Presentation by Jim Taylor (Ares Projects Flight & Integrated Test Office Manager, NASA) at the Von Braun Memorial Symposium in Huntsville, Alabama, 21 October 2008.
<a href="http://astronautical.org/vonbraun/vonbraun-2008/session1">http://astronautical.org/vonbraun/vonbraun-2008/session1</a>
Presentation by Jim Reuter (Ares Vehicle Integration Manager, NASA) at the Von Braun Memorial Symposium in Huntsville, Alabama, 21 October 2008.
<a href="http://astronautical.org/vonbraun/vonbraun-2008/session1">http://astronautical.org/vonbraun/vonbraun-2008/session1</a>
Presentation by Jim Taylor (Ares Projects Flight & Integrated Test Office Manager, NASA) at the Von Braun Memorial Symposium in Huntsville, Alabama, 21 October 2008.
<a href="http://astronautical.org/vonbraun/vonbraun-2008/session1">http://astronautical.org/vonbraun/vonbraun-2008/session1</a>
Presentation by Jim Reuter (Ares Vehicle Integration Manager, NASA) at the Von Braun Memorial Symposium in Huntsville, Alabama, 21 October 2008.
<a href="http://astronautical.org/vonbraun/vonbraun-2008/session1">http://astronautical.org/vonbraun/vonbraun-2008/session1</a>
A400M Flight Test Update: May 2012
These slides were presented during the Trade Media 2012 event held at Madrid, Spain and Toulouse, France in May 2012.
The presentation was made by Fernando Alonso, SVP Flight and Integration Tests for Airbus Military.
The A400M through May 16, 2012 has flown 3,212 hours over 1,094 flights. And these flights and tests have been conducted worldwide.
Alonso discussed as well the evolving tanker tests for the A400M. The key point is that the tanking tests to date have indicated no real problems with the design of the aircraft with regard to integrating a tanker function.
The journalists attending the Trade Media event were able to visit in small groups Grizzly 3 and to talk to the crew as well.
What's inside a Cessna 172 and flying a light planeyeokm1
A talk I gave at Hackware v5.0 on the components inside a Cessna 172, planning and making a flight.
Video of this talk: https://www.youtube.com/watch/?v=GtT5wCYhZBA
This presentation and accompanying methodological summary compares the environmental effectiveness of candidate metrics and test points for an ICAO CO2 standard. Two primary comparisons are made: between metrics with simple payload components (e.g. ton-km and seat-km) and those which include proxies of aircraft productivity (e.g. take-off weight and useful load), and between a standard measured at maximum aircraft potentials (here, maximum range at maximum payload) vs. at a test point more representative of actual operations.
NAUTILUS-X Future in Space Operations (FISO) Group PresentationA. Rocketeer
Nautilus-X: A presentation at the Future In Space Operations teleconference on Jan 26th 2011, given by Mark Holderman and Edward Henderson of NASA JSC.
F and G Taylor Series Solutions to the Circular Restricted Three-Body ProblemEtienne Pellegrini
Presentation given at the AAS/AIAA Space Flight Mechanics Meeting in Santa Fe, NM, on 1/27/2014
The Circular Restricted Three-Body Problem is solved using an extension to the classic F
and G Taylor series. The Taylor series coefficients are developed using exact recursion formulas, which are implemented via symbolic manipulation software. In addition, different
time transformations are studied in order to obtain an adapted discretization for the three-body problem. The resulting propagation method is compared to a conventional numerical
integration method, the Runge-Kutta-Fehlberg integrator, on a set of test scenarios designed to qualitatively represent the different types of three-body motion. The series solution is demonstrated to have comparable performance to the conventional integrator, when considering a variety of circumstances, such as the independent variable, error tolerance, orbit characteristics, and integration scheme. In the variable-step case, for low-fidelity applications, such as preliminary design of trajectories, the F and G series with no time transformation are shown to be two to three times faster than the conventional integrator in all cases, when selecting an appropriate order. In the fixed-step case, the Sundman time transformations are demonstrated to reduce the number of steps required for convergence by one or more orders of magnitude. This improved discretization confirms the value of regularization in the restricted three-body problem, and suggests the utility of fixed-step integration using Sundman transformed equations of motion.
A400M Flight Test Update: May 2012
These slides were presented during the Trade Media 2012 event held at Madrid, Spain and Toulouse, France in May 2012.
The presentation was made by Fernando Alonso, SVP Flight and Integration Tests for Airbus Military.
The A400M through May 16, 2012 has flown 3,212 hours over 1,094 flights. And these flights and tests have been conducted worldwide.
Alonso discussed as well the evolving tanker tests for the A400M. The key point is that the tanking tests to date have indicated no real problems with the design of the aircraft with regard to integrating a tanker function.
The journalists attending the Trade Media event were able to visit in small groups Grizzly 3 and to talk to the crew as well.
What's inside a Cessna 172 and flying a light planeyeokm1
A talk I gave at Hackware v5.0 on the components inside a Cessna 172, planning and making a flight.
Video of this talk: https://www.youtube.com/watch/?v=GtT5wCYhZBA
This presentation and accompanying methodological summary compares the environmental effectiveness of candidate metrics and test points for an ICAO CO2 standard. Two primary comparisons are made: between metrics with simple payload components (e.g. ton-km and seat-km) and those which include proxies of aircraft productivity (e.g. take-off weight and useful load), and between a standard measured at maximum aircraft potentials (here, maximum range at maximum payload) vs. at a test point more representative of actual operations.
NAUTILUS-X Future in Space Operations (FISO) Group PresentationA. Rocketeer
Nautilus-X: A presentation at the Future In Space Operations teleconference on Jan 26th 2011, given by Mark Holderman and Edward Henderson of NASA JSC.
F and G Taylor Series Solutions to the Circular Restricted Three-Body ProblemEtienne Pellegrini
Presentation given at the AAS/AIAA Space Flight Mechanics Meeting in Santa Fe, NM, on 1/27/2014
The Circular Restricted Three-Body Problem is solved using an extension to the classic F
and G Taylor series. The Taylor series coefficients are developed using exact recursion formulas, which are implemented via symbolic manipulation software. In addition, different
time transformations are studied in order to obtain an adapted discretization for the three-body problem. The resulting propagation method is compared to a conventional numerical
integration method, the Runge-Kutta-Fehlberg integrator, on a set of test scenarios designed to qualitatively represent the different types of three-body motion. The series solution is demonstrated to have comparable performance to the conventional integrator, when considering a variety of circumstances, such as the independent variable, error tolerance, orbit characteristics, and integration scheme. In the variable-step case, for low-fidelity applications, such as preliminary design of trajectories, the F and G series with no time transformation are shown to be two to three times faster than the conventional integrator in all cases, when selecting an appropriate order. In the fixed-step case, the Sundman time transformations are demonstrated to reduce the number of steps required for convergence by one or more orders of magnitude. This improved discretization confirms the value of regularization in the restricted three-body problem, and suggests the utility of fixed-step integration using Sundman transformed equations of motion.
This PowerPoint is one small part of the Astronomy Topics unit from www.sciencepowerpoint.com. This unit consists of a five part 3000+ slide PowerPoint roadmap, 12 page bundled homework package, modified homework, detailed answer keys, 8 pages of unit notes for students who may require assistance, follow along worksheets, and many review games. The homework and lesson notes chronologically follow the PowerPoint slideshow. The answer keys and unit notes are great for support professionals. The activities and discussion questions in the slideshow and meaningful. The PowerPoint includes built-in instructions, visuals, and follow up questions. Also included are critical class notes (color coded red), project ideas, video links, and review games. This unit also includes four PowerPoint review games (110+ slides each with Answers), 38+ video links, lab handouts, activity sheets, rubrics, materials list, templates, guides, and much more. Also included is a 190 slide first day of school PowerPoint presentation. Teaching Duration = 5+ weeks. Areas of Focus in the Astronomy Topics Unit: The Solar System and the Sun, Order of the Planets, Our Sun, Life Cycle of a Star, Size of Stars, Solar Eclipse, Lunar Eclipse, The Inner Planets, Mercury, Venus, Earth, Moon, Craters, Tides, Phases of the Moon, Mars and Moons, Rocketry, Asteroid Belt, NEOs, The Torino Scale, The Outer Planets and Gas Giants, Jupiter / Moons, Saturn / Moons, Uranus / Moons, Neptune / Moons, Pluto's Demotion, The Kuiper Belt, Oort Cloud, Comets / Other, Beyond the Solar System, Types of Galaxies, Blackholes, Extrasolar Planets, The Big Bang, Dark Matter, Dark Energy, The Special Theory of Relativity, Hubble Space Telescope, Constellations, Spacetime and much more. If you have any questions please feel free to contact me. Thanks again and best wishes. Sincerely, Ryan Murphy M.Ed www.sciencepowerpoint@gmail.com
The Mission Concept Review affirms the mission need and examines the proposed mission's objectives and the concept for meeting those objectives. (Cited from NASA Procedural Requirements)
he presence of civil aviation has affected our economic way of
life, it has made changes in our social and cultural viewpoints, and
has had a hand in shaping the course of political history.
The sociological changes brought about by air transportation are
perhaps as important as those it has brought about in the economy.
People have been brought closer together and so have reached a better understanding of interregional problems. Industry has found new
ways to do business. The opportunity for more frequent exchanges of
information has been facilitated, and air transport is enabling more
people to enjoy the cultures and traditions of distant lands.
In recent years, profound changes in technology and policy have
had significant impacts on civil aviation and its supporting airport
infrastructure. The industry continues to grow in numbers of aircraft,
passengers and cargo carried, and markets served, from nonstop
service on superjumbo aircraft between cities half-way across the
planet, to privately operated “very light jets” between any of thousands of small airports domestically. Growth encouraged from technological advancements countered with increased constraints on the
civil aviation system due to increased capacity limitations, security
regulations, and financial constraints have resulted in ever increasing
challenges to airport planning and design.
Civil aviation is typically considered in three sectors, commercial
service aviation (more commonly known as air carriers or airlines), air
cargo, and general aviation. Although the lines between these traditional sectors are becoming increasingly blurred, the regulations
and characteristics regarding their individual operations are often
mutually exclusive, and as such, those involved in airport planning
and design should have an understanding of each sector
Similar to Charger Rocket Works PDR: 2009-2010 (20)
Let's dive deeper into the world of ODC! Ricardo Alves (OutSystems) will join us to tell all about the new Data Fabric. After that, Sezen de Bruijn (OutSystems) will get into the details on how to best design a sturdy architecture within ODC.
PHP Frameworks: I want to break free (IPC Berlin 2024)Ralf Eggert
In this presentation, we examine the challenges and limitations of relying too heavily on PHP frameworks in web development. We discuss the history of PHP and its frameworks to understand how this dependence has evolved. The focus will be on providing concrete tips and strategies to reduce reliance on these frameworks, based on real-world examples and practical considerations. The goal is to equip developers with the skills and knowledge to create more flexible and future-proof web applications. We'll explore the importance of maintaining autonomy in a rapidly changing tech landscape and how to make informed decisions in PHP development.
This talk is aimed at encouraging a more independent approach to using PHP frameworks, moving towards a more flexible and future-proof approach to PHP development.
Accelerate your Kubernetes clusters with Varnish CachingThijs Feryn
A presentation about the usage and availability of Varnish on Kubernetes. This talk explores the capabilities of Varnish caching and shows how to use the Varnish Helm chart to deploy it to Kubernetes.
This presentation was delivered at K8SUG Singapore. See https://feryn.eu/presentations/accelerate-your-kubernetes-clusters-with-varnish-caching-k8sug-singapore-28-2024 for more details.
Key Trends Shaping the Future of Infrastructure.pdfCheryl Hung
Keynote at DIGIT West Expo, Glasgow on 29 May 2024.
Cheryl Hung, ochery.com
Sr Director, Infrastructure Ecosystem, Arm.
The key trends across hardware, cloud and open-source; exploring how these areas are likely to mature and develop over the short and long-term, and then considering how organisations can position themselves to adapt and thrive.
UiPath Test Automation using UiPath Test Suite series, part 3DianaGray10
Welcome to UiPath Test Automation using UiPath Test Suite series part 3. In this session, we will cover desktop automation along with UI automation.
Topics covered:
UI automation Introduction,
UI automation Sample
Desktop automation flow
Pradeep Chinnala, Senior Consultant Automation Developer @WonderBotz and UiPath MVP
Deepak Rai, Automation Practice Lead, Boundaryless Group and UiPath MVP
DevOps and Testing slides at DASA ConnectKari Kakkonen
My and Rik Marselis slides at 30.5.2024 DASA Connect conference. We discuss about what is testing, then what is agile testing and finally what is Testing in DevOps. Finally we had lovely workshop with the participants trying to find out different ways to think about quality and testing in different parts of the DevOps infinity loop.
Epistemic Interaction - tuning interfaces to provide information for AI supportAlan Dix
Paper presented at SYNERGY workshop at AVI 2024, Genoa, Italy. 3rd June 2024
https://alandix.com/academic/papers/synergy2024-epistemic/
As machine learning integrates deeper into human-computer interactions, the concept of epistemic interaction emerges, aiming to refine these interactions to enhance system adaptability. This approach encourages minor, intentional adjustments in user behaviour to enrich the data available for system learning. This paper introduces epistemic interaction within the context of human-system communication, illustrating how deliberate interaction design can improve system understanding and adaptation. Through concrete examples, we demonstrate the potential of epistemic interaction to significantly advance human-computer interaction by leveraging intuitive human communication strategies to inform system design and functionality, offering a novel pathway for enriching user-system engagements.
GraphRAG is All You need? LLM & Knowledge GraphGuy Korland
Guy Korland, CEO and Co-founder of FalkorDB, will review two articles on the integration of language models with knowledge graphs.
1. Unifying Large Language Models and Knowledge Graphs: A Roadmap.
https://arxiv.org/abs/2306.08302
2. Microsoft Research's GraphRAG paper and a review paper on various uses of knowledge graphs:
https://www.microsoft.com/en-us/research/blog/graphrag-unlocking-llm-discovery-on-narrative-private-data/
UiPath Test Automation using UiPath Test Suite series, part 4DianaGray10
Welcome to UiPath Test Automation using UiPath Test Suite series part 4. In this session, we will cover Test Manager overview along with SAP heatmap.
The UiPath Test Manager overview with SAP heatmap webinar offers a concise yet comprehensive exploration of the role of a Test Manager within SAP environments, coupled with the utilization of heatmaps for effective testing strategies.
Participants will gain insights into the responsibilities, challenges, and best practices associated with test management in SAP projects. Additionally, the webinar delves into the significance of heatmaps as a visual aid for identifying testing priorities, areas of risk, and resource allocation within SAP landscapes. Through this session, attendees can expect to enhance their understanding of test management principles while learning practical approaches to optimize testing processes in SAP environments using heatmap visualization techniques
What will you get from this session?
1. Insights into SAP testing best practices
2. Heatmap utilization for testing
3. Optimization of testing processes
4. Demo
Topics covered:
Execution from the test manager
Orchestrator execution result
Defect reporting
SAP heatmap example with demo
Speaker:
Deepak Rai, Automation Practice Lead, Boundaryless Group and UiPath MVP
3. PDR Objectives Introduce vehicle and payload design to USLI engineering review board Confirm vehicle and payload design meet USLI competition requirements Evaluate safety and mission assurance plans Demonstrate flight operations can be executed safely Detail cost and schedule for production, testing and operations Address risks and impacts to vehicle, cost, and schedule
4. Mission Statement USLI Mission Statement: The NASA University Student Launch Initiative is a competition that challenges university level students to design, build, and fly a reusable rocket with a scientific payload to one mile in altitude. The project engages students in scientific research and real-world engineering processes with NASA Engineers. (Cited from the NASA Education Website) Charger Rocket Works Mission Statement: Further our understanding of the science and engineering of high powered rocket thru developing and flight testing. Build a knowledge base with which to achieve even greater heights. Reach out to educate and inspire others to pursue a future in science, technology, engineering, and mathematics.
5. Project Overview Bellerophon & Pegasus Greek hero Bellerophon slew the Chimera on the back of the winged horse Pegasus. Pegasus : booster stage – homage to UAHuntsville’s mascot Bellerophon: payload - autonomous hybrid lander Bellerophon Pegasus
6. Project Overview Team Objectives Develop in-house airframe manufacturing capability* Develop a safe and reusable rocket with operations procedures** Reach closest to 1 mile in altitude*** Recover Bellerophon and Pegasus intact Successfully demonstrate a mechanical recovery release system Successfully demonstrate the Bellerophon hybrid lander Reach out to 500+ students in the local area
7. Project Overview Mission Description Bellerophon & Pegasus launch preparation and walk-out Avionics and payload power up (1.5 hr max pad-stay) Launch, powered flight, & coast Bellerophon & Pegasus separate at apogee and descend on drogue Bellerophon parasail deploys at 700 feet altitude and begins flight maneuvers Pegasus main parachute deploys at 500 feet altitude Bellerophon & Pegasus touch down and are recovered Flight data is downloaded and stored for reduction Official altitude is recorded for competition
8. Vehicle CriteriaStructures Accomplishments since proposal: 4 inch mandrel delivered for subscale and 98mm motor tubes* Carbon fiber airframe manufactured in-house for subscale* Successfully flight tested subscale rocket** Verified in-house tube manufacturing as viable path forward for full scale rocket development Vacuum bag capability being matured* Work In Progress Developing procedures for in-house airframe manufacturing** Developing fiberglass laminated phenolic honeycomb core material for centering rings and bulkplates Preparing 6 inch mandrel for full scale rocket tubes* Strength testing carbon fiber tubes**
9. Vehicle CriteriaStructures Subscale Design Description (flight tested) 4 inches diameter & 68 inches overall vehicle length 10 lbs pad weight Carbon fiber airframe & phenolic coupler Four G-10 Garolite clipped delta fins Urethane 5:1 ogive nosecone 54mm phenolic motor tube ¾ inch plywood centering rings and bulkplates First Flight Performance: 0.99 calibur static stability margin – balanced (field) 0.28 drag coeffiecient 3540 feet altitude Many lessons learned
10. Vehicle CriteriaStructures Full Scale - Design Description (Baseline) 6 inches diameter & 102 inches overall vehicle length 32 lbs pad weight (with Aerotech L1150R loaded) Carbon fiber airframe & fiberglass coupler Four G-10 Garolite clipped delta fins 6 inch diameter fiberglass 5:1 ogive nosecone 98mm carbon fiber motor tube ¾ inch birch plywood centering rings & baseplates Baseline Performance Predictions: 1.43 calibur static stability margin – hand calculated 0.34 drag coefficient
11. Vehicle CriteriaPropulsion Accomplishments since proposal: Static test fired 4 motors Developed procedures for conducting static test firings** Validated subscale computer model with flight data (Cd)** Verified subscale model stability with hand-calculations** Baselined full scale competition motor – Aerotech L1150R*** Work In Progress: Optimizing full scale computer model Ordered full scale demonstration motor for verification test Baseline Performance Predictions: Thrust to Weight Ratio of 7.2 Velocity off the pad of 60 ft/sec Maximum Altitude of 5280 ft
12. Payload & Recovery Criteria Integrated Payload and Recovery Systems are closely linked Promotes commonality & improves reliability Reliability & Redundancy Bellerophon & Pegasus use mechanical release device (baseline) Mechanical releases triggered by altimeter activated servos Bellerophon & Pegasus use independent altimeters Altimeters have dedicated batteries & switches Pegasus Recovery System (Full Scale) Drogue: B2Rocketry 24 inch parachute(75 ft/sec decent rate) Main: B2Rocketry Cert-3 XXL parachute (15 ft/sec decent rate) D-Bag: B2Rocketry XXL deployment bag
13. Payload & Recovery Criteria Support Line Anchor Bellerophon Hybrid Lander Nosecone contains GN&C system Autonomous / manual override capable Drogue: B2Rocketry 24 inch parachute (75 ft/sec decent rate) Parasail: 2.75 AR & Spans 8 feet (15 ft/sec static decent rate) Control Lines Servos
14. Payload & Recovery Criteria Accomplishments since proposal: Flight tested prototype mechanical release device Flight tested prototype hybrid lander with R/C servos Work in Progress: Mature mechanical released device design Mature requirements for parasail configuration Building payload mass simulators for iterated subscale flight testing Developing hybrid lander ground test schedule to support flight test schedule Developing autonomous flight controller
15. Verification and Testing Approach A – Mission: Subscale rocket flight test Flight test mechanical release device with two parachutes (no parasail) Mass simulator for R/C parasail control & nosecone payloads Flight test of deployment bags B – Mission: Subscale rocket flight test Flight test mechanical release device with parachute/parasail (static) Mass simulator for R/C parasail control & nosecone payloads Flight test of deployment bags C – Mission: Subscale rocket flight test Flight test mechanical release device with parachute/parasail (static) Integrated Flight test of R/C parasail control system Mass simulator for nosecone payloads Flight test of deployment bags
16. Verification and Testing Approach D – Mission: Full scale rocket flight test – sub altitude Flight test of mechanical release device two parachutes (no parasail) Mass simulator for R/C parasail control & nosecone payloads Flight test deployment bags E – Mission: Full scale rocket flight test – 1 mile Flight Test of mechanical recovery mechanism with parachutes and parasail (static) Mass simulator for R/C parasail control & nosecone payloads Test deployment bags F – Mission “Full-Up”: Full scale rocket flight test – 1 mile Flight Test of mechanical recovery mechanism with parachutes and parasail Integrated Flight Test of R/C parasail control & nosecone payloads Test deployment bags
17. Verification and Testing Approach Flight Test Schedule: Dec.12-13, 2009: A – Mission Jan. 16-17, 2010: B – Mission Feb. 13-14, 2010: C – Mission/ D – Mission March 6-7, 2010: E – Mission March 27-28, 2010: F – Mission April 10-11, 2010: (Optional) Ground Test Schedule: In development to support flight test objectives
18. Safety Tools Safety Briefings: A now standard practice before conducting any construction project, and ground or flight test. Participating individuals are briefed of responsibilities, procedures, likely hazards, and actions to take in the event of an accident or hazard. Participants are briefed on the need and the proper use of safety equipment. Written Procedures: Developed for all construction projects, ground and flight tests. Improved knowledge base, effectiveness, and safety between leaving and incoming team members. MSDS: Available in the lab and audited once at the beginning of the semester
19. Safety Tools Existing Procedures: Static Motor Test Firing Stand Setup and Test Conduction Carbon Fiber Tubing Layup and Curing Launch Day Checklist Procedures in work: Black Powder & Ground Based Recovery Testing Parachute Folding Procedures Mechanical Release Testing Launcher Assembly and Usage
20. Risk Mitigation Identified risks to vehicle, schedule, & cost Potential outcome of failure Steps taken to mitigate those risks Need to rank risk from most likely to least