18045792. AIRCRAFT, A CONTROL SYSTEM FOR THE AIRCRAFT AND A METHOD OF CONTROLLING THE AIRCRAFT simplified abstract (The Boeing Company)
Contents
- 1 AIRCRAFT, A CONTROL SYSTEM FOR THE AIRCRAFT AND A METHOD OF CONTROLLING THE AIRCRAFT
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 AIRCRAFT, A CONTROL SYSTEM FOR THE AIRCRAFT AND A METHOD OF CONTROLLING THE AIRCRAFT - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Original Abstract Submitted
AIRCRAFT, A CONTROL SYSTEM FOR THE AIRCRAFT AND A METHOD OF CONTROLLING THE AIRCRAFT
Organization Name
Inventor(s)
Francesco Giannini of Falls Church VA (US)
AIRCRAFT, A CONTROL SYSTEM FOR THE AIRCRAFT AND A METHOD OF CONTROLLING THE AIRCRAFT - A simplified explanation of the abstract
This abstract first appeared for US patent application 18045792 titled 'AIRCRAFT, A CONTROL SYSTEM FOR THE AIRCRAFT AND A METHOD OF CONTROLLING THE AIRCRAFT
Simplified Explanation
The patent application describes an aircraft with a fuselage and a tilt-wing that is movable relative to the fuselage. The aircraft has main propulsors coupled to main propellers on the tilt-wing, providing a first maximum amount of thrust, as well as auxiliary propulsors coupled to auxiliary propellers spaced apart from the tilt-wing, providing a variable amount of thrust. A controller signals the main propulsors to operate at the first maximum amount of thrust during the transition from cruise to landing, and the auxiliary propulsors to operate at the variable amount of thrust during the landing phase.
- Fuselage with tilt-wing design
- Main propulsors with main propellers for maximum thrust
- Auxiliary propulsors with auxiliary propellers for variable thrust
- Controller system for coordinating propulsor operation during flight phases
Potential Applications
This technology could be applied in the development of vertical take-off and landing (VTOL) aircraft for various purposes such as military operations, search and rescue missions, and commercial transportation.
Problems Solved
This technology solves the challenge of efficiently transitioning an aircraft from horizontal flight to vertical descent and landing, improving overall flight control and safety.
Benefits
The benefits of this technology include enhanced maneuverability, reduced landing space requirements, and increased operational flexibility for aircraft in various scenarios.
Potential Commercial Applications
The potential commercial applications of this technology include the development of VTOL aircraft for passenger transport, emergency response services, and aerial surveillance operations.
Possible Prior Art
One possible prior art for this technology could be the development of tilt-wing aircraft designs in the aerospace industry, which have been used in the past for experimental and military purposes.
Unanswered Questions
How does this technology impact fuel efficiency in comparison to traditional aircraft designs?
This article does not provide information on the fuel efficiency implications of the described aircraft design. Further research and testing would be needed to determine the specific impact on fuel consumption.
What are the potential maintenance requirements for the complex propulsor system described in the patent application?
The article does not address the maintenance aspects of the propulsor system. Understanding the maintenance needs and costs associated with this technology would be crucial for its practical implementation.
Original Abstract Submitted
An aircraft, a method of controlling the aircraft, and a control system for the aircraft has a fuselage and tilt-wing movable relative to the fuselage. A plurality of main propulsors coupled to main propellers that is coupled to the tilt-wing, which are configured to provide a first maximum amount of thrust. A plurality of auxiliary propulsors coupled to auxiliary propellers that are spaced apart from the tilt-wing, which are configured to provide a variable amount of thrust. A controller signals the main propulsors to operate at the first maximum amount of thrust when the tilt-wing moves from the cruise position to the transition position, and signals the auxiliary propulsors to operate at the variable amount of thrust when the tilt-wing is in the transition position in which the first maximum amount of thrust and the variable amount of thrust together provide an overall thrust to descend and land the aircraft.
