Is the Spaceplane Dead?

Total Page:16

File Type:pdf, Size:1020Kb

Is the Spaceplane Dead? The Air Force has pursued this concept for the past 40 years. Is the Spaceplane Dead? SPACEPLANE has been part Ideas for a spaceplane date back By Rebecca Grant of the Air Force’s long- to German research on rocketry be- A range vision for more than fore World War II. In the Air Force, 40 years. Advocates say a reusable a reusable spaceplane has long been spaceplane could cut launch costs part of the vision for full control and from $10,000 per pound of cargo to exploitation of air and space. $1,000 per pound and give the Air Force much greater flexibility in Schriever’s Vision access to space, whether for main- In 1962, Gen. Bernard A. Schriever taining satellites or performing other described a set of requirements for missions. space capabilities that included the It would also provide the ultimate ability to orbit, maneuver, rendez- counter to any adversary’s anti-ac- vous, de-orbit, re-enter, and land on cess strategies; a spaceplane that can a routine basis. Today, USAF is still fly at Mach 25, reach orbit, and re- at least a decade away from acquir- turn to Earth would be virtually im- ing a reusable spaceplane that can possible to stop before reaching its do the jobs Schriever described. objective. Technology hurdles remain at the But today, there is no single heart of the issue. Hypersonic flight— “spaceplane” on the drawing boards. defined as flying faster than Mach Several experimental vehicles are 5—began to tantalize aerospace en- seeking to demonstrate the technolo- gineers in the 1950s. One early suc- gies needed for a spaceplane. A De- cess was the North American X-15, cember 2000 report from the Air tested at speeds up to Mach 6.7 in the Force’s Scientific Advisory Board 1960s. But for the most part, pro- laid it out: “If the Air Force vision of grams dealing in hypersonics and ‘controlling and exploiting the full reusable spaceflight made only lim- aerospace continuum’ is to become ited progress. One such was the reality, the Air Force needs a com- Boeing X-20 Dyna-Soar, a boost- prehensive plan for hypersonics.” glide vehicle designed to become a Yet the Air Force has been sty- manned, orbital plane. The Air Force mied in its efforts to get Washington funded it in 1957, but Secretary of behind a stated requirement for a Defense Robert S. McNamara can- spaceplane or to fund the extensive celed the X-20 in 1963, and Phase 1 research that is still needed to make of the hypersonic spaceplane era was the concept a reality. The recent de- over. mise of the X-33 spaceplane project Dyna-Soar and other programs signaled that once again, the tech- contributed to the manned space nology hurdle is high and the gap shuttle program. NASA’s space between dollars and rhetoric is deep. shuttle first flew in April 1981 and 68 AIR FORCE Magazine / November 2001 truck and a strike platform, the space- plane would be a revolutionary leap. No “Golden Mission” However, research on NASP stalled when it failed to meet performance goals. By the early 1990s, NASP was projected to be a decade late and 500 percent over budget. NASP was “fully capable of hypersonic flight,” according to the Science Advisory Board, but could not reach orbital velocity. Advanced hypersonic tech- nology remained out of reach. “On the basis of current knowledge, it is hard to defend previous DOD plans for NASP,” concluded a RAND report in 1989. “No compelling ‘golden mission’ exists for NASP.” Cuts in the defense budget and the The quest for hypersonics and reusable spaceflight led in 1957 to the Dyna- end of the Cold War sealed the fate Soar X-20. It was designed to be a manned orbital craft and did contribute to of NASP and the program was can- the space shuttle program but was canceled in 1963. (Artist’s concept) celed in 1994. “These are exciting ideas,” said Martin Faga, assistant has logged more than 100 successful As a result, the National Aero- secretary of the Air Force for space missions, sometimes flying on a space Plane was to be a revolution- at the time, “but they are not ready monthly basis. Still, the shuttle’s need ary advance: a transatmospheric craft for commitment.” for expendable tanks to help it reach that would provide cheaper space Even before the death of NASP, orbit and the continued high cost of launch and the ability to exploit space researchers were focusing on a more each launch differed from the con- in military operations. Plans called cautious approach that divided up cept of a true spaceplane. Better ac- for NASP to fly as a single stage to the technology hurdles of hypersonic cess to space continued to be a driv- low Earth orbit and to cruise at hy- flight and reusable systems. ing issue. personic speeds of Mach 12 to The next “spaceplane experimen- In 1986, President Reagan rein- Mach 25 in the transatmosphere— tal” was an early success that raised vigorated the idea of an airplane- between the altitudes of 100,000 to hopes for both military and commer- like transatmospheric spaceplane. In 350,000 feet. cial applications for a spaceplane. 1986, he called for “a new Orient With the advent of NASP, the McDonnell Douglas won a contract in Express” that could, by the end of spaceplane concept branched into two 1991 to build what became the DC-X the 1990s, “take off from Dulles roles. Delta Clipper. This single-stage-to- Airport and accelerate up to 25 times First, a reusable spaceplane might orbit vehicle grew out of an SDI re- the speed of sound.” In Reagan’s replace the space shuttle as a launch quirement for a single-stage, reusable concept the transatmospheric plane platform carrying heavy payloads for vehicle that could put Brilliant Pebbles, could attain low Earth orbit or stay customers like the Strategic Defense a component of a ballistic missile de- in the atmosphere, “flying to Tokyo Initiative Organization, which con- fense system, into orbit at a reason- within two hours.” tributed heavily to NASP research able price. It was managed by the Air Behind Reagan’s sensational an- funding. Air Force Brig. Gen. Ken- Force for SDIO, later the Ballistic nouncement was hope for a techno- neth E. Staten, NASP program man- Missile Defense Organization. logical breakthrough in the field of ager, said in 1986 that NASP might Although the program was handed hypersonics. Research from a De- be able to deliver payloads to orbit off to NASA, the Delta Clipper stirred fense Advanced Research Projects for “between one percent and 25 Air Force thinking on the possible Agency–funded secret program called percent of the expense of doing it uses of a spaceplane. The commer- Copper Canyon suggested that ac- with the shuttle.” cial potential and simplicity of the tive thermal management could boost Second, for the Air Force, NASP program seemed to foreshadow a new the power of a scramjet engine. In- could also be a lightning-fast bomber. era when commercial launch demand stead of succumbing to a heat barrier Gen. Lawrence A. Skantze in 1985, would help fund spaceplane tech- around Mach 8, the friction from the as commander of Air Force Systems nologies. atmospheric drag would be used as Command, said NASP might have The Delta Clipper was not a hy- part of a system to superheat hydro- “the speed of response of an ICBM personic scramjet spaceplane but a gen fuel then inject it into a scramjet and the flexibility and reliability of single-stage rocket with advanced engine. Using this technique, a space- a bomber, packaged together in a lightweight materials and directional plane might overcome the thermal plane that can scramble, get into or- control. Its charter was to demon- drag barrier by dissipating heat, while bit, and change orbit so [that] the strate the ability to take off and land using the energy to boost engine per- Soviets can’t get a reading accurate vertically, using controlled, rocket- formance. enough to shoot at it.” As a satellite powered flight. In its full concept, AIR FORCE Magazine / November 2001 69 the Clipper would be a reusable ve- All programs shared the same phi- space shuttle program. The linear hicle that could be launched and re- losophy: rapid development of proto- aerospike was designed to increase covered at the same site by a small types, with no more than a few years power and, more importantly, per- ground control team. Maintenance passing between contract award and form with maximum efficiency at a would be streamlined, leading to demonstration. Some, like Boeing’s greater range of altitudes. lower operating and support costs X-37 and X-40, were demonstrators Test of the linear aerospike en- that would bring about a dramatic for a vehicle that would be ferried into gines proceeded smoothly through a reduction in the price of launching orbit, operated by its own rocket en- series of test runs in 2000. The payloads into orbit. The subscale gine, then would return to land on a aerospike engine project manager, demonstrator and an advanced ver- runway. In contrast, Lockheed Martin’s Donald Chenevert, praised the per- sion, the DC-XA, successfully com- X-33 was designed to take off verti- formance of the engines, noting that pleted a series of flights in the pe- cally, fly a suborbital path, and then “few new, much less innovative, riod 1993–96, demonstrating control land horizontally at a US base. Orbital engines even get to full power in so and maneuverability at the White Sciences’ X-34 was a rocketplane de- few tests,” but with X-33’s engines, Sands Missile Range in New Mexico.
Recommended publications
  • The Flight to Orbit
    There are numerous ways to get there— Around the Corner Th As then–US Space Command chief from rocket The Gen. Howell M. Estes III said to launch to space defense writers just before his re- tirement in August, “This is going maneuver to come along a lot quicker than we vehicles—and the think it is. ... We tend to think this stuff is way out there in the future, Air Force is but it’s right around the corner.” keeping its Flight The Air Force and NASA have divided the task of providing the options open. US government with a means of reliable, low-cost transportation to Earth orbit. The Air Force, with the largest immediate need, is heading to up the effort to revamp the Expend- to able Launch Vehicles now used to loft military and other government satellites. Called the Evolved ELV, this program is focused on derivatives of existing rockets. Competitors have been invited to redesign or value- engineer their proven boosters with new materials and technologies to provide reliable launch services at a he Air Force would like to go Orbit far lower price than today’s bench- back and forth to Earth orbit as bit mark of around $10,000 a pound to T O easily as it goes back and forth to Low Earth Orbit. The reasoning is 30,000 feet—routinely, reliably, and that an “evolved”—rather than an relatively cheaply. Such a capability all-new—vehicle will yield cost sav- goes hand in hand with being a true ings while reducing technical risk.
    [Show full text]
  • The SKYLON Spaceplane
    The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration.
    [Show full text]
  • Nasa X-15 Program
    5 24,132 6 9 NASA X-15 PROGRAM By: T.D. Barnes - NASA Contractor - 1960s NASA contractors for the X-15 program were Bendix Field Engineering followed by Unitec, Inc. The NASA High Range Tracking stations were located at Ely and Beatty Nevada with main control being at Dryden/Edwards AFB in California. Personnel at the tracking stations consisted of a Station Manager, a Technical Advisor, and field engineers for the Mod-2 Radar, Data Transmission System, Communications, Telemetry, and Plant Maintenance/Generators. NASA had a site monitor at each tracking station to monitor our contractor operations. Though supporting flights of the X-15 was their main objective, they also participated in flights of the XB-70, the three Lifting Bodies, experimental Lunar Landing vehicles, and an occasional A-12/YF-12/SR-71 Blackbird flight. On mission days a NASA van picked up each member of the crew at their residence for the 4:20 a.m. trip to the tracking station 18 miles North of Beatty on the Tonopah Highway. Upon arrival each performed preflight calibrations and setup of their various systems. The liftoff of the B-52, with the X-15 tucked beneath its wing, seldom occurred after 9:00 a.m. due to the heat effect of the Mojave Desert making it difficult for the planes to acquire altitude. At approximately 0800 hours two pilots from Dryden would proceed uprange to evaluate the condition of the dry lake beds in the event of an emergency landing of the X-15 (always buzzing our station on the way up and back).
    [Show full text]
  • Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft Through Parametric Studies
    energies Article Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies Andrew Ridgway, Ashish Alex Sam * and Apostolos Pesyridis College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK; [email protected] (A.R.); [email protected] (A.P.) * Correspondence: [email protected]; Tel.: +44-1895-267-901 Received: 26 September 2018; Accepted: 7 December 2018; Published: 10 December 2018 Abstract: This paper aims to contribute to developing a potential combined cycle air-breathing engine integrated into an aircraft design, capable of performing flight profiles on a commercial scale. This study specifically focuses on the single expansion ramp nozzle (SERN) and aircraft-engine integration with an emphasis on the combined cycle engine integration into the conceptual aircraft design. A parametric study using computational fluid dynamics (CFD) have been employed to analyze the sensitivity of the SERN’s performance parameters with changing geometry and operating conditions. The SERN adapted to the different operating conditions and was able to retain its performance throughout the altitude simulated. The expansion ramp shape, angle, exit area, and cowl shape influenced the thrust substantially. The internal nozzle expansion and expansion ramp had a significant effect on the lift and moment performance. An optimized SERN was assembled into a scramjet and was subject to various nozzle inflow conditions, to which combustion flow from twin strut injectors produced the best thrust performance. Side fence studies observed longer and diverging side fences to produce extra thrust compared to small and straight fences. Keywords: scramjet; single expansion ramp nozzle; hypersonic aircraft; combined cycle engines 1.
    [Show full text]
  • Delta Clipper a Path to the Future
    Delta Clipper A Path to the Future By Jason Moore & Ashraf Shaikh Executive Summary Although the Space Shuttle has well served its purpose for years, in order to revitalize and advance the American space program, a new space launch vehicle is needed. A prime candidate for the new manned launch vehicle is the DC-X. The DC-X isn’t a state-of-the-art rocket that would require millions of dollars of new development. The DC-X is a space launch vehicle that has already been tested and proven. Very little remains to be done in order to complete the process of establishing the DC-X as an operational vehicle. All that’s left is the building and final testing of a full-size DC-X, followed by manufacture and distribution. The Space Shuttle, as well as expendable rockets, is very expensive to build, maintain and launch. Costing approximately half a billion dollars for each flight, NASA can only afford to do a limited number of Space Shuttle missions. Also, the Shuttle is maintenance intensive, requiring hundreds of man-hours of maintenance after each flight. The DC-X, however, is very cheap to build, easy to maintain, and much cheaper to operate. If the DC-X was used as NASA’s vehicle of choice, NASA could afford to put more payloads into orbit, and manned space missions wouldn’t be the relative rarity they are now. Since not much remains in order to complete the DC-X, a new private organization dedicated solely to the DC-X would be the ideal choice for the company that would build it.
    [Show full text]
  • Flight Data Analysis of the HYSHOT Flight #2 Scramjet
    13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference Flight Data Analysis of HyShot 2 Neal E. Hass*, Michael K. Smart+ NASA Langley Research Center, Hampton, Virginia Allan Paull! University of Queensland, Brisbane, Australia Abstract The development of scramjet propulsion for alternative launch and payload delivery capabilities has comprised largely of ground experiments for the last 40 years. With the goal of validating the use of short duration ground test facilities, the University of Queensland, supported by a large international contingency, devised a ballistic re-entry vehicle experiment called HyShot to achieve supersonic combustion in flight above Mach 7.5. It consisted of a double wedge intake and two back-to-back constant area combustors; one supplied with hydrogen fuel at an equivalence ratio of 0.33 and the other un-fueled. Following a first launch failure on October 30th 2001, the University of Queensland conducted a successful second launch on July 30th, 2002. Post-flight data analysis of the second launch confirmed the presence of supersonic combustion during the approximately 3 second test window at altitudes between 35 and 29 km. Reasonable correlation between flight and some pre-flight shock tunnel tests was observed. Nomenclature f aerodynamic factor h altitude M Mach number P pressure q dynamic pressure s seconds T temperature V velocity w mass flow X axial coordinate Y lateral coordinate Z normal coordinate α angle-of-attack ηc combustion efficiency γ ratio of specific heats φ equivelance ratio ω angular velocity about longitudinal body axis ζ angular velocity of longitudinal axis about velocity vector * Aerospace Engineer, Hypersonic Airbreathing Propulsion Branch + Research Scientist, Hypersonic Airbreathing Propulsion Branch ! Professor, Mechanical Engineering Department 1 Subscripts: 0 freestream c combustor entrance w wedge t2 Pitot Introduction The theoretical performance advantage of scramjets over rockets in hypersonic flight has been well known since the 1950’s.
    [Show full text]
  • Ciam/Nasa Mach 6.5 Scramjet Flight and Ground Test
    AIAA-99-4848 CIAM/NASA MACH 6.5 SCRAMJET FLIGHT AND GROUND TEST R. T. Voland* and A. H. Auslender** NASA Langley Research Center Hampton, VA M. K. Smart Lockheed Martin Engineering Sciences Hampton, VA A.S. Roudakovà, V.L. Semenov¤, and V. Kopchenov¤ Central Institute of Aviation Motors Moscow, Russia ABSTRACT NOMENCLATURE The Russian Central Institute of Aviation Motors (CIAM) performed a flight test of a CIAM-designed, C-16V/K Ð CIAM scramjet engine ground test facility, hydrogen-cooled/fueled dual-mode scramjet engine located in Tureavo, Russia (Figure 10) over a Mach number range of approximately 3.5 to 6.4 CIAM Ð Central Institute of Aviation Motors, Moscow, on February 12, 1998, at the Sary Shagan test range in Russia Kazakhstan. This rocket-boosted, captive-carry test of CO2 Ð Carbon dioxide the axisymmetric engine reached the highest Mach Cp Ð Pressure Coefficient number of any scramjet engine flight test to date. The H Ð Altitude (km, m, or ft) flight test and the accompanying ground test program, H2 Ð Hydrogen conducted in a CIAM test facility near Moscow, were H2O Ð Water performed under a NASA contract administered by the He Ð Helium Dryden Flight Research Center with technical HFL Ð Hypersonic Flying Laboratory assistance from the Langley Research Center. Analysis HRE Ð Hypersonic Research Engine of the flight and ground data by both CIAM and NASA HRE AIM Ð Hypersonic Research Engine, resulted in the following preliminary conclusions. An Aerothermodynamic Integration Model unexpected control sensor reading caused non-optimal Hyper-X Ð NASA airframe integrated scramjet- fueling of the engine, and flowpath modifications added powered vehicle flight test program to the engine inlet during manufacture caused markedly ht Ð Total enthalpy (MJ/kg or Btu/lbm) reduced inlet performance.
    [Show full text]
  • Chemical Kinetics of SCRAMJET Propulsion by Rodger Joseph Biasca Master of Science Aeronautics and Astronautics at the Massachus
    Chemical Kinetics of SCRAMJET Propulsion by Rodger Joseph Biasca S.B. Aeronautics and Astronautics, Massachusetts Institute of Technology, 1987 SUBMITTED IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF Master of Science in Aeronautics and Astronautics at the Massachusetts Institute of Technology July 1988 ©1988, Rodger J. Biasca The author hereby grants to MIT and the Charles Stark Draper Laboratory, Inc. permission to reproduce and distribute copies of this thesis document in whole or in part. Signature of Author Department of Aeronautics and Astronautics July 1988 Certified by Professor Jean F. Louis, Co- Thesis Supervisor Department of Aeronautics and Astronautics Professor Manuel Martinez-Sanchez, Co- Thesis Supervisor pepartment of Aeronautics and Astronautics nr Phillin T). Hattis, Technical Supervisor s Stark Draper Laboratory Accepted by xtew,Ex3.*sh \. Professor Harold Y. Wachman,Chairman Department Graduate Committee MAOHUSET1S r1nTSrn OF TEO LOGY TH DRWN SEP 07 1988 A MVrN UU. fl~ u<;HZSR3ES~!'-~' Chemical Kinetics of SCRAMJET Propulsion by Rodger Joseph Biasca Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics Recent interest in hypersonics has focused on the development of a single stage to orbit vehicle propelled by hydrogen fueled SCRAMJETs. Necessary for the design of such a vehicle is a thorough understanding of the chemical kinetic mechanism of hydrogen-air combustion and the possible effect this mechanism may have on the performance of the SCRAMJET propulsion system. This thesis investigates possible operational limits placed on a SCRAMJET powered vehicle by the chemical kinetics of the combustion mechanism and estimates the performance losses associated with chemical kinetic effects.
    [Show full text]
  • Columbia Accident Investigation Board
    COLUMBIA ACCIDENT INVESTIGATION BOARD Report Volume I August 2003 COLUMBIA ACCIDENT INVESTIGATION BOARD On the Front Cover This was the crew patch for STS-107. The central element of the patch was the microgravity symbol, µg, flowing into the rays of the Astronaut symbol. The orbital inclination was portrayed by the 39-degree angle of the Earthʼs horizon to the Astronaut symbol. The sunrise was representative of the numerous science experiments that were the dawn of a new era for continued microgravity research on the International Space Station and beyond. The breadth of science conduct- ed on this mission had widespread benefits to life on Earth and the continued exploration of space, illustrated by the Earth and stars. The constellation Columba (the dove) was chosen to symbolize peace on Earth and the Space Shuttle Columbia. In addition, the seven stars represent the STS-107 crew members, as well as honoring the original Mercury 7 astronauts who paved the way to make research in space possible. The Israeli flag represented the first person from that country to fly on the Space Shuttle. On the Back Cover This emblem memorializes the three U.S. human space flight accidents – Apollo 1, Challenger, and Columbia. The words across the top translate to: “To The Stars, Despite Adversity – Always Explore“ Limited First Printing, August 2003, by the Columbia Accident Investigation Board Subsequent Printing and Distribution by the National Aeronautics and Space Administration and the Government Printing Office Washington, D.C. 2 Report Volume I August 2003 COLUMBIA ACCIDENT INVESTIGATION BOARD IN MEMORIAM Rick D. Husband Commander William C.
    [Show full text]
  • Boarding the Spaceplane by Roger D
    PageMark-Color-Comp Job Name: 546280_SpaceTimes_Oct2015 ❏ OK to proceed PDF Page: 01_24_SpaceTimes_Oct2015.p4.pdf ❏ Make corrections and proceed Process Plan: VP.MultiPage.PDF Date: 15-10-01 ❏ Make corrections and show another proof Time: 15:28:48 Signed: ___________________ Date: ______ Operator: ____________________________ Boarding the Spaceplane by Roger D. Launius During the administration of President Ronald Reagan, senior government officials began to discuss the possibility of developing an “Orient Express,” a hybrid air and spaceplane that could carry ordinary people between New York City and Tokyo in about one hour. How is this possible? Actually, the concept is quite simple: Develop an aerospace plane that can take off like a conventional jetliner from an ordinary runway. Flying supersonic, it reaches an altitude of 45,000-50,000 feet, where the pilots start scramjet engines, a jet technology that has the potential to push jetcraft to hypersonic speeds. The spaceplane rises to the edge of space and darts to the opposite side of the globe, where the process is reversed, and the vehicle lands like a conventional airplane. It never reaches orbit, but technically it flies in space. The experience is similar to orbital flight, except for the shorter time. Artist concept of the X-37 advanced technology flight demonstrator re-entering Earth’s atmosphere. The X-37 was intended as a testbed for dozens of advanced structural, propulsion, and operational technologies that could dramatically lower the cost of future reusable launch vehicles. (Source: NASA) 4 SPACE TIMES • September/October 2015 PageMark-Color-Comp Job Name: 546280_SpaceTimes_Oct2015 ❏ OK to proceed PDF Page: 01_24_SpaceTimes_Oct2015.p5.pdf ❏ Make corrections and proceed Process Plan: VP.MultiPage.PDF Date: 15-10-01 ❏ Make corrections and show another proof Time: 15:28:48 Signed: ___________________ Date: ______ Operator: ____________________________ The spaceplane concept has long been a staple of dreams of spaceflight.
    [Show full text]
  • Space Planes and Space Tourism: the Industry and the Regulation of Its Safety
    Space Planes and Space Tourism: The Industry and the Regulation of its Safety A Research Study Prepared by Dr. Joseph N. Pelton Director, Space & Advanced Communications Research Institute George Washington University George Washington University SACRI Research Study 1 Table of Contents Executive Summary…………………………………………………… p 4-14 1.0 Introduction…………………………………………………………………….. p 16-26 2.0 Methodology…………………………………………………………………….. p 26-28 3.0 Background and History……………………………………………………….. p 28-34 4.0 US Regulations and Government Programs………………………………….. p 34-35 4.1 NASA’s Legislative Mandate and the New Space Vision………….……. p 35-36 4.2 NASA Safety Practices in Comparison to the FAA……….…………….. p 36-37 4.3 New US Legislation to Regulate and Control Private Space Ventures… p 37 4.3.1 Status of Legislation and Pending FAA Draft Regulations……….. p 37-38 4.3.2 The New Role of Prizes in Space Development…………………….. p 38-40 4.3.3 Implications of Private Space Ventures…………………………….. p 41-42 4.4 International Efforts to Regulate Private Space Systems………………… p 42 4.4.1 International Association for the Advancement of Space Safety… p 42-43 4.4.2 The International Telecommunications Union (ITU)…………….. p 43-44 4.4.3 The Committee on the Peaceful Uses of Outer Space (COPUOS).. p 44 4.4.4 The European Aviation Safety Agency…………………………….. p 44-45 4.4.5 Review of International Treaties Involving Space………………… p 45 4.4.6 The ICAO -The Best Way Forward for International Regulation.. p 45-47 5.0 Key Efforts to Estimate the Size of a Private Space Tourism Business……… p 47 5.1.
    [Show full text]
  • EMISSION CALCULATIONS for a SCRAMJET POWERED HYPERSONIC TRANS PORT by Erwin A
    NASA TECHNICAL NASA TM X-71464 MEMORANDUM (NASA-TM-X-71464) EMISSION CALCULATIONS N74- 1244 FOR A'SCRANJET POWERED HYPERSONIC TRANSPORT (NASA) 32 p HC $3.75 CSCL 21E Unclas G3/28 2277 1 Cc EMISSION CALCULATIONS FOR A SCRAMJET POWERED HYPERSONIC TRANS PORT by Erwin A. Lezberg Lewis Research Center Cleveland, Ohio 44135 November, 1973 EMISSION CALCULATIONS FOR A SCRAMJET POWERED HYPERSONIC TRANSPORT by Erwin A. Lezberg Lewis Research Center ABSTRACT Calculations of exhaust emissions from a scramjet powered hy- personic transport burning hydrogen fuel have been performed over a range of Mach numbers of 5 to 12 to provide input data for wake mixing calculations and forecasts of future levels of pollutants in the strato- sphere. The calculations were performed utilizing a one-dimensional chem- ical kinetics computer program for the combustor and exhaust nozzle of a fixed geometry dual-mode scramjet engine. Inlet conditions to the combustor and engine size was based on a vehicle of 2.27x10 5 kg (500 000 lb) gross take of weight with engines sized for Mach 8 cruise. Nitric oxide emissions were very high for stoichiometric engine operation but for Mach 6 cruise at reduced equivalence ratio are in the range predicted for an advanced supersonic transport. Combustor de- signs which utilize fuel staging and rapid expansion to minimize resi- dence time at high combustion temperatures were found to be effective in preventing nitric oxide formation from reaching equilibrium concen- trations. INTRODUCTION Calculations of exhaust emissions from a scramjet powered hyper- sonic transport burning hydrogen fuel have been performed over a range of Mach numbers to provide input data for wake mixing calculations and forecasts of future levels of pollutants in the stratosphere.
    [Show full text]