Aerospace Plane Wing Body Design with Retractable Intake Doors
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Solution Overview
Problem
Current commercial airplanes face inefficiencies in fuel consumption and payload capacity due to suboptimal aerodynamic center and center of gravity positioning, leading to increased fuel usage and operational costs, especially during long-range flights, and require multiple crew members for operation, which raises labor costs.
Innovation Solution
The aerospace plane design features a hybrid wing body shape with angled trailing edges, multi-axis vectored thrust, and a single pilot cockpit, allowing for efficient fuel management by positioning the aerodynamic center forward of or coincident with the center of gravity, reducing drag, and incorporating retractable engine intake doors to conserve fuel, while also enabling single-pilot operations through advanced automation and control systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If traditional horizontal stabilizers are used to create downward balancing force, then flight stability is achieved, but induced and trim drag increase reducing aerodynamic efficiency
Solution Approach 1:
The patent inverts the traditional horizontal stabilizer function by using upward-lifting surfaces instead of downward-pushing surfaces. The canard surfaces and tail horizontal stabilizers are configured to generate upward lift forces, reversing the conventional approach where horizontal stabilizers create downward force for balance. This inversion eliminates the associated drag penalties while maintaining flight stability through alternative aerodynamic mechanisms.
2Speed
If airplanes fly at lower altitudes (33,000-39,000 feet), then airspeed is maintained, but fuel consumption increases significantly
Solution Approach 1:
The patent employs dynamic altitude management strategies that allow the aircraft to operate efficiently across varying altitude ranges. The system dynamically adjusts flight parameters including altitude, speed, and configuration to optimize the balance between airspeed maintenance and fuel consumption, enabling operations at higher altitudes where fuel efficiency is improved while maintaining adequate airspeed through optimized aerodynamic configurations.
3Reliability
If multiple crew members are required for long-range operations, then regulatory compliance is achieved, but operating costs increase
Solution Approach 1:
The patent implements advanced automation systems and enhanced monitoring technologies that fundamentally change the operational parameters of crew requirements. Through sophisticated flight management systems, automated systems, and improved reliability parameters, the aircraft can operate with reduced crew configurations while maintaining regulatory compliance, thereby reducing labor costs for long-range operations.
4Use of energy by moving object
If aerodynamic center is positioned aft of center of gravity, then aircraft stability is reduced, but fuel efficiency improves
Solution Approach 1:
The patent employs canard surfaces positioned forward of the center of gravity that generate upward lifting forces, creating a counterbalancing moment that compensates for the aft-positioned aerodynamic center. This counterweight effect from the canard surfaces allows the aircraft to maintain adequate longitudinal stability even with the aerodynamic center located behind the center of gravity, enabling the fuel-efficient configuration while managing stability through the opposing moment from the forward canards.
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
This design achieves a significant increase in range and payload capacity, reduces fuel consumption, and lowers operational costs by allowing single-pilot operations, enhancing efficiency and reducing the need for multiple crew members, thus improving overall aircraft performance and economic viability.
Implementation Method 1
A wing has an air foil cross sectional shape that generates lift by creating a pressure differential where there is a high pressure below the wing and low pressure above the wing
Implementation Method 2
an engine to provide thrust
Data Source
AI summary
An aerospace plane having an elongate body supporting a pair of wings each having at least two angled, trailing edge portions. The pair of wings are adapted to extend away from the elongated body in opposing directions. A landing gear assembly is operatively associated with the elongated body to be moveable from a retracted position where the landing gear assembly is substantially locatable within the elongated body and an extended position where the landing gear assembly extends at least partially away from the elongated body. At least one engine adapted to generate thrust. At least one stabilizer adapted to assist with movement of the aerospace plane during flight. The at least one engine is located at least partially within an intake housing adapted to direct air into said at least one engine. The intake housing having at least one inlet door adapted to move from a fully open position, which allows air to pass into the engine, to a sealingly closed position which prevents air from flowing into the engine, when the engine is shut down during flight.