This concept would be used to safely deploy scientific payloads or enable long-term human exploration of Mars with its associated cargo needs. The deployable system allows mission planners to develop an aeroshell design that fits within existing launch vehicle systems, and yet prior to the EDL mission segment, transforms into a low ballistic coefficient configuration. Thus during atmospheric entry, design requirements such as heating, acceleration, and pressure profiles imparted to the entry system are significantly lowered, allowing the use of lower heat capacity thermal protection system and lower design loads for other spacecraft components, including science instruments.
|Principal Technologist||Project Manager|
|Michelle Munk (firstname.lastname@example.org)||Paul Wercinski (email@example.com)|