Author Topic: Epsilon launch - SPRINT-A, Sept.14, 2013 (0500UTC)  (Read 136156 times)

Offline blister

Re: Epsilon Space Launch Vehicle
« Reply #80 on: 07/12/2013 12:36 pm »
Epsiron and SPRINT-A special site.
http://fanfun.jaxa.jp/countdown/epsilon/index.html

Offline Prober

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Re: Epsilon Space Launch Vehicle
« Reply #81 on: 07/12/2013 04:26 pm »
Epsiron and SPRINT-A special site.
http://fanfun.jaxa.jp/countdown/epsilon/index.html

JAXA is broadcast live via the Internet from the Uchinoura Space Center planetary spectroscopy observation of the Epsilon launch vehicle ( SPRINT-A launch of the. Recruit school, street vision, Science Museum offers delivery company will deliver this footage, such as Internet, cell phones and smart phones, tablet computers, will broadcast stations including CS, CATV, IP broadcasters and public viewing. Together, support the "Epsilon" mission! Also due to the special site open to recruitment by the Twitter messages of support we have started. Is the hashtag "# Epsilon cheer" is. I look forward to supporting messages for Epsilon rocket / planetary spectroscopy observation satellite project team to launch.
 
2017 - Everything Old is New Again.
"I fear all we have done is to awaken a sleeping giant..." --Isoroku Yamamoto

Offline blister

Re: Epsilon Space Launch Vehicle
« Reply #82 on: 07/12/2013 05:25 pm »
Epsiron seeing guide by NVS.
 http://blog.nvs-live.com/?eid=125

Offline blister

Re: Epsilon Space Launch Vehicle
« Reply #83 on: 07/12/2013 05:55 pm »
Epsilon's twitter hash tag is # Epsilon cheer in Japanese.That is # epsilon(katakana)Ouen(Chinese character)
Should you copy and paste to send message.Japanese hash tag is no good.


Offline blister

Re: Epsilon Space Launch Vehicle
« Reply #85 on: 07/19/2013 05:40 pm »
Sprint A infomation session.
July 20,1330JST webcast
start by NVS.
http://blog.nvs-live.com/?eid=128

Offline jcm

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Re: Epsilon Space Launch Vehicle
« Reply #86 on: 08/02/2013 08:08 pm »
SPRINT-A launch press kit, I think: (In Japanese..)

 

http://www.jaxa.jp/press/2013/05/20130521_epsilon.pdf
-----------------------------

Jonathan McDowell
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Offline jcm

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Re: Epsilon Space Launch Vehicle
« Reply #87 on: 08/02/2013 08:54 pm »
Here's what I have gleaned from the press kit:
The Episilon rocket (Ipushironroketto, イプシロンロケット )
consists of the SRB-A3 with M-34c and KM-V2b
stages and a hydrazine PBS (Post-boost stage),
called
小型液体推進系
(Kogata ekitai suishin-kei, small liquid propulsion system)
in Japanese.

Rocket mission:  Epsilon rocket test No. 1  (ipushironroketto shiken-ki 1-ki)
イプシロンロケット試験機 1機
or ε-1
Satellite:  Planet spectroscopic observation satellite No. 1, Wakusei bunko kansuko eisei 1-ki
惑星分光観測衛星 1基) 284s.
Mass 340 kg. Size: Box + 2 wings, 4 x 1 x 1 m (6m span across solar arrays).
Design life 1 year.
Orbit 106 min, 950 x 1150 km x 31 deg.

The launch profile is

Time  Range  Alt   V-inertial (km/s)
T+0:00   0   0     0   Launch on 112 deg azimuth.
T+1:52  70  88   2.6  Stage 1 burnout
T+2:30 131 147   2.4  Fairing sep
T+2:41 148 162   2.4  Stage 1 sep
T+2:45 154 167   2.4  Stage 2 ignition
T+4:27 415 323   5.1  Stage 2 burnout
T+10:24 1658 822  4.2 Stage 2 sep
T+10:28 1671 823  4.2 Stage 3 ignition
T+11:57 2061 840  7.5 Stage 3 burnout
T+16:48 3846 864  7.4 Stage 3 sep
T+19:08 5943 896  7.4 PBS burn 1
T+29:58 7447 921  7.4 PBS cutoff 1
T+53:50 17431 1143 7.2 PBS burn 2
T+60:30 19020 1154 7.2 PBS cutoff 2
T+61:40 19722 1151 7.2 PBS/SPRINT-A separation




The ground track shows the first PBS burn begns over the N Pacfic at 170W 20N
and the second one just off the coast of Chile, with spacecraft
sep over the northeast coast of Argentina.

Stage 1 is 11.7m long 2.6m dia, with a mass of 75.0t (66.3t prop) thrust 2271N vac,
burn time 116s, Isp(v) 284s.
Stage 2 is 4.3m long (with nozzle extended), 2.2m dia, 12.3t (10.8t prop), 371.5kN, 105s burn, Isp 300s.
Stage 3 is 2.3m long (with nozzle extended), 1.4m dia, 3.3t (2.5t prop), 99.8 kN, 90s burn, Isp 301s.
PBS is 1.2m long 1.5m dia, 0.1t (0.1t prop), 0.4 kN, 1100s max burn time, Isp 215s.
Fairing is 11.1m long 2.6m dia, 1.0t mass.
 
 ---

While one may conclude the PBS empty mass is less than 100 kg,
it would be nice to know what it is (for space debris purposes).

The second stage impact zone appears to be centered at around 170E 25N.
It appears that both the third stage and the PBS will reach orbit, with the PBS
used for minor orbit adjustments.
« Last Edit: 08/02/2013 08:55 pm by jcm »
-----------------------------

Jonathan McDowell
http://planet4589.org

Offline yoichi

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Re: Epsilon Space Launch Vehicle
« Reply #88 on: 08/08/2013 07:43 am »
http://www.jaxa.jp/press/2013/08/20130808_epsilon_e.html

Launch Postponement and Launch Time Change  for Epsilon Launch Vehicle  with SPRINT-A onboard

Scheduled launch day: August 27 (Tue.) 2013
Scheduled launch time window: 1:45 thru 2:30 p.m.
Launch window: between Aug. 28 (Wed.) thru Sept. 30 (Mon.), 2013
« Last Edit: 08/08/2013 07:44 am by yoichi »

Offline fatjohn1408

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Re: Epsilon Space Launch Vehicle
« Reply #89 on: 08/08/2013 09:01 am »
Here's what I have gleaned from the press kit:
The Episilon rocket (Ipushironroketto, イプシロンロケット )
consists of the SRB-A3 with M-34c and KM-V2b
stages and a hydrazine PBS (Post-boost stage),
called
小型液体推進系
(Kogata ekitai suishin-kei, small liquid propulsion system)
in Japanese.

Rocket mission:  Epsilon rocket test No. 1  (ipushironroketto shiken-ki 1-ki)
イプシロンロケット試験機 1機
or ε-1
Satellite:  Planet spectroscopic observation satellite No. 1, Wakusei bunko kansuko eisei 1-ki
惑星分光観測衛星 1基) 284s.
Mass 340 kg. Size: Box + 2 wings, 4 x 1 x 1 m (6m span across solar arrays).
Design life 1 year.
Orbit 106 min, 950 x 1150 km x 31 deg.

The launch profile is

Time  Range  Alt   V-inertial (km/s)
T+0:00   0   0     0   Launch on 112 deg azimuth.
T+1:52  70  88   2.6  Stage 1 burnout
T+2:30 131 147   2.4  Fairing sep
T+2:41 148 162   2.4  Stage 1 sep
T+2:45 154 167   2.4  Stage 2 ignition
T+4:27 415 323   5.1  Stage 2 burnout
T+10:24 1658 822  4.2 Stage 2 sep
T+10:28 1671 823  4.2 Stage 3 ignition
T+11:57 2061 840  7.5 Stage 3 burnout
T+16:48 3846 864  7.4 Stage 3 sep
T+19:08 5943 896  7.4 PBS burn 1
T+29:58 7447 921  7.4 PBS cutoff 1
T+53:50 17431 1143 7.2 PBS burn 2
T+60:30 19020 1154 7.2 PBS cutoff 2
T+61:40 19722 1151 7.2 PBS/SPRINT-A separation




The ground track shows the first PBS burn begns over the N Pacfic at 170W 20N
and the second one just off the coast of Chile, with spacecraft
sep over the northeast coast of Argentina.

Stage 1 is 11.7m long 2.6m dia, with a mass of 75.0t (66.3t prop) thrust 2271N vac,
burn time 116s, Isp(v) 284s.
Stage 2 is 4.3m long (with nozzle extended), 2.2m dia, 12.3t (10.8t prop), 371.5kN, 105s burn, Isp 300s.
Stage 3 is 2.3m long (with nozzle extended), 1.4m dia, 3.3t (2.5t prop), 99.8 kN, 90s burn, Isp 301s.
PBS is 1.2m long 1.5m dia, 0.1t (0.1t prop), 0.4 kN, 1100s max burn time, Isp 215s.
Fairing is 11.1m long 2.6m dia, 1.0t mass.
 
 ---

While one may conclude the PBS empty mass is less than 100 kg,
it would be nice to know what it is (for space debris purposes).

The second stage impact zone appears to be centered at around 170E 25N.
It appears that both the third stage and the PBS will reach orbit, with the PBS
used for minor orbit adjustments.


It's not really inertial speed when your reference frame is the Earth rotating reference frame right. Hope they only mixed it up in the document and not in their code :)

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Offline jcm

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Re: Epsilon Space Launch Vehicle
« Reply #91 on: 08/08/2013 10:35 pm »
Here's what I have gleaned from the press kit:
The Episilon rocket (Ipushironroketto, イプシロンロケット )
consists of the SRB-A3 with M-34c and KM-V2b
stages and a hydrazine PBS (Post-boost stage),
called
小型液体推進系
(Kogata ekitai suishin-kei, small liquid propulsion system)
in Japanese.

Rocket mission:  Epsilon rocket test No. 1  (ipushironroketto shiken-ki 1-ki)
イプシロンロケット試験機 1機
or ε-1
Satellite:  Planet spectroscopic observation satellite No. 1, Wakusei bunko kansuko eisei 1-ki
惑星分光観測衛星 1基) 284s.
Mass 340 kg. Size: Box + 2 wings, 4 x 1 x 1 m (6m span across solar arrays).
Design life 1 year.
Orbit 106 min, 950 x 1150 km x 31 deg.

The launch profile is

Time  Range  Alt   V-inertial (km/s)
T+0:00   0   0     0   Launch on 112 deg azimuth.
T+1:52  70  88   2.6  Stage 1 burnout
T+2:30 131 147   2.4  Fairing sep
T+2:41 148 162   2.4  Stage 1 sep
T+2:45 154 167   2.4  Stage 2 ignition
T+4:27 415 323   5.1  Stage 2 burnout
T+10:24 1658 822  4.2 Stage 2 sep
T+10:28 1671 823  4.2 Stage 3 ignition
T+11:57 2061 840  7.5 Stage 3 burnout
T+16:48 3846 864  7.4 Stage 3 sep
T+19:08 5943 896  7.4 PBS burn 1
T+29:58 7447 921  7.4 PBS cutoff 1
T+53:50 17431 1143 7.2 PBS burn 2
T+60:30 19020 1154 7.2 PBS cutoff 2
T+61:40 19722 1151 7.2 PBS/SPRINT-A separation




The ground track shows the first PBS burn begns over the N Pacfic at 170W 20N
and the second one just off the coast of Chile, with spacecraft
sep over the northeast coast of Argentina.

Stage 1 is 11.7m long 2.6m dia, with a mass of 75.0t (66.3t prop) thrust 2271N vac,
burn time 116s, Isp(v) 284s.
Stage 2 is 4.3m long (with nozzle extended), 2.2m dia, 12.3t (10.8t prop), 371.5kN, 105s burn, Isp 300s.
Stage 3 is 2.3m long (with nozzle extended), 1.4m dia, 3.3t (2.5t prop), 99.8 kN, 90s burn, Isp 301s.
PBS is 1.2m long 1.5m dia, 0.1t (0.1t prop), 0.4 kN, 1100s max burn time, Isp 215s.
Fairing is 11.1m long 2.6m dia, 1.0t mass.
 
 ---

While one may conclude the PBS empty mass is less than 100 kg,
it would be nice to know what it is (for space debris purposes).

The second stage impact zone appears to be centered at around 170E 25N.
It appears that both the third stage and the PBS will reach orbit, with the PBS
used for minor orbit adjustments.


It's not really inertial speed when your reference frame is the Earth rotating reference frame right. Hope they only mixed it up in the document and not in their code :)

Hmm - based on the later values I think they are indeed using inertial, not Earth rotating. But then the 0 value for launch is wrong, should be 0.34 or so...
good point.
-----------------------------

Jonathan McDowell
http://planet4589.org

Offline yoichi

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Re: Epsilon launch with SPRINT-A, August 27 2013 (ETD 0445UTC)
« Reply #92 on: 08/20/2013 05:48 am »
Launch rehersal photo and movie.

http://www.ustream.tv/recorded/37550009
« Last Edit: 08/20/2013 08:12 am by yoichi »

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Re: Epsilon launch with SPRINT-A, August 27 2013 (ETD 0445UTC)
« Reply #93 on: 08/20/2013 08:13 pm »
Epsilon Launch Vehicle/SPRINT-A Special Site

http://www.jaxa.jp/countdown/epsilon/index_e.html

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Offline yoichi

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Re: Epsilon launch with SPRINT-A, August 27 2013 (ETD 0445UTC)
« Reply #95 on: 08/21/2013 09:47 am »
« Last Edit: 08/21/2013 11:19 am by yoichi »


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Re: Epsilon launch with SPRINT-A, August 27 2013 (ETD 0445UTC)
« Reply #98 on: 08/24/2013 02:19 pm »
A3545/13 -  QRDCA THE JAPANESE SPACE EXPLORATION AGENCY (JAXA) HAS PLANNED A  ROCKET LAUNCH. DEBRIS FROM THIS LAUNCH WILL FALL WITHIN AN AREA BOUNDED BY  2345N/16730E 2645N/16736E 2635N/17221E 2335N/17215E BACK TO THE POINT OF ORIGIN.  IN THE INTEREST OF SAFETY ALL NON-PARTICIPATING AIR  TRAFFIC ARE ADVISED TO AVOID THE NOTAMED AREA.  IFR AIRCRAFT UNDER  ATC JURISDICTION SHOULD ANTICIPATE CLEARANCE AROUND THE NOTAMED AREA. SFC - UNL, 0430-0530Z DAILY, 27 AUG 04:30 2013 UNTIL 29 AUG 05:30 2013. CREATED: 23 AUG 18:56 2013

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Re: Epsilon launch with SPRINT-A, August 27 2013 (ETD 0445UTC)
« Reply #99 on: 08/24/2013 03:03 pm »
HYDROPAC   2507/2013(19,81,97).    (221156Z AUG 2013)
WESTERN NORTH PACIFIC.
ROCKETS.
1. HAZARDOUS OPERATIONS:
   A. 270454Z TO 270555Z AUG IN AREA BOUND BY
      30-36-00N 137-53-00E, 30-55-13N 138-51-18E,
      30-53-52N 139-04-49E, 29-53-00N 139-26-00E,
      29-29-00N 138-16-00E.
   B. 270504Z TO 270607Z AUG IN AREA BOUND BY
      26-45-00N 167-36-00E, 26-35-00N 172-21-00E,
      23-35-00N 172-15-00E, 23-45-00N 167-30-00E.
2. CANCEL HYDROPAC 2503/13(71).
3. CANCEL THIS MSG 270707Z AUG 13.
« Last Edit: 08/26/2013 11:28 am by input~2 »

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