Binding tool suitable for DA40 cabin cover glass

Abstract

The utility model relates to a DA40 cockpit cover glass binding tool which comprises a bearing base, an inclined face is formed on one side of the bearing base, a positioning groove which is concave inwards is formed in the inclined face, a groove hole is formed in the middle of the positioning groove, a cockpit frame is inserted into the positioning groove of the bearing base, and the groove hole is formed in the middle of the bearing base. Spring positioning pins are arranged at the upper ends and the lower ends of the two side walls of the cabin frame respectively, positioning holes opposite to the spring positioning pins are formed in the two side walls of the positioning groove, and the heads of the spring positioning pins are inserted into the positioning holes of the bearing base respectively; a plurality of push-and-pull quick clamps are fixedly connected to the portion, on the periphery of the positioning groove, of the bearing base, pressing heads of the push-and-pull quick clamps abut against the upper surface of the periphery of the cockpit cover glass, and the lower surface of the cockpit cover glass abuts against the cockpit frame. The problems that in the prior art, positioning precision is low, fixing is not firm, and operation is complex are solved, and the binding quality and efficiency of the cabin cover glass are improved.

Description

Technical field:

[0001] The utility model relates to the technical field of aircraft canopy glass installation auxiliary tooling, and more particularly to a binding tooling suitable for DA40 canopy glass. Background technology:

[0002] Currently, in the aerospace field, the binding of canopy glass usually requires precise positioning and firm fixation to ensure safety and reliability during flight. However, existing binding tooling has the following problems: 1. Low positioning accuracy: During the assembly process of the glass and the canopy frame, the lack of a precise positioning device can easily lead to inaccurate fit between the glass and the frame, affecting the sealing and overall strength of the canopy; 2. Weak fixation: During the binding process, due to the unreasonable design of the fixing device, it is unable to provide sufficient pressure and stability, causing the glass to easily shift during the bonding process, affecting the binding quality; due to the difference between the fixing device and the fuselage contour, the canopy is deformed after binding, reducing the matching degree with the fuselage. 3. Complex operation: Existing tooling usually requires multiple steps and complex operations, which increases the labor intensity and difficulty of workers and reduces production efficiency. Utility model content:

[0003] The purpose of this utility model is to address the deficiencies of the existing technology and provide a tooling for binding the glass of the DA40 cockpit canopy, so as to solve the problems of low positioning accuracy, loose fixation and complicated operation in the existing technology and improve the quality and efficiency of the binding of the cockpit canopy glass.

[0004] A tooling for binding glass for a DA40 cockpit canopy, comprising a supporting base, a sloped surface formed on one side of the supporting base, an inwardly recessed positioning groove formed on the sloped surface, and a slot formed in the middle of the positioning groove. The tooling is characterized in that a cockpit frame is inserted into the positioning groove of the supporting base, spring positioning pins are respectively provided at the upper and lower ends of two side walls of the cockpit frame, positioning holes are formed on both side walls of the positioning groove, and the heads of the spring positioning pins are respectively inserted into the positioning holes of the supporting base;

[0005] A plurality of push-pull quick clamps are fixedly connected to the bearing base around the positioning groove. The pressure heads of the push-pull quick clamps are pressed against the upper surface of the periphery of the cockpit cover glass, and the lower surface of the cockpit cover glass is pressed against the cockpit frame.

[0006] Preferably, the spring locating pin includes a column sleeve inserted and fixed in the cabin frame, a cylindrical pin is inserted in the column sleeve, and the head of the cylindrical pin extends out of the column sleeve and is inserted in the locating hole of the supporting base; a spring is inserted in the column sleeve, one end of the spring presses against the bottom of the column sleeve and is fixedly connected to the column sleeve, and the other end presses against the cylindrical pin and is fixedly connected to the cylindrical pin.

[0007] Preferably, the push-pull quick clamp includes an articulated support, a rectangular mounting plate is formed at the lower end of the articulated support, and the mounting plate is fixed to the bearing base; one end of the upper part of the articulated support is hinged to a press-fitting arm through a pin, and the upper part of the press-fitting arm is hinged to a push-pull handle through a pin, and the other end of the upper part of the articulated support is hinged to a connecting rod through a pin, and the end of the connecting rod is hinged to the push-pull handle through a pin; the end of the press-fitting arm is threadedly connected to a screw, and the lower end of the screw is plugged and fixed with a rubber pressure head, which presses against the cockpit cover glass.

[0008] Preferably, several groups of bolt assemblies are provided on the mounting plate of the hinged support, and the mounting plate is fixedly connected to a clamping plate through the bolt assemblies, and the clamping plate and the mounting plate are pressed against the inner and outer surfaces of the bearing base respectively; the bolts on the bolt assembly are inserted into the bearing base.

[0009] Preferably, the outer contour shape of the positioning groove on the supporting base is the same as the outer contour shape of the cabin frame, and the depth of the positioning groove is not less than the thickness of the cabin frame.

[0010] Preferably, the diameter of the positioning hole on the bearing base is not less than the diameter of the cylindrical pin on the spring positioning pin.

[0011] The beneficial effects of the present invention are:

[0012] 1. Improve matching accuracy: The bearing base is made through the fuselage mold to ensure that the positioning and shape of the cockpit cover are consistent before and after binding, which greatly increases the matching accuracy with the fuselage; at the same time, it ensures the matching accuracy between the glass and the frame.

[0013] 2. Enhanced fixing firmness: The adjustable clamping device can apply pressure evenly to ensure that the glass will not move during the binding process, thereby improving the binding quality.

[0014] 3. Simplify the operation process: The operation process of the tooling is simple and clear, which reduces the labor intensity and operation difficulty of workers and improves production efficiency. Description of the drawings:

[0015] Figure 1 It is a schematic structural diagram of the utility model from a top view.

[0016] Figure 2 This is a schematic diagram of the partial three-dimensional structure of the inner side of the utility model;

[0017] Figure 3 This is a schematic diagram of a partial three-dimensional structure from another angle on the inner side of the utility model;

[0018] Figure 4 This is a side view of the push-pull quick clamp used in the present invention.

[0019] In the figure: 1. Bearing base; 11. Positioning groove; 12. Slot hole; 13. Positioning hole; 2. Cockpit frame; 21. Spring positioning pin; 3. Cockpit cover glass; 4. Push-pull quick clamp; 41. Articulated support; 42. Press-fit arm; 43. Screw; 44. Rubber pressure head; 45. Push-pull handle; 5. Clamp; 6. Bolt assembly. Specific implementation method:

[0020] Example: See Figures 1 to 3 As shown, a tooling for binding the canopy glass of the DA40 cockpit is shown, comprising a supporting base 1, with an inclined surface formed on one side of the supporting base 1, an inwardly recessed positioning groove 11 formed on the inclined surface, a slot 12 formed in the middle of the positioning groove 11, and the slot 12 serving as an avoidance hole when binding the canopy glass 3 to the cockpit frame 2; the cockpit frame 2 is inserted into the positioning groove 11 of the supporting base 1, and spring positioning pins 21 are respectively provided at the upper and lower ends of the two side walls of the cockpit frame 2, and positioning holes 13 opposite to the spring positioning pins 21 are formed on the two side walls of the positioning groove 11, and the heads of the spring positioning pins 21 are respectively inserted into the positioning holes 13 of the supporting base 1;

[0021] A plurality of push-pull quick clamps 4 are fixedly connected to the supporting base 1 around the positioning groove 11 , and the pressure heads of the push-pull quick clamps 4 are pressed against the upper surface of the periphery of the cockpit cover glass 3 , and the lower surface of the cockpit cover glass 3 is pressed against the cockpit frame 2 .

[0022] See Figure 1 、 2 As shown, the spring locating pin 21 includes a column sleeve which is inserted and fixed in the cockpit frame 2, a cylindrical pin is inserted in the column sleeve, and the head of the cylindrical pin extends out of the column sleeve and is inserted in the locating hole 13 of the bearing base 1; a spring is inserted in the column sleeve, one end of the spring presses against the bottom of the column sleeve and is fixedly connected to the column sleeve, and the other end presses against the cylindrical pin and is fixedly connected to the cylindrical pin, and the cylindrical pin can be retracted in the cockpit frame 2, and when connected to the bearing base 1, it is clamped into the locating hole 13 of the bearing base 1 by the action of the spring to prevent the cockpit frame 2 from being separated from the bearing base 1.

[0023] The push-pull quick clamp 4 includes an articulated support 41, the lower end of the articulated support 41 is formed with a rectangular mounting plate 411, and the mounting plate 411 is fixed to the bearing base 1; one end of the upper part of the articulated support 41 is hinged to a press-fitting arm 42 through a pin, and the upper part of the press-fitting arm 42 is hinged to a push-pull handle 45 through a pin, and the other end of the upper part of the articulated support 41 is hinged to a connecting rod through a pin, and the end of the connecting rod is hinged to the push-pull handle 45 through a pin; the end of the press-fitting arm 42 is screwed with a screw 43, and the lower end of the screw 43 is fixed with a rubber pressure head 44, which presses against the cockpit cover glass 3. Figure 4As shown, this is a structural diagram of the push-pull quick clamp 4 when pressing and holding. By pushing the push-pull handle 45 upward, the pressing arm 42 can be rotated upward around the hinged support 41, so that the rubber pressure head 44 can be separated from the cabin frame 2.

[0024] Several groups of bolt assemblies 6 are provided on the mounting plate 411 of the hinged support 41, and the mounting plate 411 is fixedly connected to the clamping plate 5 through the bolt assemblies 6. The clamping plate 5 and the mounting plate 411 are pressed against the inner and outer surfaces of the bearing base 1 respectively; the bolts on the bolt assembly 6 are inserted into the bearing base 1. This is the specific installation structure of the push-pull quick clamp 4.

[0025] The outer contour of the positioning groove 11 on the supporting base 1 is the same as the outer contour of the cockpit frame 2, but the outer contour of the positioning groove 11 is slightly larger than the outer contour of the cockpit frame 2, and a gap is left between the side walls of the positioning groove 11 and the side walls of the cockpit frame 2; the depth of the positioning groove 11 is not less than the thickness of the cockpit frame 2.

[0026] The diameter of the positioning hole 13 on the bearing base 1 is not less than the diameter of the cylindrical pin on the spring positioning pin 21 .

[0027] Working Principle: This structure is suitable for the DA40 canopy glass binding tool. It is an auxiliary installation tool for positioning the canopy frame 2 and the canopy glass 3. The main body of the tool is the bearing base 1, which is provided with a contoured mold groove (i.e., positioning groove 11) opposite to the canopy frame 2 and a positioning hole 13, thereby accurately positioning the canopy frame 2 and ensuring the frame is accurately positioned on the bearing base 1.

[0028] Push-pull quick clamps 4 are provided on the supporting base 1 around the positioning groove 11. The push-pull quick clamps 4 are easy to operate and can quickly press the cockpit cover glass 3 onto the cockpit frame 2. The number and distribution of the push-pull quick clamps 4 are optimized to provide uniform pressure distribution, prevent local excessive pressure, and thus avoid the cockpit cover glass 3 from breaking.

[0029] The embodiments are intended to illustrate the present invention and are not intended to limit the present invention. Any person skilled in the art may modify the embodiments without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be as set forth in the claims of the present invention.

Claims

1. A tooling for binding glass of a DA40 cockpit canopy, comprising a supporting base (1), a bevel formed on one side of the supporting base (1), a positioning groove (11) recessed inwardly formed on the bevel, a slot (12) formed in the middle of the positioning groove (11), and characterized in that: The cabin frame (2) is inserted into the positioning groove (11) of the bearing base (1), and the upper and lower ends of the two side walls of the cabin frame (2) are respectively provided with spring positioning pins (21), and positioning holes (13) opposite to the spring positioning pins (21) are formed on the two side walls of the positioning groove (11), and the heads of the spring positioning pins (21) are respectively inserted into the positioning holes (13) of the bearing base (1); A plurality of push-pull quick clamps (4) are fixedly connected to the bearing base (1) around the positioning groove (11), and the pressure heads of the push-pull quick clamps (4) are respectively pressed against the upper surface of the periphery of the cockpit cover glass (3), and the lower surface of the cockpit cover glass (3) is pressed against the cockpit frame (2).

2. The tooling for binding glass of a DA40 canopy according to claim 1, characterized in that: The spring positioning pin (21) includes a column sleeve that is inserted and fixed in the cabin frame (2), a cylindrical pin is inserted in the column sleeve, and the head of the cylindrical pin extends out of the column sleeve and is inserted in the positioning hole (13) of the supporting base (1); a spring is inserted in the column sleeve, one end of the spring presses against the bottom of the column sleeve and is fixedly connected to the column sleeve, and the other end presses against the cylindrical pin and is fixedly connected to the cylindrical pin.

3. The tooling for binding glass of a DA40 canopy according to claim 1, characterized in that: The push-pull quick clamp (4) includes an articulated support (41), the lower end of the articulated support (41) is formed with a rectangular mounting plate (411), and the mounting plate (411) is fixed to the bearing base (1); one end of the upper part of the articulated support (41) is hinged to a press-fitting arm (42) through a pin, and the upper part of the press-fitting arm (42) is hinged to a push-pull handle (45) through a pin, and the other end of the upper part of the articulated support (41) is hinged to a connecting rod through a pin, and the end of the connecting rod is hinged to the push-pull handle (45) through a pin; the end of the press-fitting arm (42) is screwed and fixed with a screw (43), and the lower end of the screw (43) is plugged and fixed with a rubber pressure head (44), and the rubber pressure head (44) presses against the cockpit cover glass (3).

4. The tooling for binding glass of a DA40 canopy according to claim 3, characterized in that: A plurality of bolt assemblies (6) are provided on the mounting plate (411) of the hinged support (41); the mounting plate (411) is fixedly connected to a clamping plate (5) via the bolt assemblies (6); the clamping plate (5) and the mounting plate (411) are respectively pressed against the inner and outer surfaces of the bearing base (1); and the bolts on the bolt assembly (6) are inserted into the bearing base (1).

5. The tooling for binding glass of a DA40 canopy according to claim 1, characterized in that: The outer contour shape of the positioning groove (11) on the bearing base (1) is the same as the outer contour shape of the cabin frame (2), and the depth of the positioning groove (11) is not less than the thickness of the cabin frame (2).

6. The tooling for binding glass of a DA40 canopy according to claim 2, characterized in that: The diameter of the positioning hole (13) on the bearing base (1) is not less than the diameter of the cylindrical pin on the spring positioning pin (21).

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