HPVO Propulsion System with Differential Speed Fan for Stealth and Efficiency
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Solution Overview
Problem
Current aircraft propulsion systems face challenges with poor fuel efficiency, high noise levels, and structural sensitivity to damage, particularly in military aviation where stealth characteristics are crucial, and existing fan designs are inadequate for high speeds and stealth requirements.
Innovation Solution
The development of a High Performance Optimized Versatile Propulsion (HPVO) system featuring a differential speed fan (DVF) integrated into the aircraft hull, allowing air to pass through the fan housing and out radially, with a unique design that reduces IR and radar signatures, enables vectorized thrust, and provides stability and resistance to foreign object damage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If cross-flow fans with no solid rotor hub are used, then air can pass through the hub, but the construction is too weak for high speeds and very sensitive to damage from foreign objects
Solution Approach 1:
A solid rotor hub is introduced as an intermediary structure between the air intake and the fan blades. The hub provides structural strength and damage resistance while still allowing air to pass through designated channels within it, resolving the contradiction between structural integrity and air passage requirements.
Solution Approach 2:
The rotor hub is designed as a composite structure combining solid material for strength with internal passages for air flow. This composite approach allows the hub to simultaneously provide mechanical strength against foreign objects and maintain the necessary air passage functionality.
2Volume of moving object
If elongated fan rollers with b >> D are used, then the fan can be compact, but the structure is weak and sensitive to foreign object damage
Solution Approach 1:
The fan design transitions from static elongated rollers to a dynamic rotor assembly with a solid hub and adjustable blades. The solid hub provides structural strength while the rotor can be dynamically controlled to optimize performance and resistance to foreign objects.
Solution Approach 2:
The rotor assembly combines a solid hub structure with fan blades, creating a composite design that maintains compactness (b ≈ D) while significantly improving structural strength and resistance to foreign object damage compared to elongated roller designs.
3Object-affected harmful factors
If air intakes are positioned to provide small radar reflectors, then radar signature is reduced, but air resistance increases
Solution Approach 1:
The air intake geometry is optimized by changing parameters such as inlet angle, lip shape, and internal flow path configuration. These parameter changes allow the intake to maintain a low radar cross-section while minimizing flow separation and reducing drag penalties.
Solution Approach 2:
Different portions of the air intake system are designed with different local qualities - the external shape is optimized for radar reduction while the internal flow paths are optimized for aerodynamic efficiency. This local differentiation resolves the contradiction between radar signature and air resistance.
4Productivity
If thrust vectoring is implemented, then takeoff distance is reduced and ascent angle is increased, but system complexity increases
Solution Approach 1:
The thrust vectoring system is segmented into multiple independent control elements - individual fan blade pitch control, differential thrust capability, and vectoring nozzles. This segmentation allows for simplified control of complex thrust vectoring functions through modular, independently controllable components.
Solution Approach 2:
The propulsion system incorporates dynamic thrust vectoring capability through adjustable fan blade pitch and movable nozzle configurations. This dynamic adjustment allows the system to optimize takeoff performance by varying thrust direction and magnitude without requiring complex mechanical vectoring mechanisms.
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 HPVO system achieves short take-off and landing distances, low noise, improved stealth characteristics, and high propulsion efficiency, with the ability to operate across a wide speed range, enhancing flight safety and reducing air resistance while maintaining structural integrity.
Implementation Method 1
a first diffuser (14, 41) arranged in the forward direction of air flow behind the DVF (4), said first diffuser (14, 41) having a first diffuser outlet (14)
Implementation Method 2
a second diffuser (42) arranged in the rearward direction of air flow behind the jet nozzle (6), said second diffuser (42) having a diffuser outlet (42)
Implementation Method 3
an airplug in front of the fan, such an airplug is provided in the invention and its purpose is to reduce any pressure drops in the air before the air reaches the fan
Data Source
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AI summary
The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, "CTOL" (Conventional Take Off and Landing), "Chair" and for vertical takeoff and landing, "V (t) OL" (Vertical (Take) Off and Landing ') and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles.