Canadian Satellite Design Challenge Critical Design Review

Canadian Satellite Design Challenge Critical Design Review
<Presenter Names> <University Team Name> <Date> 1 <<University Name>>

<<University Name>>
Presentation Outline Mission Overview Spacecraft Overview Payload(s) Description Structure Thermal Power Attitude Determination & Control Communications Command & Data Handling Orbit Determination Assembly, Integration, and Test Programme Management Concept of Operations Summary & Conclusions 2 <<University Name>>

Mission Overview 3 <<University Name>>

Mission Summary – ONE SLIDE ONLY
Brief statement of mission objectives List the payload(s) and purpose(s) 4 <<University Name>>

Spacecraft Summary – ONE SLIDE ONLY
Include an annotated graphic of your spacecraft in flight configuration Show nominal operational attitude, and flight axes X+ = velocity vector; Z+ = Nadir iPod Y+ Death-ray antenna X+ Solar cells Z+ Anti-satellite skewers 5 <<University Name>>

Mission Ground Track and Ground Station Access (1/2)
Using Satellite Toolkit, show a diagram of the spacecraft ground track over the course of one day, with access to a ground station at your university. Example for RADARSAT-2 using St. Hubert Ground Station 6 <<University Name>>

Mission Ground Track and Ground Station Access (2/2)
What is the minimum elevation angle for communications with your spacecraft? How many passes per day (minimum, average) What is the daily minimum and average contact time? 7 <<University Name>>

Summary of Changes since PDR
Summarise any changes to your mission and spacecraft since PDR E.g., changes to any sub-system; components added or removed; etc. Should be no more than two slides Full details of the changes will appear in the relevant sub-section later in the presentation. 8 <<University Name>>

Spacecraft Overview 9 <<University Name>>

System Level Configuration Trade Selection
Summarise any changes to your trade-off analysis for any components, sub-systems, or mission elements. 10 <<University Name>>

Physical Layout Diagram(s) showing internal physical layout E.g., like below (does not have to be an exploded view) 11 <<University Name>>

Payloads 12 <<University Name>>

Payload #1: Purpose Give an overview of each payload or science experiment on separate slides Why does your payload need to be put into space? Why can’t your experiment/objective be accomplished on the ground? What is new or innovative about this payload experiment? What is the relevance of this payload to your university (or an industry partner)? Who will use the payload data - industry, grad students, or faculty? You should only use 1-2 slides to explain what the payload does. Please do not include slides explaining the science or theory of your payload’s objective (you can put them in the “Additional slides” at the end) 13 <<University Name>>

Payload #1: Characteristics
Physical size, mass Amount of data (KBytes, MBytes) produced to be down-linked per day Objective coverage characteristics & statistics E.g., Earth imagery in km2/day What attitude and orbit position accuracy does your payload need? What happens if it doesn’t get that? 14 <<University Name>>

Payload #2 Add slide groups describing each additional payload. 15 <<University Name>>

Spacecraft Structure 16 <<University Name>>

Spacecraft Structural Drawings
Show 2-D and isometric drawings of your spacecraft Similar to Figure 1 of the DIETR (shown below) Verify that the outer dimensions are to spec. 17 <<University Name>>

Spacecraft Structure Create a co-ordinate system called “Mechanical Build Co-ordinate System” at the geometric centre of the spacecraft. Using FEMAP (or another tool of your choice), identify the mass properties of your spacecraft including: Total Mass Centre of Mass offset in X/Y/Z with respect to the Mechanical Build Co-ordinate System Moments of Inertia about the spacecraft Centre of Mass 18 <<University Name>>

Spacecraft FEM Show the Finite Element Model generated using FEMAP List the materials assigned in the FEM and identify their mechanical properties 19 <<University Name>>

Spacecraft Static Analysis
Using the FEM, constrain the model at the launch interfaces (the rails & ends) and perform a linear static analysis by applying a body load of 12g in each spacecraft axis (±X, ±Y, ±Z) separately. Check the material stresses in the key structural members and report the margins of safety against yield and ultimate failure for these members 20 <<University Name>>

Spacecraft Normal Modes Analysis
Perform a normal modes analysis to determine the first three vibration modes of the spacecraft when constrained at the launch interface. Provide the mode frequencies and the associated mode shapes Show that the first vibration mode frequency is higher than 90 Hz (per DIETR-0200). 21 <<University Name>>

Mass Budget Table(s) providing the following: Mass of all major components & structural elements Sources/uncertainties – whether the masses are estimates, from data sheets, measured values, etc. Total mass Margin 22 <<University Name>>

Thermal Analysis 23 <<University Name>>

Thermal Analysis Create a FEMAP/TMG thermal model of your spacecraft. Include external surfaces to account for radiation exchange to the space environment. If possible use simple lumped mass representations for internal components. Create thermal couplings to couple the internal components to the external surfaces. Assign component dissipations consistent with the spacecraft operations. 24 <<University Name>>

Thermal Analysis Identify the space environment thermal fluxes (sources and sinks) acting on your spacecraft. Identify a worst case hot and a worst case cold, considering orbit, season (aphelion vs. perihelion), attitude, and internal dissipation. Run the thermal model for the hot and cold cases Recover the max/min temperatures for critical components (battery, payload). Identify the allowable temperatures and report the temperature margins for critical components. 25 <<University Name>>

Power Sub-system 26 <<University Name>>

Power Sub-system: Power Generation
Spacecraft power block diagram – ONE SLIDE ONLY Show all major power system components: Solar panels Batteries Power regulator(s) Power distribution connections to other major components and sub-systems (e.g., payload, ADCS components) Separation Switches 5.0V Regulated lines 6.0V – 7.2V Unregulated Power Regulation & Distribution Panel 1 Battery Panel 2 27 <<University Name>>

Power Sub-system: Power Generation
Slides on the spacecraft power sub-system: Location and number of solar panels – indicate whether static or deployable Orbit Average Power generated Assume sun-synchronous 10:00 and 11:00 Equator Crossing Times, for 600 km and 800 km circular orbit How much time is the spacecraft in sun vs. eclipse? Batteries: number of cells, physical size, nominal voltage, storage capacity (in Ahr or mAhr), max power output (in W or mW) Power regulation & distribution 28 <<University Name>>

Power Sub-system: Power Budget
Summarise the power consumption of the spacecraft List each electric/electronic unit, its power consumption modes, power consumed in each mode, and duty cycle (in % of an orbit) for each mode (example below) What is the expected battery Depth-of-Discharge? What is the overall power margin? = (OAP generated) / (OAP consumed) Component Nominal Power used (W) Margin Budgeted Power Used (W) Duty Cycle Orbit Average Power with margin (W) Component 1 0.5 20% 0.60 100% Component 2 0.8 40% 1.12 80% 0.90 Component 3 - Low 5% 0.84 50% 0.42 Component 3 - High 1.5 1.58 30% 0.47 Total 2.39 29 <<University Name>>

Attitude Determination & Control Sub-system (ADCS)
30 <<University Name>>

ADCS Overview – ONE OR TWO SLIDES
What is the nominal operational attitude of your spacecraft? What attitude knowledge and control accuracy do you need for payload operations or communications? What Attitude sensors will be used? What attitude determination accuracy will your spacecraft achieve? What Attitude actuators will be used? What attitude control accuracy will your spacecraft achieve? 31 <<University Name>>

ADCS Control System Details of the ADCS control system Sensor sampling frequency Actuator control frequency Telemetry produced Algorithms used What attitude determination/control does your mission need? What is the driver for your requirement? 32 <<University Name>>

Attitude Sensor #1..n For each attitude sensor: Brief overview of the sensor Expected attitude determination accuracy Effect on the overall determination accuracy if it fails 33 <<University Name>>

Attitude Actuator #1..n For each attitude actuator: Overview of the actuator used Expected control accuracy Effect on the overall control accuracy if it fails 34 <<University Name>>

Communications Systems

Communications System
One slide to summarise RF used for Commanding uplink Telemetry downlink Science data downlink (if different from Telemetry) 36 <<University Name>>

Communications: Link Budgets
Give the link budget for each uplink & downlink channel used You should be able to do each budget on one page only Space Mission Analysis & Design, Larson & Wertz, 3rd Edition, Table gives a good basic link budget Clearly indicate the required transmitting/receiving characteristics for the Ground Station. I.e., it must include everything that CSDC Management needs to be able to procure the required Ground Station hardware (and software, if applicable). 37 <<University Name>>

Communications Throughput Budget
What is your Communications Throughput Budget? How much data are you uplinking/downlinking? List each source and data size. How is data encoded for uplink/downlink? What is the communications protocol overhead as a per centage of the useable data transmitted? How much data can you uplink/downlink during a pass? What is the average amount of data to be uplinked or downlinked per day? 38 <<University Name>>

Communications Throughput Budget
E.g., your Communications Throughput Budget should look something like the example below: So, in this example, you would need an average of at least 24.9 minutes of contact time with your satellite each day to downlink this telemetry data. 39 <<University Name>>

Command and Data Handling (C&DH) Sub-system

C&DH Architecture Provide an overview of the C&DH requirements and design Should discuss Basic architecture How uplinked commands (immediate vs. time-tagged) are handled (a diagram may help). Brief summary of what the software has to do Programming language(s) 41 <<University Name>>

Orbit Determination 42 <<University Name>>

Orbit Determination What methods will you use to determine and/or predict your spacecraft’s orbital position? What orbit position accuracy does your payload need? Why? What happens if you can’t get that level of accuracy? 43 <<University Name>>

Assembly, Integration, and Test (AI&T)

Spacecraft AI&T Overview
Updated plan for how the spacecraft sub-systems will be integrated and tested – prior to environmental testing Summary of tests to be performed on each sub-system Summary of tests to be performed on the integrated spacecraft At CDR this should include concepts for how subsystems will be integrated Sequence (which subsystems are needed prior to others) Test equipment necessary Test environments necessary The goal(s) at CDR are Demonstrate that you are ready for AI&T Demonstrate that you have a path to ensure that your spacecraft works and meets requirements – and your expectations! 45 <<University Name>>

Programme Management 46 <<University Name>>

Programme Schedule Updated development schedule to show your plan from CDR until Environmental Testing (week of September 24 – 28, 2012). The schedule should be “wrapped up” to 1-2 levels Show high-level tasks only in order to make the schedule readable The goals of this schedule are to Demonstrate that you will be able to complete AI&T prior to environmental testing. Provide tool for judges to assess trouble areas and offer ways for the team to best meet the objectives of the competition A Gantt chart showing task start and stop dates and durations is recommended Schedule should include linkages between tasks to provide the team with an idea of what happens in the overall flow when milestones are not met on time Please ensure your schedule is readable in the presentation What is your Critical Path? Where is the highest risk? What margin do you have? 47 <<University Name>>

Programme Budget – Hardware
Provide an updated table listing the costs of the spacecraft flight hardware Table should include Cost of major components and hardware Indication of whether these costs are actual, estimates, or budgeted values If components are donated, give the current expected market value (excluding Payload instruments) 48 <<University Name>>

Programme Budget – Other Costs
Table(s) (same format as Hardware Budget) showing Ground control station costs Labour Cost (in hours) Other costs Prototyping Test facilities and equipment Rentals Computers Travel Income Sources of project income The goal of this budget is to demonstrate that you completely understand your financial requirements to build and test your spacecraft. 49 <<University Name>>

Risk Management 50 <<University Name>>

Risk Management List the top five risks which were given in the Programme Management Plan and at PDR How have you managed/mitigated them? Have any risks occurred? Provide an updated risk table. How has your top-five list changed since PDR? 51 <<University Name>>

Concept of Operations (CONOPS)

Concept of Operations: Operational Modes
What are the Operational Modes of your spacecraft? How does it transition from one mode to another? A diagram is very helpful to display this, e.g.,: Launch All systems OFF Safe-Hold Seek nominal attitude Wait to hear from Ground Boot-up Separation Command from Ground… All systems powered up 53 <<University Name>>

Concept of Operations: LEOP
1-3 slides detailing the operations during Launch and Early Orbit (LEOP) phase LEOP includes all operations following launch until you move into routine, nominal operations. E.g., Establish initial contact with the spacecraft Determine status of spacecraft sub-systems Determine spacecraft orbit Activate deployables Calibrate payloads, sensors, actuators Establish operational attitude 54 <<University Name>>

Concept of Operations: Nominal
1-3 slides providing an updated view of spacecraft and mission operations Simple flow-chart diagrams are a good way to present the CONOPS Focus on how the spacecraft will operate, not what everyone on the team will be doing Sample timeline of commanding events, from mission planning, to command generation, to uplink, to execution Sample timeline of payload and telemetry data downlink events, from generation of data, to storage, to downlink, to analysis, distribution, and/or archiving 55 <<University Name>>

Concept of Operations: Nominal Timelines
Sample timeline of commanding events, from mission planning, to command generation, to uplink, to execution, to downlink. E.g., if you plan on imaging a particular area on the Earth: Keep in mind that it could take more than a day before your satellite is in position to be able to capture data from the objective area, and then several more hours until it can re-contact your ground station. 56 <<University Name>>

Concept of Operations: Anomalies
What anomalies can you detect, and how will you detect them? How quickly will you detect an anomaly? What is your operational response to an anomaly? 57 <<University Name>>

Educational Outreach 58 <<University Name>>

Educational Outreach Please summarise the Educational Outreach presentations you have given Locations, approximate number of people, any local media coverage 59 <<University Name>>

Summary & Conclusions 60 <<University Name>>

Summary & Conclusions In general include the following: Major accomplishments Major unfinished work Next steps Other assistance needed? Why you are ready to proceed to next stage of development 61 <<University Name>>

Supplementary Information

Acronyms Provide a list of common acronyms used throughout the presentation. 63 <<University Name>>

Canadian Satellite Design Challenge Critical Design Review

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