18473822. CONTROL DEVICE FOR AIRCRAFT simplified abstract (HONDA MOTOR CO., LTD.)
Contents
- 1 CONTROL DEVICE FOR AIRCRAFT
CONTROL DEVICE FOR AIRCRAFT
Organization Name
Inventor(s)
Masahiko Asanuma of Wako-shi (JP)
Susumu Mashio of Wako-shi (JP)
CONTROL DEVICE FOR AIRCRAFT - A simplified explanation of the abstract
This abstract first appeared for US patent application 18473822 titled 'CONTROL DEVICE FOR AIRCRAFT
Simplified Explanation
The patent application describes a control device for an aircraft that manages the pitch of each blade and the rotation angle of each VTOL rotor to control the lift generated by the front and rear wings.
- The control device adjusts the pitch of each blade and the rotation angle of each VTOL rotor to control the lift generated by the front and rear wings.
- The device applies force to the fuselage by controlling the force generated in each VTOL rotor when the rotor rotation is stopped.
Potential Applications
This technology could be applied in the development of advanced aircraft systems, particularly in vertical take-off and landing (VTOL) aircraft.
Problems Solved
This technology solves the challenge of efficiently controlling lift and force distribution in aircraft with multiple wings and rotors.
Benefits
The technology offers precise control over lift and force distribution, enhancing the overall performance and maneuverability of the aircraft.
Potential Commercial Applications
Potential commercial applications include military drones, urban air mobility vehicles, and other VTOL aircraft for various industries.
Possible Prior Art
One possible prior art could be the use of individual blade pitch control systems in helicopters to adjust lift and thrust.
Unanswered Questions
How does this technology improve aircraft stability during flight?
This article does not delve into the specific mechanisms through which the control device enhances aircraft stability.
What are the potential energy savings associated with this technology?
The article does not address the potential energy efficiency benefits that could result from the precise control of lift and force distribution.
Original Abstract Submitted
In a state where lift is generated in a front wing and a rear wing, a control device for an aircraft controls the pitch of each blade and the stopped state rotation angle of each VTOL rotor to control the force generated in each VTOL rotor in a state where rotation of the VTOL rotor is stopped, thereby applying a force to a fuselage.
