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Mission Overview Perseverance rover to a hyperbolic escape orbit collect and store samples of selected rock and MISSION where it will begin a 7-month journey to Mars. soil, and prepare for future human missions. will occur from Space Launch Complex-41 Perseverance rover will carry seven primary at Cape Canaveral Air Force Station, Florida. instruments: MASTCAM-Z, Mars Environmental Dynamics Analyzer (MEDA), Mars Oxygen ISRU OVERVIEW The Mars 2020 mission with its Perseverance Experiment (MOXIE), Planetary Instrument for rover is part of NASA’s Mars Exploration Pro- X-ray Lithochemistry (PIXL), Radar Imager for gram, a long-term efort of robotic exploration Mars’ Subsurface Experiment (RIMFAX), Scan- of the red planet. A team from the Jet Propulsion ning Habitable Environments with Raman & Laboratory (JPL) built the spacecraft. The Perse- Luminescence for Organics & Chemicals (SHER- verance rover will seek signs of ancient life and LOC), and SuperCam. Also, the Mars helicopter, collect rock and soil samples for possible return Ingenuity, will ride to Mars attached to the belly of the rover. The helicopter is a technology demonstration to test the first powered flight on Mars. Mars 2020 and the Perseverance rover are scheduled to arrive at Mars in February 2021. The mission duration is at least one Mars year (about One of the most powerful rockets 687 Earth days). ULA and its heritage vehicles ATLAS V in the Atlas V fleet, the 541 have launched every U.S. led mission to Mars. configuration, with four solid rocket Mars 2020 will continue the legacy started by boosters, provides the optimum earlier missions to provide NASA and JPL with performance to precisely deliver a crucial knowledge and understanding of the red planet. range of mission types. In addition Image Courtesy of NASA to three national security and two weather satellites, an Atlas V 541 Payload Fairing (PLF) rocket launched NASA’s Curiosity The spacecraft is encapsulated in a 5-m (17-ft) Mars 2020 Spacecraft rover on its 10-month, 354 million- diameter short payload fairing. The 5-m PLF mile journey to the surface of Mars. is a sandwich composite structure made with a vented aluminum-honeycomb core and graph- 5-m Payload ite-epoxy face sheets. The bisector (two-piece First Launch: Nov. 26, 2011 shell) PLF encapsulates both the Centaur and Fairing Launches to date: 6 the satellite. The vehicle’s height with the 5-m short PLF is approximately 60 m (197 ft). Performance to GTO: 8,290 kg (18,270 lb) Centaur Forward Performance to LEO-Reference: Load Reactor (CFLR) The Centaur second stage is 3 m (10 ft) in diame- 17,410 kg (38,400 lb) ter and 12.6 m (41.5 ft) in length. Its propellant tanks are pressure-stabilized and constructed of Centaur corrosion-resistant stainless steel. Centaur is a cryogenic vehicle, fueled with liquid hydrogen RL10C-1 Engine and liquid oxygen, powered by an RL10C-1 en- gine producing 101.9 kilo-Newtons (22,900 lb) of Boattail thrust. The cryogenic tanks are insulated with a combination of helium-purged blankets, radia- Centaur Interstage tion shields and spray-on foam insulation (SOFI). Adapter (CISA) The Centaur forward adapter (CFA) provides Booster Cylindrical With more than a century of structural mountings for the fault-tolerant avion- MISSION Interstage Adapter combined heritage, ULA is the world’s ics system and structural and electrical interfac- most experienced and reliable es with the spacecraft. SUCCESS launch service provider. ULA has successfully delivered more than 135 Booster The booster is 3.8 m (12.5 ft) in diameter and missions to orbit that provide Earth 32.4 m (106.5 ft) in length. The booster’s tanks observation capabilities, enable global are structurally rigid and constructed of isog- communications, unlock the mysteries rid aluminum barrels, spun-formed aluminum of our solar system and support life- domes and intertank skirts. Booster propulsion is saving technology. provided by the RD-180 engine system (a single engine with two thrust chambers). The RD-180 1 (Rocket Propellant-1 or highly purified Solid Rocket kerosene) and liquid oxygen and delivers 3.83 mega-Newtons (860,200 lb) of thrust at sea lev- Boosters el. Four solid rocket boosters (SRBs) generate the additional power required at liftof, each provid- PROFILE 8 7 6 5 Time Event (hr:min:sec) 1 Liftof (Thrust to Weight > 1) 00:00:01.1 2 SRB Jettison 00:01:49.3 3 PLF Jettison 00:03:27.6 6 4 Atlas Booster Engine Cutof (BECO) 00:04:22.1 5 Atlas Centaur Separation 00:04:28.1 7 4 6 Main Engine Start (MES1) 00:04:38.1 7 Main Engine Cutof (MECO1) 00:11:27.9 8 Main Engine Start (MES2) 00:44:59.5 9 Main Engine Cutof (MECO2) 00:52:50.1 10 Mars 2020 Separation 00:57:32.8 11 Start Blowdown 01:23:52.8 12 End of Mission 01:57:12.8 1 Booster 3 MARS 2020 Orbit at Separation Boattail C3: 14.49 (km^2/s^2) | Declination (J2000): 35.32 (deg) CISA Right Ascension (J2000): 13.93 (deg) CFLR Longitude (deg) 80 Centaur 2 60 1 Atlas Spaceflight 2 Operations Center (ASOC) 40 Launch Control Center & Payload Mission Director’s Center 5 Adapter 20 4 Spacecraft 2 Delta Operations Center 6 Ofline Vertical Integration (OVI): 0 7 Interstage Adapters, Centaur, Boatail, Base Module and Centaur -20 Forward Load Reactor Deck Payload Transporter Payload 3 Spacecraft Processing Facility -40 8 Fairing Halves Spacecraft Processing, Testing & Encapsulation 1 -60 4 Vertical Integration Facility Launch Vehicle /Spacecraft Groundtrack Mobile 3 Launch Vehicle Integration & -80 Launch Testing, Spacecraft Mate & Platform Crew Integrated Operations -135 -90 -45045 90 Access .
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