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CN-224217093-U - Avionic bus test platform

CN224217093UCN 224217093 UCN224217093 UCN 224217093UCN-224217093-U

Abstract

The utility model discloses an avionic bus test platform, which relates to the technical field of bus test and comprises a processor and a coupler, wherein a first threaded hole is formed in one side of the processor and is provided with a mounting frame through a bolt, connecting frames are fixedly arranged at two ends of the bottom of the coupler, connecting holes are formed in the connecting frames, an L-shaped fixing frame is fixedly arranged on the mounting frame, a push plate is arranged between the fixing frame and the mounting frame, positioning rods are fixedly arranged at the tops of two ends of the push plate and penetrate through the mounting frame and are matched with the connecting holes, guide rods are fixedly arranged at the bottoms of the two ends of the push plate and penetrate through the fixing frame, springs are arranged on the periphery of the guide rods, the two ends of each spring are respectively connected with the push plate and the fixing frame, and pull rods fixedly arranged at the bottom of the push plate penetrate through the fixing frames and are connected with pull handles. According to the utility model, the push plate is moved by pulling the pull handle, and the positioning rod can be pulled out or inserted from the connecting hole, so that the mounting and dismounting time is greatly shortened, and the efficiency of test work is improved.

Inventors

  • SHI JINMING
  • LU HAIHUA
  • SUN LINGYAN

Assignees

  • 上海欧比特航天科技有限公司

Dates

Publication Date
20260508
Application Date
20250604

Claims (6)

  1. 1. The avionics bus test platform comprises a processor (1) and a coupler (2) and is characterized in that a first threaded hole (14) is formed in one side of the processor (1), a mounting frame (3) is mounted on the first threaded hole (14) through bolts, connecting frames (21) are fixedly arranged at two ends of the bottom of the coupler (2), connecting holes (22) are formed in the connecting frames (21), L-shaped fixing frames (31) are fixedly mounted on the mounting frame (3), a push plate (32) is arranged between the fixing frames (31) and the mounting frame (3), positioning rods (323) are fixedly mounted at the tops of two ends of the push plate (32), the positioning rods (323) penetrate through the mounting frame (3) and are matched with the connecting holes (22), guide rods (324) are fixedly mounted at the bottoms of the two ends of the push plate (32), springs (33) are arranged on the periphery of the guide rods (324) in a penetrating mode, the two ends of each spring (33) are respectively connected with the push plate (32) and the fixing frames (31), and the bottoms of the push plate (321) are fixedly connected with the pull rods (321) through the fixing frames (32).
  2. 2. The avionics bus testing platform according to claim 1, wherein a second threaded hole (23) is formed in one side of the coupler (2) at equal intervals, a first cable (24) is connected to the second threaded hole (23), and a connecting seat (25) is arranged at one end of the first cable (24).
  3. 3. An avionics bus testing platform according to claim 2, wherein a first sleeve (26) is installed in the second threaded hole (23), a first threaded pipe (262) is arranged at one end of the first sleeve (26), the first sleeve (26) is in threaded connection with the second threaded hole (23) through the first threaded pipe (262), and a first rotating frame (261) is fixedly arranged on the first sleeve (26).
  4. 4. The avionics bus testing platform according to claim 3, wherein a third threaded hole (11) is formed in one side of the processor (1) at equal intervals, a second cable (12) is connected to the third threaded hole (11), a connector (13) is arranged at one end of the second cable (12), and the connector (13) is correspondingly matched with the connecting seat (25).
  5. 5. An avionics bus testing platform according to claim 4, wherein a second sleeve (15) is installed in the third threaded hole (11), a second threaded pipe (152) is arranged at one end of the second sleeve (15), the second sleeve (15) is in threaded connection with the third threaded hole (11) through the second threaded pipe (152), and a second rotating frame (151) is arranged on the second sleeve (15).
  6. 6. An avionics bus testing platform according to claim 5, characterized in that the outer diameter of the second sleeve (15) is adapted to the inner diameter of the first sleeve (26).

Description

Avionic bus test platform Technical Field The utility model relates to the technical field of bus testing, in particular to an avionic bus testing platform. Background The avionic bus is a generic term of communication lines and related protocols for realizing data transmission and information interaction among subsystems and devices in an avionic system, wherein the 1553B bus is a serial data bus widely applied to the field of aviation, and belongs to the field of avionic buses. The system is formulated by the national defense department, has the characteristics of dual redundancy, time division multiplexing and the like, can ensure the reliability of data transmission, and is commonly used for connecting key systems on an aircraft, such as an engine control system, a flight management system and the like. The chinese patent application number 202420973667.9 provides a 1553B bus's test equipment, when using 1553B bus's test equipment, utilize socket and connector to be connected through the first cable that sets up and second cable, not only can make inside connection more convenient, also can not make inside connecting wire connect the back, the illusion is complicated, through the cooperation between first connecting pipe and the second connecting pipe that sets up simultaneously, can be convenient protect the cable after connecting, prevent to lead to contacting failure or droing because of touching. However, the device is found in the use process that the threaded connection needs to be screwed in circle by circle, so that a great deal of time can be consumed under the condition that the limiting rod needs to be frequently installed and detached, and the efficiency of test work is reduced. Disclosure of utility model Aiming at the defects of the prior art, the utility model provides an avionic bus test platform, which solves the problems that the screw connection consumes a great deal of time and reduces the efficiency of test work under the condition that a limiting rod is required to be frequently installed and disassembled in the background art. The avionic bus testing platform comprises a processor and a coupler, wherein a first threaded hole is formed in one side of the processor, a mounting frame is mounted on the first threaded hole through bolts, connecting frames are fixedly arranged at two ends of the bottom of the coupler, connecting holes are formed in the connecting frames, L-shaped fixing frames are fixedly mounted on the mounting frame, a push plate is arranged between the fixing frames and the mounting frame, positioning rods are fixedly mounted at the tops of the two ends of the push plate and penetrate through the mounting frame and are matched with the connecting holes, guide rods are fixedly mounted at the bottoms of the two ends of the push plate, the guide rods penetrate through the fixing frames, springs are arranged on the periphery of the guide rods, the two ends of each spring are respectively connected with the push plate and the fixing frames, pull rods are fixedly arranged at the bottoms of the push plate, and the pull rods penetrate through the fixing frames and are connected with pull handles. Preferably, the second threaded holes are formed in one side of the coupler at equal intervals, the first cables are connected to the second threaded holes, and the connecting base is arranged at one end of each first cable. Preferably, a first sleeve is installed in the second threaded hole, a first threaded pipe is arranged at one end of the first sleeve, the first sleeve is in threaded connection with the second threaded hole through the first threaded pipe, and a first rotating frame is fixedly arranged on the first sleeve. Preferably, third screw holes are formed in one side of the processor at equal intervals, a second cable is connected to the third screw holes, a connector is arranged at one end of the second cable, and the connector is correspondingly matched with the connecting seat. Preferably, a second sleeve is installed in the third threaded hole, a second threaded pipe is arranged at one end of the second sleeve, the second sleeve is in threaded connection with the third threaded hole through the second threaded pipe, and a second rotating frame is arranged on the second sleeve. Preferably, the outer diameter of the second sleeve is adapted to the inner diameter of the first sleeve. The utility model provides an avionics bus test platform. The beneficial effects are as follows: (1) When the coupler is required to be connected or detached, only the pull handle is required to be pulled, the push plate moves downwards, the springs are compressed, the positioning rods are separated from the fixed positions, the coupler is convenient to detach, when the coupler is required to be installed, the connecting frame of the coupler is aligned with the mounting frame of the processor, the pull handle is loosened, the springs are restored to deform, the push plate is pushed to move