Compound Helicopter Hover Control for Heading Changes
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Solution Overview
Problem
Compound helicopters struggle to maintain controlled hovering during heading changes, limiting the pilot's ability to maintain visual contact with a reference point, such as a landing zone, due to the lack of effective control over pitch angles and propulsion forces.
Innovation Solution
A method utilizing an autopilot system that controls both the pitch of rotary wings and propellers to balance forces, allowing for controlled hovering with adjustable pitch angles and automatic adjustments to setpoint positions, enabling the aircraft to maintain a stable position and trajectory during heading changes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the aircraft uses conventional hovering control without autopilot intervention, then the pilot has direct control over the aircraft, but the aircraft cannot maintain a stable position and controlled pitch angle during heading changes
Solution Approach 1:
The autopilot system automatically controls the pitch angles of rotary wing blades and propeller blades to maintain hovering stability and controlled pitch angle during heading changes, enabling the aircraft to self-regulate without continuous manual intervention while preserving pilot oversight
Solution Approach 2:
The system continuously monitors the aircraft's position, pitch angle, and heading, and automatically adjusts blade pitch angles based on feedback from sensors to maintain the desired hovering state and controlled pitch angle during maneuvering
2Ease of operation
If the aircraft maintains a fixed pitch angle during hovering, then the control system is simpler, but the pilot cannot optimize the view of a reference point during heading changes
Solution Approach 1:
The system dynamically adjusts the pitch angle of the aircraft during hovering by controlling the pitch angles of rotary wing blades and propeller blades, allowing the pilot to optimize the view of a reference point while maintaining hovering stability through automated control
Solution Approach 2:
The autopilot system performs multiple functions simultaneously: maintaining hovering stability, controlling pitch angle, enabling heading changes, and optimizing pilot view of a reference point, thereby managing complexity through integrated multi-functional control
3Reliability
If the aircraft uses manual control during hovering, then the system is simpler, but the aircraft cannot automatically balance forces and maintain controlled position during heading changes
Solution Approach 1:
The autopilot system automatically balances forces during hovering by controlling the pitch angles of rotary wing blades and propeller blades, enabling the aircraft to self-regulate its aerodynamic forces without continuous manual intervention
Solution Approach 2:
The system replaces manual mechanical control with an automated control system that uses sensors and actuators to balance forces and maintain controlled position during hovering and heading changes
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This method enhances the pilot's view of a reference point during hovering by allowing the aircraft to maintain a controlled pitch angle and position, enabling precise navigation and improved safety during landing operations.
Implementation Method 1
the airframe of a helicopter is made stationary in flight by balancing the force of gravity on the helicopter, the force generated by the wind, the aerodynamic force generated by the rotary wing
Implementation Method 2
at least one propeller that are set in permanent motion in flight by a power plant
Data Source
AI summary
A method for hovering an aircraft having at least one wing and at least one rotary wing and at least one propeller, the aircraft comprising an autopilot system. The method comprises keeping the aircraft hovering, with the autopilot system, in the setpoint position, keeping the aircraft hovering in this way comprising controlling, with the autopilot system, a pitch of blades of the at least one propeller irrespective of the setpoint pitch angle and controlling, with the autopilot system, a pitch of blades of the at least one rotary wing as a function at least of the setpoint pitch angle.