James goppert week 6 february 22 th 2007
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James Goppert Week 6: February 22 th , 2007. Aerodynamics: Reentry Optimization Dynamics and Control: Communication Satellite Orbits. Taxi Capsule Vehicle Reentry. Assumptions Delta V from HMO: 500 [m/s] TCV Total Mass: 30 [mt] (after Delta V burn from HMO) Landing close to equator

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James goppert week 6 february 22 th 2007

James GoppertWeek 6: February 22th, 2007

Aerodynamics: Reentry Optimization

Dynamics and Control: Communication Satellite Orbits

Taxi Capsule Vehicle Reentry

Goppert, 1


Taxi capsule vehicle reentry

Assumptions

Delta V from HMO: 500 [m/s]

TCV Total Mass: 30 [mt] (after Delta V burn from HMO)

Landing close to equator

Landing Speed

Actual: 4.78 [m/s]

Maximum : 6.7 [m/s] (15 mph)

Propellant

2.85 [mt]

Rocket Equation Prediction: 2.808 [mt] (Jamison)

Taxi Capsule Vehicle Reentry

Goppert, 2


Taxi capsule vehicle reentry1

Constraints

Max g load: 12g’s

Hover

Altitude: 300 [m]

Time: 60 [s]

Parachutes

1 High Mach Drogue

2 Low Mach Drogue

3 Main Chutes

Taxi Capsule Vehicle Reentry

Max g Load

Main

Drogue 1

Thrust Ignition

Drogue 2

Goppert, 3


Backup slides

Backup Slides

James GoppertWeek 4: February 22th, 2007

Goppert, 4


Landing phase
Landing Phase

Goppert, 5


Trajectory
Trajectory

Goppert, 6


Flight parameters
Flight Parameters

Goppert, 7


Position
Position

Goppert, 8


Parachute parameters
Parachute Parameters

  • First Drogue

    • Deployment Mach: 30

    • Diameter: 1 [m]

    • Number: 1

  • Second Drogue

    • Deployment Mach: 10

    • Diameter: 8 [m]

    • Number: 2

  • Main

    • Deployment Mach: 3

    • Diameter: 22 [m]

    • Number: 3

Goppert, 9


Eom s
EOM’s

  • inertial position derivative

    • i_P_cmo_i = C_ib*V_cme_b + OM_ei_i*P_cmo_i

  • body velocity derivative

    • b_Vcme_b = (1/m)*F_at_b - (OM_bi_b + OM_ei_b)*V_cme_b + C_bi*g_i

  • body angular velocity derivative

    • b_O_bi_b = J_b_inverse*(M_at_b - OM_bi_b*J_b*O_bi_b)

Goppert, 10


Landing conditional state controller
Landing Conditional State Controller

  • Gains

    • hover p controller gain: k_th = 8e2;

    • landing gain k_ln = 1;

    • velocity p controller gain k_tv = 2.1e4;

      if t_hover==0

      F_t_b = [0;0;0]

      elseif (t-t_hover)<t_hover_req

      F_t_b = k_th*[h_hover-h;0;0]-...

      k_tv*V_cme_b

      else

      F_t_b = k_ln*[0-h;0;0]-...

      k_tv*V_cme_b

      end

Goppert, 11


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