Dual deployment recovery will be used. Figure : The Mission Profile Chart includes the flight sequences for both stages and is described with more detail below Altitude Velocity Triggering Triggering Event Time [s] [ft] [mph] Condition Device Launch 0.0 0 0 Ready to launch Launch 1 Control Separation 0.7 75 125 Booster burnout Flight (negative computer 2 acceleration) Sustainer burn 0.8 1.5 85 - 400 125 - Stage 2 ignition Flight – 3 490 delay elapses computer (timer) Sustainer 22.0 5168 0 Apogee Deployment 4 altimeter (MAWD) Booster apogee, 11.0 720 0 Apogee Deployment main deployment altimeter (MAWD) Booster 76.0 0 0 - - touchdown -60 Descent Drogue - 5 drogue 500 deployment Main 64 -13 500ft reached Deployment 6 altimeter (MAWD) Sustainer 88 0 0 - - 7 touchdown Table : Flight events, including time and altitude of each event, condition that trigger an event and a device that executes the action associated with the event. Removable shear pins will be used for both the main parachute compartment and the drogue parachute compartment. We shall use removable nylon shear pins of sufficient strength to prevent premature rocket separation. The size and number of shear pins will be fine tuned during test flights. The vehicle, or any un-tethered sections, will have a descent rate under the main parachute(s) between 17ft/s and 22ft/s, inclusive. Vehicle Recovery Parachute name Parachute size [in] Descent rate [ft/s] Ejection charge size [g] Booster
Dual deployment recovery will be used. Figure : The Mission Profile Chart includes the flight sequences for both stages and is described with more detail below Event Time [s] Altitude [ft] Velocity [mph] Triggering Condition Triggering Device 1 Launch 0.0 0 0 Ready to launch Launch Control 2 Separation 0.7 75 125 Booster burnout (negative acceleration) Flight computer 3 Sustainer burn 0.8 – 1.5 85 - 400 125 - 490 Stage 2 ignition delay elapses Flight computer (timer) 4 Sustainer 22.0 5168 0 Apogee Deployment altimeter (MAWD) Booster apogee, main deployment 11.0 720 0 Apogee Deployment altimeter (MAWD) Booster touchdown 76.0 0 0 - - 5 Descent drogue -60 Drogue deployment - 6 Main 64 500 -13 500ft reached Deployment altimeter (MAWD) 7 Sustainer touchdown 88 0 0 - - Table : Flight events, including time and altitude of each event, condition that trigger an event and a device that executes the action associated with the event. Removable shear pins will be used for both the main parachute compartment and the drogue parachute compartment. We shall use removable nylon shear pins of sufficient strength to prevent premature rocket separation. The size and number of shear pins will be fine tuned during test flights. The vehicle, or any un-tethered sections, will have a descent rate under the main parachute(s) between 17ft/s and 22ft/s, inclusive. Vehicle Recovery Parachute name Parachute size [in] Descent rate [ft/s] Ejection charge size [g] Booster
CDR_MadisonWest2011_Bamboo.docx