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Decision Package #1 Decision Package #1: Conjunction Class Missions (Long Surface Stays) vs. Opposition Class Missions (Short Surface Stays) July 23, 2007 1 This Page Intentionally Left Blank 2 Topic Outline Problem Statement • Mission Planning Fundamentals • Trajectory Implications • Mission Planning Considerations Typical Short-Stay Mission Overview Typical Long-Stay Mission Overview Special Considerations • Goals and Objectives • Human Health and Performance • Flight and Surface Systems Figures of Merit Assessments • Performance • Risk • Cost Recommendation July 23, 2007 Decision Package #1: Long / Short 3 Top-level Trade Tree This is the first of three decision packages that addresses the two primary mission types for human exploration of Mars: Long surface stays versus short surface stays. Human missions to Mars are classified into these two primary approaches as governed by orbital mechanics which are described in this package. The attributes of each mission approach, along with the key characteristics and distinguishing features are provided. The branches of the trade tree considered in this trade are those numbered 10, 12, 34, and 36 in the trade tree. These branches were chosen because experience has shown that the cases chosen represent typical approaches and the trends will be similar for the other branches of the trade tree. July 23, 2007 Decision Package #1: Long / Short 4 nn19881988 “Mars“Mars Expedition”Expedition” oo 19891989 “Mars“Mars Evolution”Evolution” Top-level Trade Tree pp 19901990 “90-Day“90-Day Study”Study” qq 19911991 “Synthesis“Synthesis Group”Group” r 1995 “DRM 1” r 1995 “DRM 1” Human Exploration s 1997 “DRM 3” s 1997 “DRM 3” Of Mars tt 19981998 “DRM“DRM 4”4” uu 19991999 “Dual“Dual Landers”Landers” vv 19891989 Zubrin,Zubrin, et.al*et.al* Decision Package 1 ww 1994-991994-99 Borowski,Borowski, et.alet.al Long vs Short cc 20002000 SERTSERT (SSP)(SSP) dd 20022002 NEPNEP Art.Art. GravityGravity Conjunction Class Opposition Class Special Case ee 20012001 DPT/NEXTDPT/NEXT Long Surface Stay Short Surface Stay 1-year Round-trip Type M1M1 20052005 MSFCMSFC MEPTMEPT Mission M2M2 20052005 MSFCMSFC NTPNTP MSAMSA e Pre-Deploy All-up Pre-Deploy All-up Cargo Deployment Aerocapture Propulsive Aerocapture Propulsive Aerocapture Propulsive Aerocapture Propulsive Method Mars Capture Mars No No No No No No No No ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU ISRU Propellant Mars Ascent NTR NTR NTR NTR NTR NTR NTR NTR NTR NTR NTR NTR NTR NTR NTR NTR in Phase 1) Phase in Electric Electric Electric Electric Electric Electric Electric Electric Electric Electric Electric Electric Electric Electric Electric Electric (no hybrids Propulsion Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Chemical Interplanetary 1 2 3 4 5 6 7 89 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 M2 M2 r vu owwM2 cdp nq s M1 M1 M1 M2 M2 t NTR- Nuclear Thermal Rocket 5 July 23, 2007 Decision Package #1: Long / Short Electric= Solar or Nuclear Electric Propulsion Key Findings Recommendation Based on the analysis and deliberations conducted to date, the team has concluded that the best mission approach are the Conjunction Class missions which provide the opportunity for long surface stays on Mars. These factors will be discussed further in this package, but are provided as a summary here. Provides greater mission return Conjunction class missions enable long stays at Mars which provide the opportunity to maximize mission return. Given that the objective is to explore the surface of Mars, providing the crew with the time and tools necessary to explore the surface at Mars at ever greater distances from the landing site is essential. The long-stay missions provide one to two orders of magnitude greater mission return in terms of expected crew-time on the surface. The value of return is also enhanced by the ability to explore at great distances, to greater depth, and with time to collaborate with scientists back on Earth. Provides greater mission flexibility Conjunction class missions enhance mission flexibility by providing for the necessary operational tasks that must be conducted such as vehicle checkout, orbital phasing, plane changes, etc. In addition, the long-stay at Mars provides ample time to account for environmental anomalies such as dust storms. Lastly, providing time for the crew to acclimate to the gravity conditions on Mars after an extended zero-gravity transit is necessary, and thus enhanced by the long stay feature of conjunction missions. Enables transits which are within experience base Transit times to and from Mars are on the order of 180-210 days which is within human mission experience base Requires similar/lower total initial mass Total mission mass for the long stay missions are similar or lower than the short stay missions.. Enables equal and consistent transportation vehicles Since the propulsive energy required varies less, it is much easier to design vehicles to operate during each mission opportunity. In addition, the transportation vehicles are very similar for both cargo and crew missions, unlike the short stay variants. Provides better crew safety The overall probability of loss of crew is lower for the long stay missions as compared to the short stay missions even when accounting for the reliability aspects of the longer total mission duration. July 23, 2007 Decision Package #1: Long / Short 6 Key Findings The Long Stay mission is the preferred approach: • Provides greater mission return (order of magnitude) • Provides greater mission flexibility • Enables transits which are within experience base • Requires similar/lower total initial mass • Enables equal and consistent transportation vehicles • Provide better crew safety While accounting for: • Slightly greater cost for additional systems, and • Slightly greater mission risk due to longer system operational time July 23, 2007 Decision Package #1: Long / Short 7 Mars Trajectory Classes Earth-Mars Mission Planning Round-trip missions to Mars and back are, in effect, a double rendezvous problem. The outbound trajectory must be established while considering the position of Earth at the end of the mission. Upon arrival at Mars the Earth is in a relatively unfavorable alignment (phase angle) for an energy efficient return. This unfavorable alignment results in two distinct classes of round-trip Mars missions: Opposition class missions, which are also commonly referred to as short-stay missions, and Conjunction class missions, referred to as long-stay missions. Practical considerations, such as total propulsive requirements, mission duration, surface objectives, and human health considerations must be considered in the mission design process when choosing between these mission classes.. The period of time necessary for the phase angle between Earth and Mars to repeat itself varies. This variation is referred to as the Synodic Cycle. The Synodic Cycle, or mission repetition rate for identical Earth-Mars phasing, and therefore launch opportunities for similar mission classes, is on the order of every 26 months. The mission characteristics such as mission duration, trip times, and propulsive requirements vary to due to the eccentricity of Mars’ orbit. Opposition Class: Short-Stay Missions Short-stay missions consists of short stay-times (typically 30 sols) and round-trip mission times ranging from 550- 660 days. This is often referred to as an opposition-class mission, although the exploration community has adopted the more descriptive terminology “short-stay” mission. Trajectory profiles for typical short-stay missions are shown. This class of mission has high propulsive requirements. Short-stay missions always have one short transit leg, either outbound or inbound, and one long transit leg, the latter requiring close passage by the sun (0.7 AU or less). After arrival at Mars, rather than waiting for a near-optimum return alignment, the spacecraft initiates the return after a brief stay and the return leg cuts well inside the orbit of the Earth to make up for the “negative” alignment of the planets that existed at Mars departure. Distinguishing characteristics of the short-stay mission are: 1) short-stay at Mars, 2) medium total mission duration, 3) perihelion passage inside the orbit of Venus on either the outbound or inbound legs, and 4) large total energy (propulsion) requirements. Conjunction Class: Long Stay Missions The second Mars mission class is typified by long-duration stay-times (as much as 550 sols) and long total round- trip times (approximately 900 days). This mission type is often referred to as conjunction-class, although the exploration community has adopted the more descriptive terminology “long-stay” mission. These missions represent the global minimum-energy solutions for a given launch opportunity. Unlike the short-stay mission approach, instead of departing Mars on a non-optimal return trajectory, time is spent at Mars waiting for more optimal alignment for lower energy return. Distinguishing characteristics of the long-stay mission include: 1) long total mission durations, 2) long-stays at Mars, 3) relatively little energy change between opportunities, 4) bounding of both transfer arcs by the orbits of Earth and Mars (closest perihelion passage of 1 AU), and 5) relatively short transits to and from Mars (less than 200 days). July 23, 2007 Decision Package #1: Long
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