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軌道發射系統比較

維基媒體列表條目 来自维基百科，自由的百科全书

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軌道發射系統的比較（英語：Comparison of orbital launch systems）包含兩個常規軌道發射系統列表（各個火箭配置），按運行狀態分開。有關所有常規發射器系列的簡單列表，請參閱：軌道發射器系列的比較。有關主要使用固體燃料的軌道發射系統的列表，請參見：比較固體燃料的軌道發射系統。

航天器推進是用於加速航天器和人造衛星的任何方法。常規固體火箭或常規固體燃料火箭是一種帶有使用固體推進劑（燃料/氧化劑）的電動機的火箭。[注2]軌道發射系統是能夠將有效載荷置於地球軌道內或軌道外的火箭和其他系統。當前所有航天器都使用常規化學火箭（雙推進劑或固體燃料）進行發射，儘管有些[注3]在其第一階段就使用了呼吸發動機。

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當前與開發中的火箭

軌道說明:

發射系統狀態說明
  發展中
  運作中
更多信息 載具, 國家/地區 ...
  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]
    引用錯誤：沒有為名為vulcan-aces-calc的參考文獻提供內容
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已退役和取消的火箭

更多信息 載具, 國家 ...
  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) 網際網路檔案館的存檔，存檔日期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]
    三級發射前爆炸
  9. [i]
    First orbital launch attempt in 2005
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各國發射系統

下圖顯示了每個國家/地區開發的發射系統的數量，並按運行狀態進行了細分。火箭變種沒有區別；也就是說，擎天神5號系列的所有配置401-431、501-551、552和N22僅計一次。

10
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AUS
BRZ
CHN
EUR
ESP
FRA
IND
IRN
ISR
JPN
NKR
NZL
RUS
SKR
TWN
UKR
UK
USA
  •   運作中
  •   發展中
  •   已退役

備註

  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 –透過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 –透過Twitter.

參考資料

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