Abstract
Many concepts for future robotic Mars lander missions require landing heavier payloads than those landed to date. Mars lander architectures to date have relied on a parachute to help slow the lander; however, the effectiveness of a parachute in the thin Martian atmosphere is diminished with heavier payloads unless the diameter of the parachute is increased or it is deployed at a higher Mach number, both of which are significant technical challenges. In addition, the parachute can be successfully deployed only within a specific Mach number and dynamic pressure range. Targeting the entry trajectory to hit this “Mach-Q box” imposes constraints on the entry ballistic coefficient, limiting it to ~ 150-200 kg/m^2. Eliminating the parachute from the design requires descent engine ignition at supersonic speeds (Supersonic Retropropulsion, or SRP). SRP increases the propellant requirement, but also allows entry ballistic coefficients of ~600 kg/m^2 or more, with the consequence of significantly increased entry mass and landed payload mass.
| Original language | English (US) |
|---|---|
| Title of host publication | AAS/AIAA Astrodynamics Specialist Conference, 2018 |
| Editors | Puneet Singla, Ryan M. Weisman, Belinda G. Marchand, Brandon A. Jones |
| Publisher | Univelt Inc. |
| Pages | 643-657 |
| Number of pages | 15 |
| ISBN (Print) | 9780877036579 |
| State | Published - Jan 1 2018 |
| Event | AAS/AIAA Astrodynamics Specialist Conference, 2018 - Snowbird, United States Duration: Aug 19 2018 → Aug 23 2018 |
Publication series
| Name | Advances in the Astronautical Sciences |
|---|---|
| Volume | 167 |
| ISSN (Print) | 0065-3438 |
Conference
| Conference | AAS/AIAA Astrodynamics Specialist Conference, 2018 |
|---|---|
| Country | United States |
| City | Snowbird |
| Period | 8/19/18 → 8/23/18 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science
Cite this
Supersonic retropropulsion on robotic Mars landers : Selected design trades. / Wolf, Aron A.; Noyes, Connor; Strauss, William; Benito, Joel; Lobbia, Marcus; McCann, John; Nakazono, Barry; Putnam, Zachary R.; Lorenz, Christopher G.
AAS/AIAA Astrodynamics Specialist Conference, 2018. ed. / Puneet Singla; Ryan M. Weisman; Belinda G. Marchand; Brandon A. Jones. Univelt Inc., 2018. p. 643-657 (Advances in the Astronautical Sciences; Vol. 167).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Supersonic retropropulsion on robotic Mars landers
T2 - Selected design trades
AU - Wolf, Aron A.
AU - Noyes, Connor
AU - Strauss, William
AU - Benito, Joel
AU - Lobbia, Marcus
AU - McCann, John
AU - Nakazono, Barry
AU - Putnam, Zachary R.
AU - Lorenz, Christopher G.
PY - 2018/1/1
Y1 - 2018/1/1
N2 - Many concepts for future robotic Mars lander missions require landing heavier payloads than those landed to date. Mars lander architectures to date have relied on a parachute to help slow the lander; however, the effectiveness of a parachute in the thin Martian atmosphere is diminished with heavier payloads unless the diameter of the parachute is increased or it is deployed at a higher Mach number, both of which are significant technical challenges. In addition, the parachute can be successfully deployed only within a specific Mach number and dynamic pressure range. Targeting the entry trajectory to hit this “Mach-Q box” imposes constraints on the entry ballistic coefficient, limiting it to ~ 150-200 kg/m^2. Eliminating the parachute from the design requires descent engine ignition at supersonic speeds (Supersonic Retropropulsion, or SRP). SRP increases the propellant requirement, but also allows entry ballistic coefficients of ~600 kg/m^2 or more, with the consequence of significantly increased entry mass and landed payload mass.
AB - Many concepts for future robotic Mars lander missions require landing heavier payloads than those landed to date. Mars lander architectures to date have relied on a parachute to help slow the lander; however, the effectiveness of a parachute in the thin Martian atmosphere is diminished with heavier payloads unless the diameter of the parachute is increased or it is deployed at a higher Mach number, both of which are significant technical challenges. In addition, the parachute can be successfully deployed only within a specific Mach number and dynamic pressure range. Targeting the entry trajectory to hit this “Mach-Q box” imposes constraints on the entry ballistic coefficient, limiting it to ~ 150-200 kg/m^2. Eliminating the parachute from the design requires descent engine ignition at supersonic speeds (Supersonic Retropropulsion, or SRP). SRP increases the propellant requirement, but also allows entry ballistic coefficients of ~600 kg/m^2 or more, with the consequence of significantly increased entry mass and landed payload mass.
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M3 - Conference contribution
AN - SCOPUS:85069468559
SN - 9780877036579
T3 - Advances in the Astronautical Sciences
SP - 643
EP - 657
BT - AAS/AIAA Astrodynamics Specialist Conference, 2018
A2 - Singla, Puneet
A2 - Weisman, Ryan M.
A2 - Marchand, Belinda G.
A2 - Jones, Brandon A.
PB - Univelt Inc.
ER -