CN218856767U - Aircraft finished product erection joint frock of changing outfit - Google Patents

Abstract

The utility model belongs to the technical field of aviation assembly, and discloses a replacement tool for an aircraft finished product mounting joint, which comprises a main body frame, a positioning pin rod, a positioning angle seat and a positioner; the positioning angle seats are symmetrically distributed in pairs, each positioning angle seat is provided with a positioner, each positioner is of a plate-shaped structure, the upper end of each positioner is provided with two rows of holes, the first row of holes are holes with the sizes and positions consistent with those of finished product mounting holes in an old connector for mounting a finished product of an airplane, the second row of holes are holes with the sizes and positions consistent with those of finished product mounting holes in a new connector for mounting the finished product of the airplane, and the positioning pin rods are pin rods matched with the sizes of the mounting holes in the finished product of the airplane. The utility model discloses it becomes very convenient to make aircraft finished product erection joint change outfit, has avoided setting-out positioning method to change outfit the hole site deviation that produces, solves the problem that setting-out positioning method can't carry out aircraft finished product erection joint and change outfit, has improved change outfit efficiency and product percent of pass, has shortened joint change outfit cycle effectively.

Description

Aircraft finished product erection joint frock of changing outfit

Technical Field

The utility model belongs to the technical field of the aviation assembly, a frock structure that old joint hole used is borrowed in aircraft joint reloading is related to, concretely relates to aircraft finished product erection joint reloading frock.

Background

The number of finished product installation joints of a certain type of airplane is 6, 2 finished product installation joints are respectively installed at 3 frame positions on the outer surface of the airplane in a group, and each joint and the airplane body are connected through a fastening piece. And a finished product mounting hole is formed in the top end of each joint, the finished product mounting holes in the 6 joints have dimensional requirements in the directions of course, horizontal symmetry and height, and the tolerance is +/-0.1 mm.

At present, the finished product is changed through, the appearance adaptability of the finished product installation connector is changed, and after the appearance of the connector is changed, compared with the original connector, the size of the finished product installation hole is changed, but the connector and the connecting hole of the machine body are not changed. At present, the installation position of the joint needs to be replaced, if in-situ replacement is adopted, a connecting hole needs to be manufactured on a new joint, then the new joint is positioned according to the hole for connecting the original joint and the machine body, and the replacement according to the method inevitably causes assembly error accumulation in the replacement process, so that the 6 joints are integrally inconsistent and cannot meet the installation precision of +/-0.1 mm.

Disclosure of Invention

In order to solve the problem, the utility model provides an aircraft finished product erection joint frock of reloading has guaranteed that high-efficient accurate reloading connects, and the assurance that can be very big connects the position accuracy after the reloading, also can avoid reloading in-process damage product, uses portably, can improve reloading efficiency, can ensure product quality again.

The technical scheme of the utility model as follows:

a replacing tool for an aircraft finished product installation joint comprises a main body frame, a positioning pin rod, a positioning angle seat and a positioner; the positioning angle seats are symmetrically distributed in pairs, each positioning angle seat is provided with a positioner, each positioner is of a plate-shaped structure, the upper end of each positioner is provided with two rows of holes, the first row of holes are holes with the sizes and positions consistent with those of finished product mounting holes in an old connector for mounting a finished product of an airplane, the second row of holes are holes with the sizes and positions consistent with those of finished product mounting holes in a new connector for mounting the finished product of the airplane, and the positioning pin rods are pin rods matched with the sizes of the mounting holes in the finished product of the airplane.

Furthermore, the device also comprises an adjusting inserting sheet which is a thin sheet with a long round through hole, and the size of the long round through hole is matched with that of the positioning pin rod.

Furthermore, the positions of six positioning angle seats which are symmetrically distributed pairwise on the main body frame are matched with six positions of the aircraft finished product installation joint.

Furthermore, a third row of holes are formed in the bottom of the positioner, and the bottom of the positioner is detachably connected with the positioning angle seat through the third row of holes.

Furthermore, the positioner is divided into a first positioner, a second positioner and a third positioner, the central line of the main body frame is aligned with the symmetry axis of the airplane, and the two first positioners, the two second positioners and the third positioner are respectively arranged along the central line from the back to the front.

Furthermore, the profiles of the first locator and the third locator are parallel to the central line of the main body frame, and the profile of the second locator is perpendicular to the central line of the main body frame.

The utility model has the advantages as follows:

1. the utility model discloses an aircraft finished product erection joint frock of reloading, the advantage makes aircraft finished product erection joint dress of reloading become very convenient, and the hole site deviation of having avoided setting-out location method dress change to produce leads to the unable installation of finished product, solves the unable problem of carrying out aircraft finished product erection joint dress change of original setting-out location method.

2. The utility model discloses satisfy on the joint finished product mounting hole apart from the size of aircraft symmetry axis, apart from the size of aircraft horizontal reference face, apart from the dimensional requirement of aircraft frame axis, improved the reloading efficiency, guarantee product quality, improved the product percent of pass, shortened effectively and connect the reloading cycle.

Drawings

FIG. 1 is a schematic structural view of the tool of the present patent;

FIG. 2 is a front view of the tooling of this patent;

FIG. 3 is a top view of the tooling of this patent;

FIG. 4 is a schematic illustration in elevation of the present tool in use in an aircraft configuration;

FIG. 5 is a schematic left side view of the inventive tooling in use in an aircraft configuration;

the method comprises the following steps of 1, replacing a tool for a finished product installation joint of an airplane, 2, installing a joint for a finished product, and 3, covering a fuselage; 1 a-main part frame, 1 b-locating pin stick, 1 c-adjusting inserted sheet, 1 d-locating angle seat, 1 e-first locator, 1 f-second locator, 1 g-third locator.

Detailed Description

This section is an embodiment of the present invention for explaining and explaining the technical solution of the present invention. Without conflict, embodiments of the present invention and features of the embodiments may be combined with each other.

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate directions or positional relationships for directions or positional relationships given to the drawings, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device referred to or the case must have a specific orientation, be constructed and operated in a specific orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include more than one of the feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "mounted," "connected" and "connected" should be interpreted broadly, and may be, for example, a fixed connection, a detachable connection or an integrated connection; the connection can be mechanical connection or point connection; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail with reference to the accompanying drawings in conjunction with embodiments.

A replacement tool for an aircraft finished product installation joint comprises a main body frame 1a, a positioning pin rod 1b, a positioning angle seat 1d and a positioner; the positioning pin rod 1b is a bolt rod matched with the size of the mounting hole in the aircraft finished product installation, and the second row of holes are consistent with the size and the position of the finished product mounting hole in the aircraft finished product installation new joint.

The adjusting pin rod is characterized by further comprising an adjusting insertion piece 1c, wherein the adjusting insertion piece 1c is a thin sheet with a long round through hole, and the size of the long round through hole is matched with that of the positioning pin rod 1 b.

The positions of six positioning angle seats 1d which are symmetrically distributed pairwise on the main body frame 1a are matched with six positions of the aircraft finished product installation joint.

Still be equipped with the third round on the locator bottom, the locator bottom can be dismantled through the third round with location angle seat 1d and be connected.

The positioner is divided into a first positioner 1e, a second positioner 1f and a third positioner 1g, the central line of the main body frame 1a is aligned with the symmetry axis of the airplane, and the two first positioners 1e, the two second positioners 1f and the third positioner 1g are respectively arranged along the central line from the air back to the front.

The profiles of the first locator 1e and the third locator 1g are parallel to the center line of the main body frame 1a, and the profile of the second locator 1f is perpendicular to the center line of the main body frame 1 a.

Referring to attached drawings 1-5, the patent tool is divided into 7 parts, namely a main body frame 1a, a positioning pin rod 1b, an adjusting insert 1c, a positioning angle seat 1d and a positioner; the main body frame 1a is mainly used for bearing a positioning angle seat 1d, and the positioning angle seat 1d is mainly used for various positioners; three rows of holes are formed in the three types of positioners, the upper row of holes are consistent with the sizes of finished product mounting holes in an old airplane finished product mounting joint, the middle second row of holes are consistent with the sizes of finished product mounting holes in a new airplane finished product mounting joint, and the lower third row of holes are used for fixing the positioning angle seat 1 d. During the use, first row of holes on first locator 1e, second locator 1f, third locator 1g main part are just right with the old joint finished product mounting hole of aircraft finished product installation, adopt locating pin stick 1b to fix with the old joint finished product mounting hole of aircraft finished product installation through first row of holes on three kinds of locator main parts, the old joint notch of aircraft finished product installation is controlled through adjustment inserted sheet 1c, the width size of the notch on the old joint of every aircraft finished product installation is unanimous, insert adjustment inserted sheet 1c in the old joint notch of aircraft finished product installation through standard clearance fit, the aircraft finished product installation joint changes the dress frock and fixes and finishes after inserting, can carry out the dress that changes of new joint.

When the airplane is changed, the connection between any one of the old airplane finished product installation joints and the airplane is disassembled, the old joint is disassembled, the new airplane finished product installation joint is fixed by adopting a positioning pin rod 1b and an adjusting inserting piece 1c through a second row of holes on the positioner, the new joint is installed by means of the original airplane body installation hole position, and the positioner and the new airplane finished product installation joint are still fixed after the installation is finished; and then the old joint in the diagonal direction is disassembled, the new joint is installed according to the method, and then the replacement of all the joints is completed according to the method.

The tooling is characterized in that after three-dimensional digital analog simulation is carried out, the finished product mounting hole on each aircraft finished product mounting joint is confirmed to be consistent with the positioning hole site of the positioning device on the reloading tooling, and then the tooling is processed through a numerical control machine tool, so that the manufactured hole site is ensured to be accurate. The operator uses the time division 2 steps: the 1 st step is earlier just right with connecting the mounting hole with the locating hole of locator on the frock, and 2 nd step is fixed with the joint with locating pin stick and adjustment inserted sheet with the frock, only needs 2 steps aircraft finished product erection joint to change the dress and just install the completion, alright in order to accomplish one by one and connect the operation of changing the dress, all connect to change the dress and accomplish the back along the reverse order of installation and demolish the frock.

Claims (6)

1. The frock for replacing the aircraft finished product installation joint is characterized by comprising a main body frame (1 a), a positioning pin rod (1 b), a positioning angle seat (1 d) and a positioner; wherein, be equipped with six two bisymmetry distributions's location angle seat (1 d) on main body frame (1 a), all install the locator on every location angle seat (1 d), the locator is platelike structure, the locator upper end is equipped with two rows of holes, the first row of hole is the hole unanimous with finished product mounting hole size and position on the old joint of aircraft finished product installation, the second row of hole is the hole unanimous with finished product mounting hole size and position on the new joint of aircraft finished product installation, location round pin stick (1 b) is the bolt stick of mounting hole size on the cooperation aircraft finished product installation.

2. The aircraft finished product erection joint reloading tool according to claim 1, further comprising an adjusting insertion sheet (1 c), wherein the adjusting insertion sheet (1 c) is a thin sheet with a long round through hole, and the size of the long round through hole is matched with that of the positioning pin rod (1 b).

3. The aircraft finished product erection joint reloading tool according to claim 1, characterized in that the positions of six pairwise symmetrically distributed positioning angle seats (1 d) on the main body frame (1 a) are matched with six positions of the aircraft finished product erection joint.

4. The aircraft finished product erection joint frock of changing of claim 1 characterized in that still is equipped with the third row of hole on the locator bottom, and locator bottom and location angle seat (1 d) are through the detachable connection of third row of hole.

5. The aircraft finished product erection joint frock of changing outfit of claim 1, characterized in that, the locator divide into first locator (1 e), second locator (1 f) and third locator (1 g), main body frame (1 a) central line aims at the aircraft axis of symmetry, and the distribution of locator is two first locator (1 e), two second locator (1 f) and third locator (1 g) respectively from navigating backward to forward along the central line.

6. The aircraft finished product erection joint reloading tool as claimed in claim 1, wherein the profiles of the first locator (1 e) and the third locator (1 g) are parallel to the center line of the main body frame (1 a), and the profile of the second locator (1 f) is perpendicular to the center line of the main body frame (1 a).

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