Aircraft paddle and paddle sleeve shaping tool

Abstract

The invention relates to an aircraft paddle and paddle sleeve shaping tool, and belongs to the technical field of aerospace, the aircraft paddle and paddle sleeve shaping tool comprises a fixing plate, a profiling frame, a first shaping plate and a second shaping plate, one end of the profiling frame is fixed on the fixing plate, and the other end of the profiling frame is provided with an opening; a positioning hole communicated with the interior of the profiling frame is formed in the fixing plate; the first shaping plate and the second shaping plate are oppositely fixed on two opposite sides of the opening at an interval, and a paddle sleeve shaping area is defined between the first shaping plate and the second shaping plate. One end of the profiling frame is fixed to the fixing plate, then the first shaping plate and the second shaping plate are fixed to the two opposite sides of the opening in the other end of the profiling frame in a spaced mode, and the paddle sleeve shaping area is defined between the first shaping plate and the second shaping plate, so that deformation of a metal paddle root outer sleeve can be avoided in the production process of the composite paddle, and the production efficiency of the composite paddle is improved. And the yield of blade production is improved.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to an aircraft propeller blade sleeve shaping tool. Background Art

[0002] During the production process of composite blades, the metal propeller root jacket was deformed, that is, the bearing seat elliptical problem occurred. As a result, the position and size of the eccentric pin seat were difficult to guarantee during the welding process in the later stage, and the eccentric pin seat needed to be re-matched. In addition, when the blade was working, the bearing ball interacted with the deformed bearing seat, causing uneven force on the propeller shell raceway, affecting the fatigue life of the aluminum alloy propeller shell and the performance of the propeller.

[0003] Therefore, how to design an aircraft propeller blade sleeve shaping tooling is a problem that technical personnel in this field urgently need to solve. Summary of the invention

[0004] The invention provides an aircraft propeller blade sleeve shaping tool, which solves the technical problem that the metal propeller root sleeve is easily deformed during the production process of composite material propeller blades.

[0005] The technical solution of the present invention to solve the above technical problems is as follows: an aircraft propeller blade sleeve shaping tool, comprising: a fixing plate, a profiling frame, a first shaping plate and a second shaping plate,

[0006] One end of the profiling frame is fixed to the fixing plate and the other end thereof is provided with an opening; the fixing plate is provided with a positioning hole connected to the interior of the profiling frame; the first shaping plate and the second shaping plate are fixed at opposite sides of the opening at relative intervals and a paddle sleeve shaping area is defined between the first shaping plate and the second shaping plate.

[0007] The beneficial effect of the present invention is: first, one end of the profiling frame is fixed on the fixed plate, and then the first shaping plate and the second shaping plate are fixed at intervals on the two opposite sides of the opening at the other end of the profiling frame. Since the propeller sleeve shaping area is defined between the first shaping plate and the second shaping plate, deformation of the metal propeller root jacket can be avoided during the production of the composite blade, thereby improving the qualified rate of the composite blade production.

[0008] Based on the above technical solution, the present invention can also be improved as follows.

[0009] Furthermore, the contoured frame is a ladder frame, the small-area end of the ladder frame is fixed to the fixing plate, and the opening is arranged at the large-area end of the ladder frame.

[0010] Furthermore, the side surfaces of the first shaping plate and the second shaping plate opposite to each other are plane surfaces, and the side surfaces of the second shaping plate and the first shaping plate opposite to each other are curved surfaces.

[0011] A further beneficial effect of the above method is that the sides of the first shaping plate and the second shaping plate that are close to each other are designed to be a plane and a curved surface respectively. Since the propeller sleeve shaping area is located between the plane and the curved surface, it can better fit on the outer peripheral side of the metal propeller sleeve of the composite blade, thereby improving the shaping effect of the metal propeller sleeve.

[0012] Furthermore, it also includes a plurality of reinforcing plates, which are arranged at intervals on the outer periphery of the profiling frame and whose adjacent two sides are respectively fixed on the fixing plate and the profiling frame.

[0013] A further beneficial effect of the above method is that the structural strength of the shaping tooling can be improved by fixing a plurality of reinforcing plates on the fixing plate and the profiling frame respectively.

[0014] Furthermore, the plurality of reinforcing plates are all of right-angled trapezoidal structure and two adjacent right-angled sides thereof are respectively fixed on the fixing plate and the contoured frame.

[0015] Furthermore, it also includes a plurality of support blocks, which are respectively located between the second shaping plate and the opposite sides of the openings and fixed at intervals on the opposite sides of the openings; the second shaping plate is fixed on the plurality of support blocks.

[0016] A further beneficial effect of the above-mentioned method is that the second forming plate is supported by a plurality of support blocks, so that the stability of the second forming plate can be improved, deformation of the propeller sleeve forming area can be avoided, and the forming effect of the metal propeller root jacket can be improved.

[0017] Furthermore, it also includes a positioning ring, which is fixed on the plate surface of the fixing plate away from the contour frame, and the ring hole of the positioning ring is arranged opposite to the positioning hole.

[0018] Furthermore, it also includes a plurality of fixing bolts. The contour frame is provided with a plurality of fixing holes at intervals on the frame body corresponding to the peripheral side of the opening. The first shaping plate and the second shaping plate are both provided with threaded holes corresponding to the plurality of fixing holes. The plurality of fixing bolts respectively pass through the fixing holes and are screwed into the corresponding threaded holes. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the left three-dimensional structure of an aircraft propeller blade sleeve shaping tool of the present invention;

[0020] Figure 2 It is a right-side three-dimensional structural schematic diagram of an aircraft propeller blade sleeve shaping tool of the present invention;

[0021] Figure 3 It is a front structural schematic diagram of an aircraft propeller blade sleeve shaping tooling of the present invention;

[0022] Figure 4The present invention is a schematic diagram of the rear structural view of an aircraft propeller blade sleeve forming tooling.

[0023] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0024] 1. fixing plate, 11. positioning hole, 2. profiling frame, 3. first shaping plate, 4. second shaping plate, 5. reinforcing plate, 6. supporting bracket, 7. positioning ring, 8. fixing bolt. DETAILED DESCRIPTION

[0025] The principles and features of the present invention are described below in conjunction with the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0026] like Figure 1 As shown, an aircraft propeller blade sleeve shaping tool comprises: a fixing plate 1, a profiling frame 2, a first shaping plate 3 and a second shaping plate 4,

[0027] One end of the profiling frame 2 is fixed on the fixed plate 1 and the other end thereof is provided with an opening; the fixed plate 1 is provided with a positioning hole 11 connected to the interior of the profiling frame 2; the first shaping plate 3 and the second shaping plate 4 are fixed at opposite sides of the opening at relative intervals and a paddle sleeve shaping area is defined between the first shaping plate 3 and the second shaping plate 4.

[0028] In some specific embodiments, the contour frame 2 is a ladder frame, the small-area end of the ladder frame is fixed on the fixing plate 1, and the opening is provided at the large-area end of the ladder frame.

[0029] In some specific embodiments, the side surfaces of the first shaping plate 3 and the second shaping plate 4 opposite to each other are plane surfaces, and the side surfaces of the second shaping plate 4 and the first shaping plate 3 opposite to each other are curved surfaces.

[0030] In some specific embodiments, a plurality of reinforcing plates 5 may be further included. The plurality of reinforcing plates 5 are arranged at intervals on the outer periphery of the profiling frame 2 and two adjacent sides thereof are fixed on the fixing plate 1 and the profiling frame 2 respectively.

[0031] In some specific embodiments, the plurality of reinforcing plates 5 may all be of a right-angled trapezoidal structure, and two adjacent right-angled sides thereof are respectively fixed on the fixing plate 1 and the contour frame 2 .

[0032] In some specific embodiments, a plurality of support brackets 6 may be further included, wherein the plurality of support brackets 6 are respectively located between the second shaping plate 4 and the opposite opening sides and are fixed at intervals on the opposite opening sides; the second shaping plate 4 is fixed on the plurality of support brackets 6 .

[0033] In some specific embodiments, a positioning ring 7 may be further included. The positioning ring 7 is fixed on the plate surface of the fixing plate 1 away from the contour frame 2 , and the ring hole of the positioning ring 7 is arranged opposite to the positioning hole 11 .

[0034] In some specific embodiments, a plurality of fixing bolts 8 may be further included. A plurality of fixing holes are provided at intervals on the frame body of the profiling frame 2 corresponding to the peripheral side of the opening. The first shaping plate 3 and the second shaping plate 4 are both provided with threaded holes corresponding to the plurality of fixing holes. The plurality of fixing bolts 8 pass through the fixing holes respectively and are screwed into the corresponding threaded holes.

[0035] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft propeller blade sleeve shaping tool, characterized in that: include: Fixing plate (1), A profiling frame (2), one end of the profiling frame (2) is fixed on the fixing plate (1) and the other end of the profiling frame (2) is provided with an opening; the fixing plate (1) is provided with a positioning hole (11) which is in communication with the interior of the profiling frame (2); A first shaping plate (3) and a second shaping plate (4), wherein the first shaping plate (3) and the second shaping plate (4) are fixed at opposite sides of the opening at a relative interval and define a paddle sleeve shaping area between the first shaping plate (3) and the second shaping plate (4).

2. The aircraft propeller blade sleeve shaping tool according to claim 1, characterized in that: The contoured frame (2) is a ladder frame, the small-area end of the ladder frame is fixed on the fixing plate (1), and the opening is arranged at the large-area end of the ladder frame.

3. The aircraft propeller blade sleeve shaping tool according to claim 1, characterized in that: The side surfaces of the first shaping plate (3) and the second shaping plate (4) opposite to each other are plane surfaces, and the side surfaces of the second shaping plate (4) and the first shaping plate (3) opposite to each other are curved surfaces.

4. The aircraft propeller blade sleeve shaping tool according to claim 1, characterized in that: It also comprises a plurality of reinforcing plates (5), which are arranged at intervals on the outer peripheral side of the profiling frame (2) and whose adjacent two sides are respectively fixed on the fixing plate (1) and the profiling frame (2).

5. The aircraft propeller blade sleeve shaping tool according to claim 4, characterized in that: The plurality of reinforcing plates (5) are all of right-angled trapezoidal structure, and two adjacent right-angled sides thereof are respectively fixed on the fixing plate (1) and the contoured frame (2).

6. The aircraft propeller blade sleeve shaping tool according to claim 1, characterized in that: It also comprises a plurality of support brackets (6), wherein the plurality of support brackets (6) are respectively located between the second shaping plate (4) and the opposite sides of the opening and are fixed on the opposite sides of the opening at intervals; the second shaping plate (4) is fixed on the plurality of support brackets (6).

7. The aircraft propeller blade sleeve shaping tool according to claim 1, characterized in that: It also comprises a positioning ring (7), wherein the positioning ring (7) is fixed on a plate surface of the fixing plate (1) away from the contour frame (2), and the ring hole of the positioning ring is arranged opposite to the positioning hole (11).

8. The aircraft propeller blade sleeve shaping tool according to claim 1, characterized in that: It also includes a plurality of fixing bolts (8), the profiling frame (2) is provided with a plurality of fixing holes at intervals on the frame body corresponding to the peripheral side of the opening, and the first shaping plate (3) and the second shaping plate (4) are both provided with threaded holes corresponding to the plurality of fixing holes; the plurality of fixing bolts (8) respectively pass through the fixing holes and are screwed into the corresponding threaded holes.

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