Orbiter-Forum http://www.orbiter-forum.com/ Orbiter and Space Flight Discussion Board en Thu, 17 May 2012 23:06:34 GMT vBulletin 60 http://orbiter-forum.com/images/misc/rss.jpg Orbiter-Forum http://www.orbiter-forum.com/ I will like again a long time this voice - Donna Summer http://www.orbiter-forum.com/showthread.php?t=27550&goto=newpost Thu, 17 May 2012 21:04:10 GMT rest in peace. Donna Summer dies at 63 http://www.bbc.co.uk/news/entertainment-arts-18109654 Donna Summer - On The Radio (1979) .wmv ... rest in peace.

Donna Summer dies at 63

http://www.bbc.co.uk/news/entertainment-arts-18109654

]]> Brighton Lounge fort http://www.orbiter-forum.com/showthread.php?t=27550 Launch News Nimiq 6, Proton-M/Briz-M, May 17/18, 2012 http://www.orbiter-forum.com/showthread.php?t=27549&goto=newpost Thu, 17 May 2012 13:42:35 GMT Image: http://www.ilslaunch.com/sites/default/files/images/NIMIQ6-drupal.jpg Image:...







The third launch of today will see yet another run-of-the-mill Proton launch mission to deliver another communication satellite to orbit. Today's passenger is Nimiq 6, a direct TV broadcasting satellite for Telesat of Canada.

Nimiq 6 is an all Ku-band satellite with 32 high power transponders. It will be located at 91 degrees West Longitude, where it will provide HDTV and advanced video services for Bell TV’s subscriber base. The satellite is based on SS/L’s high power LS-1300 spacecraft bus which provides the flexibility for a broad range of applications. It has a planned mission life of 15 years.

Launch location:

Baikonur Baikonur Launch pad no. 81/24 46°4'15.38"N, 62°59'5.11"E



Launch dates and times:

Launch times
Time Zone
Australia - Sydney/UTC+11
Baikonur / UTC+6
Moscow / UTC+4/
Universal / UTC
Ottawa / EDT
Launch time (Primary):
06:12:14
01:12:14
23:12:14
19:12:14
15:12:14
on:
May. 18, 2012
May. 18, 2012
May. 17, 2012
May. 17, 2012
May. 17, 2012
*Click here to restart the timer* Nimiq 6 launch
*Click here to restart the timer* Yahsat 1B Separation From the Launch Vehicle

Live Coverage Of The Launch:

PAYLOAD

Nimiq 6 is a direct broadcasting communications satellite serving Canada and the US.

Nimiq 6 is a Direct Broadcast Service (DBS) satellite being built for Telesat, one of the world’s leading satellite operators. Nimiq 6 is fully leased to Bell TV and will provide Direct-to-Home television service in Canada, including HDTV channels and other video content for Bell TV’s growing subscriber base. An all Ku-band satellite with 32 high-power transponders, Nimiq 6 will utilize SS/L’s flight-proven 1300 spacecraft bus and be located at 91 degrees West longitude. The satellite is scheduled for launch in 2012.



Mission Summary

Summary
ParameterValue
Working Orbit:
GEO
Orbital Location:
91° West
Coverage:
Canada, Northern US
Orbit after separation from the launcher:
12073 x 35786 km, Inc 10.2°

Coverage Maps



Characteristics
Nimiq 6
Customer:
  • Telesat Canada
Prime contractor:
  • Space Systems/Loral
Platform:
  • LS-1300
Mass at Separation:
  • 4745 kg
Dry Mass:
  • ?
Dimensions (stowed):
  • ?
Payload:
  • Ku band: 32 transponders
Life time:
  • 15 years



Launch Vehicle:

Characteristics
Proton-M / Briz-M
Prime contractor:
  • Khrunichev Space Centre
GRAU Index:
  • 8K82KM
Height:
 58.2 m with upper stage and payload fairing
Diameter:
 max 7.4 m
Liftoff mass:
 705 metric tonnes
Payload mass:
 ~22 tonnes at LEO
1st stage:
  • 6 X RD-275 engines
  • Empty 30.6 tonnes
  • Propellants 419.41 tonnes (UDMH and NTO)
  • Thrust in vacuum 1069.8 tonnes of force
  • Thrust at sea level 971.4 tonnes of force
2nd stage:
  • 1 X RD-0211 engine 3 X RD-0210 engines
  • Empty 11.4 tonnes
  • Propellants 156.113 tonnes (UDMH and NTO)
  • Thrust in vacuum 237.4 tonnes of force
3rd stage:
  • 1 X RD-0213 engine & 1 X RD-0214 vernier engine
  • Empty 3.7 tonnes
  • Propellants 46.562 tonnes (UDMH and NTO)
  • Thrust in vacuum 59.36 (core) + 3.15 (vernier) tonnes of force
Upper Stage:
  • GRAU Index: 14S43
  • Common Name: Briz-M
  • Designer & Manufacturer: Khrunichev Space Centre
  • Dimensions: Length 2.654 m, Diameter 4 m
  • Empty Mass 2.2 tonnes
  • Propellants 6 660 kg UDMH + 13 260 kg N2O4
  • Flight time: no less than 24 hours
  • Main Engine: 1 X 14D30
  • Thrust in vacuum 2.0 tonnes of force
  • ISP 328.6 s
  • Main engine restarts: up to 8 times
  • Precision Manoeuvering Engines: 4 X 11D458
  • Thrust in vacuum 400 N each
  • ISP 252 s
  • RCS Engines: 12 X 17D58E
  • Thrust in vacuum 13.3 N each
  • ISP 274 s
Payload Fairing:
  • Diameter 4.35 m
  • Length 11.6 m

The vehicle's reliability statistics according to http://www.spacelaunchreport.com/log2011.html#rate:

Code:
================================================================
Vehicle    Successes/Tries Realzd Pred  Consc. Last    Dates   
                            Rate  Rate* Succes Fail   
================================================================
Proton-M/Briz-M  51    55    .93  .91      9    08/17/11 2001-
Nimiq 6 Ascent Timeline

EventTime rel lift-offTime MoscowTime UTCComment
Lift-off00:00:0023:12:1419:12:14 
1st/2nd Stage Separation00:02:0023:14:1419:14:14 
2nd/3rd Stage Separation00:05:2723:17:4119:17:41 
Payload Fairing Separation00:05:4823:18:0219:18:02 
3rd Stage/Breeze M Separation00:09:4223:21:5619:21:56 
1st Burn Ignition00:11:1623:23:3019:23:30 
1st Burn Shutdown00:15:4223:27:5619:27:561st Burn's Duration 00:04:26
2nd Burn Ignition01:07:3000:19:4420:19:44 
2nd Burn Shutdown01:25:1600:37:3020:37:302nd Burn's Duration 00:17:46
3rd Burn Ignition03:28:4402:40:5822:40:58 
3rd Burn Shutdown03:44:1402:56:2822:56:283rd Burn's Duration 00:15:30
APT Jettison03:45:0402:57:1822:57:18 
4th Burn Ignition03:46:3102:58:4522:58:45 
4th Burn Shutdown03:48:4203:00:5623:00:564th Burn's Duration 00:02:11
5th Burn Ignition08:50:5008:03:0404:03:04 
5th Burn Shutdown09:00:4608:13:0004:13:005th Burn's Duration 00:09:56
Separation of Nimiq 609:14:0008:26:1404:26:14in GTO









Weather forecast for Baikonur, Kazakhstan on May 18, 2012 (1 a.m.)

TimeTempsWind ChillHeat IndexUV IndexDew PointRelative HumidityPrecipSnowCloudsVisibilityWindWeather
4 AM12°C12°C12°C0 Low7°C69%0%0%0%16KMW 5 mph Clear 

Sunrise and Sunset times for the location of launch

Times are local.
EventTime
Astronomical twilight begins03:53
Nautical twilight begins04:49
Civil twilight begins05:35
Sunrise06:09
Transit (sun is at its highest)13:44
Sunset21:19
Civil twilight ends21:53
Nautical twilight ends22:39
Astronomical twilight ends23:35


References
http://www.federalspace.ru
http://tvroscosmos.ru
http://www.tsenki.com/launch_service...011/?EID=88633
http://www.khrunichev.ru
http://tihiy.fromru.com/Rn/RN_Proton.htm
http://www.space-center.ru/ApriEvents.aspx
http://www.ssloral.com/html/satexp/nimiq6.html
http://www.telesat.com/
http://forum.nasaspaceflight.com
http://www.novosti-kosmonavtiki.ru
http://www.spacelaunchreport.com
http://www.intellicast.com/Local/Forecast.aspx
http://www.good-stuff.co.uk/suntimes/sunmap.php
 ]]> Spaceflight News Galactic Penguin SST http://www.orbiter-forum.com/showthread.php?t=27549 Launch News Cobalt-M (Cosmos-2480) atop Soyuz-U on May 17, 2012 http://www.orbiter-forum.com/showthread.php?t=27547&goto=newpost Thu, 17 May 2012 13:05:21 GMT With the good lighting conditions setting in the Northern Hemisphere, we now have another strategic optical survelliance Russian sat launched. ... With the good lighting conditions setting in the Northern Hemisphere, we now have another strategic optical survelliance Russian sat launched.

Cosmos-2480 is expected to be the formal designation for Cobalt-M spacecraft to be launched today by Russian Space Force. Cobalt-M is an optical survelliance satellite which uses film camera and return capsule to deliver the shot footage to the ground at the end of its mission, which can last for several months and include several alterations of its orbit.





Launch location:

Plesetsk Launch pad no. 16/2 62°57'35.83"N, 40°40'56.22"E

Launch dates and times:

Launch times
Time Zone
Australia - Sydney/AEST
Hong Kong / HKT, UTC+8/
Moscow Summer / MSK, UTC+4/
Universal / UTC
Washington / EDT
Launch time (Primary):
12:05:00 a.m.
10:05:00 p.m.
18:05:00
14:05:00
10:05:00 a.m.
on:
May 18, 2012
May 17, 2012
May 17, 2012
May 17, 2012
May 17, 2012
*Click here to restart the timer* Cosmos-2480 Launch

Live Coverage Of The Launch:

None, sorry.

PAYLOAD

Cobalt-M photo film-returning reconnaissnace satellite

Characteristics
Cobalt-M (AKA Yantar-4K2M, Yantar means Amber)
Picture:
GRAU Index:
  • 11F695U
Customer:
  • Russian MoD.
Prime contractor:
  • PLC Arsenal Machine Building Plant, St. Petersburg
Platform:
  • Yantar-M (?)
Mass at Separation:
  • 6600 kg
Dry Mass:
  • ?
Stabilization:
  • 3 axis stabilized
Dimensions:
  • ?
Batteries:
  • ?
Mission time:
  • 60 to 120 days
Typical initial orbit:
  • 170 x 330 km, 62.8°-67.2° inclination
Survelliance Payload:
Film Camera with 300-mm lens produced by Lytkarino Factory of Optical Systems
Data Returning:
Two ball-shaped strap-on film return capsules plus the main reentry vehicle used to deliver back the camera and the main load of film.

Mission Profile:

Inclination for this launch is expected to be 82°, initial orbit is about 185 * 250 km.

Launch Vehicle:

Characteristics
Soyuz-U
Prime contractor:
  • Samara Space Sentre (Energia Holding enterprise)
GRAU Index:
  • 11A511U
Height:
 51.1 m
Diameter:
 max 10.3 m
Liftoff mass:
 313 metric tonnes
Payload mass:
 6.95 tonnes at ISS orbit from Baikonur
1st stage (boosters B, V, G, D):
  • 4 X RD-117 engines
  • Propellants (T-1 Kerosene and LOX)
  • Thrust/ISP in vacuum - / 316 s
  • Thrust/ISP at sea level 79.4 tonnes / 253 s
  • Total 1st stage's thrust at sea level: 411.1 tonnes
2nd stage (core A):
  • 1 X RD-118 engine
  • Propellants (T-1 Kerosene and LOX)
  • Thrust/ISP in vacuum 102 tonnes / 314 s
  • Thrust/ISP at sea level 83.5 tonnes / 257 s
3rd stage (block I):
  • 1 X RD-0110 engine
  • Propellants (T-1 Kerosene and LOX)
  • Thrust/ISP in vacuum 30.38 tonnes / 359 s

Launch Complex:

The launch will be performed off LC 2 at site 16.


Weather forecast for Plesetsk, Russia on May 17, 2012 (6 p.m.)

TimeTempsWindChillHeat IndexUV IndexDew PointRelative HumidityPrecipSnowCloudsVisibilityWindWeather
6 PM25°C25°C25°C1Low10°C40%10%0%29%16KMSSE 3.6 m/s M Sunny

Sunrise/Sunset and associated twilight times for Plesetsk on Thursday, May 17, 2012

Times are local.
EventTime
Astronomical twilight beginsNever
Nautical twilight beginsNever
Civil twilight begins2:39
Sunrise4:05
Transit (sun is at its highest)13:14
Sunset0:24
Civil twilight ends1:50
Nautical twilight endsNever
Astronomical twilight endsNever


References
http://forum.nasaspaceflight.com
http://www.novosti-kosmonavtiki.ru
http://www.russianspaceweb.com
www.svengrahn.pp.se
http://www.planet4589.org
http://www.samspace.ru
http://www.npoenergomash.ru/engines/
http://intellicast.com
http://www.good-stuff.co.uk/suntimes/sunmap.php
http://www.intellicast.com/Local/Forecast.aspx
http://www.good-stuff.co.uk/suntimes/sunmap.php
 ]]> Spaceflight News SiberianTiger http://www.orbiter-forum.com/showthread.php?t=27547 <![CDATA[Launch News GCOM-W1 "Shizuku" and 3 other satellites, H-IIA, May 17/18, 2012]]> http://www.orbiter-forum.com/showthread.php?t=27546&goto=newpost Thu, 17 May 2012 12:52:26 GMT A joint Japanese-American satellite to observe the Earth's water cycle in unprecedented detail, a Korean optical satellite and 2 nano-satellites for Japanese institutions will be launched today on the H-IIA rocket from Tanegashima Island on the southern tip of Japan.











Launch window:16:39-16:42 UTC / 12:39-12:42 p.m. EDT / 01:39-01:42 JST
Launch site:Pad 1, Yoshinobu Launch Complex, Tanegashima Space Center, Japan
L*Click here to restart the timer*

There is an O-F's calendar event created for this launch, for which you can request a reminder, that will be sent via e-mail on set time before the launch.



Payload 1:The Global Change Observation Mission - Water (GCOM-W) satellite aims to construct, use, and verify systems that enable continuous global-scale observations (for 10 to 15 years) of effective geophysical parameters for elucidating global climate change and water circulation mechanisms. Water circulation changes will be observed by a microwave radiometer onboard the GCOM-W (Water) satellite (scheduled to be launched in Japan Fiscal Year 2011). The GCOM-W will observe precipitation, vapor amounts, wind velocity above the ocean, sea water temperatures, water levels on land areas and snow depths. Climate change observation will be performed by a multi-wavelength optical radiometer onboard the GCOM-C (Climate) satellite (under consideration) on clouds, aerosol, seawater color (marine organisms), vegetation, snow and ice. These satellites will enable us to perform comprehensive observations of the surface layer of the Earth such as the atmosphere, including clouds, land, oceans and the cryosphere.

The Advanced Microwave Scanning Radiometer 2 (AMSR2) is a sensor to observe radiometers, or microwaves emitted naturally from the ground, sea surface and atmosphere, using 6 different frequency bands ranging from 7 GHz to 89 GHz. The strength of a natural microwave is determined by its characteristics and moisture, including the surface condition and temperature of the material. Although it depends on the frequency, the microwave is very weak. AMSR2 will detect such weak microwaves at an altitude of 700 kilometers and measure the strength of them with a very high accuracy. For example, by measuring the strength of a microwave emitted from the sea surface with the AMSR2, we can understand the water temperature of the sea surface to an accuracy of 0.5 degrees Celsius. The antenna of the AMSR2, which receives microwaves from the ground, arc scans the ground surface at a ratio of one turn every 1.5 seconds and observes an area approximately 1,450 kilometers wide in one scan. Using this scanning method, the AMSR2 can observe over 99 percent of the Earth's area in just 2 days. The diameter of the antenna is about 2 meters, making it the world's largest observation sensor aboard a satellite. The height of the rotating part is about 2.7 meters and the weight is about 250 kilograms. The AMSR2 can keep rotating such a large and heavy antenna at a speed of one turn per 1.5 seconds for 24 hours a day and more than five years without a minute of rest.

The nickname "SHIZUKU (meaning a "drop" or "dew")" has been selected as a result of a naming contest. We asked the public to christen the satellite through the Internet and conventional mail service between July 1 and Aug. 31, 2011. Among the suggestions from a total of 20,998, some 1,392 people proposed "Shizuku."
Some typical reasoning for picking "Shizuku" was that the satellite will observe water circulation, which originated from a "drop" of water that becomes rain, then runs into the ocean, and ultimately evaporates in the air as vapor or becomes ice. Some explained that they would also like the satellite to observe each drop of water carefully. Those descriptions precisely illustrate the GCOM-W1 mission.

Characteristics
Mass:
  • 1900kg
Power:
  • 4.05 kW
Lifetime:
  • 5 years
Orbit:
  • 700 km Sun-synchronous orbit
Inclination:
  • 98.2 degrees





Payload 2:KOMPSat 3 (Korean Multi-purpose Satellite 3) is a lightweight Earth observation satellite developed by the Korea Aerospace Research Institute KARI. It will be similar to the KOMPSat 2 spacecraft and is scheduled to be launched in 2012. The optical component is being developed by Astrium.

It will operate at an altitude of 685 km in a sun-synchronous orbit for 4 years and monitor the Korean peninsula using a payload capable of submeter class resolution. The mission objectives of the KOMPSAT-3 are to provide continuous satellite Earth observation after KOMPSat 1 and KOMPSat 2 and to meet the nation's needs for high-resolution EO (Electro-Optical) images required for GIS (Geographical Information Systems) and other environmental, agricultural and oceanographic monitoring applications.

Characteristics
Mass:
  • 800kg
Lifetime:
  • 4 years
Orbit:
  • 700 km Sun-synchronous orbit
Inclination:
  • 98.2 degrees



Payload 3:SDS 4 (Small Demonstration Satellite 4) is a small technology experiment satellite developed by JAXA.

As with SDS-1, this small satellite (a cube of 50 kg and 50 cm edge, with a 120 W power available) will test several promising technologies. Unlike the SDS-1 satellite attitude SDS-4 can be controlled on its 3-axis pointing toward the Sun in normal operation phase and to Earth at nadir during his experimental phase. SDS-4 will be launched in 2012 with the GCOM-W1 satellite, and placed on a sun-synchronous orbit at 677 km altitude.

SDS-4 will carry four technology validation missions:

FOX (FHP On-orbit Experiment) will validate the new orbit flat heat pipes for future thermal control systems for satellites.
IST (In-flight experiment of Space Materials using THERME) characterize the degradation of thermal control materials, using the component THERME provided by the French space agency.
QCM (Quartz Crystal Microbalance) will characterize a quartz microbalance developed by the scientific division of JAXA (ISAS), a component that will be useful to develop future sensors that will measure internal contamination.
SPAISE (Space-based Automatic Identification System Experiment), an experiment of receiving signals AIS (Automatic Identification System) from ships, with two dedicated antennas.

Characteristics
Mass:
  • 50kg
Power:
  • 120 W
Orbit:
  • 677 km Sun-synchronous orbit
Inclination:
  • 98.2 degrees



Payload 4:Horyu 2 is a small technological satellite built by Kyusyu Institute of Technology.

Horyu 2 will testing an experimental high-voltage solar array system and observing corresponding spacecraft charging effects on the satellite caused by the high voltage.

Missions:

- Power generation of 300 V in low orbit
- Demonstrating the deterioration of electric discharge control film
- On-orbit demonstration of electron-emitting film (ELF elements) for mitigating electric charging
- On-orbit verification of satellite surface potential meter that was developed based on terrestrial commercial technology
- Debris observation by debris censor
- On-orbit demonstration of the Surrey Camera Payload (SCAMP)
- Taking images by camera for regional contribution and providing educational materials for human resource development using satellite data




Launch Vehicle:
The 21st flight of the H-IIA Launch Vehicle (H-IIA F21) is an "H2A202" type with two solid rocket boosters (SRB-As) attached. The4/4D-LC (4 m in diameter) type fairing is applied.





The launch vehicle is slated for injecting its main payloads "SHIZUKU" and "KOMPSAT-3" in their scheduled orbit. Also it will carry two more small co-payloads to orbit using extra launch capability. After inserting its payloads into their respective orbits, the H-IIA F21 will further perform second stage flight experiments for acquiring technological data of its propellant system in order to upgrade our mainstay rocket as part of our efforts to continuously improving the H-IIA.
Also in this flight experiment, we will test the effectiveness of vapor reduction by coating the second stage liquid hydrogen tank outer surface with white paint, and acquire technological data on the second stage engine precooling status.
Live coverage of the launch:
  • JAXA webcast.
    Live Broadcast of the launch is scheduled to start on May 17/18 at 12:10 p.m. EDT / 16:10 UTC / 1:10 a.m. JST - i.e. it *Click here to restart the timer* hours*Click here to restart the timer*
  • Countdown Report - Final countdown status of H-IIA Flight F21 will be reported there.

Links:

Launch Sequence:
EventTime [mm:ss]Altitude [km]Inertial speed [km/s]
1.
Liftoff
0:00
0
0.4
2.
Solid rocket booster burnout*
1:55
51
1.5
3.
Solid rocket booster jettison**
2:05
59
1.5
4.
Payload fairing jettison
4:10
148
1.9
5.
1st stage engine (main engine) cutoff (MECO)
6:36
301
3.6
6.
1st and 2nd stages separation
6:44
313
3.6
7.
2nd stage ignition (SEIG)
6:50
322
3.5
8.
2nd stage engine cutoff (SECO)
15:26
676
7.5
9.
KOMPSAT-3 separation
16:16
676
7.5
10.
Lower fairing adapter separation
19:21
679
7.5
11.
Lower fairing cylinder separation
19:26
679
7.5
12.
Shizuku separation
23:11
683
7.5
13.
SDS-4 separation
33:20
696
7.5
14.
Horyu-2 separation
50:00
692
7.5

*) When the maximum combustion pressure reaches 2%
**) Thrust strut cutoff


[center]The current view on Tanegashima Space Center (webcam). *

* This picture is automatically updated at intervals.
You need to reload the page to see the latest image. ]]> Spaceflight News Galactic Penguin SST http://www.orbiter-forum.com/showthread.php?t=27546 Congratulations to our norwegian members :) http://www.orbiter-forum.com/showthread.php?t=27544&goto=newpost Thu, 17 May 2012 10:40:20 GMT It's today, may 17th, and they have parades in almost any corner of the globe to celebrate it.

Here's a video of one of them:
http://bambuser.com/v/2652295

Later today there will also be one in New York (and other places also)

Congratulations ("gratulerer med dagen") to our norwegian members :tiphat: :cheers:

(From ballard, Seattle, in 2010)
]]> Brighton Lounge JEL http://www.orbiter-forum.com/showthread.php?t=27544 Fuel For Black Holes http://www.orbiter-forum.com/showthread.php?t=27541&goto=newpost Thu, 17 May 2012 03:58:53 GMT *Fuel For Black Holes* (http://spaceref.com/astronomy/black-holes/fuel-for-black-holes.html) - SpaceRef ---Quote--- An international research... Fuel For Black Holes - SpaceRef
Quote:
An international research team led by Gerd Weigelt from the Max-Planck-Institut fuer Radioastronomie in Bonn reports on high-resolution studies of an active galactic nucleus in the near-infrared. The observations were carried out with the Very Large Telescope Interferometer (VLTI) of the European Southern Observatory (ESO).

The use of near-infrared interferometry allowed the team to resolve a ring-shaped dust distribution (generally called "dust torus") in the inner region of the nucleus of the active galaxy NGC 3783...The resolved dust torus has an angular radius of only 0.7 milliarcseconds on the sky, an angle that is 5 million times smaller than one degree. This angular radius corresponds to a radius of approximately 0.5 light-year for a distance of 130 million light-years.
By my calculations, that is the same as resolving a feature on 3 m across on the Moon :blink: ]]> tblaxland http://www.orbiter-forum.com/showthread.php?t=27541 Flight Question XR5 Take-Off http://www.orbiter-forum.com/showthread.php?t=27540&goto=newpost Wed, 16 May 2012 18:17:35 GMT Every time i try to take off in the XR5, either i come crashing down to earth, or the runway is too short, any help? Every time i try to take off in the XR5, either i come crashing down to earth, or the runway is too short, any help? ]]> KuatYards http://www.orbiter-forum.com/showthread.php?t=27540 Idea Javascript interface http://www.orbiter-forum.com/showthread.php?t=27536&goto=newpost Wed, 16 May 2012 10:49:26 GMT Well, as asking doesn't hurt, I'd like to be able to read / write some Orbiter vessel variables from Javascript running from a webpage.

As we already have multiplayer implementations, there certainly is a way to get data to and from the simulator.
For example, there's Orb:Connect and is seems to do what I need, but it works with Java, not Javascript/HTML environment.

What would I do with this? Of course nice 2d panels and universal system simulation for any ship does come into mind...


Simple isn't it :thumbup: ? ]]> Addon Requests 4throck http://www.orbiter-forum.com/showthread.php?t=27536 <![CDATA[Science Milestone for wi-fi with 'T-rays']]> http://www.orbiter-forum.com/showthread.php?t=27535&goto=newpost Wed, 16 May 2012 08:38:57 GMT http://www.bbc.co.uk/news/science-environment-18072618 ---Quote--- The band lies between the microwave and far-infrared regions of the... http://www.bbc.co.uk/news/science-environment-18072618

Quote:
The band lies between the microwave and far-infrared regions of the spectrum, and is currently completely unregulated by telecommunications agencies.
Bet that won't last long.

Waiting for Yobba-rays now...

http://en.wikipedia.org/wiki/Space_Patrol_(1962)

N. ]]> Brighton Lounge Notebook http://www.orbiter-forum.com/showthread.php?t=27535 Problem ISS scenario crashing http://www.orbiter-forum.com/showthread.php?t=27532&goto=newpost Wed, 16 May 2012 05:35:58 GMT **** Orbiter.log
Build Aug 30 2010 [v.100830]
Timer precision: 3.77506e-007 sec
Found 0 joystick(s)
Devices enumerated: 6
Devices accepted: 5
==> RGB Emulation
==> Direct3D HAL
==> Direct3D T&L HAL
==> Direct3D HAL (NVIDIA GeForce 9500 GT (Microsoft Corporation - WDDM v1.1))
==> Direct3D T&L HAL (NVIDIA GeForce 9500 GT (Microsoft Corporation - WDDM v1.1))
Module AtlantisConfig.dll .... [Build 100830, API 100830]
Module AtmConfig.dll ......... [Build 100830, API 100830]
Module DGConfigurator.dll .... [Build 100830, API 100830]

**** Creating simulation session
DirectDraw interface OK
Direct3D interface OK
Graphics: Viewport: Window 1434 x 872 x 32
Graphics: Hardware T&L capability: Yes
Graphics: Z-buffer depth: 32 bit
Graphics: Active lights supported: 8
Loading 15382 records from star database
Module Sun.dll ............... [Build 100830, API 100830]
VSOP87(E) Sun: Precision 1e-006, Terms 554/6634
Module Earth.dll ............. [Build 100830, API 100830]
Module EarthAtmJ71G.dll ...... [Build 100830, API 100830]
VSOP87(B) Earth: Precision 1e-008, Terms 2564/2564
Module Moon.dll .............. [Build 100830, API 100830]
ELP82: Precision 1e-005, Terms 116/829
Finished initialising world
Module ISS.dll ............... [Build 100905, API 100830]
Module P6.dll ................ [Build 100904, API 100830]
Module PMA.dll ............... [Build 100904, API 100830]
Module SMDP.dll .............. [Build 100904, API 100830]
Module SSRMS.dll ............. [Build 100905, API 100830]
Module MBS.dll ............... [Build 100904, API 100830]
Module CETA.dll .............. [Build 100902, API 100830]
Module Strela.dll ............ [Build 100904, API 100830]
Module APFR.dll .............. [Build 100902, API 100830]
Module SouyzTMA.dll .......... [Build 100902, API 100830]
Module Progress_M1.dll ....... [Build 100902, API 100830]
>>> ERROR: No vessel class configuration file found for:
---------------------------------------------------------------
>>> ERROR: r7_SZ\LES
>>> [Vessel::OpenConfigFile | .\Vessel.cpp | 252]
---------------------------------------------------------------
>>> TERMINATING <<<

Something similar to this happens everytime I try to launch a mission... What can I do? What's wrong? ]]> DrunkenCosmonaut http://www.orbiter-forum.com/showthread.php?t=27532 <![CDATA[Software Soyuz Family won't display]]> http://www.orbiter-forum.com/showthread.php?t=27531&goto=newpost Wed, 16 May 2012 04:58:16 GMT Hello. I have only just installed Orbiter on a new PC and have installed both the 2006 and the 2010 versions. My problem is this: When I try to... Hello. I have only just installed Orbiter on a new PC and have installed both the 2006 and the 2010 versions.

My problem is this: When I try to launch any of the Soyuz Family scenarios, the simulator loads, and the pad is there, but no rocket sits upon it. Try as I might, I can't get the rocket to appear! This happens for both versions of Orbiter.

Is this a known problem? Does anyone know what I can do to fix this?

I am fully prepared to do anything up to a full reinstall of the simulator and all additions.

Thank you in advance for all your help! ]]> DrunkenCosmonaut http://www.orbiter-forum.com/showthread.php?t=27531 Update New version of Kourou ELS now available! http://www.orbiter-forum.com/showthread.php?t=27530&goto=newpost Wed, 16 May 2012 04:16:10 GMT Was checking Dansteph's forum, and noticed that Jacques et al. have put up a new version of the Soyuz launch site at Kourou at their webpage! The new version contains new surface tiles, as well as new LOX fuming effects and the function to adjust the light intensity.

Link: http://www.orbiterfrancophone.com/?disp=addons&id=90

Announcement: http://orbiter.dansteph.com/?news=191

Discussion: http://orbiter.dansteph.com/forum/re...=23181&t=23181 ]]> Addons Galactic Penguin SST http://www.orbiter-forum.com/showthread.php?t=27530