Langmuir probe for Quadsat/PnP

Company: New Mexico Tech
Manager: Anders M. Jorgensen
Start: January 17, 2011
Finish: May 6, 2011
Report Date: March 6, 2011

Gantt Chart

WBS Name Work
     
1 Perliminary design 63d
1.1 Electronic preliminary design 25d
1.1.1 CPU requirements 5d
1.1.2 VVS preliminary design 5d
1.1.3 CMS preliminary design 5d
1.1.4 Power supply preliminary design 5d
1.1.5 Spacecraft communication preliminary design 5d
1.2 Test rig preliminary design 8d
1.3 Mechanical preliminary design 15d
1.3.1 Probe preliminary design 5d
1.3.2 Enclosure preliminary design 5d
1.3.3 Circuit board mechanical constraints 5d
1.4 Software preliminary design 15d
2 Detailed design 155d
2.1 Electronic detailed design 85d
2.1.1 CPU selection 5d
2.1.2 VVS detailed design 10d
2.1.3 CMS detailed design 10d
2.1.4 Spacecraft communication detailed design 5d
2.1.5 Power supply detailed design 5d
2.1.6 Circuit design complete
2.1.7 Circuit board detailed design 50d
2.1.7.1 Circuit protoboard tests 24d
2.1.7.2 PCB final layout 9d
2.1.7.3 Prepare Bill of Materials 5d
2.1.7.4 Purchase PCBs and wait for arrival 4d
2.1.7.5 Populate PCB and test 8d
2.1.8 Electronic design complete
2.2 Purchase evaluation board 5d
2.3 Test rig detailed design 10d
2.4 Software detailed design 25d
2.5 Detailed mechanical design 30d
2.5.1 Probe detailed design 15d
2.5.2 Enclosure detailed design 15d
3 Manufacture 80d
3.1 Electronics Manufacture 35d
3.1.1 Select circuit board manufacturer 10d
3.1.2 Procure components 10d
3.1.3 Manufacture circuit board 15d
3.2 Test Rig Manufacture 15d
3.3 Mechanical Manufacture 30d
3.3.1 Manufacture probe 15d
3.3.2 Manufacture enclosure 15d
4 Test and calibration 75d
4.1 Software test on evaluation board 20d
4.2 Shake test 10d
4.3 Plasma chamber test 15d
4.4 Software test on flight board 30d
5 Delivery
Week 4, 2011 Week 5, 2011 Week 6, 2011 Week 7, 2011 Week 8, 2011 Week 9, 2011 Week 10, 2011 Week 11, 2011 Week 12, 2011 Week 13, 2011 Week 14, 2011 Week 15, 2011 Week 16, 2011 Week 17, 2011 Week 18, 2011
18 19 20 21 22 23 24 25 26 27 28 29 30 31 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 1 2 3 4 5 6 7 8 9 10 11 12 13
BM, JM
ML, CY
DG, JQ, VR, CY
AH, JM, VR
BM, JM
BM, JM
BM, JM
ML, CY
DG, JQ, VR, CY
BM, JM
AH, JM, VR
◆
ML, VR, CY
DG, AH, JM
AMJ, DG, ML, VR, CY
DG, AH, JM
ML, VR, CY
◆
AMJ, BM, JM
AH, ML
AMJ, JQ
AH, ML, JM
◆

Tasks

WBS Name Start Finish Work Priority Complete Cost Notes
1 Perliminary design Jan 18 Feb 14 63d Define function and circuitry without selecting specific components
1.1 Electronic preliminary design Jan 18 Jan 24 25d
1.1.1 CPU requirements Jan 18 Jan 24 5d 100% Requirements: Watch dog timer. I2C. Evaluation board available. Free programming interface. ADCs and DACS. Triggered timers. Built-in flash that can be permanently programmed. Some amount of RAM built-in, 128KBytes?
1.1.2 VVS preliminary design Jan 18 Jan 24 5d 100% This is the variable voltage supply which applies voltages to the probe. Use a DAC with a voltage follower. Voltage range should be -10 to +10 V.
1.1.3 CMS preliminary design Jan 18 Jan 24 5d 100% This is the current measuring system, which measures the current through the probe. One possibility is an integrator. A counter operates while the integrator integrates. When the integrator reaches a pre-determined voltage (either negative or positive) then the clock counter is recorded.
1.1.4 Power supply preliminary design Jan 18 Jan 24 5d 100% Should supply necessary voltages. These might be: +3 V for CPU, +-10V for VVS and CMS.
1.1.5 Spacecraft communication preliminary design Jan 18 Jan 24 5d 100% We need to use the SPA interface which is a 4-wire interface supplying power at a single voltage, ground, and two lines for communications via I2C interface.
1.2 Test rig preliminary design Jan 18 Jan 27 8d 100% The test rig should allow us to emulate the communication with the spacecraft through the SPA interface. We should be able to record data from the SPA interface, ideally store them, and analyze them, but at least examine the data. We may also want to be able to apply probes to test points on the flight board. What else should it be able to do? It may consists of a CPU evaluation board which communicates vis the I2C protocol, and which has a useful user interface on a desktop computer.
1.3 Mechanical preliminary design Feb 1 Feb 7 15d
1.3.1 Probe preliminary design Feb 1 Feb 7 5d 100% Should the probe be deployed or not? The length should be at least 10-20 cm with a head which is cylindrical and 5 cm long and 1.5 cm in diameter.
1.3.2 Enclosure preliminary design Feb 1 Feb 7 5d 100% Outside dimensions 50 x 50 x 12.5 mm. The probe is attached to the enclosure. There are bolt attachments to attach to the spacecraft.
1.3.3 Circuit board mechanical constraints Feb 1 Feb 7 5d 100% For the purpose of laying out the circuit board we need to know the space available inside the enclosure.
1.4 Software preliminary design Jan 25 Feb 14 15d 40% The design of the software depends on the design of the VVS and CMS. Calibration steps and steps to change settings.
2 Detailed design Jan 25 Mar 21 155d This involves selecting components with enough detail to be ready for manufacture
2.1 Electronic detailed design Jan 25 Mar 4 85d
2.1.1 CPU selection Jan 25 Feb 7 5d 100%
2.1.2 VVS detailed design Jan 25 Feb 7 10d 100%
2.1.3 CMS detailed design Jan 25 Feb 7 10d 100%
2.1.4 Spacecraft communication detailed design Jan 25 Feb 7 5d 100%
2.1.5 Power supply detailed design Jan 25 Feb 1 5d 100%
2.1.6 Circuit design complete Feb 7 Feb 7
2.1.7 Circuit board detailed design Feb 8 Mar 4 50d
2.1.7.1 Circuit protoboard tests Feb 8 Feb 17 24d 90%
2.1.7.2 PCB final layout Feb 8 Feb 15 9d 80%
2.1.7.3 Prepare Bill of Materials Feb 8 Feb 14 5d 90%
2.1.7.4 Purchase PCBs and wait for arrival Feb 16 Feb 21 4d 50%
2.1.7.5 Populate PCB and test Feb 22 Mar 4 8d 0%
2.1.8 Electronic design complete Mar 4 Mar 4
2.2 Purchase evaluation board Jan 25 Feb 3 5d 100%
2.3 Test rig detailed design Jan 28 Feb 10 10d 60%
2.4 Software detailed design Feb 15 Mar 21 25d 20% Start writing the software here.
2.5 Detailed mechanical design Feb 8 Feb 28 30d
2.5.1 Probe detailed design Feb 8 Feb 28 15d 70%
2.5.2 Enclosure detailed design Feb 8 Feb 28 15d 80%
3 Manufacture Jan 18 Mar 25 80d
3.1 Electronics Manufacture Jan 18 Mar 25 35d
3.1.1 Select circuit board manufacturer Jan 18 Jan 31 10d 100%
3.1.2 Procure components Feb 15 Feb 28 10d 90%
3.1.3 Manufacture circuit board Mar 4 Mar 25 15d 0%
3.2 Test Rig Manufacture Feb 11 Mar 4 15d 20%
3.3 Mechanical Manufacture Mar 1 Mar 21 30d
3.3.1 Manufacture probe Mar 1 Mar 21 15d 0%
3.3.2 Manufacture enclosure Mar 1 Mar 21 15d 0%
4 Test and calibration Mar 22 May 6 75d
4.1 Software test on evaluation board Mar 22 Apr 18 20d 0%
4.2 Shake test Mar 25 Apr 8 10d 0%
4.3 Plasma chamber test Mar 25 Apr 15 15d 0%
4.4 Software test on flight board Mar 25 May 6 30d 0%
5 Delivery May 6 May 6

Resources

Name Short name Type Group Email Cost
A. Huynh AH Work ahuynh@nmt.edu 0
A. M. Jorgensen AMJ Work anders@nmt.edu 0
Byron Marohn BM Work bmarohn@nmt.edu 0
Chris Yelton CY Work cyelton@nmt.edu 0
D. Guillette DG Work dguillet@nmt.edu 0
James Mason JM Work jlmasonbsat121@hotmail.com 0
Jerry Quiroga JQ Work jquirog1@nmt.edu 0
Matthew Landavazo ML Work matthewlandavazo@gmail.com 0
Vinayak Ravindran VR Work vravindr@nmt.edu 0
This file was generated by  Planner