Flight Opportunities 2013 Annual Report
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The Regulatory Role of the Federal Aviation Administration
The Regulatory Role of the Federal Aviation Federal Aviation Administration Administration Presented to: Legal Subcommittee of the United Nations Committee on the Peaceful Uses of Outer Space By: Laura Montgomery, Senior Attorney, FAA Regulatory Structure • Congress • Executive Branch – Federal Aviation Administration – space transportation – Federal Communications Commissions – space communications – National Oceanic and Atmospheric Administration – remote sensing from space • Judiciary Federal Aviation 2 2 Administration March 2010 Administrative Procedure Act • Rulemaking • Authorizations: licenses and permits • Adjudication Federal Aviation 3 3 Administration March 2010 Statutory Authority • 49 U.S.C. Subtitle IX, chapter 701 (Ch. 701) – Authorizes the Secretary of Transportation to authorize launch and reentry and operation of launch and reentry sites as carried out by U.S. citizens or within the United States. – Directs the Secretary to • Exercise this responsibility consistent with public health and safety, safety of property, and national security and foreign policy interests of the United States. • Encourage, facilitate and promote commercial space launches and reentries by the private sector. Federal Aviation 4 Administration March 2010 Statutory Mission ELV Air Launch Launch & Reentry Sites RLV Launch & Reentry Sea Launch Human Space Flight Federal Aviation 5 5 Administration March 2010 Types of Launch Sites Oklahoma Spaceport ELV California Spaceport Sea Launch Florida Kodiak Launch Spaceport Complex Mid-Atlantic Mojave Air -
Reusable Suborbital Market Characterization
Reusable Suborbital Market Characterization Prepared by The Tauri Group for Space Florida March 2011 Introduction Purpose: Define and characterize the markets reusable suborbital vehicles will address Goals Define market categories Identify market drivers Characterize current activities Provide basis for future market forecasting (Note that this study is not a forecast) Benefits Shared understanding improves quality and productivity of industry discourse A consistent taxonomy enables communications across the community, with Congress, press, and investors Accessible information helps industry participants assess opportunities, plan and coordinate activities, seek funding, and budget Proprietary www.taurigroup.com 2 Agenda Methodology Suborbital spaceflight attributes and vehicles Value proposition Characterization and analysis of markets Commercial human spaceflight Basic and applied research Aerospace technology test and demonstration Remote sensing Education Media & PR Point-to-point transportation Conclusions Proprietary www.taurigroup.com 3 Methodology Literature review and data Analysis and findings collection Vehicles Articles, reports, and publications Payload types Available launch and research Markets datasets Opportunities Applicable payloads Challenges Initial customers Users Interviews Economic buyers Researchers Launch service providers Funding agencies Potential commercial customers Users Proprietary www.taurigroup.com 4 Reusable Suborbital Vehicles Industry catalyzed by Ansari X -
NASA Flight Opportunities Space Technology Mission Directorate
National Aeronautics and Space Administration Flight Opportunities Space Technology Mission Directorate (STMD) NASA’s Flight Opportunities program strives to advance the operational readiness of innovative space technologies while also stimulating the development and utilization of the U.S. commercial spaceflight industry, particularly for the suborbital and small How to launch vehicle markets. Since its initiation in 2010, the program has provided affordable Access Flight access to relevant space-like environments for over 100 payloads across a variety of Opportunities flight platforms. There are currently two paths for accessing flight test opportunities: Space Technology Research, Development, Demonstration, and Infusion (REDDI) External researchers can compete for flight funding through the REDDI NASA Research Announcement (NRA). Awardees receive a grant allowing them to directly purchase flights from U.S. commercial flight vendors that best meet their needs. The solicitation is biannual. Suborbital Reusable High-Altitude Balloon Parabolic Aircraft Launch Vehicles (sRLV) Systems These platforms enable NASA Internal Call for sRLVs enable a wide variety of These systems facilitate impact investigation of short-term Payloads experiments, such as testing studies on extended exposure exposure to reduced gravity, This path facilitates algorithms for landing or to cold, atmosphere, and with typical missions flying suborbital flight hazard avoidance, or evaluating radiation. In addition, high approximately 40 parabolas demonstrations for the response of systems to altitude balloons enable testing providing several seconds of technologies under microgravity. of sensors and instruments for reduced gravity during the flight. development by NASA and a variety of applications. other government agencies. Typical parabolic vehicles include Typical vehicles include Blue Zero G’s G-FORCE ONE. -
Commercial Space Transportation Developments and Concepts: Vehicles, Technologies and Spaceports
Commercial Space Transportation 2006 Commercial Space Transportation Developments and Concepts: Vehicles, Technologies and Spaceports January 2006 HQ003606.INDD 2006 U.S. Commercial Space Transportation Developments and Concepts About FAA/AST About the Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA/AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 49 United States Code, Subtitle IX, Chapter 701 (formerly the Commercial Space Launch Act). FAA/AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA/AST is directed to encour- age, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA/AST’s web site at http://ast.faa.gov. Federal Aviation Administration Office of Commercial Space Transportation i About FAA/AST 2006 U.S. Commercial Space Transportation Developments and Concepts NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Federal Aviation Administration Office of Commercial Space Transportation 2006 U.S. Commercial Space Transportation Developments and Concepts Contents Table of Contents Introduction . .1 Significant 2005 Events . .4 Space Competitions . .6 Expendable Launch Vehicles . .9 Current Expendable Launch Vehicle Systems . .9 Atlas 5 - Lockheed Martin Corporation . -
Reusable Launch Vehicles Exos Aerospace Is Making
Reusable Launch Vehicles Exos Aerospace is making SPACEavailable…TM The 4 FAA/AST The other 6 of 10 Licensed Reusable EXOS AEROSPACE is… “Non-Reusable Rocket Launch Rocket” Launch Providers Providers companies of companies of 1 4 IN THE 1 10 in the United WORLD with a licensed States with an Active reusable rocket. Launch License $ <10% reuse cost Access to space $$ 25% reuse cost is too inflexible Air Launch Provides for increased flexibility $$ reuse cost… % unknown (Exos, Virgin Orbit, Lockheed Martin) Reusability Enables increased ROI through cost reductions (Exos, SpaceX, Blue Origin) 1- Ignition 2- Clean Lox Ethanol Engine (launch) Apogee SARGE Flight 1 3- Drogue Return to 4.- Canopy Return from reenter the atmosphere Rocket flight 3 Our team has built hundreds of rocket engines and dozens of suborbital flying vehicles designed for reusability TEAM’S PAST EXPERIENCE Vehicle Evolution (20+ Years) Armadillo 4 Launches and 3 Rocket Racing st J Aerospace Lunar recoveries on 1 League SARGE vehicle Founded by Lander development SARGE a st John Carmack Challenge 1 Today program Super Mod Aug 2018 – Oct 2019 SARGE-LW Place g u a r 2000 2006 2008 2009 2010 2011 2015 2020 Apr 2020 Air Force X-Prize Lunar lander 2010-2013 Stig Exos Aerospace Hypersonic Challenge2009 flies to 95km acquires assets of Contract Competition Armadillo Aerospace Armadillo prize $ w/Pixel and and brings on the team Testing SARGE R2 J Texel Round 1 winner- NASA with new management for return to flight Winners Morpheus Sale supporting commercial post COVID 19 a objectives -
Flow Visualization Studies of VTOL Aircraft Models During Hover in Ground Effect
NASA Technical Memorandum 108860 Flow Visualization Studies of VTOL Aircraft Models During Hover In Ground Effect Nikos J. Mourtos, Stephane Couillaud, and Dale Carter, San Jose State University, San Jose, California Craig Hange, Doug Wardwell, and Richard J. Margason, Ames Research Center, Moffett Field, California Janua_ 1995 National Aeronautics and Space Administration Ames Research Center Moffett Field, California 94035-1000 Flow Visualization Studies of VTOL Aircraft Models During Hover In Ground Effect NIKOS J. MOURTOS,* STEPHANE COUILLAUD,* DALE CARTER,* CRAIG HANGE, DOUG WARDWELL, AND RICHARD J. MARGASON Ames Research Center Summary fountain fluid flows along the fuselage lower surface toward the jets where it is entrained by the jet and forms a A flow visualization study of several configurations of a vortex pair as sketched in figure 1(a). The jet efflux and jet-powered vertical takeoff and landing (VTOL) model the fountain flow entrain ambient temperature air which during hover in ground effect was conducted. A surface produces a nonuniform temperature profile. This oil flow technique was used to observe the flow patterns recirculation is called near-field HGI and can cause a on the lower surfaces of the model. Wing height with rapid increase in the inlet temperature which in turn respect to fuselage and nozzle pressure ratio are seen to decreases the thrust. In addition, uneven temperature have a strong effect on the wing trailing edge flow angles. distribution can result in inlet flow distortion and cause This test was part of a program to improve the methods compressor stall. In addition, the fountain-induced vortex for predicting the hot gas ingestion (HGI) for jet-powered pair can cause a lift loss and a pitching-moment vertical/short takeoff and landing (V/STOL) aircraft. -
Small Launch Vehicles a 2015 State of the Industry Survey Carlos Niederstrasser
Small Launch Vehicles A 2015 State of the Industry Survey Carlos Niederstrasser An update to this survey will be presented at the 2016 Internaonal Astronau9cal Congress 1 Agenda Overview of Small Launch Vehicles Launch Method/Locations Launch Performance Projected Launch Costs Individual Rocket Details Copyright © 2015 by Orbital ATK, Inc. 2 Listing Criteria Have a maximum capability to LEO of 1000 kg (definition of LEO left to the LV provider). The effort must be for the development of an entire launch vehicle system (with the exception of carrier aircraft for air launch vehicles). Mentioned through a web site update, social media, traditional media, conference paper, press release, etc. sometime after 2010. Have a stated goal of completing a fully operational space launch (orbital) vehicle. Funded concept or feasibility studies by government agencies, patents for new launch methods, etc., do not qualify. Expect to be widely available commercially or to the U.S. Government No specific indication that the effort has been cancelled, closed, or otherwise disbanded. Correc&ons, addi&ons, and comments are welcomed and encouraged! Copyright © 2015 by Orbital ATK, Inc. 3 We did not … … Talk to the individual companies … Rely on any proprietary/confidential information … Verify accuracy of data found in public resources Ø Primarily relied on companies’ web sites Funding sources, when listed, are not implied to be the vehicles sole or even majority funding source. We do not make any value judgements on technical or financial credibility -
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L. Pepermans Technische Universiteit Delft Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability by L. Pepermans to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Wednesday October 30, 2019 at 14:30 AM. Student number: 4144538 Project duration: September 1, 2018 – October 30, 2019 Thesis committee: Ir. B.T.C Zandbergen , TU Delft, supervisor Prof. E.K.A Gill, TU Delft Dr.ir. D. Dirkx, TU Delft This thesis is confidential and cannot be made public until October 30, 2019. An electronic version of this thesis is available at http://repository.tudelft.nl/. Cover image: S-IVB upper stage of Skylab 3 mission in orbit [23] Preface Before you lies my thesis to graduate from Delft University of Technology on the feasibility and cost-effectiveness of reusable upper stages. During the accompanying literature study, it was determined that the technology readiness level is sufficiently high for upper stage reusability. However, it was unsure whether a cost-effective system could be build. I have been interested in the field of Entry, Descent, and Landing ever since I joined the Capsule Team of Delft Aerospace Rocket Engineering (DARE). During my time within the team, it split up in the Structures Team and Recovery Team. In September 2016, I became Chief Recovery for the Stratos III student-built sounding rocket. During this time, I realised that there was a lack of fundamental knowledge in aerodynamic decelerators within DARE. -
Reusable Stage Concepts Design Tool
DOI: 10.13009/EUCASS2019-421 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) DOI: ADD DOINUMBER HERE Reusable stage concepts design tool Lars Pepermans?, Barry Zandbergeny ?Delft University of Technology Kluyverweg 1, 2629 HS Delft [email protected] yDelft University of Technology Kluyverweg 1, 2629 HS Delft Abstract Reusable launch vehicles hold the promise of substantially reducing the cost of access to space. Many different approaches towards realising a reusable rocket exist or are being proposed. This work focuses on the use of an optimisation method for conceptual design of non-winged reusable upper stages, thereby allowing it to take into account landing on land, sea or mid-air retrieval as well as landing the full stage or the engine only. As the optimisation criterion, the ratio of the specific launch cost of the reusable to the expendable version is used. The tool also provides for a Monte Carlo analysis, which allows for investigating the ruggedness of the design solution(s) found. The article will describe the methods implemented in the Conceptual Reusability Design Tool (CRDT) together with the modifications made to ParSim v3, a simulation tool by Delft Aerospace Rocket Engi- neering. Furthermore, it will present the steps taken to verify and validate CRDT. Finally, several example cases are presented based on the Atlas V-Centaur launch vehicle. The cases demonstrate the tools capa- bility of finding optimum and the sensitivity of the found optimum. However, it also shows the optimum when the user disables some Entry Descent and Landing (EDL) options. 1. Introduction To make space more accessible, one can reduce the cost of an orbital launch. -
Simulating and Evaluating Regolith Propagation Effects During Drilling in Low Gravity Environments
Advances in Computational Design, Vol. 4, No. 2 (2019) 141-153 DOI: https://doi.org/10.12989/acd.2019.4.2.141 141 Simulating and evaluating regolith propagation effects during drilling in low gravity environments Patrick C. Suermann1, Hriday H. Patel1a and Luke D. Sauter2b 1Department of Construction Science, Texas A&M University Francis Hall 321D, 3137 TAMU, College Station, TX 77843-3137 2Department of Astronautical Engineering, United States Air Force Academy, HQ USAFA/DFAS, 2354 Fairchild Dr., USAFA, CO 80840 (Received September 30, 2018, Revised January 11, 2019, Accepted February 13, 2019) Abstract. This research is comprised of virtually simulating behavior while experiencing low gravity effects in advance of real world testing in low gravity aboard Zero Gravity Corporation’s (Zero-G) research aircraft (727- 200F). The experiment simulated a drill rig penetrating a regolith simulant. Regolith is a layer of loose, heterogeneous superficial deposits covering solid rock on surfaces of the Earth’ moon, asteroids and Mars. The behavior and propagation of space debris when drilled in low gravity was tested through simulations and visualization in a leading dynamic simulation software as well as discrete element modeling software and in preparation for comparing to real world results from flying the experiment aboard Zero-G. The study of outer space regolith could lead to deeper scientific knowledge of extra-terrestrial surfaces, which could lead us to breakthroughs with respect to space mining or in-situ resource utilization (ISRU). These studies aimed to test and evaluate the drilling process in low to zero gravity environments and to determine static stress analysis on the drill when tested in low gravity environments. -
Aviation Acronyms
Aviation Acronyms 5010 AIRPORT MASTER RECORD (FAA FORM 5010-1) 7460-1 NOTICE OF PROPOSED CONSTRUCTION OR ALTERATION 7480-1 NOTICE OF LANDING AREA PROPOSAL 99'S NINETY-NINES (WOMEN PILOTS' ASSOCIATION) A/C AIRCRAFT A/DACG ARRIVAL/DEPARTURE AIRFIELD CONTROL GROUP A/FD AIRPORT/FACILITY DIRECTORY A/G AIR - TO - GROUND A/G AIR/GROUND AAA AUTOMATED AIRLIFT ANALYSIS AAAE AMERICAN ASSOCIATION OF AIRPORT EXECUTIVES AAC MIKE MONRONEY AERONAUTICAL CENTER AAI ARRIVAL AIRCRAFT INTERVAL AAIA AIRPORT AND AIRWAY IMPROVEMENT ACT AALPS AUTOMATED AIR LOAD PLANNING SYSTEM AANI AIR AMBULANCE NETWORK AAPA ASSOCIATION OF ASIA-PACIFIC AIRLINES AAR AIRPORT ACCEPTANCE RATE AAS ADVANCED AUTOMATION SYSTEM AASHTO AMERICAN ASSOCIATION OF STATE HIGHWAY & TRANSPORTATION OFFICIALS AC AIRCRAFT COMMANDER AC AIRFRAME CHANGE AC AIRCRAFT AC AIR CONTROLLER AC ADVISORY CIRCULAR AC ASPHALT CONCRETE ACAA AIR CARRIER ACCESS ACT ACAA AIR CARRIER ASSOCIATION OF AMERICA ACAIS AIR CARRIER ACTIVITY INFORMATION SYSTEM ACC AREA CONTROL CENTER ACC AIRPORT CONSULTANTS COUNCIL ACC AIRCRAFT COMMANDER ACC AIR CENTER COMMANDER ACCC AREA CONTROL COMPUTER COMPLEX ACDA APPROACH CONTROL DESCENT AREA ACDO AIR CARRIER DISTRICT OFFICE ACE AVIATION CAREER EDUCATION ACE CENTRAL REGION OF FAA ACF AREA CONTROL FACILITY ACFT AIRCRAFT ACI-NA AIRPORTS COUNCIL INTERNATIONAL - NORTH AMERICA ACID AIRCRAFT IDENTIFICATION ACIP AIRPORT CAPITAL IMPROVEMENT PLANNING ACLS AUTOMATIC CARRIER LANDING SYSTEM ACLT ACTUAL CALCULATED LANDING TIME Page 2 ACMI AIRCRAFT, CREW, MAINTENANCE AND INSURANCE (cargo) ACOE U.S. ARMY -
Development of a Methodology for Parametric Analysis of STOL Airpark Geo-Density
Development of a Methodology for Parametric Analysis of STOL Airpark Geo-Density Joseph N. Robinson∗, Max-Daniel Sokollek†, Cedric Y. Justin‡, and Dimitri N. Mavris§ Georgia Institute of Technology, Atlanta, Georgia, 30332-0150, United States Vehicles designed for urban air mobility (UAM) or on-demand mobility (ODM) applications typically adopt an architecture enabling vertical takeoff and landing (VTOL) capabilities. UAM or ODM systems featuring these capabilities typically have a smaller ground footprint but are subject to a number of performance compromises that make sizing and optimizing the vehicles more challenging. These design challenges can be further compounded when additional environmental considerations are taken into account and in particular if electric propulsion is considered. Alternative architectures such as short takeoff and landing (STOL) and super-short takeoff and landing (SSTOL) vehicles are thus investigated because they present possible advantages in terms of energy efficiency, overall vehicle performance, and noise footprint. However, the larger ground footprint of the infrastructure necessary to operate these systems means that these systems may be more difficult to integrate into a urban and suburban environment. One objective of this research is to estimate the geo-density of airparks suitable for STOL and SSTOL operations based on vehicle performance and ground footprint parameters. In turn, this helps establish requirements for the field performances of STOL and SSTOL vehicles to be considered for ODM and UAM applications. This research proposes and interactive and parametric design and trade-off analysis environment to help decision makers assess the suitability of candidate cities for STOL and SSTOL operations. Preliminary results for the Miami metropolitan area show that an average airpark geo-density of 1.66 airparks per square mile can be achieved with a 300 foot long runway.