Delta Telemetry Tracking Network BOEING

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Delta Launch Vehicle Flight Data Collection & Display: 

Delta Launch Vehicle Flight Data Collection & Display Cheree Kiernan, Michael Taylor Boeing Delta Expendable Launch Vehicle Programs


Overview Flight Data Collection Pre-launch Analysis Architecting a Telemetry Tracking Network Flight Imagery Collection Real-time Situational Awareness Flight Visualization Acquisition Assistance Post-flight Assessment Tracking Network Performance Anomaly Resolution USAF Heavy Demo Scenario

Application of STK within Delta Flight Operations: 

Application of STK within Delta Flight Operations Pre-launch Flight Data Collection Analysis Flight telemetry coverage analysis Deployable telemetry station siting Solar conjunction analysis Link margin analysis Acquisition assistance message processing Flight imagery assessment Real-time situational awareness Use real-time or last known flight position and velocity to determine rise and set time at tracking stations Post-flight Analysis/Anomaly Resolution Compare tracking network antenna pointing to flight trajectory

Software in use: 

Software in use STK: STK PRO, AVO, Connect, Chains, Terrain modules SLC-37 & Delta IV Heavy model (thank you Scott Cross!) Imagery Terraserver for 1 meter resolution at CCAFS & VAFB MODIS 250m imagery for Florida, Bahamas, California Blue Marble 1 km global imagery Terrain USGS GEM data for Vandenberg, SRTM data for California SRTM DTED data for rest of planet Boeing STICS Lab Software SPAM processor (telemetry front end, EU conversion) grokc (graphical rendering of kinematics – c): Event Monitoring and Detection, conversion to earth fixed coordinates, TCP/IP connection to STK

Pre-Launch Analysis: Siting a Deployable Asset: 

Pre-Launch Analysis: Siting a Deployable Asset Short-notice need for deployable ground station STK supports immediate analysis of site feasibility (e.g. pass geometry, obscura, solar conjunctions) Prior to implementation of STK capability A short-notice deployment made adjacent to a fixed site resulted in the deployable missing spacecraft sep Obscurra analysis now reduces the probability of repeating this mistake

Pre-Launch Analysis: Flight Imagery Aspect Angle: 

Pre-Launch Analysis: Flight Imagery Aspect Angle Requirement for unobstructed imagery of particular mission events (e.g. liftoff, solid rocket motor separation, Max-Q, etc) Finite supply of cameras Multiple points of interest on the vehicle Camera site considerations LV Attitude LV Obstruction (e.g. Solid Rocket Motors, Common Booster Cores, Fixed Umbilical Tower etc) Sun angle Playalinda Beach DOAMS Universal Camera Site 23 Cocoa Beach DOAMS Example: Delta IV interstage (located near triangular blue Delta logo) during Heavy Demo transsonic flight

Real-Time Situational Awareness: 

Real-Time Situational Awareness GROK first used on Globalstar-3 (June 1999) Used GROK C code with modifications to send STK connect commands Allows 5 years of experience in event detection & noise filtering Heavy Demo was first experience in using STK in a real time application, and just in time! Off-nominal performance Use of STK to aid station acquisition, critical to flight data collection

Connect Commands Employed: 

Connect Commands Employed Commands send every two seconds: SetPosition SetAttitude Engine Gimbal Angles Commands sent upon event detection: Solid motor ignition/burnout/jettison Stage 1-2 separation (and stage 2-3 separation for Delta II) Nozzle extension Fairing Jettison Engine burns Spacecraft separation Manual commands available Reassemble launch vehicle stack to pre-liftoff configuration Set vehicle to on-orbit configuration Jettison spacecraft

Post-Flight Analysis: Station failure to acquire LV: 

Post-Flight Analysis: Station failure to acquire LV Typically hardware anomalies (e.g. cable wrap, antenna drive failure, etc) or operator error In the case of Delta II SIRTF, an acquisition assistance message was generated using a different coordinate system than the antenna control unit which led to a missed pass CAUTION: Configuration Management Strict attention to detail Acquisition assistance message Actual ACU pointing


USAF Heavy Demo Example

Delta IV USAF Heavy Demo: 

Delta IV USAF Heavy Demo HLV Description LV Height: 235 ft LV Width: 53 ft LV Liftoff Weight: 1,627,038 lbs Payload Primary: DemoSat (Boeing) Weight: 13,500 lbs Secondary: NanoSat (Ralphie and Sparky) Weight: 110 lbs Day of Launch Launch Date: December 21, 2004 Orbit Parameters Altitude (nmi): 19,623 (based on a 3443.918 nmi Earth radius) Inclination (deg): 10 RAAN (deg): 146.04

Data Flow: 

Data Flow 1.92Mbps PCM Data STK/Connect Commands Telemetry Conversion Position Attitude Model Articulations Delta IV Operations Center Data Collection Data Display Data Distribution & Conversion Huntington Beach, CA

Real Time Example: Heavy Demo - Ascent: 

Real Time Example: Heavy Demo - Ascent Pre-mature cutoff of all three Common Booster Core engines resulted in first stage velocity shortfall Second stage guidance attempted to make up performance, but vehicle not in expected location at first and second engine cutoffs STK provided real time situational awareness of present vehicle location & angles to all tracking stations predicted actual T+767.8 s View from Cape Verde @ T+945 s 231 km predicted actual



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