Reaction Drive Helicopter Non-Rotating Fuselage Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Rotorcraft face inefficiencies due to mechanical complexity, frictional losses, and aerodynamic drag, limiting flight endurance and requiring frequent recharging and reconfiguration.
Innovation Solution
An electrically powered rotorcraft system with a non-rotating fuselage and rotor attachment ring assembly, featuring spinning wings for lift generation, onboard thrust generators for precise control, and modular rotors for quick battery exchange and payload adjustment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If conventional rotorcraft with mechanical drivetrains are used, then lift and propulsion functions are achieved, but mechanical complexity and frictional losses severely limit flight endurance
Solution Approach 1:
The rotorcraft system is segmented into independent rotor modules, each with its own thrust generator and control system. This modular architecture eliminates the need for a complex centralized mechanical drivetrain, reducing frictional losses and enabling extended flight endurance through efficient power distribution to individual rotors.
Solution Approach 2:
The patent replaces the conventional mechanical drivetrain with an electrically-powered system where independent electric motors (thrust generators) directly drive each rotor. This substitution eliminates mechanical friction, reduces maintenance requirements, and significantly extends flight endurance by improving overall system efficiency.
2Measurement precision
If high propeller speeds are used in multi-rotor drones, then control precision and payload carrying capability are improved, but aerodynamic drag consumes energy quickly
Solution Approach 1:
The system dynamically adjusts rotor speeds and thrust generation based on real-time flight conditions and control requirements. By using independently controlled thrust generators on each rotor, the system can precisely modulate power output to match actual needs, maintaining control precision while minimizing energy consumption through adaptive speed control rather than continuously operating at high speeds.
3Speed
If conventional rotorcraft control systems are used, then basic flight control is achieved, but response to control inputs is slow and non-intuitive due to high rotational inertia
Solution Approach 1:
The control system is segmented into independent control channels for each rotor, allowing individual adjustment of rotor speeds and thrust. This segmentation enables rapid, localized control responses without the need to overcome the combined rotational inertia of a large centralized rotor system, resulting in faster and more intuitive control response.
Solution Approach 2:
The patent replaces conventional mechanical flight control systems with an electrically-controlled system where independent electric motors respond to control inputs with minimal mechanical lag. This substitution eliminates the delays associated with mechanical linkages and high rotational inertia, enabling rapid and precise control response.
4Measurement precision
If battery-powered multi-rotor drones are used, then controlled payload positioning is achieved, but frequent battery recharging and reconfiguration are required
Solution Approach 1:
The rotorcraft is designed with universal, modular battery compartments and standardized electrical connections that allow rapid battery exchange without requiring system reconfiguration. The independent rotor modules can operate with different battery configurations, enabling quick swaps and extended operational availability while maintaining precise payload positioning capability.
Solution Approach 2:
Multiple batteries can be pre-charged and prepared in advance, allowing for rapid exchange during flight operations. The system is designed to accommodate preliminary preparation of power sources, minimizing service downtime by enabling quick battery swaps without requiring complex reconfiguration procedures.
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
The system achieves improved flight endurance, quick reactivation, and precise control, enabling long-duration flights and efficient energy management without climate-changing emissions.
Implementation Method 1
spinning wings to generate lift
Implementation Method 2
onboard thrust generators to generate thrust
Data Source
AI summary
Disclosed is an electrically powered, reaction-drive type rotorcraft. Thrust generators on the outer portion of each rotor blade cause the rotors to spin and generate lift, and additionally, may be controlled to produce variable amounts of thrust as the rotor blades rotate through different sectors around a generally non-rotating fuselage such that net lateral forces are produced to control the position and velocity of the vehicle. The rotorcraft may also employ aerodynamic surfaces on each rotor blade whose parts or entire structure can be moved to produce net lateral and vertical forces for control of position and velocity of the vehicle. The rotorcraft, which may be operationally carbon-neutral, stores its electrical energy in batteries and other optional energy storage methods, and may harvest solar energy using arrays of photovoltaic cells disposed on its upper surfaces. Vehicle sizes may range from small Uncrewed Air vehicle Systems to large crewed aircraft.