Method for designing control distribution and optimal transition route of combined helicopter

Abstract

The invention provides a method for designing a control distribution and optimal transition route of a combined helicopter. The method comprises the following steps: establishing an HCH flight mechanical model which specifically comprises a rotor wing model, a wing model, a nacelle model and a fuselage model; and carrying out optimization balancing calculation to obtain the balancing amount in any state. A combined type high-speed helicopter control strategy at each speed is provided, control distribution coefficients between different control mechanisms and a pitch attitude angle transition route in the transition process are obtained according to control strategy design optimization, so that each control variable is in smooth transition, and the attitude quantity is maintained within a reasonable range. Based on a flight mechanical model, the calculation method can be fed back to an overall design link, and reference is provided for overall parameter optimization of an aircraft. Compared with the power and the manipulated variable which are obtained by balancing according to the transition route and the distribution coefficient and balancing according to the fixed pitch angle, the method has the advantage of small power, the manipulated variable can be smoothly and continuously transited, and the method is more in line with the manipulation habit of a driver.

Description

technical field [0001] The invention relates to the field of flight mechanics and control of a compound rotorcraft, in particular to a compound helicopter manipulation distribution and optimal transition route design method. Background technique [0002] The compound high-speed helicopter propelled by twin propellers is a design concept used to realize the high-speed flight of the helicopter. The configuration is as follows figure 1 As shown, on the basis of a conventional helicopter, the aircraft has two wings on both sides of the fuselage, cancels the tail rotor and installs an empennage, and installs a pair of propulsion propellers on both sides of the wing. The addition of a pair of propulsion propellers, ailerons, elevators and rudders means that four control variables are added, and the resulting control redundancy problem poses a difficult problem for the compound helicopter control system design and trim analysis [0003] In order to delay the airflow compressibilit...

AI Technical Summary

Problems solved by technology

Compared with conventional helicopters, HCH adds a pair of propulsion propellers, a pair of wings, and a pair of empennages. Since they are all under the rotor wake, the force change during the flight of HCH cannot be accurately calculated by simply using the helicopter model.

It is necessary to establish the flight mechanics model of HCH, taking into account the disturbance of various parts; the increase of new control variables, 6 dynamic relations can not solve the 7 unknown quantities of HCH trim solution, so the pitch angle is set to a fixed value for trim calculation , resulting in the problem of pitch angle transition route design at different speeds

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