Oblique All-Wing Vehicle Vertical Launch and Glide
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Solution Overview
Problem
Existing payload launch vehicles lack the versatility and efficiency to operate across a wide range of flight conditions and to perform tasks such as payload delivery and cargo transport effectively.
Innovation Solution
The oblique all-wing (OAW) vehicle, which features an elongated airfoil body with a rocket engine mounted at one end, allowing for vertical launch and subsequent oblique orientation for maximum performance and flexibility in flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a conventional fuselage-based vehicle is used for payload launch, then structural strength is maintained, but versatility across different flight conditions deteriorates
Solution Approach 1:
The vehicle is divided into functional segments: the elongated airfoil body provides aerodynamic performance across multiple flight regimes, while the rocket engine module provides propulsion. This segmentation allows each component to be optimized independently for its specific function while maintaining overall system versatility.
Solution Approach 2:
The elongated airfoil body serves multiple functions: it provides structural support, generates aerodynamic lift during gliding flight, and serves as the mounting structure for the rocket engine and payload. This multi-functionality eliminates the need for separate fuselage and wing structures, achieving versatility without proportionally increasing complexity.
2Productivity
If vertical launch configuration is used, then payload delivery efficiency is improved, but control during flight deteriorates
Solution Approach 1:
The vehicle transitions dynamically between different flight configurations: vertical orientation during rocket-powered ascent for maximum delivery efficiency, then rotating to an oblique angle during gliding flight for optimal aerodynamic control and stability. This dynamic reconfiguration allows the vehicle to optimize for each flight phase independently.
Solution Approach 2:
The vehicle operates in an asymmetric oblique orientation during gliding flight, with the longitudinal axis at an angle to the flight path. This asymmetric configuration provides inherent aerodynamic stability and simplified control compared to symmetric configurations, while maintaining the vertical launch capability for efficient payload delivery.
3Use of energy by moving object
If oblique orientation during flight is used, then aerodynamic performance is improved, but structural stability deteriorates
Solution Approach 1:
The vehicle changes its orientation parameter from vertical (during launch) to oblique (during gliding flight). This parameter change optimizes aerodynamic performance by aligning the airfoil body with the flight path at the optimal angle of attack, while the elongated airfoil structure maintains structural stability through its inherent design that distributes aerodynamic loads along its length.
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
The OAW vehicle achieves efficient payload delivery and cargo transport by utilizing its unique airfoil design and rocket propulsion system, enabling it to operate effectively across a wide range of flight conditions and to land safely while in an oblique orientation.
Implementation Method 1
a rocket engine可以提供推力来垂直发射OAW车辆
Implementation Method 2
OAW车辆以纵向轴线与飞行路径成角度的倾斜方向飞行和/或着陆
Data Source
AI summary
An oblique all-wing (OAW) vehicle and methods are described where the OAW vehicle has a unique configuration and can be used to, for example, launch a payload. The OAW vehicle can include an elongated airfoil body with a longitudinal axis, a top surface, a bottom surface, a first longitudinal end, a second longitudinal end, a first longitudinal edge at a first juncture between the top surface and the bottom surface, and a second longitudinal edge at a second juncture between the top surface and the bottom surface. The elongated airfoil body has an airfoil-shaped cross-section, with the first longitudinal edge defining a leading edge and the second longitudinal edge defining a trailing edge. A rocket engine or other propulsion device is mounted to the elongated airfoil body at the first longitudinal end.