Blunt Body Geometry Optimization for Re-entry Vehicles
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Solution Overview
Problem
Current vehicles designed for planetary exploration and re-entry have limitations in lift and maneuverability, with existing designs reaching payload deliverability limits and being costly or vulnerable to launch debris, necessitating a simultaneous optimization of structural, aerodynamic, aerothermodynamic, and heat transfer responses through geometric parameters and materials.
Innovation Solution
The development of a parametric class of closed convex hull shapes, referred to as COBRA-SQ, and a multi-disciplinary optimization process, COBRA MDO, which optimizes vehicle geometry and performance by analyzing environmental and geometric parameters to achieve desired aerodynamic and aerothermal properties, allowing for automated optimization of aeroshell shapes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional capsule configurations (truncated sphere or sphere-cone) are used, then thermal protection is achieved, but lift and maneuverability are limited
Solution Approach 1:
The patent applies parameter changes by systematically varying geometric parameters (nose radius, body diameter, fin angles, wing camber) to optimize the balance between thermal protection and maneuverability. The vehicle geometry is defined by multiple parameters that can be independently adjusted to achieve desired performance characteristics.
Solution Approach 2:
The patent incorporates dynamic elements through adjustable fin angles and wing camber configurations that can be optimized for different entry conditions. The vehicle design allows for adaptive geometric characteristics to handle varying thermal and aerodynamic loads during re-entry.
2Ease of operation
If high-lift winged vehicles are used, then maneuverability is improved, but operational cost increases and vulnerability to launch debris increases
Solution Approach 1:
The patent employs asymmetric vehicle configurations with differentiated fin and wing geometries that provide enhanced maneuverability without requiring full winged vehicle complexity. The asymmetric fin arrangement and cambered wings deliver improved control characteristics with reduced structural mass and lower operational costs.
3Strength
If existing vehicle designs are used, then structural integrity is maintained, but payload deliverability reaches upper limits
Solution Approach 1:
The patent segments the vehicle structure into optimized components with differentiated structural requirements. The aeroshell, fins, and wings are designed as separate elements that can be independently optimized for strength-to-weight ratios, allowing increased payload capacity while maintaining structural integrity through targeted reinforcement rather than uniform strengthening.
4Force
If geometric parameters are optimized for aerodynamic properties, then lift and drag characteristics improve, but heat transfer control becomes more challenging
Solution Approach 1:
The patent applies local quality optimization by differentiating geometric parameters across different regions of the vehicle. The nose radius, body diameter, and fin geometries are independently optimized to create localized aerodynamic and thermal characteristics. This allows specific regions to be tailored for aerodynamic efficiency while other regions are designed for heat management, resolving the contradiction between aerodynamic performance and thermal protection.
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 improved aerodynamic stability, reduced structural mass, increased payload capacity, and enhanced thermal protection, leading to more efficient and cost-effective vehicle designs for planetary exploration and re-entry missions.
Implementation Method 1
optimization of geometric parameters for blunt bodies for moving vehicles, such as re-entry vehicles, based upon control of heat transfer, aerothermodynamics
Implementation Method 2
yield favorable hypersonic heat transfer and aerothermodynamic properties for low heating and hypersonic aerodynamic properties for maneuverability and stability
Implementation Method 3
the vehicle will be subject to both launch and entry loading to meet structural integrity constraints that may further influence shape design
Data Source
AI summary
A method and associated system for multi-disciplinary optimization of various parameters associated with a space vehicle that experiences aerocapture and atmospheric entry in a specified atmosphere. In one embodiment, simultaneous maximization of a ratio of landed payload to vehicle atmospheric entry mass, maximization of fluid flow distance before flow separation from vehicle, and minimization of heat transfer to the vehicle are performed with respect to vehicle surface geometric parameters, and aerostructure and aerothermal vehicle response for the vehicle moving along a specified trajectory. A Pareto Optimal set of superior performance parameters is identified.