哪位大大来介绍一下前苏联的矛式洲际导弹？

7000KM射程的两级液体洲际导弹，另外还有3000KM射程的常规型，南方设计局在乌克兰独立后中止了开发

有长度，直径等数据么？
只有两级?

弹长12.9米，直径1.15米，设计意图估计无非也就是在钻条约空子的情况下维持对美帝的核威慑力，同时尽量降低成本。一旦成型，就是一种集成有限资源下的单方面数量优势，能掩护重型弹道导弹对严密的防御系统实施成功突防（可能是被星球大战吓到了），必要时自身也是一种可怕的反击力量；不过，对战略导弹尺寸上的战术导弹化，先天不足过于明显，为了使用部署灵活、机动性强且更难以通过卫星分辨并监控的4轴TEL车作为载具，其大小仅仅只与SS-12短程导弹相当（长11.25米、直径: 1.01米、总重: 9700千克、最大射程: 800KM），故某些方面必须有所取舍，装备战略火箭军的型号在配备了带诱饵的轻型核战斗部（当量不详）时还能达到接近7000KM的射程，但配备重型常规战斗部的陆军型号只有3000KM的射程。尽管如此，个人认为其无论是在设计思想的创新上还是设计水平的超前上都已经能称得上是创举了，尤其是在那个年代，那个行将就木的红色帝国...

这玩意可不可以说就是个中导？主要威力体现在对欧洲的威慑？

小液体远程弹，TG恐怕是看不上滴！运载火箭还说说。

TG不需要这种类型的导弹
1。TG核战略与毛国不同，有限的核反击策略注定只需要维持一只少而精的战略核力量即可。
2。TG没有条约限制，有必要的话完全可以遵循国家意志生产和部署大量重型洲际弹道导弹。
3。矛-P导弹基本已经达到了极限，与毛国情况不同的是，7000KM射程对TG而言根本无法威胁美国本土。
4。该项目的诞生有其特殊背景，至于TG是不会去花那么大力气到头来却只能投射200KG弹头的。

luzhen_sh323 发表于 2009-4-30 13:22
小型导弹难道就一定要数量很多？再说了这东西还不够精么
第二条也有问题，太重的导弹限制太多了，这种小型导弹部署起来灵活性要大很多
第三条更没根据，实在不行加重几吨就好，打到美国肯定没问题
202KG的弹头威力能到50万吨，就算TG技术落后，20万吨也没问题

在新虚幻的讨论中，大家觉得我们必要的时候也需要类似的“侏儒”。

您说话的口气像中央军委{:3_85:}失禁失禁

小型导弹难道就一定要数量很多？再说了这东西还不够精么
第二条也有问题，太重的导弹限制太多了，这种小型导弹部署起来灵活性要大很多
第三条更没根据，实在不行加重几吨就好，打到美国肯定没问题
202KG的弹头威 ...
纸飞机 发表于 2009-4-30 18:48

您说话的口气像中央军委{:3_85:}失禁失禁

luzhen_sh323 发表于 2009-4-29 00:54

液体的，而且才7000km，土共不会感兴趣的

学习了。......

如果修改DF-3的投掷重量，是否能搞成类似的东西？

没记错的话，那个战神用的是所谓的核动力火箭发动机
你说DF-3能改不…………

SaturnV 发表于 2009-7-28 14:26
你这资料上哪里介绍发动机了？就一句高比冲发动机…………

SaturnV 发表于 2009-7-28 10:28

http://www.astronautix.com/engines/ares.htm

Engine Model: Ares. Designer: Aerojet. Application: SSTO ICBM. Propellants: N2O4/Aerozine-50. Thrust(vac): 440.000 kN (98,910 lbf). Isp: 370 sec. Chambers: 1. Chamber Pressure: 320.00 bar. Country: USA. Status: Development 1968.
Rudi Beichel of Huntsville had previously worked closely with Aerojet, and then came to work for Aerojet directly in 1956. His initial assignments included managing several small rocket programs, then the proposal for conversion of the Titan I first stage to burn LO2/LH2.

In mid-1960, after Aerojet lost the Saturn main engine competition, they formed a task force under Beichel to study large advanced technology rockets. This resulted in an unsolicited proposal to NASA for a "Design Study of a Large Unconventional Liquid Propellant Rocket Engine and Vehicle," and a contract was granted in early 1961. Designs were prepared for a variety of concepts. These included:


LOX/LH2 or LOX/hydrocarbon propellants
200 atm chamber pressure
Topping cycle/staged combustion
Unique plug and forced deflection nozzle clusters
Thrust range from 2 tonnes to 2.7 million kgf
Ablative nozzles
Other studies resulting in design of a single chamber LOX/LH2 engine with 11 million kgf thrust. But NASA interest in such advanced concepts dwindled, and finally settled on the relatively conservative 680,000 kgf M-1.

Meanwhile Beichel discovered that Bill Schnare at Edwards AFB had a similar interest in large, high performance rockets. The Air Force also believed that a very high performance ARES (Advanced Rocket Engine System) would allow the development of a single-stage ICBM with the range and payload performance of the Titan II.

Aerojet's ARES contract had a total value of about $20 million, supplemented by considerable corporate IR&D funds, and ran from 1962 to 1968

Initial development work focused on high chamber pressure operation, and used a regeneratively cooled tube bundle engine. The very high heat flux resulted in nozzle throat burnout, despite extensive film cooling. Even the use of auxiliary tubes (smaller in diameter than the main tubes, and laid in the "valley" between the main tubes) to carry additional film cooling propellant flow to the throat area did not solve the problem. Transpiration (sweat) cooling was suggested, but previous programs had shown that serious problems might be expected with pore clogging/non-uniformity , structural considerations, and severe manufacturing difficulties.

At this point, Robert Kuntz came forward with the idea of making the chamber of a stack of thin metal plates that had coolant channels photo-etched in their surfaces. Mueggenberg, LaBotz, and Schoenman did the design and heat transfer work, and Aerojet's platelet technology, the basis for many future Aerojet products, was created. Photo-etched platelets were also adopted for the main propellant injection, making it possible to achieve very intimate mixing of the injected propellants, as well as intricate and low volume flow passages.

Another innovation was the use of a complex, vane type, ramjet injector, fabricated by use of the platelet technology. The combination of this chamber and injector allowed achieving the objective of testing at 45,000 kgf thrust and a primary chamber pressure of 320 atm using N2O4 and Aerozine-50 propellants. For development testing, the high propellant feed pressures were achieved by using a piston driven intensifier in series with Titan engine turbopumps. The ARES design featured a single shaft turbopump, and an integrated single pressure vessel in a staged combustion cycle configuration. Subsequent work included Single Stage to Orbit (SSTO) studies, tri-propellants (dual-fuel engine), dual expander concepts, and air augmentation.

In the end the development problems and a USAF policy decision that all future ICBMs would use solid rocket propulsion killed ARES.

Note: Indicated specific impulse estimated based on use in a Titan 2-sized rocket with a Titan 2 payload but single stage to orbit performance.