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Description
The design of an efficient Thermal Protection System (TPS) remains one of the most challenging
tasks of planetary exploration missions. Because of the harshness of atmospheric entry environments,
no ground facility can exactly replicate all of the conditions. Consequently, engineers
must rely on numerical models to design TPS. Over the last few years, significant improvements
have been made on the ability to numerically predict flight environment and the associated material
response. However, to increase confidence on these models, it is important to compare
them to actual fight data.
There are limited flight data available to inform TPS performance: Apollo 4, Apollo 6, FIRE-II,
MER, MSL, and, very recently, Orion EFT-1. Not only were these flights part of elaborate and
costly flight programs, but the TPS tested on them were at the final stage of design.
Therefore, there is a need to provide a low-cost test-bed to quickly and reliably
screen TPS materials. To that point, Thermal Protection System research is a topic of great
interest to NASA, and Entry systems is currently listed as one of the main Technology Area (TA
9.1) of the 2015 NASA Technology Roadmaps.
Over the last few years, NASA has started the development of several of small capsules, of
various sizes, for various purposes. For instance, the REBR capsule (Aerospace Corp./NASA
Ames) was designed to record re-entry breakup patterns for large orbital debris entering the
atmosphere. REBR flew on several missions, with successful results on the great majority of
them. Building on that, the Maraia capsule (NASA Jonhson Space Center (JSC)) was designed
with the purpose of providing a quick payload return option for the ISS. At the same time, both
the Red-DATA (TVA/NASA JSC) and the SPRITE capsule (NASA Ames Research Center
(Ames)) were intended to test heat shield materials in flight conditions.
Inspired by these designs, the Kentucky Re-entry Universal Payload System (KRUPS) capsule
was developed at the University of Kentucky as a cost-efficient atmospheric entry experiment
testbed. Although KRUPS could be used to test several di.erent experiments, the current
incarnation aims at providing a test-bed for TPS testing. The design of KRUPS has been
ongoing for the last 5 years, starting from conceptual design to baseline qualifications.
As a technology maturation step, two KRUPS spacecraft were recently ejected from two separate sub-orbital
sounding rockets at altitudes of 150 km and 175 km, respectively. The capsules were instrumented so that
the thermal behavior of the heat shield would be monitored during reentry. In order to fully assess the capability
of the KRUPS capsule to be used for TPS testing, it is imperative that the whole system be tested at orbital velocity.
The most cost-e.ective method to do so is to perform entry from the ISS. The proposed
project therefore aims at de-orbiting a KRUPS capsule from the ISS, and transmit
the measured TPS performance data to the Iridium satellite as the capsule enters
the atmosphere. The Concept of Operation of this mission is illustrated in Fig. 1. After
completion of this flight, it is expected that the capsule will have risen to a TRL of 7.
Status | Finished |
---|---|
Effective start/end date | 1/1/19 → 12/31/21 |
Funding
- National Aeronautics and Space Administration: $100,000.00
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Projects
- 1 Finished
-
Science: NASA KY EPSCoR KRUPS: ISS Flight for Heat Shield Testing
Martin, A. (PI), Smith, W. (CoI) & Smith, S. (CoI)
National Aeronautics and Space Administration
1/1/19 → 12/31/21
Project: Research project