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轨道发射系统比较

维基媒体列表条目 来自维基百科，自由的百科全书

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轨道发射系统的比较（英语：Comparison of orbital launch systems）包含两个常规轨道发射系统列表（各个火箭配置），按运行状态分开。有关所有常规发射器系列的简单列表，请参阅：轨道发射器系列的比较。有关主要使用固体燃料的轨道发射系统的列表，请参见：比较固体燃料的轨道发射系统。

航天器推进是用于加速航天器和人造卫星的任何方法。常规固体火箭或常规固体燃料火箭是一种带有使用固体推进剂（燃料/氧化剂）的电动机的火箭。[注2]轨道发射系统是能够将有效载荷置于地球轨道内或轨道外的火箭和其他系统。当前所有航天器都使用常规化学火箭（双推进剂或固体燃料）进行发射，尽管有些[注3]在其第一阶段就使用了呼吸发动机。

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当前与开发中的火箭

轨道说明:

发射系统状态说明
  发展中
  运作中
更多信息 载具, 国家/地区 ...
  1. [a]
    Suborbital flight tests and on-pad explosions are excluded, but launches failing en route to orbit are included.
  2. [b]
    Effective year for active rockets, planned year for rockets in development
  3. [c]
    A suborbital flight was conducted in 2014 as Angara-1.2pp, testing only the first and second stages.[5]
  4. [d]
    Reference altitude 500 km
  5. [e]
    Upgraded to 11,115 kg by 2020[10]
  6. [f]
    for Starliner[17]
  7. [g]
    PAF structural limit: 10,886 kg[42]
  8. [h]
    GTO payload is 5,550 kg when the first stage lands downrange on a drone ship (ASDS). Reduced to 3,500 kg if the first stage returns to the launch site (RTLS).
  9. [i]
    Additionally, one rocket exploded on the launch pad in 2016.[41]
  10. [j]
    GTO payload is 8,000 kg when the core first-stage booster lands downrange on a drone ship (ASDS) and the side boosters return to the launch site (RTLS). Increased to 10,000 kg if all boosters land on drone ships.[43]
  11. [k]
    As of 2019 Falcon Heavy has only flown in partially reusable configuration; fully expendable configuration is considered operational in the sense that it is a simplified version of the reusable configuration.
  12. [l]
    GTO payload with enhanced engines, as of GSLV version 2A[53]
  13. [m]
    A suborbital test flight was conducted in 2014 (designated LVM-3/CARE) without the cryogenic upper stage (CUS).[56]
  14. [n]
    5,100 kg to a 500-km Sun-synchronous orbit; 3,300 kg to 800 km[57]:64–65
  15. [o]
    A suborbital test flight was conducted in April 2018.[63]
  16. [p]
    A suborbital test flight was conducted in March 2012.[68]
  17. [q]
    Includes 6 possible launches of CZ-2C (3) noted by Gunter Krebs in reference [75].
  18. [r]
    Reference altitude 400 km
  19. [s]
    A suborbital test flight was conducted in November 2018.
  20. [t]
    A suborbital test flight was conducted in May 2018.[113]
  21. [u]
    Additionally, two rockets exploded on the launch pad, one in 2012 and one in 2019.[126]
  22. [v]
    A suborbital test flight succeeded in 2016; both orbital flights in 2017 and 2019 failed.[129]
  23. [w]
    Suborbital test flight in 2004, without Fregat upper stage.[131]
  24. [x]
    with ICPS
  25. [y]
    with EUS
  26. [z]
    with EUS and
    advanced boosters
  27. [aa]
    A prior version of the SS-520 flew twice as a suborbital sounding rocket in 1998 and 2000. In 2017, the addition of a small third stage enabled orbital launches of ultra-light nano- or picosatellites.[149]
  28. [ab]
    A suborbital test flight failed in 2006. The first two orbital missions failed in 2009 and 2012, and the rocket finally reached orbit in late 2012.[160]
  29. [ac]
    Reference altitude 700 km
  30. [ad]
    引用错误：没有为名为vulcan-aces-calc的参考文献提供内容
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已退役和取消的火箭

更多信息 载具, 国家 ...
  1. [a]
    First suborbital test in 1969, first orbital launch attempt in 1970
  2. [b]
    Without Buran, and assuming payload providing orbital insertion
  3. [c]
    The U.S. Space Shuttle Transportation System and the Soviet Energia-Buran system consist of launch vehicle rockets and returnable spaceplane orbiter. Payload values listed here are for the mass of the payload in cargo bay of the spaceplanes, excluding the mass of the spaceplanes themselves.
  4. [d]
    The SpaceX website lists the F9 payload to LEO as 13,150kg. The payload to GTO is listed as 4,850kg. However, SpaceX has stated that these numbers include a 30% margin to accommodate re-usability.
  5. [e]
    Suborbital test flights in 1995, 1997 and 2002, no orbital launches attempted
  6. [f]
    The N1 rocket was initially designed for 75mt LEO capacity and launch attempts were made with this version, but there were studies to increase the payload capacity to 90–95 mt, if a liquid-hydrogen upper stage engine could be developed.
  7. [g]
    The Saturn V made 13 launches, 12 of which reached the correct orbits, and the other (Apollo 6) reached a different orbit than the one which had been planned; however, some mission objectives could still be completed; NASA, Saturn V News Reference, Appendix: Saturn V Flight History (1968) 互联网档案馆的存档，存档日期2011-05-17.. For more information, see the Saturn V article. The Saturn V launch record is usually quoted as having never failed, e.g. "The rocket was masterminded by Wernher Von Braun and did not fail in any of its flights", Alan Lawrie and Robert Godwin; Saturn, but the Apollo 6 launch should be considered a partial mission failure. The 13th launch of Saturn V was in special configuration (SA-513) with the Skylab.
  8. [h]
    三级发射前爆炸
  9. [i]
    First orbital launch attempt in 2005
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各国发射系统

下图显示了每个国家/地区开发的发射系统的数量，并按运行状态进行了细分。火箭变种没有区别；也就是说，擎天神5号系列的所有配置401-431、501-551、552和N22仅计一次。

10
20
30
40
50
AUS
BRZ
CHN
EUR
ESP
FRA
IND
IRN
ISR
JPN
NKR
NZL
RUS
SKR
TWN
UKR
UK
USA
  •   运作中
  •   发展中
  •   已退役

备注

  1. [N 1]
    Elon Musk [@elonmusk]. Mass of initial SN ships will be a little high & Isp a little low, but, over time, it will be ~150t to LEO fully reusable (推文). 2020-03-31 –通过Twitter.
  2. [N 2]
    Elon Musk [@elonmusk]. Mass of initial SN ships will be a little high & Isp a little low, but, over time, it will be ~150t to LEO fully reusable (推文). 2020-03-31 –通过Twitter.

参考资料

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