Inflatable Aerodynamic Decelerator Using Thin Film Radiative Cooling
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Solution Overview
Problem
Current atmospheric entry systems face challenges with high heat and mass requirements due to rigid aeroshells and inflatable decelerators, which limit payload capacity and increase launch vehicle costs, as they necessitate substantial thermal protection systems and bulky inflation systems.
Innovation Solution
An ultra-low ballistic coefficient inflatable aerodynamic decelerator design using a large, lightweight balloon envelope made of thin films, such as Kapton, surrounded by high-strength scrim materials, which reduces heat flux and mass fraction, allowing for efficient deceleration with minimal thermal protection needs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If rigid aeroshells with thermal protection systems are used, then heat shielding capability is improved, but mass and volume increase significantly
Solution Approach 1:
The patent employs a thin-film inflatable aeroshell structure that replaces traditional rigid thermal protection systems. The flexible membrane can be inflated to create a large surface area for heat radiation while maintaining low mass. The thin film structure allows the system to achieve adequate heat shielding through radiative cooling without requiring heavy ablative or reflective thermal protection materials.
Solution Approach 2:
The aeroshell transitions from a compressed low-volume state during launch to an inflated large-volume state during atmospheric entry. This dynamic transformation allows the system to optimize its thermal management characteristics during entry by inflating to a larger surface area that enhances radiative heat dissipation, while minimizing mass and volume constraints during launch.
2Weight of moving object
If inflatable aerodynamic decelerators are used, then payload mass capability is improved, but heating rates increase due to smaller size
Solution Approach 1:
The thin-film inflatable aeroshell provides a large surface area to volume ratio that enhances radiative heat dissipation. The flexible membrane structure can be inflated to optimal dimensions that balance payload capacity with thermal management requirements, allowing the system to radiate heat effectively across its entire surface area.
Solution Approach 2:
The system changes its physical parameters by inflating to a larger volume and surface area during atmospheric entry. This parameter change increases the radiative heat dissipation capability while maintaining the payload mass advantage of inflatable structures. The inflation process allows the aeroshell to achieve thermal management characteristics appropriate for the entry phase while retaining compact launch dimensions.
3Object-affected harmful factors
If thermal protection system materials are applied to inflatable decelerators, then heat protection is improved, but mass and volume available for payload are reduced
Solution Approach 1:
The patent uses the thin-film inflatable aeroshell itself as the primary thermal protection mechanism rather than adding separate TPS materials. The flexible membrane's large surface area enables effective radiative heat dissipation, eliminating or reducing the need for additional thermal protection layers that would consume payload volume and mass.
Solution Approach 2:
The inflatable aeroshell structure serves multiple functions simultaneously: it provides aerodynamic deceleration, structural protection during launch, and thermal management during entry through radiative cooling. This multi-functionality eliminates the need for separate dedicated thermal protection systems, maximizing the volume and mass available for payload.
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 design significantly reduces the mass and volume of the deceleration system, enabling larger payloads with lower heating rates and reduced thermal protection needs, allowing for more efficient and cost-effective atmospheric entry by utilizing the thin film's ability to radiate heat and withstand g-loads effectively.
Implementation Method 1
causing aerodynamic forces to decelerate the atmospheric entry payload
Implementation Method 2
utilizing the thin film's ability to radiate heat
Data Source
AI summary
An inflatable aerodynamic deceleration method and system is provided for use with an atmospheric entry payload. The inflatable aerodynamic decelerator includes an inflatable envelope and an inflatant, wherein the inflatant is configured to fill the inflatable envelope to an inflated state such that the inflatable envelope surrounds the atmospheric entry payload, causing aerodynamic forces to decelerate the atmospheric entry payload.