Preliminary Aerodynamic Design of a Reusable Booster Flight Experiment
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Validation of Wind Tunnel Test and Cfd Techniques for Retro-Propulsion (Retpro): Overview on a Project Within the Future Launchers Preparatory Programme (Flpp)
VALIDATION OF WIND TUNNEL TEST AND CFD TECHNIQUES FOR RETRO-PROPULSION (RETPRO): OVERVIEW ON A PROJECT WITHIN THE FUTURE LAUNCHERS PREPARATORY PROGRAMME (FLPP) D. Kirchheck, A. Marwege, J. Klevanski, J. Riehmer, A. Gulhan¨ German Aerospace Center (DLR) Supersonic and Hypersonic Technologies Department Cologne, Germany S. Karl O. Gloth German Aerospace Center (DLR) enGits GmbH Spacecraft Department Todtnau, Germany Gottingen,¨ Germany ABSTRACT and landing (VTVL) spacecraft, assisted by retro-propulsion. Up to now, in Europe, knowledge and expertise in that field, The RETPRO project is a 2-years activity, led by the Ger- though constantly growing, is still limited. Systematic stud- man Aerospace Center (DLR) in the frame of ESA’s Future ies were conducted to compare concepts for possible future Launchers Preparatory Program (FLPP), to close the gap of European launchers [2, 3], and activities on detailed inves- knowledge on aerodynamics and aero-thermodynamics of tigations of system components of VTVL re-usable launch retro-propulsion assisted landings for future concepts in Eu- vehicles (RLV) recently started in the RETALT project [4, 5]. rope. The paper gives an overview on the goals, strategy, and Nevertheless, validated knowledge on the aerodynamic current status of the project, aiming for the validation of inno- and aerothermal characteristics of such vehicles is still lim- vative WTT and CFD tools for retro-propulsion applications. ited to a small amount of experimental and numerical inves- Index Terms— RETPRO, retro-propulsion, launcher tigations mostly on lower altitude VTVL trajectories, e. g. aero-thermodynamics, wind tunnel testing, CFD validation within the CALLISTO project [6, 7, 8]. Other studies were conducted to analyze the aerothermodynamics of a simplified generic Falcon 9 geometry during its re-entry and landing 1. -
Reusable Launch Vehicle Technology Program{
Acta Astronautica Vol. 41, No. 11, pp. 777±790, 1997 # 1998 Published by Elsevier Science Ltd. All rights reserved Printed in Great Britain PII: S0094-5765(97)00197-5 0094-5765/98 $19.00 + 0.00 REUSABLE LAUNCH VEHICLE TECHNOLOGY PROGRAM{ DELMA C. FREEMAN{ JR. and THEODORE A. TALAY} NASA Langley Research Center, Hampton, Virginia 23681-0001, USA R. EUGENE AUSTIN} NASA Marshall Space Flight Center, Marshall Space Flight Center, Alabama 35812-1000, USA (Received 25 April 1997) AbstractÐIndustry/NASA reusable launch vehicle (RLV) technology program eorts are underway to design, test, and develop technologies and concepts for viable commercial launch systems that also satisfy national needs at acceptable recurring costs. Signi®cant progress has been made in understanding the technical challenges of fully reusable launch systems and the accompanying management and oper- ational approaches for achieving a low-cost program. This paper reviews the current status of the RLV technology program including the DC-XA, X-33 and X-34 ¯ight systems and associated technology programs. It addresses the speci®c technologies being tested that address the technical and operability challenges of reusable launch systems including reusable cryogenic propellant tanks, composite structures, thermal protection systems, improved propul- sion, and subsystem operability enhancements. The recently concluded DC-XA test program demon- strated some of these technologies in ground and ¯ight tests. Contracts were awarded recently for both the X-33 and X-34 ¯ight demonstrator systems. The Orbital Sciences Corporation X-34 ¯ight test ve- hicle will demonstrate an air-launched reusable vehicle capable of ¯ight to speeds of Mach 8. -
A Review of Current Research in Subscale Flight Testing and Analysis of Its Main Practical Challenges
aerospace Article A Review of Current Research in Subscale Flight Testing and Analysis of Its Main Practical Challenges Alejandro Sobron * , David Lundström and Petter Krus Department of Management and Engineering, Division of Fluid and Mechatronic Systems, Linköping University, SE-58183 Linköping, Sweden; [email protected] (D.L.); [email protected] (P.K.) * Correspondence: [email protected]; Tel.: +46-1328-1893 Abstract: Testing of untethered subscale models, often referred to as subscale flight testing, has traditionally had a relatively minor, yet relevant use in aeronautical research and development. As recent advances in electronics, rapid prototyping and unmanned-vehicle technologies expand its capabilities and lower its cost, this experimental method is seeing growing interest across academia and the industry. However, subscale models cannot meet all similarity conditions required for simulating full-scale flight. This leads to a variety of approaches to scaling and to other alternative applications. Through a literature review and analysis of different scaling strategies, this study presents an overall picture of how subscale flight testing has been used in recent years and synthesises its main issues and practical limitations. Results show that, while the estimation of full-scale characteristics is still an interesting application within certain flight conditions, subscale models are progressively taking a broader role as low-cost technology-testing platforms with relaxed similarity constraints. Different approaches to tackle the identified practical challenges, implemented both by the authors and by other organisations, are discussed and evaluated through flight experiments. Citation: Sobron, A.; Lundström, D.; Keywords: subscale flight testing; similarity; scale model; remotely piloted aircraft; demonstration; Krus, P. -
+ Part 10: Test and Evaluation
10. Test and Evaluation 10.1 Approach Architecture Design, Development, Test, and Evaluation (DDT&E) schedule, costs, and risk are highly dependent on the integrated test and evaluation approach for each of the major elements. As a part of the Exploration Systems Architecture Study (ESAS), a top-level test and evaluation plan, including individual flight test objectives, was developed and is summarized in this section. The test and evaluation plan described here is derived from the Apollo Flight Test Program of the 1960s. A more detailed test and evaluation plan will be based on detailed verification requirements and objectives documented in specifications and verification plans. In order to support schedule, cost, and risk assessments for the reference ESAS architecture, an integrated test and evaluation plan was developed to identify the number and type of major test articles (flight and ground) and the timing and objectives of each major flight test, including facilities and equipment required to support those tests. This initial plan is based on the Apollo Program and the ESAS Ground Rules and Assumptions (GR&As)—including the human- rating requirements from NASA Procedural Requirements (NPR) 8705.2A, Human-Rating Requirements for Space Systems. 10. Test and Evaluation 645 10.2 Ground Rules and Assumptions ESAS GR&As establish the initial set of key constraints to testing. Although all ESAS GR&As are considered, the specific ones listed below are particularly significant, as they deal with schedule and testing/qualification assumptions. • The crew launch system shall facilitate crew survival using abort and escape. There will be three all-up tests of the Launch Abort System (LAS). -
Abstract US Patent References
Architecture for Reusable Responsive Exploration Systems: ARES - Platform and Reusable Responsive Architecture for Innovative Space Exploration: PRAISE (Part 1) PATENT PENDING Abstract A comprehensive Modular Reusable Responsive Space Exploration Platform (Architecture) composed of multiple modular reusable elements such that the assemblies can be flexibly configured into systems for low earth orbits launches and for long-range exploration such as orbits to moon, Lagrange points and others. This platform & architecture is named as Architecture for Reusable Responsive Exploration System (acronym ARES) / Platform and Reusable Responsive Architecture for Innovative Space Exploration (acronym PRAISE), in short ARES/PRAISE or simply ARES. It is also known as Alpha Spaces Architecture and Platform (acronym ASAP), in short as “αPlatform” or “αArchitecture”, or “αAres”. As an example, the configuration involves reusable lightweight wing, core stage, (optional booster stages) combination of expendable upper stage and reusable crew capsule. Further, the expendable upper stage can be re-used to serve as in-orbit fuel depots and for other innovative uses. This is first part of the multi part patent application. Inventor: Atreya, Dinesh S. US Patent References US Patent 6158693 - Recoverable booster stage and recovery method US Patent 4878637 - Modular space station US Patent 6726154 - Reusable space access launch vehicle system US Patent 6113032 - Delivering liquid propellant in a reusable booster stage US Patent 4557444 - Aerospace vehicle US Patent 4880187 - Multipurpose modular spacecraft US Patent 4452412 - Space shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank US Patent 4802639 - Horizontal-takeoff transatmospheric launch system US Patent 4884770 - Earth-to-orbit vehicle providing a reusable orbital stage US Patent 4265416 - Orbiter/launch system U.S. -
Flight Engineer Knowledge Test Guide
AC 63-1 FLIGHT ENGINEER KNOWLEDGE TEST GUIDE U.S. Department of Transportation Federal Aviation Administration 1 FLIGHT ENGINEER KNOWLEDGE TEST GUIDE 1995 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION Flight Standards Service 2 PREFACE The Flight Standards Service of the Federal Aviation Administration (FAA) has developed this guide to help applicants meet the knowledge requirements for the computer administered tests for flight engineer turbojet, turboprop, and reciprocating class certification. This guide contains information about the knowledge test eligibility requirements, test descriptions, testing and retesting procedures, and sample test questions with answers. As a convenience to the applicant, the eligibility requirements for the oral and flight tests are included. Appendix 1 provides a list of reference materials and subject matter knowledge codes, and computer testing designees. Changes to the subject matter knowledge code list will be published as a separate advisory circular. The sample questions and answers in this guide are predicated on Federal Aviation Regulations (FAR's) and references that were current at the time of publication. Questions and answers in the computer administered knowledge tests are updated when changes are made to these reference materials. The flight engineer test question bank and subject matter knowledge code list for all airmen certificates and ratings, with changes, may be obtained by computer access from FedWorld at (703) 321-3339. This bulletin board service is provided by the U.S. Department of Commerce, 24 hours a day, 7 days per week. For technical assistance regarding computer requirements for this service, contact the FedWorld help desk at (703) 487-4608 from 7:30 a.m. -
Feasibility of Reusable Continuous Thrust Spacecraft for Cargo Resupply Missions to Mars
Feasibility of reusable continuous thrust spacecraft for cargo resupply missions to Mars by C. B. Rabotin M.S., ESIEE Paris, 2011 A thesis submitted to the Faculty of the Graduate School of the University of Colorado in partial fulfillment of the requirements for the degree of Masters of Science in Aerospace Engineering Sciences Ann and H.J. Smead Aerospace Engineering Sciences 2017 This thesis entitled: Feasibility of reusable continuous thrust spacecraft for cargo resupply missions to Mars written by C. B. Rabotin has been approved for the Ann and H.J. Smead Aerospace Engineering Sciences Dr. Hanspeter Schaub Dr. Natasha Bosanac Dr. Jay McMahon Date The final copy of this thesis has been examined by the signatories, and we find that both the content and the form meet acceptable presentation standards of scholarly work in the above mentioned discipline. Rabotin, C. B. (M.Sc., Aerospace) Feasibility of reusable continuous thrust spacecraft for cargo resupply missions to Mars Thesis directed by Dr. Hanspeter Schaub Continuous thrust propulsion systems benefit from a much greater efficiency in vacuum than chemical rockets, at the expense of lower instantaneous thrust and high power requirements. The satellite telecommunications industry, known for greatly emphasizing heritage over innovation, now uses electric propulsion for station keeping on a number of spacecraft, and for orbit raising for some smaller satellites, such as the Boeing 702SP platform. Only a few interplanetary missions have relied on continuous thrust for most of their mission, such as ESA's 367 kg SMART-1 and NASA's 1217 kg Dawn mission. The high specific impulse of these continuous thrust engines should make them suitable for transportation of heavy payloads to inner solar system destinations in such a way to limit the dependency on heavy rocket launches. -
UAS FLIGHT TEST for SAFETY and for EFFICIENCY Seamus M
UAS FLIGHT TEST FOR SAFETY AND FOR EFFICIENCY Seamus M. McGovern, U.S. DOT National Transportation Systems Center, Cambridge, Massachusetts Abstract (e.g., SAE International technical standards and recommended practices) but also takes advantage of Manned aircraft that operate in the National competitive racing in order to evaluate new Airspace System (NAS) typically undergo technologies and materials (as it turns out, this may certification flight test to ensure they meet a have applicability to UASs as well with the advent of prescribed level of safety—dependent on their several organizations and sanctioning bodies category—before they are able to enter service [for including the European Rotor Sports Association and example, Federal Aviation Administration (FAA) the Drone Racing League). Other aviation-related advisory circular (AC) 25-7C is the flight-test guide tests and test formats not discussed here include the for certification of transport-category airplanes]. typically Department of Defense-focused With the integration of unmanned aircraft systems developmental test and evaluation; operational test (UAS) into the NAS, in the future some type of and evaluation; and research, development, test, and certification flight test may ultimately be required, evaluation structures. however, even lacking such a requirement UAS manufacturers can find value in flight testing UASs In terms of flight test, the military services have using familiar experimental and certification flight- their own criteria for evaluating their various aircraft. test procedures, the results of which can enhance the These requirements are often bound by contractual safety of the design, the safety of the operation, agreements between the service and the vendor, and/or the efficiency of the operation. -
General Flight Test Theory Applied to Aircraft Modifications
General Flight Test TheoryTUTORIAL Applied to Aircraft Modifications GENERAL FLIGHT TEST THEORY APPLIED TO AIRCRAFT MODIFICATIONS Lt Col Lionel D. Alford, Jr., USAF and Robert C. Knarr Any external aircraft modification has potentially far-reaching effects on the capability of the aircraft to succeed or fail in its mission. The authors take a systematic look at the effects that small changes can have upon the whole, with a series of examples that demonstrate why careful review of data or testing is often vital in the assessment of system modifications. new design aircraft program always external aircraft modification. The aircraft includes an instrumented test to design problems covered here represent Avalidate the analyses. But a modifi- the fundamental characteristics by which cation program may rely instead on pre- aircraft capability is judged. These design viously collected data for model valida- problems, when not properly analyzed and tion. Such a program must adequately tested (if required), have historically address the effects of the modification on resulted in significant degradation of air the aircraft and its mission. The user must worthiness. We define the subject area and judge these effects for their desirability— explain the importance of each problem especially when they degrade mission by discussing the rationale behind stan- capability. But, to be judged, they must dard design practices and air worthiness be fully understood. Reviewing historical and operational considerations for the fleet data or conducting a test are two ways to aircraft. Concrete examples illustrate each validate the data by which these effects case. Although only effects to the C–130 on aircraft capability are judged. -
Soviet Reusable Space Systems Program: Implications for Space Operations in the 1990S
) (I ' ·-·.;;;;:, .. Dire.ctorate of . ttJ _)\ Intelligence . G0 Soviet Reusable Space Systems Program: Implications for Space Operations in the 1990s An Intelligence Assessment SOV 88-10061 sw 88-/IJOj6 Stpu'"hu J9RR Copy Warning Notice Intelligence Sources or Methods Involved (WNINTEL) National &curity Unauthorized Disclosure Information Subject to Criminal Sanctions Oissc:mination Control Abbr~riations NOFORN (NFJ Not releasable to foreien nationals NOSONTR~_CT_CN_C_I ___~N_o_t~re_lc_•_s•_b_le_t~o_c_M_l~rz~~-o_rs_o.,.r~c_o~nl_rz_c~lo_r~/c_o_ns_u_h_z_nt_s PROP IN (PRJ Caution-proprietary inform;.tion involved OR CON (OCJ Dissemination and Cltraction of inform.1tion ---···----------,--,---,---.,.---------,-----controlled by oricinator REl___ This inform3.tion h.u been :~uthorizcd for release to ... ___________,_ __ W_N ______ --:----- WNI ~TEL-Intcllia:cncc sources or mel hods involved A microfiche copy o( I his docu- Clauillcd bl men! is available front OIR/ Declassify: OADR DLB (~82-7177~ printed copies Derived from muhiplc sources from CPAS/IMC(~&l-HOJ; or AIM request to uscrid CPASIMCJ. Rceulu rcccip! of 01 reports can be am need chrouch CPAS/IMC. All material on this ~r:c . --·-------------------- is Unclassified. ') / ' Directorate or lntdligrocc Soviet Reusable Space Systems Program: Implications for Space Operations in the 1990s An lntdligcnce Assessment This paper was prepared b ,Qflicc of Soviet Anal)'sis. an<'.- ~f Science and Weapons Rescare #:ontributions fro. t?_o~ . Comments znd queries arc welcome and may be dircctcdl\0 . or to . USWR. J yrf sov 88-10061 SWS8-100l6 Scpumba 1933 I ' Soviet Reusable Space Systems Program: Implications for Space Operations in the_l990! Key Judgments The Soviets arc developing at least one, and possibly two, reusable space llffurmation availabl~ systems. -
Reusable Launch Systems Aerospace
Nov, 2010 DEPARTMENT OF REUSABLE LAUNCH SYSTEMS AEROSPACE ENGINEERING Soumik Bose Keshav Kishore Anand Indian Institute Of Technology, Kharagpur 1 INTRODUCTION A hundred years ago, on December 17, 1903, Wilbur and Orville Wright successfully achieved a piloted, powered flight. Though the Wright Flyer I flew only 10 ft off the ground for 12 seconds, traveling a mere 120 ft, the aeronautical technology it demonstrated paved the way for passenger air transportation. Man had finally made it to the air. The Wright brother’s plane of 1903 led to the development of aircrafts such as the WWII Spitfire, and others. In 1926 the first passenger plane flew holiday makers from American mainland to Havana and Bahamas. In 23 years the world had moved from a plane that flew 120 ft and similar planes that only a chosen few could fly, to one that can carry many passengers. In October 1957, man entered the space age. Russia sent the first satellite, the Sputnik, and in April 1961, Yuri Gagarin became the first man on space. In the years since Russia and United States has sent many air force pilots and a fewer scientists, engineers and others. But even after almost 50 years, the number of people who has been to space is close to 500. The people are losing interest in seeing a chosen few going to space and the budgets to space research is diminishing. The space industry now makes money by taking satellites to space. But a major factor here is the cost. At present to put a single kilogram into orbit will cost you between $10000 and $20000. -
Re-Usable Launch and Payload Delivery System MDDP 2012/3
Group 2 Re-usable Launch and Payload Delivery System MDDP 2012/3 Re-usable Launch and Payload Delivery System MDDP Group 2 James Dobberson Robert Taylor Matthew Chapman Timothy West Mukudzei Muchengeti William Wou Group 2 Re-usable Launch and Payload Delivery System MDDP 2012/3 1. Contents 1. Contents ..................................................................................................................................... i 2. Executive Summary .................................................................................................................. ii 3. Introduction .............................................................................................................................. 1 4. Down Selection and Integration Methodology ......................................................................... 2 5. Presentation of System Concept and Operations ...................................................................... 5 6. System Investment Plan ......................................................................................................... 20 7. Numerical Analysis and Statement of Feasibility .................................................................. 23 8. Conclusions and Future Work ................................................................................................ 29 9. Launch Philosophy ................................................................................................................. 31 10. Propulsion ..............................................................................................................................