阅读说明：本技术 一种飞机扰流板安装方法 (Method for installing spoiler of airplane ) 是由 林震宇 曹祖权 胡愈刚 范斌 魏学志 刘伟 杨毅 方勇军 于 2020-06-12 设计创作，主要内容包括：本发明属于飞机装配领域,公开了一种飞机扰流板安装方法,通过扰流板悬挂主接头、辅助接头交点孔为基准,实现了主接头和辅助接头之间的安装协调,并对梁平面的位置进行了控制,采用接头交点保形工装,保证了接头交点同轴度及槽口间隙,控制了扰流板安装交点的变形,并通过增加扰流板模拟件,确定了扰流板前缘与对接结构之间的间隙协调基准,安装出满足设计要求的飞机机翼扰流板,实现了扰流板开启角度和运动性能要求的目的。(The invention belongs to the field of airplane assembly, and discloses an airplane spoiler installation method, which is characterized in that a main joint and an auxiliary joint are hung on a spoiler by taking an intersection point hole of the main joint and the auxiliary joint as a reference, the installation coordination between the main joint and the auxiliary joint is realized, the position of a beam plane is controlled, a joint intersection point shape-preserving tool is adopted, the coaxiality of the joint intersection point and a notch gap are ensured, the deformation of the spoiler installation intersection point is controlled, the gap coordination reference between the front edge of the spoiler and a butt joint structure is determined by adding a spoiler simulation part, an airplane wing spoiler meeting the design requirements is installed, and the purposes of opening angle and motion performance requirements of the spoiler are realized.)

1. An aircraft spoiler installation method is characterized by comprising the following steps:

preparing 4 groups of spoiler suspension joints, wherein each group of spoiler suspension joints comprises 1 spoiler suspension front main joint, 1 spoiler suspension rear main joint, 1 auxiliary front joint and 1 auxiliary rear joint;

measuring the distance between intersection point holes of suspension joints of all spoilers and the plane of a back beam of the airplane wing after installation, and ensuring that the distance tolerance is controlled between-0.2 mm and 0;

thirdly, assembling a spoiler suspension front main joint and spoiler suspension front and rear joints by taking cross point holes of all spoiler suspension joints as an assembling and positioning reference to manufacture a spoiler suspension main joint;

fourthly, positioning and installing the rear beam of the airplane wing by taking the spoiler suspension main joint as a reference;

fifthly, installing an auxiliary front joint and an auxiliary rear joint;

and step six, installing and connecting the spoiler with the spoiler suspension joint.

2. An aircraft spoiler installation method according to claim 1, further comprising the step of: and adjusting the appearance and the step difference between every two spoilers respectively, and measuring the gap after the spoilers are installed.

3. An aircraft spoiler installation method according to claim 2, further comprising the step of eight: the motion performance of the opening angle of the spoiler is checked.

4. The method of claim 1, wherein in the fourth step, when the rear wing beam of the airplane is out of alignment with the main spoiler suspension joint, the contact plane between the rear wing beam of the airplane and the main spoiler suspension joint is adjusted to ensure the accurate joint intersection.

5. The method as claimed in claim 1, wherein in the fifth step, the auxiliary front joint and the auxiliary rear joint are installed with all spoiler suspension joint intersection holes as the assembly positioning reference.

6. The method of claim 1, wherein after step five and before step five, the spoiler suspension joint intersection coaxiality and the notch clearance are inspected, wherein the inspection requirements are as follows: the coaxiality of the intersection points is less than 0.3mm, and the gap of the notch is less than 0.5 mm.

7. The method for installing the spoiler of the airplane according to claim 1, wherein after the fifth step, before the fifth step, a shape-preserving tool is used for preserving the shape of the intersection point of the suspension joints of the spoiler.

8. The method as claimed in claim 7, wherein after the fifth step, a spoiler dummy is added to the assembling tool after the fifth step, and the gap coordination and repair between the assembled skin T-shaped material and the front edge of the spoiler is completed by taking the spoiler dummy as a coordination reference. .

Technical Field

The invention belongs to the field of aircraft assembly, relates to an installation method of an aviation system structural member, and particularly relates to an installation method of an aircraft spoiler.

Background

The spoiler is attached to the machine body structure system. The spoiler is arranged between 6-14 ribs of upper wing surfaces of outer wing flap cabins in the left wing and the right wing, each spoiler is divided into 4 parts in the spanwise direction, and each part is provided with 1 main suspension joint and 2 auxiliary suspension joints which are connected with the wings through hinges. The spoiler is opened forwards and upwards through a single hydraulic actuator cylinder, the opening angle is not more than 50 degrees, and the spoiler has the functions of meeting the structural integrity of wings, realizing the air and ground deceleration of the airplane and assisting the ailerons to realize the rolling operation of the airplane. These structural forms and functions of the spoiler require a higher connection portion between the body structure and the spoiler.

At present, no public spoiler installation method is available at home and abroad, and the coaxiality of the connection part of the engine body structure and the spoiler cannot be ensured by adopting a common airplane structure installation method.

Disclosure of Invention

In order to solve the problems, the invention provides an aircraft spoiler installation method which can ensure the control of the installation precision of a spoiler.

The technical scheme of the invention is as follows: an aircraft spoiler installation method comprising the steps of:

preparing 4 groups of spoiler suspension joints, wherein each group of spoiler suspension joints comprises 1 spoiler suspension front main joint, 1 spoiler suspension rear main joint, 1 auxiliary front joint and 1 auxiliary rear joint;

measuring the distance between intersection point holes of suspension joints of all spoilers and the plane of a back beam of the airplane wing after installation, and ensuring that the distance tolerance is controlled between-0.2 mm and 0;

thirdly, assembling a spoiler suspension front main joint and spoiler suspension front and rear joints by taking cross point holes of all spoiler suspension joints as an assembling and positioning reference to manufacture a spoiler suspension main joint;

fourthly, positioning and installing the rear beam of the airplane wing by taking the spoiler suspension main joint as a reference;

fifthly, installing an auxiliary front joint and an auxiliary rear joint;

and step six, installing and connecting the spoiler with the spoiler suspension joint.

Further, the method also comprises the step seven: and adjusting the appearance and the step difference between every two spoilers respectively, and measuring the gap after the spoilers are installed.

Further, the method also comprises the step eight: the motion performance of the opening angle of the spoiler is checked.

Furthermore, in the fourth step, when the rear wing beam of the airplane is inconsistent with the main suspension joint of the spoiler, the contact plane of the rear wing beam of the airplane and the main suspension joint of the spoiler is adjusted, and the accuracy of the intersection point of the joints is ensured.

Furthermore, in the fifth step, the auxiliary front joint and the auxiliary rear joint are installed by taking intersection point holes of all spoiler suspension joints as an assembling and positioning reference. The assembly positioning reference of the auxiliary joint takes the intersection point holes of all the joints as a reference, but not takes the airplane wing back beam as a reference, so that the accuracy of the installation axis of the airplane spoiler can be more accurately ensured, and if the airplane wing back beam is not accurate, the airplane wing back beam is polished for processing.

Further, after step five, before the undercarriage, the spoiler hangs and connects nodical axiality and notch clearance to inspect, and the inspection requirement is: the coaxiality of the intersection points is less than 0.3mm, and the gap of the notch is less than 0.5 mm.

And further, after the fifth step, before the lower frame, using a shape-preserving tool to preserve the shape of the intersection point of the suspension joint of the spoiler. The axis consistency of the intersection point position of the suspension joint of the spoiler caused by stress release and other reasons after the lower frame is ensured to be influenced.

And further, after the fifth step, after the assembly, adding a spoiler simulation piece on the assembly tool, and finishing the gap coordination and repair between the assembled skin T-shaped material and the front edge of the spoiler after the installation of the upper skin T-shaped material of the flap cabin by taking the spoiler simulation piece as a coordination reference. The step can ensure the axis consistency of the spoiler installation to the maximum extent.

The invention has the advantages that: the main joint and the auxiliary joint are hung on the spoiler through the cross point hole as a reference, so that the installation coordination between the main joint and the auxiliary joint is realized, the position of a beam plane is controlled, the joint cross point shape-preserving tool is adopted, the joint cross point coaxiality and the notch gap are ensured, the deformation of the installation intersection point of the spoiler is controlled, the gap coordination reference between the front edge of the spoiler and a butt joint structure is determined by adding a spoiler simulation piece, the airplane wing spoiler meeting the design requirement is installed, and the purposes of opening angle and motion performance requirements of the spoiler are realized.

Drawings

FIG. 1 is a schematic view of a spoiler mounting structure according to the present invention;

FIG. 2 is a schematic view of a stress relief groove of the present invention;

the spoiler comprises a spoiler 1-1, a spoiler 2-2, a spoiler 3-3, a spoiler 4-4, an airplane wing back beam 5, a flap cabin 6, a spoiler suspension main joint 7, an auxiliary front joint 8 and an auxiliary rear joint 9.

Detailed Description

This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.

An aircraft spoiler installation method comprising the steps of:

preparing 4 groups of spoiler suspension joints, wherein each group of spoiler suspension joints comprises 1 spoiler suspension front main joint, 1 spoiler suspension rear main joint, 1 auxiliary front joint and 1 auxiliary rear joint;

measuring the distance between intersection point holes of suspension joints of all spoilers and the plane of a back beam of the airplane wing after installation, and ensuring that the distance tolerance is controlled between-0.2 mm and 0;

thirdly, assembling a spoiler suspension front main joint and spoiler suspension front and rear joints by taking cross point holes of all spoiler suspension joints as an assembling and positioning reference to manufacture a spoiler suspension main joint;

fourthly, positioning and installing the rear beam of the airplane wing by taking the spoiler suspension main joint as a reference;

fifthly, installing an auxiliary front joint and an auxiliary rear joint;

and step six, installing and connecting the spoiler with the spoiler suspension joint.

And seventhly, adjusting the shape and the step difference between every two spoilers respectively, and measuring the gap after the spoilers are installed.

And step eight, checking the movement performance of the opening angle of the spoiler.

And in the fourth step, when the rear beam of the airplane wing is inconsistent with the main spoiler suspension joint, the contact plane of the rear beam of the airplane wing and the main spoiler suspension joint is adjusted, and the accuracy of the joint intersection point is ensured.

And fifthly, mounting the auxiliary front joint and the auxiliary rear joint by taking intersection point holes of all spoiler suspension joints as an assembling and positioning reference.

After the fifth step, before the lower frame, the coaxiality of the intersection points and the gap of the notch of the suspension joint of the spoiler are checked, and the checking requirement is as follows: the coaxiality of the intersection points is less than 0.3mm, and the gap of the notch is less than 0.5 mm.

And fifthly, before the spoiler is lifted off, a shape-preserving tool is used for preserving the shape of the intersection point of the suspension joint of the spoiler.

And fifthly, after the assembly, adding a spoiler simulation piece on the assembly tool, and finishing the gap coordination repair between the assembled skin T-shaped material and the front edge of the spoiler after the installation of the flap cabin upper skin T-shaped material by taking the spoiler simulation piece as a coordination reference. Another embodiment of the present invention is described below with reference to the drawings.

A method for installing the spoilers of airplane includes such steps as installing the spoilers shown in FIG. 1, dividing them into No. 1 spoiler 1, No. 2 spoiler 2, No. 3 spoiler 3 and No. 4 spoiler 4, installing 4 spoilers on the back beam 5 of airplane wing, and installing the wing opening cabin 6

The invention uses the cross point hole of the main joint and the auxiliary joint hung on the spoiler as the reference, realizes the installation coordination between the main joint and the auxiliary joint, controls the position of the beam plane, adopts the joint cross point shape-preserving tool, ensures the coaxiality of the joint cross point and the gap of the notch, controls the deformation of the installation cross point of the spoiler, determines the gap coordination reference between the front edge of the spoiler and the butt joint structure by adding the spoiler simulation part, installs the airplane wing spoiler meeting the design requirement, and realizes the purpose of the opening angle and the movement performance requirement of the spoiler.

The joint shown in fig. 2 was used: the spoiler suspends a main joint 7, an auxiliary front joint 8 and an auxiliary rear joint 9.

The method specifically comprises the following steps:

1. the tolerance of the spoiler suspension main joint, the intersection point hole of the auxiliary joint and the plane of the airplane wing back beam is controlled to be-0.2-0, and the deviation direction of the end face of the spoiler suspension joint back beam and the plane of the airplane wing back beam is ensured to be consistent;

2. the assembly of the spoiler suspension main joint is completed by taking the cross point hole of the spoiler suspension joint as an assembly positioning reference, then the plane wing back beam is positioned by taking the spoiler suspension main joint as a reference, and when the plane of the beam is inconsistent with the joint, the plane of the plane wing back beam of the plane is adjusted to ensure the accuracy of the joint cross point;

3. completing the repairing connection of the spoiler suspension joint and the airplane wing back beam;

4. the coaxiality of intersection points and the gap of a notch of a suspension joint of a spoiler are checked before a rear beam assembly of an airplane wing is put on a lower frame, the coaxiality of the intersection points is less than 0.3, and the gap of the notch is less than 0.5 mm;

5. before the airplane wing back beam assembly is put on the shelf, a shape-preserving tool is adopted to preserve the shape of the intersection point of the suspension joint of the spoiler;

6. adding a spoiler simulation piece on an assembly tool, and finishing the gap coordination repair between the mounted skin T-shaped material on the flap cabin and the front edge of the spoiler by taking the spoiler simulation piece as a coordination reference;

7. removing the protective frame, and then installing and connecting the spoiler and the spoiler suspension joint;

8. and adjusting the appearance and the step difference between every two spoilers respectively, and measuring the gap after the spoilers are installed.

9. The motion performance of the opening angle of the spoiler is checked.