A tooling for inspecting the condition of engine bearings on an on-wing aircraft

Abstract

This utility model discloses a fixture for inspecting the condition of engine bearings on a winged aircraft. It includes a bracket, a screw, and a pressure plate mounted on the aircraft's observation window. The bracket has a mounting surface with an oblong hole. The pressure plate is mounted on the mounting surface by a locking screw and has a stepped through hole, which is a strip-shaped through hole extending in the same direction as the oblong hole. A threaded sleeve is threaded onto the screw, with its bottom engaged within the stepped through hole. The sleeve can move along the extension direction of the stepped through hole. The bottom of the screw passes through the stepped through hole and the oblong hole sequentially, and a copper sleeve is mounted on the top of the screw. The advantages of this utility model are: when mounted on the aircraft's observation window, rotating the screw brings the copper sleeve into contact with the sensor probe. During testing, simply pressing the screw ensures the sensor probe's position is fixed, thus guaranteeing measurement accuracy, reducing measurement errors, and avoiding human error.

Description

Technical Field

[0001] This utility model relates to the field of condition inspection of on-wing aircraft engine bearings, and in particular to a tooling for condition inspection of engine bearings on on-wing aircraft. Background Technology

[0002] The aircraft engine is the power plant of fighter jets, and the condition of the engine bearings directly affects the aircraft's operational safety. Currently, the most common method for field inspections is to use Vadim sensors (for inspecting bearings) in situ.

[0003] Because the bearing inspection location is at the tail of the aircraft, the personnel stand with one foot on the ladder and one foot on the aircraft (the ladder is about 1 meter away from the inspection site) and hold the Vajim in place by hand. This poses a risk of unstable pressure and personnel falling off the ladder. Moreover, the Vajim sensor is extremely sensitive, and even slight changes in the pressure applied to the sensor can trigger the Vajim malfunction indicator light. Especially during long-term inspections, the fatigue of the inspector can lead to personnel safety risks, a significant decrease in the accuracy of the inspection results, and repeated confirmations, resulting in a long inspection cycle and posing a great threat to flight safety.

[0004] Moreover, the above-mentioned testing has two prominent problems. First, there is the issue of personnel safety. Currently, maintenance and support personnel mainly hold the sensor probe with one hand and the Vadim device with the other, relying entirely on their own body balance to ensure safety on the aircraft. This may lead to personnel losing their balance and falling off the ladder during the inspection process. Second, the measurement data contains errors and inaccurate results. Because the Vadim device's sensor is a highly sensitive probe, even slight changes in the pressure applied to the sensor may trigger the Vadim malfunction indicator light. Especially when personnel conduct inspections for extended periods, the accuracy of the inspection results decreases significantly. Repeated confirmations lead to long inspection cycles, which cannot meet the requirements for aircraft sortie training. In severe cases, inaccurate data poses a significant safety hazard to the aircraft. Utility Model Content

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a tooling for inspecting the condition of engine bearings on winged aircraft.

[0006] The object of the present utility model is achieved through the following technical solutions: A tool for inspecting the state of engine bearings on an in-wing aircraft, comprising a bracket, a screw rod, and a pressing plate installed on the aircraft observation window. The bracket has an installation plane, and a waist-shaped hole is opened on the installation plane. The pressing plate is installed on the installation plane through a locking screw, and a stepped through-hole is opened on the pressing plate. The stepped through-hole is a strip-shaped through-hole, and the extending direction of the strip-shaped through-hole is the same as that of the waist-shaped hole. A nut sleeve is installed on the screw rod in a threaded fit manner. The bottom of the nut sleeve is stuck in the stepped through-hole, and the nut sleeve can move in the extending direction of the stepped through-hole. The bottom of the screw rod sequentially passes through the stepped through-hole and the waist-shaped hole, and a copper sleeve is installed at the top of the screw rod.

[0007] Optionally, the nut sleeve is a cylinder structure with a smaller upper part and a larger lower part, and two symmetric flat surfaces are opened on the cylinder at the bottom of the nut sleeve. The widths of the two flat surfaces match the width of the large hole of the stepped through-hole.

[0008] Optionally, clamping parts are provided at both ends of the bracket. Clamping grooves are opened on the clamping parts, and through-holes vertically penetrating the clamping parts are provided, and the through-holes penetrate the clamping grooves.

[0009] Optionally, the bracket is a "U"-shaped bracket.

[0010] Optionally, a threaded connection head is provided at the bottom of the screw rod, and a threaded hole is opened at the top of the copper sleeve. The threaded connection head is threadedly connected to the threaded hole.

[0011] Optionally, a receiving groove for accommodating a sensor probe is opened at the bottom of the copper sleeve.

[0012] The present utility model has the following advantages: The tool for inspecting the state of engine bearings on an in-wing aircraft of the present utility model is installed on the aircraft observation window. By rotating the screw rod, the copper sleeve contacts the sensor probe. During testing, only by pressing the screw rod, the position of the sensor probe can be ensured to be fixed, thereby ensuring the measurement accuracy, reducing the measurement error, avoiding human errors, and at the same time solving the safety risks of unstable pressing and falling off the ladder by maintenance personnel and support personnel during inspection at the aircraft ladder and the aircraft vertical fin. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 is a schematic structural diagram of the present utility model;

[0014] Figure 2 is a schematic structural diagram of the pressing plate;

[0015] Figure 3 is a schematic structural diagram of the nut sleeve;

[0016] In the figure, 1-bracket, 2-pressure plate, 3-screw sleeve, 4-screw, 5-copper sleeve, 6-locking screw, 7-sensor probe, 11-clamping groove, 12-through hole, 13-mounting plane, 14-slender hole, 15-clamping part, 21-stepped through hole, 31-flat surface, 41-threaded connection section, 51-accommodating groove. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can typically be arranged and designed in various different configurations.

[0018] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0019] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other.

[0020] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0021] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0022] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0023] like Figure 1 As shown, a tooling for inspecting the condition of engine bearings on an aircraft includes a bracket 1, a screw 4, and a pressure plate 2 mounted on the aircraft observation window. The bracket 1 has a mounting surface 13 with an oblong hole 14. The pressure plate 2 is mounted on the mounting surface 13 by a locking screw 6 and has a stepped through hole 21, which is a strip-shaped through hole and extends in the same direction as the oblong hole 14. A threaded sleeve 3 is threaded onto the screw 4, with its bottom engaged in the stepped through hole 21 and movable in the extending direction of the stepped through hole 21. The bottom of the screw 4 passes through the stepped through hole 21 and the oblong hole 14 in sequence, and a copper sleeve 5 is mounted on the top of the screw 4. In use, the bracket 1 is fixedly mounted on the aircraft observation window. The dimensions correspond to the positioning holes on the aircraft observation window. After the bracket 1 is installed, the copper sleeve 5 can be adjusted to be above the sensor probe 7. In this embodiment, the screw sleeve 3 is fitted onto the screw 4, and then the screw sleeve 3 is placed on the stepped through hole 21. At this time, the bottom of the screw 4 passes through the waist-shaped hole 14, and then the copper sleeve 5 is installed on the top of the screw 4. Then the position of the screw sleeve 3 in the stepped through hole 21 is adjusted so that the copper sleeve 5 is adjusted to be above the sensor probe 7. Then the screw 4 is rotated so that the copper sleeve 5 moves downward and finally contacts the sensor probe 7. Then the screw 4 is pressed by hand to ensure that the sensor probe 7 cannot be displaced. After the test is completed, the operator lifts the screw 4 upward and can remove the screw sleeve 3 from the stepped through hole 21, so that the copper sleeve 5 is detached from the sensor probe 7.

[0024] In this embodiment, the screw sleeve 3 is a cylindrical structure with a smaller top and a larger bottom. Two symmetrical flat surfaces 31 are provided on the bottom cylinder of the screw sleeve 3. The width of the two flat surfaces 31 matches the width of the large hole of the stepped through hole 21. Therefore, when the screw sleeve 3 is installed in the stepped through hole 21, the stepped surface of the stepped through hole 21 can prevent the screw sleeve 3 from passing through the small hole of the stepped through hole 21. The flat surfaces 31 fit with the flat surfaces of the corresponding large holes of the stepped through holes 21, so that the screw sleeve 3 can only move along the extension direction of the stepped through hole 21. At the same time, when the screw 4 is rotated, the screw sleeve 3 can stop the rotation, which facilitates the rotation of the screw 4.

[0025] In this embodiment, clamping portions 15 are provided at both ends of the bracket 1. A clamping groove 11 is formed in the clamping portion 15, and a through hole 12 vertically penetrating the clamping portion 15 is provided, and the through hole 12 penetrates the clamping groove 11. There is a positioning hole on the aircraft observation window. During use, the clamping groove 11 is used to clamp the aircraft observation window, and the through hole is aligned with the positioning hole, and then the clamping portion 15 and the aircraft observation window are locked with bolts, thereby ensuring the fixed installation of the bracket 1 and the aircraft observation window.

[0026] In this embodiment, the bracket 1 is a "U"-shaped bracket 1, so that the installation plane 13 and the clamping portion 15 are not in the same plane, and the installation plane 13 is higher than the plane where the clamping portion 15 is located, so that the middle part of the bracket becomes prominent, so that there is enough space between the installation plane 13 and the sensor probe 7, which facilitates the installation of the screw sleeve 3 and the screw 4, and the "U"-shaped bracket 1 can also ensure its structural strength.

[0027] In this embodiment, a threaded connection head 41 is provided at the bottom of the screw 4, and a threaded hole is formed at the top of the copper sleeve 5. The threaded connection head 41 is threadedly connected to the threaded hole, so that the copper sleeve 5 can be replaced. Further, a receiving groove 51 for receiving the sensor probe 7 is formed at the bottom of the copper sleeve 5. Therefore, a suitable copper sleeve 5 can be selected according to the model of the sensor probe 7.

[0028] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A tooling for engine bearing condition inspection on a wing aircraft, characterized in that: It includes a bracket, a screw rod and a pressing plate installed on the observation window of an aircraft. The bracket has an installation plane, on which an oblong hole is opened. The pressing plate is installed on the installation plane through a locking screw, and a stepped through hole is opened on the pressing plate. The stepped through hole is a strip-shaped through hole, and the extending direction of the strip-shaped through hole is the same as that of the oblong hole. A screw sleeve is installed on the screw rod in a threaded fit manner. The bottom of the screw sleeve is stuck in the stepped through hole, and the screw sleeve can move in the extending direction of the stepped through hole. The bottom of the screw rod sequentially passes through the stepped through hole and the oblong hole, and a copper sleeve is installed at the top of the screw rod.

2. A tool for engine bearing condition check on a winged aircraft as claimed in claim 1, wherein: The screw sleeve is a cylinder structure with a smaller upper part and a larger lower part, and two symmetrical flat surfaces are opened on the cylinder at the bottom of the screw sleeve. The widths of the two flat surfaces match the width of the large hole of the stepped through hole.

3. A tool for engine bearing condition inspection on a wing aircraft according to claim 1 or 2, characterized in that: Clamping parts are arranged at both ends of the bracket. A clamping groove is opened on the clamping part, and a through hole vertically penetrating the clamping part is opened on the clamping part, and the through hole penetrates the clamping groove.

4. A tool for engine bearing condition inspection on a winged aircraft as claimed in claim 3, wherein: The bracket is a "U"-shaped bracket.

5. A tool for engine bearing condition check on a winged aircraft as claimed in claim 3 wherein: A threaded connection head is arranged at the bottom of the screw rod, a threaded hole is opened at the top of the copper sleeve, and the threaded connection head is threadedly connected with the threaded hole.

6. A tool for engine bearing condition inspection on a winged aircraft as claimed in claim 5, characterized in that: A receiving groove for receiving a sensor probe is opened at the bottom of the copper sleeve.

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