Lynx

=**__Lynx__**=


 * //Project Type// || **Suborbital Tourism** ||
 * //Function// || **Achieve suborbital flight at low cost** ||
 * //operating body// || **XCOR** (Private) ||
 * //Host Nation// || **USA / California** ||
 * //Program cost// ||  ||
 * //Cost per vehicle// ||  ||
 * Take off || **Horizontal take of and landing (HOTL)** ||
 * //Life support// || **Yes** ||
 * //Crew// || yes ||
 * Reusable || yes ||
 * //Status// || **Research and development** ||

Useful Links
Company homepage: http://www.xcor.com

=Lynx rocketplane= From Wikipedia, the free encyclopedia The Lynx rocketplane in flight (artists' conception) - XCOR Aerospace

The **Lynx rocketplane** is a [|suborbital] [|horizontal-takeoff, horizontal-landing] (HTHL),[|[][|1][|]] [|rocket-powered] [|spaceplane] being developed by the California-based company [|XCOR] to compete in the [|emerging] suborbital space flight market. The Lynx is projected to carry one pilot, a ticketed passenger, and/or a payload or small satellites above 100 km altitude. As of December 2008 [|[update]], the passenger ticket was to cost $95,000.[|[][|2][|]] The Lynx was initially announced on March 26, 2008, with plans for an operational vehicle within two years.[|[][|3][|]] That date has since fallen to late 2011.[|[][|4][|]][|[][|5][|]] [[|hide]]
 * ==Contents==
 * [|1] [|Description]
 * [|1.1] [|Mark I Prototype]
 * [|1.2] [|Mark II Production Model]
 * [|1.3] [|Lynx XR-5K18 engine]
 * [|2] [|Test program]
 * [|3] [|Operations]
 * [|3.1] [|NASA sRLV program]
 * [|3.2] [|Commercial operations]
 * [|4] [|See also]
 * [|5] [|References]
 * [|6] [|External links] ||

[[|edit]] Description
The Lynx will have four liquid rocket engines at the rear of the [|fuselage] burning a mixture of [|LOX]-[|Kerosene] and each of them will produce 2,900 pounds-force (13,000 N) of thrust.[|[][|4][|]]

[[|edit]] Mark I Prototype

 * Maximum Altitude: 62 km (203,000 ft)[|[][|4][|]]
 * Primary Internal Payload: 120 kg (260 lb)[|[][|4][|]]
 * External Dorsal Mounted Pod: 280 kg (620 lb)[|[][|4][|]]
 * Secondary payload spaces include a small area inside the cockpit behind the pilot or outside the vehicle in two areas in the aft fuselage fairing.[|[][|4][|]]

[[|edit]] Mark II Production Model

 * Maximum Altitude: +100 km (330,000 ft)[|[][|4][|]]
 * Primary Internal Payload: 120 kg (260 lb)[|[][|4][|]]
 * External Dorsal Mounted Pod: 650 kg (1,400 lb) and is large enough to hold a two stage carrier to launch a microsatellite or multiple nanosatellites into low Earth orbit.[|[][|4][|]]
 * Secondary payload spaces include the same as the Mark I.[|[][|4][|]]
 * [|Non-toxic] (non-[|hydrazine]) [|reaction control system] (RCS) thrusters,[|[][|6][|]] type 3N22[|[][|7][|]]

[[|edit]] Lynx XR-5K18 engine
The development program of the XCOR Lynx 5K18 [|LOX]/[|kerosene] engine reached a major milestone in March 2011. Integrated test firings of the engine/nozzle combination have demonstrated the ability of the "aluminum nozzle to withstand the high temperatures of rocket-engine exhaust over numerous tests, with no discernable degradation of the material properties of the alloys. The tests validated the design, materials and manufacturing processes used in the nozzle."[|[][|8][|]] Importantly, the 5K18 engine tests have "laid a foundation for scaling the design to EELV-sized engines"[|[][|8][|]] In March 2011, [|United Launch Alliance] (ULA) announced they had entered into a joint-development contract with XCOR for a flight-ready, 25,000 to 30,000 pounds-force (110,000–130,000 N) cryogenic [|LH2]/[|LOX] [|upper-stage] rocket engine (see [|XCOR/ULA liquid-hydrogen, upper-stage engine development project]). Partially as a result of positive results achieved from Lynx 5K18 effort to develop a new [|aluminium alloy] engine nozzle using new manufacturing techniques, ULA believes the new engine technology will shave several hundred pounds of weight from the large engine and will lead to significantly lower-cost and more-capable commercial and US government space flights.[|[][|9][|]]

[[|edit]] Test program
Tests of the XR-5K18 main engine began in 2008[|[][|10][|]] and, as of February 2011 [|[update]], are largely complete.[|[][|6][|]] As of February 2011 [|[update]], the vehicle aerodynamic design has completed two rounds of wind tunnel testing. A third and final round of tests is planned for later in 2011.[|[][|6][|]] The tests were completed using a "1/60-scale supersonic wind tunnel model of Lynx."[|[][|11][|]] Flight tests of the Mark I prototype are expected to start in 2011.[|[][|12][|]]

[[|edit]] Operations
Artists' depiction of Lynx on ground with people - XCOR Aerospace

The first engine hot fire tests were conducted on December 15, 2008.[|[][|4][|]] Wind tunnel tests were conducted in July 2009.[|[][|13][|]]

[[|edit]] NASA sRLV program
As of March 2011 [|[update]], XCOR has submitted the Lynx as a reusable launch vehicle for carrying research payloads in response to [|NASA]'s suborbital reusable launch vehicle (sRLV) solicitation, which is a part of NASA's Flight Operations Program. XCOR projects 110 km (68 mi) altitude in flights of 30 to 45 minutes duration, while carrying up to 140 kg (310 lb) internal—or 650 kg (1,400 lb) external—of research payload. Flights will provide up to three minutes of microgravity below 0.01 [|g] [|[][|1][|]]

[[|edit]] Commercial operations
According to XCOR, the Lynx will fly four or more times a day, and will also have the capacity to deliver payloads into space. A Lynx prototype called Mark I is expected to perform its first test flight in early 2011, followed with a flight of the Mark II production model nine to eighteen months after.[|[][|4][|]] XCOR currently plans to have the Lynx's initial flights from the [|Mojave Air and Spaceport] in [|Mojave, California][|[][|14][|]] or any licensed spaceport with a 2,400 meter (7900 ft) runway. Beginning in January, 2014 the Lynx is expected to be flying suborbital [|space tourism] flights and scientific research missions from a new [|spaceport] on the [|Caribbean] island of [|Curaçao].[|[][|15][|]][|[][|16][|]] Because it lacks any propulsion system other than its rocket engines, the Lynx will have to be towed to the end of the runway. Once positioned on the runway, the pilot will ignite the four rocket engines and begin a steep climb. The engines will be shut off at approximately 138,000 feet (42 km) and [|Mach] 2. The [|spaceplane] will then continue to climb, unpowered until it reaches an [|apogee] of approximately 200,000 feet (61 km). The spacecraft will experience a little over four minutes of weightlessness before re-entering the Earth's [|atmosphere]. The occupants of the Lynx may experience up to four times normal gravity during re-entry. Once it has completed re-entry, the Lynx will then glide down and perform an unpowered landing. The total flight time is projected to last about 30 minutes.[|[][|17][|]] The Lynx is expected to be able to perform 40 flights before maintenance is required. The occupants would wear pressure suits made by [|Orbital Outfitters].[|[][|4][|]] The successor to the Mark II is planned to be a two stage fully-reusable orbital vehicle that takes off and lands horizontally.[|[][|18][|]]

[[|edit]] See also

 * [|Xerus (spaceplane)]
 * [|XCOR EZ-Rocket]
 * [|XCOR Mark-I X-Racer]
 * [|Private spaceflight]

[[|edit]] References

 * 1) ^ [|//**a**//][|//**b**//] [|"sRLV platforms compared"]. NASA. 2011-03-07 . [] . Retrieved 2011-03-10 . "Lynx: Type: HTHL/Piloted"
 * 2) **[|^]** [|"Press Reacts to RocketShip Tours"]. Satnews Daily. December 12, 2008 . [] . Retrieved 2012-12-27.
 * 3) **[|^]**[|XCOR AEROSPACE SUBORBITAL VEHICLE TO FLY WITHIN TWO YEARS]


 * 1) ^ [|//**a**//][|//**b**//][|//**c**//][|//**d**//][|//**e**//][|//**f**//][|//**g**//][|//**h**//][|//**i**//][|//**j**//][|//**k**//][|//**l**//][|//**m**//] [|"The Lynx Suborbital Spacecraft"]. XCOR Aerospace . [] . Retrieved April 29, 2010.
 * 2) **[|^]**[|XCOR Ready for Liftoff - Sept. 13, 2010]


 * 1) ^ [|//**a**//][|//**b**//][|//**c**//] Foust, Jeff (2011-02-28). [|"Suborbital back out of the shadows"]. //The Space Review// . [] . Retrieved 2011-02-28 . "//the 5K18 engine, four of which will power the Lynx ... the last few technical milestones for the engine are largely complete. ... non-toxic reaction control system (RCS) thrusters, a project that Greason said was more challenging in some respects than the larger main engine, but critical to the company’s vision of rapid turnaround times that would not be possible if conventional hydrazine RCS systems are used. The Lynx design has been through two rounds of wind tunnel tests, with a final round planned for later this year for some final tweaks//"
 * 2) **[|^]**[|Suborbital Provider Session, NSRC 2011, accessed 2011-03-01.]


 * 1) ^ [|//**a**//][|//**b**//] [|"XCOR and ULA Demonstrate Revolutionary Rocket Engine Nozzle Technology; Also Sign Contract for Liquid Hydrogen Engine Development"]. //press release//. XCOR Aerospace. 2011-03-22 . [] . Retrieved 2011-03-25.
 * 2) **[|^]** Morring, Frank, Jr. (2011-03-23). [|"ULA, XCOR to Develop Upper-Stage Engine"]. //Aviation Week// . [] . Retrieved 2011-03-25 . "//United Launch Alliance (ULA) and XCOR Aerospace are planning a joint effort to develop a low-cost upper-stage engine in the same class as the venerable RL-10, using technology XCOR is developing for its planned Lynx suborbital spaceplane. The two companies have been testing actively cooled aluminum nozzles XCOR is developing for its liquid oxygen/kerosene 5K18 engine for the Lynx, a reusable two-seat piloted vehicle the company plans to use for commercial research and tourist flights.//"
 * 3) **[|^]** [|"XCOR Aerospace Completes Successful First Test Fire of Engine for Lynx Suborbital Launch Vehicle"]. XCOR Aerospace . [].
 * 4) **[|^]** Joiner, Stephen (2011-05-01). [|"The Mojave Launch Lab"]. //Air & Space Smithsonian// . [] . Retrieved 2011-03-18 (online precedes the print edition date) . "//a 4-G pullout and a circling, dead-stick reentry. ... a 1/60-scale supersonic wind tunnel model of Lynx.//".
 * 5) **[|^]** Messier, Doug (2011-02-23). [|"Lynx Development Proceeds Towards First Test Flight"]. Parabolic Arc . [] . Retrieved 2011-02-28 . "//work is coming along nicely on building the first test flight vehicle which the company hopes to fly by the end of the year.//"
 * 6) **[|^]**[|XCOR Aerospace Tests Lynx Aerodynamic Design in USAF Wind Tunnel]


 * 1) **[|^]** [|"XCOR Unveils New Suborbital Rocketship"]. SPACE.com . [].
 * 2) **[|^]** Staff writers (October 6, 2010). [|"Space Experience Curacao Announces Wet Lease of XCOR Lynx Suborbital"]. //Space Media Network Promotions//. Space-Travel.com . [] . Retrieved 2010-10-06.
 * 3) **[|^]** [|"Space Experience Curacao"]. //Home//. Space Experience Curacao. 2009-2010 . [] . Retrieved 2010-10-06.
 * 4) **[|^]** [|"Lynx flight profile"] (PDF). XCOR Aerospace . [].
 * 5) **[|^]**[|Aero-TV: XCOR Aerospace -- An Innovative Route To Space (Part 2)]

[[|edit]] External links

 * [|Lynx Suborbital Spacecraft Page]
 * [|XCOR Aerospace Lynx Press Release - 2008-03-26]
 * [|Tourist suborbital flights in the Xcor Lynx planned for 2011]
 * [|XCOR Aerospace video - Part 1] [|Part 2] July 2, 2009