Method for measuring assembly clearance of complex-profile aircraft structure

Abstract

The invention relates to the field of aviation equipment manufacturing and repairing, and particularly discloses a complex profile aircraft structure assembly clearance measuring method, which comprises the steps of cleaning a mounting surface when a connecting piece and a connected piece are assembled; uniformly coating a layer of lubricating grease on the cleaned mounting surfaces of the connecting piece and the connected piece; the surface of the mounting surface of the connecting piece and the surface of the mounting surface of the connected piece are evenly coated with filler; the connecting piece and the connected piece are installed; after the filler is solidified, the connecting piece and the connected piece are disassembled, and a solidified filler forming piece between the connecting piece and the connected piece is taken out; and measuring the wall thickness of the filler forming part as the mounting gap. The mounting surface of the complex profile structure is coated with special filler, the thickness of a filler forming part is measured after the filler is cured, a mounting gap value is indirectly obtained, and measurement of the assembly gap between the complex profile structures is completed.

Description

Technical Field

[0001] The invention relates to an assembly gap measurement method, in particular to an assembly gap measurement method for a complex-surface aircraft structure, and belongs to the field of aviation equipment manufacturing and repair. Background Art

[0002] The design, manufacturing, repair and maintenance of aircraft involve structural connection and installation. In order to meet the functionality and structural bearing capacity of the system, the main bearing structures are mostly designed as complex surface structural connection forms. Due to processing and manufacturing errors, the complex surface structural connection form is prone to assembly gaps during assembly. However, the general method of using feeler gauges to measure the assembly gaps between complex surfaces cannot directly measure the assembly gaps. The existence of assembly gaps reduces the actual bearing capacity of the structure and even initiates stress corrosion cracks, affecting the flight safety of the aircraft structure. Summary of the invention

[0003] In view of the problems in the prior art, the present invention provides a method for measuring assembly gaps of complex-profile aircraft structures.

[0004] The purpose of the present invention can be achieved through the following technical solutions:

[0005] A method for measuring assembly clearance of a complex-profile aircraft structure, the method comprising the following steps:

[0006] Step 1: Clean the installation surface of the connecting part and the connected part during assembly;

[0007] Step 2: Apply a layer of grease evenly on the cleaned mounting surfaces of the connector and the connected parts;

[0008] Step 3: Select the preset filler and apply it evenly on the mounting surfaces of the connector and the connected parts;

[0009] Step 4: Install the connecting parts and the connected parts;

[0010] Step 5: After the filler is solidified, the connecting member and the connected member are disassembled and the solidified filler molded part between the connecting member and the connected member is taken out;

[0011] Step 6: Measure the wall thickness of the filler molding to obtain the installation clearance.

[0012] Preferably, the grease in step 2 is 932 aviation low-temperature grease.

[0013] Preferably, the filler used in step 3 is J-190 filler.

[0014] Preferably, in step 4, after the connecting member and the connected member are installed, they are fastened using fasteners so that the installation of the connecting member and the connected member reaches a preset installation torque.

[0015] Preferably, the fastener is a bolt, and corresponding positions on the connecting member and the connected member are penetrated with through holes. After the connecting member and the connected member are installed, the bolt passes through the corresponding through holes to fix the connecting member and the connected member.

[0016] Preferably, a layer of grease is evenly applied on the outside of the bolt before the bolt fixes the connecting member and the connected member.

[0017] Preferably, in step 5, the filler curing temperature is greater than 15° C. and the curing time is greater than 24 hours.

[0018] Preferably, after the filler molded part is taken out in step 5, a preset position on its outer wall is marked as a standard relative position.

[0019] Beneficial effects of the present invention:

[0020] By applying special fillers on the installation surface of complex profile structures, and measuring the thickness of the filler molded parts after the fillers are cured, the installation gap value is indirectly obtained, and the assembly gap measurement between complex profile structures is completed. The effective measurement of the installation gap of complex profile aircraft structures is achieved, and the measurement method is simple and easy to operate; by indirectly obtaining the installation gap value through measurement, corresponding measures can be taken to control the assembly gap, reduce the impact of assembly stress on the structure, and ensure the installation quality of the aircraft structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to facilitate understanding by those skilled in the art, the present invention is further described below with reference to the accompanying drawings.

[0022] Figure 1 Schematic diagram of the connecting piece of the present invention.

[0023] Figure 2 It is a schematic diagram of the connected parts of the present invention.

[0024] Figure 3 It is an isometric view of the connecting member and the connected member after installation of the present invention.

[0025] Figure 4 It is a side view of the connecting member and the connected member after installation of the present invention.

[0026] In the figure: 1. Connecting part; 2. Connected part; 3. Installation gap. DETAILED DESCRIPTION

[0027] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] See also Figure 1-4 As shown, a method for measuring the gap between complex-surface aircraft structures and assembling them comprises the following steps:

[0029] Step 1: Clean the installation surface of the connector 1 and the connected part 2 during assembly to ensure that there are no other inclusions on the installation surface. Finally, there will be only filler in the gap between the connector 1 and the connected part 2 after installation, without other impurities, thereby ensuring that the measured installation gap 3 is more accurate.

[0030] Step 2: Apply a layer of grease evenly on the cleaned mounting surfaces of the connector 1 and the connected part 2. The grease is 932 aviation low temperature grease. The use of 932 aviation low temperature grease makes it difficult for the connector 1, the connected part 2 and the filler molding to adhere to each other, and they can automatically separate when disassembled. The mounting surface is the surface where the connector 1 and the connected part 2 are opposite to each other when they are installed. Applying grease makes it easy to separate the filler molding formed between the two, and then to remove the filler molding.

[0031] Step 3: Select the preset filler, which is J-190 filler, and evenly apply the filler on the mounting surface of the connector 1 and the connected component 2; even coating makes the final filler molding more uniform, making the measured installation gap 3 more accurate. At the same time, it also avoids the situation where the filler is not applied, resulting in a state where a part of the filler molding is missing.

[0032] Step 4: Install the connector 1 and the connected component 2; the connection of complex surface structures is as follows Figure 3 As shown, respectively, by Figure 1 Connector 1 and Figure 2 The connected parts 2 are connected in a nested manner, and after installation, they form Figure 4 The installation gap 3 is formed in the middle. The connected member 2 is sleeved under the connecting member 1, and the bottom end of the connecting member 1 has multiple complex profiles.

[0033] Step 5: After the filler is solidified, remove the bolts, disassemble the connector 1 and the connected part 2, and take out the solidified filler molded part between the connector 1 and the connected part 2; when disassembling the connector 1, the connected part 2, and taking out the filler molded part, do not use sharp knives to pry open the installation surface to avoid damaging the surface of the filler molded part, which will cause a large error in the subsequent thickness measurement. If the connector 1, the connected part 2, and the filler molded part are bonded to each other, you can use a slight tap on the connector 1 or the connected part 2 to remove it normally.

[0034] Step 6: Measure the wall thickness of the filler molding to obtain the installation gap 3.

[0035] Specifically, in step 4, after the connector 1 and the connected member 2 are installed, fasteners are used to fasten them, so that the connector 1 and the connected member 2 are installed to a preset installation torque. Fastening with fasteners to achieve the preset installation torque in the assembly drawing can simulate the state of the connector 1 and the connected member 2 when they are actually assembled, and then obtain the real installation gap 3 between the two. In addition, when the connector 1 and the connected member 2 are installed, not only the installation torque needs to meet the preset standard, but also the relative position of the two after installation must meet the preset standard. For example, after installation, the tops of the connector 1 and the connected member 2 need to be in a flush state so that each installation surface is installed in place.

[0036] Specifically, the fastener is a bolt, and corresponding parts of the connecting member 1 and the connected member 2 are penetrated with through holes. After the connecting member 1 and the connected member 2 are installed, the bolt passes through the corresponding through holes to fix the connecting member 1 and the connected member 2. The bolt is a commonly used process bolt, and the bolt and nut are used together during installation, which is convenient for installation and disassembly, and has a stable fastening force.

[0037] Specifically, before the bolt fixes the connecting member 1 and the connected member 2, a layer of grease is evenly applied to the outside of the bolt, so that the bolt is easily separated from the connecting member 1, the connected member 2 and the filler molded member during subsequent disassembly without causing damage to the filler molded member.

[0038] Specifically, in step 5, the filler curing temperature is greater than 15° C., and the curing time is greater than 24 hours.

[0039] Specifically, in step 5, after the filler molding is taken out, the preset position of the outer wall is marked as the standard relative position. The marked position can be at irregular corners or positions of various flat surfaces, so as to avoid the inability to clearly know the specific direction and position of the corresponding installation surface after the filler molding is taken out, thereby facilitating the subsequent determination of the position for measuring the thickness and improving the accuracy of the measurement.

[0040] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A method for measuring the gap between complex-surface aircraft structures, characterized in that: The measurement method includes the following steps: Step 1: Clean the installation surface of the connecting part and the connected part when assembling; Step 2: Apply a layer of grease evenly on the cleaned mounting surfaces of the connector and the connected parts; Step 3: Select the preset filler and apply it evenly on the mounting surfaces of the connector and the connected parts; Step 4: Install the connecting parts and the connected parts; Step 5: After the filler is solidified, the connecting member and the connected member are disassembled and the solidified filler molded part between the connecting member and the connected member is taken out; Step 6: Measure the wall thickness of the filler molding to obtain the installation clearance.

2. A method for measuring assembly gap of complex-profile aircraft structure according to claim 1, characterized in that: The lubricating grease in step 2 is 932 aviation low temperature lubricating grease.

3. The method for measuring assembly gap of complex-profile aircraft structure according to claim 1, characterized in that: The filler used in step 3 is J-190 filler.

4. The method for measuring assembly gap of complex-surface aircraft structure according to claim 1, characterized in that: In step 4, after the connecting member and the connected member are installed, they are fastened with fasteners so that the installation of the connecting member and the connected member reaches a preset installation torque.

5. The method for measuring assembly gap of complex-profile aircraft structure according to claim 4, characterized in that: The fasteners are bolts, and corresponding positions on the connecting member and the connected member are penetrated with through holes. After the connecting member and the connected member are installed, the bolts pass through the corresponding through holes to fix the connecting member and the connected member.

6. A method for measuring assembly gaps of complex-profile aircraft structures according to claim 5, characterized in that: Before the bolts are used to fix the connecting member and the connected member, a layer of lubricating grease is evenly applied to the outside of the bolts.

7. The method for measuring assembly gap of complex-profile aircraft structure according to claim 1, characterized in that: In step 5, the filler curing temperature is greater than 15° C. and the curing time is greater than 24 hours.

8. The method for measuring assembly gap of complex-profile aircraft structure according to claim 1, characterized in that: In step 5, after the filler molded part is taken out, the preset position on the outer wall is marked as a standard relative position.

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