JAXA's H-IIB launched manned spacecraft

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Решил открыть новую тему про японский пилотируемый космический корабль от JAXA -
последние сообщения про японское космическое агентство на форуме были:
- Japanese Moon о 20-летней программе JAXA (вкл. пилотируемые полеты);
- HTV о японском грузовом корабле для МКС.

Rob Coppinger Hyperbola Blog January 9, 2009
JAXA's H-IIB launched manned spacecraft:

The Japan Aerospace Exploration Agency (JAXA)'s rocket and spacecraft development establishment, the Tsukuba Space Center,
has produced a concept for a four-crew capsule that is part of a Mitsubishi Heavy Industries H-IIB rocket launched spacecraft
consisting of four modules
- the Launch Escape System (LES),
- Manned Re-entry Module (MRM),
- Orbital Habitation Module (OHM),
- Propulsion Module (PM).

Designed for LEO missions the JAXA's 2025 vision includes a Japanese human spaceflight capability and the concept work has
been drawn up in preparation for possible formal design cycles

The spacecraft is a 16,800kg (36,960lb), 4m (13.1ft)-diameter vehicle that would use systems from Japan's International Space
Station resupply ship H-IIB Transfer Vehicle (HTV) for its 3,800kg (fuelled) PM and 5,000kg OHM. Examples include the engines,
the Environmental Control and Life Support Systems (ECLSS), electrical power network and avionics. However JAXA expects to
have to find some mass savings in the HTV systems.

The OHM would also provide life support for the 5,000kg MRM during periods on-orbit. This would enable the MRM ECLSS to
be smaller. JAXA flight tested its Orbital Re-Entry Flight Experiment in 1994 and this would aid the MRM's development. No
final decision has been taken on the MRM's shape but the agency wants to employ controlled lift for a lift/drag ratio of 0.4

The LES is 3,000kg making up the final 16,800kg figure. Like Soyuz JAXA's spacecraft will abort with its habitation module
attached meaning it will probably require the four folding drag plates that are used to control the aborting Soyuz's
aerodynamics before its parachute controlled descent starts.

In an odd change to the norm JAXA wants, understandably, to have its MRM in the normal launch orientation but then on
orbit to use a mechanical guidance "rail and wheel system" to move the RM forwards, round and back so it can 'dock'
with its OHM.

JAXA envisages four demonstration flights, two unmanned and two manned. The first demonstrates the MRM's re-entry
performance, the second the LES, and the operational H-IIA rocket could be used for these. The third is a manned on-orbit
demonstration and the fourth is a full mission and both would need the H-IIB.

The LEO mission would involve two or three days to reach the space station and then an on-orbit capability of one to two
further weeks. JAXA rules out a lunar mission as it's beyond the H-IIB's "launch capability". What no double launch mission?

Like China's orbital module JAXA envisages its OHM as potentially becoming an additional module for a space station.

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JAXA 2025 Vision:
- MPEG 35MB
- JAXA Vision Summary (2005) PDF 4.16MB
- JAXA Vision -JAXA 2025-  (2005) PDF 2.04MB

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Первоисточник - 26th International Symposium on Space Technology and Science (Hamamatsu, Japan, 1-8 June 2008)
- это тот же симпозиум где Брюханов выступал со своей презентацией.

Preliminary Study for Manned Spacecraft with Escape System and H-IIB Rocket
By Takane Imada, Michio Ito, Shinichi Takata Japan Aerospace Exploration Agency, Tsukuba, Japan.

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JAXA's Capsule: 5 tons with 4 crew, diameter: 4m

[ronatu]

Target for manned missions are classified into following
points.
- Ballistic Flight (less than 1 revolution)
- Low Earth Orbit (a few days)
- Round trip to a base in LEO
- Round trip to the Lunar Orbit
- Round trip and landing to the Lunar Surface

[ronatu]

Propulsion Module and Orbital Habitant Module will be developed based on current design of HTV...

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Re-entry Module should be fully developed but JAXA has
experiences for un-manned re-entry module in previous
satellite programs.

OREX  was one of them and conducted de-orbit and atmosphere
re-entry experience successfully in 1994.



OREX re-entered on ballistic trajectory but Manned Re-entry
Module should flight with controlled lift (Lift/Drag = around 0.4)
for both of relieving gravity force on crews and increasing the
accuracy of splashing point in the sea.

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Re-entry Module should be fully developed but JAXA has
experiences for un-manned re-entry module in previous
satellite programs.

OREX  was one of them and conducted de-orbit and atmosphere
re-entry experience successfully in 1994.



OREX re-entered on ballistic trajectory but Manned Re-entry
Module should flight with controlled lift (Lift/Drag = around 0.4)
for both of relieving gravity force on crews and increasing the
accuracy of splashing point in the sea.

OREX flight expriment (Feb 1994) JAXA web site:






Main Characteristics
Nose radius    1.35m
Diameter    3.40m
Height    1.46m
Weight    Approx. 865kg at launch, Approx. 761kg at re-entry

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H-IIB Manned Flight (Artist Image)


HTV (Original) Configuration


Technical Relations between HTV and Manned Vehicle


Delta-V Requirements for Missions:


Propulsion Module

[RadioactiveRainbow]

А мне их корабль нравится!
Очень изящное решение компоновки модуля. Ну и вообще... хороший корабль. Без излишеств..

[Leroy]

Не понял, у него что, перестроение отсеков на орбите будет?  :shock:

[ааа]

А мне их корабль нравится!
Очень изящное решение компоновки модуля. Ну и вообще... хороший корабль. Без излишеств..

Я лет десять назад тоже до такой компоновки додумался.
Но у нее есть и ряд недостатков. Как, впрочем, и достоинств.

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Не понял, у него что, перестроение отсеков на орбите будет?  :shock:

Да - с помощью зубчато-реечного механизма:

Capability to Support Future Missions:

Fig. 10. Shows differences in Soyuz, Apollo, and JAXA's concept for module configuration. Soyuz type is simple for
operation but it is not selected in this paper mainly because of the weight penalty for Launch Escape System (LES has to
kick Habitant Module for Re-entry Module separation). Also, Apollo type is better to enhance functions in Habitant Module
such as longer on-orbit staying time capability. Two points major difference between Apollo and JAXA's concept in this
paper are as follows.
Mechanical guidance is used for orbiting connection of Re-entry Module and Habitant Module.
Orbital Habitant Module has service functions such as electrical power supply, crew support, rendezvous/docking

JAXA developed "Rail & Wheel System" for HTV Exposed pallet in un-pressurized carrier and the experience
could be usable for mechanical guidance design for module connection on orbit. Service functions were installed into
Orbital Habitant Module with considering the operation scenario to re-use Orbital Habitant Module on-orbit as one
module of space station.

Идея такая:
- стартовая конфигурация ВА (RM - Re-entry Module) и СМ (PM - Propulsion Moule) размещаются над БО (OHM - Orbital Habitant Module).
СМ и БО соединены подвижно с помощью Rail & Wheel System, имеющего 2 степени движения:
* поступательного движения вверх-вниз ();
** вращательного (СМ вращается вокруг своей горизонтальной оси на угол 180 из положения "ВА+СМ к БО задом" в положение "ВА+СМ к БО передом");  
- при аварии на активном участке выведения КК, САС (LES Launch Escape System) уводит ВА от РН (СМ и БО не уводятся - таким образом требуется менее мощная САС);
- при штатном выходе КК на околоземную орбиту после отделения верхней ступени РН, Rail & Wheel System опускает "вниз" БО на безопасное расстояние (для перестройки отеков путем вращения);
В зависимости от длины модулей КК может не осуществляться если обеспечен гарантированный зазор;
- СМ вращается вокруг своей горизонтальной оси на угол 180 из положения "ВА+СМ к БО задом" в положение "ВА+СМ к БО передом";
- Rail & Wheel System подымает "вверх" БО и тем самым осуществляет стыковку ВА с БО; У ВА 1 стыковочный агрегат, у  БО - 2 (носовой и кормовой)

[Salo]

Спасибо!
А идея перестроения отсеков Феоктистову принадлежит. :roll:

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Propulsion Module for LEO missions:


LES specifications:


Launch Escape System (LES):


Launch Profile for Demo-missions from left to right: Demonstration 1 - 4   


[Demonstration-1]
- Un-manned Flight
- Demonstrations for Re-entry Vehicle, Recovery in Sea
- Total Weight: 6 ton + Margin
i. Re-entry Capsule: 5 ton
ii. De-orbit Module: 1 ton

[Demonstration-2]
- Un-manned, but Manned Flight Path
- Demonstrations for Launch Escape/Abort System
- Total Weight: 9 ton + Margin
i. Re-entry Capsule: 5 ton
ii. De-orbit Module: 1 ton
iii. Launch Escape System: 3 ton
- Flight Path and Abort Flight (Re-entry Module L/D=0.4)

[Demonstration-3]
- Manned Flight
- Demonstrations for On-orbit Flight
- Total Weight: 14.3 ton + Margin
i. Re-entry Capsule: 5 ton
ii. Propulsion Module: 1.3 ton
iii. Propellant (off-loaded): 1 ton
iv. Launch Escape System: 3 ton
v. Orbital Habitant Module (subset): 4 ton

[Demonstration-4]
- Manned Flight
- Demonstrations for all Mission
- Total Weight: 16.8ton + Margin
i. Re-entry Capsule: 5 ton
ii. Propulsion Module: 1.3 ton
iii. Propellant (full-loaded): 2.5 ton
iv. Launch Escape System: 3 ton
v. Orbital Habitant Module: 5 ton

[frigate]

Спасибо!
А идея перестроения отсеков Феоктистову принадлежит. :roll:

"Автора в студию" (C) - в этих книгах не нашел: :oops:
- К. П. Феоктистов Траектория жизни. Между вчера и завтра. — М.: Вагриус, 2000.
- К. П. Феоктистов Космическая техника. Перспективы развития  — М.:
МГТУ им. Н. Э. Баумана  1997 - 172.

Сергей, у вас ссылки нет?

[Petrovich]

Спасибо!
А идея перестроения отсеков Феоктистову принадлежит. :roll:

"Автора в студию" (C)

Отсканил из



Под редакцией проф. К.Феоктистова. 1983г.

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С  грассирующим американским акцентом, голосом Любови Орловой из к/ф "Цирк":

"Я люблю тебя, Petrovich!"

"Спасибо  от имени парткома, профкома и от себя лично..." (C)

Космические аппараты / Под ред.Феоктистова К.П. - М. : Воениздат, 1983. - 319 с. - (Ракетно-космический комплекс).

[Petrovich]

:lol:
Голосом Савелия Краморова из к/ф ,,12 стульев,, -

Ваше кредо?
ВСЕГДА !!!