The projet is now advanced enough to start a proper developpement thread.
Overview :
The Sigma rocket is supposed to be a near-future class of Heavy Launch Vehicles developped by NASA, with main focus put on re-using Shuttle hardware.
Things to work on :
Launcher
- Custom sounds.
- Some camera/lights functions for the "logical launchpad".
HCV
- Solar panels Sun-tracking animations [on hold].
- Adjust solar panels efficiency relative to the spacecraft orientation [on hold].
- Code a "loss of control" and "loss of focus" when the battery is flat and a possible regain of control [on hold].
- Create several "cargo tanks" (liquids, air, gases, hardware, junk).
- Variables load/save.
- Custom sounds.
Things that work :
Launcher
- The first and second stage autopilots can follow a time/pitch program and put the HCV to a viable 200 x 200-220 km orbit.
- The first stage autopilot can follow a pitch/time, yaw, roll program which is a little oversensitive but functional.
- Initial roll sequence.
- The second stage now "adapts" to the situation in a limited but working way.
- Separation sequence.
- Fairing separation.
- The SRBs thrust follow the proper power curve. Much more realistic, and keeps acceleration under 4G.
- ACS for the 2 stages.
- For the first stage, the ACS is enabled when the SRB are jettisonned (with only one engine left, you need it for roll control).
- SSME ignition sequence : coolant vent & sparkles.
- SRBs burnout effect.
- MaxQ condensation effects.
- Launch azimuth can be set in the .scn file.
- Guidance pitch targets can be adjusted in the .scn file [stage 1].
- Manual "Range Officer" command.
- Very tight MaxQ corridor, if you get out the rocket goes boom.
- Two cameras for each stage (back & front views).
- Guidance program data can be adjusted in the .scn file [stage 2].
- A safety rating can be entered in the .scn file ; failures include 15 different scenarios with random timing, from countdown hold to SRB failure. Some failures are more likely than others, in regard of historic data.
- Stage 2 orbital vent/safing sequence.
- Possibility to set a custom payload with a custom offset (this will be pushed further in a next release).
- Variables Load/Save (1st stage)
HCV
- HCV RCS (rotation + linear), anti-torque programs.
- HCV Main + Retro engines.
- 2 RCS submodes : "coarse" (use all RCS thrusters) and "fine" (use half of the RCS thrusters).
- Solar Panels deployement animation.
- Antenna deployement animation.
- Docking port (tilted, requires some adaptation with DockMFD).
- Headlights (local light) & navlights (beacons).
- Battery management : power is drained when in Earth shadow, headlights drain power. 36 hours of autonomy (lights off, drops to 6 hours if lights on). Battery charges when the spacecraft is in sunlight.
- De-orbit auto-sequence.
- Variables load/save (power-on anims, lights, RCS mode).
Further developpement possiblities :
- 6 meters, 3x SSME first stage, 2x 5-Segments RSRM. (HLV), "Sigma III"
- 8 meters, 5x SSME first stage, 4x 5-Segments RSRM. (SHLV) "Sigma V"
- 6 and 8 meters upper stages. "Sigma III-6", "Sigma V-8", etc...
The "Sigma I-5/2"
Payload to LEO* : 55 metric tons
* 200 x 200 km orbit, 51.6° Eq. Inc
Payload to GTO : TBD.
First stage
- Diameter : 4 meters
- 1x SSME engine (2.17 MN in vacuum)
- Propellants : 105,560 kg of LOX/LH2
- ACS : 8x 400 N thrusters, 76 kg of MMH/N2O4
Boosters
- 2x RSRM (up to 2x 13.6 MN at power peak)
- Propellant : 2x 500,000 kg of HTPB/solid
- Burn time : 123 seconds.
Second stage
- Diameter : 5 meters
- 1x J2-X engine (1.31 MN in vacuum)
- 2x 5 kN engines for separation/ullage burn, 75 kg of MMH/N2O4.
- Propellants : 109,956 kg of LOX/LH2
- ACS : 12x 400 N thrusters, 320 kg of MMH/N2O4
The "HCV" (Heavy Cargo Vehicle)
The HCV is designed to resupply space stations, obviously including the ISS. It will also provide an orbit re-boost capability. It can also be fitted to be a temporary module for a space station (laboratory, living space).
Mass : 53 metric tons, fully fueled & loaded.
Diameter : 4.8 meters.
Lenght : 18.5 meters.
Delta-V : 619.5 m/s
Propellants : 9400 kg of N2O4.
Engines : 1x OMS (hypergolic), 26700 N.
RCS : 26x 3870 N thrusters.
Power : 4 solar panels arrays, 4x 10 m², 4600 W/h average output.
Orbital lifespan : 1 year.
---------- Post added at 07:10 PM ---------- Previous post was at 07:09 PM ----------
Some pictures of the Sigma I-5/2 with the HCV as payload :
Pictures of the HCV :
Overview :
The Sigma rocket is supposed to be a near-future class of Heavy Launch Vehicles developped by NASA, with main focus put on re-using Shuttle hardware.
Things to work on :
Launcher
- Custom sounds.
- Some camera/lights functions for the "logical launchpad".
HCV
- Solar panels Sun-tracking animations [on hold].
- Adjust solar panels efficiency relative to the spacecraft orientation [on hold].
- Code a "loss of control" and "loss of focus" when the battery is flat and a possible regain of control [on hold].
- Create several "cargo tanks" (liquids, air, gases, hardware, junk).
- Variables load/save.
- Custom sounds.
Things that work :
Launcher
- The first and second stage autopilots can follow a time/pitch program and put the HCV to a viable 200 x 200-220 km orbit.
- The first stage autopilot can follow a pitch/time, yaw, roll program which is a little oversensitive but functional.
- Initial roll sequence.
- The second stage now "adapts" to the situation in a limited but working way.
- Separation sequence.
- Fairing separation.
- The SRBs thrust follow the proper power curve. Much more realistic, and keeps acceleration under 4G.
- ACS for the 2 stages.
- For the first stage, the ACS is enabled when the SRB are jettisonned (with only one engine left, you need it for roll control).
- SSME ignition sequence : coolant vent & sparkles.
- SRBs burnout effect.
- MaxQ condensation effects.
- Launch azimuth can be set in the .scn file.
- Guidance pitch targets can be adjusted in the .scn file [stage 1].
- Manual "Range Officer" command.
- Very tight MaxQ corridor, if you get out the rocket goes boom.
- Two cameras for each stage (back & front views).
- Guidance program data can be adjusted in the .scn file [stage 2].
- A safety rating can be entered in the .scn file ; failures include 15 different scenarios with random timing, from countdown hold to SRB failure. Some failures are more likely than others, in regard of historic data.
- Stage 2 orbital vent/safing sequence.
- Possibility to set a custom payload with a custom offset (this will be pushed further in a next release).
- Variables Load/Save (1st stage)
HCV
- HCV RCS (rotation + linear), anti-torque programs.
- HCV Main + Retro engines.
- 2 RCS submodes : "coarse" (use all RCS thrusters) and "fine" (use half of the RCS thrusters).
- Solar Panels deployement animation.
- Antenna deployement animation.
- Docking port (tilted, requires some adaptation with DockMFD).
- Headlights (local light) & navlights (beacons).
- Battery management : power is drained when in Earth shadow, headlights drain power. 36 hours of autonomy (lights off, drops to 6 hours if lights on). Battery charges when the spacecraft is in sunlight.
- De-orbit auto-sequence.
- Variables load/save (power-on anims, lights, RCS mode).
Further developpement possiblities :
- 6 meters, 3x SSME first stage, 2x 5-Segments RSRM. (HLV), "Sigma III"
- 8 meters, 5x SSME first stage, 4x 5-Segments RSRM. (SHLV) "Sigma V"
- 6 and 8 meters upper stages. "Sigma III-6", "Sigma V-8", etc...
The "Sigma I-5/2"
Payload to LEO* : 55 metric tons
* 200 x 200 km orbit, 51.6° Eq. Inc
Payload to GTO : TBD.
First stage
- Diameter : 4 meters
- 1x SSME engine (2.17 MN in vacuum)
- Propellants : 105,560 kg of LOX/LH2
- ACS : 8x 400 N thrusters, 76 kg of MMH/N2O4
Boosters
- 2x RSRM (up to 2x 13.6 MN at power peak)
- Propellant : 2x 500,000 kg of HTPB/solid
- Burn time : 123 seconds.
Second stage
- Diameter : 5 meters
- 1x J2-X engine (1.31 MN in vacuum)
- 2x 5 kN engines for separation/ullage burn, 75 kg of MMH/N2O4.
- Propellants : 109,956 kg of LOX/LH2
- ACS : 12x 400 N thrusters, 320 kg of MMH/N2O4
The "HCV" (Heavy Cargo Vehicle)
The HCV is designed to resupply space stations, obviously including the ISS. It will also provide an orbit re-boost capability. It can also be fitted to be a temporary module for a space station (laboratory, living space).
Mass : 53 metric tons, fully fueled & loaded.
Diameter : 4.8 meters.
Lenght : 18.5 meters.
Delta-V : 619.5 m/s
Propellants : 9400 kg of N2O4.
Engines : 1x OMS (hypergolic), 26700 N.
RCS : 26x 3870 N thrusters.
Power : 4 solar panels arrays, 4x 10 m², 4600 W/h average output.
Orbital lifespan : 1 year.
---------- Post added at 07:10 PM ---------- Previous post was at 07:09 PM ----------
Some pictures of the Sigma I-5/2 with the HCV as payload :
Pictures of the HCV :
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