IGS-Radar Spare – H-2A 202 (F27) – Танегасима – 01.02.2015 01:21 UTC

Автор che wi, 21.01.2015 15:46:40

« предыдущая - следующая »

0 Пользователей и 1 гость просматривают эту тему.

che wi

Пуск 29 января 2015, время: 10:00-12:00 JST (01:00-03:00 UTC / 04:00-06:00 MSK)

Пресс-релиз на сайте JAXA (пока только на японском)
http://www.jaxa.jp/press/2014/12/20141204_h2af27_j.html

Статья на spaceflight101.com
http://www.spaceflight101.com/h-iia---igs-9-launch-updates.html


Безумный Шляпник

HYDROPAC 271/2015 (81,97)  

WESTERN NORTH PACIFIC.
PHILIPPINE SEA.
ROCKETS.
DNC 11, DNC 12, DNC 23.
1. HAZARDOUS OPERATIONS 290100Z TO 290331Z JAN
   IN AREAS BOUND BY:
   A. 26-49N 135-25E, 27-38N 136-16E,
      26-14N 137-36E, 25-26N 136-45E.
   B. 16-32N 134-17E, 13-43N 135-28E,
      12-52N 133-25E, 15-41N 132-15E.
2. CANCEL THIS MSG 290431Z JAN 15.

( 241208Z JAN 2015 )

Salo

http://forum.nasaspaceflight.com/index.php?topic=36613.msg1321700#msg1321700
ЦитатаGalactic Penguin SST пишет:
Launch time has just been confirmed as 01:21 UTC on January 29 (as expected from the orbit of similar satellites). Launch window lasts 13 minutes to 01:34 UTC.

http://www.jaxa.jp/press/2015/01/20150127_h2af27_j.html
"Были когда-то и мы рысаками!!!"









Space Alien

28.01.2015 11:31:05 #12 Последнее редактирование: 28.01.2015 15:31:12 от Артём Жаров
Ну и запись вывоза:

http://www.youtube.com/watch?v=nsOCWOHkJXw

che wi

28.01.2015 15:51:13 #13 Последнее редактирование: 28.01.2015 17:20:27 от che wi
 

che wi

H-IIA Rocket set to Launch classified IGS Radar Surveillance Satellite
http://www.spaceflight101.com/h-iia---igs-radar-launch-updates-2015.html

ЦитатаA Japanese H-IIA rocket is ready for the launch of a semi-classified radar reconnaissance satellite on Thursday to keep Japan's fleet of optical and radar surveillance satellites topped up and in operation. Liftoff of the H-IIA is set for 1:21 UTC on Thursday, the opening of a 13-minute launch window. The mission is of a semi-secret nature - there will be no official launch broadcast and the only information that will be provided is a confirmation of launch success.

The satellite to be launched on Thursday is part of Japan's IGS satellite constellation (Information Gathering Satellites) that have gone through several generations of optical and radar imaging spacecraft since the program's first launch in 2003. Over the course of the program, more and more advanced satellites were launched achieving better ground resolutions for optical and radar data products. The satellites also operate from different orbits.

The IGS satellite launching in January is a Radar Satellite launched as an in-orbit spare likely belonging to the third generation of SAR satellites to be ready to take over from IGS 7 launched in December 2011, passing the three-year mark in its mission which may be the identified design life of the spacecraft based on the behavior of earlier IGS satellites. It will be followed by another IGS later in 2015 which will be an operational 5th generation optical satellite following the experimental 5th generation satellite launched in 2013.

JAXA issued the confirmation of the planned launch date and window on Tuesday and officially identified the satellite as IGS Radar Spare. Mitsubishi Heavy Industries, operator of the H-II rocket fleet, will not issue any updates on the launch and the only official information will confirm the liftoff and the separation of the satellite into the target orbit less than 25 minutes after launch. No information on pre-launch processing milestones for this mission are available and there will be no official launch webcast. Usually, there will be amateur webcasts and photos from the visitors site covering the initial stages of the H-IIA flight.

 Скрытый текст:
Countdown operations are expected to begin with the rollout of the H-IIA rocket from the Vehicle Assembly Building to the second launch pad at the Tanegashima Space Center, planned to begin at 12 UTC on Wednesday. Riding atop the Mobile Launch Table, the H-IIA rocket will take about 30 minutes for the 400-meter trip - being centered in a precise position at the launch pad.

After arriving at the Pad, technicians connect data and electrical lines and put propellant umbilicals in place before completing final fueling preparations and close-outs. About eight hours before launch, teams evacuate the launch pad to get ready for the long propellant loading sequence.

Beginning at about X-7 Hours and 45 Minutes, the complex propellant loading sequence gets underway with the pressurization and chilldown of ground support systems handling the -183-degree Celsius LOX and -253°C LH2. Fueling goes through a number of steps including ground support system chilldown, propellant tank chilldown and propellant loading, before tanking enters replenish mode. The propellant loading sequence takes approximately three hours until the 116,600 Kilograms of cryogenics needed for launch are loaded. Replenishing the propellants as they boil off, the tanks are kept at topping level until late in the countdown.

The majority of the countdown will be spent with extensive tests of the launch vehicle's flight control system, checks of all electronics and controllers and verifications of the radio link between the launcher and the ground. Flight Termination System testing is also performed in the early stages of the countdown.

H-IIA 202 has a liftoff weight of 285,000 Kilograms standing 53 meters tall with a core diameter of 4 meters using a two-stage stack with two Solid Rocket Boosters attached to the first stage. The rocket is capable of delivering payloads of up to 4,500 Kilograms to an IGS-type Sun-Synchronous Orbit.

The first stage of the H-IIA is 37.2 meters long and capable of holding about 100,000 Kilograms of cryogenic propellants, Liquid Oxygen and Liquid Hydrogen for consumption by the single LE-7A main engine. LE-7A is a staged combustion cycle engine delivering 1,087 Kilonewtons of thrust. Attached to the first stage are two SRB-A Solid Rocket Boosters - each 15.1 meters long and 2.5 meters in diameter weighing 76.4 metric tons.

Each of the boosters (when flying in the SRB-A configuration) burns around 65,000kg of propellants during a 110-second burn. SRB-A delivers 2,260kN of thrust. Booster separation is triggered by pyrotechnics and the SRBs use struts to ensure a clean separation.

The second stage of the H-IIA 202 is 9.2 meters long with a diameter of 4 meters. It also uses LOX and LH2 propellants, being filled with 16,600kg of cryogenics. One LE-5B engine powers the second stage providing a vacuum thrust of 137kN. The engine can make multiple ignitions to target a variety of orbits.

At X-60 Minutes, the Terminal Countdown Sequence will start. During the final hour of the countdown, last-minute items will be closed out and the vehicle will be reconfigured for the Automatic Countdown Sequence starting just 4.5 minutes prior to blastoff.

As computers are given control of the countdown, H-IIA's Propellant Tanks will be pressurized for flight. At X-3 minutes, the launch vehicle is switched to internal power while 'IGS Radar Spare' will have been switched to battery power ahead of the final countdown sequence. One minute before liftoff, thousands of Kilograms of water are being poured over the launch platform to suppress the acoustic loads at ignition & liftoff.

Launch Vehicle Ordnances will be armed at X-30 Seconds and the Guidance System of the Vehicle is being switched to Flight Mode 12 Seconds later before the sparklers underneath the LE-7A main engine ignite to burn off residual Hydrogen.

Ignition Sequence Start is commanded at X-5.2 Seconds and the LE-7A Engine soars to life as the turbopumps spin up to flight speed being monitored by on-board computers to make sure the engine is healthy before the booster ignition command is issued at T-0 - committing the vehicle to launch.

At the moment of booster ignition, the H-IIA rocket leaps off its pad with a total thrust of around 570 metric ton-force with the two boosters delivering 75% of the total thrust at liftoff, supplying the extra kick needed to send IGS on its way. H-IIA will make a short vertical ascent before beginning to pitch and roll in order to get aligned with its precisely planned ascent path taking the launch vehicle to the south-east for a Dogleg Maneuver. On its way uphill, H-IIA quickly passes Mach 1 and Maximum Dynamic Pressure.
To reach a polar orbit from its picturesque launch site located on the southern tip of Japan, H-IIA will have to make a Dogleg Maneuver. A Dogleg is a powered turn in the ascent trajectory of a rocket. For a direct ascent into a polar orbit, H-IIA would need to fly south-west over the Philippines. To avoid populated islands located along the direct ascent path, the Dogleg has to be inserted in order to ensure no launch vehicle debris hit populated areas, both during a nominal flight and in a launch failure.

For the Dogleg, H-IIA will fly downrange for about 100 Kilometers sticking to a south-easterly path before initiating the turn to the south-west late in the first stage burn, ensuring that all debris fall short of populated areas. A Dogleg comes at the cost of launch vehicle performance in terms of payload capability as additional fuel is required for the turn.

The two boosters burn for about 100 (SRB-A) to 115 (SRB-A3) seconds - burnout will be sensed by the declining pressure in the combustion cambers. Booster jettison occurs after thrust tail-off as both SRBs separate simultaneously after completing their job of helping accelerate the vehicle to ~1.5 Kilometers per second.

Powered flight continues on the LE-7A engine of the first stage alone. The engine delivers 109,300 Kilograms of thrust, burning about 260 Kilograms of cryogenics per second.

Passing T+4 minutes, H-IIA will reach an altitude of over 130 Kilometers making it safe to jettison the Payload Fairing as aerodynamic forces can no longer harm the spacecraft. Separating the fairing as early as possible increases ascent performance as additional weight is lost at fairing separation.

In a nominal flight scenario, H-IIA's first stage will burn until T+6 minutes and 36 seconds, accelerating the launch vehicle to over 5.0 Kilometers per second. Stage separation occurs eight seconds after cutoff as pyrotechnics cut the connection between stages and springs push the Core Stage away.

The LE-5B engine of the second stage will ignite six seconds after stage separation, delivering 13,970kgf of thrust over a burn of up to 8.5 minutes to deliver the IGS satellite to its target orbit with spacecraft separation occurring prior to T+20 minutes. The target orbit will be circular, around 500 Kilometers in altitude at an inclination of 98 degrees.

che wi

Из-за плохой погоды пуск вроде перенесли на сутки.


che wi

Согласно сегодняшнему пресс-релизу JAXA, пуск перенесён на 1 февраля (10:21 JST / 01:21 UTC / 04:21 MSK)
В зависимости от погодных условий, может быть сдвинут ещё дальше.

http://www.jaxa.jp/press/2015/01/20150129_h2af27_2_j.html