Closed-Wing VTOL Ejector Layout for Thrust-Balanced Transition
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Solution Overview
Problem
VTOL aircraft face challenges in engine sizing and thrust balance, particularly in transitioning between vertical take-off and horizontal flight, with existing designs often requiring heavy engines that are inefficient for cruise conditions and difficult to balance.
Innovation Solution
The use of thrust augmenting ejectors and a gas generator system, combined with a closed wing shroud, to distribute thrust across various locations on the aircraft, achieving augmentation ratios up to 3:1, and incorporating swiveling thrusters for attitude control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple independent communication systems are used for different functions (telemetry, voice, data, video), then communication reliability is improved, but device complexity and cost increase
Solution Approach 1:
The patent implements a single communication system that performs multiple functions including telemetry, voice communication, data transmission, and video transmission. The system uses a unified transceiver with configurable modes that can handle different communication protocols and data types through one interface, eliminating the need for separate independent communication systems for each function.
Solution Approach 2:
The patent combines previously separate communication functions into a single integrated communication system. The unified system merges telemetry, voice, data, and video communication capabilities into one platform, reducing the number of separate systems while maintaining all required communication functions through shared hardware and software resources.
2Reliability
If multiple independent communication systems are used for different functions, then communication reliability is improved, but cost increases
Solution Approach 1:
The patent implements a single communication system that performs multiple functions including telemetry, voice, data, and video transmission. The system uses a unified transceiver with configurable modes that can handle different communication protocols and data types through one interface, eliminating the need for separate independent communication systems for each function.
Solution Approach 2:
The patent combines previously separate communication functions into a single integrated communication system. The unified system merges telemetry, voice, data, and video communication capabilities into one platform, reducing the number of separate systems while maintaining all required communication functions through shared hardware and software resources.
3Area of stationary object
If communication antenna is collocated with radar antenna, then spatial requirements are reduced, but interference between systems increases
Solution Approach 1:
The patent introduces a reflector as an intermediary element between the radar antenna and communication antenna. The reflector redirects radar energy away from the communication antenna while allowing communication signals to pass through or around it. This intermediary structure enables spatial collocation of both antennas without direct interference, as the reflector mediates the interaction between the two electromagnetic fields.
Solution Approach 2:
The patent uses a reflector structure that manipulates electromagnetic waves in three-dimensional space to resolve the two-dimensional conflict between radar and communication antennas. By introducing spatial dimensionality through the reflector's geometric configuration, the system allows both antennas to occupy the same general area while maintaining electromagnetic isolation through directional wave propagation control.
Data Source
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AI summary
A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.