火箭有哪些部分和各部分的功用是什麼?不同的火箭有什麼分別?
有什麼內容相關的書籍或網頁?
英文作答較好, 中文也可
火箭的構造
2006-11-17 6:34 am
回答 (3)
2006-11-17 7:27 pm
✔ 最佳答案
先說你提到的返回倉那是載人太空船或會重返地球的衛星/探測器的一部分
不屬於火箭的一部分
以下是 New Horizons 的火箭的介紹, 當中有提到該火箭的構造
http://pluto.jhuapl.edu/launch/FINAL-PLUTO_MO.pdf
火箭有很多小部分的....
我只說一些常見的
大型
第一級, 第二級, 第三級火箭
一枝火箭通常有幾級, 第一級燃料耗盡則第二級接力
kick-in motor
把負載送到較高軌道 (e.g. 同步軌道), 或加速負載脫離地球引力
助推火箭
提供額外推力
小型
負載
火箭存在的價值...就是把負載送往向目的地的軌跡
可以是衛星, 太空探測船, 載人太空船等等
整流罩
穿過大氣層較密的部分是保護負載及改善火箭表現 (負載不是流線型)
到大氣較稀薄的時候會拋棄, 減輕重量
電腦
控制推力, 導航等
接駁器
有時候火箭有兩級直徑不同
就用一接駁器連接
逃生火箭
載人太空船的火箭才有
火箭出事時把太空船帶離火箭
火箭常見分別：
推力/可載重量不同
燃料不同
用途不同 (送載人/無人負載)
Stages to Saturn : a technological history of the Apollo/Saturn launch vehicle
這本書介紹阿波羅計劃的登月火箭土星五型
內容不錯的 ^^
至於其他火箭, 可以去 Wikipedia
http://en.wikipedia.org/wiki/List_of_launch_vehicles 找找~
留意內文引用的出處
你可以找到很多 press kit, 或其他介紹文件~
亦可到太空探測器的官方網頁找 press kit
通常這些 press kit 是給新聞界的~
裏面有火箭的構造, 升空前後的事件 (e.g. 升空前檢驗) 等等
2006-11-17 11:34:49 補充：
火箭還會有一些小型火箭引掣負責控制火箭的姿勢 (pitch motor果類)以及分離時把用完的火箭推開 (retromotor)
2006-11-17 4:39 pm
In this topic, I choose Saturn V vehicle which is the largest rockect that human ever built in the history. The Saturn V vehicle is used during the moon exploration program in the 1970s.
The Saturn V (pronounced 'Saturn Five', popularly known as the Moon Rocket) was a multistage liquid-fuel expendable rocket used by NASA's Apollo and Skylab programs.
In all, NASA launched thirteen Saturn V rockets between 1967 and 1973, with no loss of payload. The design payload was the manned Apollo spacecraft used by NASA for moon landings, and the Saturn V went on to launch the Skylab space station.
three stages of the Saturn V were developed by various NASA contractors, but following a sequence of mergers and takeovers all of them are now owned by Boeing. Each first and second stage was test fired at the Stennis Space Center located near Bay St. Louis, Mississippi. The facility was later used for the testing and verification of both the Space Shuttle Main Engine and the newer RS-68 rocket engine currently used on the Delta IV EELV rocket and in the future, on the Ares V rocket.
On all but one of its flights, the Saturn V consisted of three stages — the S-IC first stage, S-II second stage and the S-IVB third stage — and the instrument unit. All three stages used liquid oxygen (LOX) as an oxidizer. The first stage used RP-1 for fuel, while the second and third stages used liquid hydrogen (LH2). All three stages also used small solid-fuelled ullage motors that helped to separate the stages during the launch, and to ensure that the liquid propellants were in a proper position to be drawn into the pumps.
S-IC first stage
The S-IC was built by The Boeing Company at the Michoud Assembly Facility, New Orleans, where the Space Shuttle External Tanks are now constructed. As with almost every rocket stage, most of its mass of over two thousand metric tonnes at launch was fuel, in this case RP-1 rocket fuel and liquid oxygen oxidizer. It was 42 meters tall and 10 meters in diameter, and provided 34.02 MN of thrust to get the rocket through the first 61 kilometers of ascent. The five F-1 engines were arranged in a cross pattern. The center engine was fixed, while the four on the outer ring could be hydraulically turned to control the rocket.
S-II second stage
The S-II was built by North American Aviation at Seal Beach, California. Using liquid hydrogen and liquid oxygen, it had five J-2 engines in a similar arrangement to the S-IC. The second stage accelerated the Saturn V through the upper atmosphere with 5 MN of thrust. When loaded, 97% of the weight of the stage was propellant. Instead of having an intertank structure to separate the two fuel tanks as was done in the S-IC, the S-II used a common bulkhead that was constructed from both the top of the LOX tank and bottom of the LH2 tank. It consisted of two aluminium sheets separated by a honeycomb structure made of phenol. This had to insulate against the 70 °C (125 °F) temperature difference between the two tanks. The use of a common bulkhead saved 3.6 metric tons in weight.
S-IVB third stage
The S-IVB was built by the Douglas Aircraft Company at Huntington Beach, California. It had one J-2 engine and used the same fuel as the S-II. This stage was used twice during the mission: first for the orbit insertion after second stage cutoff, and later for the trans lunar injection (TLI) burn. The S-IVB also used a common bulkhead to insulate the two tanks. The S-IVB was the only rocket stage of the Saturn V small enough to be transported by plane, in this case the Super Guppy. Apart from the interstage adapter, this stage is nearly identical to the second stage of the Saturn IB rocket.
圖片參考：http://upload.wikimedia.org/wikipedia/en/b/b2/Saturn_v_schematic.jpg
A Saturn V is ready to launch
圖片參考：http://upload.wikimedia.org/wikipedia/commons/thumb/c/c9/Ap10-KSC-69PC-110.jpg/753px-Ap10-KSC-69PC-110.jpg
The Saturn V (pronounced 'Saturn Five', popularly known as the Moon Rocket) was a multistage liquid-fuel expendable rocket used by NASA's Apollo and Skylab programs.
In all, NASA launched thirteen Saturn V rockets between 1967 and 1973, with no loss of payload. The design payload was the manned Apollo spacecraft used by NASA for moon landings, and the Saturn V went on to launch the Skylab space station.
three stages of the Saturn V were developed by various NASA contractors, but following a sequence of mergers and takeovers all of them are now owned by Boeing. Each first and second stage was test fired at the Stennis Space Center located near Bay St. Louis, Mississippi. The facility was later used for the testing and verification of both the Space Shuttle Main Engine and the newer RS-68 rocket engine currently used on the Delta IV EELV rocket and in the future, on the Ares V rocket.
On all but one of its flights, the Saturn V consisted of three stages — the S-IC first stage, S-II second stage and the S-IVB third stage — and the instrument unit. All three stages used liquid oxygen (LOX) as an oxidizer. The first stage used RP-1 for fuel, while the second and third stages used liquid hydrogen (LH2). All three stages also used small solid-fuelled ullage motors that helped to separate the stages during the launch, and to ensure that the liquid propellants were in a proper position to be drawn into the pumps.
S-IC first stage
The S-IC was built by The Boeing Company at the Michoud Assembly Facility, New Orleans, where the Space Shuttle External Tanks are now constructed. As with almost every rocket stage, most of its mass of over two thousand metric tonnes at launch was fuel, in this case RP-1 rocket fuel and liquid oxygen oxidizer. It was 42 meters tall and 10 meters in diameter, and provided 34.02 MN of thrust to get the rocket through the first 61 kilometers of ascent. The five F-1 engines were arranged in a cross pattern. The center engine was fixed, while the four on the outer ring could be hydraulically turned to control the rocket.
S-II second stage
The S-II was built by North American Aviation at Seal Beach, California. Using liquid hydrogen and liquid oxygen, it had five J-2 engines in a similar arrangement to the S-IC. The second stage accelerated the Saturn V through the upper atmosphere with 5 MN of thrust. When loaded, 97% of the weight of the stage was propellant. Instead of having an intertank structure to separate the two fuel tanks as was done in the S-IC, the S-II used a common bulkhead that was constructed from both the top of the LOX tank and bottom of the LH2 tank. It consisted of two aluminium sheets separated by a honeycomb structure made of phenol. This had to insulate against the 70 °C (125 °F) temperature difference between the two tanks. The use of a common bulkhead saved 3.6 metric tons in weight.
S-IVB third stage
The S-IVB was built by the Douglas Aircraft Company at Huntington Beach, California. It had one J-2 engine and used the same fuel as the S-II. This stage was used twice during the mission: first for the orbit insertion after second stage cutoff, and later for the trans lunar injection (TLI) burn. The S-IVB also used a common bulkhead to insulate the two tanks. The S-IVB was the only rocket stage of the Saturn V small enough to be transported by plane, in this case the Super Guppy. Apart from the interstage adapter, this stage is nearly identical to the second stage of the Saturn IB rocket.
圖片參考：http://upload.wikimedia.org/wikipedia/en/b/b2/Saturn_v_schematic.jpg
A Saturn V is ready to launch
圖片參考：http://upload.wikimedia.org/wikipedia/commons/thumb/c/c9/Ap10-KSC-69PC-110.jpg/753px-Ap10-KSC-69PC-110.jpg
2006-11-17 6:36 am
火箭的構造
火箭的外殼堅固耐熱
火箭的原理
火箭內裝配高效能燃料及氧化劑。
高效能燃料燃燒時，火箭底部噴出氣體，能產生強大的力量。
這種力量足以抵消地心吸力，把太空船送到太空去。
穿梭機發射的影片
火箭的速度最少要每秒8公里，才能脫離地心吸力
盛載燃料的部分用完後會脫落
火箭的外殼堅固耐熱
火箭的原理
火箭內裝配高效能燃料及氧化劑。
高效能燃料燃燒時，火箭底部噴出氣體，能產生強大的力量。
這種力量足以抵消地心吸力，把太空船送到太空去。
穿梭機發射的影片
火箭的速度最少要每秒8公里，才能脫離地心吸力
盛載燃料的部分用完後會脫落
收錄日期: 2021-04-12 22:45:44
原文連結 [永久失效]:
https://hk.answers.yahoo.com/question/index?qid=20061116000051KK04673