Ракета-носитель. H2A202. [Редактировать]

H2A202, Японский ракетаноситель, разработанные для выполнения задач различного направления. Обладает простым диазйном и повышенной эффективностью. 

Дополнительная классификация

#Наименования
1Все ракеты-носители
2Ракеты-носители среднего класса (от 4 до 15 тонн ПН на НОО)

Технические характеристики

#ХарактеристикаЗначение
1Длина, метра53
2Стартовая масса, кг289000
3Масса ПН (ГПО), кг4100
4Масса ПН (НОО), кг10000
5Масса ПН (ССО (летом)), кг4000
6Масса ПН (ССО (зима, весна и осень)), кг3800
7Масса ПН (отлетные траектории), кг2500
81-ая ступень 1x1-ая ступень H2A
92-ая ступень 1x2-ая ступень H2A
100-ая ступень 2xРН H2A SRB-A
11Обтекатель 1xОбтекатель 4S

Экономические характеристики

#ХарактеристикаДата измеренияЗначение
1Страна Япония
2Стоимость (пуска), млн. долл.2015-03-2688.85

Перечень запусков ракетаносителя

#Наименование Дата пуска Ракета-носитель Космодром АппаратыТип
12017-0602017-10-10H2A202ТанегасимаЯпонияЯпония1xQZS 4
Запуск
22017-0282017-06-01H2A202ТанегасимаЯпонияЯпония1xQZS 2
Запуск
32017-0152017-03-17H2A202ТанегасимаЯпонияЯпония1xIGS-Radar 5
Запуск
42016-0652016-11-02H2A202ТанегасимаЯпонияСШАЯпония1xHimawari 9
Запуск
52016-0122016-02-17H2A202ТанегасимаЯпонияЯпония1xChubuSat 3
ЯпонияЯпония1xChubuSat 2
ЯпонияЯпония1xHoryu 4
ЯпонияЯпония1xAstro-H
Запуск
62015-0162015-03-26H2A202ТанегасимаЯпонияЯпония1xIGS-Optical 5
Запуск
72015-0042015-02-01H2A202ТанегасимаЯпонияЯпония1xIGS-Radar Spare
Запуск
82014-0762014-12-03H2A202ТанегасимаЯпонияЯпонияГермания1xHayabusa-2
ЯпонияЯпония1xProcyon
ЯпонияЯпония1xDESPATCH
ЯпонияЯпония1xShinen 2
Запуск
92014-0602014-10-06H2A202ТанегасимаЯпонияСШАЯпония1xHimawari 8
Запуск
102014-0292014-05-24H2A202ТанегасимаЯпонияЯпония1xALOS 2
ЯпонияЯпония1xUniform 1
ЯпонияЯпония1xSOCRATES
ЯпонияЯпония1xRising 2
ЯпонияЯпония1xSPROUT
Запуск
112014-0092014-02-27H2A202ТанегасимаЯпонияЯпония1xShindaiSat
ЯпонияЯпония1xITF 1
МеждународныеМеждународные1xGPM
ЯпонияЯпония1xOPUSAT
ЯпонияЯпония1xTeikyoSat 3
ЯпонияЯпония1xINVADER
ЯпонияЯпония1xKSAT 2
ЯпонияЯпония1xSTARS 2
Запуск
122013-0022013-01-27H2A202ТанегасимаЯпонияЯпония1xIGS 8A
ЯпонияЯпония1xIGS 8B
Запуск
132012-0252012-05-17H2A202ТанегасимаСШАЯпонияЯпония1xGCOM W1
Южная КореяЮжная КореяФранцияВеликобританияГермания1xKompsat 3
ЯпонияЯпония1xSDS 4
ЯпонияЯпония1xHoryu 2
Запуск
142011-0752011-12-12H2A202ТанегасимаЯпонияЯпония1xIGS 7A
Запуск
152011-0502011-09-23H2A202ТанегасимаЯпонияЯпония1xIGS 6A
Запуск
162010-0452010-09-11H2A202ТанегасимаЯпонияЯпония1xQZS 1 (Michibiki)
Запуск
172010-0202010-05-20H2A202ТанегасимаЯпонияЯпония1xHayato
ЯпонияЯпония1xWaseda-Sat2
ЯпонияЯпония1xNegai
ЯпонияЯпония1xAkatsuki
ЯпонияЯпония1xIKAROS
ЯпонияЯпония1xUnitec-1
Запуск
182009-0662009-11-28H2A202ТанегасимаЯпонияЯпония1xIGS 5A
Запуск
192009-0022009-01-23H2A202ТанегасимаЯпонияЯпония1xGOSat
ЯпонияЯпония1xPrism
ЯпонияЯпония1xSprite-Sat
ЯпонияЯпония1xKagayaki
ЯпонияЯпония1xSOHLA 1
ЯпонияЯпония1xSDS 1
ЯпонияЯпония1xStars
ЯпонияЯпония1xKKS 1
Запуск
202006-0372006-09-11H2A202ТанегасимаЯпонияЯпония1xIGS 3A
Запуск
212002-0562002-12-14H2A202ТанегасимаЯпонияМеждународные1xADEOS 2
АвстралияАвстралия1xFedsat
ЯпонияЯпония1xWEOS
ЯпонияЯпония1xMicro-labsat
Запуск
222001-0382001-08-29H2A202ТанегасимаЯпонияЯпония1xLRE
Запуск

Надежность ракета-носителя



Найдено 19 документов по запросу «H2A202». [Перейти к поиску]


Дата загрузки: 2017-09-24
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0.11/5
... Vehicle Family............................................................................................. 30 Figure 1.3-2 H-IIA (H2A202) Launch Vehicle configuration ................................................................. 31 Figure... standard GTO flight sequence for H2A202 ........................................................... 45 Figure 2.1-2 Typical long-coast... 2.3-1 Standard GTO mission Launch Capabilities (H2A202 and H2A204 with model 4S... 2.3-2 Standard GTO mission Launch Capabilities (H2A202 and H2A204 with model 5S...-coast GTO mission Launch Capabilities (H2A202 with model 4S Fairing) ............. 52...-coast GTO mission Launch Capabilities (H2A202 with model 5S Fairing) ............. 52... parameters for Standard GTO mission (H2A202) Acceleration and Relative Velocity ................................................................................................................................ 54... (H2A202) Altitude ........................ 54 Figure 2.3-9 Typical flight trajectory for Standard GTO mission (H2A202... trajectory for Standard GTO mission (H2A202) Latitude ~ Longitude ............................................................................................................................................................ 55 Figure 2.3-11... for Long-coast GTO mission (H2A202) Acceleration and Relative velocity (Lift... for Long-coast GTO mission (H2A202) Altitude (Lift-off~SECO2) ............................................................................................................................... 59... for Long-coast GTO mission (H2A202) Latitude ~ Longitude ............................................................................................................................................................ 60 Figure 2.3-21... flight trajectory for SSO mission (H2A202 with Model 4S fairing) ..................... 65... 2.5-1 Launch capability for LEO mission (H2A202 with Model 5S fairing) (inclination... 2.5-2 Launch capability for LEO mission (H2A202 with Model 5S fairing) (inclination... capability for earth escape mission (H2A202)....................................................... 68 Figure 2.7-1 Sample image of... Model 4/4D upper fairing for H2A202 .............................................................................................................................................. 87 Figure 3.3-2 Typical internal surface... inside fairing with acoustic blanket (H2A202) .................................. 77 Table 3.2-4 Sound pressure level... H-IIA subsystems and characteristics. The "H2A202" consists of the first stage...-H, 1666LS-H First stage Propellant Tank H2A202 53 4.0 : Fairing 4.07 / 5.1 4.07 / 5.1 4S... NOTE : Core Propulsion SRB-A (for H2A202) Propellant (per each) H2A204 (2) 4 : HTPB... 21 20 Figure 1.3-2 Ver. 4.0 H-IIA (H2A202) Launch Vehicle configuration 31 YET04001... for sequence of events for H2A202 is representatively used corresponding to... (two burns of second stage) H2A202 [s] Events H2A204 [s] Chapter 2 Guidance flight... (three burns of second stage) H2A202 [s] Events H2A204 [s] Guidance flight mode... standard GTO flight sequence for H2A202 45 YET04001 Chapter 2 Chapter 2 Geostationary... 2.3.3(1) are as follows. Chapter 2 For H2A202 (delta-V to GEO =1830m/s), -Model... below. -H2A202 and H2A204 with model 4S fairing: Figure 2.3-1 -H2A202 and H2A204... Section 2.3.3(2) are as follows. For H2A202 (delta-V to GEO =1500m/s), -Model... as below. -H2A202 with model 4S fairing: Figure 2.3-3 -H2A202 with model 5S... shown below. -Standard GTO mission (H2A202) : Figure 2.3-7~2.3-10 -Standard GTO mission...~2.3-14 -Long-coast GTO mission (H2A202) : Figure 2.3-15~2.3-20 -Long-coast... 2.3-1 Standard GTO mission Launch Capabilities (H2A202 and H2A204 with model 4S.... 4.0 Standard GTO mission Launch Capabilities (H2A202 and H2A204 with model 5S...=99% 6,000 H2A202, Standard GTO 5,000 4,500 3,500 H2A202, Long-coast GTO... parameters for Standard GTO mission (H2A202) Acceleration and Relative Velocity S/C SEP... parameter for Standard GTO mission (H2A202) Altitude 54 Ver. 4.0 Performance 1800... trajectory for Standard GTO mission (H2A202) Altitude ~ Range SEIG1 Tanegashima Space... trajectory for Standard GTO mission (H2A202) Latitude ~ Longitude 55 YET04001 Chapter... for Long-coast GTO mission (H2A202) Acceleration and Relative velocity (Lift... for Long-coast GTO mission (H2A202) Acceleration and Relative velocity (~3rd... for Long-coast GTO mission (H2A202) Latitude ~ Longitude 60 Ver. 4.0 Performance... 2.5-1 Launch capability for LEO mission (H2A202 with Model 5S fairing) (inclination.... 4.0 Launch capability for LEO mission (H2A202 with Model 5S fairing) (inclination... capability for earth escape mission (H2A202) 68 Ver. 4.0 Performance 2.7.2 Separation sequence... inside fairing with acoustic blanket (H2A202) Center Frequency (Hz) SPL (dB... events Chapter 3 Pyrotechnic shock events H2A202 H2A204 Remarks SRB-A separation upper... Max. temperature (℃) Section Emittance Chapter 3 H2A202 H2A204 Nose cap 140 160... of Model 5S fairing for H2A202 88 Ver. 4.0 Environments Chapter 3 Aerothermal...



Дата загрузки: 2017-02-23
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0.12/5
... tall, the standard H-IIA, dubbed H2A202, has a 4-meters diameter payload fairing.... Configuration of H-IIA Launch Vehicle (H2A202) The H-IIA second stage was... tall, the standard H-IIA, dubbed H2A202, has a 4-meters diameter payload fairing.... Configuration of H-IIA Launch Vehicle (H2A202) The H-IIA second stage was...



Дата загрузки: 2017-05-20
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0.05/5
... tall, the standard H-IIA, dubbed H2A202, has a 4-meters diameter payload fairing... rocket accelerates through the atmosphere. H2A202 can put about 4 tons into... of Launch Vehicle (H2A202) Configuration of H-IIA Launch Vehicle (H2A202) The H-IIA...



Дата загрузки: 2017-06-16
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0.05/5
... Launch Vehicle. TF1 (H2A202) TF2 (H2A2024) F3 (H2A2024) F4 (H2A202) F5 (H2A2024... Acoustic Blanket) Center Frequency (Hz) H2A202 Acoustic Level (dB) H2A212 Acoustic...



Дата загрузки: 2017-02-23
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0.08/5
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: 2017-06-15
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0.06/5
...-3: Configuration of the Launch Vehicle (H2A202 Type) Figure-4: On-orbit Configuration...-3: Configuration of the Launch Vehicle (H2A202 type) - 15 - Table-3: Major Characteristics...



Дата загрузки: 2017-09-24
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0.28/5
...-by Jupiter Gravity Assist (JGA) • H2A202 +KM_V2 (kick-motor) • Solar observations... plane. JGA + Earth Gravity Assist • H2A202 +KM_V2 (kick-motor) • Orbital period... orbital plane. JGA + Powered EGA • H2A202+KM_V2 (kick-motor) + additional engine...



Дата загрузки: 2017-09-25
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0.11/5
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: 2017-04-24
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0.04/5
... Orbit for HTV H2B SRB-A H2A202 First Stage Engine LE-7A...



Дата загрузки: 2017-03-28
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0.12/5
... in 2013 H-IIA Launch Parameters H2A202 Height Gross Mass (excluding satellite...