According to prliminary report for NASA's Space Launch System and Multipurpose Crew Vehicle-2011, the challenges and developments in summary were-
NASA was required upgrade it's SLS so that lower versons hardware can be used for it's future missions to astroids and mars.According to expected capabilities as-
1. To 70-100 tons to lower earth orbit and 130 tons or more in further developments.
2.Able to lift MPCV
3.For supplying and supporting cargo and crew to ISS when needed.
Five heavy lift launch vehicle families were reviewed according to weighted figure of merit as follows-
1.Affordability-55%
2.Shedule-25%
3.Performence-10%
4.Programmatic-10%
By this 27.5-foot LOX/LH2/SSME HLV and 2Mlbf GG RP vehicles were highest rated across all of the FOMs
Current SLS vehicle design utilize to the maximum extent practicable assets from Space Shuttle Program and Ares Project. The Reference Vehicle Design is an in-line,
1.large-diameter liquid oxygen/liquid hydrogen (LOX/LH2) core stage with multiple liquid propulsion core stage SSME-derived engines, and two five segment solid rocket boosters.
2.The Upper Stage consists of a J-2X cryogenic Upper Stage with approximately
294 klbf thrust capability, initially lift approximately 100 tons to LEO, and be evolvable to 130 tons or more; 3. be able to lift an MPCV; and
4.be capable of serving as a backup system for supplying and supporting cargo and crew delivery requirements for the ISS.
The Requirements For MPCV are-
1. To serve as the primary crew vehicle for missions beyond LEO.
2.To conduct regular in-space operations.
3.Provide an alternative means of crew and cargo transportation to and from the ISS
4.Capability for efficient and timely evolution.
NASA’s designs for the beyond-LEO (formerly lunar) version of the Orion include the following basic capabilities and specifications – all of which were traceable to MPCV requirements
1.Crew size: 2 to 4
2.Crewed mission duration: 21.1 days
3.Velocity change capability: 5233 ft/s
4.Main engine thrust: 7,500 pounds
5.Pressurized volume: 690.6 cubic feet
6.Net habitable volume: 316 cubic feet
7.Skipped Entry Capability: Can traverse up to 4,800 nautical miles (nmi) from atmospheric entry interface to landing point from lunar return trajectories;
8.Landing: Water landing off California coast with a 5.4 nmi landing accuracy
9.EVA Capability: Via depressurization of the crew compartment
Based on the aforementioned minimum capability requirements listed in Section 3.1 of this report, NASA has concluded that--
Given the applicability of the current Orion work, NASA’s Reference Vehicle Design for MPCV is the beyond-LEO version of the current Orion. It must be emphasized for clarity that the MPCV design will be optimized for beyond-LEO exploration capability. Any contingency utilization as a backup-LEO crew vehicle will represent a highly inefficient vehicle usage.
It is not yet clear whether the Reference Vehicle Design fully meets the NASA Administrator’s three principles for development of any future systems for exploration -- namely that these systems must be affordable, sustainable, and realistic. Further work is required in assessing potential contract changes, oversight simplifications and other cost-saving measures to understand the degree to which this development meets these principles. NASA recognizes that new affordability strategies must be implemented in the design and Project management process to meet a constrained budget environment
.http://www.nasa.gov/pdf/510449main_SLS_MPCV_90-day_Report.pdf
MPCV was announced by NASA on 24 May 2011,and will launch a delta IV heavy rocket in july 2013.
NASA had hoped to follow this (now obsolete) schedule in development of the Orion
NASA was required upgrade it's SLS so that lower versons hardware can be used for it's future missions to astroids and mars.According to expected capabilities as-
1. To 70-100 tons to lower earth orbit and 130 tons or more in further developments.
2.Able to lift MPCV
3.For supplying and supporting cargo and crew to ISS when needed.
Five heavy lift launch vehicle families were reviewed according to weighted figure of merit as follows-
1.Affordability-55%
2.Shedule-25%
3.Performence-10%
4.Programmatic-10%
By this 27.5-foot LOX/LH2/SSME HLV and 2Mlbf GG RP vehicles were highest rated across all of the FOMs
Current SLS vehicle design utilize to the maximum extent practicable assets from Space Shuttle Program and Ares Project. The Reference Vehicle Design is an in-line,
1.large-diameter liquid oxygen/liquid hydrogen (LOX/LH2) core stage with multiple liquid propulsion core stage SSME-derived engines, and two five segment solid rocket boosters.
2.The Upper Stage consists of a J-2X cryogenic Upper Stage with approximately
294 klbf thrust capability, initially lift approximately 100 tons to LEO, and be evolvable to 130 tons or more; 3. be able to lift an MPCV; and
4.be capable of serving as a backup system for supplying and supporting cargo and crew delivery requirements for the ISS.
The Requirements For MPCV are-
1. To serve as the primary crew vehicle for missions beyond LEO.
2.To conduct regular in-space operations.
3.Provide an alternative means of crew and cargo transportation to and from the ISS
4.Capability for efficient and timely evolution.
NASA’s designs for the beyond-LEO (formerly lunar) version of the Orion include the following basic capabilities and specifications – all of which were traceable to MPCV requirements
1.Crew size: 2 to 4
2.Crewed mission duration: 21.1 days
3.Velocity change capability: 5233 ft/s
4.Main engine thrust: 7,500 pounds
5.Pressurized volume: 690.6 cubic feet
6.Net habitable volume: 316 cubic feet
7.Skipped Entry Capability: Can traverse up to 4,800 nautical miles (nmi) from atmospheric entry interface to landing point from lunar return trajectories;
8.Landing: Water landing off California coast with a 5.4 nmi landing accuracy
9.EVA Capability: Via depressurization of the crew compartment
Based on the aforementioned minimum capability requirements listed in Section 3.1 of this report, NASA has concluded that--
Given the applicability of the current Orion work, NASA’s Reference Vehicle Design for MPCV is the beyond-LEO version of the current Orion. It must be emphasized for clarity that the MPCV design will be optimized for beyond-LEO exploration capability. Any contingency utilization as a backup-LEO crew vehicle will represent a highly inefficient vehicle usage.
It is not yet clear whether the Reference Vehicle Design fully meets the NASA Administrator’s three principles for development of any future systems for exploration -- namely that these systems must be affordable, sustainable, and realistic. Further work is required in assessing potential contract changes, oversight simplifications and other cost-saving measures to understand the degree to which this development meets these principles. NASA recognizes that new affordability strategies must be implemented in the design and Project management process to meet a constrained budget environment
.http://www.nasa.gov/pdf/510449main_SLS_MPCV_90-day_Report.pdf
MPCV was announced by NASA on 24 May 2011,and will launch a delta IV heavy rocket in july 2013.
NASA had hoped to follow this (now obsolete) schedule in development of the Orion
- 2006–2007 — Engineering review of selected design
- May 6, 2010 — PA-1 (Pad Abort-1) unmanned pad abort test
- 2009 (Sep) — AA-1 (Ascent Abort-1) unmanned ascent abort test.
- 2010 (Spring) — PA-2 unmanned pad abort test
- 2010 (August) — AA-2 unmanned ascent abort test
- 2011 (February) — AA-3 unmanned ascent abort test (low-altitude tumble test)
- 2012 (September) — Ares I-Y unmanned ascent abort test (high altitude)
- 2014 — First unmanned flight of Orion in Earth orbit
- 2016 — First manned flight of Orion in Earth orbit.
- 2015–2018 — First unmanned flight of Altair.
- 2016–2018 First manned flight of Altair.
- 2019 First manned lunar landing with Orion/Altair system.
- 2020 Review of Mars missions
- 2031 The Mission to Mars has tentative dates
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