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CN-115628671-B - Axial clearance measuring device for rotary actuator of aircraft

CN115628671BCN 115628671 BCN115628671 BCN 115628671BCN-115628671-B

Abstract

The axial clearance measuring device for the rotary actuator of the aircraft comprises a workpiece clamping and positioning mechanism and a measuring executing mechanism, wherein the workpiece clamping and positioning mechanism is provided with a base, a side pressing plate and a workpiece positioning pin assembly, a workpiece accommodating cavity is formed in the middle of the base, the side pressing plate comprises two parts which are arranged front and back symmetrically and are respectively arranged on front and back vertical faces of the base, positioning pin holes corresponding to positioning holes in lugs of the rotary actuator are formed in each part, bonding surfaces matched with the angles of the lugs of the rotary actuator are formed in the inner side of each part, the number of the workpiece positioning pin assemblies is identical to that of the positioning holes in the lugs of the rotary actuator, the lugs of the rotary actuator are fixedly connected with the side pressing plate through the workpiece positioning pin assembly, and the measuring executing mechanism is arranged on one side of the base and is provided with a dial indicator. The invention meets the requirement of the maintenance operation standard of the aircraft and achieves the purpose of ensuring the assembly quality of the aircraft after maintenance.

Inventors

  • CUI ZHANBO
  • WANG JIN
  • LI BO
  • ZHANG YINGYING
  • SHA LEI
  • YANG JIANSHAN
  • LI YUXIAO
  • REN FEI
  • LIU QIANG
  • HU SHUXIN
  • WANG ZHICONG
  • JIAO XIAOXUAN
  • ZHANG ZHONGZHOU
  • ZHU ZIHONG
  • ZHANG GUANGBIN

Assignees

  • 中国人民解放军第五七二一工厂

Dates

Publication Date
20260505
Application Date
20220920

Claims (10)

  1. 1. An axial clearance measuring device for a flexible connecting shaft is characterized in that the axial clearance measuring device (2) of a rotary actuator comprises a workpiece clamping and positioning mechanism and a measuring actuating mechanism (2-6), the workpiece clamping and positioning mechanism is provided with a base (2-1), a side pressing plate (2-2) and workpiece positioning pin assemblies, the base (2-1) is of a box frame structure, a workpiece accommodating cavity (2-1-1) is arranged in the middle of the base (2-1), the side pressing plate (2-2) comprises two parts which are symmetrically arranged front and back and are respectively arranged on front and back vertical faces of the base (2-1), positioning pin holes (2-2-1) corresponding to positioning holes on lugs (1-1) of the rotary actuator are formed in each part, bonding surfaces (2-2-2) matched with the lugs of the rotary actuator (1) in angle are formed in the inner side of each part, the number of the workpiece positioning pin assemblies is consistent with the number of the positioning holes on the lugs (1-1), the rotary actuator (1) and the lug plate (1) is fixedly connected with the lug (2-1) on one side of the base (2-1) through the workpiece positioning pin assemblies, a dial indicator (2-6-1) is arranged in a measurement executing mechanism (2-6), a measuring rod of the dial indicator (2-6-1) penetrates into a workpiece accommodating cavity (2-1-1) of a base (2-1), and the tail end of the dial indicator axially abuts against a measured rotary actuator (1).
  2. 2. The axial gap measuring apparatus for a flexible joint shaft as claimed in claim 1, wherein the diameter dimension of the dowel hole (2-2-1) in the side pressure plate (2-2) is larger than the outer diameter dimension of the workpiece dowel pin assembly.
  3. 3. The axial clearance measuring device for the flexible connecting shaft according to claim 2, wherein the workpiece locating pin assembly comprises a locating sleeve (2-4) and a locating pin (2-3), the locating sleeve (2-4) is arranged in a locating pin hole (2-2-1) of the side pressing plate (2-2) and is fixedly connected with the locating pin hole (2-2-1) through filling an adhesive (3), and the locating pin (2-3) penetrates through the locating sleeve (2-4) and locating holes in lugs (1-1) of the rotary actuator (1) and is connected with corresponding parts on an aircraft at the tail end.
  4. 4. The axial clearance measuring device for the flexible connecting shaft according to claim 3 is characterized in that the positioning pin (2-3) is provided with an operating handle (2-3-1), a positioning part (2-3-2) and a locking part (2-3-3), the operating handle (2-3-1) is of a cylindrical structure, anti-slip textures are arranged on the outer wall of the operating handle, the positioning part (2-3-2) is located between the operating handle (2-3-1) and the locking part (2-3-3) and is of a cylinder matched with an inner hole of the positioning sleeve (2-4), and the locking part (2-3-3) is of a cylindrical pin structure and is located at the tail end of the positioning pin (2-3).
  5. 5. The device for measuring the axial play of a flexible connection shaft as claimed in claim 4, wherein the locking portion of the locating pin (2-3) is matched with a fitting hole of a lug (1-1) of a rotary actuator (1) on an aircraft body.
  6. 6. An axial gap measuring device for a flexible connection shaft as claimed in claim 3 or 4 or 5, characterized in that a spiral groove (2-4-1) is provided on the outer side wall of the positioning sleeve (2-4).
  7. 7. The axial gap measuring apparatus for a flexible connecting shaft according to claim 6, wherein the support legs (2-5) are provided at four corners of the base (2-1), and the support legs (2-5) are hexagon head bolts mounted on the base (2-1).
  8. 8. The axial gap measuring device for flexible connecting shafts according to claim 6, wherein the measuring actuator (2-6) is further provided with a reference plate (2-6-5), a clamping seat (2-6-2), a spring housing (2-6-4) and a locking cap (2-6-3), the reference plate (2-6-5) is fixedly mounted on the left side or right side wall of the base (2-1), the clamping seat (2-6-2) is mounted in the middle of the reference plate (2-6-5), the clamping seat (2-6-2) is provided with a conical inner hole, threads matched with the locking cap (2-6-3) are arranged on the outer wall of the clamping seat (2-6-2), the clamping seat (2-6-2) is assembled with the locking cap (2-6-3) through a threaded connection structure, the spring housing (2-6-4) is a conical sleeve with an axial groove (2-6-4 a) on the side wall, is mounted in the conical inner hole of the clamping seat (2-6-2), the spring housing (2-6-2) is mounted in a cylindrical inner hole of the clamping seat (2-6-2) and is mounted in a cylindrical inner hole of the clamping seat (2-6-4), the dial indicator (2-6-1) is clamped and fixed by applying radial pressure to the spring sleeve (2-6-4) through the cooperation of the locking cap (2-6-3) and the clamping seat (2-6-2).
  9. 9. The axial clearance measuring device for a flexible connecting shaft according to claim 8, wherein the number of the axial grooves (2-6-4 a) on the outer wall of the spring sleeve (2-6-4) is four, and the axial grooves are uniformly distributed along the circumferential direction, and one of the groups is a radial through notch (2-6-4 b).
  10. 10. The axial gap measuring device for flexible connecting shafts according to claim 9, wherein the spring housing (2-6-4) is made of H62 copper zinc alloy.

Description

Axial clearance measuring device for rotary actuator of aircraft Technical Field The invention relates to a measuring device, in particular to a special measuring device for measuring the axial clearance of a rotating actuator of a front edge flap driving system of an aircraft in the overhauling process. Background In the process of taking off and landing of an aircraft, the wing is subjected to huge air external force, as shown in figures 1 and 2, in order to reduce the internal stress generated by the wing under the action of the air external force, the wing is stressed and deformed within a safety value range, and an aircraft manufacturing plant designs a rotary actuator 1 in a leading edge flap driving system into a joint-shaped flexible connection structure, so that the rotary actuator 1 can generate flexible deformation in an I-IV curve shape as shown in figure 1 under the condition of the wing stress, and energy generated by the action of the air external force is released. As shown in fig. 1 and 2, nine sets of lugs 1-1 connected with other mechanisms are arranged on two sides of a rotary actuator 1 in the front edge flap driving system of an aircraft, each set of lugs consists of two parts which are oppositely arranged, wherein the two parts which are oppositely arranged in the four upper sets of lugs form a certain inclination angle (8 degrees 36'±15') with the horizontal plane, the two parts which are oppositely arranged in the five lower sets of lugs are parallel to the horizontal plane, after the aircraft passes a certain flight time, the locating holes and internal parts on the lugs 1-1 of the rotary actuator 1 are worn to different degrees, so that certain index parameters of the rotary actuator 1 exceed a set range, therefore, when the aircraft is overhauled, parts with serious wear and due service life are required to be replaced, after the aircraft is reassembled, the axial movement clearance of the rotary actuator is also required to be measured, so as to judge whether the technical requirement of 0.10-0.15 mm of the axial movement clearance is met. According to the operation standard of aircraft overhaul, the measurement of the axial movement clearance of the rotary actuator is carried out under the theoretical state (without flexible deformation) when the rotary actuator is simulated to leave the factory, namely, the relative dimensions and tolerances such as the hole pitch dimension (45+/-0.1 mm), the one-side lug angle (8 degrees 36 '+/-15'), the flatness (less than or equal to 0.05 mm), the coaxiality (less than 0.1 mm) and the like of two adjacent sets of lugs of the rotary actuator are required to be ensured to be consistent with those when leaving the factory. Therefore, a special measuring device capable of realizing axial clearance measurement of the rotary actuator is required to be designed so as to meet the maintenance operation specification of the aircraft and ensure the assembly quality of the aircraft after maintenance. Disclosure of Invention The invention provides an axial clearance measuring device of an aircraft rotary actuator, which aims to meet the requirement of an aircraft maintenance operation standard by innovative design of a workpiece clamping and positioning mechanism and a measuring and executing mechanism so as to achieve the aim of ensuring the assembly quality of an aircraft after maintenance. In order to achieve the above purpose, the invention adopts the following technical scheme: The axial clearance measuring device for the rotary actuator of the aircraft comprises a workpiece clamping and positioning mechanism and a measuring executing mechanism, wherein the workpiece clamping and positioning mechanism is provided with a base, a side pressing plate and a workpiece positioning pin assembly, the base is of a box frame structure, a workpiece accommodating cavity is formed in the middle of the base, the side pressing plate comprises two parts which are arranged in a front-back symmetrical mode and are respectively arranged on front and back vertical faces of the base, positioning pin holes corresponding to positioning holes in lugs of the rotary actuator are formed in each part, an attaching face matched with the angles of the lugs of the rotary actuator is formed in the inner side of each part, the number of the workpiece positioning pin assemblies is consistent with that of the lugs of the rotary actuator, the lugs of the rotary actuator are fixedly connected with the side pressing plate through the workpiece positioning pin assembly, the measuring executing mechanism is arranged on one side of the base, a dial indicator is arranged in the measuring executing mechanism, a measuring rod of the dial indicator penetrates into the workpiece accommodating cavity of the base, and the tail end of the dial indicator is in axial interference with the measured rotary actuator. According to the axial clearance measuring device for the aircraft rotary actuator, t