Emerging Capabilities for the Next Mars Orbiter

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Presentation transcript:

Emerging Capabilities for the Next Mars Orbiter Presented to MEPAG February 24, 2015 Charles Whetsel, Rich Zurek, Rob Lock Pre-Decisional: For planning and discussion purposes only.

Next Orbiter Can Support Many Potential Next Steps Now through 2020 Early ‘20’s Mid-’20’s Late ‘20’s through ‘30’s Accessing Special Resources & Regions Mars 2020 Next Mars Orbiter (Options: Remote Sensing, Relay/Comm, Rendezvous, Round Trip EP) Other Objectives + Emplacement of Infrastructure for Human Missions Round-trip Missions (Return from Mars to Earth, Sample Retrieval) Can be a Long-Duration Asset servicing Multiple Stakeholder interests Precursors Advancing Exploration Capabilities Multiple Pathways provide flexibility to adapt to new knowledge and partnerships Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Introduction - Some Context MRO launched in August 2005 – 9 years in Mars orbit First to use Atlas V family of launch vehicles Highest deep-space planetary mission data rates and volumes, to date Largest and most capable payload to Mars, to date Provided <1m resolution reconnaissance , multispectral imaging, atmospheric and regional observing, radar sounding and relay telecommunications Successful Ka-band and optical navigation demonstrations The intervening decade has brought significant new capabilities Larger and more diverse launch vehicles Commercial space industry and NASA continue to develop and demonstrate Solar Electric Propulsion (SEP) components that support a broad range of missions Commercial space has developed large lightweight solar arrays for TeleSats and for SEP – NASA has developed even larger arrays Improved instruments and detectors, optical communications, improved radio communications components are also available for future Mars missions Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

What might a Mars orbiter offer in the early 2020s? Have potential for multi-use to support diverse agency objectives Mission-class between Discovery and New Frontiers Improved capabilities versus previous orbiter missions High-power, High-Isp Solar Electric Propulsion (SEP) Thrusters High-power, Lightweight Solar Arrays Very High Data Rate Telecommunications (Ka-band and Optical) (All these have flown or have been qualified to fly since MRO) Using these new capabilities, an orbiter could provide Significantly more payload mass and data return Abundant electrical power to payloads Increased variety of access to orbits at Mars On-orbit rendezvous Using Electric Propulsion – Mass, Power, Orbit barriers are lowered Capabilities of the mission can be set based on what MEP and our Partners are willing to financially support Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Capability and Mission Range for 2022 Orbiters Exploration SEP NASA Components 1000 – 2000 kg Bus 200 – 800 kg P/L >5 kW for P/L Commercial SEP COTS Components 500 – 1000 kg Bus 100 – 200 kg P/L >2 kW for P/L Multi-objective Orbiter Advanced Telecom and SEP Recon/Resource/Rendezvous (new class) Telecom/Recon/Resource Rendezvous Orbiter (MRO upgrade) Telecom/Recon+ Orbiter (MRO-class) Telecom/Recon Replacement Orbiter (MRO-lite) All missions benefit from SEP orbits and payload power Bi-Prop Telecom/Recon Orbiter Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Benefits of SEP 1: Mars Orbit Destinations Mission Delta V Usage (km/s) Outbound to Mars Earth-Mars Heliocentric 4.0 6.6 km/s Spiral to Areostationary 0.6 Spiral to Phobos 0.7 Spiral to 320km, 0 deg 1.3 Additional ∆V for inclination change from Phobos altitude to 320 km at inclination of: 30 deg 1.2 Pick one 45 deg 2.1 70 deg 3.3 90 deg Return to Earth-Moon System Spiral Out from Mars 2.6 6.8 km/s Mars-Earth Heliocentric 4.2 Mission ∆V range (km/s) 13 - 17 SEP interplanetary delivery to any inclination Spirals start above 200,000 km altitude Fuel cost for inclination change is cheaper when farther away MAV Rendezvous &/or Science-Relay Orbit 400 km, i = 45°- 90° Phobos Orbit 6,000 km, i = 1.1° Deimos Orbit 20,000 km, i = 0.9° Areostationary Orbit 17,000 km, i = 0° Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Benefits of SEP 2: Excess Power for Payloads SEP systems to Mars require 7-30 kW (at 1 AU) Roughly, for operations at Mars, divide the nominal power by 3 and subtract 1 kW for orbiter bus needs E.g., A 15 kW SEP system allows 4kW of P/L power in Mars orbit Several instruments and components might benefit from extra power Active Instruments e.g, Radar, Lidar Telecommunications e.g., Optical lasers and RF amplifiers ?? Creative thinking might open interesting opportunities Issues For high power systems, heat rejection is more challenging Batteries can get bulky for eclipse operations Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Example Strategic Orbiter Characteristics ARM-based Orbiter Engine ARMi # Active 1 # Spares Throughput Used 30% LV F9 C3 11 Array Type ROSA BoL Power (kW) 29 P/L power at Mars 8 Launch Mass (kg) 2513 Dry Bus Mass 1183 Mass for ALL payloads 300 Propellant 1029 Total Duration (Yr) 9.1 Outbound 1.6 At Mars 5.4* Inbound 2.1 This is one example to show feasibility and capability Many many orbiter variations possible Launch vehicle Thruster types/number Array types Telecom configuration Payload placement Bus/tank configuration Can trade payload mass and return fuel for plane change ∆V at Mars * Assumes Lander mission two opportunities later with one Mars year mission, then return to Earth Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Mission Context Notional Timeline and Launch Dates ‘22 2023 2024 2025 2026 2027 2028 2029 2030 2031 Landers Orbiter Launch (2022) Orbiter Mission Duration (9 + yrs) Earth to Mars > 1 year Spiral In < 1 year Science and Relay in Low Mars Orbit, (>5 Years) Transition to new science orbit Optional Science at Martian Moons Earth Launch Spiral In Science and Relay Spiral Orbit Adjust Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Pre-Decisional: For planning and discussion purposes only. Further Questions Discussions of questions and concerns is encouraged Suggestions for how to make use of Mars orbiter resources and opportunities are welcome Please Contact your favorite Mars Program scientist and/or Rob Lock robert.e.lock@jpl.nasa.gov (818) 393-2525 Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Pre-Decisional: For planning and discussion purposes only. Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.

Potential Launch Vehicles Current orbiter concepts fit on smaller Atlas V and Falcon-9 launch vehicles SEP missions can use any C3 and still reach Mars Reducing C3 increases launch and arrival mass but takes more time in cruise Launch mass does not vary significantly by launch opportunity Range of Reasonable Masses and Launch Energies for a 2022 Orbiter mission F Example ARM-based Orbiter F MRO Atlas V 411 Falcon-9 Feb 24, 2015 Pre-Decisional: For planning and discussion purposes only.