Forced rock test device for high-speed wind tunnel

Abstract

The invention discloses a forced rock test device for a high-speed wind tunnel. The test device comprises three step cylindrical sections, namely a motor section, a speed reducer section and a supporting rod section which are connected in sequence, a servo motor of the motor section, a speed reducer of the speed reducer section and a rocking shaft of the supporting rod section are positioned on the same central axis; an output shaft of the servo motor is connected with the input end of the speed reducer through a motor coupling, and the output end of the speed reducer is connected with the rocking shaft through a rocking shaft coupling; the servo motor is sleeved with a motor support, the speed reducer is sleeved with a speed reducer support, the rocking shaft is sleeved with a supportingrod, and the motor support, the speed reducer support and the supporting rod are in positioning connection through screws and pins I; and the front end of the rocking shaft is provided with a needle bearing, and the rear end is provided with a ball bearing. According to the test device, the servo motor is used for controlling the rocking shaft to drive the test model to roll through the speed reducer amplifying torque, the dynamic rocking characteristics of the aircraft are researched, and then the appearance optimization design and flight control robustness design of the aircraft are guided.

Description

technical field [0001] The invention belongs to the technical field of high-speed wind tunnel tests, and in particular relates to a forced rock test device for high-speed wind tunnels. Background technique [0002] Various unsteady and asymmetric phenomena of the air flow around the aircraft during the flight will have a significant impact on the roll characteristics of the aircraft. Even an aircraft with a statically stable roll may have dynamic instability. Serious situations may cause Rolling and diverging directly threatens flight safety. The current conventional dynamometric wind tunnel test can only obtain the rolling static derivative or the aerodynamic stiffness derivative, and the rolling rotational derivative test can further obtain the rolling rotational derivative or the aerodynamic damping derivative. The dynamic aerodynamic characteristics of rock and roll during limit cycle vibration and other movements cannot reflect the dynamic aerodynamic phenomena such as...

AI Technical Summary

Problems solved by technology

[0002] Various unsteady and asymmetric phenomena of the air flow around the aircraft during the flight will have a significant impact on the roll characteristics of the aircraft. Even an aircraft with a statically stable roll may have dynamic instability. Serious situations may cause Rolling and spreading, a direct threat to flight safety

The current conventional dynamometric wind tunnel test can only obtain the rolling static derivative or the aerodynamic stiffness derivative, and the rolling rotational derivative test can further obtain the rolling rotational derivative or the aerodynamic damping derivative. The dynamic aerodynamic characteristics of rock and roll during limit cycle vibration and other movements cannot reflect the dynamic aerodynamic phenomena such as dynamic hysteresis brought about by large-angle rapid rock and roll motion during the actual flight of the aircraft. The roll stability analysis and dynamic aerodynamic characteristics of the aerodynamic layout of the aircraft Assessment work has technical deficiencies

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