CN216328180U

CN216328180U - Fixed support device for aircraft frame machining

Info

Publication number: CN216328180U
Application number: CN202123184300.4U
Authority: CN
Inventors: 刘惠超; 邹倩
Original assignee: Jinan vocational college
Current assignee: Jinan vocational college
Priority date: 2021-12-17
Filing date: 2021-12-17
Publication date: 2022-04-19
Anticipated expiration: 2031-12-17

Abstract

The utility model discloses a fixed supporting device for aircraft frame processing, which comprises a processing table, wherein a plurality of groups of aircraft frame fixed supporting mechanisms are arranged on the processing table, each aircraft frame fixed supporting mechanism consists of two groups of contact pressing assemblies which are symmetrically arranged, a placing table is arranged on the processing table and is positioned between the two groups of contact pressing assemblies, each contact pressing assembly comprises a fixed frame, a transverse fixed seat, a power plate, a first connecting rod, a vertical fixed seat, a vertical rod and a pressing plate, the fixed frame is arranged on the processing table, the transverse fixed seat is arranged on the fixed frame, the first connecting rod penetrates through the transverse fixed seat in a sliding mode, and the vertical fixed seat is arranged on the first connecting rod. The utility model relates to the technical field of fixed supporting devices, and particularly provides a fixed supporting device for machining an aircraft frame, which can realize quick fixation of the aircraft frame.

Description

Fixed support device for aircraft frame machining

Technical Field

The utility model relates to the technical field of fixed supporting devices, in particular to a fixed supporting device for machining an aircraft frame.

Background

When an aircraft frame is machined, the aircraft frame needs to be fixed, a traditional fixing and supporting device often fixes parts in a bolt fixing and connecting mode, and the fixing mode is complex when the aircraft frame is detached.

SUMMERY OF THE UTILITY MODEL

Aiming at the situation, in order to overcome the defects of the prior art, the fixing and supporting device for the aircraft frame machining can realize the quick fixing of the aircraft frame.

The technical scheme adopted by the utility model is as follows: the fixing and supporting device for the aircraft frame processing comprises a processing table, wherein a plurality of groups of aircraft frame fixing and supporting mechanisms are arranged on the processing table, each aircraft frame fixing and supporting mechanism consists of two groups of contact pressing assemblies which are symmetrically arranged, a placing table is arranged on the processing table and is positioned between the two groups of contact pressing assemblies, each contact pressing assembly comprises a fixing frame, a transverse fixing seat, a power plate, a first connecting rod, a vertical fixing seat, a vertical rod and a pressing plate, the fixing frame is arranged on the processing table, the transverse fixing seats are arranged on the fixing frame, the first connecting rod slidably penetrates through the transverse fixing seats, the vertical fixing seats are arranged on the first connecting rods, the vertical rods slidably penetrate through the vertical fixing seats, the pressing plates are arranged at the top ends of the vertical rods, the power plates are arranged at the other ends of the first connecting rods, and a pressing transmission rod group is connected between the power plates and the bottom ends of the vertical rods, move through the power board and drive vertical fixing base side contact and place the frame side of placing the bench, drive the clamp plate and push down and press in the frame top, realize the fixed of frame, the going on of convenient processing.

According to the scheme, the push-down transmission rod group comprises a transverse rod, a tilting plate and a telescopic rod, the telescopic rod is arranged on the power plate and penetrates through the fixing frame in a sliding mode, the transverse rod is arranged at the bottom end of the vertical rod, the tilting plate is arranged on the transverse rod, a tilting groove is formed in the tilting plate, a protruding shaft is arranged in the tilting groove in a sliding mode, the protruding shaft is fixedly connected to the movable end of the telescopic rod, a first spring is sleeved on the vertical rod in a sliding mode, and the first spring is located between the pressing plate and the vertical fixing base.

Preferably, the power plate and the fixing frame are connected with a second spring.

Preferably, the workbench is provided with a motor, an output shaft of the motor is provided with a cam, and the cam is in sliding contact with the power plate.

Preferably, the power plate is far away from the placing table, and elastic protection layers are arranged on the bottom side of the pressing plate and on the outer side of the vertical fixing seat.

Preferably, the plurality of groups of aircraft frame fixed supporting mechanisms are distributed annularly.

Preferably, the upper end of the inclined groove is close to the vertical fixing seat.

The utility model with the structure has the following beneficial effects: this scheme cam promotes the power plate and removes and drive vertical fixing base side contact and place the frame side of placing the bench in, drive the clamp plate and push down and press in the frame top, realize the quick fixed to the frame, can relieve the fixed of frame fast simultaneously when the power plate resets, avoids the fixed complex operation problem that brings of traditional use bolt mode.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model and not to limit the utility model. In the drawings:

FIG. 1 is a schematic overall structure diagram of a fixed support device for aircraft frame processing according to the present invention;

fig. 2 is a schematic structural diagram of the aircraft frame fixing and supporting mechanism of the fixing and supporting device for aircraft frame processing according to the scheme.

The device comprises a processing table 1, a processing table 2, a placing table 3, a fixing frame 4, a transverse fixing seat 5, a power plate 6, a first connecting rod 7, a vertical fixing seat 8, a vertical rod 9, a pressing plate 10, a downward pressing transmission rod group 11, a transverse rod 12, an inclined plate 13, an expansion rod 14, an inclined groove 15, a convex shaft 16, a first spring 17, a second spring 18, a motor 19, a cam 20 and an elastic protection layer.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments; all other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

As shown in figures 1-2, the fixing and supporting device for aircraft frame processing comprises a processing table 1, a plurality of sets of aircraft frame fixing and supporting mechanisms are arranged on the processing table 1, each aircraft frame fixing and supporting mechanism is composed of two sets of contact pressing assemblies which are symmetrically arranged, a placing table 2 is arranged on the processing table 1, the placing table 2 is positioned between the two sets of contact pressing assemblies, each contact pressing assembly comprises a fixing frame 3, a transverse fixing seat 4, a power plate 5, a first connecting rod 6, a vertical fixing seat 7, a vertical rod 8 and a pressing plate 9, the fixing frame 3 is arranged on the processing table 1, the transverse fixing seat 4 is arranged on the fixing frame 3, the first connecting rod 6 slidably penetrates through the transverse fixing seat 4, the vertical fixing seat 7 is arranged on the first connecting rod 6, the vertical rod 8 slidably penetrates through the vertical fixing seat 7, the pressing plate 9 is arranged at the top end of the vertical rod 8, and the power plate 5 is arranged at the other end of the first connecting rod 6, a downward pressing transmission rod group 10 is connected between the power plate 5 and the bottom end of the vertical rod 8.

As shown in fig. 2, the push-down transmission rod group 10 includes a transverse rod 11, a tilting plate 12 and a telescopic rod 13, the telescopic rod 13 is disposed on the power plate 5 and slides to penetrate through the fixing frame 3, the transverse rod 11 is disposed at the bottom end of the vertical rod 8, the tilting plate 12 is disposed on the transverse rod 11, a tilting groove 14 is disposed on the tilting plate 12, the high end of the tilting groove 14 is close to the vertical fixing seat 7, a protruding shaft 15 is slidably disposed in the tilting groove 14, the protruding shaft 15 is fixedly connected to the movable end of the telescopic rod 13, a first spring 16 is slidably sleeved on the vertical rod 8, and the first spring 16 is located between the pressing plate 9 and the vertical fixing seat 7.

Wherein, the power plate 5 and the fixed mount 3 are connected with a second spring 17; the workbench 1 is provided with a motor 18, an output shaft of the motor 18 is provided with a cam 19, and the cam 19 is in sliding contact with the power plate 5.

The power plate 5 is far away from the placing table 2, and the bottom side of the pressing plate 9 and the outer side of the vertical fixing seat 7 are both provided with an elastic protection layer 20.

The plurality of groups of aircraft frame fixing and supporting mechanisms are distributed in an annular shape.

When the aircraft is used specifically, the wing part on the aircraft frame is placed on the placing table 2, then the motor 18 is started to drive the cam 19 to rotate, namely, the outer convex side pushes the power plate 5 to move forwards to compress the spring II 17, on one hand, the power plate 5 pushes the vertical fixing seat 7 to move forwards through the connecting rod I6, so that the side elastic protective layer 20 is contacted with the side edge of the wing on the frame, on the other hand, the power plate 5 pushes the telescopic rod 13 to move forwards, when the vertical fixing seat 7 is contacted with the wing, the telescopic rod 13 extends to drive the convex shaft 15 to slide from the bottom end to the top end along the inclined groove 14, so that the pressing plate 9 is pulled downwards through the vertical rod 8 to compress the spring I16 and is pressed above the wing on the frame, and the frame is fixed;

when the fixed supporting state needs to be released, the telescopic rod 13 is started to contract, the motor 18 drives the outer convex side of the cam 19 to be far away from the power plate 5, and the vertical fixed seat 7 and the pressing plate 9 can be driven to reset by rebounding of the first spring 16 and the second spring 17 to be far away from the rack.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

While there have been shown and described what are at present considered the fundamental principles and essential features of the utility model and its advantages, it will be apparent to those skilled in the art that the utility model is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides an aircraft is fixed strutting arrangement for frame processing which characterized in that: including the processing platform, be equipped with multiunit aircraft frame fixed stay mechanism on the processing platform, aircraft frame fixed stay mechanism presses the subassembly by the contact that two sets of symmetries set up and constitutes, the processing bench is equipped with places the platform, it is located between two sets of contact pressing assemblies to place the platform, the contact is pressed the subassembly and is included mount, horizontal fixing base, power plate, connecting rod one, vertical fixing base, vertical pole and clamp plate, the mount is located on the processing platform, horizontal fixing base is located on the mount, connecting rod one slides and runs through horizontal fixing base, vertical fixing base is located on the connecting rod one, vertical pole slides and runs through vertical fixing base setting, the top of vertical pole is located to the clamp plate, the other end of connecting rod one is located to the power plate, be connected with down between the bottom of power plate and vertical pole and press the drive rod group.

2. The fixed support device for the machining of the aircraft frame according to claim 1, wherein: the push-down transmission rod group comprises a transverse rod, a tilting plate and a telescopic rod, the telescopic rod is arranged on the power plate and penetrates through the fixing frame in a sliding mode, the transverse rod is arranged at the bottom end of the vertical rod, the tilting plate is arranged on the transverse rod, a tilting groove is formed in the tilting plate, a protruding shaft is arranged in the tilting groove in a sliding mode, the protruding shaft is fixedly connected to the movable end of the telescopic rod, a first spring is sleeved on the vertical rod in a sliding mode, and the first spring is located between the pressing plate and the vertical fixing base.

3. The fixed support device for the machining of the aircraft frame according to claim 2, characterized in that: and the power plate and the fixed frame are connected with a second spring.

4. The fixed support device for the machining of the aircraft frame according to claim 3, wherein: the workbench is provided with a motor, an output shaft of the motor is provided with a cam, and the cam is in sliding contact with the power plate.

5. The fixed support device for the machining of the aircraft frame according to claim 1, wherein: the power plate is far away from the placing table, and elastic protective layers are arranged on the bottom side of the pressing plate and the outer side of the vertical fixing seat.

6. The fixed support device for the machining of the aircraft frame according to claim 1, wherein: the aircraft frame fixed support mechanisms are distributed annularly.

7. The fixed support device for the machining of the aircraft frame according to claim 2, characterized in that: the high end of the inclined groove is close to the vertical fixed seat.