Pneumatic performance comprehensive testing platform of non-tail-rotor reaction torque system of a helicopter

Abstract

The invention discloses a pneumatic performance comprehensive testing platform of a non-tail-rotor reaction torque system of a helicopter. The pneumatic performance comprehensive testing platform comprises a power input mechanism, an air compressor assembly, a force balance, a circular rector control tail beam assembly, a pressure control assembly, a combined stabilizing plane and a rotary type end piece assembly which are sequentially connected in serial mode. The air compressor assembly comprises an air inlet channel, an air inlet casing, a pressure expansion casing and an air compressor disc assembly. The circular rector control tail beam assembly comprises a tail beam carrying pipe section and a slit control assembly. The rotary type end piece assembly comprises a gear driving mechanism, a gear bearing mechanism and a tail section main body. The combined type stabilizing plane comprises a hoop ring and a stabilizing plane assembling unit. By means of the pneumatic performance comprehensive testing platform, research on the relationship between geometrical parameters and pneumatic parameters of a tail beam and a lift generated by the circular rector control tail beam and the relationship between the geometrical parameters and pneumatic parameters of the tail beam and the power required by the non-tail-rotor reaction torque system is performed. By combined with a reaction torque testing table of the helicopter, the pneumatic performance comprehensive testing platform can be used in researches on matching and optimization design of the geological parameters and pneumatic parameters of the circular rector control tail beam and a main rotor of the helicopter and the like.

Description

technical field [0001] The invention relates to a test device for researching the aerodynamic characteristics of a helicopter tailless anti-torque system, including the working principle and mechanical structure of a test platform, and belongs to the test platform used in the aviation field. Background technique [0002] The tailless rotor anti-torque system is a new type of anti-torque system applied to single main rotor helicopters, which is used to balance the anti-torque generated by the main rotor and perform heading control. Compared with the conventional tail rotor of the traditional anti-torque system, the structure of the non-tail rotor anti-torque system is simpler, so it has higher reliability and maintainability. The tailless anti-torque system has no high-speed rotating parts exposed to the air, so the ground personnel are safer when the helicopter takes off and lands, and the helicopter itself is safer when flying at low altitudes, and at the same time, it prod...

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Problems solved by technology

[0004] At present, no similar test platform has been found at home and abroad

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