1. Stevens Institute of Technology - New Jersey Space Grant Consortium with Rutgers University Critical Design Review Mike Giglia, Ethan Hayon Robert Hopkins Mark Siembab, Sean Watts, and Jenny Jean

2. Mission Overview Rob Hopkins

3. Mission Overview To collect and analyze data for future space research operations through various experiments designed and implemented on a payload.

4. Mission Overview - Theory of Requirements At launch we will begin to take atmospheric readings. As the rocket ascends and the ports are opened completely, air will flow in the dynamic port across our sensors and out the static port. This will be able to show us different levels of various gases at changing altitudes. Gathered information will provide future payloads an example of what they will come in contact with during flight to avoid using anything that may malfunction or receive interference as a result of the environment. The Earth's atmosphere is composed of 71% Nitrogen, 21% Oxygen, 8% CO 2, and 1% various other gases.

5. Requirements One Static Atmospheric Port One Dynamic Atmospheric Port

6. Mission Expectations We expect to retrieve a CO 2 and H 2 0 concentration gradient as the rocket ascends to apogee as well as descent to earth. The data retrieved will assist in environmental studies. The physical data will aid in the design of future payloads.

7. Team Organizational Chart

8. Example ConOps

9. Expected Results At the beginning of the flight, we expect to have a CO 2 concentration of roughly 390 ppm which decreases with altitude. We expect a slight increase of temperature due to air friction on the skin of the rocket. The strongest vibration should be experienced during the initial Orion burn.

10. Design Description Ethan Hayon

11. De-Scopes Elimination of all gas sensors except CO2 due to heating and cost concerns. Simplification of the Latch Circuit using a Thyristor instead of an NPN-PNP chain system.

12. Off-Ramps Problem: Possibility that the pinch valve will not remain open during the flight, causing a catastrophic loss of data. Solution: Possible dedicated battery for the pinch valves.

13. Off-Ramps Problem: It may be difficult to mount the ACV securely due to its cylindrical shape. Solution: The shape of the ACV can be changed to a rectangular prism to allow for more secure mounting.

14. Off-Ramps Problem: The center of mass of the payload is offset 0.37 inches from the center along the Z- axis. Solution: This will be solved by moving components between the two plates until there is an even weight balance between them.

15. Prototyping/Analysis Mike Giglia

16. Prototyping/Analysis A latch circuit was successfully prototyped using a thyristor PNP-NPN system. Humidity, Pressure, Temperature sensors have also been tested.

17. Electrical Design Mark Siembab

18. Electrical Schematic Text The ATMega displayed is an Arduino Mega The SEN is essentially a breakout board, the schematic is not displayed. Power Latch Circuit

19. Power Budget

20. Mechanical Design Mike Giglia

21. Payload Isometric View

22. Center of Mass Center of Mass (offset from origin)

23. Center of Mass The center of mass calculated by SolidWorks: o X: 0.00 inches o Y: -0.08 inches o Z: 0.36 inches We will work to improve the center of mass of our payload. The center of mass along the Z axis can be corrected by relocating objects between the plates to balance them better.

24. Dimensioned Drawing

25. Risks Mark Siembab

26. Risk Walk-Down The biggest risk addressed in the PDR was the exceedingly long heating time associated with the original gas sensors. Since then, we have reduced our gas sensors to just one infrared CO 2 sensor which does not have a heating element and thus requires not heating period.

27. Risk 1 Rsk.1: Low sample time establishes a poor CO 2 gradient Rsk.2: Startup period not complete by T minus zero Rsk.3: Power loss prevents redundant valve opening

28. Software Design Sean Watts

29. Software Flowchart

30. User Guide Compliance Mark Siembab

31. User Guide Compliance Mass without canister according to SolidWorks = 1.7 lbs. o CG is within the 1x1x1 envelope. It is located off the center of the payload by (0, 0.8, 0.37) o Batteries: 4 x 9 Volt alkaline in series to provide 32V to be used around the payload. o Thyristor-based latching circuit with g-switch activation supplied power to the payload. o High voltage, low current pulses produced by piezo vibration sensor. These pulses will then be reduced using resistors to permit data collection. This component will be insulated with conformal coating to inhibit spark jumps. o One static and one dynamic port are used, both of which are protected by redundant safety valves.

32. Sharing Logistics We are sharing the canister with Mitchell Community College. o They are harvesting electrical energy throughout the rocket flight. Teleconference scheduled for next week. The platform interfacing strategy is to be determined during the conference call.

33. Manufacturing Plan Mike Giglia

34. Mechanical Elements What needs to be manufactured? o ACV out of PolyCarbonate Schedule o SolidWorks 3D Model o Parts Ordered o Mechanical Assembly o Testing

35. Electrical Elements What needs to be manufactured? o Sensor Board (SEN) Schedule o Eagle schematics created o Schematics converted to eagle board file o Board file sent to PCB fab-house o Electrical components ordered o Assembly of electrical components onto PCB o Testing

36. Software Elements Blocks of code to complete: o Flash (SD) card I/O o Sensor reading (CO 2, H 2 0, Vibration, Temperature) o Data Protection (latch) Schedule o Acquire development platform (Arduino Mega) o Refine flowchart o Prototype code segments o Implementation o Assemble the code segments o I&T (Integration and Testing)

37. Testing Plan Sean Watts

38. System Level Testing ACV Pressure Testing o Ensure that the ACV can handle the dynamic pressure during the rocket flight. o Utilize SolidWorks to simulate a pressure test o Pressurize the finished vessel with an air compressor. o The test passes if the ACV remains in tact and there are no leaks. The CO2 sensor will be tested by filling the ACV with CO 2 o This also will ensure that the AVR is correctly reading the sensor o Also a useful software test These tests will be performed in February as the components are being completed.

39. Project Management Plan Ethan Hayon

40. Schedule

41. Budget

42. Conclusion Issues o Sourcing a rechargeable battery which can supply 24+ volts and replace the 9V alkaline arrangement while falling within size and mass requirements. Final components will be purchased and the majority of the project time will be devoted to construction. Over winter break the ACV will be machined and pressure tested. If necessary, the layout inside the ACV will be adjusted to optimize airflow to the CO 2 sensor.