A method for integrating the outer cylinder and the body structure of a hydraulic actuator

Abstract

The present application belongs to the field of aircraft control surface drive structure design, and particularly relates to a method for integrating the outer cylinder of a hydraulic actuator with the fuselage structure. The method comprises the following steps: Step 1: Calculate the hydraulic piston rod load based on the torque of the aircraft control surface and the motion envelope arm of the hydraulic actuator; Step 2: Calculate the pressure action area of the hydraulic actuator based on the pressure of the hydraulic actuator and the load of the hydraulic piston rod, and then obtain the inner diameter of the outer cylinder of the hydraulic actuator; Step 3: Calculate the wall thickness of the outer cylinder of the hydraulic actuator based on the load, material strength and safety factor of the outer cylinder of the hydraulic actuator, and then obtain the outer diameter of the outer cylinder of the hydraulic actuator; Step 4: Determine the configuration, material and size of the fuselage structure based on the aircraft load and aerodynamic shape; Step 5: Integrate the outer cylinder of the hydraulic actuator with the fuselage structure and complete the production using a 3D printing process. The present application improves the support stiffness of the hydraulic actuator and the flutter speed of the aircraft control surface.

Description

Technical Field

[0001] The present application relates to the field of aircraft control surface drive structure design, and in particular to a method for integrating the outer cylinder of a hydraulic actuator with the body structure. Background Art

[0002] Aircraft control surfaces are driven by hydraulic actuators to achieve rotational motion around their axes. Traditional hydraulic actuators are mechanically connected to the airframe structure via flanges on the actuator's outer cylinder, resulting in numerous connections and parts. Furthermore, the mechanical connection to the airframe structure limits the hydraulic actuator's support stiffness, affecting the flutter velocity of the control surfaces and, consequently, the aircraft's flight envelope.

[0003] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned deficiencies of the prior art. Summary of the Invention

[0004] The purpose of this application is to provide a method for integrating the outer cylinder and the body structure of a hydraulic actuator to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] A method for designing an integrated structure of a hydraulic actuator outer cylinder and a body structure, comprising:

[0007] Step 1: Calculate the hydraulic piston rod load based on the torque of the aircraft control surface and the motion envelope arm of the hydraulic actuator;

[0008] Step 2: Calculate the pressure action area of the hydraulic actuator based on the pressure of the hydraulic actuator and the load of the hydraulic piston rod, and then obtain the inner diameter of the outer cylinder of the hydraulic actuator;

[0009] Step 3: Calculate the wall thickness of the outer cylinder of the hydraulic actuator based on the load, material strength, and safety factor of the outer cylinder of the hydraulic actuator, and then obtain the outer diameter of the outer cylinder of the hydraulic actuator;

[0010] Step 4: Determine the configuration, material, and dimensions of the airframe structure based on the aircraft load and aerodynamic shape;

[0011] Step 5: Integrate the outer cylinder of the hydraulic actuator with the body structure and complete the production using a 3D printing process.

[0012] In at least one embodiment of the present application, in step 1, calculating the hydraulic piston rod load based on the torque of the aircraft control surface and the motion envelope arm of the hydraulic actuator includes:

[0013] Obtain the torque T of the aircraft control surface and the motion envelope arm L of the hydraulic actuator;

[0014] The hydraulic piston rod load F1 is calculated as:

[0015] F1=T / L / cosθ

[0016] Where θ is the angle of change in the movement of the hydraulic piston rod.

[0017] In at least one embodiment of the present application, in step 2, calculating the pressure action area of the hydraulic actuator based on the pressure of the hydraulic actuator and the load of the hydraulic piston rod, and then obtaining the inner diameter of the outer cylinder of the hydraulic actuator, includes:

[0018] Obtain the pressure P of the hydraulic actuator. Based on the pressure P of the hydraulic actuator and the hydraulic piston rod load F1, calculate the pressure action area S of the hydraulic actuator as follows:

[0019] S=F1 / P

[0020] Then the inner diameter d of the outer cylinder of the hydraulic actuator is:

[0021]

[0022] In at least one embodiment of the present application, in step three, calculating the wall thickness of the outer cylinder of the hydraulic actuator based on the bearing load of the outer cylinder of the hydraulic actuator and the material safety factor, and then obtaining the outer diameter of the outer cylinder of the hydraulic actuator, includes:

[0023] Obtain the load F2, material strength σ, and safety factor n of the hydraulic actuator outer cylinder, and calculate the wall thickness t of the hydraulic actuator outer cylinder as follows:

[0024]

[0025] Then the outer diameter D of the outer cylinder of the hydraulic actuator is:

[0026] D=d+2t.

[0027] In at least one embodiment of the present application, in step three, the outer cylinder of the hydraulic actuator is made of 3D titanium alloy material, and the material safety factor is 1.5.

[0028] In at least one embodiment of the present application, in step four, the body structure includes two longitudinal webs and two transverse webs, and the two longitudinal webs and the two transverse webs are arranged in a crisscross pattern.

[0029] In at least one embodiment of the present application, ribs are provided on both the longitudinal web and the transverse web.

[0030] In at least one embodiment of the present application, the body structure is a 3D titanium alloy material part.

[0031] The invention has at least the following beneficial technical effects:

[0032] The integrated design method of the hydraulic actuator outer cylinder and the fuselage structure of the present application reduces the number of parts in the connection structure between the aircraft control surface and the fuselage, improves the support stiffness of the hydraulic actuator, and increases the flutter speed of the aircraft control surface. It is easy to promote and use and has great practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a schematic diagram of the integrated structure of the outer cylinder and the body structure of the hydraulic actuator in one embodiment of the present application.

[0034] in,

[0035] 1-Hydraulic actuator outer cylinder; 2-Machine body structure. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be understood as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0037] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be understood as limiting the scope of protection of this application.

[0038] The following is combined with Figure 1 This application is described in further detail.

[0039] The present application provides a method for designing an integrated structure of a hydraulic actuator outer cylinder and a body, comprising the following steps:

[0040] Step 1: Calculate the hydraulic piston rod load based on the torque of the aircraft control surface and the motion envelope arm of the hydraulic actuator;

[0041] Step 2: Calculate the pressure action area of the hydraulic actuator based on the pressure of the hydraulic actuator and the load of the hydraulic piston rod, and then obtain the inner diameter of the outer cylinder 1 of the hydraulic actuator;

[0042] Step 3: Calculate the wall thickness of the outer cylinder 1 of the hydraulic actuator according to the load, material strength, and safety factor of the outer cylinder 1 of the hydraulic actuator, and then obtain the outer diameter of the outer cylinder 1 of the hydraulic actuator;

[0043] Step 4: Determine the configuration, material, and size of the airframe structure 2 based on the aircraft load and aerodynamic shape;

[0044] Step 5: Integrate the outer cylinder 1 of the hydraulic actuator with the body structure 2 and complete the production using a 3D printing process.

[0045] The present invention relates to a method for designing an integrated hydraulic actuator outer cylinder and an aircraft body structure. First, the torque T of the aircraft control surface and the motion envelope arm L of the hydraulic actuator are obtained.

[0046] The hydraulic piston rod load F1 is calculated as:

[0047] F1=T / L / cosθ

[0048] Where θ is the angle of change in the movement of the hydraulic piston rod.

[0049] Obtain the pressure P of the hydraulic actuator. Based on the pressure P of the hydraulic actuator and the hydraulic piston rod load F1, calculate the pressure action area S of the hydraulic actuator as follows:

[0050] S=F1 / P

[0051] Then the inner diameter d of the outer cylinder 1 of the hydraulic actuator is:

[0052]

[0053] Obtain the load F2, material strength σ, and safety factor n of the hydraulic actuator outer cylinder 1, and calculate the wall thickness t of the hydraulic actuator outer cylinder 1 as follows:

[0054]

[0055] Then the outer diameter D of the hydraulic actuator outer cylinder 1 is:

[0056] D=d+2t.

[0057] In this embodiment, an appropriate metal material is selected according to the load-bearing size of the hydraulic actuator outer cylinder 1. The hydraulic actuator outer cylinder 1 is made of 3D titanium alloy material. According to the strength value of the appropriate 3D titanium alloy material, the material safety factor is considered to be 1.5.

[0058] The structure of the outer cylinder 1 of the hydraulic actuator is determined according to the above steps.

[0059] The present invention proposes a method for integrating the outer cylinder of a hydraulic actuator with the airframe structure. The airframe structure 2 is then configured as a longitudinal and transverse skeleton. The configuration and dimensions are determined based on the aircraft's load and aerodynamic shape. Space is reserved within the hydraulic actuator piston rod's motion area to prevent interference between the piston rod and the airframe structure. In this embodiment, the airframe structure 2 comprises two longitudinal webs and two transverse webs arranged in a crisscross pattern. Ribs are provided on both the longitudinal and transverse webs. The airframe structure 2 is also constructed of a 3D titanium alloy.

[0060] The integrated design method of the hydraulic actuator outer cylinder and the body structure of the present application finally integrates the longitudinal and transverse skeletons of the hydraulic actuator outer cylinder 1 and the body structure 2 into an integrated design to form an integral component, which is manufactured using titanium alloy material suitable for 3D printing technology.

[0061] In one embodiment of the present application, the hydraulic actuator adopts a double-tube configuration, the two actuators are of the same size, the torque of the aircraft control surface is 2.91 kN·m, the motion envelope arm of the hydraulic actuator is 70 mm, and the angle of change of the hydraulic piston rod motion is 0.209. The total load of the hydraulic piston rod is calculated to be 42500.16 N. Since the two actuators are of the same size, the load of a single hydraulic piston rod is 21250.08 N. Based on the pressure of the hydraulic actuator of 28 MPa and the total load of the hydraulic piston rod of 42500.16 N obtained in the previous step, the total pressure action area of the hydraulic actuator is calculated to be 1517.86 mm 2 Since the two actuators have the same size, the pressure acting area of a single hydraulic actuator is 758.93mm 2 , and then the inner diameter of the hydraulic actuator outer cylinder 2 is 31.09mm, rounded up to 32mm; according to the load-bearing capacity of the hydraulic actuator outer cylinder 1 of 862607.7N, since the two actuators are of the same size, the load-bearing capacity of a single hydraulic actuator is 431303.85N, and according to the strength value of the adapted 3D titanium alloy material of 930MPa, considering the safety factor of 1.5, the wall thickness of the hydraulic actuator outer cylinder 2 is calculated to be 6mm, and then the outer diameter of the hydraulic actuator outer cylinder 2 is obtained to be 44mm; the longitudinal and transverse skeleton layout of the fuselage structure 2 is determined according to the aircraft load size and aerodynamic shape, and space is left in the movement area of the hydraulic actuator piston rod to avoid interference between the piston rod and the fuselage structure 2. The longitudinal and transverse skeletons of the hydraulic actuator outer cylinder 1 and the fuselage structure 2 are integrated into an integrated design to form an integral component, which is made of titanium alloy material adapted to the 3D printing process, such as Figure 1 shown.

[0062] The integrated design method of the hydraulic actuator outer cylinder and the fuselage structure of the present application reduces the number of parts in the connection structure between the aircraft control surface and the fuselage, improves the support stiffness of the hydraulic actuator, and increases the flutter speed of the aircraft control surface. It is easy to promote and use and has great practical value.

[0063] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A method for integrating the outer cylinder and the body structure of a hydraulic actuator, characterized in that: include: Step 1: Calculate the hydraulic piston rod load based on the torque of the aircraft control surface and the motion envelope arm of the hydraulic actuator; Step 2: Calculate the pressure action area of the hydraulic actuator based on the pressure of the hydraulic actuator and the load of the hydraulic piston rod, and then obtain the inner diameter of the outer cylinder of the hydraulic actuator; Step 3: Calculate the wall thickness of the outer cylinder of the hydraulic actuator based on the load, material strength, and safety factor of the outer cylinder of the hydraulic actuator, and then obtain the outer diameter of the outer cylinder of the hydraulic actuator; Step 4: Determine the configuration, material, and dimensions of the airframe structure based on the aircraft load and aerodynamic shape; Step 5: Integrate the outer cylinder of the hydraulic actuator with the body structure and complete the production using a 3D printing process.

2. The method for designing an integrated structure of the outer cylinder and the body of a hydraulic actuator according to claim 1, characterized in that: In step 1, the calculation of the hydraulic piston rod load based on the torque of the aircraft control surface and the motion envelope arm of the hydraulic actuator includes: Obtain the torque T of the aircraft control surface and the motion envelope arm L of the hydraulic actuator; The hydraulic piston rod load F1 is calculated as: F1=T / L / cosθ Where θ is the angle of change in the movement of the hydraulic piston rod.

3. The method for designing an integrated structure of the outer cylinder and the body of a hydraulic actuator according to claim 2, characterized in that: In step 2, the pressure acting area of the hydraulic actuator is calculated based on the pressure of the hydraulic actuator and the load of the hydraulic piston rod, thereby obtaining the inner diameter of the outer cylinder of the hydraulic actuator, including: Obtain the pressure P of the hydraulic actuator. Based on the pressure P of the hydraulic actuator and the hydraulic piston rod load F1, calculate the pressure action area S of the hydraulic actuator as follows: S=F1 / P Then the inner diameter d of the outer cylinder of the hydraulic actuator is:

4. The method for designing an integrated structure of the outer cylinder and the body of a hydraulic actuator according to claim 3, characterized in that: In step three, the wall thickness of the outer cylinder of the hydraulic actuator is calculated based on the bearing load of the outer cylinder of the hydraulic actuator and the material safety factor, thereby obtaining the outer diameter of the outer cylinder of the hydraulic actuator, including: Obtain the load F2, material strength σ, and safety factor n of the hydraulic actuator outer cylinder, and calculate the wall thickness t of the hydraulic actuator outer cylinder as follows: Then the outer diameter D of the outer cylinder of the hydraulic actuator is: D=d+2t.

5. The method for designing an integrated structure of the outer cylinder and the body of a hydraulic actuator according to claim 1, characterized in that: In step three, the outer cylinder of the hydraulic actuator is made of 3D titanium alloy material with a material safety factor of 1.

5.

6. The method for designing an integrated structure of the outer cylinder and the body of a hydraulic actuator according to claim 5, characterized in that: In step 4, the body structure includes two longitudinal webs and two transverse webs, and the two longitudinal webs and the two transverse webs are arranged in a crisscross pattern.

7. The method for designing an integrated structure of the outer cylinder and the body of a hydraulic actuator according to claim 6, characterized in that: Ribs are provided on both the longitudinal web and the transverse web.

8. The method for designing an integrated structure of a hydraulic actuator outer cylinder and a body according to claim 6, characterized in that: The body structure is made of 3D titanium alloy material.

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