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Full Mission Simulation Report. New Jersey Space Grant Consortium at Stevens Institute of Technology and Rutgers University Ethan Hayon, Mark Siembab, Mike Giglia, Robert Hopkins, Sean Watts. Mission Statement:.
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Full Mission Simulation Report New Jersey Space Grant Consortium at Stevens Institute of Technology and Rutgers University Ethan Hayon, Mark Siembab, Mike Giglia, Robert Hopkins, Sean Watts
Mission Statement: –To collect and analyze data for future space research operations through various experiments designed and implemented on a payload.
Mission Overview: • The payload has been assembled and we have began testing it. • Pressure tests of the ACV and pneumatic components will take place in the upcoming week. • The IR temperature sensor will be mounted in the coming week. • We are working on acquiring access to a vibration table. • Code will be organized into cleaner functions for easier maintainability.
Subsystem Overview: • Mechanical/Structure • Electrical • Power / EPS • Atmospheric Containment Vessel/Pneumatics • Software
Mechanical / Structure: • After minor adjustments to the pneumatic system, nearly all components were integrated successfully. • Written integration procedure and current parts list have not been drafted but will be, if required; so far we have encountered no problems with assembly, nor keeping track of components. • Spare hardware and components are available for nearly every subsystem. • Payload weight: 1318.4g (46.5 ounces or 2.9 lbs) • A ballast may be necessary; it will consist of nuts + short bolts (steel) mounted through the payload plates at specific locations.
Mechanical / Structure: • Integrating with Mitchell County College: • Aluminum hex standoffs will be used to combine the payloads. • Inside will be threaded steel rods used to connect the female-female aluminum standoffs. • These standoffs are 2" in height each making our payload height 4.5" including the thickness of the plates. • The combined center of gravity is to be reviewed this week to be finalized. • Action Items: Teleconference with Mitchell County College regarding final integration plans and combined mass and center of gravity.
Electrical: • All electronics have been integrated except for the Infrared Temperature Sensor. The sensor is connected, but not yet attached to the plate. • We are unsure of the best location to mount it. It needs to be as close to the rocket skin as possible. • Can we use the access window on the canister? • We have received data, and it makes sense. • Data on the next slide • Once we connect the IR temp sensor (code is already written and functional) the payload will be electrically complete. • We also need to organize the wires and stake down the components.
Sample Data (From SD Card): Time: 20 | x: 0 | y: 0 | z: 7 | CO2: 805 Time: 21 | x: 0 | y: 1 | z: 8 | CO2: -1 Time: 22 | x: 0 | y: 0 | z: 8 | CO2: -1 Time: 23 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 24 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 25 | x: 0 | y: 1 | z: 7 | CO2: -1 Time: 26 | x: 0 | y: 1 | z: 7 | CO2: -1 Time: 27 | x: 1 | y: 0 | z: 7 | CO2: -1 Time: 28 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 29 | x: 2 | y: 0 | z: 12 | CO2: -1 Time: 30 | x: 0 | y: 0 | z: 7 | CO2: 1255 Time: 31 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 32 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 33 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 34 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 35 | x: 0 | y: 0 | z: 9 | CO2: -1 Time: 36 | x: 0 | y: 0 | z: 7 | CO2: -1 Time: 37 | x: 0 | y: 0 | z: 6 | CO2: -1 Time: 38 | x: 0 | y: 0 | z: 3 | CO2: -1 Time: 39 | x: 0 | y: 3 | z: 2 | CO2: -1 Time: 40 | x: 0 | y: 0 | z: 8 | CO2: 1285 Each increment to "time" is 1/20th of a second.
Power / EPS: • The 600mAh NiCD battery used for initial testing lasted approximately 45 minutes • The idle current draw of the servo proved more significant than expected, but still marginal compared to the previous pinch valve and will not cause any problems • Acquisition of a higher capacity 9.6V NiMH battery pack. • Ordered on April 28th
Atmospheric Containment Vessel / ACV: • Final machining on the ACV was completed and it was mounted successfully. • ACV ports were over-tapped and angled barbed fittings were used to minimize the ACV's footprint and simplify assembly. • Silicone-bead sealing will be pressure tested within the next week.
Pneumatic System: • A welded metal bracket was devised to secure the ball valve to the plate. • Bracket provides 1/2" of left-right position adjustment if required. • HS-625MG Servo tested and found to actuate ball valve with no problems. • Servo mounted to ball-valve using machined metal parts to ensure durability.
Software: • The software ran as expected. • We are still working out the timing for when the inlet valve will open and close. • Data was written successfully to the SD Card. • We are sampling the IR temperature sensor and the accelerometer at 20Hz. The CO2 sensor is being sampled at 2Hz (using a mod 10 operation) • Set up the timing on the open/close valve operation. Right now we can automatically open and close the valve, however, it is not on a timer.
Action Item Summary: • Order a third revision of the shield. This board will contain some extra ports for flexibility if we choose to add components. Also, additional power outputs will be helpful. • Order before May 1st. • Use a higher capacity NiMH battery • Ordered on April 29th. • Set timing on ball valve open/close action • Coded before May 1st
Conclusions: • Currently we do not have a location planned for our IR thermometer and we request advice as it is expected to measure rocket skin temperature. Note: C of G will not be impacted by placement of thermometer because it weighs <1 gram.