Jacking fixing device assisting in assembling aircraft pneumatic control valve

Abstract

The utility model discloses a jacking fixing device for assisting in assembling a pneumatic control valve of an airplane, which comprises a flange plate, a screw-in shaft, a positioning connector and at least two clamping components arranged on the flange plate, the clamping assembly is used for clamping a flange of a support of the aircraft pneumatic control valve placed on the flange plate, a first threaded hole is formed in the middle of the flange plate, the screw-in shaft is connected into the first threaded hole in a threaded mode, and the lower end of the positioning connector is rotationally connected with the upper end of the screw-in shaft through a bearing. The positioning connector is used for abutting against the lower face of a connecting column of the aircraft pneumatic control valve, and a limiting protruding block correspondingly inserted into a positioning connecting hole of the connecting column of the aircraft pneumatic control valve is arranged at the upper end of the positioning connector. When the valve spring part of the pneumatic control valve of the airplane is assembled, the valve spring compression device can assist personnel in compressing the valve spring, so that the safety and the assembly efficiency are improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft pneumatic control valve assembly, and particularly relates to a jacking fixing device for assisting in assembling an aircraft pneumatic control valve. BACKGROUND

[0002] Aircraft pneumatic control valves are commonly used in air conditioning, anti-icing, and air induction systems of various aircraft models to achieve pneumatic control or even system control functions. Most aircraft pneumatic control valves use air path control and spring actuation to regulate their functions.

[0003] Aircraft pneumatic control valves generally have valve springs installed in their structures. During the assembly of aircraft pneumatic control valves, the valve springs need to be compressed. Figure 2 A part of an aircraft pneumatic control valve is shown in the figure, which includes a conical bracket 10, a connecting column 12, and a valve spring 11. The lower edge of the bracket 10 has a flange 10.1, and the upper end has a mounting hole. The lower end of the connecting column 12 has two positioning connection holes 12.1.

[0004] The existing maintenance method for assembling the valve spring part of an aircraft pneumatic control valve involves two people working together. The valve spring 11 is placed into the bracket 10, and the connecting column 12 is inserted from the bottom to the top through the mounting hole of the valve spring 11 and the bracket 10. A large enough jacking block is placed below, and the lower end of the connecting column 12 is jacked against the jacking block. One person presses the bracket 10 downward with both hands to compress the valve spring 11, and the connecting column 12 is inserted upward until it is compressed to the correct position and maintains a stable pressure. Then, the other person gradually installs the remaining parts above the bracket 10 and partially fixes them to the connecting column 12. After the installation of the remaining parts above the bracket 10 is completed, the pressure on the bracket 10 is released.

[0005] However, the above-mentioned assembly process of the valve spring part of an aircraft pneumatic control valve has the following problems:

[0006] 1. The valve spring 11 of an aircraft pneumatic control valve has a large spring force, which is difficult to control and install by hand, and may cause safety hazards.

[0007] 2. The worker needs to press the bracket 10 for a long time to keep the valve spring 11 compressed, and the compressed position of the valve spring 11 may not be accurate, which may cause incorrect installation.

[0008] Therefore, the existing assembly method not only wastes manpower but also poses safety hazards to people and components during the installation and pressing process. UTILITY MODEL CONTENTS

[0009] The utility model discloses a kind of jacking fixing devices for assisting the assembly of aircraft aerodynamic control valve, which can assist personnel to compress valve spring when the valve spring part of aircraft aerodynamic control valve is assembled, to improve safety and improve assembly efficiency.

[0010] The utility model discloses a kind of jacking fixing devices for assisting the assembly of aircraft aerodynamic control valve, which can assist personnel to compress valve spring when the valve spring part of aircraft aerodynamic control valve is assembled, to improve safety and improve assembly efficiency.

[0011] A kind of jacking fixing device for assisting the assembly of aircraft aerodynamic control valve, it is characterized by: including flange, spin into shaft, positioning connector and at least two clamping assemblies being arranged on flange, flange is horizontally arranged, clamping assembly is arranged around the center of flange, clamping assembly is used to clamp the flange of the bracket of aircraft aerodynamic control valve placed on flange, the middle part of flange is equipped with vertical first threaded hole, outer thread is equipped on spin into shaft, spin into shaft is threadedly connected in first bolt hole, the lower end of positioning connector is rotatably connected with the upper end of spin into shaft by bearing, positioning connector is used to abut on the lower surface of the connecting column of aircraft aerodynamic control valve, the upper end of positioning connector is equipped with limiting lug corresponding to being inserted into the positioning connecting hole of the connecting column of aircraft aerodynamic control valve.

[0012] The utility model further provides the technical scheme that: clamping assembly includes fixed stud, nut, clamping sheet and locking bolt, fixed stud is fixedly installed on the upper surface of flange, clamping sheet is sleeved on fixed stud by the through hole in the middle portion, the through hole is gap fit with fixed stud, nut is threadedly connected on fixed stud and is located on the upper surface of clamping sheet, the end of clamping sheet close to spin into shaft is the clamping part for clamping the flange of the bracket of aircraft aerodynamic control valve, the end of clamping sheet away from spin into shaft is equipped with vertical second threaded hole, locking bolt is connected in second threaded hole downward.

[0013] The utility model further provides the technical scheme that: clamping assembly further includes compression spring, compression spring is sleeved on fixed stud, and is located between clamping sheet and flange.

[0014] The utility model further provides the technical scheme that: the lower surface of clamping part is equipped with recess for being clamped on the flange of the bracket of aircraft aerodynamic control valve.

[0015] The utility model further provides the technical scheme that: the lower end of fixed stud is threadedly connected with the threaded hole on the upper surface of flange.

[0016] The utility model further provides the technical scheme that: the lower end of spin into shaft is provided with hand wheel.

[0017] The further technical scheme of the utility model discloses: the upper end middle part of the screwing shaft is equipped with a connecting cylinder, the lower end middle part of the positioning connector is equipped with a connecting round hole, the bearing is arranged in the connecting round hole, the connecting cylinder is inserted into the connecting round hole and is connected with the bearing.

[0018] The further technical scheme of the utility model discloses: the upper end of the positioning connector is equipped with two limiting lugs located at opposite sides.

[0019] Compared with the prior art, the utility model has the following beneficial effects:

[0020] The jacking fixing device can clamp the support of the aircraft pneumatic control valve on the flange plate through the clamping assembly, then rotates the screwing shaft, pushes the connecting column of the aircraft pneumatic control valve upwards through the positioning connector, further compresses the valve spring of the aircraft pneumatic control valve, and the jacking fixing device can keep the valve spring in the compressed state without the continuous pressure of workers, so that the workers can release hands to continue to install the remaining parts of the aircraft pneumatic control valve, manpower is saved, safety is improved, and the assembly efficiency is also improved. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is the sectional view schematic diagram of the jacking fixing device of the utility model embodiment;

[0022] Figure 2 It is the structural schematic diagram of the support, valve spring and connecting column of the aircraft pneumatic control valve.

[0023] The meaning of the reference signs in the drawing is as follows:

[0024] 1-flange plate;1.1-first threaded hole;2-screwing shaft;2.1-hand wheel;2.2-connecting cylinder;3-positioning connector;3.1-limiting lug;3.2-connecting round hole;4-bearing;5-clamping piece;5.1-clamping part;5.2-notch;5.3-second threaded hole;6-locking bolt;7-nut;8-fixing stud;9-compression spring;10-support;10.1-flange;11-valve spring;12-connecting column;12.1-positioning connecting hole. DETAILED DESCRIPTION

[0025] The utility model will be further described in connection with the embodiment.

[0026] In the description of this utility model, it should be understood that the directional descriptions, such as up, down, front, back, left, right, etc., indicate the directional or positional relationship based on the directional or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0027] In the description of this utility model, "several" means one or more, "multiple" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. If "first" or "second" is used in the description, it is only for the purpose of distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0028] In the description of this utility model, unless otherwise explicitly defined, terms such as "setting," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0029] Example:

[0030] like Figure 1 The image shows a lifting and fixing device for assembling aircraft pneumatic control valves, which includes a flange 1, a screw-in shaft 2, a positioning connector 3, and two clamping assemblies.

[0031] Flange 1 is disc-shaped and placed horizontally during use. Its size is designed according to the size of the bracket 10 for fixing the aircraft pneumatic control valve, and can be designed in different sizes. A large, vertical first threaded hole 1.1 is provided in the center of flange 1. The screw-in shaft 2 has external threads and is threaded into the first bolt hole 1.1, with the screw-in shaft 2 in a vertical position. A handwheel 2.1 is provided at the lower end of the screw-in shaft 2, allowing the operator to rotate the screw-in shaft 2 more conveniently. A connecting cylinder 2.2 is provided at the upper center of the screw-in shaft 2.

[0032] The positioning connector 3 is in a cylindrical shape, and is used to abut against the lower surface of the connecting column 12 of the aircraft aerodynamic control valve. A connecting hole 3.2 is arranged in the middle of the lower end of the positioning connector 3, and a bearing 4 is arranged in the connecting hole 3.2. In use, the connecting cylinder 2.2 of the screwing shaft 2 is inserted into the connecting hole 3.2 and connected with the bearing 4, so that the positioning connector 3 is rotationally connected with the upper end of the screwing shaft 2, and the positioning connector 3 does not rotate with the screwing shaft 2. The upper end of the positioning connector 3 is provided with two limiting protrusions 3.1 arranged on opposite sides, and the distance between the two limiting protrusions 3.1 is equal to the distance between the two positioning connecting holes 12.1 of the connecting column 12 of the aircraft aerodynamic control valve. The limiting protrusions 3.1 can be inserted into the positioning connecting holes 12.1 of the connecting column 12 of the aircraft aerodynamic control valve.

[0033] The clamping assembly is arranged on the upper surface of the flange plate 1 and is arranged on both sides around the center of the flange plate 1. The clamping assembly is used to clamp the flange 10.1 of the bracket 10 of the aircraft aerodynamic control valve placed on the flange plate 1.

[0034] The clamping assembly of the embodiment includes a fixing stud 8, a nut 7, a clamping piece 5, a compression spring 9, and a locking bolt 6. The fixing stud 8 is arranged vertically, and the lower end thereof is threadedly connected with a threaded hole on the upper surface of the flange plate 1, so as to be fixed on the flange plate 1. The middle part of the clamping piece 5 is provided with a through hole, and the clamping piece 5 is sleeved on the fixing stud 8 through the through hole in the middle part. The through hole is in clearance fit with the fixing stud 8. The nut 7 is threadedly connected with the fixing stud 8 and is arranged on the upper surface of the clamping piece 5. The end of the clamping piece 5 close to the screwing shaft 2 is a clamping portion 5.1 used to clamp the flange 10.1 of the bracket 10 of the aircraft aerodynamic control valve. The lower surface of the clamping portion 5.1 is provided with a notch 5.2 used to be clamped on the flange 10.1 of the bracket 10 of the aircraft aerodynamic control valve. The end of the clamping piece 5 away from the screwing shaft 2 is provided with a vertical second threaded hole 5.3, and the locking bolt 6 is connected downward in the second threaded hole 5.3. The locking bolt 6 is arranged above the flange plate 1. The compression spring 9 is sleeved on the fixing stud 8 and is arranged between the clamping piece 5 and the flange plate 1.

[0035] The use process of the jacking fixing device for assisting the assembly of the aircraft aerodynamic control valve of the embodiment is as follows:

[0036] The screwing shaft 2 and the positioning connector 3 of the jacking fixing device are initially in low position for the placement of components. The valve spring 11 of the aircraft aerodynamic control valve is placed in the bracket 10, the connecting column 12 is passed through the mounting hole of the valve spring 11 and the bracket 10 from bottom to top, the bracket 10 is placed on the flange plate 1 together with the valve spring 11 and the connecting column 12, the position is adjusted so that the positioning connector 3 is inserted into the middle part of the bracket 10 and supported below the connecting column 12, the limiting lug 3.1 on the positioning connector 3 is correspondingly inserted into the positioning connecting hole 12.1 of the connecting column 12, thereby connecting the positioning connector 3 with the connecting column 12 of the aircraft aerodynamic control valve, and the flange 10.1 of the bracket 10 of the aircraft aerodynamic control valve is below the clamping part 5.1 of the clamping piece 5. Then the adjusting nut 7 is rotated so that the notch 5.2 of the clamping part 5.1 is buckled on the flange 10.1 of the bracket 10 of the aircraft aerodynamic control valve, and finally the bracket 10 is pre-clamped. Whether the position of the bracket 10, the valve spring 11 and the connecting column 12 is correct is determined again, after the position is determined to be correct, the locking bolt 6 is rotated and tightened, the lower end of the locking bolt 6 is abutted on the flange plate 1, so that the clamping part 5.1 is tightly pressed downward on the flange 10.1 of the bracket 10 of the aircraft aerodynamic control valve, thereby being clamped more firmly. After it is determined that the bracket 10 is completely clamped, the screwing shaft 2 is rotated, the positioning connector 3 is jacked, and then the connecting column 12 of the aircraft aerodynamic control valve is pushed upward, so that the valve spring 11 is continuously compressed until the connecting column 12 is jacked into position, the installation requirement is reached, the valve spring 11 is kept in the compressed position by the jacking fixing device, and then the installation of the remaining components above the bracket 10 can be more easily carried out.

[0037] The above embodiments of the utility model are not the limitation of the protection scope of the utility model, the implementation mode of the utility model is not limited to this, according to the above content of the utility model, according to the ordinary technical knowledge and usual means of the art, other various forms of modification, replacement or change of the above structure of the utility model are made under the premise of not departing from the above basic technical thought of the utility model, and all should fall within the protection scope of the utility model.

Claims

1. A jacking fixture to assist in the assembly of an aircraft aerodynamic control flap, characterised in that: The flange plate is horizontally arranged, the clamping assembly is arranged around the center of the flange plate, the clamping assembly is used for clamping the flange of the bracket of the aircraft aerodynamic control valve placed on the flange plate, the middle part of the flange plate is provided with a vertical first threaded hole, the screwing shaft is provided with an external thread, the screwing shaft is threadedly connected in the first threaded hole, the lower end of the positioning connector is rotatably connected with the upper end of the screwing shaft through a bearing, the positioning connector is used for abutting against the lower surface of the connecting column of the aircraft aerodynamic control valve, and the upper end of the positioning connector is provided with a limiting protrusion which is inserted into a positioning connecting hole of the connecting column of the aircraft aerodynamic control valve.

2. Jacking fixture to assist in the assembly of an aerodynamic control flap of an aircraft according to claim 1, characterized in that: The clamping assembly comprises a fixing stud, a nut, a clamping sheet and a locking bolt, the fixing stud is fixedly installed on the upper surface of the flange plate, the clamping sheet is sleeved on the fixing stud through a through hole in the middle part, the through hole is in clearance fit with the fixing stud, the nut is threadedly connected on the fixing stud and located on the upper surface of the clamping sheet, one end of the clamping sheet close to the screwing shaft is a clamping portion for clamping the flange of the bracket of the aircraft aerodynamic control valve, and the other end of the clamping sheet away from the screwing shaft is provided with a vertical second threaded hole, and the locking bolt is downwardly connected in the second threaded hole.

3. Jacking fixture to assist in the assembly of an aerodynamic control flap of an aircraft according to claim 2, characterized in that: The clamping assembly further comprises a compression spring, the compression spring is sleeved on the fixing stud and located between the clamping sheet and the flange plate.

4. Jacking fixture to assist in the assembly of an aerodynamic control flap of an aircraft according to claim 2, characterized in that: The lower surface of the clamping portion is provided with a notch for clamping the flange of the bracket of the aircraft aerodynamic control valve.

5. Jacking fixture to assist in the assembly of an aerodynamic control flap of an aircraft according to claim 3, characterized in that: The lower end of the fixing stud is threadedly connected with a threaded hole in the upper surface of the flange plate.

6. The lift fixture to assist in the assembly of an aircraft aerodynamic control flap according to claim 1, wherein: The lower end of the screwing shaft is provided with a hand wheel.

7. The lift fixture to assist in the assembly of an aircraft aerodynamic control flap according to claim 1, wherein: The upper end of the screwing shaft is provided with a connecting cylinder in the middle part, the lower end of the positioning connector is provided with a connecting circular hole in the middle part, the bearing is arranged in the connecting circular hole, the connecting cylinder penetrates into the connecting circular hole and is connected with the bearing.

8. The lift fixture to assist in the assembly of an aircraft aerodynamic control flap according to claim 1, wherein: The upper end of the positioning connector is provided with two limiting protrusions located on opposite sides.

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