by78
General
Tianlong-3's dedicated launchpad at Jiuquan.
Tianbing's dedicated launchpad for Tianlong-3 at Jiuquan has entered formal service. A launch drill using a full-scale Tianlong-3 model was carried out.
China's Space Program Thread II
- Thread starter Blitzo
- Start date
Tianbing's dedicated launchpad for Tianlong-3 at Jiuquan has entered formal service. A launch drill using a full-scale Tianlong-3 model was carried out.
Does anyone have the specs for the Tianhuo-12 engine other than what can be found on Wikipedia?
by78
General
Development of the OrienSpace Gravity-2 launch vehicle continues. This latest hot test run not only tested the YF-102 engine, but also the gimbal and valve systems.
OrienSpace has carried out high-altitude test runs of the 50N attitude control engine for the Gravity-2 launch vehicle.
Propellant: Liquid oxygen + coal-based kerosene
Thrust at sea level: 93t (note: rumors of uprating)
Specific impulse at sea level: 285s
Thrust-to-mass ratio (probably in vacuum; ~600kg mass): 163
Number of starts 4 times
Circulation mode Gas generator
Swing mode Pump backswing
Variable thrust range 50%~110%
Vacuum thrust 110t
Vacuum specific impulse 330s
Thrust-to-mass ratio 115
Number of starts 2 times
Circulation mode Gas generator
Swing mode Pump front swing
So
| Thrust, vacuum | 1,350 (300,000 ) |
|---|---|
| Thrust, sea-level | 1,090 (250,000 ) |
| Throttle range | 40%~110% |
| 163 | |
| , vacuum | 335s |
| , sea-level | 285s |
is bs?
Originally Space Pioneer was developping Tianlong 3 with 7 engines on the 1st stage with these thrust figures, sometime in 2023 however, maybe because they couldn't hit these engine performance figures, they eventually went for a 9 engines design with lower individual thrust. So these figures are outdated.
The ideal configuration is the 9 engines one.
The ratio of first stage to second stage in orbital rockets is that the first stage should have 10x the thrust of the second stage.
9 is closer to 10 than 7 is.
I am assuming the second stage uses a similar engine.
It is also easier to throttle down for landing with smaller engines.
When less engines are selected on a design this is typically done to increase reliability at the cost of performance.
The ratio of first stage to second stage in orbital rockets is that the first stage should have 10x the thrust of the second stage.
9 is closer to 10 than 7 is.
I am assuming the second stage uses a similar engine.
It is also easier to throttle down for landing with smaller engines.
When less engines are selected on a design this is typically done to increase reliability at the cost of performance.
by78
General
DeepBlue has successfully conducted a partial-system ignition test of the Thunder-RS 130-ton LOX/Kerosene engine.
DeepBlue's first Thunder-RS has rolled off the production line.
by78
General
Progress on Zhongke's dedicated rocket assembly and testing plant for Lijian-2 located in Jiuquan. It's expected to come online in the near future.
Zhongke's dedicated rocket assembly and testing facility for Lijian-2 (located at Jiuquan) has been put into service.
