Clamping device for airplane emergency horizon meter test

Abstract

A clamping device for airplane emergency horizon meter testing comprises a base, a first clamping part, a second clamping part and a workpiece adjusting mechanism. The base is a rectangular base, and the first clamping part and the second clamping part are mounted on the base; the first clamping part is used for positioning and clamping one side of an indicating cylinder of a tested workpiece; the second clamping part is used for positioning and clamping one side of the gyroscope of the tested workpiece; and the workpiece adjusting mechanism is assembled with the first clamping part and the second clamping part, and adjustment of different angles and directions of the tested workpiece is completed through the workpiece adjusting mechanism. According to the utility model, different working states of the airplane emergency horizon meter can be simulated, and the purposes of ensuring the reliability of a test result and safe flight of an airplane are achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of testing and measuring, in particular to a tested workpiece clamping device used for aircraft emergency horizon test. Background Art

[0002] The main function of the emergency horizon indicator on an aircraft is to provide the pilot with effective indications of pitch and bank attitude angles within a certain period of time by utilizing the long inertial operation time of its internal gyro motor when the inertial navigation subsystem and the backup attitude and heading system are invalid. Therefore, the emergency horizon indicator on an aircraft is an important component to ensure safe flight, and its performance needs to be tested during aircraft maintenance operations.

[0003] As attached Figure 1 As shown, an aircraft emergency horizon gauge 1 includes an indicator tube 1-1, a gyroscope 1-2, and a housing 1-3. The indicator tube 1-1 and gyroscope 1-2 are positioned on the left and right sides of the interior of the housing 1-3. During performance testing of the aircraft emergency horizon gauge 1, the numerous test items require position and angle adjustment of the gyroscope 1-2 and indicator tube 1-1, respectively. This requires very high precision, and to ensure the reliability of the test results, an optimized design of the clamping device for the test piece is required. Utility Model Content

[0004] The utility model provides a clamping device for testing an emergency horizon gauge on an aircraft. The device is designed to simulate the working state of the emergency horizon gauge on an aircraft through the cooperation of a base, a first clamping part, a second clamping part and an adjustment mechanism, so as to adjust the tested object to different angles and directions, thereby ensuring the reliability of the test results and the safe flight of the aircraft.

[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0006] A clamping device for testing an emergency horizon gauge of an aircraft comprises a base, a first clamping portion, a second clamping portion and a workpiece adjustment mechanism; the base is a rectangular base, on which the first clamping portion and the second clamping portion are mounted; the first clamping portion is used to position and clamp the indicator tube side of the tested workpiece; the second clamping portion is used to position and clamp the gyroscope side of the tested workpiece; the workpiece adjustment mechanism is assembled with the first clamping portion and the second clamping portion, and adjustment of different angles and directions of the tested workpiece is completed through the workpiece adjustment mechanism.

[0007] The above-mentioned clamping device for aircraft emergency horizon test is provided with a positioning seat, a positioning arm and a positioning clamping screw in the first clamping part. The positioning seat and the positioning arm are both U-shaped frame structures. The positioning seat is fixedly assembled with the base through the bottom surface of the U-shaped frame. The two side walls of the U-shaped frame of the positioning seat are hingedly assembled with the positioning arm through the positioning pin shaft, and a locking top screw is provided on the positioning pin shaft. The positioning arm is sleeved inside the positioning seat, and the positioning clamping screws are symmetrically installed on the two side walls of the U-shaped frame of the positioning arm.

[0008] The above-mentioned clamping device for aircraft emergency horizon test, the second clamping part is provided with an outer shell clamping seat, an eccentric roller assembly and a support plate; the outer shell clamping seat is a tilted U-shaped frame structure, the horizontal wall at its lower part is fixedly assembled with the base, the support plate is installed at the front end of the horizontal wall, and the eccentric roller assembly is installed on the vertical bottom surface of the U-shaped frame, the eccentric roller assemblies are arranged in two groups at the same height on the left and right, and a supporting roller and a hinge shaft are provided in each group of eccentric roller assemblies, the supporting roller is docked with the hinge shaft, and the center axes of the two are staggered.

[0009] The above-mentioned clamping device for aircraft emergency horizon test has a weight-reducing balancing hole provided in the supporting roller. The weight-reducing balancing hole is a blind hole with an opening located on one side of the hinge shaft, and its central axis is parallel to the central axis of the supporting roller and the hinge shaft.

[0010] The above-mentioned clamping device for aircraft emergency horizon test, the workpiece adjustment mechanism includes a workpiece indicator tube leveling adjustment nut assembly and an eccentric roller adjustment handwheel assembly; the indicator tube leveling adjustment nut assembly is equipped with the positioning arm in the first clamping part and is located in the middle part of the bottom surface of the positioning arm U-shaped frame; the eccentric roller adjustment handwheel assembly is fixedly assembled with one end of the hinge shaft of the eccentric roller assembly.

[0011] The clamping device for aircraft emergency horizon test has base leveling bolts at the four corners of the base, and a level is provided on the base along the transverse and longitudinal edges of the base.

[0012] The above-mentioned clamping device for aircraft emergency horizon test, the positioning clamping screw includes a screw sleeve and a clamping pin, the screw sleeve is assembled with the positioning arm in an interference fit manner, and the clamping pin is sleeved in the screw sleeve and assembled with the screw sleeve through a threaded connection structure.

[0013] The clamping device for aircraft emergency horizon test is provided with a slot on the upper horizontal wall of the U-shaped frame on which the shell clamping seat is tilted, a clamping screw hole is provided on the upper part of the slot, and a clamping screw is installed in the clamping screw hole.

[0014] The clamping device for aircraft emergency horizon test is provided with an insert in the middle of the vertical bottom surface of the shell clamping seat. The insert matches the gyroscope structure of the tested workpiece and is located above the eccentric roller assembly.

[0015] The utility model provides a clamping device for testing an emergency horizon gauge on an aircraft. The clamping device can accurately simulate different working states of the emergency horizon gauge on an aircraft through the cooperation of a base, a first clamping part, a second clamping part and an adjustment mechanism. The device has the characteristics of flexible adjustment, simple operation and strong versatility, and realizes adjustment of different angles and directions of a tested object, thereby achieving the purpose of ensuring the reliability of test results and the safe flight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the structure of an aircraft emergency horizon (the workpiece being tested);

[0017] Figure 2 It is a schematic diagram of the overall structure of the utility model;

[0018] Figure 3 yes Figure 2 K-direction view;

[0019] Figure 4 yes Figure 3 Schematic diagram of the AA section structure;

[0020] Figure 5 yes Figure 3 Schematic diagram of the BB cross-section structure;

[0021] Figure 6 yes Figure 5 A magnified view of the structure at position Ⅰ in the middle;

[0022] Figure 7 This is a schematic diagram of the eccentric roller structure;

[0023] Figure 8 yes Figure 7 Side view of;

[0024] Figure 9 、 Figure 10 It is a schematic diagram of the utility model and the workpiece assembly structure.

[0025] Explanation of the numbers in the figure:

[0026] 1 is the aircraft emergency horizon indicator, 1-1 is the indicator tube, 1-2 is the gyroscope, and 1-3 is the outer shell;

[0027] 2 is the base;

[0028] 3 is a positioning seat;

[0029] 4 is a positioning arm;

[0030] 5 is the housing clamping seat, 5-1 is the upper horizontal wall of the tilted U-shaped frame, 5-2 is the slot, 5-3 is the tightening screw hole, and 5-4 is the insert;

[0031] 6 is an eccentric roller assembly, 6-1 is a hinge shaft, 6-2 is a supporting roller, and 6-3 is a weight-reducing balancing hole;

[0032] 7 is a level;

[0033] 8 is a supporting sheet;

[0034] 9 is the base leveling bolt;

[0035] 10 is a positioning clamping screw, 10-1 is a screw sleeve, and 10-2 is a clamping pin;

[0036] 11 is a workpiece indicator tube leveling adjustment nut assembly;

[0037] 12 is the positioning pin, 12-1 is the locking screw;

[0038] 13 is an eccentric roller adjustment hand wheel assembly;

[0039] 14 is a compression screw;

[0040] D1 is the first clamping portion, and D2 is the second clamping portion. DETAILED DESCRIPTION

[0041] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0042] 1 , an aircraft emergency horizon 1 includes an indicator tube 1 - 1 , a gyroscope 1 - 2 and a housing 1 - 3 , wherein the indicator tube 1 - 1 and the gyroscope 1 - 2 are arranged on the left and right sides of an inner cavity of the housing 1 - 3 .

[0043] See Figure 1. Figure 2 、 Figure 3When performing a performance test on an aircraft emergency horizon 1, there are many test items, and the gyroscope 1-2 and the indicator tube 1-1 need to be adjusted in direction and angle respectively, and the accuracy requirement is very high. In order to ensure the reliability of the test results and accurately simulate the different working conditions of the aircraft emergency horizon 1, the utility model provides a clamping device for testing an aircraft emergency horizon, which includes a base 2, a first clamping part D1, and a second clamping part D2; the base 2 is a rectangular base, on which the first clamping part D1 and the second clamping part D2 are installed, and the first clamping part D1 and the second clamping part D2 are arranged in a left-right state, and base leveling bolts 9 are provided at the four corners of the base 2, and a spirit level 7 is provided on the base 2 along the horizontal and longitudinal edges of the base; the first clamping part D1 is used to position and clamp the indicator tube 1-1 side of the tested workpiece 1; the second clamping part D2 is used to position and clamp the gyroscope 1-2 side of the tested workpiece 1.

[0044] See Figure 3 、 Figure 4 The clamping device for aircraft emergency horizon test described in the present invention is provided with a positioning seat 3, a positioning arm 4 and a positioning clamping screw 10 in its first clamping part D1; the positioning seat 3 and the positioning arm 4 are both U-shaped frame structures, the positioning seat 3 is fixedly assembled with the base 2 through the bottom surface of the U-shaped frame, and the positioning arm 4 is hingedly assembled on the two side walls of the U-shaped frame of the positioning seat 3 through the positioning pin shaft 12, and a locking top screw 12-1 is provided on the positioning pin shaft 12; the positioning arm 4 is sleeved inside the positioning seat 3, and the positioning clamping screw 10 is symmetrically installed on the two side walls of the U-shaped frame of the positioning arm 4; the positioning clamping screw 10 includes a screw sleeve 10-1 and a clamping pin 10-2, the screw sleeve 10-1 is assembled with the positioning arm 4 in an interference fit manner, the clamping pin 10-2 is sleeved in the screw sleeve 10-1, and is assembled with the screw sleeve 10-1 through a threaded connection structure.

[0045] See Figure 3 、 Figure 5 , the clamping device for aircraft emergency horizon test described in the present invention is provided with a shell clamping seat 5, an eccentric roller assembly 6 and a support piece 8 in its second clamping part D2; the shell clamping seat 5 is an inverted U-shaped frame structure, the horizontal wall at the lower part is fixedly assembled with the base 2, and a support piece 8 is installed at the front end of the horizontal wall, and an inward plug-in structure is provided on the top of the support piece 8, which can be inserted into the structure corresponding to the gyroscope 1-2 of the workpiece to be tested, an eccentric roller assembly 6 is installed on the vertical bottom surface of the U-shaped frame of the shell clamping seat 5 and an insert 5-4 is provided, a slot 5-2 is provided on the upper horizontal wall 5-1 of the inverted U-shaped frame, a tightening screw hole 5-3 is provided on the upper part of the slot 5-2, and a tightening screw 14 is fitted in the tightening screw hole 5-3, the insert 5-4 matches the structure of the gyroscope 1-2 of the workpiece to be tested, and the insert 5-4 is located above the eccentric roller assembly 6.

[0046] See Figure 5 、 Figure 6 、 Figure 7 、 Figure 8 , the clamping device for aircraft emergency horizon test described in the utility model, the eccentric roller assemblies 6 in the second clamping part D2 are arranged in two groups at the same height on the left and right, and a supporting roller 6-2 and a hinge shaft 6-1 are provided in each group of eccentric roller assemblies 6, the supporting roller 6-2 is docked with the hinge shaft 6-1, the center axes of the two are staggered, and a weight-reducing balancing hole 6-3 is provided in the supporting roller 6-2, the weight-reducing balancing hole 6-3 is a blind hole with an opening on one side of the hinge shaft 6-1, and its center axis is parallel to the center axes of the supporting roller 6-2 and the hinge shaft 6-1. The stability of the center of gravity of the eccentric roller assembly 6 is ensured by the weight-reducing balancing hole 6-3, so that the supporting roller 6-2 is in a stable balanced state at any position.

[0047] See Figure 2 、 Figure 3 、 Figure 5 The clamping device for aircraft emergency horizon test described in the utility model is also provided with a workpiece adjustment mechanism, which includes a workpiece indicator tube leveling adjustment nut assembly 11 and an eccentric roller adjustment handwheel assembly 13; the indicator tube leveling adjustment nut assembly 11 is equipped with the positioning arm 4 in the first clamping part D1, and is located in the middle part of the bottom surface of the U-shaped frame of the positioning arm 4. The height of the workpiece indicator tube 1-1 can be adjusted by the indicator tube leveling adjustment nut assembly 11; the eccentric roller adjustment handwheel assembly 13 is fixedly assembled with one end of the hinge shaft 6-1 of the eccentric roller assembly 6, and the rotation angle of the supporting roller 6-2 can be adjusted by the eccentric roller adjustment handwheel assembly 13 to achieve the adjustment of the height and spatial angle of the workpiece gyroscope 1-2.

[0048] See Figure 2 、 Figure 3 、 Figure 9 、 Figure 10 The utility model provides a clamping device for testing an aircraft emergency horizon gauge. When the performance test of the aircraft emergency horizon gauge 1 is carried out on the ground, the indicator tube 1-1 part and the gyroscope 1-2 part of the tested workpiece can be clamped and positioned respectively by the first clamping part D1 and the second clamping part D2, wherein the positioning arm 4 of the first clamping part D1 can be spatially flipped around the positioning pin shaft 12, so that the positioning clamping screw 10 on the positioning arm 4 matches the shell 1-3 of the tested workpiece, and the spatial posture of the workpiece can be adjusted by the cooperation between the workpiece indicator tube leveling adjustment nut assembly 11, the handwheel assembly 13 of the second clamping part D2 and the eccentric roller assembly 6 to adapt to different working conditions of the workpiece. After the above adjustment action is completed, the positioning arm 4 is locked and fixed by the locking screw 12-1 on the positioning pin shaft 12.

Claims

1. A clamping device for aircraft emergency horizon test, characterized by: The invention comprises a base (2), a first clamping part (D1), a second clamping part (D2) and a workpiece adjustment mechanism; the base (2) is a rectangular base, and the first clamping part (D1) and the second clamping part (D2) are mounted on the base (2); the first clamping part (D1) is used for positioning and clamping one side of the indicator tube (1-1) of the tested workpiece (1); the second clamping part (D2) is used for positioning and clamping one side of the gyroscope (1-2) of the tested workpiece (1); the workpiece adjustment mechanism is assembled with the first clamping part (D1) and the second clamping part (D2), and the adjustment of the tested workpiece in different angles and directions is completed through the workpiece adjustment mechanism.

2. The clamping device for aircraft emergency horizon test according to claim 1, characterized in that: A positioning seat (3), a positioning arm (4) and a positioning clamping screw (10) are provided in the first clamping portion (D1); the positioning seat (3) and the positioning arm (4) are both U-shaped frame structures, the positioning seat (3) is fixedly assembled with the base (2) through the bottom surface of the U-shaped frame, the two side walls of the U-shaped frame of the positioning seat (3) are hingedly assembled with the positioning arm (4) through the positioning pin shaft (12), and a locking top screw (12-1) is provided on the positioning pin shaft (12), the positioning arm (4) is sleeved inside the positioning seat (3), and the positioning clamping screws (10) are symmetrically installed on the two side walls of the U-shaped frame of the positioning arm (4).

3. The clamping device for aircraft emergency horizon test according to claim 2, characterized in that: The second clamping portion (D2) is provided with a shell clamping seat (5), an eccentric roller assembly (6) and a support plate (8); the shell clamping seat (5) is in the form of an inverted U-shaped frame structure, the horizontal wall at the lower portion is fixedly assembled with the base (2), the support plate (8) is installed at the front end of the horizontal wall, and the eccentric roller assembly (6) is installed on the vertical bottom surface of the U-shaped frame, the eccentric roller assembly (6) is arranged in two groups at the same height on the left and right, and a supporting roller (6-2) and a hinge shaft (6-1) are provided in each group of eccentric roller assemblies (6), the supporting roller (6-2) and the hinge shaft (6-1) are docked, and the central axes of the two are staggered.

4. The clamping device for aircraft emergency horizon test according to claim 3, characterized in that: A weight-reducing balancing hole (6-3) is provided in the supporting roller (6-2), and the weight-reducing balancing hole (6-3) is a blind hole with an opening located on one side of the hinge shaft (6-1), and a central axis thereof is parallel to the central axes of the supporting roller (6-2) and the hinge shaft (6-1).

5. The clamping device for aircraft emergency horizon test according to claim 4, characterized in that: The workpiece adjustment mechanism comprises a workpiece indicator tube leveling adjustment nut assembly (11) and an eccentric roller adjustment handwheel assembly (13); the indicator tube leveling adjustment nut assembly (11) is assembled with the positioning arm (4) in the first clamping portion (D1) and is located in the middle of the bottom surface of the U-shaped frame of the positioning arm (4); the eccentric roller adjustment handwheel assembly (13) is fixedly assembled with one end of the hinge shaft (6-1) of the eccentric roller assembly (6).

6. The clamping device for emergency ground level test of an aircraft according to any one of claims 1 to 5, characterized in that: Base leveling bolts (9) are provided at the four corners of the base (2), and a level (7) is provided on the base (2) along the transverse and longitudinal edges of the base.

7. The clamping device for aircraft emergency horizon test according to claim 2, characterized in that: The positioning clamping screw (10) comprises a screw sleeve (10-1) and a clamping pin (10-2); the screw sleeve (10-1) is assembled with the positioning arm (4) in an interference fit manner; the clamping pin (10-2) is sleeved in the screw sleeve (10-1) and assembled with the screw sleeve (10-1) via a threaded connection structure.

8. The clamping device for aircraft emergency horizon test according to claim 3 or 4, characterized in that: A slot (5-2) is provided on the upper horizontal wall (5-1) of the U-shaped frame tilted and placed in the housing clamping seat (5), a clamping screw hole (5-3) is provided on the upper part of the slot (5-2), and a clamping screw (14) is installed in the clamping screw hole (5-3).

9. The clamping device for aircraft emergency horizon test according to claim 8, characterized in that: An insert (5-4) is provided in the middle of the vertical bottom surface of the shell clamping seat (5), the insert (5-4) matches the structure of the gyroscope (1-2) of the tested workpiece, and the insert (5-4) is located above the eccentric roller assembly (6).

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