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((Short description|Russian hypersonic aircraft))
{|((Infobox aircraft begin
  |name = Tu-2000
  |image = Tu-2000.jpg
  |caption = Artist's impression of the Tu-2000 entering orbit around Earth
))
((Infobox aircraft type
  |type = [[Hypersonic]] [[technology demonstrator]]
  |manufacturer = [[Tupolev]] OKB
  |designer = 
  |first flight =
  |introduction =
  |retired =
  |status = Cancelled
  |primary user = 
  |produced =
  |number built = 0
  |unit cost =
  |variants with their own articles = [[Tupolev Tu-360]]
))
|}

The '''Tupolev Tu-2000''' was a planned [[hypersonic flight]] [[experimental aircraft]] designed by the [[Tupolev]] design bureau. It was intended to test technologies for a [[single-stage-to-orbit]] aerospaceplane and also the [[Tupolev Tu-360]] intercontinental bomber.

==Design and development==
((More citations needed section|date=February 2021))
Development of the Tu-2000 began in 1986 as a [[Soviet Union|Soviet]] response to the [[X-30]] project in the [[United States#Cold War and civil rights era|US]].<ref name=TU-2000>((cite web
 |url=http://astronautix.com/t/tu-2000.html
 |archive-url=https://web.archive.org/web/20161228024015/http://astronautix.com/t/tu-2000.html
 |url-status=dead
 |archive-date=December 28, 2016
 |title=Tu-2000
 |last=Wade
 |first=Mark
 |date=
 |website=Encyclopedia Astronautica
 |publisher=
 |access-date=2019-12-08
 |quote= This Soviet equivalent to the US X-30 single-stage-to-orbit scramjet aerospaceplane began development in 1986))</ref> Following the [[Dissolution of the Soviet Union|fall of the Soviet Union]], Russia took over the project and pursued it until 1992, when it was suspended due to lack of funds.<ref name=tu2000>" [https://web.archive.org/web/20020830010746/http://astronautix.com/stages/tu2000.htm Tu-2000 ]", ''[[astronautix.com]]'', Retrieved 24 April 2010</ref>

The experimental technology demonstrator would have weighed ((convert|70-90|tonnes|lb)) with a length of ((convert|196|feet|m|abbr=on|order=flip)), while the single-stage-to-orbit vehicle would have weighed ((convert|210-280|tonnes|lb)) and carried a maximum payload of ((convert|10|tonnes|lb)) into earth orbits ((convert|200-400|km|abbr=on)) high.<ref name=Gordon>Gordon and Komissarov, 2013. ''Unflown Wings''. Birmingham: Ian Allan Publishing. p. 75</ref>

Work on the project began in the 1970s. The Tupolev Design Bureau began the development of an [[aerospace plane]] with a launch weight of about ((convert|300|tonnes|lb)). Various propulsion methods were considered, such as [[liquid rocket engine]] on [[fuel element]]s, [[aircraft nuclear propulsion]], [[Plasma propulsion engine|plasma engine]], or an [[ion engine]].

The reason for the appearance of the [[Soviet Air Defense]] was the appearance of the US [[Space Shuttle]]. Works were activated in 1981. Three years later, an aerospace system based on a single-stage orbital aircraft with a liquid-propellant rocket engine was proposed, which could be launched both from the ground and from [[aircraft carriers]]. However, to increase efficiency and increase the fuel stock, a variant with a [[Spacecraft propulsion|combined power plant]] of a [[turbojet engine]], [[ramjet|ramjet engine]], and a [[liquid rocket engine]] was soon adopted, which became the prototype of the Tu-2000.

The aircraft was designed as a [[tailless aircraft]], and had an engine and [[Aircraft wing|triangular wing]] [[Extending wing|low extension]] located under [[fuselage]]. The core of the design was the power plant, which included:
* 4 turbojet engines in the rear fuselage;
* 1 main accelerating wide-range ramjet (located at the rear of the fuselage);
* 2 liquid fuel rocket engines for maneuvering in vacuum (installed between the turbojets).

The large number of engines was required to optimize efficiency in different flight modes. Most of the aircraft's volume was occupied by [[liquid hydrogen]] [[fuel tank]]s. The crew of two people was located in the nose of the fuselage. An automatic crew rescue system was to provide an escape route at all altitudes. The bow section, including the cabin, was detachable. Two escape options were considered: rescued by [[parachute]] from the cockpit and an [[ejection seat]].

[[Radio]] and [[avionics|electronic equipment]] was located behind the flight deck. The nose strut [[landing gear|chassis]] was removed in the same compartment. The middle and rear parts of the fuselage held the liquid hydrogen fuel tank. The liquid oxygen tank supplying [[oxidizer]] for the rocket engines was located in the tail of the fuselage. Liquid hydrogen was used as fuel for all engines and came from a single [[Aircraft fuel system|fuel system]].

The aircraft was designed with [[tricycle landing gear]].  The front gear had twin small diameter wheels with high pressure tyres. The main landing gear was to be single-wheeled, retracting to the fuselage compartments.

The VKS((clarify|reason=VKS first uses without explanation, it this an alternate name for the craft?|date=April 2022)) was supposed to take off from standard [[runway]]s up to ((convert|3|km|abbr=on)) long, fly back to [[subsonic speed]] after takeoff to reach the set starting point of acceleration and before landing for approach to a given [[airfield]]; carry out flights to change the airfield base, quickly perform acceleration to a given speed and altitude, including access to a [[circular orbit]]; perform multiple [[orbital maneuver]]s; perform an autonomous orbital flight of up to a day; perform [[Cruise (aeronautics)|cruising flight]] in the atmosphere with [[Hypersonic aircraft|hypersonic speeds]], perform deceleration with deceleration when returning from orbit; in the process of acceleration to orbital parameters and in the process of descending, perform maneuvering for the passage of a given route and exit to a given orbit and a given airfield; change the orbital flight plane.

Acceleration of the work contributed to the information about the [[Rockwell X-30]] project, a [[technology demonstrator]] for the US '''National Aero-Space Plane''' (NASP) project. In 1986, two government decrees were issued to develop a similar project. On September 1 of the same year, the [[Soviet Ministry of Defense|Ministry of Defense]] was released [[technical task]] to single-stage reusable video conferencing, capable of solving problems in the atmosphere and [[Outer space|near space]] and performing high-speed intercontinental transatmospheric transportation.

It was planned to implement the project in two stages:
# Creation of a Tu-2000A aircraft with a flight weight of ((convert|70-90|tonnes|lb)) and a speed of [[Mach number|Mach]] 6 at an altitude of ((convert|30|km|ft|abbr=on)). The VKS was to be ((convert|60|m|ft|-1|abbr=on)) long; with a [[wing span]] of ((convert|14|m|ft|abbr=on)); and a 70-degree [[Swept wing|leading edge wing sweep]].
# The second stage assumed various implementation options: Tu-2000B, MVKS, and a hypersonic airliner.
* The [[Tupolev Tu-360|Tu-2000B]] was a double [[bomber]], which had a range of ((convert|10000|km|nmi|abbr=on)) and a take-off weight of ((convert|350|tonnes|lb)). Six engines provided a speed of Mach 6 at an altitude of ((convert|30|km|abbr=on)).
* The MVKS version was to have a take-off weight of ((convert|260|t|lb)), a [[Ceiling (aeronautics)|flight ceiling]] of over ((convert|60|km|ft|abbr=on)), and a speed of Mach 15–25. It would carry a load of ((convert|8-10|t|lb)) into a ((convert|200|km|nmi|abbr=on)) orbit.
* Detailed study of the hypersonic liner proposal was not carried out, because it was not considered a priority.

By the time of [[Dissolution of the Soviet Union|the collapse of the USSR]] the project was in full swing. [[Perestroika]] resulted in lower project costs. However, by December 1991, many structural elements had already been manufactured: the nickel alloy [[wing box|wing torque box]], part of the fuselage, cryogenic fuel tanks, and composite fuel lines.<ref name=TU-2000 /> For comparison, at the time the US X-30 project was stuck on an attempt to build a titanium alloy section of the fuselage. The Tu-2000 could have been completed by the year 2000, but circumstances had changed.

Due to lack of funding in the summer of 1992, the project was declassified and had to be transferred to a commercial basis. The layout of the MVKS was presented at the [[MAKS (air show)|Mosaeroshow-92]] exhibition. The country's top leadership promised to support the project to raise the country's prestige, but did nothing. Soon, funding was discontinued altogether.

At 1995 prices, the cost of building one Tu-2000 was estimated at $450 million, and the cost of development work estimated as $5.29 billion. At a rate of 20 starts per year, the cost of one start should have been $13.6 million. With adequate funding, the project could have been completed in 13–15 years, but in 1993 the Tu-2000 was cancelled.

==Specifications (Single-stage-to-orbit design)==
((Aircraft specs
|ref=<ref name=Gordon/>
|prime units?=met
<!--
        General characteristics
-->
|crew=two
|capacity=((convert|8,000|kg|lb)) payload
|length m=72
|length ft=
|length in=
|length note=
|span m=14
|span ft=
|span in=
|span note=
|upper span m=
|upper span ft=
|upper span in=
|upper span note=
|mid span m=
|mid span ft=
|mid span in=
|mid span note=
|lower span m=
|lower span ft=
|lower span in=
|lower span note=
|swept m=<!-- swing-wings -->
|swept ft=<!-- swing-wings -->
|swept in=<!-- swing-wings -->
|swept note=
|dia m=13
|dia ft=<!-- airships etc -->
|dia in=<!-- airships etc -->
|dia note=
|width m=<!-- if applicable -->
|width ft=<!-- if applicable -->
|width in=<!-- if applicable -->
|width note=
|height m=
|height ft=
|height in=
|height note=
|wing area sqm=
|wing area sqft=
|wing area note=
|swept area sqm=<!-- swing-wings -->
|swept area sqft=<!-- swing-wings -->
|swept area note=
|volume m3=<!-- lighter-than-air -->
|volume ft3=<!-- lighter-than-air -->
|volume note=
|aspect ratio=<!-- sailplanes -->
|airfoil=
|empty weight kg=
|empty weight lb=
|empty weight note=
|gross weight kg=
|gross weight lb=
|gross weight note=
|max takeoff weight kg=280,000
|max takeoff weight lb=
|max takeoff weight note=
|fuel capacity=
|lift kg=<!-- lighter-than-air -->
|lift lb=<!-- lighter-than-air -->
|lift note=
|more general=
<!--
        Powerplant
-->
|eng1 number=7
|eng1 name=[[liquid hydrogen]] with [[liquid oxygen]] [[oxidizer]]
|eng1 type=4 [[turbojet]]s, 1 [[scramjet]], and 2 [[rocket]]s
|eng1 kw=<!-- prop engines -->
|eng1 hp=<!-- prop engines -->
|eng1 shp=<!-- prop engines -->
|eng1 kn=<!-- jet/rocket engines -->
|eng1 lbf=<!-- jet/rocket engines -->
|eng1 note=
|power original=
|thrust original=
|eng1 kn-ab=<!-- afterburners -->
|eng1 lbf-ab=<!-- afterburners -->

|eng2 number=
|eng2 name=
|eng2 type=
|eng2 kw=<!-- prop engines -->
|eng2 hp=<!-- prop engines -->
|eng2 shp=<!-- prop engines -->
|eng2 kn=<!-- jet/rocket engines -->
|eng2 lbf=<!-- jet/rocket engines -->
|eng2 note=
|eng2 kn-ab=<!-- afterburners -->
|eng2 lbf-ab=<!-- afterburners -->

|eng3 number=
|eng3 name=
|eng3 type=
|eng3 kw=<!-- prop engines -->
|eng3 hp=<!-- prop engines -->
|eng3 shp=<!-- prop engines -->
|eng3 kn=<!-- jet/rocket engines -->
|eng3 lbf=<!-- jet/rocket engines -->
|eng3 note=
|eng3 kn-ab=<!-- afterburners -->
|eng3 lbf-ab=<!-- afterburners -->
|more power=

|prop blade number=<!-- propeller aircraft -->
|prop name=
|prop dia m=<!-- propeller aircraft -->
|prop dia ft=<!-- propeller aircraft -->
|prop dia in=<!-- propeller aircraft -->
|prop dia note=

|rot number=<!-- helicopters -->
|rot dia m=<!-- helicopters -->
|rot dia ft=<!-- helicopters -->
|rot dia in=<!-- helicopters -->
|rot area sqm=<!-- helicopters -->
|rot area sqft=<!-- helicopters -->
|rot area note=
<!--
        Performance
-->
|perfhide=

|max speed kmh= 
|max speed mph=
|max speed kts=
|max speed note=
|max speed mach=25 (in orbit)
|cruise speed kmh=
|cruise speed mph=
|cruise speed kts=
|cruise speed note=
|stall speed kmh=
|stall speed mph=
|stall speed kts=
|stall speed note=
|never exceed speed kmh=
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|minimum control speed kmh=
|minimum control speed mph=
|minimum control speed kts=
|minimum control speed note=
|range km=
|range miles=
|range nmi=
|range note=
|combat range km=
|combat range miles=
|combat range nmi=
|combat range note=
|ferry range km=
|ferry range miles=
|ferry range nmi=
|ferry range note=
|endurance=<!-- if range unknown -->
|ceiling m=
|ceiling ft=
|ceiling note=
|g limits=<!-- aerobatic -->
|roll rate=<!-- aerobatic -->
|glide ratio=<!-- sailplanes -->
|climb rate ms=
|climb rate ftmin=
|climb rate note=
|time to altitude=
|sink rate ms=<!-- sailplanes -->
|sink rate ftmin=<!-- sailplanes -->
|sink rate note=
|lift to drag=
|wing loading kg/m2=
|wing loading lb/sqft=
|wing loading note=
|disk loading kg/m2=
|disk loading lb/sqft=
|disk loading note=
|fuel consumption kg/km=
|fuel consumption lb/mi=
|power/mass=
|thrust/weight=

|more performance=
<!--
        Armament
-->
|armament=<!-- add bulletted list here or if you want to use the following 
specific parameters, remove this parameter-->
|guns= 
|bombs= 
|rockets= 
|missiles= 
|hardpoints=
|hardpoint capacity=
|hardpoint rockets=
|hardpoint missiles=
|hardpoint bombs=
|hardpoint other=

|avionics=
))

==References==
((Reflist))

==External links==
((commons category|Tupolev Tu-2000))
* [https://web.archive.org/web/20091026144216/http://geocities.com/spacetransport/rlv-tu2000.html SPACE TRANSPORT: Tupolev Tu-2000 Hyperplane – Russia]
* ((cite web
 |url=http://astronautix.com/t/tu-2000.html
 |archive-url=https://web.archive.org/web/20161228024015/http://astronautix.com/t/tu-2000.html
 |url-status=dead
 |archive-date=December 28, 2016
 |title=Tu-2000
 |last=
 |first=
 |date=
 |website=Encyclopedia Astronautica
 |publisher=Mark Wade
 |access-date=2019-08-28
 |quote=This Soviet equivalent to the US X-30 single-stage-to-orbit scramjet aerospaceplane began development in 1986.))

((Tupolev aircraft))

[[Category:Tupolev aircraft]]
[[Category:Tailless delta-wing aircraft]]
[[Category:Scramjet-powered aircraft]]
[[Category:Spaceplanes]]
[[Category:Hypersonic aircraft]]
[[Category:Cancelled projects in the Soviet Union]]
[[Category:Cancelled Soviet spacecraft]]

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