Method for repairing polished rod of aircraft joint rocker arm

Abstract

The invention discloses a method for repairing a polished rod of an aircraft joint rocker arm, which is used for repairing the polished rod of the aircraft joint rocker arm by correcting the axis reference of the polished rod, adding a process chuck, adopting an inner circle die head grinding method and the like. The problems of defects and non-uniform clamping benchmark existing in conventional repairing means of the aircraft joint rocker arm are solved, the repairing performance is obviously improved, and meanwhile economic losses caused by part scrapping are reduced. And the technical problems that the surface of an existing joint rocker polished rod is abraded, the original machining standard is damaged, and conventional repairing and reusing cannot be conducted are solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of machining, more particularly to a method for repairing a light rod of a joint rocker arm of an airplane. BACKGROUND

[0002] TC4 alloy is an alpha-beta type two-phase titanium alloy, has excellent comprehensive performance and long time working temperature 400℃, is widely used in the field of aviation. The main material of the joint rocker arm of the airplane is TC4 titanium alloy, which plays a role of flow distribution in the hydraulic system of the airplane. In the working process, the matching surfaces contact and rotate each other, the light rod of the rocker arm is worn, which directly affects the sealing performance and reliability of the hydraulic system. The surface (working surface) of the worn joint rocker arm light rod is repaired by additive and subtractive methods to restore the size and shape accuracy of the joint rocker arm light rod, improve the wear resistance of the light rod, and reduce the production cost.

[0003] As shown in Figure 1 The joint rocker arm 1 is in a "U" shape structure, which includes a connecting shaft 11 and two light rods 12 connected at both ends of the connecting shaft 1. The working surfaces of the two light rods 12 are worn, and the repair of the joint rocker arm light rod is completed by the additive and subtractive machining method. However, due to long-term use, the joint rocker arm is deformed and the original processing reference is damaged, so that the conventional repair and reuse cannot be carried out. Moreover, due to the influence of the layout of the two light rods, the repair operation space is limited, the light rod has no clamping part and reference for machining, and the repair difficulty is great. The conventional repair method is to separate the connecting shaft and the light rod, repair the light rod of the rocker arm, and then weld and assemble the repaired light rod and the connecting shaft. This method has long repair cycle and poor sealing after welding. SUMMARY

[0004] Therefore, the present application provides a method for repairing a light rod of a joint rocker arm of an airplane to solve the technical problems that the surface of the joint rocker arm light rod is worn and the original processing reference is damaged, so that the conventional repair and reuse cannot be carried out.

[0005] In order to achieve the above-mentioned purpose, the present application adopts the following technical scheme: A method for repairing a light rod of a joint rocker arm of an airplane, comprising the following steps: Step 1, part straightening: straightening the two light rods on the joint rocker arm by a straightening machine to ensure that the axes of the two light rods are parallel; Step 2, increase process chuck: install process chucks on both sides of the connecting shaft to facilitate subsequent process clamping treatment, and the two process chucks are arranged opposite to the positions of the two light rods; Step 3, repair the size of the light rod: the joint rocker is clamped on the grinding machine through the process chuck, the size of the light rod before spraying is ground, the consistency of the size of the light rod is ensured, and the spraying operation is facilitated, and at the same time, the surface plating is removed, the bonding force of the sprayed layer is improved, and the repaired light rod is more wear-resistant and has higher reliability; Step 4, repair site spraying treatment: The joint rocker is fixed on the spraying machine through the process chuck, and the repair site of the light rod is treated by WC spraying; Step 5, size repair of spraying: The joint rocker is fixed on the grinding machine through the process chuck, and the spraying surface of the light rod is ground to ensure that the light rod processing meets the requirements.

[0006] In step 1, after the light rod is straightened, the straightened joint rocker is also subjected to incomplete annealing to eliminate internal residual stress, improve its dimensional stability and machining accuracy.

[0007] The specific content of step 5 is that the process chuck is installed in the Morse taper handle chuck on the internal grinding machine, and the internal circular die head is used to grind the surface of the light rod.

[0008] In step 2, after the process chuck is welded, the surface of the process chuck is processed to make the fitting gap between the process chuck and the Morse taper handle chuck 0.01mm, and at the same time, the coaxiality between the process chuck and the light rod is ensured to be within 0.01mm.

[0009] After step 5, the part is also detected, and after the detection is qualified, the process chuck is removed, and then the part is subjected to incomplete annealing to reduce the stress deformation of the part.

[0010] The purpose of the present application is to provide a kind of joint rocker light rod repair method of aero-engine, to solve the current joint rocker light rod surface wear, after repair by WC powder spraying material, light rod subtractive processing has no clamping surface, no clamping reference, grinding space is limited and other technical problems.The present application corrects the light rod axis reference, increases the process chuck, and adopts internal circular die head grinding method to repair a kind of joint rocker light rod of aero-engine.The drawbacks of conventional repair means of joint rocker of aero-engine and the problem of non-uniform clamping reference are solved, the repair performance is obviously improved, and the economic loss caused by part scrap is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0011] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only embodiments of the present application, and those skilled in the art can obtain other drawings according to the provided drawings without creating any inventive labor.

[0012] Figure 1 The structure diagram of the joint rocker after adding the process chuck is provided.

[0013] Figure 2 The schematic diagram of the joint rocker fixed on the internal grinding machine. DETAILED DESCRIPTION

[0014] Embodiments of the present application are described in detail below with reference to the accompanying drawings, in which the same or similar elements or elements having the same or similar functions are denoted by the same or similar reference numerals throughout. The embodiments described below by reference to the accompanying drawings are exemplary and are intended to explain the present application, and cannot be understood as limiting the present application. In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second" are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise explicitly specified and limited. In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0015] The specific implementation method is as follows: The embodiment of the present application discloses a method for repairing the light pole of the joint rocker of the airplane, comprising the following steps: Step 1, part straightening: straighten the two light poles 12 on the joint rocker 1 through a straightening machine, ensure that the axes of the two light poles 12 are parallel, and perform incomplete annealing on the straightened joint rocker 1 to eliminate internal residual stress, improve its dimensional stability and machining precision; The purpose of this step is to address the issue that the rocker arm's two guide rod axes deform due to the different force fields applied during operation, thus disrupting the original axial reference and making subsequent repair and assembly impossible. The solution involves two steps: first, straightening the rocker arm guide rods to restore their original state; second, manually aging the rocker arm to remove residual stress and improve its dimensional stability and machining accuracy. Step 2: Add process chucks: Install process chucks 2 on both sides of the connecting shaft 11 by argon arc welding (the material of the process chucks should be the same as that of the connecting shaft, which is conducive to welding and its stability and reliability) to facilitate subsequent process clamping. The two process chucks 2 are respectively arranged opposite to the two smooth rods 12. After welding the process chucks 2, machine the surface of the process chucks 2 so that the fit clearance between the process chucks 2 and the Morse taper shank chuck 3 is 0.01mm, while ensuring that the coaxiality between the process chucks 2 and the smooth rods 12 is within 0.01mm.

[0016] The purpose of this step is to establish a machining process benchmark for the repair of the smooth rod. Therefore, adding a process chuck to the connecting shaft facilitates clamping during subsequent repair operations. Furthermore, due to the limitations of the rocker arm structure, a welded process chuck is used. By converting the benchmark, it is ensured that the axis of the rocker arm smooth rod is consistent with the repair machining benchmark, which not only meets the needs of subsequent repair operations but also guarantees benchmark consistency.

[0017] Step 3, Repair the dimensions of the polished rod: The joint rocker arm 1 is clamped on the grinding machine using the process chuck 2, and the dimensions of the polished rod 12 before spraying are ground to ensure the consistency of the polished rod dimensions and facilitate the spraying operation. At the same time, the surface coating is removed to improve the adhesion and thickness uniformity of the sprayed coating, making the repaired polished rod more wear-resistant and more reliable. Step 4: Spraying treatment on the repaired area: The joint rocker arm 1 is fixed on the spraying machine by the process chuck 2, and the repair part of the smooth rod 12 is treated with WC spraying. The purpose of this step is to use WC powder for high-power spraying to improve the adhesion to the substrate, while the coating surface has high hardness, no pores, good sealing performance, and is more wear-resistant. Step 5, spraying size correction: The joint rocker arm 1 is fixed on the grinding machine by the process chuck 2, and the sprayed surface of the polished rod 12 is ground to ensure that the polished rod 12 meets the requirements.

[0018] Step 5 involves installing the process chuck 2 into the Morse taper shank chuck 3 on an internal grinding machine. The Morse taper shank chuck 3 contains a spring collet to ensure uniform force distribution on the workpiece, resulting in high clamping accuracy controlled within 0.02 mm. The surface of the guide rod 12 is then ground using an internal die 4 and a transverse layered grinding method. After the part passes inspection, the process chuck 2 is removed by turning. Finally, the part undergoes incomplete annealing to reduce stress deformation.

[0019] In this step, due to the limitations of the rocker arm structure, traditional external cylindrical grinding machines cannot grind the polished rod. The "internal grinding external" method (using an internal cylindrical grinding machine to grind the rocker arm polished rod through an internal grinding head) is adopted, which effectively solves the problem of polished rod grinding.

[0020] The relevant process parameters in the above process are as follows: The grinding process parameters in step 3 are as follows: transverse layer grinding method, fully cooled, grinding wheel 401 with a diameter of φ30, material is diamond, grit size is 120 mesh, grinding wheel linear speed is 25m / s, workpiece rotation speed is 120r / min, rough grinding feed: 0.005mm / min, semi-finish grinding feed: 0.004mm / min, finish grinding feed: 0.002mm / min; semi-finish grinding allowance is 0.02mm, finish grinding allowance is 0.01mm; number of grinding passes is 15, and feed rate is 320mm / min.

[0021] Incomplete annealing process parameters in steps 1 and 5: Vacuum heat treatment is used, with a vacuum pressure ≤ 6.66 × 10⁻⁶. -2 Pa, temperature 580±10℃, holding time 180~240min, cool in the furnace to ≤50℃ and then unload.

[0022] The coating grinding process parameters in step 5 are as follows: feed grinding method, sufficient cooling, 401 grinding wheel with a diameter of φ30, diamond material, grit size of 120 mesh, grinding wheel linear speed of 30m / s, workpiece rotation speed of 100r / min, rough grinding feed: 0.005mm / min, semi-finish grinding feed: 0.003mm / min, finish grinding feed: 0.001mm / min; semi-finish grinding allowance of 0.02mm, finish grinding allowance of 0.01mm; number of grinding passes: 25, feed rate of 250mm / min.

[0023] This invention solves the technical problems of unifying the original machining datum with the machining datum before and after repair, as well as the inability to clamp the parts, by designing process datums, clamping methods, and changing traditional grinding methods. Furthermore, using this invention shortens the repair cycle, increases the pass rate, and saves repair costs.

[0024] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0025] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for repairing the smooth rod of an aircraft joint rocker arm, characterized in that, It comprises the following steps: Step 1, straightening of parts: straighten the two light poles (12) on the joint rocker arm (1) through a straightening machine, ensure that the axes of the two light poles (12) are parallel; Step 2, increase the process chuck: install process chucks (2) on both sides of the connecting shaft (11) to facilitate subsequent process clamping processing, the two process chucks (2) are arranged opposite to the positions of the two light poles (12); Step 3, repair the size of the light pole: clamp the joint rocker arm (1) on the grinding machine through the process chuck (2), grind the size of the light pole (12) before spraying, ensure the consistency of the size of the light pole, and facilitate the spraying operation, at the same time, remove the surface plating layer, improve the bonding force of the sprayed layer, make the repaired light pole more wear-resistant and more reliable; Step 4, repair site spraying treatment: Fix the joint rocker arm (1) on the spraying machine through the process chuck (2), and perform WC spraying treatment on the repair site of the light pole (12); Step 5, repair the size of the spraying: Fix the joint rocker arm (1) on the grinding machine through the process chuck (2), and grind the sprayed surface of the light pole (12) to ensure that the light pole (12) meets the requirements.

2. The method of claim 1, wherein the method further comprises: In step 1, after straightening the light pole, the straightened joint rocker arm (1) is also subjected to incomplete annealing to eliminate internal residual stress, improve its dimensional stability and machining accuracy.

3. The method of claim 1, wherein the method further comprises: The specific content of step 5 is: install the process chuck (2) in the Morse taper chuck (3) on the internal grinding machine, and use the internal circular die (4) to grind the surface of the light pole (12).

4. The method of claim 3, wherein the method further comprises: In step 2, after welding the process chuck (2), process the surface of the process chuck (2) to make the gap between the process chuck (2) and the Morse taper chuck (3) 0.01mm, and at the same time ensure that the coaxiality of the process chuck (2) and the light pole (12) is within 0.01mm.

5. The joint rocker arm light pole repair method of claim 1, wherein After step 5, it further comprises part detection, after detection, remove the process chuck (2), and then perform incomplete annealing on the part to reduce stress deformation of the part.

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