КК CEV "Constellation"

[Yegor]

[unhappy]

Это концепт-кар (картинка для пионеров). Может лучше будет, может хуже.
А его действительно зовут, как в заголовке указано?

[Yegor]

А его действительно зовут, как в заголовке указано?

Да вроде так: Сonstellation/CEV

[Yegor]

Ronatu, а что это такое? КК Союз-2 made in USA   ?

[unhappy]

Кража китайских технологий шлионами Америки :!:

[pkl]

Занятно. Узнать бы где габариты и массу бандуры. Интересно, а ОО американского корабля будет выводиться вместе с ВА и приборно-агрегатным отсеком или отдельно? Это я к тому, что на Луну то они летят со стыковкой на околоземной орбите. Так, может, им и бытовой отсек CEVа запускать вместе с лунным лэндером. Как вам такая схема?

[Yegor]

Занятно. Узнать бы где габариты и массу бандуры. Интересно, а ОО американского корабля будет выводиться вместе с ВА и приборно-агрегатным отсеком или отдельно? Это я к тому, что на Луну то они летят со стыковкой на околоземной орбите. Так, может, им и бытовой отсек CEVа запускать вместе с лунным лэндером. Как вам такая схема?

Эх, если требуются дополнительные удобства и топливные ресурсы позволяют: Как на счёт того чтобы бочку от лунного лендера за собой таскать? Ну к Луне она и так и так с нами. На обратной дороге: взлетели с Луны, состыковались, отбросили от лендера платформу с баками и осталась у нас одна бочка со всеми удобствами   .

[pk13]

Это концепт-кар (картинка для пионеров). Может лучше будет, может хуже.

Да уж, по крайней мере МКС такая как на картинке уже точно не будет.

[ДмитрийК]

НАСА уже готовится раздавать контракты:
http://www.spaceref.com/news/viewsr.html?pid=18285

NASA/GRC plans to issue a Request for Proposal (RFP)] for the development of a prototype cryogenic propellant isolation valve that provides approximately 36 lbm/sec of liquid oxygen at approximately 15 psid (or 12 lbm/sec liquid methane) for long duration in-space operation. This valve should be hermetically sealed, operate on 28 VDC, provide liquid lock back relief, and operate at approximately 500 psia MAWP. The valve should be able to operate in vacuum with insulation on the valve and motor (motor at cryogenic temperatures), and minimize heat leak into the valve from the mounting fixture. It is expected that the resultant contract will have a value between $1,5M and $2.0M.

Очень интересно. Они еще смутно представляют как этот пепрелац будет выглядеть, но уже точно знают какой им нужен клапан, а главное - сколько будет стоить

[Agent]

Нортроп с Боингом наконец начали чето показывать...

[X]

[X]

[Yegor]

Молодцы ребята из НАСА перенимают лучший мировой опыт - наш. Все на одной платформе ПАО как в наших КК Союз и гузовике Прогресс. Только ещё более всё универсально - ПАО большой и туда можно больше топлива заливать. Молодцы!

[X]

НАСА то тут не при чем.
Boeing & Northrop Grumman

About 200 workers at Northrop Grumman in El Segundo, and about 30 more at Boeing-Huntington Beach, have been at work on the concept since summer 2004, when NASA awarded the consortium $28 million to come up with a proposal.

[X]

http://www.irconnect.com/noc/press/pages/news_releases.mhtml?d=87722

[X]

http://www.irconnect.com/noc/press/pages/news_releases.mhtml?d=87722

[Agent]

NASA LaRC Solicitation: Landing System for Earth Entry Capsules

Synopsis - Oct 11, 2005

General Information

Solicitation Number: N/A
Reference Number: LAS-101105-LCT
Posted Date: Oct 11, 2005
FedBizOpps Posted Date: Oct 11, 2005
Original Response Date: Oct 24, 2005
Current Response Date: Oct 24, 2005
Classification Code: A -- Research and Development
NAICS Code: 541710 - Research and Development in the Physical, Engineering, and Life Sciences

Contracting Office Address

NASA/Langley Research Center, Mail Stop 144, Industry Assistance Office, Hampton, VA 23681-0001

Description

NASA/LaRC is hereby soliciting information about potential sources to participate in the development of a landing attenuation system for the Crew Exploration Vehicle (CEV). NASA envisions this development project to include trade studies, energy absorber design, and characterization tests of candidate landing system configurations. NASA is currently conducting market research to identify firms with specialized expertise in the design, analysis, and fabrication of energy absorbers capable of meeting the preliminary CEV landing specifications listed below. Candidate energy absorber concepts include, but are not limited to air bags, crushable structures, and energy absorbing landing struts.

Preliminary CEV Landing Attenuation System Specifications: The following landing attenuation system specifications are preliminary and therefore subject to change. The specifications are intended to depict the general performance envelope of the anticipated landing attenuation system. Specific, more-detailed performance requirements will be developed by the Government at a later date.

1. The landing attenuation system shall be designed for a CEV landing within a Government-controlled land range in the continental United States, but must also be suitable for off-nominal water landings associated with launch abort scenarios.

2. The landing attenuation system shall reduce the landing loads of the CEV to within human-acceptable limits. The human-acceptable limits will be defined by the Government at a later date.

3. The landing attenuation system shall prevent the CEV capsule from over-turning or rolling over during or after landing. 4. The landing attenuation system shall operate within acceptable limits for the following ranges of landing conditions:

    * Landed CEV Mass: 9,000 to 12,000 kg
    * Landing Velocity (Vertical): 6 m/sec to 8 m/sec
    * Landing Velocity (Horizontal): 0 m/sec to 8 m/sec
    * Capsule Attitude: 0 degrees to 15 degrees relative to surface

5. The landing attenuation system shall stow within the available volume within the CEV capsule, be capable of withstanding extended duration space environments, and then be capable of being deployed during the CEV terminal descent at Earth. The available CEV volume will be provided by the Government at a later date. 6. The landing attenuation system shall be capable of being successfully deployed at angles-of-attack up to +/- 20 degrees during the CEV terminal descent. 7. The landing system shall be at a state of technological readiness such that a full-scale system can be designed, fabricated, and tested no later than November 1, 2006.

When responding to this RFI, respondents shall address their capabilities and experience in the areas listed below.

a) Design of landing attenuation systems for aerospace hardware, with specific emphasis on human-rated systems.

b) Energy absorber system analysis and modeling including deployment modeling and impact dynamic analysis.

c) Development testing and qualification testing of energy absorber systems including flight tests and drop tests.

d) Fabrication of energy absorber systems and related deployment systems.

Respondents shall emphasize how their stated capabilities and experience relate to the specific performance requirements and challenges associated with developing the CEV landing attenuation system. Interested respondents shall include a narrative that explains their actual capability and experience in the design, analysis, fabrication and testing, of deployable impact attenuation systems for aerospace applications.

No solicitation exists; therefore, do not request a copy of the solicitation. If a solicitation is released it will be synopsized in FedBizOpps and on the NASA Acquisition Internet Service. It is the potential offeror's responsibility to monitor these sites for the release of any solicitation or synopsis.

Interested offerors/vendors having the required specialized capabilities to meet the above requirement should submit a capability statement indicating the ability to perform all aspects of the effort described herein. Written responses shall be limited to ten (10) pages, # 12 pt, Times New Roman font,

[Oleg]

http://www.andrews-space.com/thumb/phpThumb.php?src=../images/pages/cevmockup.jpg&w=750

Интересное решение.

[Yegor]

http://www.andrews-space.com/thumb/phpThumb.php?src=../images/pages/cevmockup.jpg&w=750

Во дают! Не прошло и двух месяцев, а у них уже макет готов!

[Yegor]

http://www.andrews-space.com/thumb/phpThumb.php?src=../images/pages/cevmockup.jpg&w=750

Ух ты! А у них тепловой щит кривой! С чего бы это? :roll:
И воздушные подушки лопаются при посадке, то есть смягчают удар при приземлении.