Ultra-light full-motion horizontal tail

Abstract

The invention provides an ultra-light full-motion horizontal tail, and belongs to the field of aircraft structure design, the full-motion horizontal tail comprises a main pipe beam extending in the spanwise direction, and a plurality of connecting flanges are arranged on the main pipe beam; the plurality of wing ribs form an all-moving and translation-tail-moving shape, are mounted on the main pipe beam and are fixedly connected with the connecting flange; the front edge and the tail edge of the all-moving horizontal tail are provided with front edge strips and tail edge strips, and the front edge strips and the tail edge strips are fixedly connected with the wing ribs; the skin covers the outer surfaces of the leading edge, the trailing edge strip and the wing ribs, and the skin forms the aerodynamic shape of the full-motion horizontal tail; the two butt joints are arranged in the middle of the main pipe beam and are hinged with the fuselage structure to form two suspension points; the operating rocker arm is arranged at the position matched with the butt joint, the operating rocker arm is supported through a supporting shaft borne on the wing rib, the operating rocker arm is connected with an actuating mechanism, and connection and up-and-down deflection of the full-motion horizontal tail are achieved through operation of the actuating mechanism.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure design, and in particular relates to an ultra-lightweight all-moving horizontal tail. Background Art

[0002] The horizontal tail of an aircraft is a wing surface that maintains the longitudinal (pitch) stability and control of the aircraft, and is usually located at the tail of the aircraft. The full-moving horizontal tail is a structure that combines the horizontal tail and the elevator of the aircraft into one. It is connected to the fuselage through a rotating shaft. The pilot can control the deflection of the entire horizontal tail, which greatly improves the control performance of the aircraft.

[0003] In order to ensure the technical requirements of strength, rigidity and other indicators, conventional full-moving horizontal tail usually adopts a structural form of combined components, which results in a relatively large overall weight of the full-moving horizontal tail. Summary of the invention

[0004] The purpose of the present application is to provide an ultra-lightweight all-moving horizontal tail to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: an ultra-lightweight all-moving horizontal tail, comprising:

[0006] A main beam extending in the span direction, wherein a plurality of connecting flanges are provided on the main beam;

[0007] A plurality of wing ribs forming the aerodynamic shape of the full-moving horizontal tail, wherein the wing ribs are mounted on the main pipe beam and fixedly connected to the connecting flange;

[0008] Leading edge and trailing edge strips of the leading edge and trailing edge of the all-moving horizontal tail, wherein the leading edge and trailing edge strips are fixedly connected to the wing ribs;

[0009] A skin covering the outer surface of the leading edge, the trailing edge strip and the ribs, the skin forming the aerodynamic shape of the all-moving horizontal tail;

[0010] Two butt joints, which are arranged in the middle of the main beam and are hinged to the fuselage structure to form two suspension points;

[0011] An operating rocker arm is arranged at the position of the matching docking joint, and the operating rocker arm is supported by a supporting shaft carried on the wing rib. The operating rocker arm is connected to an actuating mechanism, and the connection and up and down deflection of the full-moving horizontal tail are realized through the operation of the actuating mechanism.

[0012] In a preferred embodiment of the present application, the main pipe beam is a ring-shaped laminated structure with equal cross-section.

[0013] In a preferred embodiment of the present application, the position of the main beam in the chord direction is 20-30%.

[0014] In a preferred embodiment of the present application, the distance between two adjacent ribs is 350 mm to 400 mm.

[0015] In a preferred embodiment of the present application, the number of ribs from the butt joint to the span-wise edge of the full-moving horizontal tail does not exceed 10.

[0016] In a preferred embodiment of the present application, the wing ribs include end ribs and middle ribs, both of which are foam sandwich structures, and the edges of all foam sandwich structures are provided with edging, and the width of the edging is 5mm to 15mm.

[0017] In a preferred embodiment of the present application, the wing ribs among the intermediate ribs for mounting the support shaft are provided with hanging ears, and the other intermediate ribs are truss-type wing ribs.

[0018] In a preferred embodiment of the present application, the upper and lower edge strips of the wing rib are both carbon fiber fabric structures, carbon tubes are arranged in the upper and lower edge strips, and a foam sandwich structure is pre-embedded in the leading edge fillet area of ​​the wing rib.

[0019] In a preferred embodiment of the present application, the leading edge is a multi-layer carbon fiber prepreg material, which is supported by a foam board with lightening holes.

[0020] In a preferred embodiment of the present application, the skin is a thin film structure.

[0021] The ultra-lightweight fully movable horizontal tail of this application is ensured to have a weight of 1Kg / m by comprehensively optimizing the spacing arrangement of wing ribs, the position of the docking intersection, the parameters of the truss ribs, etc. 2 In order to meet the weight requirement, the overall stiffness requirement of the full-moving horizontal tail is guaranteed by rationally arranging the positions of the steel cables on both sides of the horizontal tail and adjusting the preload of the steel cables. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0023] Figure 1 This is a schematic diagram of the ultra-lightweight all-moving horizontal tail structure of this application. DETAILED DESCRIPTION

[0024] 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.

[0025] In order to achieve a full-motion horizontal tail of 1Kg / m 2 In order to meet the ultra-light weight requirement, the present application provides an ultra-light all-moving horizontal tail.

[0026] like Figure 1As shown, the ultra-lightweight all-moving horizontal tail provided by the present application includes: a main beam 1, a leading edge 2, a trailing edge strip 3, a rib 4, a butt joint 5, a control rocker arm 6 and a skin 7.

[0027] The main beam 1 extends in the span direction and serves as the main load-bearing structure of the full-moving horizontal tail. A plurality of connecting flanges 11 are arranged on the main beam 1 .

[0028] There are multiple ribs 4 , including end ribs 41 and middle ribs 42 . The end ribs 41 and middle ribs 42 are both installed on the main beam 1 , which is connected to the connecting flange 11 .

[0029] The leading edge 2 and the trailing edge 3 are respectively arranged at the leading edge and the trailing edge of the full-moving horizontal tail, and both are connected to the rib 4.

[0030] The skin 7 covers the outer surfaces of the leading edge 2, the trailing edge strip 3 and the ribs 4 to form the aerodynamic shape of the all-moving horizontal tail.

[0031] There are two butt joints 5, which are arranged in the middle of the main beam 1. The butt joints 5 are hinged to the fuselage to form two suspension points, thereby realizing the connection between the full-moving horizontal tail and the fuselage.

[0032] The operating rocker arm 6 is arranged at the position of the matching docking joint 5, which is supported by a supporting shaft carried on the wing rib 4. The operating rocker arm 6 is connected to the corresponding actuating mechanism (actuating cylinder or servo, not shown), and the connection and up and down deflection of the full-moving horizontal tail are realized through the operation of the actuating mechanism.

[0033] In the present application, the main pipe beam 1 is a ring-shaped laminated structure with a uniform cross-section, a length of 5000 mm, an outer diameter of 70 mm, and a thickness of 1.105 mm.

[0034] In some embodiments of the present application, the position of the main beam 1 in the chord direction is about 20-30%, and preferably the position of the main beam 1 in the chord direction is 25%.

[0035] In the present application, the wing ribs 4 are the main bearing mechanism of the aerodynamic profile, and the spacing between them on the main beam 1 should not be too large or too small. Preferably, the spacing between two adjacent wing ribs 4 is 350 mm to 400 mm. For example, the spacing between typical wing ribs 4 can be set to 390 mm.

[0036] Furthermore, the number of ribs 4 distributed on the main beam 1 should not be too large. Preferably, the number of ribs 4 from the butt joint 5 to the spanwise edge of the full-moving horizontal tail does not exceed 10. For example, in this embodiment of the present application, the number of ribs 4 on a single side is 7, thereby forming a full-moving horizontal tail with 14 ribs 4 distributed along the spanwise direction.

[0037] In the present application, the end ribs 41 and the middle ribs 42 are both foam sandwich structures, and the edges of all foam sandwich structures are provided with edging, and the edging width is about 5mm to 15mm. The end ribs 41 and the middle ribs 42 have the same appearance, and their heights are both 10mm. Among them, the wing ribs used to install the support shaft in the middle ribs 42 are provided with hanging ears, and the other middle ribs 42 are truss-type wing ribs. The upper and lower edge strips of the wing ribs 4 are both carbon fiber fabric structures, and carbon tubes are arranged in the upper and lower edge strips. The foam sandwich structure is pre-embedded in the leading edge fillet area of ​​the wing rib 4.

[0038] In the present application, the leading edge 2 is a multi-layer carbon fiber prepreg, supported by a foam board with lightening holes, wherein the number of carbon fiber layers of the leading edge is generally not less than 3 layers.

[0039] In the present application, the skin 7 is a thin film structure.

[0040] Finally, the full-moving horizontal stabilizer of the present application further includes an adjustment rope 8, which is connected to both sides of the full-moving horizontal stabilizer and is connected to the fuselage bearing structure that suspends the full-moving horizontal stabilizer after the pre-tightening force of the adjustment rope 8 is controlled to a predetermined value.

[0041] In the preferred embodiment of the present application, the adjustment rope 8 is a steel cable.

[0042] The ultra-lightweight fully movable horizontal tail of this application is ensured to have a weight of 1Kg / m by comprehensively optimizing the spacing arrangement of wing ribs, the position of the docking intersection, the parameters of the truss ribs, etc. 2 In order to meet the weight requirement, the overall stiffness requirement of the full-moving horizontal tail is guaranteed by rationally arranging the positions of the steel cables on both sides of the horizontal tail and adjusting the preload of the steel cables.

[0043] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An ultra-lightweight fully-moving horizontal tail, characterized in that: include: A main beam extending in the span direction, wherein a plurality of connecting flanges are provided on the main beam; A plurality of wing ribs forming the aerodynamic shape of the full-moving horizontal tail, wherein the wing ribs are mounted on the main pipe beam and fixedly connected to the connecting flange; Leading edge and trailing edge strips of the leading edge and trailing edge of the all-moving horizontal tail, wherein the leading edge and trailing edge strips are fixedly connected to the wing ribs; A skin covering the outer surface of the leading edge, the trailing edge strip and the ribs, the skin forming the aerodynamic shape of the all-moving horizontal tail; Two butt joints, which are arranged in the middle of the main beam and are hinged to the fuselage structure to form two suspension points; An operating rocker arm is arranged at the position of the matching docking joint, and the operating rocker arm is supported by a supporting shaft carried on the wing rib. The operating rocker arm is connected to an actuating mechanism, and the connection and up and down deflection of the full-moving horizontal tail are realized through the operation of the actuating mechanism.

2. The ultra-lightweight all-moving horizontal stabilizer according to claim 1, characterized in that: The main pipe beam is a ring-shaped laminated structure with equal cross-section.

3. The ultra-lightweight all-moving horizontal stabilizer according to claim 2, characterized in that: The position of the main beam in the chord direction is 20-30%.

4. The ultra-lightweight all-moving horizontal stabilizer according to claim 1, characterized in that: The distance between two adjacent ribs is 350mm to 400mm.

5. The ultra-lightweight all-moving horizontal stabilizer according to claim 4, characterized in that: The number of ribs from the butt joint to the spanwise edge of the full-moving horizontal tail shall not exceed 10.

6. The ultra-lightweight all-moving horizontal stabilizer according to claim 5, characterized in that: The wing ribs include end ribs and middle ribs, both of which are foam sandwich structures, and the edges of all foam sandwich structures are provided with edging, and the width of the edging is 5mm to 15mm.

7. The ultra-lightweight all-moving horizontal stabilizer according to claim 6, characterized in that: The wing ribs used for installing the support shaft among the intermediate ribs are provided with hanging ears, and the other intermediate ribs are truss-type wing ribs.

8. The ultra-lightweight all-moving horizontal stabilizer according to any one of claims 4 to 7, characterized in that: The upper and lower edge strips of the wing rib are both carbon fiber fabric structures, carbon tubes are arranged in the upper and lower edge strips, and a foam sandwich structure is pre-embedded in the leading edge fillet area of ​​the wing rib.

9. The ultra-lightweight all-moving horizontal stabilizer according to claim 1, characterized in that: The leading edge is a multi-layer carbon fiber prepreg material supported by a foam board with lightening holes.

10. The ultra-lightweight all-moving horizontal stabilizer according to claim 1, characterized in that: The skin is a thin film structure.

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