System and method for measuring unfolding angle of outer rudder of aircraft in high-speed impact state in real time
A high-speed impact and real-time measurement technology, which is applied in the field of ground wind tunnel tests, can solve the problems of no docking port and the inability to install angle sensors, etc., and achieve the effect of avoiding measurement errors
Pending Publication Date: 2022-01-14
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology
[0007] In order to solve the technical problem that the outer rudder connecting shaft of the existing air rudder has no docking port, the angle sensor cannot be installed, and the outer rudder angle measurement is realized during the air rudder deployment process, the present invention provides a real-time measurement system for the outer rudder deployment angle of the aircraft in the high-speed impact state and method
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[0040] The content of the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0041] like figure 1 and figure 2 As shown, a real-time measurement system for the deployment angle of the outer rudder of the aircraft in a high-speed impact state; wherein, the outer wall of the aircraft 1 is provided with an air rudder, and the air rudder includes an inner rudder 111 fixed on the outer wall of the aircraft 1 and connected by an outer rudder. The rotating shaft 112 is connected to the outer rudder 113 on the outside of the inner rudder 111; the measurement system realizes the real-time measurement of the deployment angle of the outer rudder of the aircraft. The sensor 6, the sensor fixing bracket 7 and two fixing screws 8 are composed.
[0042] The positioning plate 2 is installed on the side wall of the aircraft 1 as a positioning reference;
[0043] The transmission shaft 3 is installed on the p...
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The invention provides a system and method for measuring unfolding angle of an outer rudder of an aircraft in a high-speed impact state in real time, and solves the problems that an outer rudder connecting rotating shaft of an existing air rudder is not provided with a butt joint port, an angle sensor cannot be installed, and outer rudder angle measurement in the unfolding process of the air rudder cannot be achieved. The system comprises a positioning plate, a transmission shaft, a transmission shaft supporting frame, an L-shaped connecting rod, an angle sensor, a sensor fixing support and two fixing screws. The positioning plate is mounted on the side wall of the aircraft; the transmission shaft is installed on the positioning plate through the transmission shaft supporting frame and is coaxial with the outer rudder connecting rotating shaft; one end of the L-shaped connecting rod is vertically and fixedly connected with the transmission shaft, and the other end is provided with a U-shaped notch; the two fixing screws are located on the two sides of the U-shaped notch respectively and make contact with the two side faces of the outer rudder respectively in a compression joint mode; and the angle sensor is installed on the positioning plate through the sensor fixing support, and an input shaft of the angle sensor is coaxially connected with the transmission shaft.
Description
technical field [0001] The invention belongs to the field of ground wind tunnel tests, and in particular relates to a real-time measurement system and method for an outer rudder deployment angle of an aircraft in a high-speed impact state. Background technique [0002] The air rudder is the key equipment for adjusting the flight attitude and trajectory of the aircraft during flight, and maintaining the stable flight of the aircraft. During the flight of the aircraft, when the air rudder is deployed, due to the poor synchronization of the air rudder deployment process or the influence of aerodynamics, it will cause the aircraft itself to Extra torque is generated, causing the aircraft to become unstable and fail to fly. [0003] The ground wind tunnel test is an important measure for the aircraft to obtain various parameters of the flight state. The aircraft simulates the actual flight state in the wind tunnel test, including the aerodynamic parameters of its flight process....
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IPC IPC(8): G01M9/06G01B21/22B64F5/60
CPCG01M9/06G01M9/062G01B21/22B64F5/60
Inventor 李国涛沈继彬关春王栋余爱英郭宁敏雷倩楠徐玲王诚慧胡强郝华王斌王西昊刘新原
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST