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CN-224209905-U - Stringer overturning tool for aircraft panel structure

CN224209905UCN 224209905 UCN224209905 UCN 224209905UCN-224209905-U

Abstract

The utility model discloses a stringer overturning tool for an aircraft panel structure, which comprises an overturning tool main body, a first shaft body, a stringer main body and a placing frame, wherein the placing frame is arranged at two ends of the inside of the overturning tool main body through the first shaft body and the second shaft body respectively, six-dimensional force sensors are arranged on the first shaft body and the second shaft body respectively, the stringer main body is arranged between the placing frames, regulating grooves are arranged at two sides below the overturning tool main body, screw rods are arranged in the regulating grooves, driving blocks are sleeved on the screw rods, and balancing weights are arranged at the top ends of the driving blocks. According to the turnover fixture, the moment of the balancing weight on the turnover fixture body can be changed by adjusting the horizontal position of the balancing weight, so that the turnover fixture body is balanced.

Inventors

  • FAN YU

Assignees

  • 西安前程机械制造有限公司

Dates

Publication Date
20260508
Application Date
20250613

Claims (8)

  1. 1. The utility model provides a long purlin upset frock of aircraft panel structure, its characterized in that, including upset frock main part (1), first axis body (2), long purlin main part (3) and rack (8), the inside both ends of upset frock main part (1) are provided with rack (8) through first axis body (2) and second axis body (9) respectively, just be provided with six dimension force transducer (25) on first axis body (2) and second axis body (9) respectively, be provided with long purlin main part (3) between rack (8), the top of upset frock main part (1) one side is fixed with driving motor (4), just driving motor (4) output and first axis body (2) are connected, the both sides of upset frock main part (1) below all are provided with adjustment tank (6), just the inside of adjustment tank (6) all is provided with lead screw (10), all the cover is equipped with driving piece (12) on lead screw (10), just the top of driving piece (12) all is provided with balancing weight (7), driving motor (6) one end (11) are all connected with servo motor (11).
  2. 2. The aircraft panel structure stringer overturning tool as claimed in claim 1, wherein clamping blocks (13) are arranged at the bottom ends of the balancing weights (7), and clamping grooves (14) matched with the clamping blocks (13) are formed in the tops of the driving blocks (12).
  3. 3. The aircraft panel structure stringer overturning tool as claimed in claim 1, wherein 2 groups of brackets (19) are arranged on two sides of the inside of the placement frame (8), screw rods (21) are penetrated through the brackets (19), and limiting pieces (20) are arranged at the bottom ends of the screw rods (21).
  4. 4. The aircraft panel structure stringer overturning tool as claimed in claim 3, wherein fixed rods (15) are arranged at the top end of one side of the placing frame (8), 2 groups of movable sleeves (16) are sleeved on the fixed rods (15), and the bottom ends of the movable sleeves (16) are connected with the support (19).
  5. 5. The aircraft panel structure stringer overturning tooling as set forth in claim 4, wherein strip-shaped holes (17) are formed in the top surfaces of the fixed rods (15), and the movable sleeves (16) are connected with the strip-shaped holes (17) through fasteners (18).
  6. 6. The aircraft panel structure stringer overturning tool as claimed in claim 1, wherein supporting cylinders (5) are arranged at two ends of two sides of the overturning tool main body (1), supporting rods (24) are arranged in the supporting cylinders (5) through rigid springs (23), and the top ends of the supporting rods (24) are connected with the overturning tool main body (1).
  7. 7. The aircraft panel structure stringer overturning tool of claim 6, wherein damping blocks (22) are arranged at the bottom end inside the supporting cylinder (5), and one ends of the damping blocks (22) are connected with rigid springs (23).
  8. 8. The aircraft panel structure stringer overturning tool as claimed in claim 6, wherein guide grooves are formed in two sides of the inside of the supporting cylinder (5), and guide blocks are arranged on two sides of one end of the supporting rod (24).

Description

Stringer overturning tool for aircraft panel structure Technical Field The utility model relates to the technical field of overturning tools, in particular to an overturning tool for a stringer of an aircraft wallboard structure. Background The aircraft panel structure is generally composed of components such as a skin, stringers, a bulkhead and the like, wherein the stringers are generally arranged along the longitudinal direction of an aircraft fuselage or wing, and the stringers have the main functions of enhancing the bearing capacity of the skin, bearing various loads generated in the aircraft flight process, forming an integral stress structure together with the skin, maintaining the shape and the strength of the aircraft panel together and ensuring the safety and the reliability of the aircraft structure. The stringer usually needs to carry out various processing operations on its surface, such as drilling, riveting etc., and upset frock can overturn the stringer, just can accomplish multiaspect processing through single clamping, reduces repeated positioning error, makes things convenient for the workman to operate, and the stringer can change at the upset in-process, and because focus skew, upset frock can lose balance, leads to the stringer to rock even drop, influences the security and the stability of upset operation. Disclosure of Invention The utility model aims to provide an aircraft panel structure stringer overturning tool for solving the problems in the background technology. In order to achieve the above purpose, the utility model provides the technical scheme that the aircraft panel structure stringer overturning tool comprises an overturning tool main body, a first shaft body, a stringer main body and a placing frame, wherein two ends of the inside of the overturning tool main body are respectively provided with the placing frame through the first shaft body and the second shaft body, six-dimensional force sensors are respectively arranged on the first shaft body and the second shaft body, the stringer main body is arranged between the placing frames, a driving motor is fixed at the top end of one side of the overturning tool main body, the output end of the driving motor is connected with the first shaft body, regulating grooves are respectively arranged at two sides below the overturning tool main body, screw rods are respectively arranged in the regulating grooves, driving blocks are respectively sleeved on the screw rods, balancing weights are respectively arranged at the top ends of the driving blocks, servo motors are respectively arranged at one ends of the regulating grooves, and the output ends of the servo motors are respectively connected with the screw rods. Preferably, clamping blocks are arranged at the bottom ends of the balancing weights, and clamping grooves matched with the clamping blocks are formed in the tops of the driving blocks. Preferably, 2 groups of brackets are arranged on two sides of the inside of the rack, screw rods penetrate through the brackets, and limiting pieces are arranged at the bottom ends of the screw rods. Preferably, the top of rack one side all is provided with the dead lever, the cover is equipped with 2 group's movable sleeve on the dead lever, the bottom of movable sleeve all is connected with the support. Preferably, the top surface of dead lever has all offered the bar hole, all be connected with the bar hole through the fastener on the movable sleeve. Preferably, both ends of the two sides of the overturning tool main body are provided with supporting cylinders, the inside of each supporting cylinder is provided with a supporting rod through a rigid spring, and the top ends of the supporting rods are connected with the overturning tool main body. Preferably, damping blocks are arranged at the bottom end of the inside of the supporting cylinder, and one ends of the damping blocks are connected with the rigid springs. Preferably, guide grooves are formed in two sides of the inside of the support cylinder, and guide blocks are arranged on two sides of one end of the support rod. Compared with the prior art, the aircraft panel structure stringer overturning tool has the beneficial effects that through the installation of the overturning tool main body, the stringer main body, the placing frame, the first shaft body, the driving motor, the second shaft body, the six-dimensional force sensor, the adjusting groove, the screw rod, the servo motor, the driving block and the balancing weight, the stringer main body to be processed is placed in the placing frame to be fixed, the driving motor drives the first shaft body to rotate so as to drive the placing frame and the stringer main body to carry out overturning processing, the servo motor can drive the screw rod to rotate during overturning, the driving block moves along the screw rod, so that the position of the balancing weight is adjusted, the six-dimensional force sensor on the first shaft b