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Cost-Effective 3-Arm LISA-Like Space-Based Gravitational-Wave Observatory Mission

The SGO-Mid mission aims to develop a low-cost, three-arm gravitational-wave observatory designed for optimal performance and minimal risk. Key features include a reduced arm length of 1 Gm, a two-year mission duration, and a starting distance from Earth significantly less than previous models. The configuration allows for instantaneous polarization data collection and noise estimation, thanks to Sagnac effects. It supports redundancy, tolerating the loss of two links while maintaining scientific output. This mission promises to yield valuable insights into gravitational waves while ensuring budget efficiency.

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Cost-Effective 3-Arm LISA-Like Space-Based Gravitational-Wave Observatory Mission

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  1. Space-based Gravitational-wave Observatory(SGO)-Mid MinimumCost 3-arm/6-link LISA-like Mission Presented by Jeff Livas for the SGO Core Team

  2. Concept Description • Rationale for the configuration • Try to find lowest cost 6 links for LISA-like mission • Benefits of 6 links • Instantaneous/continuous polarization information • Sagnac enables noise estimation • Redundancy: tolerates loss of up to 2 links while still doing science • SGO-Mid differs from LISA by: • Arm length reduced from 5 to 1 Gm • Mission length reduced from 5 to 2 years. • Starting distance from Earth reduced by ~2.5X to a 9-degree trailing orbit. • Telescope diameter reduced from 40 to 25 cm • Laser power out of telescope reduced from 1.2 to 0.7 W (end of life). • In-field guiding instead of articulating optical assembly

  3. SGO-Mid Science

  4. SGO-Mid Science • Covers decadal-endorsed science • Generally detects fewer sources of all types • Main science risk is shortened mission duration • Event rates uncertain • Science return lower if event rates are lower

  5. Parameter Estimation

  6. SGO-Mid Configuration • Small telescope means optical bench sets height • In-field guiding simplifies optical assembly • Launch stack fits easily into a Falcoln 9 fairing • drift away orbit requires little fuel, simplifying prop module Low High Mid

  7. Scientific Payload

  8. Orbits/trajectory • 2 year drift-away • ~ 6 deg/year drift rate starting at 9 degrees • 2 year end of mission similar to nominal SGO-high orbital station • Communications requirements similar to SGO-high • Stable constellation • DL/L ~0.06 • Da~ 0.6 • Dv~ 2 m/s • 18 month trajectory • Optimized DV ~ 130 m/s (each)

  9. Cost Estimate • Cost model includes • Non-recurring Engineering costs • “learning curve” for multiple copies • 20% additional management reserves • Scaling with mission lifetime • Scaling rates for NRE, learning curve based on • Spacecraft/Vehicle-Level Cost Model • NASA/Air Force Cost Model

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