Honda motor co., ltd. (20240109652). BLADE AND ROTOR simplified abstract
Contents
- 1 BLADE AND ROTOR
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 BLADE AND ROTOR - 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 Unanswered Questions
- 1.11 Original Abstract Submitted
BLADE AND ROTOR
Organization Name
Inventor(s)
Takaaki Yasuda of Wako-shi (JP)
Susumu Mashio of Wako-shi (JP)
Masahiko Asanuma of Wako-shi (JP)
BLADE AND ROTOR - A simplified explanation of the abstract
This abstract first appeared for US patent application 20240109652 titled 'BLADE AND ROTOR
Simplified Explanation
The abstract describes a blade for use in a rotor of an aircraft that is swept in a region extending to a blade tip from a first position located between the rotation center of the rotor and the blade tip in a radial direction of the VTOL rotor. The sweep amount increases from the first position toward the blade tip, and the rate of change of the sweep amount in a region extending to the blade tip from a second position located between the first position and the blade tip in the radial direction of the VTOL rotor is greater than the rate of change of the sweep amount in a region extending from the first position to the second position.
- The blade is designed to have a swept shape that increases in sweep amount towards the blade tip.
- The rate of change of the sweep amount is higher in the region closer to the blade tip compared to the region closer to the rotation center of the rotor.
Potential Applications
The technology could be applied in the design and manufacturing of rotor blades for VTOL aircraft, improving their aerodynamic performance and efficiency.
Problems Solved
1. Improved aerodynamic performance of rotor blades. 2. Enhanced efficiency of VTOL aircraft.
Benefits
1. Increased lift and stability during flight. 2. Reduced drag and fuel consumption. 3. Enhanced maneuverability and control.
Potential Commercial Applications
Optimizing rotor blade design for VTOL aircraft in the aerospace industry.
Possible Prior Art
There may be prior art related to swept blade designs in the aerospace industry, but specific examples are not provided in the abstract.
Unanswered Questions
How does the increased sweep amount towards the blade tip affect the overall performance of the rotor blade?
The abstract does not delve into the specific impact of the increased sweep amount on the aerodynamic characteristics and efficiency of the rotor blade.
Are there any limitations or drawbacks associated with the design of the swept blade for VTOL rotors?
The abstract does not mention any potential limitations or drawbacks that may arise from implementing this specific design in VTOL rotor blades.
Original Abstract Submitted
a blade for use in a rotor of an aircraft is swept in a region extending to a blade tip from a first position located between the rotation center of the rotor and the blade tip in a radial direction of the vtol rotor, the sweep amount increases from the first position toward the blade tip, and the rate of change of the sweep amount in a region extending to the blade tip from a second position located between the first position and the blade tip in the radial direction of the vtol rotor, is greater than the rate of change of the sweep amount in a region extending from the first position to the second position.
