Wing Leading Edge Antenna System for Aircraft
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Solution Overview
Problem
Current large gimbaled antennas on aircraft for on-board entertainment add significant weight and drag, reducing fuel efficiency due to their bulky design, which is not effectively addressed by existing solutions.
Innovation Solution
A wing leading edge antenna system featuring a two-dimensional non-gimbaled scannable antenna integrated into the aircraft wing's leading edge, utilizing a cylindrical feed structure and holographic antenna technology to reduce bulk and weight while maintaining scanning capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If large mechanically steered (gimbaled) antennas are placed on the aircraft fuselage, then on-board entertainment capabilities (satellite TV, broadband Internet) are provided, but weight and drag increase significantly, reducing fuel efficiency
Solution Approach 1:
The patent replaces the mechanical gimbaled antenna system with a fixed antenna integrated into the wing leading edge. The mechanical steering mechanism is substituted with electronic beam scanning capability, eliminating the need for moving parts while maintaining satellite communication functionality. This resolves the contradiction by removing the weight penalty of mechanical components while preserving entertainment capabilities.
Solution Approach 2:
The antenna is merged with the wing structure itself, specifically integrated into the leading edge of the wing. The antenna housing becomes part of the aircraft's structural components rather than a separate attached system. This integration eliminates additional weight from separate mounting structures and streamlines the overall aircraft design.
2Adaptability or versatility
If large mechanically steered (gimbaled) antennas are placed on the aircraft fuselage, then on-board entertainment capabilities are provided, but drag increases by approximately 840 lbs of equivalent operating empty weight, reducing fuel efficiency
Solution Approach 1:
The mechanical gimbal system that required significant space and created aerodynamic drag is replaced with a fixed antenna design. The electronic scanning mechanism eliminates the need for a large radome and mechanical housing, dramatically reducing the cross-sectional area and aerodynamic drag profile of the antenna system.
Solution Approach 2:
The antenna system transitions from a three-dimensional protruding radome structure to a two-dimensional planar array integrated into the wing surface. This dimensional reduction allows the antenna to be flush with the aircraft skin, minimizing disruption to airflow and reducing drag.
3Reliability
If large mechanically steered (gimbaled) antennas with bulky radomes are used, then satellite communication functionality is achieved, but the antenna system mass weight is approximately 200 to 300 lbs or more
Solution Approach 1:
The heavy mechanical gimbal assembly, radome, and support structure are replaced with a lightweight fixed antenna array. The electronic scanning system uses minimal mechanical components, reducing the stationary mass from 200-300 lbs to a fraction of that weight while maintaining full satellite communication capability through electronic beam steering.
4Weight of moving object
If a fixed antenna system is integrated into the wing leading edge, then weight and drag are reduced, but the antenna must achieve scanning capability without mechanical gimbal
Solution Approach 1:
The mechanical scanning mechanism is replaced with an electronic phased array system. By controlling the phase and amplitude of signals across multiple antenna elements, the beam can be electronically steered to different satellite positions without any moving parts. This electronic scanning approach reduces mechanical complexity while achieving the required scanning functionality.
Solution Approach 2:
The scanning capability is achieved by changing electrical parameters (phase, amplitude, frequency) of the signals fed to individual antenna elements rather than physically moving the antenna. This parameter-based control allows flexible beam steering while maintaining a fixed, lightweight antenna structure integrated into the wing.
Data Source
AI summary
Disclosed is a wing leading edge antenna system (“WLEAS”). The WLEAS includes an upper leading edge (“LE”) of a wing of an aircraft, a two-dimensional non-gimbaled scannable antenna (“2D-NGSA”), and an adapter plate. The upper LE of the wing includes two LE ribs and a LE cavity formed by the two LE ribs and a lower LE surface of the wing and the adapter plate is attached to both of the LE ribs within the LE cavity. Moreover, the 2D-NGSA is attached to the adapter plate within the LE cavity.