A reusable launch system (RLS, or reusable launch vehicle, RLV) is a space launch system intended to allow for recovery of all or part of the system for later reuse. To date, several fully reusable sub-orbital systems and partially reusable orbital systems have been flown. However the design issues are extremely challenging and no fully reusable orbital launch system has yet been demonstrated. A wide variety of system concepts have been proposed, and several are represented in those which have actually flown.
An orbital spaceflight is a spaceflight in which a spacecraft is placed on a trajectory where it could remain in space for at least one orbit. To do this around the Earth, it must be on a free trajectory which has an altitude at perigee above 100 kilometers (62 mi); this is, by at least one convention, the boundary of space. To remain in orbit at this altitude requires an orbital speed of ~7.8 km/s. Orbital speed is slower for higher orbits, but attaining them requires greater delta-v.
The first aircraft to attain sub-orbital flight was the North American X-15. The first reusable vehicle to reach orbit was NASA's Space Shuttle. It was intended to reduce launch costs below those of expendable launch systems, but instead ended up being more expensive. The last Shuttle was retired in 2011.
The North American X-15 was a hypersonic rocket-powered aircraft operated by the United States Air Force and the National Aeronautics and Space Administration as part of the X-plane series of experimental aircraft. The X-15 set speed and altitude records in the 1960s, reaching the edge of outer space and returning with valuable data used in aircraft and spacecraft design. The X-15's official world record for the highest speed ever recorded by a manned, powered aircraft, set in October 1967 when William J. Knight flew Mach 6.70 at 102,100 feet (31,120 m), a speed of 4,520 miles per hour, has remained unbroken as of 2017.
The National Aeronautics and Space Administration is an independent agency of the United States Federal Government responsible for the civilian space program, as well as aeronautics and aerospace research.
The Space Shuttle was a partially reusable low Earth orbital spacecraft system operated by the U.S. National Aeronautics and Space Administration (NASA) as part of the Space Shuttle program. Its official program name was Space Transportation System (STS), taken from a 1969 plan for a system of reusable spacecraft of which it was the only item funded for development. The first of four orbital test flights occurred in 1981, leading to operational flights beginning in 1982. In addition to the prototype whose completion was cancelled, five complete Shuttle systems were built and used on a total of 135 missions from 1981 to 2011, launched from the Kennedy Space Center (KSC) in Florida. Operational missions launched numerous satellites, interplanetary probes, and the Hubble Space Telescope (HST); conducted science experiments in orbit; and participated in construction and servicing of the International Space Station. The Shuttle fleet's total mission time was 1322 days, 19 hours, 21 minutes and 23 seconds.
During the 21st century, commercial interest in reusable launch systems has grown. The SpaceX Falcon 9 rocket has a reusable first stage and expendable second stage, and is currently in use for the NASA Commercial Orbital Transportation Services program and commercial satellite launches. Additionally, SpaceX is developing the fully reusable BFR for manned interplanetary missions. Scaled Composites have flown two prototype sub-orbital spaceplanes for Virgin Galactic, while the Blue Origin New Shepard rocket has recoverable first and second stages but is only capable of suborbital flights.
Space Exploration Technologies Corp., doing business as SpaceX, is a private American aerospace manufacturer and space transportation services company headquartered in Hawthorne, California. It was founded in 2002 by entrepreneur Elon Musk with the goal of reducing space transportation costs and enabling the colonization of Mars. SpaceX has since developed the Falcon launch vehicle family and the Dragon spacecraft family, which both currently deliver payloads into Earth orbit.
Falcon 9 is a two-stage-to-orbit medium lift launch vehicle designed and manufactured by SpaceX in the United States. It is powered by Merlin engines, also developed by SpaceX, burning liquid oxygen (LOX) and rocket-grade kerosene (RP-1) propellants. It was named after the Millennium Falcon and the nine engines of the rocket's first stage. The rocket evolved with versions v1.0 (2010–2013), v1.1 (2013–2016), v1.2 "Full Thrust" (2015–2018), and its Block 5 variant, flying since May 2018. Unlike most rockets, which are expendable launch systems, Falcon 9 is partially reusable, with the first stage capable of re-entering the atmosphere and landing back vertically after separating from the second stage. This feat was achieved for the first time on flight 20 with the v1.2 version in December 2015.
Commercial Orbital Transportation Services (COTS) was a NASA program to coordinate the delivery of crew and cargo to the International Space Station by private companies. The program was announced on January 18, 2006 and successfully flew all cargo demonstration flights by September 2013. NASA has suggested that "Commercial services to ISS will be necessary through at least 2015."
There are two approaches to Single stage to orbit or SSTO. The rocket equation says that an SSTO vehicle needs a high mass ratio. "Mass ratio" is defined as the mass of the fully fueled vehicle divided by the mass of the vehicle when empty (zero fuel weight, ZFW).
A single-stage-to-orbit vehicle reaches orbit from the surface of a body without jettisoning hardware, expending only propellants and fluids. The term usually, but not exclusively, refers to reusable vehicles. No Earth-launched SSTO launch vehicles have ever been constructed. To date, orbital launches have been performed either by multi-stage fully or partially expendable rockets, the Space Shuttle having both attributes.
In aerospace engineering, mass ratio is a measure of the efficiency of a rocket. It describes how much more massive the vehicle is with propellant than without; that is, the ratio of the rocket's wet mass to its dry mass. A more efficient rocket design requires less propellant to achieve a given goal, and would therefore have a lower mass ratio; however, for any given efficiency a higher mass ratio typically permits the vehicle to achieve higher delta-v.
One way to increase the mass ratio is to reduce the mass of the empty vehicle by using very lightweight structures and high-efficiency engines. This tends to push up maintenance costs as component reliability can be impaired, and makes reuse more expensive to achieve.
Another is to reduce the weight of oxidant carried, by burning the fuel in air during the atmospheric stage of flight. A dual-cycle powerplant such as a liquid air cycle engine or the proposed SABRE engine is used.
A liquid air cycle engine (LACE) is a type of spacecraft propulsion engine that attempts to increase its efficiency by gathering part of its oxidizer from the atmosphere. A liquid air cycle engine uses liquid hydrogen (LH2) fuel to liquefy the air.
SABRE is a concept under development by Reaction Engines Limited for a hypersonic precooled hybrid air-breathing rocket engine. The engine is being designed to achieve single-stage-to-orbit capability, propelling the proposed Skylon spaceplane to low Earth orbit. SABRE is an evolution of Alan Bond's series of liquid air cycle engine (LACE) and LACE-like designs that started in the early/mid-1980s for the HOTOL project.
The margins are so small with the SSTO approach that there is uncertainty whether such a vehicle could carry any payload into orbit.
Two stage to orbit uses two vehicles, joined together at launch. Usually the second-stage orbiter is 5-10 times smaller than the first-stage launcher, although in biamese and triameseconfigurations both vehicles are the same size.
Besides the cost of developing two independent vehicles, the complexity of the interactions between them both as a unit and when separating must also be evaluated.
In addition, the first stage needs to be returned to the launch site for it to be reused. This is usually proposed to be done by flying a compromise trajectory that keeps the first stage above or close to the launch site at all times, or by using small air-breathing engines to fly the vehicle back, or by recovering the first stage down range and returning it some other way (often landing in the sea, and returning it by ship.) Most techniques involve some performance penalty; these can require the first stage to be several times larger for the same payload, although for recovery from downrange these penalties may be small.
The second stage is normally returned after flying one or more orbits and reentering.
This is also called a combination launch system.
In a cluster system, multiple stages are stacked side by side and typically burn in parallel, but only one is the orbiter. As the orbiter burns fuel, crossfeeds from the tanks of the booster stages may be used to keep it topped up. Once a booster runs dry it separates and (typically) glides back to a safe landing for re-use. [ citation needed ]
Although not fully re-usable, the Space Shuttle used a similar crossfeed between the main external tank and the Shuttle orbiter.
The fully reusable BAC Mustard project included an engine in each of its near-identical modules, allowing its shut-down engines to be discarded along with the empty tankage, where the Shuttle had the penalty of carrying its shut-down engines into orbit. A criticism of this approach is that designing separate orbiter and boosters, or a single vehicle that could do both, would compromise performance, safety, and possible cost savings. Compromising maximum performance to reduce cargo cost, however, is the point of the clustering approach. Stacking two or three winged vehicles can also be challenging.
All orbital vehicles to date have been launched vertically. Rockets are good for this regime because they have a very high thrust/weight ratio (~100).
Non-rocket spacelaunch systems provide a theoretical increase in efficiency. Since rocket delta-v has a non linear relationship to mass fraction due to the rocket equation, any small reduction in delta-v gives a relatively large reduction in the required mass fraction; and starting a mission at higher altitude also helps.
A vehicle which takes off, or separates from the previous stage horizontally, needs wings. A 'wet wing' might be used, where the wing contains propellant. Wings may be about 9-12% of the vehicle takeoff weight.
Rockets air launched from aircraft may be considered to be at least partially reusable, because the launch aircraft is reusable. An example of this configuration is the Orbital Sciences Pegasus system.
The Scaled Composites Tier One combination of SpaceShipOne and White Knight One used wings on both the launch aircraft and the sub-orbital second stage.
Other proposed launch assists include high-altitude balloons such as the zero2infinity bloostar. km) maglev systems such as launch loops, and more exotic systems such as tether propulsion systems to catch the vehicle at high altitude, or even Space Elevators.More speculative technologies include ground-based sleds, maglev systems, high-altitude (80
Every component vehicle of a reusable system must be able to land safely.
Horizontal landers require wings and undercarriage (unless landing at sea). This typically requires about 9-12% of the landing vehicle to be wings; which in turn implies that the takeoff weight is higher and/or the payload smaller. Concepts such as lifting bodies attempt to deal with the somewhat conflicting issues of reentry, hypersonic and subsonic flight; as does the delta wing shape of the Space Shuttle.
A variety of systems are proposed for vertical landers. Parachutes may be augmented with small landing rockets (as with Soyuz). McDonnell Douglas DC-X ascended to an altitude of about 3.1 kilometers before returning safely. [ citation needed ].Alternatively, rockets could be used to fully decelerate and soft land the vehicle on the ground, after the subsonic speeds had been reached at low altitude (see DC-X). This typically requires about 10% of the vehicle's landing weight to be propellant. SpaceX's Falcon 9 rocket became the first orbital rocket to vertically land its first stage on the ground, after propelling its second stage and payload to a suborbital trajectory, where it would continue on to orbit. A different approach to vertical landing is to use an autogyro or helicopter rotor. This requires perhaps 2-3% of the landing weight for the rotor
Airbreathing approaches use the air during ascent for propulsion. The most commonly proposed approach is the scramjet, but turborocket, Liquid Air Cycle Engine (LACE) and precooled jet engines have also been proposed such as the SABRE engine.
In all cases, the highest speed that an air-breathing engine can reach is far short of orbital speed (about Mach 15 for Scramjets and Mach 5-6 for the other engine designs), and rockets would be used for the remaining 10-20 Mach required for orbit.
The thermal situation for airbreathers (particularly scramjets) can be awkward; normal rockets fly steep initial trajectories to avoid drag, whereas scramjets would deliberately fly through the relatively thick atmosphere at high speed generating enormous heating of the airframe. The thermal situation for the other airbreathing approaches is much more benign, although is not without its challenges.
Any RLV is degrading the launcher's performance compared to ELV due to additional stage inert mass. This additional mass is almost unavoidable due to either supplementary mechanical or propulsion systems or surplus propellant needed for the safe return of RLV stages. The actual amount of the mass penalty and its dispersal between structure and propellant is depending on the chosen RLV stage return modes and staging velocity.
Robert Zubrin has said that as a rough rule of thumb, 15% of the landed weight of a vehicle needs to be aerobraking reentry shielding.
Reentry heat shields on these vehicles are often proposed to be some sort of ceramic and/or carbon-carbon heat shields, or occasionally metallic heat shields (possibly using water cooling or some sort of relatively exotic rare earth metal.)Ablative heat shields offer light weight, but are not reusable.
A newer Thermal Protection System (TPS) technology was first developed for use in steering fins on ICBM MIRVs. Given the need for such warheads to reenter the atmosphere swiftly and retain hypersonic velocities to sea level, researchers developed what are known as SHARP materials, typically hafnium diboride and zirconium diboride, whose thermal tolerance exceeds 3600 C. SHARP equipped vehicles can fly at Mach 11 at 30 km altitude and Mach 7 at sea level. The sharp-edged geometries permitted with these materials also eliminates plasma shock wave interference in radio communications during reentry. SHARP materials are very robust and would not require constant maintenance as did the silica tiles used on the Space Shuttle, which accounted for over half of that vehicle's maintenance costs and turnaround time. The maintenance savings are thus a major factor in favor of using these materials for a reusable launch vehicle.
The research & development costs of reusable vehicle are expected to be higher, because making a vehicle reusable implies making it robust enough to survive more than one use, which adds to the testing required. Increasing robustness is most easily done by adding weight; but this reduces performance and puts further pressure on the R&D to recoup this in some other way.
These extra costs must be recouped; and this pushes up the average cost of the vehicle.
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Reusable launch systems require maintenance, which is often substantial. The Space Shuttle system required extensive refurbishing between flights, primarily dealing with the silica tile TPS and the high performance LH2/LOX burning main engines. Both systems require a significant amount of detailed inspection, rebuilding and parts replacement between flights, and account for over 75% of the maintenance costs of the Shuttle system. These costs, far in excess of what had been anticipated when the system was constructed, have cut the maximum flight rate of Shuttle to 1/4 of that planned. This has also quadrupled the cost per pound of payload to orbit, making Shuttle economically infeasible in today's launch market for any but the largest payloads, for which there is no competition.
For any RLV technology to be successful, it must learn from the failings of Shuttle and overcome those failings with new technologies in the TPS and propulsion areas.
The Space Shuttle program required a standing army of over 9,000 employees to maintain, refurbish, and relaunch the shuttle fleet, irrespective of flight rates. That manpower budget must be divided by the total number of flights per year. The fewer flights means the cost per flight goes up significantly. Streamlining the manpower requirements of any launch system is an essential part of making an RLV economical. Projects that have attempted to develop this ethic include the DC-X Delta Clipper project, as well as SpaceX's Falcon 9 and Falcon 1 programs.
One issue mitigating against this drive for labor savings is government regulation. Given that NASA and USAF (as well as government programs in other countries) are the primary customers and sources of development capital, government regulatory requirements for oversight, parwork, quality, safety, and other documentation tend to inflate the operational costs of any such system.
With the invention of rocket propulsion in the first half of the twentieth century, space travel in the void beyond the atmosphere became a technical possibility.
Early ideas of a single-stage reusable spaceplane proved unrealistic and although the first practical rocket vehicles such as the V-2 weapon of WWII could reach the fringes of space, re-usable technology was too heavy and the rockets were expendable. The problem of mass efficiency could be overcome using multiple stages and both vertical-launch multistage rockets and horizontal-launch composite spaceplanes were proposed. However the first re-usable stages did not appear until the advent of the US Space Shuttle in 1981.
During WWII the German Eugen Sänger proposed the Silbervogel ("Silverbird") suborbital skip bomber. HTOL vehicles which can reach orbital velocity are harder to design than VTOL due to their higher vehicle structural weight. This led to several multi-stage prototypes such as a suborbital X-15. Aerospaceplane being one of the first HTOL SSTO concepts. Proposals have been made to make such a vehicle more viable including:
During the 1960s the partially reusable multi-stage NEXUS launcher was studied by Krafft Arnold Ehricke. Philip Bono, worked at Douglas, proposed several VTOL SSTO launch vehicles including: ROOST, ROMBUS, Ithacus, Pegasus and SASSTO. Most of his vehicles combined similar innovations to achieve SSTO capability. Bono proposed:
Bono also proposed the use of his vehicles for space launch, rapid intercontinental military transport (Ithacus), rapid intercontinental civilian transport (Pegasus), even Moon and Mars missions (Project Selena, Project Deimos).
In Europe, Dietrich Koelle, inspired by Bono's SASSTO design, proposed his own VTVL vehicle named BETA.
Other launch system configuration designs are possible such as horizontal launch with vertical landing (HTVL) and vertical launch with horizontal landing (VTHL). One of the few HTVL vehicles is the 1960s concept spacecraft Hyperion SSTO, designed by Philip Bono. [ citation needed ] while the HL-20 and X-34 are examples from the 1990s.[ citation needed ]As of February 2010 [update] , the VTHL X-37 has completed initial development and flown an initial classified orbital mission of over seven months duration.[ citation needed ] Currently proposed VTHL manned spaceplanes include the Dream Chaser and Prometheus, both circa 2010 concept spaceplanes proposed to NASA under the CCDev program.[ citation needed ]X-20 Dyna-Soar is an early example of a VTHL design,
The late 1960s saw the start of the Space Shuttle design process. From an initial multitude of ideas, a two-stage reusable VTHL design was pushed forward that eventually resulted in a reusable orbiter payload spacecraft and reusable solid rocket boosters. The external tank and its load frame were discarded, and the parts that were reusable took a 10,000-person group nine months to refurbish for flight.[ citation needed ] Early studies from 1980 and 1982 proposed in-space uses for the tank but NASA never pursued those options beyond the proposal stage.
During the 1970s, further VTOL and HTOL SSTO designs were proposed for solar power satellite and military applications. There was a VTOL SSTO study by Boeing. HTHL SSTO designs included the Rockwell Star-Raker and the Boeing HTHL SSTO study. However, the focus of all space launch funding in the United States on the Shuttle killed off these prospects. The Soviet Union followed suit with Buran. Others preferred expendables for their lower design risk and lower design cost.
Eventually, the Shuttle was found to be even more expensive to operate than an expendable launch system.
The cancellation of a Shuttle-Centaur rocket after the loss of Challenger also caused a hiatus, and the United States military scrambled back towards expendables to launch their payloads. Many commercial satellite customers had already switched to expendables, due to the lack of response to customer concerns by the Shuttle launch system.
In 1986 President Ronald Reagan called for an air-breathing scramjet plane to be built by the year 2000, called NASP/X-30 that would be capable of SSTO. Based on the research from Project Copper Canyon,the project failed due to severe technical issues and was canceled in 1993.
This research may have inspired the British HOTOL program, which rather than air breathing up to high hypersonic speeds as with NASP, proposed to use a pre-cooler up to Mach 5.5. The program's funding was canceled by the British government when the research identified some technical risks and indicated the proposed vehicle architecture would only be able to deliver a relatively small payload to orbit.
When the Soviet Union collapsed in the early nineties, the cost of Buran became untenable. Russia has only used pure expendables for space launch since.
Interest in developing new reusable vehicles arose during the 1990s The military Strategic Defense Initiative ("Star Wars") program "Brilliant Pebbles" required low cost, rapid turnaround launches. From this requirement came the McDonnell Douglas Delta Clipper VTOL SSTO proposal. The DC-X prototype for Delta Clipper demonstrated rapid turnaround time, and that automatic computer control of such a vehicle was possible. It also demonstrated that a reusable space launch vehicle need not require a large standing army to maintain like the Shuttle.
In mid-1990, further British research and major re-engineering to avoid deficiencies of the HOTOL design led to the far more promising Skylon design, with a much greater payload.
From the commercial side, large satellite constellations such as Iridium satellite constellation were proposed which also demanded low-cost launches. This fueled a private launch industry, including partially reusable vehicle players, such as Rocketplane Kistler, and reusable vehicle players such as Rotary Rocket.
The end of that decade saw the implosion of the satellite constellation market with the bankruptcy of Iridium. In turn, the nascent private launch industry collapsed. The fall of the Soviet Union eventually had political ripples which led to a scaling down of ballistic missile defense, including the demise of the "Brilliant Pebbles" program. The military decided to replace their aging expendable launcher workhorses, evolved from ballistic missile technology, with the EELV program. NASA proposed riskier reusable concepts to replace the Shuttle technology, to be demonstrated under the X-33 and X-34 programs.
In the early 2000s, rising costs and teething problems led to the cancellation of both X-33 and X-34, and the 2003 Space Shuttle Columbia disaster caused another grounding of the fleet. The Shuttle design was now over 20 years old, and in need of replacement. Meanwhile, the military EELV program churned out a new generation of better expendables. The commercial satellite market was depressed due to a glut of cheap expendable rockets and a dearth of satellite payloads. The Space Shuttle retired in 2011.
Against this backdrop came the Ansari X Prize contest, inspired by the aviation contests made in the early 20th century. Many private companies competed, the winner being Scaled Composites with their reusable HTHL SpaceShipOne. It won the ten million dollars, by reaching the Kármán line twice in a two-week period. While SpaceShipOne is suborbital like the X-15, some hope the private sector can eventually develop reusable orbital vehicles given enough incentive. SpaceX is a recent player in the private launch market succeeding in converting its Falcon 9 expendable launch vehicle into a partially reusable vehicle by returning the first stage for reuse.
In 2012, SpaceX had started a flight test program with experimental vehicles Grasshopper and F9R Dev1. These subsequently led to the development of the Falcon 9 re-usable rocket launcher.
On 23 November 2015 the Blue Origin New Shepard rocket became the first Vertical Take-Off/Landing (VTOL) rocket to reach space by passing the Kármán line (100 kilometres), reaching 329,839 feet (100.5 kilometers) before returning to a parachute landing.
SpaceX achieved the first vertical soft landing of a re-usable rocket stage on December 21, 2015, after helping send 11 Orbcomm OG-2 commercial satellites into low Earth orbit.
A refurbished booster was successfully re-used on March 30, 2017 and recovered by landing on an Autonomous Spaceport Drone Ship (ASDS).SpaceX now routinely recovers and reuses their first stages both on land and, using the ASDS, at sea.
As of October 2017 [update] , the only operational orbital reusable module is the SpaceX Falcon 9 core booster, which forms the first stage of the Falcon 9 and also propels the Falcon Heavy three-core version.
SpaceX is also developing a fully and more rapidly reusable launch system, the BFR. The 9-meter (30 ft) core diameter system is intended to replace both Falcon 9 and Falcon Heavy launch vehicles, as well as the Dragon spacecraft, initially aiming at the Earth-orbit launch market, but explicitly adding substantial capability to support long-duration spaceflight in the cislunar and Mars mission environments.
|ARCASPACE||Orizont||Sub-orbital||Project||[ citation needed ]|
|Airbus||Adeline||Project||Partially reusable main stage for Ariane 5.|
|Armadillo||Black Armadillo||Sub-orbital||Project||Cancelled. [ citation needed ]|
|Blue Origin||New Shepard||US||Sub-orbital||2015||Prototype|
|Blue Origin||New Glenn||US||Rocket||Orbital||Project||First stage reusable.|
|Canadian Arrow||Canadian Arrow||Sub-orbital||Project||Cancelled.[ citation needed ]|
|Kliper||Russia||2006||Project||Partly reusable orbiter.[ citation needed ]|
|DLR||Liquid Fly-back Booster||Germany||Project||Reusable boosters for Ariane 5 with additional derivatives.|
|ISRO||RLV-TD||India||Rocket||2012||Project||Successful flight test|
|MAKS||Russia||Project||Buran-like smaller winged reusable orbiter on heavy aircraft carrier.|
|Masten||XA 1.0||Launch stage||Project||[ citation needed ]|
|North American||X-15||US||Spaceplane||Sub-orbital||1959||Operational||Air launched. Retired.|
|NASA||Space Shuttle||US||Spaceplane||Orbital||1981||Operational||Vertical launch. Retired.|
|PlanetSpace||Silver Dart||Spaceplane||2000s||Project||Partially reusable.[ citation needed ]|
|PLD Space||Miura 5||Spain||Rocket||Orbital||2021||Project||First stage of 3 is reusable.|
|Reaction Engines||Skylon||UK||Spaceplane||SSO||Project||SABRE air-breathing rocket engines.|
|Molniya||Buran||USSR||Spaceplane||Orbital||1988||Prototype||Vertical launch. Retired.|
|Rotary Rocket||Roton ATV||US||Helicopter||Experimental||1999||Prototype||Vertical launch.|
|Scaled Composites||SpaceShipOne||US||Sub-orbital||Prototype||Flew to space twice in 2004.|
|The Spaceship Company||SpaceShipTwo||US||Sub-orbital||Prototype|
|Shenlong||China||2005||Project||Scale model flown.|
|SpaceX||Falcon 9||US||Rocket||Orbital||2015||Operational||First stage reusable.|
|SpaceX||Falcon Heavy||US||Rocket||Orbital||2018||Operational||Core and side boosters reusable.|
|SpaceX||Starship-Super Heavy||US||Rocket||Orbital||2016||Project||Fully reusable, capable of interplanetary transfers.|
|Spiral||USSR||Project||Small winged reusable orbiter on winged hypersonic air-carrier.[ citation needed ]|
|Sura||Ukraine||Project||Reusable launch vehicle, proposed by Ukraine.|
|Swiss Space Systems||SOAR||Switzerland||Spaceplane||Sub-orbital||Project||Air-launched from an Airbus 300.|
In 2006, the US Federal Aviation Administration issued a new regulation regarding commercial reusable launch vehicles, both suborbital and orbital, as Part 431. The text can be found under the US Federal Code at 14 CFR Part 431. The new regulation was made in anticipation of planned commercial reusable launch operations including the American companies listed above. FAA regulations only have jurisdiction within the United States and its territories, and to aircraft and spacecraft registered in the United States.
An expendable launch vehicle (ELV) is a launch system or launch vehicle stage that is used only once to carry a payload into space. Historically, satellites and human spacecraft were launched mainly using expendable launchers. ELV advantages include cost savings through mass production, and a greater payload fraction.
A spaceplane is an aerospace vehicle that operates as an aircraft in Earth's atmosphere, as well as a spacecraft when it is in space. It combines features of an aircraft and a spacecraft, which can be thought of as an aircraft that can endure and maneuver in the vacuum of space or likewise a spacecraft that can fly like an airplane. Typically, it takes the form of a spacecraft equipped with wings, although lifting bodies have been designed and tested as well. The propulsion to reach space may be purely rocket based or may use the assistance of airbreathing jet engines. The spaceflight is then followed by an unpowered glide return to landing.
A two-stage-to-orbit (TSTO) or two-stage rocket launch vehicle is a spacecraft in which two distinct stages provide propulsion consecutively in order to achieve orbital velocity. It is intermediate between a three-stage-to-orbit launcher and a hypothetical single-stage-to-orbit (SSTO) launcher.
The Lockheed Martin X-33 was an unmanned, sub-scale technology demonstrator suborbital spaceplane developed in the 1990s under the U.S. government-funded Space Launch Initiative program. The X-33 was a technology demonstrator for the VentureStar orbital spaceplane, which was planned to be a next-generation, commercially operated reusable launch vehicle. The X-33 would flight-test a range of technologies that NASA believed it needed for single-stage-to-orbit reusable launch vehicles, such as metallic thermal protection systems, composite cryogenic fuel tanks for liquid hydrogen, the aerospike engine, autonomous (unmanned) flight control, rapid flight turn-around times through streamlined operations, and its lifting body aerodynamics.
A space vehicle or spaceship is a rocket-powered vehicle used to transport unmanned satellites or humans between the Earth's surface and outer space. The earliest space vehicles were expendable launch systems, consisting of rocket launch vehicles carrying spacecraft payloads which were relatively small portions of the total vehicle size and mass. The single or multistage rocket without the payload is referred to as a launch vehicle. Most space vehicles in production use are expendable systems, although reusable launch systems have been envisioned since the late 1960s.
A launch vehicle or carrier rocket is a rocket used to carry a payload from Earth's surface through outer space, either to another surface point, or into space. A launch system includes the launch vehicle, launch pad, vehicle assembly and fuelling systems, range safety, and other related infrastructure.
Shuttle-Derived Launch Vehicle, or simply Shuttle-Derived Vehicle (SDV), is a term describing one of a wide array of concepts that have been developed for creating space launch vehicles from the components, technology and infrastructure of the Space Shuttle program. SDVs have also been part of NASA's plans several times in the past. In the late 1980s and early 1990s, NASA formally studied a cargo-only vehicle, Shuttle-C, that would have supplemented the crewed Space Shuttle in orbiting payloads.
Vertical takeoff, vertical landing (VTVL) is a form of takeoff and landing for rockets. Multiple VTVL craft have flown.
Aircraft can have different ways to take off and land. Conventional airplanes accelerate along the ground until sufficient lift is generated for takeoff, and reverse the process to land. Some airplanes can take off at low speed, this being a short takeoff. Some aircraft such as helicopters and Harrier Jump Jets can take off and land vertically. Rockets also usually take off vertically, but some designs can land horizontally.
The SpaceX reusable launch system development program is a privately funded program to develop a set of new technologies for an orbital launch system that may be reused many times in a manner similar to the reusability of aircraft. The company SpaceX is developing the technologies over a number of years to facilitate full and rapid reusability of space launch vehicles. The project's long-term objectives include returning a launch vehicle first stage to the launch site in minutes and to return a second stage to the launch pad following orbital realignment with the launch site and atmospheric reentry in up to 24 hours. SpaceX's long term goal is that both stages of their orbital launch vehicle will be designed to allow reuse a few hours after return.
The DARPA XS-1 is an experimental spaceplane/booster with planned capability to deliver small satellites into orbit for the U.S. Military. It is reported to be designed to be reusable as frequently as once a day, with a stated goal of doing so for 10 days straight. The XS-1 is intended to directly replace the "first stage" of a multistage rocket that will be capable of hypersonic flight at suborbital altitude, enabling one or more expendable upper stages to separate and deploy a payload into low Earth orbit. The XS-1 would then return to Earth, where it could ostensibly be serviced fast enough to repeat the process at least once every 24 hours.
Falcon 9 v1.1 was the second version of SpaceX's Falcon 9 orbital launch vehicle. The rocket was developed in 2011–2013, made its maiden launch in September 2013, and its final flight in January 2016. The Falcon 9 rocket was fully designed, manufactured, and operated by SpaceX. Following the second Commercial Resupply Services (CRS) launch, the initial version Falcon 9 v1.0 was retired from use and replaced by the v1.1 version.
Falcon 9 Full Thrust is a partially reusable medium-lift launch vehicle, designed and manufactured by SpaceX. Designed in 2014–2015, Falcon 9 Full Thrust began launch operations in December 2015. As of 31 December 2018 Falcon 9 Full Thrust had launched 46 times.
A medium-lift launch vehicle - MLV a rocket orbital launch vehicle that is capable of lifting between 2,000 to 20,000 kg of payload into Low Earth orbit - LEO. The category is between small-lift launch vehicles and heavy-lift launch vehicles.
A super heavy-lift launch vehicle (SHLLV) is a launch vehicle capable of lifting more than 50 tonnes (110,000 lb) of payload into low Earth orbit (LEO).
RLV-TD is the first unmanned flying testbed developed for the Indian Space Research Organisation (ISRO)’s Reusable Launch Vehicle Technology Demonstration Programme. It is a scaled down prototype of an eventual two-stage-to-orbit (TSTO) reusable launch vehicle.
The 'Hyperion' vehicle was truly remarkable since it would have been launched horizontally and landed vertically (HTVL) — an extremely rare combination. The payload capability was 110 passengers or 18t of cargo.
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