超级军网猜猜这是哪个星球？（高凉陈君進来，有一个疯狂计划）
来源：百度文库 编辑：超级军网 时间：2024/05/06 13:26:44
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远在天边，近在眼前。:D
纳美克星。:D
是不是还要加上什么时候？;P
难道是传说中的赛博特？！:D
月亮的卫星
原帖由 bigblu 于 2008-1-21 11:53 发表
是不是还要加上什么时候？;P
应该是数十亿年前了。
再提示一下，就在太阳系里面。
呀,这不是那个什么星吗....
不就是火星吗。在那个还有海洋的年代。
地球！:D
原帖由 fmXXX 于 2008-1-21 12:30 发表
不就是火星吗。在那个还有海洋的年代。
火星的海洋很小，而且大多处于北半球。
谜底揭晓。这个星球叫“金星”。
几十亿年前啊;funk ;funk 。。。那时有没金星人啊
胡说，命名是我的弹子球嘛。
还我弹子球~~~
还我弹子球~~~
很明显不是地球，那种颜色分明不是可见光拍摄
原帖由 Spica 于 2008-1-21 15:14 发表
很明显不是地球，那种颜色分明不是可见光拍摄
对。此图是根据金星现今地貌用电脑模拟的。今天的金星大气不透明，从外面看什么也没有。
原帖由 超大嫦娥 于 2008-1-21 13:39 发表
几十亿年前啊;funk ;funk 。。。那时有没金星人啊
很久以前太阳没有现在这么大，金星地理构成和地球几乎一样，很有可能在一定时期以内有过适合生命居住的环境。
再过很长时间,火星上的人拿出一张N年前的地球照片说...
金星居然有过这样的样子?;funk
:D 我也发一个
猜猜这是哪个
猜猜这是哪个
楼上要猜也别把水手谷露出来，太明显了:D ;P
以前看过一种言论说，太阳系九大行星中的某些成员（or八大，不算冥王）每隔多少时间就会轨道互换一次;P
那言论真搞笑……轨道变动意味着引力平衡被打破了，一切都乱套了
会有金星人吗:L
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BIGBLU说到水手谷就知道是火星了……
有了液态水，看上去都有很美啊
不过……呃……火星上的高地好像都集中在南半球啊
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Wet workshop is the idea of using a spent rocket stage as a makeshift space station. A liquid-fuel rocket primarily consists of two large, airtight fuel tanks; it was realized that the fuel tanks could be retrofitted into the living quarters of a space station. A large rocket stage would reach a low Earth orbit and undergo later modification. This would make for a cost-effective reuse of hardware that would otherwise have no further purpose, but the in-orbit modification of the rocket stage could prove difficult and expensive.
A wet workshop is contrasted with a "dry workshop", where the empty upper stage is internally outfitted on the ground before launch with a human habitat and other equipment. Then the upper stage is launched into orbit by a sufficiently powerful rocket.
Wernher von Braun proposed a wet workshop concept for launch on the Saturn V. His design replaced the S-IVB stage with a shell containing a cylindrical equipment section. On reaching orbit the S-II stage would be "vented" to remove any remaining fuel, and then a large access hatch in the top of the hydrogen tank would be opened. The cylindrical cargo module would then be inserted hydraulically into the tank through this opening, sealed, and then the tank would be repressurized to form a large living space. Power would be provided by solar cells lining the outside of the S-II. However, this proposal would require an entire Saturn V to launch the station, and at the time the design was being considered by Apollo X, all the Saturn V's were already earmarked for lunar missions.
In the meantime a number of the proposed Earth-orbit tests for Apollo had been canceled, leaving a small number of Saturn IB launchers available for use. A station could be built in an S-IVB instead, which both the Saturn V and Saturn I used. However, the lower throw-weight of the Saturn I meant that the power of the S-IVB would be needed to place the station in orbit. Again, the need to fire the stage that would eventually form the station suggested the use of a wet workshop concept. To allow this, the resulting design included metal mesh floors that were designed to allow the fuel to pass through them during launch.
Considerable work along these lines was carried out. Ironically, when the later Apollo missions were canceled (18 through 20), a supply of Saturn V's became available. However, instead of switching back to von Braun's original S-II-derived design, so much work had been done on the S-IV-derived system that they decided to continue along those lines instead. The Saturn V had enough power to place the station in orbit without firing the S-IVB, and the design was flown as a "dry workshop", even though it retained many of its original wet workshop design features.
A wet workshop is contrasted with a "dry workshop", where the empty upper stage is internally outfitted on the ground before launch with a human habitat and other equipment. Then the upper stage is launched into orbit by a sufficiently powerful rocket.
Wernher von Braun proposed a wet workshop concept for launch on the Saturn V. His design replaced the S-IVB stage with a shell containing a cylindrical equipment section. On reaching orbit the S-II stage would be "vented" to remove any remaining fuel, and then a large access hatch in the top of the hydrogen tank would be opened. The cylindrical cargo module would then be inserted hydraulically into the tank through this opening, sealed, and then the tank would be repressurized to form a large living space. Power would be provided by solar cells lining the outside of the S-II. However, this proposal would require an entire Saturn V to launch the station, and at the time the design was being considered by Apollo X, all the Saturn V's were already earmarked for lunar missions.
In the meantime a number of the proposed Earth-orbit tests for Apollo had been canceled, leaving a small number of Saturn IB launchers available for use. A station could be built in an S-IVB instead, which both the Saturn V and Saturn I used. However, the lower throw-weight of the Saturn I meant that the power of the S-IVB would be needed to place the station in orbit. Again, the need to fire the stage that would eventually form the station suggested the use of a wet workshop concept. To allow this, the resulting design included metal mesh floors that were designed to allow the fuel to pass through them during launch.
Considerable work along these lines was carried out. Ironically, when the later Apollo missions were canceled (18 through 20), a supply of Saturn V's became available. However, instead of switching back to von Braun's original S-II-derived design, so much work had been done on the S-IV-derived system that they decided to continue along those lines instead. The Saturn V had enough power to place the station in orbit without firing the S-IVB, and the design was flown as a "dry workshop", even though it retained many of its original wet workshop design features.
原帖由 苏联兵 于 2008-1-21 15:58 发表
再过很长时间,火星上的人拿出一张N年前的地球照片说...
当知道答案时，我也有同样的想法;P :handshake
采用对接手段,发射大型舱段到地球轨道或者其它外星球轨道上组装大型飞船或者空间站,在技术上是完全可行的.当年美国政府也考虑过研制月球空间站.但这一切设想随着土星系列火箭的放弃与"短脚鸭",中看不中用的航天飞机工程的上马都最终通通流产了.事实上当年NASA的这个金星飞掠设想,拥有阿瑞斯火箭之后改进下就可以用于载人火星环绕飞行了.
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Class: Manned. Type: Mars Flyby. Destination: Mars. Nation: USA. Manufacturer: Douglas.
Near-term manned Mars flyby spacecraft proposed by Douglas in 1965 for flight as early as 1973. It differed from the contemporary NASA in-house design in using the Douglas Manned Orbiting Research Laboratory as the basis for the habitation module.
Four launches of a stretched version of the Saturn V were required for the expedition. The first three launches put three fully-fuelled S-IVB stages into orbit, which were docked in series. This was followed by launch of the 90 metric ton Mars flyby spacecraft, consisting, from fore to aft, of an Apollo command module with a crew of three, a retro module used to brake the command module prior to re-entry at the end of the mission, and a modified Manned Orbiting Research Laboratory, 6.55 m diameter x 12.80 m long.
After 30 days of checkout, the mission was launched toward Mars. Each S-IV stage fires, one after the other, to put the spacecraft on a trans-Mars trajectory. After separation of the last stage, the crew separate the CRM from the MORL, transpose, and dock with the MORL in typical Apollo fashion. They then enter the MORL for the mission. The MORL was equipped with a single-person centrifuge to provide artificial-G conditioning to the crew during the long zero-G flight.
The three-member crew fly within 5000 km of Mars, releasing robotic probes and landers to explore the planet. After a 655 day flight, the crew entered the command module, and separate from the MORL. The retro module fired to slow the approach speed to one within the capabilities of the command module. The usual Apollo-type re-entry and splashdown occur, with recovery by a US aircraft carrier.
In comparison to NASA's concept, the Douglas approach required no refueling operations in low earth orbit, and required only four launches of an improved Saturn V as opposed to six launches of a standard Saturn V. From Douglas' point of view, it also had the advantage that all of the hardware (MORL, S-IVB stages, retro module) except the Apollo command module would be Douglas-provided. It had the disadvantage of requiring development of planned but not in-being hardware (MORL, upgraded Saturn V).
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MORL Mars Flyby Mission Summary:
Summary: Manned Mars flyby using Apollo hardware for earliest possible mission (mid-1970's)
Propulsion: LOX/LH2
Braking at Mars: flyby
Mission Type: Crocco
Split or All-Up: all up
ISRU: flyby
Launch Year: 1973
Crew: 3
Outbound time-days: 125
Mars Stay Time-days: 0
Return Time-days: 530
Total Mission Time-days: 655
Total Payload Required in Low Earth Orbit-metric tons: 360
Mass per crew-metric tons: 120
Launch Vehicle Payload to LEO-metric tons: 137
Number of Launches Required to Assemble Payload in Low Earth Orbit: 4
Launch Vehicle: Saturn MLV-V-1
Crew Size: 3. Design Life: 655 days. Length: 76.00 m (249.00 ft). Basic Diameter: 6.70 m (21.90 ft). Maximum Diameter: 6.70 m (21.90 ft). Mass: 360,000 kg (790,000 lb). Associated Launch Vehicle: Saturn MLV-V-1.
这是当年美国道格拉斯公司(现波音公司)的火星载人飞行设想,计划用改进型土星五型火箭发射四个各90吨的舱段组件在地球轨道上对接后,组装成一艘重达360吨的巨型飞船,用于执行美国的火星载人探测计划(宇航员三人).
今天想来,航天飞机工程真的是害人不浅啊,不少激动人心的太空飞行由于重型火箭的放弃实施的时间被迫拖延了半个多世纪乃至更长的时间.因此长征五号火箭一定要争气啊,不仅要改进出2400吨起飞推力级别的重型版,更要发誓如俄罗斯联盟火箭那样要将其打造成"百年老箭",成为中国,成为人类实行外星载人飞行的核心基石.
Near-term manned Mars flyby spacecraft proposed by Douglas in 1965 for flight as early as 1973. It differed from the contemporary NASA in-house design in using the Douglas Manned Orbiting Research Laboratory as the basis for the habitation module.
Four launches of a stretched version of the Saturn V were required for the expedition. The first three launches put three fully-fuelled S-IVB stages into orbit, which were docked in series. This was followed by launch of the 90 metric ton Mars flyby spacecraft, consisting, from fore to aft, of an Apollo command module with a crew of three, a retro module used to brake the command module prior to re-entry at the end of the mission, and a modified Manned Orbiting Research Laboratory, 6.55 m diameter x 12.80 m long.
After 30 days of checkout, the mission was launched toward Mars. Each S-IV stage fires, one after the other, to put the spacecraft on a trans-Mars trajectory. After separation of the last stage, the crew separate the CRM from the MORL, transpose, and dock with the MORL in typical Apollo fashion. They then enter the MORL for the mission. The MORL was equipped with a single-person centrifuge to provide artificial-G conditioning to the crew during the long zero-G flight.
The three-member crew fly within 5000 km of Mars, releasing robotic probes and landers to explore the planet. After a 655 day flight, the crew entered the command module, and separate from the MORL. The retro module fired to slow the approach speed to one within the capabilities of the command module. The usual Apollo-type re-entry and splashdown occur, with recovery by a US aircraft carrier.
In comparison to NASA's concept, the Douglas approach required no refueling operations in low earth orbit, and required only four launches of an improved Saturn V as opposed to six launches of a standard Saturn V. From Douglas' point of view, it also had the advantage that all of the hardware (MORL, S-IVB stages, retro module) except the Apollo command module would be Douglas-provided. It had the disadvantage of requiring development of planned but not in-being hardware (MORL, upgraded Saturn V).
--------------------------------------------------------------------------------
MORL Mars Flyby Mission Summary:
Summary: Manned Mars flyby using Apollo hardware for earliest possible mission (mid-1970's)
Propulsion: LOX/LH2
Braking at Mars: flyby
Mission Type: Crocco
Split or All-Up: all up
ISRU: flyby
Launch Year: 1973
Crew: 3
Outbound time-days: 125
Mars Stay Time-days: 0
Return Time-days: 530
Total Mission Time-days: 655
Total Payload Required in Low Earth Orbit-metric tons: 360
Mass per crew-metric tons: 120
Launch Vehicle Payload to LEO-metric tons: 137
Number of Launches Required to Assemble Payload in Low Earth Orbit: 4
Launch Vehicle: Saturn MLV-V-1
Crew Size: 3. Design Life: 655 days. Length: 76.00 m (249.00 ft). Basic Diameter: 6.70 m (21.90 ft). Maximum Diameter: 6.70 m (21.90 ft). Mass: 360,000 kg (790,000 lb). Associated Launch Vehicle: Saturn MLV-V-1.
这是当年美国道格拉斯公司(现波音公司)的火星载人飞行设想,计划用改进型土星五型火箭发射四个各90吨的舱段组件在地球轨道上对接后,组装成一艘重达360吨的巨型飞船,用于执行美国的火星载人探测计划(宇航员三人).
今天想来,航天飞机工程真的是害人不浅啊,不少激动人心的太空飞行由于重型火箭的放弃实施的时间被迫拖延了半个多世纪乃至更长的时间.因此长征五号火箭一定要争气啊,不仅要改进出2400吨起飞推力级别的重型版,更要发誓如俄罗斯联盟火箭那样要将其打造成"百年老箭",成为中国,成为人类实行外星载人飞行的核心基石.
火星的引力小。返回时所需的燃料少很多。
正是因为火星的引力比较小,而且气候环境条件也是诸类地型行星中与地球最相似的一个.因此如果在二十世纪晚期美国不搞航天飞机,美国的土星五号火箭就将能够保留下来,而在美国土星五火箭的刺激下,苏联只使H1火箭失败,.其它土星五级别的巨型火箭也会很快就会研制出来.那么无论是月球基地还是载人火星飞行人类今天都有"现成的巨型火箭"可以凭持.事实上美国苏联砸在航天飞机工程上的钱可不少,由其是苏联资金高达100多亿美元,如果用这个钱去搞载人登月飞行,在二十世纪月球就被俄罗斯民族踏在脚下了.
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苏联的东西特化的多，通用性好的貌似不是很多……