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Atul Kumar Week 7: March 1 st , 2007. Aerodynamics team member This week: Mars taxi ascent trajectory model Taxi capsule: Gmax and Drag. 1. Mars taxi trajectory visualization. First Phase GLOW = 44.3057 mt Thrust = 574.96 kN Burn time = 250 sec Mdot = 130.29 kg/sec
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Atul KumarWeek 7: March 1st , 2007 Aerodynamics team member This week: Mars taxi ascent trajectory model Taxi capsule: Gmax and Drag 1
Mars taxi trajectory visualization • First Phase • GLOW = 44.3057 mt • Thrust = 574.96 kN • Burn time = 250 sec • Mdot = 130.29 kg/sec • Altitude at periapsis = 131.82 km • Velocity at periapsis = 4.864 km/sec ra rp Vbo Author: Atul Kumar • Assumption • Mars atmosphere interface altitude 77.428 km - based on the density value at this altitude 2 03/01/2007 Atul Kumar Author: Atul Kumar
Mars taxi trajectory visualization Inner Elliptical Orbit specifications Equatorial radius of Mars = 3397 km Radius of periapsis, rp = 3528.821 km Radius of apoapsis, ra = 137056.05 km Semi major axis, a= 70292.438 km Eccentricity, e = 0.95 Total time taken to cover the first phase = 235.9 sec Time taken for one rotation = 6.54 Earth days rp ra Assumption - Launch takes place at a martian time such that radius at insertion is equal to radius of periapsis of the elliptical orbit, Ri= rp - Flight path angle is zero at that point 3 03/01/2007 03/01/2007 Atul Kumar Atul Kumar
Assumed Conical top surface S=29.014 m2 Cd=0.0112 ε+0.162 =0.45 ε- half vertex angle, for the cone 25.66 deg Max. Drag= 64.08kN at H=15.85km Gmax= 2.15 Taxi Capsule visualization drawing Project Aquarius website Author: Ben Jamison 4 03/01/2007 Atul Kumar
References • A Simplified for the Evaluation of ∆v of Ascent Trajectories Cervone, Angelo; Rapposelli, Emilio; D’Agostino Luca AIAA 2005-4507 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Tucson, Arizona, 10-13 July 2005 • Mars Atmosphere Model http://www.grc.nasa.gov/WWW/K-12/airplane/atmosmre.html 6 03/01/2007 Atul Kumar