Ракета-носитель. H2A2024. [Редактировать]

Дополнительные наименования

#НаименованияПоиск в новостяхПоиск в документах
1H-IIA 2024НайтиНайти
2H-2A 2024НайтиНайти

Дополнительная классификация

1Все ракеты-носители

Технические характеристики

1Стартовая масса, кг351000
2Масса ПН (ГПО), кг5000
31-ая ступень 1x1-ая ступень H2A
42-ая ступень 1x2-ая ступень H2A
50-ая ступень 2xРН H2A SRB-A
60-ая ступень 4xРН H2A SSB
7Обтекатель 1xОбтекатель 4 (4D-LС)

Экономические характеристики

#ХарактеристикаДата измеренияЗначение
1Страна Япония

Перечень запусков ракетаносителя

#Наименование Дата пуска Ракета-носитель Космодром АппаратыТип
22007-0052007-02-24H2A2024ТанегасимаЯпонияЯпония1xIGS 4A
ЯпонияЯпония1xIGS 4B
32006-0042006-02-18H2A2024ТанегасимаЯпонияЯпония1xMTSat 2
42003-F022003-11-29H2A2024ТанегасимаЯпонияЯпония1xIGS O-2a
ЯпонияЯпония1xIGS R-2a
52003-0092003-03-28H2A2024ТанегасимаЯпонияЯпония1xIGS 1A
ЯпонияЯпония1xIGS 1B
72002-0032002-02-04H2A2024ТанегасимаЯпонияЯпония1xMDS 1

Надежность ракета-носителя

Найдено 3 документов по запросу «H2A2024». [Перейти к поиску]

Дата загрузки: 2017-06-16
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.... TF1 (H2A202) TF2 (H2A2024) F3 (H2A2024) F4 (H2A202) F5 (H2A2024) August 29, 2001...

Дата загрузки: 2016-12-09
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powerful than the 26,400lb-thrust LE-5A. Apart from the increased thrust, the key difference between the two is in the construction of the LOX and L H fuel tanks. In the H-2, the tanks were manufactured together as a single welded unit, with the larger L H tank fixed to die top of the LOX tank. T h e tanks are now fabricated as separate units for ease of manufacture and for safety. There is, however, a weight penalty to be paid for diis change, says Endo. FOREIGN TECHNOLOGY "When we developed the H-2, the target was 100% Japanese manufacture, but in the H-2 A we decided to use foreign technology and materials," says Endo. For example, some components of the second stage fuel tanks are imported from the USA. This outsourcing, as well as the increased use of commercial off-theshelf components, from both Japanese and foreign suppliers, has helped to keep costs down. T h e H-2A uses a strap-down inertial guidance and control system, similar to the H-2's, comprising a newly developed inertial measurement unit, using ring laser gyros and a guidance control computer. These control thrust vectoring in the engine nozzles of borfi stages, while the second stage has an additional gas jet reaction control system. T h e vehicle has been fitted with a simplified electrical system, featuring a 1553B databus. Japanese electronics and computer giant NI (! is providing much of the on-board computer and telemetry equipment, while the inertial measurement system comes from Japan Aviation Electronics Industry. T h e H-2 A is fitted with an automated diagnostic system, intended to reduce pre-launch processing time dramatically. Two failures of the H-2 led to the cancellation of the last launch satellite launch industry in Japan will be saved by the H-2A's success. In the meantime, they admit that the industry remains in a "very, very dangerous" position. All these innovations and modifications are intended to cut the H-2 As launch costs to about half of the LI-2's - to about ¥8.5 billion. If all works well, NASDA proposes a family of launch vehicles, with capabilities far exceeding anythingjapan has launched to date. T h e H2 A202, H2A2022 and H2A2024 configurations will be able to put 4-4.5t payloads in geostationary transfer orbit (GTO), with the extra launch thrust provided by up to four solid strap-on boosters as well as the two SRB-As. which generated 190,001b of thrust at sea level. Manufacture of the engine and of die first stage has been simplified by increased use of casting and machining, and less welding, to reduce costs and risk. SIMPLICITY AND RELIABILITY T h e H-2's SRBs were made from polybutaT h e LRB-equipped H2A212 allows an extra T h e H-2 Ais design aims for simplicity and reli- diene composite shells and generated about ability, with the most obvious differences in its 350,0001b of thrust each. T h e H-2A's SRB-A 3.5t of payload, givinga 7.5tcapability t o G T O , MHI-built engines and boosters. NASDA pre- boosters are also composite, but, while Endo with NASDA planning an enlarged payload dicts that its basic launch configuration - named says that the original 11-2 SRB was made in four fairing for this configuration. T h e LRB itself is H2 A202, with two SRB-A boosters - will have a steel casing segments, each SRB-A is built as a powered by two LE-7A engines. T h e agency reliability of over 0.97. A planned heavyweight single unit of polybutadiene composite. This plans the first launch of this configuration a year development of the rocket, with an additional technology was imported from the USA's after the first H-2A launch. NASDA is also external liquid rocket booster (LRB) - called Thiokol, which provided the machinery and studying a further augmented configuration, H2 A2 2 2, with two LRBs as well as the"SRB-As, H2A212 -will have a reliability exceeding 0.96. know-how, says Endo. T h e agency qualifies these predictions, howevT h e new materials and manufacturing pro- which would offer a 9.5t-to-GTO capability. er, by saying that they are made with a "confi- cess cut weight and increase structural integrity. Whether any of these developments see die dence level" of 60%. T h e SRB-As also generate 507,0001b of thrust light of day depends largely on the success of die T h e H-2A's first stage is powered by the each, compared with the original SRB's H-2A's first launch in a year's time. Payload space is reserved by Hughes and Loral, which improved LE-7A LOX/LH-fuelled engine, 350,0001b. which provides 247,0001b of thrust (1,1 OOkN) T h e second stage is powered by tile 31,0001b- will only turn into real contracts if the first two • substantially more than the 11-2's LE-7 engine, thrust LE-5B engine, which is slightly more launches go smoodily. FLIGHT INTERNATIONAL 14 - 20 March 2000 35

Дата загрузки: 2016-12-09
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... by NASDA as H2A202, H2A2022, H2A2024, H2A212, and H2A222. 122 The...