Ракета-носитель. H2A204. [Редактировать]

Дополнительная классификация

#Наименования
1Все ракеты-носители

Технические характеристики

#ХарактеристикаЗначение
1Стартовая масса, кг443000
2Масса ПН (ГПО), кг6000
31-ая ступень 1x1-ая ступень H2A
42-ая ступень 1x2-ая ступень H2A
50-ая ступень 4xРН H2A SRB-A
6Обтекатель 1xОбтекатель 5S

Экономические характеристики

#ХарактеристикаДата измеренияЗначение
1Страна Япония

Перечень запусков ракетаносителя

#Наименование Дата пуска Ракета-носитель Космодром АппаратыТип
12017-0472017-08-19H2A204ТанегасимаЯпонияЯпония1xQZS 3
Запуск
22017-0052017-01-24H2A204ТанегасимаЯпонияЯпония1xDSN 2
Запуск
32015-0722015-11-24H2A204ТанегасимаКанадаЕвропейский союз1xTelstar 12V
Запуск
42006-0592006-12-18H2A204ТанегасимаЯпонияЯпония1xKiku 8
Запуск

Надежность ракета-носителя



Найдено 12 документов по запросу «H2A204». [Перейти к поиску]


Дата загрузки: 2017-09-24
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... Vehicle configuration ................................................................. 31 Figure 1.3-3 H-IIA (H2A204) Launch Vehicle configuration ................................................................. 32 Figure... mission Launch Capabilities (H2A202 and H2A204 with model 4S Fairing) ............................................................................................................................................................ 51... mission Launch Capabilities (H2A202 and H2A204 with model 5S Fairing) ............................................................................................................................................................ 51...-coast GTO mission Launch Capabilities (H2A204 with model 4S Fairing) ............. 53...-coast GTO mission Launch Capabilities (H2A204 with model 5S Fairing) ............. 53... parameters for Standard GTO mission (H2A204) Acceleration and Relative velocity ................................................................................................................................. 56... parameter for Standard GTO mission (H2A204) Altitude ...................... 56 Figure 2.3-13 Typical... trajectory for Standard GTO mission (H2A204) Altitude ~ Range ..... 57 Figure 2.3-14... trajectory for Standard GTO mission (H2A204) Latitude ~ Longitude ............................................................................................................................................................ 57 Figure 2.3-15... for Long-coast GTO mission (H2A204) Acceleration and Relative velocity (Lift... for Long-coast GTO mission (H2A204) Acceleration and Relative velocity (~3rd... for Long-coast GTO mission (H2A204) Altitude (Lift-off~SECO2) ............................................................................................................................... 62... for Long-coast GTO mission (H2A204) Altitude ~ Range (Lift-off~SECO2... for Long-coast GTO mission (H2A204) Altitude ~ Range (Lift-off~SECO3... for Long-coast GTO mission (H2A204) Latitude ~ Longitude ............................................................................................................................................................ 63 Figure 2.4-1 Launch... for SSO mission (H2A202 and H2A204 with Model 4S fairing) ......... 65... Model 4/4D upper fairing for H2A204 .............................................................................................................................................. 87 Figure 3.3-3 Typical internal surface... inside fairing with acoustic blanket (H2A204) .................................. 78 Table 3.2-5 Summary of pyrotechnic... as shown in Figure 1.3-2. The "H2A204" consists of the first stage... : Monolithic CFRP Diameter 2.5 m SRB-A (for H2A204) Propellant (per each) 53 4.0 : LE...-A (for H2A202) Propellant (per each) H2A204 (2) 4 : HTPB composite Propellant weight 66... 21 20 Figure 1.3-3 YET04001 H-IIA (H2A204) Launch Vehicle configuration 32 Ver... of second stage) H2A202 [s] Events H2A204 [s] Chapter 2 Guidance flight mode on... of second stage) H2A202 [s] Events H2A204 [s] Guidance flight mode on -18... and H2A204 with model 4S fairing: Figure 2.3-1 -H2A202 and H2A204 with model... fairing: Figure 2.3-4 -H2A204 with model 4S fairing: Figure 2.3-5 -H2A204 with model 5S...) : Figure 2.3-7~2.3-10 -Standard GTO mission (H2A204) : Figure 2.3-11~2.3-14 -Long-coast...~2.3-20 -Long-coast GTO mission (H2A204) : Figure 2.3-21~2.3-26 YET04001 50... mission Launch Capabilities (H2A202 and H2A204 with model 4S Fairing) Payload... mission Launch Capabilities (H2A202 and H2A204 with model 5S Fairing) 51...-coast GTO mission Launch Capabilities (H2A204 with model 4S Fairing) 7,000... 6,500 PCS=99% ha=20000km(*) H2A204, Standard GTO 6,000 Payload Mass...=60000km ha=80000km 5,000 4,500 H2A204, Long-coast GTO 4780kg 4,000...-coast GTO mission Launch Capabilities (H2A204 with model 5S Fairing) 53... parameters for Standard GTO mission (H2A204) Acceleration and Relative velocity 500... parameter for Standard GTO mission (H2A204) Altitude 56 Ver. 4.0 Performance 500... trajectory for Standard GTO mission (H2A204) Altitude ~ Range 50 40 SEIG1... trajectory for Standard GTO mission (H2A204) Latitude ~ Longitude 57 YET04001 Chapter... for Long-coast GTO mission (H2A204) Acceleration and Relative velocity (Lift... for Long-coast GTO mission (H2A204) Acceleration and Relative velocity (~3rd... for Long-coast GTO mission (H2A204) Altitude ~ Range (Lift-off~SECO2... for Long-coast GTO mission (H2A204) Altitude ~ Range (Lift-off~SECO3... for Long-coast GTO mission (H2A204) Latitude ~ Longitude 63 YET04001 Chapter... payload fairing for H2A202 and H2A204 respectively. This is the envelope... inside fairing with acoustic blanket (H2A204) Center Frequency (Hz) SPL (dB... Chapter 3 Pyrotechnic shock events H2A202 H2A204 Remarks SRB-A separation upper fairing... upper fairing for H2A202 and H2A204 mission. And Figure 3.3-3 shows typical.... temperature (℃) Section Emittance Chapter 3 H2A202 H2A204 Nose cap 140 160 0.15... Model 4/4D upper fairing for H2A204 87 YET04001 Chapter 3 Second nose...



Дата загрузки: 2017-06-14
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... verify its effect for the H2A204. LE-7A Engine (Regenerative cooling... area by jet in the H2A204 configuration [Development history] - Development was... SRB-A Radiation Convection In the H2A204 configuration, the first stage engine...



Дата загрузки: 2017-02-23
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H- A Upgrade The H-IIA launch vehicle is the workhorse that has provided Japan with reliable, independent and guaranteed access to space since 2001. As the first step toward the National Flagship Launch System in the next generation, the H-IIA upgrade project aims at improving the vehicle’s geostationary transfer orbit (GTO) mission capabilities and payload environment conditions. This will enable Japan to promote R&D and utilization of space, as well as to enhance the international competitiveness of the H-IIA launch vehicle. A new challenge for the next stage The H-IIA upgrade project focuses on upper stage modifications to provide better services for customers. The development will be completed by 2013 to bring the vehicle to market as quickly as possible. 1 Long-coasting capability The coasting duration of the H-IIA upper stage will be enhanced from one hour to five hours by improving cross-cutting cryogenic propulsion technologies. This will enable to inject a spacecraft closer to geostationary orbit (GSO) than our current standard transfer orbit to extend the fuel life of satellites, while also extending limited launch windows for planetary exploration missions. 2 Improved payload environment The payload shock environment will be reduced from 4,100G to below 1,000G by a non-explosive clamp-band separation system. This allows sensitive equipments to be located closer to separation plane and problems with current pyrotechnic release devices will be mitigated. 3 Onboard Tracking System for Range Safety An onboard navigation sensor for range safety will be demonstrated that provides navigation data for range safety without tracking radar stations. This concept is intended to minimize the ground infrastructure and reduce cost of operation and maintenance. Upper stage Improved payload environment Low-shock clamp-band separation system, less than 1,000 G Onboard Tracking System for Range Safety Onboard Tracking System for Range Safety eliminates tracking radar stations Long-coasting capability White painted LH2 tank reduces propellant vaporization during long coasting Propellant settling system using vented GH2 Improved LOX chill-down operation of the upper stage Throttling of the upper stage engine, LE-5B-2 /Specifications H-IIA (current version) Launch capability, ton Long-coast GTO (Inclination: 20 deg, Perigee altitude: 3,000km; ΔV to GSO : 1,500 m/s) H-IIA upgrade H2A202 H2A204 H2A202 H2A204 − − 2.9 ton~ 4.6 ton~ 4.0 ton 6.0 ton 4.0 ton 6.0 ton Standard GTO (Inclination: 28.5 deg, Perigee altitude: 250km; V to GSO : 1,830 m/s) Payload Shock Environment (Maximum level) 1-6-5 100-8260 Tel.03-6266-6400 Fax.03-6266-6910 Japan Aerospace Exploration Agency Public Affairs Department Marunouchi Kitaguchi Bldg.3F,1-6-5 Marunouchi, Chiyoda-ku,Tokyo 100-8260,Japan Phone:+81-3-6266-6400 Fax:+81-3-6266-6910 4,100 G 1,000 G 3 JAXA Website http://www.jaxa.jp/ JAXA Mail Service http://www.jaxa.jp/pr/mail/ JSF111210T



Дата загрузки: 2017-09-25
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H- A Upgrade The H-IIA launch vehicle is the workhorse that has provided Japan with reliable, independent and guaranteed access to space since 2001. As the first step toward the National Flagship Launch System in the next generation, the H-IIA upgrade project aims at improving the vehicle’s geostationary transfer orbit (GTO) mission capabilities and payload environment conditions. This will enable Japan to promote R&D and utilization of space, as well as to enhance the international competitiveness of the H-IIA launch vehicle. A new challenge for the next stage We will achieve more efficient launch vehicle operations by improving H-IIA launch capability and its global competitiveness, and simplifying the ground facility. 1 Long-coasting capability The coasting duration of the H-IIA upper stage will be enhanced from one hour to five hours by improving cross-cutting cryogenic propulsion technologies. This will enable to inject a spacecraft closer to geostationary orbit (GSO) than our current standard transfer orbit to extend the fuel life of satellites, while also extending limited launch windows for planetary exploration missions. 2 Improved payload environment The payload shock environment will be reduced from 4,100G to below 1,000G by a non-explosive clamp-band separation system. This allows sensitive equipments to be located closer to separation plane and problems with current pyrotechnic release devices will be mitigated. 3 Navigation sensor to minimize ground infrastructure An onboard navigation sensor for range safety will be demonstrated that provides navigation data for range safety without tracking radar stations. This concept is intended to minimize the ground infrastructure and reduce cost of operation and maintenance. Upper stage Improved payload environment Low-shock clamp-band separation system, less than 1,000 G Navigation sensor to minimize ground infrastructure Onboard Tracking System for Range Safety eliminates tracking radar stations Long-coasting capability White painted LH2 tank reduces propellant vaporization during long coasting Propellant settling system using vented GH2 Improved LOX chill-down operation of the upper stage Throttling of the upper stage engine, LE-5B-2 /Specifications H-IIA (current version) Launch capability, ton Long-coast GTO (Inclination: 20 deg, Perigee altitude: 2,700km; ΔV to GSO : 1,500 m/s) Standard GTO (Inclination: 28.5 deg, Perigee altitude: 250km; V to GSO : 1,830 m/s) Payload Shock Environment (Maximum level) as of October, 2015 4-6 101-8008 Tel.03-5289-3650Fax.03-3258-5051 Japan Aerospace Exploration Agency Public Affairs Department Ochanomizu sola city,4-6 Kandasurugadai, Chiyoda-ku Tokyo 101-8008,Japan Phone:+81-3-5289-3650Fax:+81-3-3258-5051 JSF1603 H-IIA upgrade H2A202 H2A204 H2A202 H2A204 − − 2.97 ton 4.82 ton 4.0 ton 6.0 ton − − 4,100 G 1,000 G Setting a mass of payload adaptor at about 100kg http://www.jaxa.jp/ JAXA Website English http://global.jaxa.jp/



Дата загрузки: 2016-12-06
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... 9 [1] [3] [1] [1] [1] [3] [3] [3] GSLV Mk!! [2] [3] [3] [3] [3] [3] [3] [3] GSLV MkII(c) [2] [3] [3] [3] [3] [3] [3] [3] H2A202 [2] [3] [3] [3] [2] [3] [3] [3] H2A204 [3] [3] [3] [3] [3] [3] [3] [3] H2B [3] [3] [3] [3] [3] [3] [3] [3] Ariane 5 AtlasV DeltaIV Denpr...



Дата загрузки: 2017-04-08
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0.09/5
... (changeable 2 or 3) ISP: 425s H2A202 H2A204 H2B Japan's Next Generation Launcher...



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0.6/5
... satellite demand for 5 years 120 H2A204* Arian5 ECA(dual)* 100 SeaLaunch...



Дата загрузки: 2017-03-09
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0.09/5
... (в Европе — ракета Ariane-6, в Японии — ракета H2A204, в Китае — ракета CZ-5/504). Тем...



Дата загрузки: 2017-05-20
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46 The Development of the H2A204 Type and the Successful Maiden Flight Takashi Maemura Takeshi Mori Koki Nimura Tokio Nara Junichi Horikawa H-IIA HA GTO HA SRB-A HA H-IIA HA GTO SRB-A GTO SRB-A HA H-IIA 47 SRB-A SRB-A SRB-A SRB-A SRB-A SRB-A HA SRB-A HA SRB-A SRB-A SRB-A SRB-A SRB-A SRB-A CFD SRB-A HA HA CFD 48 HA H-IIA HA H-IIA ETS GTO SRB-A H-IIA -



Дата загрузки: 2017-05-20
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... enhanced. JAXA has been developing H2A204, the H-IIA augmented version that...