Articulating Inlet Wings for Extended-Range Projectiles
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Solution Overview
Problem
Conventional projectiles face challenges in maximizing range due to space constraints that affect both guidance electronics and propulsion systems, particularly in ramjet-type projectiles, where the inlet drag after fuel exhaustion leads to inadequate performance.
Innovation Solution
A wing structure that doubles as an air intake inlet during propulsion and a lift surface post-propulsion, transitioning from a folded to a deployed position to optimize both range and flight time.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If a ramjet propulsion system is used to increase range during initial flight phase, then the range is improved, but the inlet drag after fuel exhaustion causes inadequate performance
Solution Approach 1:
The inlet is designed to be movable rather than fixed, allowing it to transition from a closed position during propulsion to an open position after fuel exhaustion. This dynamic configuration enables the inlet to serve dual purposes: providing air intake during the ramjet phase and minimizing drag during the glide phase, thereby resolving the contradiction between range improvement and drag reduction
Solution Approach 2:
The inlet configuration changes its physical state (open/closed) based on the operational phase. During the propulsion phase, the inlet is closed to reduce drag; during the glide phase, it opens to provide lift surface area. This parameter change allows the system to optimize performance for each phase, addressing the contradiction between maintaining range and reducing harmful drag
2Use of energy by moving object
If the inlet is kept open to provide air intake, then the propulsion system can operate, but the drag increases reducing flight efficiency
Solution Approach 1:
The inlet operates in periodic cycles, alternating between closed and open states based on the propulsion phase. The inlet closes during the glide phase to minimize drag and opens during the propulsion phase to enable air intake. This periodic action allows the system to optimize energy usage by providing air intake only when propulsion is active, while minimizing energy loss from drag during the glide phase
3Length of moving object
If a wing structure is added to provide lift surface, then the range is extended, but the space constraints within the projectile are exceeded
Solution Approach 1:
The inlet structure is designed to serve multiple functions: it acts as an air intake during the propulsion phase and as a lift surface during the glide phase. This multi-functionality eliminates the need for separate dedicated lift surfaces, thereby extending range without exceeding the projectile's space constraints
Solution Approach 2:
The inlet and lift surface are merged into a single structural element. The inlet structure is configured to function as both an air intake mechanism and a lift-generating surface, combining two functions into one component. This merging allows the projectile to achieve extended range through lift while maintaining adherence to space constraints
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 wing structure enables a projectile to achieve a long range and optimal flight time by reducing drag and utilizing the wing as a lift surface after propulsion, improving performance compared to conventional variants.
Implementation Method 1
the wing structure enables a projectile to achieve a long range and optimal flight time by reducing drag and utilizing the wing as a lift surface after propulsion
Implementation Method 2
the wing structure that acts as both the inlet and the lift surface enables both a long range and an optimal time of flight to the target
Data Source
AI summary
A projectile includes a wing structure to form both an inlet that intakes air for combustion by a propulsion system of the projectile during an initial range of flight, and a lift surface for the projectile after the propulsion engine of the propulsion system burns out. The wing structure acts as both the inlet and the lift surface to enable both a long range and an optimal time of flight for the projectile to the target. The wing structure includes at least one wing that is movable from a folded position, in which the wing extends along a propulsion body section of the projectile to define the inlet, to a deployed position, in which the wing extends outwardly from the propulsion body section to form the lift surface. Any number of wings may be provided and the wings may be simultaneously deployed or sequentially deployed depending on the application.