Hypersonic Inflatable Aerodynamic Decelerator (HIAD)Technology Development Overview

Abstract

The successful flight of the Inflatable Reentry Vehicle Experiment (IRVE)-3 has further demonstrated the potential value of Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology. This technology development effort is funded by NASA's Space Technology Mission Directorate (STMD) Game Changing Development Program (GCDP). This paper provides an overview of a multi-year HIAD technology development effort, detailing the projects completed to date and the additional testing planned for the future.The effort was divided into three areas: Flexible Systems Development (FSD), Mission Advanced Entry Concepts (AEC), and Flight Validation. FSD consists of a Flexible Thermal Protection Systems (FTPS) element, which is investigating high temperature materials, coatings, and additives for use in the bladder, insulator, and heat shield layers; and an Inflatable Structures (IS) element which includes manufacture and testing (laboratory and wind tunnel) of inflatable structures and their associated structural elements. AEC consists of the Mission Applications element developing concepts (including payload interfaces) for missions at multiple destinations for the purpose of demonstrating the benefits and need for the HIAD technology as well as the Next Generation Subsystems element.Ground test development has been pursued in parallel with the Flight Validation IRVE-3 flight test. A larger scale (6m diameter) HIAD inflatable structure was constructed and aerodynamically tested in the National Full-scale Aerodynamics Complex (NFAC) 40ft by 80ft test section along with a duplicate of the IRVE-3 3m article. Both the 6m and 3m articles were tested with instrumented aerodynamic covers which incorporated an array of pressure taps to capture surface pressure distribution to validate Computational Fluid Dynamics (CFD) model predictions of surface pressure distribution. The 3m article also had a duplicate IRVE-3 Thermal Protection System (TPS) to test in addition to testing with the Aerocover configuration. Both the Aerocovers and the TPS were populated with high contrast targets so that photogrammetric solutions of the loaded surface could be created. These solutions both refined the aerodynamic shape for CFD modeling and provided a deformed shape to validate structural Finite Element Analysis (FEA) models.Extensive aerothermal testing has been performed on the TPS candidates. This testing has been conducted in several facilities across the country. The majority of the testing has been conducted in the Boeing Large Core Arc Tunnel (LCAT). HIAD is continuing to mature testing methodology in this facility and is developing new test sample fixtures and control methodologies to improve understanding and quality of the environments to which the samples are subjected. Additional testing has been and continues to be performed in the With the successful completion to the IRVE-3 flight demonstration, mission planning efforts are ramping up on the development of the HIAD Earth Atmospheric Reenty Test (HEART) which will demonstrate a relevant...

Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight

“…In general, the use of a deployable aeroshell allows the vehicle to be decelerated at a higher altitude compared with a conventional rigid reentry vehicle. This provides several advantages for the entry, descent, and landing (EDL) approach, such as a lower heat load from aerodynamic heating and reduction in radio-frequency blackout [1][2][3][4][5][6][7][8][9]. Recently, a reentry vehicle with an inflatable aeroshell has also been developed in the Membrane Aeroshell for Atmospheric-entry Capsule (MAAC) project, in cooperation with several universities and JAXA.…”

Aerodecelerator Performance of Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry

“…This technology can provide several advantages, e.g., reduction in aerodynamic heating during atmospheric reentry [1][2][3][4][5][6][7][8][9]. For flare-type thin-membrane aeroshells, several studies of elemental technologies and demonstration flights have been performed as part of the Membrane Aeroshell for Atmospheric-entry Capsule (MAAC) project [10][11][12][13][14].…”

Morphing Hypersonic Inflatable Aerodynamic Decelerator

“…The successful Inflatable Reentry Vehicle Experiment -II (IRVE-II) was completed on August 17, 2009 [7]. This experiment demonstrated that inflatable heat shields could maintain stability from hypersonic through subsonic speeds, which is a significant milestone to overcome for any EDL system.…”

“…IRVE-II's success has generated considerable interest in the development of HIAD technology for atmospheric entry. In June 2010, the NASA Office of the Chief Technologist (OCT) initiated the HIAD Project to accelerate the development of HIAD technology [7].…”

“…In developing this technology, the HIAD Project is tackling three developmental challenges: (1) the survivability of a Flexible Thermal Protection System (FTPS) during atmospheric reentry, (2) IAD system performance at relevant scales, and (3) demonstrating IAD controllability during hypersonic entry [7]. To meet these three developmental challenges, the project has designed a flight experiment and a mission concept, the Inflatable Reentry Vehicle Experiment (IRVE) -3 and the High Energy Atmospheric Reentry Test (HEART).…”