Solar Sails for Exploration of the Interstellar Medium January 2015
|
|
|
- Horatio Jenkins
- 5 years ago
- Views:
Transcription
1 Solar Sails for Exploration of the Interstellar Medium January
2 The Sails We Need* Size: 75,000 m 2 to 250,000 m 2 Areal density: ~ 1 gram/m 2 Able to survive close solar deployment ( AU) * Based on previous studies 2
3 The Sails We Have are not close to what we need NanoSail-D as seen from the ground IKAROS in deep space Size: ~100 m 2 to ~200 m 2 Areal density: gram/m 2 Able to survive 0.5 AU deployment 3
4 Interplanetary Kite-craft Accelerated by Radiation of the Sun (IKAROS) IKAROS was launched on May 21, 2010 IKAROS has demonstrated deployment of a solar sailcraft, acceleration by photon pressure, and attitude control. Deployment was by centrifugal force Configuration / Body Diam. Configuration / Membrane Weight 1.6 m x Height 0.8 m (Cylinder shape) Square 14 m and diagonal 20 m Mass at liftoff: about 310 kg. 4
5 IKAROS Selfies 5
6 NASA s Sunjammer Canceled Design Heritage Cold Rigidization Boom Technology Distributed Load Design Aluminized Sun Side High Emissivity Eclipse Surface Beam Tip Vane Control Spreader System Design 83 m 2 ISP L Garde Solar Sail 2004 Design Features 318 m 2 ISP L Garde Solar Sail 2005 High Density Packagability Controlled Linear Deployment Structural Scalability Propellantless Operation Meets Current Needs 1200 m 2 L Garde Sunjammer Mission Concept 6
7 Many Small Missions Planned NASA s NEA Scout and Lunar Flashlight The Planetary Society s LightSail-A and LightSail-B The University of Surrey s CubeSail, DeorbitSail, and InflateSail ESA and DLR s Gossamer 1 and Gossamer-2 7
8 LightSail-A and -B 3U Cubesat design Sail Material: aluminized 4.5 micron Mylar film 32 square meters solar sail area fully deployed LightSail-A (2015) and LightSail-B (2016) 8
9 ESA s Gossamer Gossamer-1: Demonstration of the safe deployment of a 5m x 5m solar sail in a 320km Earth orbit. Gossamer-2: Deployment of a 20m x 20m solar sail in a 500km Earth orbit. DLR Boom Deployment Mechanism Gossamer-3: Deployment of a 50m x 50m solar sail in a > km Earth orbit. 9 9
10 University of Surrey s CubeSail 25 m 2 solar sail / drag sail 700 km sun-synchronous orbit 10
11 University of Surrey s InflateSail InflateSail is an inflatable, rigidisable sail to be flown in Low Earth Orbit. 3U CubeSat with deployed sail area of 10 m 2 Sail supported by CFRP bistable booms. Inflation is driven by Cool Gas Generators (CGG): low system mass, long lifespan. 11
12 Near Earth Asteroid Scout The Near Earth Asteroid Scout Will Image/characterize a NEA during a slow flyby Demonstrate a low cost asteroid reconnaissance capability Key Spacecraft & Mission Parameters 6U cubesat (20 cm X 10 cm X 30 cm) ~85 m 2 solar sail propulsion system Manifested for launch on the Space Launch System (EM-1/2017) Up to 2.5 year mission duration 1 AU maximum distance from Earth Solar Sail Propulsion System Characteristics ~ 7.3 m Trac booms 2.5m aluminized CP-1 substrate > 90% reflectivity 12
13 NEA SCOUT SAIL APPROXIMATE SCALE Human 6U Stowed Flight System Deployed Solar Sail Deployed Solar Sail School Bus Folded, spooled and packaged in here 13
14 Lunar Flashlight 85 m 2 solar sail Interplanetary 6U Cubesat
15 Solar Sail Performance Data Spacecraft A/m [m 2/ kg]* IKAROS - JAXA 1.3 Nanosail-D NASA 2.2 Cosmos 1 The Planetary Society 5.7 LightSail - The Planetary Society 7.0 Lunar Flashlight/NEA Scout - JPL 8.0 Sunjammer Developed 22 JPL NIAC Study 368 JPL Near ISM Mission Study 700 JPL Halley Comet Rendezvous Design 711 * Calculated using the total spacecraft mass (not just the sail subsystem)
16 Business As Usual (Best Case!) Expectations for Sails NEA Scout Lunar Flashlight ATP m 2 30 g/m 2 (sail system) THE NEED Size: 75,000 m 2 to 250,000 m 2 Areal density: ~ 1 gram/m AU Deployment 32 m 2 LightSail A/B 2015 /
17 Business As Usual (Best Case!) Expectations for Sails NEA Scout Lunar Flashlight ATP m 2 30 g/m 2 (sail system) THE NEED Size: 75,000 m 2 to 250,000 m 2 Areal density: ~ 1 gram/m AU Deployment LightSail A/B 2015 / m 2 Tech Demo 2 20 g/m 2 10,000 m 2 ATP Flight Tech Demo 1 30 g/m m 2 ATP Flight
18 Business As Usual (Best Case!) Expectations for Sails NEA Scout Lunar Flashlight ATP m 2 30 g/m 2 (sail system) THE NEED Size: 75,000 m 2 to 250,000 m 2 Areal density: ~ 1 gram/m AU Deployment LightSail A/B 2015 / m 2 Tech Demo 1 30 g/m m 2 ATP Flight Tech Demo 2 20 g/m 2 10,000 m 2 ATP Flight REALITY Sunjammer cancellation is huge setback Sail are not a priority in NASA Tech Roadmaps Even if support is strong, we cannot meet the goal by
19 Alternative Sail Future Seek a Breakthrough NEA Scout Lunar Flashlight ATP THE NEED Size: 100,000 m 2 to 250,000 m 2 Areal density: < 1 gram/m 2 <0.1 AU Deployment LightSail A/B 2015 / 2016 Aggressive materials R & D Alternate deployment technology Beamed energy R & D Tech Demo 100,000 m 2 ATP Flight LEAPFROG Continue incremental sail development Focus on innovative materials, packaging and deployment UV evaporative materials High temperature tolerance Alternate stabilization and deployment approaches In Space Fabrication (SpiderFab)
20 Items to trade for more capable solar sails (1/2) Traditional Large Sail Technology Development Big square sails (Sunjammer, ATK) Gyula Greschik's Space Tow Ultrasail heliogyro or ribbon sails High temperature materials and structures Lightweight sails Reduce support structure Spinning ala IKAROS R&D into adding spin rate control Tent of reflective control material Shape deformation to create pinwheel effect Inflatable booms to deploy sail, vent from tips to spin, deflate to form tethers or detach altogether 20
21 Items to trade for more capable solar sails (2/2) Lightweight sails Electrostatic structures: Minimal sail film Sublimating sail support film Heavy plastic support film that detaches from minimal sail film Electrostatic charging to repel sail film from backing Start with sail design optimized for in-space use without regard for folding and deployment High strength fiber triangular mesh with metal-only sail films held by foil springs to corners of mesh Add deployment and deployment hardware separation system In-space manufacturing to optimize mass & size Continuous 3D printed structures or sail membranes Sail materials shipped up in bulk and robotically assembled 21
CONVENTIONAL ROCKET PROPULSION NON-CONVENTIONAL PROPULSION SOLAR SAILS TETHERS ELECTRIC SAILS
CONVENTIONAL ROCKET PROPULSION NON-CONVENTIONAL PROPULSION SOLAR SAILS TETHERS ELECTRIC SAILS THE REASON? DISTANCE!!! CONVENTIONAL ROCKET PROPULSION NON-CONVENTIONAL PROPULSION SOLAR SAILS TETHERS ELECTRIC
Team Members. Surrey Space Centre (SSC): Study lead, payloads, ADCS (with Prof. Bong Wie), SK platform, sail technologies
A Solar Kite Mission to Study the Earth's Magneto-tail Dr. Vaios Lappas C. Underwood, Luis M. Gomes, B. Wie C. McInnes, L. Tarabini, K. Wallace + 18th AIAA/USU Small Satellite Conference 18 AIAA/USU Small
Títol PFC: Design of a Solar Sail as the Propulsion System for a Nanosatellite
Titulació: Enginyeria Aeronàutica Superior Alumne (nom i cognoms): Orzuri Rique Garaizar Títol PFC: Design of a Solar Sail as the Propulsion System for a Nanosatellite Director del PFC: Dr. Elena Fantino
CubeSat Balloon Drag Devices: Meeting the 25-Year De-Orbit Requirement
CubeSat Balloon Drag Devices: Meeting the 25-Year De-Orbit Requirement Jerry K. Fuller, David Hinkley, and Siegfried W. Janson The Aerospace Corporation Physical Science Laboratories August, 2010 The Aerospace
SOLAR SAILCRAFT OF THE FIRST GENERATION TECHNOLOGY DEVELOPMENT
54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law 9 September - 3 October
Research Article Design and Characterization of a Small-Scale Solar Sail Prototype by Integrating NiTi SMA and Carbon Fibre Composite
Hindawi Advances in Materials Science and Engineering Volume 2017, Article ID 8467971, 6 pages https://doi.org/10.1155/2017/8467971 Research Article Design and Characterization of a Small-Scale Solar Sail
SUMMARY: INTRODUCTION: Applications for solar sails include:
SUMMARY: We know that there are lot of money wasted for Space mission every year allaround the world. From past experience we learnt all those missions have only 50% possibility of success. So we thought
Assessing Compliance with United States Government Orbital Debris Mitigation Guidelines
Assessing Compliance with United States Government Orbital Debris Mitigation Guidelines R. L. Kelley 1, D. R. Jarkey 2 1. Jacobs, NASA Johnson Space Center, Houston, TX 77058, USA 2. HX5 - Jacobs JETS
From Sail to Soil Getting Sailcraft Out of the Harbour on a Visit to One of Earth s Nearest Neighbours
DLR.de Chart 1 IAA-PDC-15-04-17 From Sail to Soil Getting Sailcraft Out of the Harbour on a Visit to One of Earth s Nearest Neighbours Jan Thimo Grundmann (1,2), Waldemar Bauer (1,3), Jens Biele (11,12),
Gyro-Control of a Solar Sailing Satellite
of a Solar Sailing Satellite Background by Hendrik W. Jordaan Willem H. Steyn Electronic Systems Laboratory Department of Electrical & Electronic Engineering Stellenbosch University January 20, 2017 Stellenbosch
JPC A Summary of Solar Sail Technology Developments and Proposed Demonstration Missions
JPC-99-2697 A Summary of Solar Sail Technology Developments and Proposed Demonstration Missions Charles Garner Jet Propulsion Laboratory California Institute of Technology Pasadena, California 91 109 Benjamin
Ground Testing of Solar Sail
Ground Testing of Solar Sail By Huang Xiaoqi, Liu Yufei, Zhang Xinghua, Cheng ZhengAi, Wang Li Qian Xuesen Laboratory of Space Technology, China Academy of Space Technology Beijing, 100094 (Received 1
Flight Testing of a Low Cost De-Orbiting Device for Small Satellites
Flight Testing of a Low Cost De-Orbiting Device for Small Satellites Dana Turse *, Phil Keller*, Robert Taylor*, Mark Reavis*, Mike Tupper*, Chris Koehler Abstract Use of small and very small spacecraft
Gyro-Control of a Solar Sailing Satellite
Gyro-Control of a Solar Sailing Satellite By Hendrik W. JORDAAN 1) and Willem H. STEYN 1) 1) Electric and Electronic Engineering Department, Stellenbosch University, Stellenbosch, South Africa (Received
Next Generation Life Support (NGLS): Variable Oxygen Regulator Element
ABSTRACT The Variable Oxygen Regulator is a new technology to provide pressure control for the next generation space suit. Using a motor-driven actuator, this dual-stage regulator allows, for the first
The Development of a Propellantless Space Debris Mitigation Drag Sail for LEO Satellites
The Development of a Propellantless Space Debris Mitigation Drag Sail for LEO Satellites Michael Pfisterer, Kevin Schillo, Christopher Valle, and Kuo-Chi Lin Department of Mechanical, Materials, and Aerospace
Controlled Deployment of Gossamer Spacecraft
Controlled Deployment of Gossamer Spacecraft By Patric SEEFELDT, Tom SPROEWITZ, Peter SPIETZ, Eugen MIKULZ, Siebo REERSHEMIUS, Kaname SASAKI, Norbert TÓTH and Rico JAHNKE Institute of Space Systems, German
Robotic On-Orbit Satellite Servicing: One Size Does Not Fit All
Robotic On-Orbit Satellite Servicing: One Size Does Not Fit All Dr. David L. Akin Dr. Craig R. Carignan Space Systems Laboratory On-Orbit Servicing Demand by Types Reboost Inspection Dexterous Servicing
Thermal Limitations of Starwisp-Type Interstellar Probes
Thermal Limitations of Starwisp-Type Interstellar Probes By Gregory L. Matloff 1) 1) Physics Department, New York City College of Technology, CUNY, Brooklyn, NY, USA (Received 1st Dec, 2016) Starwisp,
METNET Mission for Mars. MetNet. Atmospheric science network for Mars
MetNet Atmospheric science network for Mars A.-M. Harri (1), R. Pellinen (1), V. Linkin (2), K. Pichkadze (3), M. Uspensky (1), T. Siili (1), A. Lipatov (2), H. Savijärvi (4), V. Vorontsov (3), J.Semenov
Lasercraft Dynamics and Design for Proxima Centauri b Flyby
Lasercraft Dynamics and Design for Proxima Centauri b Flyby Team 158 Problem A Abstract This paper analyses the combinations among various kinds of sail shapes, materials and laser beam shapes to be used
Canadian Advanced Nanospace experiment 7 (CanX-7) Mission Analysis, Payload Design and Testing. Barbara Shmuel
Canadian Advanced Nanospace experiment 7 (CanX-7) Mission Analysis, Payload Design and Testing by Barbara Shmuel A thesis submitted in conformity with the requirements for the degree of Master of Applied
Loads, Structures, and Mechanisms. Team C5 Matthew Marcus Chris O'Hare Alex Slafkosky Scott Wingate
Loads, Structures, and Mechanisms Matthew Marcus Chris O'Hare Alex Slafkosky Scott Wingate Presentation Overview Design requirements Initial crew capsule design choice Pressure vessel design Pressure loads
IAC-06-D4.1.2 CORRELATIONS BETWEEN CEV AND PLANETARY SURFACE SYSTEMS ARCHITECTURE PLANNING Larry Bell
IAC-06-D4.1.2 CORRELATIONS BETWEEN CEV AND PLANETARY SURFACE SYSTEMS ARCHITECTURE PLANNING Larry Bell Sasakawa International Center for Space Architecture (SICSA), University of Houston, USA e-mail: lbell@uh.edu
Venus Aerial Pla DEPLOYMENT SIMULATION OF ULTRA-LIGHTWEIGHT INFLATABLE STRUCTURES
DEPLOYMENT SIMULATION OF ULTRA-LIGHTWEIGHT INFLATABLE STRUCTURES John T. Wang * and Arthur R. Johnson NASA Langley Research Center Hampton, VA AIAA-2002-1261 Abstract Dynamic deployment analyses of folded
IAC-17-A A Passively Stable Pyramid Sail for the Deorbit of Small Satellite Constellations. Alexandra C. Long a *, David A.
IAC-17-A6.5.2 A Passively Stable Pyramid Sail for the Deorbit of Small Satellite Constellations Alexandra C. Long a *, David A. Spencer b a School of Aerospace Engineering, Georgia Institute of Technology,
3. Structure static test. 4. Solar Sail Material Test. 5. Conclusion
Ground Testing of Solar Sail Huang Xiaoqi, Liu Yufei Qian Xuesen Laboratory of Space Technology Contents 1. 8 8m 8m Solar Sail Prototype 2. Ground Deployment Demonstration 3. Structure static test 4. Solar
Adaptation and Optimization of the RIT-µX miniaturized Ion Propulsion System for Small Satellites
Adaptation and Optimization of the RIT-µX miniaturized Ion Propulsion System for Small Satellites Hans J. Leiter, Christian Altmann, Ralf Kukies and Jan-Patrick Porst 22 April 2015, Berlin (D) document
The Abracadabra of Engineering: Strong Structures from Flimsy Materials
The Abracadabra of Engineering: Strong Structures from Flimsy Materials Rockets are great for blasting spacecraft into orbit or on their way to another planet. But the trouble with rockets is that they
Altair Constellation Returns Humans to the Moon
Altair Cover Page Altair Constellation Returns Humans to the Moon Clinton Dorris Deputy Manager Altair Project Office Constellation EXPLORATION ROADMAP 05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21
NanoRacks/Quad-M Rideshare Overview. Michael D. Johnson 10/12/2016
NanoRacks/Quad-M Rideshare Overview Michael D. Johnson 10/12/2016 Why NanoRacks/Quad-M Team? NRCSD Kaber Cygnus External Deployer NREP NR Airlock Dragon Trunk Deployer Centaur Aft Bulkhead Deployer Centaur
Gossamer Spacecraft Survey Study
Gossamer Spacecraft Survey Study Preliminary Report - Historical Survey Prepared by Forward Unlimited 8114 Pebble Court Clinton, WA 98236 360-579-1340 under Purchase Order No. 1207157 with Jet Propulsion
Preliminary Cost Analysis MARYLAND. Cost Sources Vehicle-level Costing Heuristics Applications Learning Curves Program-Level Analysis
Cost Sources Vehicle-level Costing Heuristics Applications Learning Curves Program-Level Analysis 2003 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu Cost Analysis Direct Costs - directly
Introducing the new Farr 25 OD Built by OD Yachting
Introducing the new Built by OD Yachting... e n g i n e e r e d f o r p e r f o r m a n c e w i t h s u p e r i o r h a n d l i n g Specs LOA LWL Beam Draft Displ Ballast 7.62 m 6.96 m 2.47 m 1.80 m 930
Design of the Gossamer-1 Deployment Demonstrator
Design of the Gossamer-1 Deployment Demonstrator By Tom SPROEWITZ 1), Patric SEEFELDTI 1), Jan-Thimo GRUNDMANN 1), Peter SPIETZ 1), Norbert TOTH 1) ; Martin HILLEBRANDT 2), Marco STRAUBEL 2) and Martin
Tether-based Robot Locomotion Experiments in REX-J mission
Tether-based Robot Locomotion Experiments in REX-J mission H. Nakanishi*, M. Yamazumi*, S. Karakama*, M. Oda*, S. Nishida****, H. Kato**, K. Watanabe*, A. Ueta**, M. Yoshii***, S. Suzuki*** *Tokyo Institute
Science Museum Oklahoma presents Space Day Teacher s Resource Guide
Science Museum Oklahoma presents Space Day Teacher s Resource Guide Thank you for your participation in Space Day. Science Museum Oklahoma wants to ensure your students experience goes beyond the museum.
1 Korean-American Scientists and Engineers Association National Mathematics and Science Competition. 1. Raft Rally
1 Korean-American Scientists and Engineers Association 1. Raft Rally GOAL The goal of raft rally contest is to understand the concept of buoyancy and apply it to the design of a mini boat that can hold
Today Mr. Happer told us to use the following physics vocabulary words and relate them to our experiment:
Design Your Own Experiment Lab Report Objective While making our water rocket, our group tried to achieve different criteria listed by Mr. Happer. With our rocket, we were trying to achieve a distance
A Low Power Approach to Small Satellite Propulsion
A Low Power Approach to Small Satellite Propulsion Joe Cardin Director of Engineering VACCO Industries 0350 Vacco Street, South El Monte, CA 9733 JCardin@VACCOcom (626) 450-6435 Larry E Mosher Senior Professional
I I I I I I I I I I I I I I I
A Deployable Stiffened Biconvex Mast Nancy Galley Holt Stanford University, Stanford CA 94305 Emery J. Reeves Stanford University, Stanford CA 94305 Deployable structures are a common spacecraft configuration
C01 ISLAND. Performance everywhere : Freestyle, Wave, Freeride, Foil & Hang Time 4 / 5,5 / 7 / 9 / 10 / 12 C02 ALOHA C03 DEEP WATER
2016 C01 ISLAND Performance everywhere : Freestyle, Wave, Freeride, Foil & Hang Time 4 / 5,5 / 7 / 9 / 10 / 12 C02 ALOHA C03 DEEP WATER NOTUS REV 2016 Notus Rev 2016 retains & confirms its ultra versatile
A Study on the End-Effector Exchange Mechanism of a Space Robot
Journal of Mechanics Engineering and Automation 7 (2017) 278-284 doi: 10.17265/2159-5275/2017.05.005 D DAVID PUBLISHING A Study on the End-Effector Exchange Mechanism of a Space Robot Rui Qu 1, Yuto Takei
DemoSat II Design Guidelines
1. BALLOON DESCRIPTION AND CAPABILITIES This document defines key interfaces between the DemoSat teams and the Balloon for the purpose of establishing program responsibilities. 1.1 Balloon Interface General
Engineering Flettner Rotors to Increase Propulsion
Engineering Flettner Rotors to Increase Propulsion Author: Chance D. Messer Mentor: Jeffery R. Wehr Date: April 11, 2016 Advanced STEM Research Laboratory, Odessa High School, 107 E 4 th Avenue, Odessa
College of Engineering
College of Engineering Department of Mechanical and Aerospace Engineering MAE-250, Section 001 Introduction to Aerospace Engineering Final Project Bottle Rocket Written By: Jesse Hansen Connor Petersen
Comparison of Methods and Devices for High Pressure Vessel Passivation B. Zitouni (1), L. Denies (1),M. Peukert (1)
SPC2016_ 3124678 Comparison of Methods and Devices for High Pressure Vessel Passivation B. Zitouni (1), L. Denies (1),M. Peukert (1) (1) OHB System AG, Universitätsallee 27-29, 28359 Bremen, Germany Email:
Assembly Instructions for STS-97 payload (P6 Truss)
2008 Assembly Instructions for STS-97 payload (P6 Truss) Familiarization with P6 Truss sides This is the FORWARD side of P6. It is the side that will be facing forward on top of the Z1 truss. Easily identified
Test Flights of the Revised ULDB Design
Test Flights of the Revised ULDB Design Michael S. Smith * Aerostar International, Inc., Sulphur Springs, TX 75482, USA Henry M. Cathey, Jr. Physical Science Laboratory, New Mexico State University, Wallops
IAC-04-IAA DESIGN OF A HIGH-TENSION ELASTICALLY DEFORMING SPACE TETHER DEPLOYER
IAC-04-IAA-3.8.2 DESIGN OF A HIGH-TENSION ELASTICALLY DEFORMING SPACE TETHER DEPLOYER Bas Lansdorp, MSc Delft University of Technology, The Netherlands bas.lansdorp@lr.tudelft.nl Prof. ir. H.M.J.R. Soemers
Crew Systems Design Project Group A8. Chrissy Doeren Kip Hart Kiran Patel Alex Slafkosky
Crew Systems Design Project Group A8 Chrissy Doeren Kip Hart Kiran Patel Alex Slafkosky Project Overview Objective: design a crewed spacecraft for a low cost lunar mission Crew: 3-95th percentile men Duration:
WATER ROCK. Lawndart The rocket goes straight up and comes down nose first at high speed. Disadvantages
Water Rocket Recovery Index What is a recovery system? A recovery system is a feature of a rocket that allows it to come back to Earth with minimal damage. Introduction This guide is intended to serve
WINDSWEPT & INTERESTING LTD
Page 1 WINDSWEPT & INTERESTING LTD Portable Wind Power Page 2 Table of Contents Overview... 3 Off-Grid, On the Road... 3 Airborne Wind Energy Systems (AWES)... 3 A Network of Kites... 3 Background... 4
ESAIL D45.1 Final Report of Remote Unit Gas Thruster
D45.1 Final Report of Remote Unit Gas Thruster Work Package: WP 45 Version: Version 1.2 Prepared by: NanoSpace AB, Kristoffer Palmer, Tor-Arne Grönland Time: Uppsala, November 8 th, 2013 Coordinating person:
Load Responsive Multilayer Insulation Performance Testing
Load Responsive Multilayer Insulation Performance Testing S. Dye 1, A. Kopelove 1, and G. L. Mills 2 1 Quest Thermal Group, 6452 Fig Street Suite A, Arvada, CO 80004 USA 2 Ball Aerospace & Technologies
Case studies from classes led by Dr. Ron Fulbright, University of South Carolina Upstate. INNOVATIVE ANALYSIS A BETTER KITE
INNOVATIVE ANALYSIS A BETTER KITE 1 1. BRIEF DESCRIPTION OF THE SITUATION A kite is a tethered aircraft. The necessary lift that makes the kite wing fly is generated when air flows over and under the kite's
SSC15-II-6. payload), allowing a new class of larger deployable payloads to utilize the ISS as a research platform.
SSC15-II-6 Paving the Way for Small Satellite Access to Orbit: Cyclops Deployment of SpinSat, the Largest Satellite ever Deployed from the International Space Station Matthew P. Hershey, Daniel R. Newswander,
DEVELOPMENT OF COMMERCIAL DRAG-AUGMENTATION SYSTEMS FOR SMALL SATELLITES
DEVELOPMENT OF COMMERCIAL DRAG-AUGMENTATION SYSTEMS FOR SMALL SATELLITES Chiara Palla, Jenny Kingston, and Stephen Hobbs Space Research Group, Cranfield University, Cranfield, MK43 0AL, UK c.palla@cranfield.ac.uk,
IAC-11-C Deployment Simulation of Very Large Inflatable Tensegrity Reflectors
IAC-11-C2.2.10 Deployment Simulation of Very Large Inflatable Tensegrity Reflectors Thomas Sinn Advanced Space Concepts Laboratory, University of Strathclyde, United Kingdom, thomas.sinn@strath.ac.uk Massimilano
Very Basic Design Considerations for Water-Bottle Rockets
Very Basic Design Considerations for Water-Bottle Rockets The next few pages are provided to help in the design of your water-bottle rocket. Read through this packet and answer the questions on the last
A Novel Cold Gas Propulsion System for Nanosatellites and Picosatellites
A Novel Cold Gas Propulsion System for Nanosatellites and Picosatellites David Hinkley This work was supported under The Aerospace Corporation's Independent Research and Development Program 1 The Need
Initial Design of a Lightweight Mars Aircraft Mission
Initial Design of a Lightweight Mars Aircraft Mission Lochie Ferrier This paper outlines the design of a CubeSat based mission for Mars observation using a lightweight unpowered fixed-wing aircraft. The
Accessible Performance is True Performance
Accessible Performance is True Performance I N S P I R E D B Y N AT U RE / / D RI V EN B Y T HE EL EMENT S Our understanding of True Performance is not just raw power or speed - it s the combination of
ME 239: Rocket Propulsion. Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD
ME 239: Rocket Propulsion Forces Acting on a Vehicle in an Atmosphere (Follows Section 4.2) J. M. Meyers, PhD 1 Commonly acting forces on a vehicle flying in a planetary atmosphere: Thrust Aerodynamic
SPECIFICALLY FOR THE AUSTRALIAN CLIMATE
ORBIT INFLATABLE CARAVAN ANNEXE RANGE COMET SINGLE INFLATION ANNEXE Spacious and light-filled the ORBIT Air Comet Annexe is a perfect choice SINGLE INFLATION POINT The ORBIT Air Annexe is fully sealed
Feasibility of Developing a Refrigerant-Based Propulsion System for Small Spacecraft
Feasibility of Developing a Refrigerant-Based Propulsion System for Small Spacecraft Carl Seubert, et al. Small Satellite Conference August 14 th 2007 Outline Background Propulsion system requirements
The only thing. is everything
p u r e I NS P I RED B Y NAT U RE / / D RI V EN B Y T HE E LEMEN TS p e r f o r m a n c e The only thing that s changed is everything Race performance at it s best yet the all-new R1 V2. Taking a completely
3. Real-time operation and review of complex circuits, allowing the weighing of alternative design actions.
PREFERRED RELIABILITY PAGE 1 OF 5 PRACTICES VOLTAGE & TEMPERATURE MARGIN TESTING Practice: Voltage and Temperature Margin Testing (VTMT) is the practice of exceeding the expected flight limits of voltage,
Presentation Contents
OTOS Presentation Contents Mission Requirements Mission Operations Architecture Design Reference Missions Habitat Configuration CONOPS Life Support Contingency Accommodations Plans for Experimental Testing
Project Background and Scope
Project Background and Scope The purpose of the project is to generate a design that can easily and effectively convert a Laser sailboat to a human powered Flettner ship. A Flettner ship is a ship that
PUFF! Rocket Activity. Students will learn about rocket stability as they. Students will construct small indoor paper
Rocket Activity 3...2...1...PUFF! Students will learn about rocket stability as they Unifying Concepts and Processes Science as Inquiry inquiry Physical Science Science and Technology Students will construct
A Dual-Chamber Hybrid Inflatable Suitlock (DCIS) for Planetary Surfaces or Deep Space
41st International Conference on Environmental Systems 17-21 July 2011, Portland, Oregon AIAA 2011-5064 A Dual-Chamber Hybrid Inflatable Suitlock (DCIS) for Planetary Surfaces or Deep Space A. Scott Howe,
2017 LOCKHEED MARTIN CORPORATION. ALL RIGHTS RESERVED
1 Lockheed Martin (LM) Space Systems Software Product Line Focused organization (LM1000) Deep Space Heritage Avionics/SW leveraged for LM1000 product line solution Combined Commercial and Civil Space Organizations
Micro Cold Gas Proportion thruster for Deep Interplanetary Exploration Development in BICE
Micro Cold Gas Proportion thruster for Deep Interplanetary Exploration Development in BICE Xudong Wang, Jinyue Geng, Xuhui Liu kyffwd@163.com (Dr. Xudong Wang,Chief Designer) Special requirements of Deep
#6 Lesson Emergency Rescue Vehicles Engineering Design Assessment
#6 Lesson Emergency Rescue Vehicles Engineering Design Assessment The engineering design process has its own built in assessment phase as the students create their inventions, test them and improve them.
(12) United States Patent (10) Patent No.: US 7, B1
USOO7066428B1 (12) United States Patent (10) Patent No.: US 7,066.428 B1 Haggard et al. (45) Date of Patent: Jun. 27, 2006 (54) UNFOLDING WING FOR AIR-LAUNCHED, 5,836,541 A * 1 1/1998 Pham... 244/2 LOW
UNIVERSAL HIGH LEVEL FOIL KITE
UNIV ER SAL I NS P I RED NAT U RE / / D RI V EN H IGH T HE E LEMEN TS LEVEL FOIL KIT E UNIVERSAL HIGH LEVEL FOIL KITE The Chrono V3 is also available in an Ultra Light version. This is the same design
Development of a Back Pressure Valve for the Spacesuit Water Membrane Evaporator (SWME)
45th 12-16 July 2015, Bellevue, Washington ICES-2015-338 Development of a Back Pressure Valve for the Spacesuit Water Membrane Evaporator (SWME) Brad Harris 1 and Thomas O. Leimkuehler 2 Paragon Space
Proof of Concept Demonstration of the Hybrid Remotely Operated Vehicle (HROV) Light Fiber Tether System
Proof of Concept Demonstration of the Hybrid Remotely Operated Vehicle (HROV) Light Fiber Tether System Barbara Fletcher Chris Young James Buescher Space and Naval Warfare Systems Center San Diego, CA
SSC13-VII-10 INTRODUCTION
SSC13-VII-10 Closed-loop thrust control in a MEMS-based micro propulsion module for CubeSats Pelle Rangsten, Kristoffer Palmer, Johan Bejhed, Ana Zaldivar Salaverri, Kerstin Jonsson, and Tor-Arne Grönland
NSW Mines Rescue Unmanned Aerial Vehicle (UAV)
NSW Mines Rescue Unmanned Aerial Vehicle (UAV) 2015 IMRB Conference Hanover Emergency Response Q. Will the systems providing this required information remain operational once an incident occurs? Likely
Space Simulation MARYLAND U N I V E R S I T Y O F. Space Simulation. ENAE 483/788D - Principles of Space Systems Design
Focus is on human-in-the-loop operational simulations, not component sims (e.g., thermal vacuum chambers) Microgravity Planetary surfaces Specialty simulations A vision and a challenge... 1 2012 David
R.J.P. BARKER AND S.D. GUEST Cambridge University Engineering Department Trumpington Street, Cambridge CB2 1PZ, UK
INFLATABLE TRIANGULATED CYLINDERS R.J.P. BARKER AND S.D. GUEST Cambridge University Engineering Department Trumpington Street, Cambridge CB2 1PZ, UK Abstract A study is described into the use of triangulated
Space Simulation MARYLAND U N I V E R S I T Y O F. Space Simulation. ENAE 483/788D - Principles of Space Systems Design
Lecture #27 December 4, 2014 Focus of this lecture is on human-in-the-loop operational simulations, not component sims (e.g., thermal vacuum chambers) Microgravity Planetary surfaces Specialty simulations
» Wind Propulsion for Cargo Ships «Performance Parameters and Operational Aspects
Prof. Capt. Michael Vahs Maritime Department / HS Emden-Leer Germany» Wind Propulsion for Cargo Ships «Performance Parameters and Operational Aspects Natural Propulsion Wageningen, 20.01.2011 Maritime
Design of a double quadruped for the Tech United soccer robot
Design of a double quadruped for the Tech United soccer robot M.J. Naber (0571509) DCT report number: 2009.134 Master Open Space project Eindhoven, 21 December 2009 Supervisor dr.ir. P.C.J.N. Rosielle
Exploration Series. MODEL ROCKET Interactive Physics Simulation Page 01
MODEL ROCKET ------- Interactive Physics Simulation ------- Page 01 How high will your model rocket fly? At liftoff, the rocket engine is ignited and a thrust force is generated. The rocket accelerates
Igniting Solutions for a Safer Future
Igniting Solutions for a Safer Future A Tawazun Subsidiary 2 Advanced PyroTechnics Tawazun Industrial Park United Arbab Emirates t +971-2-4927950 f +971-2-4927951 info@aptuae.ae www.aptuae.ae Our Mission
3, 2, 1, Blast Off! Division A 2019
3, 2, 1, Blast Off! Division A 2019 Event Description Construct and launch two rockets designed to stay aloft the greatest amount of time. Failure to follow all construction rules will result in rockets
catalyst The Art of Progress
catalyst v2 The Art of Progress i n s p i r e d b y n a t u r e / / d r i v e n b y t h e e l e m e n t s The Art of Progress The Catalyst V1 has been a great success but the Ozone design team is never
ultimate All-round Performance
ultimate All-round Performance During the development of the R1 V2 we experienced the overall enhancement in performance achieved from a lighter weight kite. The Chrono V2 UltraLight combines our high
Notes on Risk Analysis
Notes on Risk Analysis MAXIMIZING THE CHANCES OF SUCCESS AERO 401 D. B. KANIPE MARCH, 2016 Focus of Design process Design of Spacecraft Getting the design to work as planned Accomplishing the mission objectives
Monday, May 18, 2015 Not for Sailors Only: Sailmaking--Think High-Tech, Stateof-the-Art
Monday, May 18, 2015 Not for Sailors Only: Sailmaking--Think High-Tech, Stateof-the-Art If you think sailmaking is a craft reserved for wizened old sea dogs with needles and palm-protectors, you're in
SOLAR ENERGY. solutions. adhesives, sealants, and Potting encapsulants For solar energy applications
SOLAR ENERGY solutions adhesives, sealants, and Potting encapsulants For solar energy applications Micro-inverters charge controllers J-Box Potting Batteries Bonding / sealing EPIC RESINS quality SolutIoNS
How Feathered and Plastic Fletchings Affect the Control Of Arrows By Lucy Kiefer 7B
How Feathered and Plastic Fletchings Affect the Control Of Arrows By Lucy Kiefer 7B 12-10-17 Archery has had a resurgence in popular culture with prominent roles in movies like Brave or the Hunger Games
Entry Descent and Landing Tools
Entry Descent and Landing Tools Steve Lingard Vorticity Ltd Oxfordshire,UK Content Introduction Entry and Descent Dynamics Tools Airbag Design Environment LS-DYNA Applications Entry system dynamics Inflatable
LASER-PROPELLED LIGHTSAILS AND LIGHTCRAFT LATEST RESEARCH DEVELOPMENTS
LASER-PROPELLED LIGHTSAILS AND LIGHTCRAFT LATEST RESEARCH DEVELOPMENTS Abstract: This paper summarizes the latest developments over the past two years, on the author's laser-propelled Lightsails and Lightcraft
EXPERIMENTAL STUDY TO INCREASE THE SHOCK SPEED IN A FREE PISTON DOUBLE DIAPHRAGM SHOCK TUBE
EXPERIMENTAL STUDY TO INCREASE THE SHOCK SPEED IN A FREE PISTON DOUBLE DIAPHRAGM SHOCK TUBE Hiroyuki Ishida (1), Kyosuke ARAI (2), Yusuke SHIMAZU (3), Asei TEZUKA (4), Yasunori NAGATA (5), Kazuhiko YAMADA
CRITICAL DESIGN REVIEW
STUDENTS SPACE ASSOCIATION THE FACULTY OF POWER AND AERONAUTICAL ENGINEERING WARSAW UNIVERSITY OF TECHNOLOGY CRITICAL DESIGN REVIEW November 2016 Issue no. 1 Changes Date Changes Pages/Section Responsible