Reasons for triple-funding of the jet-engine-industry to meet 2020-2040 6TH-Gen-Challenge: Counter-Air Penetration, CAP
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Benjamin Gal-Or
Abstract
The forthcoming 2020-2040 6TH-Generation is characterized by a host of debated and confused CASLAP-strategies, doctrines, tactics, mission definitions, jetonautic-funding, systems-of-systems technologies vis-à-vis AOOF-based-prop-swarm-technologies and almost symmetric jetonautics at both sides, [Part-A references 5,10,11,17,20,24,26,32,36,48,49].
CASLAP offensive-defensive options for each country vary with jetonautics, location, time, scientific and technological education, economics, geopolitics and stealth/super-agility/armament/AI of its fighter aircraft, UCAVs, JES-UCAV, prop-drones or USV, LCS, ULV, each with a different control-communication and various propulsion systems ranging from $100/unit in prop-drone-swarms to $10+ million per jet engine unit with spares, parts, maintenance, etc. It therefore deems timely to introduce an initial degree of order and classification to prevent today future misunderstanding/errors in designs, funding and encounters – the central aim and scope of these editorials.
© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Editorials
- Reasons for Triple-Funding of the Jet-Engine-Industry to Meet 2020–2040 6th-Gen-Challenge: Counter-Air Penetration, CAP
- Reasons for triple-funding of the jet-engine-industry to meet 2020-2040 6TH-Gen-Challenge: Counter-Air Penetration, CAP
- Original Research Articles
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Experimental Investigation of Shape Transition Effects on Isolator Performance
- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
- Gas Turbine Engine Gas-path Fault Diagnosis Based on Improved SBELM Architecture
- The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor
- Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation
- Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle
- Nonlinear System Modeling based on System Equilibrium Manifold
- Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
Articles in the same Issue
- Frontmatter
- Editorials
- Reasons for Triple-Funding of the Jet-Engine-Industry to Meet 2020–2040 6th-Gen-Challenge: Counter-Air Penetration, CAP
- Reasons for triple-funding of the jet-engine-industry to meet 2020-2040 6TH-Gen-Challenge: Counter-Air Penetration, CAP
- Original Research Articles
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Experimental Investigation of Shape Transition Effects on Isolator Performance
- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
- Gas Turbine Engine Gas-path Fault Diagnosis Based on Improved SBELM Architecture
- The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor
- Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation
- Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle
- Nonlinear System Modeling based on System Equilibrium Manifold
- Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
