Honda motor co., ltd. (20240109653). CONTROL DEVICE FOR AIRCRAFT simplified abstract
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 20240109653 titled 'CONTROL DEVICE FOR AIRCRAFT
Simplified Explanation
The patent application describes a control device for an aircraft that manages the pitch of each blade in the front and rear wings, as well as the rotation angle of each VTOL rotor when it is not in motion, to regulate the force generated by each rotor and apply force to the fuselage.
- The control device adjusts the pitch of the blades in the front and rear wings to control lift generation.
- It also manages the rotation angle of each VTOL rotor when it is not spinning to control the force generated by each rotor.
- The goal is to apply force to the fuselage of the aircraft.
Potential Applications
This technology could be applied in the development of advanced aircraft with improved control systems for lift generation and force application.
Problems Solved
This innovation solves the challenge of effectively controlling the lift and force generated by the front and rear wings, as well as the VTOL rotors, in an aircraft.
Benefits
The benefits of this technology include enhanced maneuverability, stability, and control of the aircraft during flight operations.
Potential Commercial Applications
Commercial applications of this technology could include the production of next-generation aircraft with superior control mechanisms for lift and force management.
Possible Prior Art
Prior art in this field may include patents or research related to aircraft control systems and mechanisms for managing lift and force generation.
Unanswered Questions
How does this technology impact fuel efficiency in aircraft?
This article does not address the potential impact of this technology on fuel consumption in aircraft operations.
What are the safety implications of implementing this control device in aircraft?
The safety considerations and implications of integrating this control device into aircraft systems are not discussed in this article.
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.
