Conductive Airframe Antenna Segmentation for Radiation Efficiency

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Solution Overview

Problem

Integrating wide-band high-efficiency antennas into airframes, especially at low frequencies, is challenging due to size constraints and the electrical conductivity of airframes, which limits bandwidth and efficiency of conformal antennas.

Innovation Solution

The integration of zero net weight, wide-band high-efficiency antennas is achieved by electrically isolating and combining conductive sections of the airframe to form dipole and monopole antenna structures, allowing for selective electrical interconnection to create various antenna configurations, including wing dipoles, fuselage monopoles, and stabilizer antennas, without adding weight or altering the airframe's aerodynamics.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If conformal antennas are printed on conductive airframe surfaces, then antenna integration is achieved, but bandwidth and radiation efficiency are reduced

Engineering Contradiction:

Improveantenna integrationVSAvoidradiation efficiency

Core Design Contradiction:

Adaptability or versatilityVSLoss of energy

Solution Approach 1:

The conductive airframe is segmented into multiple electrically isolated sections (wings, fuselage, stabilizers) that can be selectively connected to form antenna elements. This segmentation allows the antenna to be decoupled from the continuous conductive surface, improving radiation efficiency while maintaining integration benefits

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Electrically conductive but mechanically insulating elements are introduced as intermediaries to connect antenna elements while maintaining electrical isolation from the airframe. These intermediaries enable selective electrical connection without compromising radiation efficiency

Inventive Principle:

Principle #24Intermediary (Mediator)

2Loss of energy

If large antennas are used for low frequency operation, then radiation efficiency is improved, but antenna size and aerodynamic drag increase

Engineering Contradiction:

Improveradiation efficiencyVSAvoidaerodynamic drag

Core Design Contradiction:

Loss of energyVSObject-affected harmful factors

Solution Approach 1:

Multiple existing airframe structures (wings, fuselage, stabilizers) are merged to form a complete antenna system. By combining these structures, the antenna achieves the necessary electrical length for low frequency operation without adding separate protruding elements, thus maintaining aerodynamic cleanliness

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The airframe structures serve dual functions: their primary aerodynamic/structural roles and their secondary role as antenna elements. This multi-functionality allows low frequency antennas to be formed using existing structures rather than adding dedicated antenna components that would increase drag

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Loss of energy

If antenna elements are electrically isolated from the airframe, then radiation efficiency is improved, but antenna integration and structural complexity increase

Engineering Contradiction:

Improveradiation efficiencyVSAvoidelectrical isolation complexity

Core Design Contradiction:

Loss of energyVSDevice complexity

Solution Approach 1:

The antenna system uses the airframe's own structures (wings, fuselage, stabilizers) as antenna elements, eliminating the need for separate antenna components. The electrically isolated conductive sections are already present as structural elements, so no additional components are needed to achieve the antenna function

Inventive Principle:

Principle #25Self-service

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 approach results in antennas with near-perfect radiation efficiency, minimal weight, and no drag, capable of operating across multiple frequency bands, including HF, VHF, and UHF, with improved efficiency compared to conventional conformal solutions.

Implementation Method 1

electrically isolating and combining select conductive sections of an airframe to form dipole and monopole antenna structures

Methodology Applied

Scientific EffectElectromagnetic radiation: Electromagnetic Induction

Data Source

PatentUS10644384B1Zero weight airborne antenna with near perfect radiation efficiency utilizing conductive airframe elements and method

Publication Date: 2020.05.05 VIRTUAL EM INC

AI summary

An aircraft includes a fuselage assembly including a first elongated structural member formed of electrically conductive material, at least one wing assembly including a second structural member formed of electrically conductive material, at least one horizontal stabilizer assembly including a third structural member formed of electrically conductive material, and at least one vertical stabilizer assembly including a fourth structural member formed of electrically conductive material. The wing assembly, the horizontal stabilizer, and the vertical stabilizer are each interconnected with the fuselage assembly in a flight configuration normal to the fuselage. The first, second, third and fourth structural members are electrically insulated from one another. An electronic communication device within the aircraft is configurable for selective electrical interconnection of two or more of said structural members to form a dipole or monopole type transmitting/receiving antenna.