B737NG aircraft horizontal stabilizer actuator secondary brake function testing and measuring tool
By designing the B737NG aircraft horizontal stabilizer actuator secondary brake function test and measurement tooling, the problems of inaccurate measurement data and cumbersome operation are solved, fast and accurate measurement results are achieved, the testing process is simplified, and the FOD risk is reduced.
Patent Information
- Application Number
- CN202422558260.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-23
- Publication Date
- 2025-07-25
- Estimated Expiration
- 2034-10-23
AI Technical Summary
In the prior art, during the secondary brake function test of the horizontal stabilizer actuator, the measurement data is inaccurate and the operation is complicated. The use of paper tape marking leads to difficulty in measuring, and there are problems with difficult tape cleaning and FOD (flying foreign objects).
A B737NG aircraft horizontal stabilizer actuator secondary brake function test and measurement tool is designed, including a base, an angle measuring instrument, an instrument seat driving mechanism and a locking mechanism. The angle or distance of the actuator screw is directly read through the sliding mechanism and an angle measuring instrument to simplify the measurement process.
Accurate and fast measurement results are achieved, avoiding the use of paper tape, improving measurement efficiency and data accuracy, and reducing operational complexity and FOD risks.
Smart Images
Figure CN223148715U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft maintenance tools, and particularly relates to a test and measurement tool for the secondary brake function of the horizontal stabilizer actuator of a B737NG aircraft. Background Art
[0002] The test of the secondary brake function of the horizontal stabilizer actuator is a frequently performed test item in the regular inspection of the aircraft maintenance machinery specialty. Its main purpose is to test the non-command movement function and locking reliability of the horizontal stabilizer actuator to determine whether the horizontal stabilizer actuator meets the airworthiness requirements. The structure of the horizontal stabilizer lead screw is as shown in the appendix Figure 1 In daily tests, the problem is that when using a torque wrench to rotate the upper stop block 2 of the actuator lead screw 1 clockwise or counterclockwise and measure the angle or distance of the relative rotation of the lead screw with respect to the body, the Boeing manual does not give specific implementation steps and suitable test tools. The current common practice is to use paper tape to stick on the lower end shield of the lead screw and the adjacent actuator body respectively, mark the positions of rotating the lead screw clockwise and counterclockwise at the target torque with a marker pen on the paper tape, then tear off and flatten the tape from the lower end shield of the lead screw and use a vernier caliper to measure the distance marked on the paper tape, and compare it with the standard value in the manual and work card to obtain the test result. Therefore, the required data cannot be directly read during the measurement process, and it takes a long time to convert. Moreover, the use of a marker pen and paper tape will result in inaccurate measurement data. At the same time, there are also problems such as difficult tape cleaning, FOD (foreign object debris), and difficult execution in a narrow space. Summary of the Invention
[0003] The utility model provides a test and measurement tool for the secondary brake function of the horizontal stabilizer actuator of a B737NG aircraft, which can measure both the angle and the distance to overcome the above-mentioned deficiencies in technology.
[0004] The technical solution adopted by the utility model to overcome its technical problems is as follows:
[0005] A test and measurement tool for the secondary brake function of the horizontal stabilizer actuator of a B737NG aircraft, comprising:
[0006] A base, on which an instrument seat is slidably installed horizontally through a sliding mechanism;
[0007] An angle measuring instrument, installed in the instrument seat;
[0008] An instrument seat driving mechanism, arranged on the base, for driving the instrument seat to slide through the sliding mechanism;
[0009] The locking mechanism is arranged at the tail end of the base. The base is locked and fixed on the screw mounting seat at the lower end of the actuator screw through the locking mechanism. The instrument seat driving mechanism drives the instrument seat to move until it contacts the screw guard of the angle measuring instrument. When the actuator screw is rotated by using a torque wrench through the upper stop block, the angle measuring instrument measures the rotation angle or distance of the screw guard.
[0010] Further, the sliding mechanism includes a dovetail groove arranged horizontally in the base and a dovetail guide rail arranged at the lower end of the instrument seat. The instrument seat is slidably mounted in the dovetail groove of the base through the dovetail guide rail.
[0011] Further, the instrument seat driving mechanism includes a screw I screwed into the front end of the base, a ball head arranged at the tail end of the screw I, a ball groove I arranged at the head end of the instrument seat, and clamp block I and clamp block II. The axis of the screw I is arranged horizontally. Screw holes I and screw holes II are respectively arranged on the left and right sides of the ball groove I. Bolt I passes through clamp block I and is screwed into screw hole I, and bolt II passes through clamp block II and is screwed into screw hole II. A hemispherical groove I is arranged on the inner side of clamp block I, and a hemispherical groove II is arranged on the inner side of clamp block II. The hemispherical groove I, the hemispherical groove II and the ball groove I form a limiting ball groove matching the ball head, and the ball head is rotatably mounted in the limiting ball groove.
[0012] Further, the angle measuring instrument includes a rotating shaft IV arranged vertically on the instrument seat, a circular roller rotatably mounted on the rotating shaft IV, and a pointer I and a pointer II respectively arranged on the rotating shaft IV. A distance scale is arranged along the circumferential direction at the outer end of the roller, and the pointer I points to the distance scale. An angle scale is arranged along the circumferential direction at the inner end of the roller, and the pointer II points to the angle scale. The outer ring of the roller contacts the screw guard.
[0013] For the convenience of operation, it further includes a wing nut II. A through hole I is arranged at the head end of the screw I, and a through hole II is arranged on the wing nut II. The wing nut II is screwed onto the head end of the screw I. When the through hole I and the through hole II are rotated to the same axis, a cylindrical pin is inserted into the through hole II and the through hole I.
[0014] Further, the locking mechanism includes a clamping arm I rotatably mounted on the left side of the tail end of the base through a rotating shaft I, a clamping arm II rotatably mounted on the right side of the tail end of the base through a rotating shaft II, a groove arranged at the tail end of the clamping arm I, and a screw II rotatably mounted on the tail end of the clamping arm II through a rotating shaft III. A clamping groove matching the outer shape of the mounting seat is formed among the clamping arm I, the clamping arm II and the base. When the screw II rotates to the horizontal state and is located in the groove, a wing nut I is screwed onto the head end of the screw II, and the mounting seat is clamped and fixed in the clamping groove.
[0015] The beneficial effects of the present utility model are as follows: After adjusting the torque wrench to the target torque value required by the Boeing manual or work card, clamp the torque wrench on the upper stop block at the upper end of the actuator lead screw, apply torque counterclockwise to the actuator lead screw and hold it. The actuator lead screw rotates, and the distance or angle value is read through the angle measuring instrument. Then, perform the same working procedure, apply torque clockwise to the actuator lead screw and hold it. At this time, read the distance or angle value through the angle measuring instrument. The difference between the two readings is the measurement value required by the manual or work card. After comparing with the standard in the manual or work card, the test result is obtained. Description of the Drawings
[0016] Figure 1 It is a three-dimensional structure diagram of the horizontal stabilizer lead screw part of the present utility model;
[0017] Figure 2 It is a three-dimensional structure diagram of the present utility model;
[0018] Figure 3 It is a three-dimensional structure diagram of the use state of the present utility model;
[0019] Figure 4 It is an exploded three-dimensional structure diagram of the angle measuring instrument part of the present utility model;
[0020] Figure 5 It is an exploded three-dimensional structure diagram of the angle measuring instrument part of the present utility model;
[0021] Figure 6 It is a three-dimensional structure diagram of the rolling measuring instrument part of the present utility model;
[0022] In the figure, 1. Actuator lead screw 2. Upper stop block 3. Lead screw guard 4. Lead screw mounting seat 5. Base 6. Instrument seat 7. Screw rod I 8. Angle measuring instrument 9. Rotating shaft I 10. Clamping arm I 11. Rotating shaft II 12. Clamping arm II 13. Card slot 14. Groove 15. Rotating shaft III 16. Screw rod II 17. Wing nut I 18. Ball slot I 19. Clamping block I 20. Clamping block II 21. Screw hole I 22. Screw hole II 23. Bolt I 24. Bolt II 25. Ball head 26. Through hole I 27. Wing nut II 28. Through hole II 29. Hemispherical slot I 30. Hemispherical slot II 31. Cylindrical pin 32. Dovetail groove 33. Dovetail guide rail 34. Rotating shaft IV 35. Roller 36. Pointer I 37. Distance scale 38. Pointer II 39. Angle scale. Detailed Implementation Manner
[0023] The following further describes the present utility model in conjunction with the attached Figure 1 to the attached Figure 6 drawings.
[0024] A secondary brake function test measuring tool for the horizontal stabilizer actuator of a B737NG aircraft, comprising: a base 5, on which an instrument seat 6 is slidably mounted in the horizontal direction through a sliding mechanism; a rotation angle measuring instrument 8, installed in the instrument seat 6; an instrument seat driving mechanism, arranged on the base 5 and used to drive the instrument seat 6 to slide through the sliding mechanism; a locking mechanism, arranged at the tail end of the base 5, and the base 5 is locked and fixed on the lead screw mounting seat 4 at the lower end of the actuator lead screw 1 through the locking mechanism. The instrument seat driving mechanism drives the instrument seat 6 to move until the rotation angle measuring instrument 8 contacts the lead screw guard 3. When the actuator lead screw 1 is rotated by using a torque wrench through the upper stop block 2, the rotation angle measuring instrument 8 measures the rotation angle or distance of the lead screw guard 3 (the measuring position required by the Boeing manual). During use, the base 5 is fixed to the lead screw mounting seat 4 through the locking mechanism. After the torque wrench is adjusted to the target torque value required by the Boeing manual or work card, the torque wrench is clamped on the upper stop block 2 at the upper end of the actuator lead screw 1, and a torque is applied counterclockwise to the actuator lead screw 1 and maintained. The actuator lead screw 1 rotates, and the distance or angle value is read through the rotation angle measuring instrument 8. Then, the same working procedure is executed, and a torque is applied clockwise to the actuator lead screw 1 and maintained. At this time, the distance or angle value is read through the rotation angle measuring instrument 8. The difference between the two readings is the measured value required by the manual or work card. After comparing with the standard in the manual or work card, the test result is obtained.
[0025] In an embodiment of the present invention, the sliding mechanism includes a dovetail groove 32 arranged in the base 5 in the horizontal direction and a dovetail guide rail 33 arranged at the lower end of the instrument seat 6. The instrument seat 6 is slidably mounted in the dovetail groove 32 of the base 5 through the dovetail guide rail 33. The instrument seat 6 realizes its forward and backward sliding along the base 5 through the sliding fit between the dovetail guide rail 33 and the dovetail groove 32.
[0026] In an embodiment of the present utility model, the instrument seat driving mechanism may have the following structure, which includes a screw rod I 7 screwed onto the front end of the base 5, a ball head 25 provided at the tail end of the screw rod I 7, a ball groove I 18 provided at the head end of the instrument seat 6, and a clamping block I 19 and a clamping block II 20. The axis of the screw rod I 7 is arranged in the horizontal direction. Screw holes I 21 and screw holes II 22 are respectively provided on the left and right sides of the ball groove I 18. A bolt I 23 passes through the clamping block I 19 and is screwed into the screw hole I 21, and a bolt II 24 passes through the clamping block II 20 and is screwed into the screw hole II 22. A hemispherical groove I 29 is provided on the inner side of the clamping block I 19, and a hemispherical groove II 30 is provided on the inner side of the clamping block II 20. The hemispherical groove I 29, the hemispherical groove II 30 and the ball groove I 18 form a limiting ball groove matching the ball head 25, and the ball head 25 is rotatably installed in the limiting ball groove. When the screw rod I 7 is rotated, since the screw rod I 7 is in threaded driving connection with the base 5, the screw rod I 7 moves axially while rotating. The clamping block I 19 and the clamping block II 20 cooperate to enclose the ball head 25 at the tail end of the screw rod I 7 in the limiting ball groove. Therefore, when the screw rod I 7 rotates, the ball head 25 can rotate in the limiting ball groove, realizing the driving of the instrument seat 6 to move back and forth relative to the base 5 under the guidance of the sliding mechanism.
[0027] In an embodiment of the present utility model, the angle measuring instrument 8 includes a rotating shaft IV 34 arranged on the instrument seat 6 in the vertical direction, a circular roller 35 rotatably installed on the rotating shaft IV 34, and a pointer I 36 and a pointer II 38 respectively arranged on the rotating shaft IV 34. A distance scale 37 is arranged along the circumferential direction on the outer side end of the roller 35, the pointer I 36 points to the distance scale 37, an angle scale 39 is arranged along the circumferential direction on the inner side end of the roller 35, the pointer II 38 points to the angle scale 39, and the outer ring of the roller 35 is in contact with the lead screw guard 3. When the actuator lead screw 1 is rotated by using a torque wrench through the upper stop block 2, the actuator lead screw 1 drives the lead screw guard 3 to rotate relative to the lead screw mounting seat 4. Since the roller 35 is in contact with the lead screw guard 3, the lead screw guard 3 synchronously drives the roller 35 to rotate when rotating. When the roller 35 rotates, the distance scale 37 and the angle scale 39 rotate accordingly. Therefore, the distance scale 37 and the angle scale 39 can be conveniently read through the pointer I 36 and the pointer II 38.
[0028] In an embodiment of the present utility model, it further includes a wing nut II 27. A through hole I 26 is provided at the head end of the screw rod I 7, a through hole II 28 is provided on the wing nut II 27, and the wing nut II 27 is screwed onto the head end of the screw rod I 7. When the through hole I 26 and the through hole II 28 are rotated to the same axis, a cylindrical pin 31 is inserted into the through hole II 28 and the through hole I 26. At this time, the wing nut II 27 and the screw rod I 7 are rigidly connected, and the screw rod I 7 can be conveniently driven to rotate through the wing nut II 27, improving the convenience of operation.
[0029] In an embodiment of the present utility model, the locking mechanism may have the following structure, which includes a clamping arm I 10 rotatably mounted on the left side of the tail end of the base 5 through a rotating shaft I 9, a clamping arm II 12 rotatably mounted on the right side of the tail end of the base 5 through a rotating shaft II 11, a groove 14 provided at the tail end of the clamping arm I 10, and a screw rod II 16 rotatably mounted at the tail end of the clamping arm II 12 through a rotating shaft III 15. A clamping groove 13 matching the outer shape of the mounting seat 4 is formed among the clamping arm I 10, the clamping arm II 12 and the base 5. When the screw rod II 16 rotates to the horizontal state and is located in the groove 14, the wing nut I 17 is screwed onto the head end of the screw rod II 16, and the mounting seat 4 is clamped and fixed in the clamping groove 13. The clamping arm I 10 and the clamping arm II 12 can play the role of a clamp, so that the base 5 can be quickly fixed on the lead screw guard 3. When disassembling, after loosening the wing nut I 17, the screw rod II 16 is rotated until it disengages from the groove 14, then the clamping arm I 10 can rotate outwardly by using the rotating shaft I 9, and the clamping arm II 12 can rotate outwardly by using the rotating shaft II 11, which can facilitate the removal of the base 5.
[0030] Finally, it should be noted that the above are only the preferred embodiments of the present utility model and are not used to limit the present utility model. Although the present utility model 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 utility model shall be included in the protection scope of the present utility model.
Claims
1. A secondary brake function test and measurement tool for the horizontal stabilizer actuator of a B737NG aircraft, characterized in that, Comprising: A base (5) on which an instrument seat (6) is slidably mounted horizontally through a sliding mechanism; A corner measuring instrument (8) installed in the instrument seat (6); An instrument seat driving mechanism provided on the base (5) for driving the instrument seat (6) to slide through the sliding mechanism; A locking mechanism provided at the tail end of the base (5). The base (5) is locked and fixed to a lead screw mounting seat (4) at the lower end of an actuator lead screw (1) through the locking mechanism. The instrument seat driving mechanism drives the instrument seat (6) to move until the corner measuring instrument (8) contacts the lead screw guard (3). When the actuator lead screw (1) is rotated by using a torque wrench through an upper stop block (2), the corner measuring instrument (8) measures the angle or distance of rotation of the lead screw guard (3).
2. The measuring tool for the secondary brake function test of the horizontal stabilizer actuator of the B737NG aircraft according to claim 1, wherein: The sliding mechanism includes a dovetail groove (32) provided horizontally in the base (5) and a dovetail guide rail (33) provided at the lower end of the instrument seat (6). The instrument seat (6) is slidably mounted in the dovetail groove (32) of the base (5) through the dovetail guide rail (33).
3. The secondary brake function test measurement tooling for the horizontal stabilizer actuator of the B737NG aircraft according to claim 1, characterized in that: The instrument seat driving mechanism includes a screw I (7) screwed into the front end of the base (5), a ball head (25) provided at the tail end of the screw I (7), a ball groove I (18) provided at the head end of the instrument seat (6), and clamp blocks I (19) and clamp blocks II (20). The axis of the screw I (7) is arranged horizontally. Screw holes I (21) and screw holes II (22) are respectively provided on the left and right sides of the ball groove I (18). A bolt I (23) passes through the clamp block I (19) and is then screwed into the screw hole I (21). A bolt II (24) passes through the clamp block II (20) and is then screwed into the screw hole II (22). A hemispherical groove I (29) is provided inside the clamp block I (19), and a hemispherical groove II (30) is provided inside the clamp block II (20). The hemispherical groove I (29), the hemispherical groove II (30), and the ball groove I (18) form a limiting ball groove matching the ball head (25), and the ball head (25) is rotatably installed in the limiting ball groove.
4. The secondary brake function test measurement tooling for the horizontal stabilizer actuator of the B737NG aircraft according to claim 1, characterized in that: The corner measuring instrument (8) includes a rotating shaft IV (34) provided vertically on the instrument seat (6), a circular roller (35) rotatably installed on the rotating shaft IV (34), and a pointer I (36) and a pointer II (38) respectively provided on the rotating shaft IV (34). A distance scale (37) is provided along the circumferential direction on the outer side end of the roller (35), and the pointer I (36) points to the distance scale (37). An angle scale (39) is provided along the circumferential direction on the inner side end of the roller (35), and the pointer II (38) points to the angle scale (39). The outer ring of the roller (35) contacts the lead screw guard (3).
5. The measuring tool for the secondary brake function test of the horizontal stabilizer actuator of the B737NG aircraft according to claim 3, characterized in that: It further includes a wing nut II (27). A through hole I (26) is provided at the head end of the screw I (7), and a through hole II (28) is provided on the wing nut II (27). The wing nut II (27) is screwed onto the head end of the screw I (7). When the through hole I (26) and the through hole II (28) are rotated to the same axis, a cylindrical pin (31) is inserted into the through hole II (28) and the through hole I (26).
6. The secondary brake function test measuring tooling for the horizontal stabilizer actuator of the B737NG aircraft according to claim 1, characterized in that: The locking mechanism includes a clamping arm I (10) rotatably mounted on the left side of the tail end of the base (5) through a rotating shaft I (9), a clamping arm II (12) rotatably mounted on the right side of the tail end of the base (5) through a rotating shaft II (11), a groove (14) provided at the tail end of the clamping arm I (10), and a screw II (16) rotatably mounted at the tail end of the clamping arm II (12) through a rotating shaft III (15). A clamping groove (13) matching the outer shape of the mounting seat (4) is formed among the clamping arm I (10), the clamping arm II (12) and the base (5). When the screw II (16) rotates to the horizontal state and is located in the groove (14), the wing nut I (17) is screwed onto the head end of the screw II (16), and the mounting seat (4) is clamped and fixed in the clamping groove (13).