Aircraft part heat treatment device

Abstract

The utility model discloses an aircraft part heat treatment device which comprises a treatment box body, a bottom plate and a clamping base, a T-shaped supporting plate is installed on the bottom plate, rails are arranged on the bottom face of an inner cavity of the treatment box body and the upper side wall of the T-shaped supporting plate, and the clamping base is connected to the rails in a sliding mode. A clamping top cover is rotationally connected to the clamping base, and a manual auxiliary opening mechanism is installed on the side wall of the clamping top cover. A motor is installed on the side wall of the clamping base, a lead screw is installed at the output end of the motor, a movable block is arranged outside the lead screw and rotationally connected with one end of a rotating rod, and the other end of the rotating rod is installed on a manual auxiliary opening mechanism. In a conventional state, the clamping top cover can be pushed to be opened by the motor matched with the movable block. And through cooperation of the manual auxiliary opening mechanism, when the mechanical opening mode is not stable enough, the clamping top cover can be freely opened according to needs, and therefore the part subjected to heat treatment is taken out.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft parts, in particular to a heat treatment device for aircraft parts. Background Art

[0002] Aircraft parts easily absorb hydrogen and oxygen when heated, and hot forming requires hot forming molds, which are costly. Subsequent trimming of parts is difficult and prone to deformation, so industrial parts are generally cold formed and then heat treated to eliminate stress.

[0003] During the heat treatment process after cold forming is completed, it is necessary to use special heat treatment equipment according to the actual size of the parts to ensure good treatment results. Utility Model Content

[0004] The utility model aims to provide a heat treatment device for aircraft parts to solve the problem of batch stable heat treatment of aircraft parts.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a heat treatment device for aircraft parts, comprising a processing box, a bottom plate, and a clamping base, wherein a T-shaped support plate is installed on the bottom plate, and tracks are provided on the bottom surface of the inner cavity of the processing box and the upper side wall of the T-shaped support plate, and the clamping base is slidably connected to the track; a clamping top cover is rotatably connected to the clamping base, and a manual auxiliary opening mechanism is installed on the side wall of the clamping top cover; a motor is installed on the side wall of the clamping base, a screw is installed on the output end of the motor, a movable block is provided outside the screw, the movable block is rotatably connected to one end of a rotating rod, and the other end of the rotating rod is installed on the manual auxiliary opening mechanism.

[0006] Preferably, the wall surfaces of the processing box, the clamping base and the clamping top cover are in a mesh shape.

[0007] Preferably, the manual auxiliary opening mechanism includes a base and a rotating seat, the base is installed on the clamping top cover, one end of the rotating seat is rotatably connected to the clamping top cover, and the other end of the rotating seat is rotatably connected to the rotating rod.

[0008] Preferably, the number of the rails is three pairs, and two pairs are symmetrically provided on the bottom surface of the inner cavity of the processing box, and one pair is provided on the upper surface of the T-shaped support plate.

[0009] Preferably, a hook is installed on the processing box.

[0010] Preferably, a parts cavity is provided on the mating surfaces of the clamping base and the clamping top cover.

[0011] Preferably, the outer wall of the motor is provided with a heat insulating cover.

[0012] Preferably, a slideway is provided on the side wall of the clamping base, and the movable block is slidably connected to the slideway.

[0013] Compared with the prior art, the beneficial effects of the utility model are:

[0014] By providing a freely movable processing box and a clamping mechanism capable of properly holding aircraft parts, it is convenient to perform heat treatment on the parts after they are cold-formed, thereby eliminating the internal stress.

[0015] The clamping cover is designed to open in a dual mode of mechanical and manual opening. Under normal conditions, the clamping cover can be opened by the motor in conjunction with the movable block. By adding a manual auxiliary opening mechanism, when the mechanical opening method is not stable enough, the clamping cover can be opened freely as needed to take out the heat-treated parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a front cross-sectional view of the aircraft parts heat treatment device of the present invention.

[0017] Figure 2 The utility model is a side view of the opening mechanism of the aircraft parts heat treatment device.

[0018] Figure 3 It is a schematic diagram of the rotating seat of the utility model.

[0019] 1. Processing box; 2. Bottom plate; 3. T-shaped support plate; 4. Track; 5. Clamping base; 6. Clamping top cover; 7. Motor; 8. Screw; 9. Movable block; 10. Turning rod; 11. Base; 12. Rotating seat; 13. Hook; 14. Parts chamber; 15. Heat insulation cover. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0021] See also Figure 1-3 The utility model provides a technical solution: a heat treatment device for aircraft parts, comprising a treatment box 1, a bottom plate 2, and a clamping base 5, wherein a T-shaped support plate 3 is installed on the bottom plate 2, and the T-shaped support plate 3 divides the interior of the treatment box 1 into three chambers, one large and two small, so as to adapt to different sizes of aircraft parts and realize heat treatment after cold forming.

[0022] The inner cavity bottom surface of the processing box 1 and the upper side wall of the T-shaped support plate 3 are provided with rails 4, and the clamping base 5 is slidably connected to the rails 4. The number of rails 4 is three pairs, and two pairs are symmetrically provided on the inner cavity bottom surface of the processing box 1, and the spacing between the two pairs of rails 4 is relatively narrow. A pair of rails 4 is provided on the upper surface of the T-shaped support plate 3, and the spacing between the pair of rails 4 is relatively wide. This arrangement can reasonably cooperate with parts clamping mechanisms of different sizes.

[0023] The clamping base 5 is rotatably connected to the clamping top cover 6, and the fitting surfaces of the clamping base 5 and the clamping top cover 6 are provided with a part chamber 14, and the parts to be heat treated will be placed in the part chamber 14. The wall surfaces of the treatment box 1, the clamping base 5 and the clamping top cover 6 are in a mesh shape, so as to ensure that heat can act normally on the parts in the part chamber 14.

[0024] The side wall of the clamping base 5 is installed with a motor 7, and the outer wall of the motor 7 is provided with a heat-insulating cover 15 to prevent the motor 7 from malfunctioning due to overheating. A lead screw 8 is installed at the output end of the motor 7, and a movable block 9 is provided outside the lead screw 8. The movable block 9 is slidably connected to the slideway on the side wall of the clamping base 5 to ensure that the lateral movement of the movable block 9 is smoother. The movable block 9 is rotatably connected to one end of a rotating rod 10, and the other end of the rotating rod 10 is installed on a manual auxiliary opening mechanism, and the manual auxiliary opening mechanism is arranged on the side wall of the clamping top cover 6. When the mechanical opening method is not stable enough and manual opening is required, the device can ensure that the clamping base 5 and the clamping top cover 6 open and close normally, so as to normally remove the heat-treated parts.

[0025] like Figure 3 As shown, the manual auxiliary opening mechanism includes a base 11 and a rotating base 12, wherein the base 11 is mounted on the clamping top cover 6, one end of the rotating base 12 is rotatably connected to the clamping top cover 6, and the other end of the rotating base 12 is rotatably connected to the rotating rod 10. Figure 2 As shown, due to the presence of four rotating mechanisms, the normal opening of the clamping cover 6 will not be affected. At the same time, it is necessary to ensure that the base 11 and the rotating seat 12 are located outside the clamping base 5 and the clamping cover 6 to avoid affecting the normal closing.

[0026] The processing box 1 is provided with a hook 13, through which the assembled parts can be placed into the heat treatment furnace to perform stress relief treatment on the parts.

[0027] Working principle: After the aircraft parts are cold-formed, they are placed in the parts chamber 14 between different clamping bases 5 and clamping top covers 6 according to their actual sizes. The entire device is lifted by the hook 13 and placed in a heat treatment furnace. After the heat treatment is completed, the entire device is lifted, and the operator can appropriately pull out the clamping base 5 and the clamping top cover 6, and turn on the motor 7 to open the clamping top cover 6.

[0028] If the clamping cover 6 cannot be pushed open normally when the motor 7 is turned on, the clamping cover 6 can be manually lifted up, and the base 11 will rotate on the rotating seat 12 to avoid the problem that the processed parts cannot be taken out.

[0029] It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be regarded as exemplary and non-restrictive from any point of view, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention. Any reference numeral in a claim should not be regarded as limiting the claim to which it relates.

Claims

1. A heat treatment device for aircraft parts, characterized in that: It comprises a processing box (1), a bottom plate (2), and a clamping base (5); a T-shaped support plate (3) is installed on the bottom plate (2); a track (4) is provided on the bottom surface of the inner cavity of the processing box (1) and the upper side wall of the T-shaped support plate (3); and the clamping base (5) is slidably connected to the track (4); The clamping base (5) is rotatably connected to a clamping top cover (6), and a manual auxiliary opening mechanism is installed on the side wall of the clamping top cover (6); a motor (7) is installed on the side wall of the clamping base (5), a lead screw (8) is installed at the output end of the motor (7), and a movable block (9) is provided outside the lead screw (8), and the movable block (9) is rotatably connected to one end of a rotating rod (10), and the other end of the rotating rod (10) is installed on the manual auxiliary opening mechanism.

2. The aircraft parts heat treatment device according to claim 1, characterized in that: The wall surfaces of the processing box body (1), the clamping base (5) and the clamping top cover (6) are in the shape of a screen.

3. The aircraft parts heat treatment device according to claim 1, characterized in that: The manual auxiliary opening mechanism comprises a base (11) and a rotating seat (12), wherein the base (11) is mounted on the clamping top cover (6), one end of the rotating seat (12) is rotatably connected to the clamping top cover (6), and the other end of the rotating seat (12) is rotatably connected to the rotating rod (10).

4. The aircraft parts heat treatment device according to claim 1, characterized in that: The number of the rails (4) is three pairs, and two pairs are symmetrically provided on the bottom surface of the inner cavity of the processing box (1), and one pair is provided on the upper surface of the T-shaped support plate (3).

5. The aircraft parts heat treatment device according to claim 1, characterized in that: A hanging hook (13) is installed on the processing box (1).

6. The aircraft parts heat treatment device according to claim 1, characterized in that: A parts chamber (14) is provided on the fitting surfaces of the clamping base (5) and the clamping top cover (6).

7. The aircraft parts heat treatment device according to claim 1, characterized in that: The outer wall of the motor (7) is provided with a heat-insulating outer cover (15).

8. The aircraft parts heat treatment device according to claim 1, characterized in that: The side wall of the clamping base (5) is provided with a slideway, and the movable block (9) is slidably connected to the slideway.

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