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| Titel |
RITD - Adapting Mars Entry, Descent and Landing System for Earth |
| VerfasserIn |
Jyri Heilimo, Ari-Matti Harri, Sergey Aleksashkin, Vsevolod Koryanov, Ignacio Arruego, Walter Schmidt  , Harri Haukka, Valery Finchenko, Maxim Martynov, Boris Ostresko, Andrey Ponomarenko, Viktor Kazakovtsev, Susanna Martin, Tero Siili |
| Konferenz |
EGU General Assembly 2014
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| Medientyp |
Artikel
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| Sprache |
Englisch
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| Digitales Dokument |
PDF |
| Erschienen |
In: GRA - Volume 16 (2014) |
| Datensatznummer |
250091227
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| Publikation (Nr.) |
 EGU/EGU2014-5506.pdf |
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| Zusammenfassung |
| Abstract
A new generation of inflatable Entry, Descent and Landing System (EDLS) for Mars has
been developed. It is used in both the initial atmospheric entry and atmospheric descent
before the semi-hard impact of the penetrator into Martian surface. The EDLS applicability to
Earth’s atmosphere is studied by the EU/RITD [1] project. Project focuses to the analysis and
tests of the transonic behaviour of this compact and light weight payload entry system at the
Earth re-entry.
1. EDLS for Earth
The dynamical stability of the craft is analysed, concentrating on the most critical
part of the atmospheric re-entry, the transonic phase. In Martian atmosphere the
MetNet vehicle stability during the transonic phase is understood. However, in
the more dense Earth’s atmosphere, the transonic phase is shorter and turbulence
more violent. Therefore, the EDLS has to be sufficiently dynamically stable to
overcome the forces tending to deflect the craft from its nominal trajectory and
attitude.
The preliminary design of the inflatable EDLS for Earth will be commenced once the
scaling of the re-entry system and the dynamical stability analysis have been performed. The
RITD-project concentrates on mission and applications achievable with the current
MetNet-type (i.e. “Mini-1” category) of lander, and on requirements posed by other type
Earth re-entry concepts.
2. Entry Angle Determination for Mini-1 – lander
For successful Earth landing, the suitable re-entry angle and velocity with specific descent
vehicle (DV) mass and heat flux parameters need to be determined. These key parameters in
determining the Earth re-entry for DV are:
qmax (kW/m2): maximal specific heat flux,
Q (MJ/m2): specific integral heat flux to DV front shield,
m (kg): descent vehicle (DV) mass,
V (m/s): re-entry velocity and
Î (deg.): flight-path angle at Earth re-entry
For Earth re-entry, the calculation results in the optimal value of entry velocity for
MetNet (“Mini-1” category) -type lander, with mass of 22kg, being VSOL = 5268 m/s. Using
the basic pre-defined parameters for MetNet-type of lander in Earth atmosphere, we get the
optimal angle of Î = -3.06 degrees for Earth re-entry.
3. Payload Mass for Earth Entry DV
One of the key elements in Earth entry lander is the amount of available payload mass.
The payload mass depends on, e.g., the lander size, landing type (soil or water), heat shield
durability and additional landing gear.
The payload mass will have an impact to the center of gravity of the lander.
The payload with a “low” CoG (compared the the lander structure) has a larger
tolerance than the payload with “high” CoG. In cases where payload CoG causes
instability, the extra balance mass can be used to adjust CoG. This balance mass will
reduce the available payload mass. A major limitation for payload mass is the heat
shielding.
Acknowledgements
The research leading to these results has received funding from the European
Community’s Seventh Framework Programme (FP7/2007-2013) under grant agreement n°
263255.
References
[1] http://ritd.fmi.fi |
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