Manufacturing challenges and benefits when scaling the HIAD stacked-torus aeroshell to a 15m-class system

Cheatwood, F. McNeil; Hughes, Stephen J.; Calomino, Anthony M.; Swanson, Gregory T.; Gilles, Brian; Anderson, Paul; Johnson, R. Keith; Bond, Bruce

doi:10.1109/aero.2016.7500773

Cited by 6 publications

(1 citation statement)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…-Southern Highlands at Mars), and/or greater payload mass and volume than has been demonstrated by rigid capsule systems to date. 14 DEVs are well suited to address the stated emphasis on technology development for aerocapture, drag modulation, and advancements in TPS materials. 15 HIADs have mission applicability at Earth, providing for International Space Station downmass, enabling return for free-flying orbital manufacturing, and the recovery of spent launch vehicle assets for reuse.…”

Section: Mission Applicationsmentioning

confidence: 99%

Deployable Entry Vehicles for Future Science and Exploration Missions

Cassell

Cheatwood

Hughes

et al. 2021

Bulletin of the AAS

View full text Add to dashboard Cite

Vehicle (DEV) technology has made significant advances over the last decade with ground test development campaigns and flight test demonstrations. DEVs offer benefits over traditional rigid entry vehicles including lower volume and mass, w hile enabling larger payload delivery and greater landing access. A crucial mission benefit is the DEV capability to transform from a compactly stowed configuration within the launch vehicle to a high drag area entry system for delivery of landers, rovers, aerial platforms, and orbiters (via aerocapture). These benefits span the range of mission classes from Small Satellite (smallsat) to human-class exploration systems. This paper will describe DEV technology development status, highlight mission concepts, and recommend future investments.

show abstract

Section: Mission Applicationsmentioning

confidence: 99%

Deployable Entry Vehicles for Future Science and Exploration Missions

Cassell

Cheatwood

Hughes

et al. 2021

Bulletin of the AAS

View full text Add to dashboard Cite

show abstract

Performance Efficient Launch Vehicle Recovery and Reuse

et al. 2016

Self Cite

View full text Add to dashboard Cite

For decades, economic reuse of launch vehicles has been an elusive goal. Recent attempts at demonstrating elements of launch vehicle recovery for reuse have invigorated a debate over the merits of different approaches. The parameter most often used to assess the cost of access to space is dollars-per-kilogram to orbit. When comparing reusable vs. expendable launch vehicles, that ratio has been shown to be most sensitive to the performance lost as a result of enabling the reusability. This paper will briefly review the historical background and results of recent attempts to recover launch vehicle assets for reuse. The business case for reuse will be reviewed, with emphasis on the performance expended to recover those assets, and the practicality of the most ambitious reuse concept, namely propulsive return to the launch site.In 2015, United Launch Alliance (ULA) announced its Sensible, Modular, Autonomous Return Technology (SMART) reuse plan for recovery of the booster module for its new Vulcan launch vehicle. That plan employs a non-propulsive approach where atmospheric entry, descent and landing (EDL) technologies are utilized. Elements of such a system have a wide variety of applications, from recovery of launch vehicle elements in suborbital trajectories all the way to human space exploration. This paper will include an update on ULA's booster module recovery approach, which relies on Hypersonic Inflatable Aerodynamic Decelerator (HIAD) and Mid-Air Retrieval (MAR) technologies, including its concept of operations (ConOps). The HIAD design, as well as parafoil staging and MAR concepts, will be discussed. Recent HIAD development activities and near term plans including scalability, next generation materials for the inflatable structure and heat shield, and gas generator inflation systems will be provided. MAR topics will include the ConOps for recovery, helicopter selection and staging, and the state of the art of parachute recovery systems using large parafoils for space asset recovery and high altitude deployment.The next proposed HIAD flight demonstration is called HULA (for HIAD on ULA), and will feature a 6m diameter HIAD. An update for the HULA concept will be provided in this paper. As proposed, this demonstration will fly as a secondary payload on an Atlas mission.

show abstract

Mission for an Impermanent Surface Stay to Investigate Our Neighbor, Mars

Paletta

Hoffman

et al. 2020

Ascend 2020

View full text Add to dashboard Cite

Manufacturing challenges and benefits when scaling the HIAD stacked-torus aeroshell to a 15m-class system

Cited by 6 publications

References 5 publications

Deployable Entry Vehicles for Future Science and Exploration Missions

Deployable Entry Vehicles for Future Science and Exploration Missions

Performance Efficient Launch Vehicle Recovery and Reuse

Mission for an Impermanent Surface Stay to Investigate Our Neighbor, Mars

Contact Info

Product

Resources

About