Aircraft emergency horizon performance test tool

Abstract

The airplane emergency horizon surface performance test tool 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 invention, different working states of the airplane emergency horizon 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 invention relates to the field of testing and measuring technology, in particular to a tooling fixture used for performance testing of an aircraft emergency horizon. 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 the 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, wherein the indicator tube 1-1 and the gyroscope 1-2 are arranged on the left and right sides of the inner cavity of the housing 1-3. When the aircraft emergency horizon gauge 1 is tested for performance, since there are many test items, the gyroscope 1-2 and the indicator tube 1-1 need to be adjusted in position and angle respectively, and the accuracy requirement is very high. In order to ensure the reliability of the test results, the clamping fixture of the tested piece needs to be optimized in design. Summary of the invention

[0004] The present invention provides an aircraft emergency horizon performance test tool, which aims to simulate the working state of the emergency horizon on the aircraft through the cooperation of a base, a first clamping part, a second clamping part and an adjustment mechanism, and realize the adjustment of different angles and directions of the tested object, so as to achieve the purpose of ensuring the reliability of the test result and the safe flight of the aircraft.

[0005] In order to achieve the above object, the present invention adopts the following technical scheme: A tool for testing performance of an emergency horizon gauge for an aircraft comprises a base, a first clamping part, a second clamping part and a workpiece adjustment mechanism; the base is a rectangular base, and the first clamping part and the second clamping part are installed on the base; the first clamping part is used to position and clamp one side of an indicator tube of a workpiece under test; the second clamping part is used to position and clamp one side of a gyroscope of the workpiece under test; the workpiece adjustment mechanism is assembled with the first clamping part and the second clamping part, and the workpiece adjustment mechanism is used to complete the adjustment of different angles and directions of the workpiece under test.

[0006] The above-mentioned aircraft emergency horizon performance test tooling has a positioning seat, a positioning arm and a positioning clamping screw in the first clamping part, and 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, and 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 arranged 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.

[0007] The above-mentioned aircraft emergency horizon performance test tooling, 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 in the form of an inverted 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, the eccentric roller assembly is installed on the vertical bottom surface of the U-shaped frame, the eccentric roller assembly is arranged in two groups at the same height on the left and right, and a supporting roller and an articulated shaft are provided in each group of the eccentric roller assembly, the supporting roller is butt-jointed with the articulated shaft, and the central axes of the two are staggered.

[0008] In the above-mentioned aircraft emergency horizon performance test tooling, a weight-reducing balancing hole is arranged in the supporting roller, and 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.

[0009] The above-mentioned aircraft emergency horizon performance test tooling, 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 a positioning arm in the first clamping part, and is located in the middle part of the bottom surface of the U-shaped frame of the positioning arm; the eccentric roller adjustment handwheel assembly is fixedly assembled with one end of the hinge shaft of the eccentric roller assembly.

[0010] The above-mentioned aircraft emergency horizon performance test tooling has base leveling bolts at the four corners of the base, and a level is set on the base along the horizontal and vertical edges of the base.

[0011] The above-mentioned aircraft emergency horizon performance test tooling, the positioning clamping screw pin includes a screw pin sleeve and a clamping pin, the screw pin sleeve is assembled with the positioning arm in an interference fit manner, the clamping pin sleeve is sleeved in the screw pin sleeve, and is assembled with the screw pin sleeve through a threaded connection structure.

[0012] The aircraft emergency horizon performance test fixture 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.

[0013] The aircraft emergency horizon performance test fixture 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 the insert is located above the eccentric roller assembly.

[0014] The present invention provides an aircraft emergency horizon performance test tool, which can accurately simulate different working states of the emergency horizon on the aircraft through the cooperation of a base, a first clamping part, a second clamping part and an adjustment mechanism, has the characteristics of flexible adjustment, simple operation and strong versatility, realizes the adjustment of different angles and directions of a tested piece, and achieves the purpose of ensuring the reliability of the test result and the safe flight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the structure of an aircraft emergency horizon table (the workpiece being tested); Figure 2 It is a schematic diagram of the overall structure of the present invention; Figure 3 yes Figure 2 K-direction view; Figure 4 yes Figure 3 Schematic diagram of the AA section structure; Figure 5 yes Figure 3 Schematic diagram of the structure of the middle BB section; Figure 6 yes Figure 5 The enlarged view of the structure at position Ⅰ in the middle; Figure 7 It is a schematic diagram of the eccentric roller structure; Figure 8 yes Figure 7 Side view of Fig. 9 , Fig.10 It is a schematic diagram of the present invention and the workpiece assembly structure.

[0016] Explanation of the symbols in the figure: 1 is the aircraft emergency horizon, 1-1 is the indicator tube, 1-2 is the gyroscope, and 1-3 is the outer shell; 2 is a base; 3 is a positioning seat; 4 is a positioning arm; 5 is a housing clamping seat, 5-1 is an upper horizontal wall of the tilted U-shaped frame, 5-2 is a slot, 5-3 is a tightening screw hole, and 5-4 is an insert; 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; 7 is a level; 8 is a supporting sheet; 9 is the base leveling bolt; 10 is a positioning clamping screw pin, 10-1 is a screw pin sleeve, and 10-2 is a clamping pin; 11 is a workpiece indicator tube leveling adjustment nut assembly; 12 is a positioning pin, 12-1 is a locking screw; 13 is an eccentric roller adjustment hand wheel assembly; 14 is a clamping screw; D1 is the first clamping portion, and D2 is the second clamping portion. DETAILED DESCRIPTION

[0017] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0018] 1 , an aircraft emergency horizon gauge 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 .

[0019] See Figure 1. Figure 2 , Figure 3 When performing a performance test on an aircraft emergency horizon gauge 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 gauge 1, the present invention provides an aircraft emergency horizon gauge performance test tool, which includes a base 2, a first clamping part D1, and a second clamping part D2; the base 2 is a rectangular base, and the first clamping part D1 and the second clamping part D2 are installed on the base, and the first clamping part D1 and the second clamping part D2 are arranged on the left and right, and 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 horizontal and longitudinal edges of the base; the first clamping part D1 is used to position and clamp one side of the indicator tube 1-1 of the tested workpiece 1; the second clamping part D2 is used to position and clamp one side of the gyroscope 1-2 of the tested workpiece 1.

[0020] See also Figure 3 , Figure 4 The aircraft emergency horizon performance test tooling described in the present invention has 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, 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 arranged 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 assembled with the screw sleeve 10-1 through a threaded connection structure.

[0021] See also Figure 3 , Figure 5The aircraft emergency horizon performance test tooling described in the present invention has an outer shell clamping seat 5, an eccentric roller assembly 6 and a support sheet 8 in its second clamping portion D2; the outer shell clamping seat 5 is an inverted U-shaped frame structure, and the horizontal wall located at the lower part is fixedly assembled with the base 2, and the support sheet 8 is installed at the front end of the horizontal wall. An inward plug-in structure is arranged on the top of the support sheet 8, which can be inserted into the structure corresponding to the gyroscope 1-2 of the tested workpiece, and the eccentric roller assembly 6 is installed on the vertical bottom surface of the U-shaped frame of the outer shell clamping seat 5 and an insert sheet 5-4 is arranged, and a slot 5-2 is arranged on the upper horizontal wall 5-1 of the inverted U-shaped frame, and a clamping screw hole 5-3 is arranged on the upper part of the slot 5-2, and a clamping screw 14 is installed in the clamping screw hole 5-3, and the insert sheet 5-4 matches the structure of the gyroscope 1-2 of the tested workpiece, and the insert sheet 5-4 is located above the eccentric roller assembly 6.

[0022] See also Figure 5 , Figure 6 , Figure 7 , Figure 8 In the aircraft emergency horizon performance test tooling described in the present invention, 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 connected to the hinge shaft 6-1, and the central axes of the two are staggered. 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 located on one side of the hinge shaft 6-1, and its central axis is parallel to the central 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.

[0023] See also Figure 2 , Figure 3 , Figure 5 The aircraft emergency horizon performance test tooling described in the present invention 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, and 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, so as to adjust the height and spatial angle of the workpiece gyroscope 1-2.

[0024] See also Figure 2 , Figure 3 , Fig. 9 , Fig.10The present invention provides an aircraft emergency horizon performance test tool. When the aircraft emergency horizon 1 is subjected to a performance test on the ground, the indicator tube 1-1 and the gyroscope 1-2 of the workpiece to be tested can be clamped and positioned by the first clamping part D1 and the second clamping part D2, respectively. The positioning arm 4 of the first clamping part D1 can realize spatial flipping 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 workpiece to be tested, and the spatial posture of the workpiece can be adjusted through 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 top screw 12-1 on the positioning pin shaft 12.

Claims

1. An aircraft emergency horizon performance test tool, characterized in that: 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 to position and clamp one side of an indicator tube (1-1) of a workpiece (1) to be tested; the second clamping part (D2) is used to position and clamp one side of a gyroscope (1-2) of the workpiece (1) to be tested; the workpiece adjustment mechanism is assembled with the first clamping part (D1) and the second clamping part (D2), and the workpiece adjustment mechanism is used to complete the adjustment of different angles and directions of the workpiece to be tested.

2. The aircraft emergency horizon performance test tool according to claim 1, characterized in that: A positioning seat (3), a positioning arm (4) and a positioning clamping screw (10) are arranged 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 arranged 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 aircraft emergency horizon performance test tool according to claim 2, characterized in that: The second clamping portion (D2) is provided with an outer shell clamping seat (5), an eccentric roller assembly (6) and a support plate (8); the outer shell clamping seat (5) is in the form of an inverted U-shaped frame structure, the horizontal wall at the bottom 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) is butt-jointed with the hinge shaft (6-1), and the central axes of the two are staggered.

4. The aircraft emergency horizon performance test tool according to claim 3 is characterized by: 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 aircraft emergency horizon performance test tool 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 aircraft emergency horizon performance test tool 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 gauge (7) is provided on the base (2) along the transverse and longitudinal edges of the base.

7. The aircraft emergency horizon performance test tool according to claim 2, characterized in that: The positioning clamping screw pin (10) comprises a screw pin sleeve (10-1) and a clamping pin (10-2); the screw pin 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 pin sleeve (10-1) and assembled with the screw pin sleeve (10-1) via a threaded connection structure.

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

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