team advisor: sam gagnard zoltan sternovsky pros8
TRANSCRIPT
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PROS8Quinton Nietfeld, Kieran O’Day, Colton Ord, Ryan Cameron, Yang Lee,
Zaki Laouar, Zachary Arbogast, Mamdooh Alkalbani
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Critical Design Review
Team Advisor:Zoltan Sternovsky
Point of Contact:Sam Gagnard
Passive Radio Frequency Observation System 8
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Project Motivation
Background
• Orbit Logic specializes in space situational awareness (SSA) and utilizes a software called Heimdall
• Heimdall schedules observations of known and uncharacterized space objects
• Heimdall currently uses Optical and RADAR sensors when scheduling observations
2Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Project Motivation
Problem
• Heimdall software does not support passive radio frequency (RF) observations
• Best practices for observing and characterizing satellites using RF sensors are unknown
3Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject PlanProject Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Project Objective
PROS8 is a satellite observation scoring and scheduling software that uses a passive radio frequency (RF) ground-station to determine and
compare satellite observation opportunities.
4Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject PlanProject Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Key Terms
• Two Line Element (TLE) Data – a data format encoding a list of orbital elements for Earth orbiting satellites
• Doppler Shift - change in frequency of a wave in relation to an observer who is moving relative to the wave source
• Radio Frequency (RF) – Electromagnetic waves with frequency ranging from 20kHz to 300 GHz.
• L1 Band – Subset of Radio Frequency with a range of 1 – 2 GHz
5Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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CONOPS
6Project Overview Design Solution
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RiskVerification &
ValidationProject PlanProject Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
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Design Solution
7Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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FunctionalBlockDiagram
8Project Overview Design SolutionCritical Project
ElementsDesign
RequirementsRisk
Verification & Validation
Project PlanProject Overview Design SolutionCritical Project
ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan
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9Project Overview Design Solution
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RiskVerification &
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Ground Station Design Solution
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Signal Reception
10Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Signal Reception
11Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Pointing Controls
Project Overview Design SolutionCritical Project
ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan12
RF HAMDESIGN SPX-02
RF HAMDESIGN Rot2Prog
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Signal Processing
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Software Defined RadioSignal Hound USB-SA44B
Project Overview Design SolutionCritical Project
ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan
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Software DesignSolution
14Project Overview Design Solution
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Design Requirements
RiskVerification &
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User Input
1. Satellite Orbit Parameters (TLE Data)
2. Observation window
Propagate Satellite Orbit from TLE data
Calculate Inertial Position of the
Satellite and the ground station.
Use the inertial position information to Calculate Satellite’s Azimuth and
Elevation Relative to the Ground Station
Output
Satellite observational score
Scoring Software Flow Diagram
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Orbit Determination: Doppler Shift
• Doppler Shift - change in frequency of the received signal in time
• Doppler Shift can be used to find Slant Range Rate (Relative Speed)• Based on the difference in velocities of
ground asset and the satellite
• Difference in velocity is the range rate
• The range rate is then used to find the orbit elements estimate
16Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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17Project Overview Design Solution
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Orbit DeterminationOrbit Determination Basics:
1. Six variables are required to determine an orbit
I. Position Vector Components (3) & Velocity Vector Components (3)
II. Vectors used instead of orbit elements due to simplicity
2. Vector Equation Relate Range Rate to the Position & Velocity Vectors
3. Range Rate (Relative Speed) Obtained through Doppler Shift
4. To solve for the six components numerically, at least six range rate
measurements are required.
I. 6 variables -> 6 equations for a full set
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Orbit Determination
SoftwareFlow Diagram
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RiskVerification &
ValidationProject Plan
Fourier Transform
Determine Center Frequency
Calculate Doppler Shift
Calculate Measured Range Rate
Compare Expected Range Rate to Measured Range Rate
Calculate Error in Position and Velocity Errors
Output New Position and Velocity Vectors
Determine if Solution Converges
User Input
1. Known Transmission Frequency
2. Satellite Orbit Parameters (TLE Data)
NO YES
Output
Final TLE Data Based on Final Position and Velocity
Calculations
SDRSignal
Reception
= Laptop
= Ground Station
Update ExpectedPosition,
Velocity Vectors and Range rate
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Scheduling Software
Flow Diagram
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If only one satellite is selected
Remove Selected Satellite from List
User Input
1.Priority of Each Satellite
2. Satellite Orbit Parameters (TLE Data)
Satellite is Put Into Plan
Click to add text
Create Priority List
Create Scoring List Based on First Time in FOV
Select Satellite(s) With Highest Score
Two or More Satellites Selected
Higher Priority Satellite Put Into Observation Plan
Remove Higher Priority Satellite from List
Calculate Next Observation(s)
Calculate New Score(s) and Put Into List
MoreObservation
Spots Available
No ObservationSpots Available
Observation Plan Created
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Critical Project Elements
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Designation CPE Critical Characteristics
CPE-1 Signal Reception Receive radio frequency signals from satellite
CPE-2 Pointing Control Point antenna at the location of the satellite
CPE-3 Signal Processing Process the received analog signal and turn it into a digital signal
CPE-4 Scoring Software Gives a score to a given observation
CPE-5 Scheduling Software Schedules a plan for several observations
Project Overview Design SolutionCritical Project
ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan
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Design Requirements and their Satisfaction
21Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Signal Reception – CPE1
• FR 1: Receive RF signals from satellites in various conditions, with various orbital geometries
• DR 1.1: Half-Power Beam-Width (θ) of the receiver 3 < θ < 20
• DR 1.2: The receiver will have a Gain > 15 dB
• DR 1.3: The receiver will be designed to receive frequencies in the L1 band
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Critical Project Elements
Design Requirements
RiskVerification &
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Signal Reception Satisfaction
23Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Signal Reception Satisfaction
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Design Requirements
RiskVerification &
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CPE1 SATISFIED✔
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Pointing Control – CPE2
• FR 2 - Point system along orbit path from manual input with 1°pointing accuracy
• DR 2.1 - Pointing hardware provides enough torque to rotate the antenna
• DR 2.2 - Able to run on 120V, 60Hz, 15A power supply
25Project Overview Design Solution
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Pointing Control Satisfaction
26Project Overview Design Solution
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Design Requirements
RiskVerification &
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Performance Measure Standard Version
Controller Rot2Prog
Resolution 0.5°/Step
Turning Torque 80 N*m
Weight 14.5 kg
Supply Voltage 12-18 VDC
Current Draw 3-20 A
Price $723.76
SPX-02
Rot2Prog Controller
FR 2
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Pointing Control Satisfaction
27Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
• Assumptions• Uniform density for each component
• Components firmly secured
• Constant Torque
• Model• Inertia estimate generated in SolidWorks
• SF = 4.0
• 𝜏 = 80 𝑁𝑚
• 𝐼 = 6.5248 𝑘𝑔 ∗ 𝑚^2
• 𝜔𝐿𝐸𝑂 = .008727𝑟𝑎𝑑
𝑠
𝜏 = 𝐼𝛼
𝑑𝜔
𝑑𝑡= 𝛼
𝜔 = 𝛼𝑡
𝛼 = 12.26𝑟𝑎𝑑
𝑠
Integrate w/ constant = 0
𝑡 = .00071𝑠To get to required slew rate.
DR 2.1
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Pointing Control Satisfaction
28Project Overview Design Solution
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Design Requirements
RiskVerification &
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PW-32015 PSU
Regulates input voltage and current from wall outlet for to provide
optimal power for the SPX-02
DR 2.2
CPE2 SATISFIED✔
Power Supply
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Signal Processing – CPE3
• FR 3 - Convert L1 band analog RF signal into a digital signal
• DR 3.1 - SDR must have a resolution bandwidth (RBW) of at most 2 kHz
• DR 3.2 - SDR must have a frequency range of at least 1 GHz—2 GHz
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SDR Theory of Operation
30Project Overview Design Solution
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Signal Processing Satisfaction
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CPE3 SATISFIED✔
Signal Hound SDR
Resolution Bandwidth = 0.1 Hz to 250 kHz and 5 MHz
Frequency Range = 1 Hz to 4.4 GHz
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Scoring and Orbit Determination Software – CPE4
• FR 4: The scoring software shall provide scores for each planned observation and update orbit estimates after observation
• DR 4.1: The software shall take frequency measurements as its input and calculate Doppler shift
• DR 4.2: The software shall calculate orbit estimates based on Doppler shift
• DR 4.3: The software shall output scores for pre-planned scoring opportunities
32Project Overview Design Solution
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Design Requirements
RiskVerification &
ValidationProject Plan
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Software Input
• Desired observation timeframe
• Which satellites to observe
• Number of times to observe the satellites
• Ground Station information
• Two Line Element (TLE) Data
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Design Requirements
RiskVerification &
ValidationProject Plan
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Scoring Software Process
1. Choose Satellite & Time of Observation
2. Determine Orbit and Calculate Expected Inertial Position and Velocity of Satellite
3. Determine Azimuth and Elevation Relative to Ground Station
4. Calculate Score Based on Predetermined Factors
5. Output Observation Score
34Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Scoring Software Process
1. Choose Satellite & Time of Observation
2. Determine Orbit and Calculate Expected Inertial Position and Velocity of Satellite
3. Determine Azimuth and Elevation Relative to Ground Station
4. Calculate Score Based on Predetermined Factors
5. Output Observation Score
35Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Scoring Software Process
1. Choose Satellite & Time of Observation
2. Determine Orbit and Calculate Expected Inertial Position and Velocity of Satellite
3. Determine Azimuth and Elevation Relative to Ground Station
4. Calculate Score Based on Predetermined Factors
5. Output Observation Score
36Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Orbit Determination Process
1. Propagate Orbit Using TLE data to Calculate Expected Initial Inertial Position and Velocity
2. Software Takes Frequency Measurements at Positions at the times Provided by Scheduling Software
3. Frequency Measurement is used to calculate Doppler Shift at each viewing
4. Doppler shift is converted into slant range rate
5. Slant Range Rate is then turned into Orbit Estimate
37Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Orbit Determination Process
1. Propagate Orbit Using TLE data to Calculate Expected Initial Inertial Position and Velocity
2. Software Takes Frequency Measurements at Positions at the times Provided by Scheduling Software
3. Frequency Measurement is used to calculate Doppler Shift at each viewing
4. Doppler shift is converted into slant range rate
5. Slant Range Rate is then turned into Orbit Estimate
38Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Software Input: TLE Data
• Online database of Satellite Information
• Accessible to public
• Not fully accurate
• Includes:• Inclination (i)• Right Ascension of the Ascending Node (Ω)• Eccentricity (e)• Argument of Perigee (ω)• Mean Anomaly (M)• Mean Motion (n)
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Orbit Determination Process
1. Propagate Orbit Using TLE data to Calculate Expected Initial Inertial Position and Velocity
2. Software Takes Frequency Measurements at Positions at the times Provided by Scheduling Software
3. Frequency Measurement is used to calculate Doppler Shift at each viewing
4. Doppler shift is converted into slant range rate
5. Slant Range Rate is then turned into Orbit Estimate
41Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Orbit Determination Process
1. Propagate Orbit Using TLE data to Calculate Expected Initial Inertial Position and Velocity
2. Software Takes Frequency Measurements at Positions at the times Provided by Scheduling Software
3. Frequency Measurement is used to calculate Doppler Shift at each viewing
4. Doppler shift is converted into slant range rate
5. Slant Range Rate is then turned into Orbit Estimate
44Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Orbit Simulation Example (GPS BIIR 8)Rx (km) Ry (km) Rz (km) Vx (m/s) Vy (m/s) Vz (m/s)
TruthPosition & Velocity
8192.2 12225.3 21925.6 -2554.96 2940.54 -80.33
Propagated Position & Velocity
8192.2 12225.3 21925.6 -2554.96 2940.54 -91.54
Percent Error (%)
0 0 0 0 0 13.96
i (deg) e(dim less) ω (deg) Ω (deg) Θ (deg) a(km)
Truth Orbit Elements
57.16 0.129 3.92 310.22 94.88 26558.3
Propagated OrbitElements
57.18 0.127 4.23 310.11 94.64 26561.7
Percent Error (%)
0.0242 1.852 7.69 0.034 0.28 0.013
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Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Orbit Determination Process
1. Propagate Orbit Using TLE data to Calculate Expected Initial Inertial Position and Velocity
2. Software Takes Frequency Measurements at Positions at the times Provided by Scheduling Software
3. Frequency Measurement is used to calculate Doppler Shift at each viewing
4. Doppler shift is converted into slant range rate
5. Slant Range Rate is then turned into Orbit Estimate
47Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Scoring Software Process
1. Choose Satellite & Time of Observation
2. Determine Orbit and Calculate Expected Inertial Position and Velocity of Satellite
3. Determine Azimuth and Elevation Relative to Ground Station
4. Calculate Score Based on Predetermined Factors
5. Output Observation Score
48Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Scoring Software Process
1. Choose Satellite & Time of Observation
2. Determine Orbit and Calculate Expected Inertial Position and Velocity of Satellite
3. Determine Azimuth and Elevation Relative to Ground Station
4. Calculate Score Based on Predetermined Factors
5. Output Observation Score
49Project Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
ValidationProject Plan
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Scoring: Factors and Scores
50Project Overview Design Solution
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Scoring Factors Score Range
• Priority (Multiplier)• Importance viewing the chosen satellite
Value between 1 to 100
• Signal to Noise Ratio (Multiplier)• Ability to discern satellite's signal
0: Below System Threshold1: Above System Threshold
• Visibility (Multiplier)• Satellite is above the horizon
0: No Line of Sight1: Direct Line of Sight
• Number of Satellites within HPBW (Multiplier)• Observing only 1 satellite
0: Greater than 1 or No Satellites1: 1 Satellite
• Orbit Geometry (Function Inversely Proportional to Elevation)• Value based on experimental results
A*cos(Elevation) + C
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Scoring Software Process
1. Choose Satellite & Time of Observation
2. Determine Orbit and Calculate Expected Inertial Position and Velocity of Satellite
3. Determine Azimuth and Elevation Relative to Ground Station
4. Calculate Score Based on Predetermined Factors
5. Output Observation Score
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Scoring Example
• For an observation window of 45 minutes, sampling rate of 1 Hz, a satellite with clear LOS (Line Of Sight), and only 1 Satellite in View,
• If any one of the multiplier condition is not met• Score for viewing = 0
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CPE4 SATISFIED✔
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Scoring Software Process
1. Choose Satellite & Time of Observation
2. Determine Orbit and Calculate Expected Inertial Position and Velocity of Satellite
3. Determine Azimuth and Elevation Relative to Ground Station
4. Calculate Score Based on Predetermined Factors
5. Output Observation Score
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Scheduling Software – CPE5
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• FR 5 - The scheduling software shall develop an observation plan for given satellites
• DR 5.1 - The software shall give the orbit of a satellite within a given timeframe
• DR 5.2 - The software shall calculate the time between each viewing to be made
• DR 5.3 - The software shall determine if an observation can be made
Project Overview Design SolutionCritical Project
ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan
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Scheduling Software: Terminology
• Viewing• An instance of when the antenna is receiving signal from the satellite
• Observation• All required viewings to update the orbital elements
• Observation Spot• A timeframe for an observation to take place
• Scoring List• List containing scores for each satellite for an observation spot
• Observation Plan• The plan that tells the software which satellite to look at and when to start and end
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User Input
1. Satellite Orbit Parameters (TLE Data)
2. Observation Time and Priority
Calculate Orbit ofSatellite during
Observation Timeframe
Determine when Satellite is in Field Of View of
Ground Station
Calculate time between each viewing
Observation is determined and scored
Put Into Scoring List
Scheduling Software
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DR 3.5.1
DR 3.5.2 DR 3.5.3
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Scheduling Software
Calculating Orbit Calculate time in-between Observation Decision
• Use TLE data to get position and velocity of satellite
• Enables the software to be aware of when and for how long the satellite is in view
• Software knows where to look for the satellite next
• Required to get the most information out of the observation
• Depends heavily on the timeframe
• Let's software know when to look for the satellite to get the most information
• Determines if the observation can be made during a particular time
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58Project Overview Design Solution
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• Scores of each observation are needed to fill out Observation Plan
• Scoring List• List of score for each possible observation
• Takes Highest Score per Observation Spot• If two or more same scores, highest priority satellite is picked
• Satellite not picked put back into scoring list to obtain a new score and observation spot
• Software goes through list until all satellites have an observation spots or no more observation spots are available
Observation Plan
CPE5 SATISFIED✔
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Project Risk
59Project Overview Design Solution
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Project Risks
60Project Overview Design Solution
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Risk Matrix
61Project Overview Design Solution
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Risk Mitigation
62Project Overview Design Solution
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Design Requirements
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Risk Mitigation
63Project Overview Design Solution
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Risk Mitigation
64Project Overview Design Solution
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Design Requirements
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Testing, Verification, and Validation
65Project Overview Design Solution
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66Project Overview Design Solution
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Test Schedule
Fall 2019 Scoring Software Orbit DeterminationSoftware
Scheduling Software
Jan 2020 Pointing Control System Lab Test
Signal ReceptionLab Test
Signal Processing Lab Test Software Lab Test (In Conjunction with Hardware)
Feb 2020
Complete System Field TestMarch 2020
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Beam width Requirement:
1. Find max gain
2. Find angle at which gain attenuated by 3 dB
Gain Requirement:
1. Model max power received at 0 dB gain
2. Compare against actual received power
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Signal Reception Test
Dish
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Pointing Controls Test: Resolution• Accuracy of movement
• Equipment: Laser Pointer, wall outlet, grid
• Plan• Attach laser pointer to rotor,
• move controller 1 step,
• measure movement on grid,
• calculate angle moved,
• repeat 10 times.
• Calculate average movement per step and compare to supplier specs
• Measurement issues: Making sure laser pointer is fully secured to the rotor
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Pointing Controls Test: Torque
• Simulate whole dynamic torque mission segment.• Equipment: DYNOmite Dynamometer,• Plan:
• Connect rotor to dynamometer• For a given mission segment, adjust the
applied torque to match the segment torque
• Repeat for each mission segment• Calculate torque profile
• Measurement Issues: Dynamometer is not currently set up, slip in gear connection to the dynamometer.
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Signal Processing Test
70Project Overview Design Solution
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Software Test
• Provide a list of satellites, priorities, and observation times, output scores for satellite & observation time combinations.
• Highest priority satellites need to be viewed first
• Satellites near the horizon need to be viewed first
• Calculate & Update Orbit Elements to Reflect the Satellite's Orbit
• TLE Data is inaccurate
• Compare the Calculated Satellite Orbit to Real-Time Online Satellite Trackers
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Field Tests
• Hardware• Set up system as planned
• Powered through wall outlet• Position and Attitude Determined via GPS & Compass
• Software• Scoring
• Input several satellites and observation times• Output scores for aforementioned satellites
• Scheduling• Schedule observations for satellites and observation opportunities with a non-zero score
• Orbit Determination• Update TLE data based on actual observations• Compare with real-time online satellite trackers
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Project Plan
73Project Overview Design Solution
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Design Requirements
RiskVerification &
ValidationProject Plan
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Organizational Structure
74Project Overview Design Solution
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Design Requirements
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Work Breakdown Structure
75Project Overview Design Solution
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Design Requirements
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= Completed
= Future Work
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Work Plan
76Project Overview Design Solution
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Design Requirements
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Software Development and Testing
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Work Plan
77Project Overview Design Solution
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Component purchases, component testing, and ground station assembly
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Work Plan
78Project Overview Design Solution
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Design Requirements
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Full System integration and testing
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Work Plan
79Project Overview Design Solution
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Design Requirements
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Critical Path
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Cost PlanComponent Cost Allocated
AmountBudget Margin
Antenna $917.55 $1300 29.42%
SDR $919 $1100 16.45%
Antenna Pointing
$855.05 $1400 38.93%
Tripod $419.80 $500 16.04%
Cables and Power Supply
$260.88 $400 34.78%
Mounting $202.84 $300 32.39%
Total $3575.12 $5000 28.50%
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Design Requirements
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Questions
81
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Backup Slides
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Project Motivation
83Project Overview Design Solution
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Design Requirements
RiskVerification &
ValidationProject PlanProject Overview Design Solution
Critical Project Elements
Design Requirements
RiskVerification &
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Critical Project Elements
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Dish Efficiency
• Blockage Efficiency
85
• Feed Efficiency
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Signal Reception with chosen components
86Project Overview Design Solution
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Design Requirements
RiskVerification &
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Full Link Budget
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Signal Reception Satisfaction
88Project Overview Design Solution
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Design Requirements
RiskVerification &
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Pointing Controls - Specifications
89
Additional Accessories
Needed:
PW32015 Power Supply Unit
$110.74
CC8-001 Motor Control Cable (25m)
$102.72
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ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan
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CPE - AntennaGoverning Equations
F = 1+Tr/T0
Ts = Ta + Tr
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Orbit Determination Details
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Orbit Determination: Range Rate
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Scheduling Software: Viewing
• Need to get most information for observation• Depends on time between
(Δt) each viewing
• Δt depends on the position and velocity of the satellite
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Observation Plan Details
• Chance of observation of a satellite depends on priority and quality of all viewings
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Priority• Based on user input• Ensures that more important
satellites, to the user, have a higher chance of being observe
• Not the most important factor
Quality of Viewings• Depends on score of the
viewings• Makes sure that the viewing
gets the most and correct information
• Better scores means higher chance of being observed
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Observation Plan Details
• Creating Priority List• Created from User Input
• List that rearranges the satellites based on priority
• Scoring List• This is done by finding the first time each satellite is in the field of view
• A score is given during that observation window.
• After all satellites have been found, the list is rearranged from highest to lowest score
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Observation Plan Details
• Creation of Observation Plan• The software then goes through the whole list, starting at the highest score,
until either there is no more observation spots, or the list is empty• If an observation spot is taken, the next time the satellite is in the FOV is calculated and
scored. This score is then put back into the list
• If two or more satellites have the same score for an observation spot, the spot goes to the higher priority satellite
• The satellite(s) not picked have their next time in the FOV calculated and scored. This score is then placed back into the list
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Antenna Pick-up to Dish Mount
• GeoSat Pro comes with LNBF Type clamp• Diameter – 40mm
• Logarithmic pickup comes with threaded hole for a tripod mount.• ¼" - 20 thread
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ElementsDesign
RequirementsRisk
Verification & Validation
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Antenna Dish to Pointer Mount
• Material: Aluminum 6061 T6
• Max allowable force:• 8885.59 N
• Static Force:• 56.0456 N
• sF = 317.084
• Max Dynamic Force:
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Tripod
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STR-01 – RFHamdesign• Height: 0.67 to 0.83 m
• Weight: 11 kg
• Max load: 30 kg
• Price: $419.8
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RequirementsRisk
Verification & Validation
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Software Verification
MATLAB Unit Verification
• Calculate Doppler Shift for Test Case (FR 3.4)
• Calculate Orbit Elements for Test Case (FR 3.4)
• Calculate Eigenvalues for Test Case (FR 3.5)
MATLAB Integration Verification
• Input Test Case into Full Simulation (FR 3.4 & FR 3.5)
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Functional Testing:• Unit Testing• Integration
TestingNon-Function Testing:• Performance
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ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan
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Power
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• Power Margin: 360 W
• Current Margin: 1.69 A
• Voltage Drop: 0.5 VAC (negligible)
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ElementsDesign
RequirementsRisk
Verification & Validation
Project Plan
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Functional Requirements
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FR 3.1: Receive radio frequency (RF) signals from satellites in various conditions, with various orbital geometries
FR 3.2: Point system along orbit path from manual input with 1° pointing accuracy
FR 3.3: Convert L1 band analog RF signal into a digital signal to calculate Doppler shift
FR 3.4: The scoring software shall provide orbit estimates and scores for each planned observation
FR 3.5: The scheduling software shall develop an observation scheduling plan for a given satellite.