coanda profile a, a first cavity b, a second cavity c, a first jet outlet d, and a second jet outlet e. The first jet outlet d and the second jet outlet e are located on opposite sides of the Coanda profile a. The first cavity b is connected to the outside of the aircraft through the first jet outlet d, and the second cavity c is connected to the outside of the aircraft through the second jet outlet e. The first jet outlet d and the second jet outlet e are both facing the trailing edge of the tail 200. The first jet outlet d is connected to the first cavity b, and the first jet outlet d is arranged toward the trailing edge of the tail 200. The second jet outlet e is connected to the second cavity c, and the second jet outlet e is arranged toward the trailing edge of the tail 200. Thus, the high-speed ejection of the gas flow is achieved through the first jet outlet d and / or the second jet outlet e.

[0039] It should be noted that when the tail circulation control unit 140 includes a vertical tail circulation control unit 141 and a horizontal tail circulation control unit 142, the vertical tail circulation control unit 141 and the horizontal tail circulation control unit 142 may both include a Coanda surface, a first cavity, a second cavity, a first jet outlet, and a second jet outlet.

[0040] The jet circulation tail control system has the ability to distribute and control the flow with high precision. The APU adjusts the total pressure of the tail circulation control unit's stationary chamber (first cavity, second cavity), thereby controlling the jet velocity at the jet outlet, changing the blowing momentum coefficient, and thus changing the jet intensity, adjusting the jet flow direction, and the control effect of the aerodynamic control surface, which can meet the requirements of the aircraft for different attitude adjustments on the control torque. By arranging sensors on the tail, the direction of the airflow on the wing surface can be monitored at any time, and the air source control characteristics can be adjusted in time through the flight control algorithm, so that the tail can complete the corresponding actions according to the instructions.

[0041] In one embodiment of the present application, the airflow monitoring sensor 150 includes at least two of a flow sensor, a temperature sensor, and a pressure sensor. The temperature sensor is mainly used to monitor the temperature in the pipeline to prevent excessive airflow temperature from damaging the pipeline, valves, controllers, and tail circulation control unit. The pressure sensor is mainly used to monitor the pressure in the pipeline, and the flow sensor is used to monitor the flow of compressed air in the pipeline.

[0042] In one embodiment of the present application, the servo control module 120 may include a servo controller 121 and a driving servo 122. The servo controller 121 may be used to receive the target opening sent by the circulation controller 110 and determine the servo execution parameters. The driving servo 122 may be used to drive the airflow valve 160 according to the servo execution parameters. The driving servo 122 may be connected to the airflow valve 160.

[0043] In one embodiment of the present application, the jet circulation tail control system further includes an alarm device, which is connected to the circulation controller 110. The alarm device can be electrically connected to the circulation controller 110, and when the circulation controller determines that the gas flow characteristics are abnormal based on the data transmitted by the airflow monitoring sensor 150, an alarm opening prompt can be sent to the alarm device to prompt the pilot that the aircraft is abnormal.

[0044] Using the jet circulation tail control system provided in the embodiment of the present application, the jet circulation tail control system adopts a modular design method, has a compact structure and is light in weight. After adopting the jet circulation tail control system, the aircraft no longer needs a complex hydraulic system, which reduces the weight of the aircraft and the fuel consumption, thereby improving the economy of the aircraft. In addition, the reduction in the take-off weight of the aircraft can also shorten the take-off and landing distance and increase the payload of the aircraft, thereby improving the overall flight performance of the aircraft. The jet circulation tail control system eliminates the control subsystem, reduces the number of parts of the entire aircraft, and improves the reliability of the system; the control link is simple, the control components are few, and because the hydraulic mechanism is eliminated, it can be stored for a long time, so it is convenient to maintain and has a low cost, which can improve the use efficiency and attendance rate of the aircraft.

[0045] In addition, the control link of the jet circulation tail control system is simple. The jet circulation tail control system precisely controls the compressed air through the valve, and sprays it from the trailing edge of the tail circulation control unit to form a virtual rudder to achieve flight control. The entire control link is simple, which greatly reduces the system response delay; the low-pressure air source control is achieved through the valve opening in the control link, and the air pressure can be lower than 1.5MPa, with fewer control components, small space and light structure weight; since the drive mechanism only adjusts the valve opening, only a small amount of energy is needed to meet the requirements, and the working environment is less affected by the model scale and flight Mach number changes.

[0046] In the embodiments of the present application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance. "Including" and "comprising" mentioned throughout the specification and claims are open-ended terms and should be interpreted as "including but not limited to".

[0047] The above embodiments are merely illustrative of the principles and effects of the present application, and are not intended to limit the present application. Anyone familiar with the technology may modify or change the above embodiments without violating the spirit and scope of the present application. Therefore, all equivalent modifications or changes made by a person of ordinary skill in the art without departing from the spirit and technical ideas disclosed in the present application shall still be covered by the claims of the present application.

Claims

1. A jet circulation tail wing control system, characterized in that: include: Circulation controller, steering gear control module, auxiliary power system, tail circulation control unit, airflow monitoring sensor, airflow valve; The auxiliary power system is connected to the airflow valve through a pipeline, and the airflow valve is connected to the input port of the tail circulation control unit through a pipeline; the auxiliary power system is used to provide compressed air, and the tail circulation control unit is arranged at the trailing edge of the tail of the aircraft, and the tail circulation control unit is used to realize yaw control and / or pitch control of the aircraft under the action of compressed air; The airflow monitoring sensor is arranged on the connecting pipe between the auxiliary power system and the airflow valve, and the airflow monitoring sensor is connected to the circulation controller; The circulation controller, the servo control module and the airflow valve are connected in sequence, and the circulation controller is connected to the auxiliary power system; the circulation controller is used to control the auxiliary power system to turn on or off the air supply, and the circulation controller is also used to receive data sent by the airflow monitoring sensor and send a target opening to the servo control module, and the servo control module is used to drive the airflow valve according to the target opening.

2. The jet circulation tail fin control system according to claim 1, characterized in that: The tail circulation control unit includes a vertical tail circulation control unit and / or a horizontal tail circulation control unit, and the vertical tail circulation control unit and the horizontal tail circulation control unit are respectively connected to the airflow valve.

3. The jet circulation tail fin control system according to claim 1, characterized in that: The air flow valve is a pressure reducing valve.

4. The jet circulation tail fin control system according to claim 1, characterized in that: The tail circulation control unit includes a Coanda surface, a first cavity, a second cavity, a first jet outlet, and a second jet outlet. The first jet outlet and the second jet outlet are located on opposite sides of the Coanda surface. The first cavity is connected to the outside of the aircraft through the first jet outlet, and the second cavity is connected to the outside of the aircraft through the second jet outlet.

5. The jet circulation tail fin control system according to claim 1, characterized in that: The airflow monitoring sensor includes at least two of a flow sensor, a temperature sensor, and a pressure sensor.

6. The jet circulation tail fin control system according to claim 1, characterized in that: The servo control module includes a servo controller and a driving servo. The servo controller is used to receive the target opening sent by the circulation controller and determine the servo execution parameters. The driving servo is used to drive the airflow valve according to the servo execution parameters.

7. The jet circulation tail fin control system according to claim 1, characterized in that: The circulation controller includes a programmable logic controller or a proportional integral derivative controller.

8. The jet circulation tail fin control system according to claim 1, characterized in that: The jet circulation tail wing control system also includes an alarm device, which is connected to the circulation controller.

9. A tail wing, characterized in that: The tail wing is provided with a jet circulation tail wing control system as described in any one of claims 1 to 8.

10. An aircraft, characterized in that: The aircraft comprises a tail structure, and the tail structure is provided with a jet circulation tail control system as described in any one of claims 1 to 8.

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