Propeller pitch independent control operation system for three blade propeller coaxial unmanned helicopter

Abstract

The invention discloses a propeller pitch independent control operation system for a three blade propeller coaxial unmanned helicopter. The propeller pitch independent control operation system for thethree blade propeller coaxial unmanned helicopter comprises an upper rotor operation unit and a lower rotor operation unit; an upper rotor servo steering engine transmits pitch variable operation toan upper rotor inclinator; the outer ring of the upper rotor inclinator is connected with a helicopter body; the inner ring of the upper rotor inclinator and the outer ring of the upper rotor inclinator are kept to rotate relative to each other; the inner ring of the upper rotor inclinator rotates with a rotating shaft of an upper rotor; the upper rotor inclinator is connected with an upper rotortransitional ring through a triangular beam mechanism and transmits pitch variable operation to the upper rotor transitional ring; the upper rotor transitional ring rotates with the rotating shaft ofthe upper rotor and transmits the pitch variable operation to the upper rotor; a lower rotor servo steering engine is connected with a lower rotor inclinator; the lower rotor inclinator is connected with a lower rotor; the inner ring of the lower rotor inclinator rotates together with a rotating shaft of the lower rotor; and the outer ring of the lower rotor inclinator does not rotate with the lower rotor.

Description

technical field [0001] The invention relates to the technical field of coaxial unmanned helicopters, in particular to a three-bladed propeller coaxial unmanned helicopter pitch control system. Background technique [0002] At present, the common unmanned helicopters mainly have two forms: single rotor with tail rotor and coaxial dual rotor. Due to the large load capacity and good stability, the coaxial dual rotor has gradually attracted people's attention. As early as the middle of the 20th century, many countries in the world conducted research on the aerodynamic characteristics, spatial layout and manipulation forms of coaxial dual rotors, especially the former Soviet Union made outstanding contributions in the field of coaxial dual rotor helicopters. Coaxial twin-rotor helicopters can be roughly divided into a "seesaw" type with two upper and lower blades and a structure with multiple upper and lower blades according to the number of blades. The coaxial dual-rotor with t...

AI Technical Summary

Problems solved by technology

The disadvantages of this traditional control form are: the connection between the upper rotor tilter and the lower rotor tilter is connected by a complex mechanical structure, which reduces the reliability; at the same time, these mechanical structures are completely exposed to the flow field of the rotor, and the non-linear The structural parts greatly increase the waste resistance of the helicopter; for the semi-differential control system, there is a heading-collective coupling effect, which increases the complexity of the control

Through the cooperation of the upper rotor and the lower rotor control, the four controls of longitudinal, lateral, collective pitch and yaw of the coaxial unmanned helicopter are realized, but this control form is currently only applied to the "seesaw" coaxial dual rotor On the unmanned helicopter, and each rotor of the "seesaw" has only two blades, which cannot meet the needs of unmanned helicopters with large loads

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