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3D-Plots

Junichi (Jun) Kanehara 03/06/2008 Trajectory The Winner of the Balloon, 5[kg] case (LB-HA-DA-DA_v125) & New Version of Trajectory 3-D Plots. 3D-Plots. Payload Mass= 5.0 [kg] GLOW= 6,295 [kg] eccentricity: 0.0025 periapsis : 773.14 [km] apoapsis : 809.57 [km] (from the surface of the Earth)

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3D-Plots

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  1. Junichi (Jun) Kanehara03/06/2008TrajectoryThe Winner of the Balloon, 5[kg] case(LB-HA-DA-DA_v125) &New Version of Trajectory 3-D Plots AAE 450 Spring 2008

  2. 3D-Plots • Payload Mass= 5.0 [kg] • GLOW= 6,295 [kg] • eccentricity: 0.0025 • periapsis: 773.14 [km] • apoapsis: 809.57 [km](from the surface of the Earth) • Max Acceleration: 5.22 G • deltaV Thrust-total : 11,853 [m/s] • deltaV required: 9,354 [m/s] Plots generated by the version 2.0 of “AAE450_Trajectory_Plots.m” modified by Jun Kanehara AAE 450 Spring 2008 Trajectory

  3. June Solstice Plots generated by the version 2.0 of “AAE450_Trajectory_Plots.m” modified by Jun Kanehara AAE 450 Spring 2008 Trajectory

  4. DecemberSolstice Plots generated by the version 2.0 of “AAE450_Trajectory_Plots.m” modified by Jun Kanehara AAE 450 Spring 2008 Trajectory

  5. Steering Law AAE 450 Spring 2008

  6. Model Name: LB-HA-DA-DA Delta V = 11,313 Delta V Percentages = [ 0.400 0.350 ] Inert Mass = [ 903.020 277.097 17.785 ] Stage 1 Prop Mass = 4,122.85 [kg] Inert Mass = 842.9585 [kg] Engine Mass = 193.49 [kg] Thrust (vac) = 75,073.2 [N] Burn Time = 174.9 [s] Mass Flow Rate = 23.571 [kg/s] Exit Area = 1.198 [m^2] Exit Pressure = 2,821.167 [Pa] Length = 7.0718 [m] Diameter = 1.839 [m] Stage 2 Prop Mass = 1,009.33 [kg] Inert Mass = 261.1954 [kg] Engine Mass = 75.72 [kg] Thrust (vac) = 15,256.9 [N] Burn Time = 213.0 [s] Mass Flow Rate = 4.739 [kg/s] Exit Area = 0.070 [m^2] Exit Pressure = 11,453.660 [Pa] Length = 2.1921 [m] Diameter = 0.817 [m] Stage 3 Prop Mass = 38.37 [kg] Inert Mass = 15.0986 [kg] Engine Mass = 8.56 [kg] Thrust (vac) = 692.4 [N] Burn Time = 178.4 [s] Mass Flow Rate = 0.215 [kg/s] Exit Area = 0.003 [m^2] Exit Pressure = 11,453.660 [Pa] Length = 1.0025 [m] Diameter = 0.275 [m] AAE 450 Spring 2008 Trajectory

  7. Case ID: LB_HA_DA_DA_v125.txt Orbital Parameters Period: 6038.7878 [s] Semi-major axis: 7167.36 [km] eccentricity: 0.0025 periapsis: 773.14 [km] apoapsis: 809.57 [km] Linear Tangent Steering Parameters: a1 = -0.16117 b1 = 28.6363 a2 = -0.00502483 b2 = 1.32415 a3 = 2.86231e-019 b3 = -0.624869 Flight Path Angle = 0.1 [deg]. at t=0[s]: Altitude: h=30000 [m] (Initial Condition) Radial (Vertical) Speed: Vr=0 [m/s] Thrust 1st stage: 75.073 [kN] 2nd stage: 15.257 [kN] 3rd stage: 0.692 [kN] Max Acceleration Max a @1st Stage= 28.5 [m/s^2] Max a @1st Stage= 2.90 G Max a @2nd Stage= 51.2 [m/s^2] Max a @2nd Stage= 5.22 G Max a @3rd Stage= 39.0 [m/s^2] Max a @3rd Stage= 3.97 G Max a @Coasting Stage= 3.8 [m/s^2] Max a @Coasting Stage= 0.38 G AAE 450 Spring 2008 Trajectory

  8. Burn Times 1st Stage: 175[s] (first 10.00 [s] is vertical flight) 2nd Stage: 212.96[s] 3rd Stage: 178.40[s] Times at the end of each stage End of first stage: 174.00[s] End of second stage: 386.00[s] End of third stage: 564.00[s] Constant Mass Flow Rates 1st Stage: 23.571[kg/s] 2nd Stage: 4.739[kg/s] 3rd Stage: 0.215[kg/s] Constant Exit Pressures 1st Stage: 2.82[kPa] 2nd Stage: 11.45[kPa] 3rd Stage: 11.45[kPa] Altitudes at the end of the vertical part of flight: 30,112.44[m] at t= 0 [s]: 30.00[km] at the end of the first stage: 131.57[km] at the end of the second stage: 560.08[km] at the end of the third stage: 801.62[km] from AAE450_Delta_V.m Delta_V_Thrust_1st= 3486 [m/s] (29.4 %) Delta_V_Thrust_2nd= 4775 [m/s] (40.3 %) Delta_V_Thrust_3rd= 3592 [m/s] (30.3 %) Delta_V_Thrust_Total (what we get)= 11,853 [m/s] Delta_V_Leo= 7,727 [m/s] Delta_V_Grav= 2,034 [m/s] DeltaV_drag= 4 [m/s] Delta_V_Earth_assist= 411 [m/s] Delta_V_Total (what we need)= 9,354 [m/s] Delta V required to circularize: 568 [m/s] AAE 450 Spring 2008 Trajectory

  9. Current Design: LB-HA-DA-DA_v125 Balloon ICs Aircraft ICs with Vertical Vi r_dot_i = 59.72 [m/s] hi = 15,000 [m] r_dot_i = 0.0 [m/s]hi = 30,000 [m] Delta_V_Leo= 7,727 [m/s]Delta_V_Grav= 2,084 [m/s]DeltaV_drag= 21 [m/s]Delta_V_Earth_assist= 410 [m/s]Delta_V_Total (w/o circ) = 9,422 [m/s]Delta V required to circularize= 546 [m/s]Delta_V_Total_ (w/ circ) = 9,968 [m/s] e: 0.0073rp: 655.85 [km] ra: 759.40 [km] Delta_V_Leo= 7,727 [m/s]Delta_V_Grav= 2,034 [m/s]DeltaV_drag= 4 [m/s]Delta_V_Earth_assist= 411 [m/s]Delta_V_Total (w/o circ) = 9,354 [m/s]Delta V required to circularize= 568 [m/s]Delta_V_Total_ (w/ circ) = 9,922 [m/s] e: 0.0025rp: 773.14 [km]ra: 809.57 [km] Delta_V_savings = 46 [m/s] AAE 450 Spring 2008 Trajectory

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