V-9 Rocket

Tech notice: Tech Level MT+1, or light PMT.

Aerospace Logistics V-9P, two-stage heavy orbital launcher rocket, the first in the V line to use a partially reentering launcher, is a new product entering the testing stage. "P" suffix denotes the operational prototype version.

This rocket is being built for the Freedom Hall Space Exploration Project. The launch cost is expected to be as low as 230 million caps, with full rocket cost below 1,1 billions, both decreasing as the technology is perfected. Carrying 820 tonnes of payload, this rocket makes space exploration more feasible than ever before.

The construction of V-9P includes:

• Main engine, which the rocket is built around. The fuel is burnt inside a passively safe low-pollution nuclear reactor, which increases the temperature of the gases. Ignition is provided by compression and heat. The main engine reenters afterwards and can be used for at least 40 launches. The engine weights 150 tonnes, and its cost comprises 80% of the rocket's total cost in the optimal configuration, while maintenance and recycling costs are expected to be up to 1.5 times higher. Being passively safe, the reactor is easily stopped for reentering. The engine is a long-term investment, and its use only accounts for 20% of the launch cost, unless a failure occurs, which quadruples the expenses.

• The first stage applies air-hydrogen system. Inexpensive hydrogen is fed to the main engine together with air from single-use compressor turbine. The compressor is built of low alloyed steel and driven by solid-fuel jets located on the blade tips. The inside of thin double-layer airframe is filled with water, which cools it, and the steam is vented into the engine. Air-hydrogen system receives one third of the power from the nuclear heater, which works efficiently with steam exhaust. Constructed of welded and pressed steel sheets, up to 95% of its dry mass of 400 tonnes can be fully used for a new one with little reprocessing. This system has loose tolerances more characteristic for shipbuilding and can be built on slghtly reequipped naval shipyards, comprising only 8% of the rocket's cost if 80% of the returning mass is reused, and doubling if it is lost.

• Separation system is a part of the first stage. In high mesosphere air-hydrogen-water system becomes ineffective and is discarded, while the second stage continues the flight. It is still capable of producing thrust, which is used to soften the landing, using autorotation. Stabilization is provided by the heavy rotating compressor. The percentage of the steel airframe burnt depends on amount of water used and on the payload. Fully loaded, the standart payload of Stage I is 1400 tonnes or 1650 with hydrazine, and 95% of the airframe return. If less water is used, the payload may be increased by up to 100 tonnes, but part of the airframe is lost. This may be used for overweight loads, at expense of 30% launch cost increase.

• The second stage lifts the payload to a high orbit and accelerates it to speeds of up to 12 km/s. It may use either water or hydrazine as the propellant, with all heat in the first case and 80% in the second provided by the nuclear heater. If water is used, the frame is built of light alloys and the hull of alloyed steel, the second stage comprises 12% of the rocket's cost. Use of hydrazine may add 250 more tonnes to the payload by increasing available power, but cost of the stage increases by 90%, with total launch cost up by 45%. Building all the frame and hull of HSLA steel and using cheaper heatshields makes the stage 30% and the launch 15% cheaper, but the dry weight increases from 150 to 260 tonnes, decreasing the final payload.

• Engine reentry system, being a part of the second stage, decelerates with remaining fuel and lands the engine, burning the second stage for cooling. Its cost is included in the engine cost. The reentry system at the rocket's last launch may be potentially removed, engine staying with the payload. This may save recycling costs and allow use of V-9 as a long-range rocket, if the issues with nuclear non-proliferation were lifted, as even worn engine is a working nuclear reactor. However, V-9 is not a dedicated long-range rocket, having excessive thrust and fuel use, and is only marginally better for this purpose than conventional hydrazine rockets.

• An alternative to the second stage is the Orbital Aircraft, now-developed concept. If an air-only system is used for the first stage, the resulting payload must either be decreased to 400 tonnes or the maximum attitude decreased to lower mesosphere. In the latter case the first stage may be returned intact, serving for over 1000 launches and the engine will be able to serve for 500 launches, with total expenses per launch below 0.3% of the full rocket cost. The second stage, however, will gain less altitude, restricting the system to Low Earth Orbit. Current proposals include:
  • Two-stage fully reuseable launcher with a 850-tonne orbital glider with 750-tonne payload;
  • Single-stage system with oxygen-hydrogen powered 1000-tonne orbital powered aircraft with 700-tonne payload;
  • A system retaining the main engine and carrying only water for propulsion, carrying all 1400 tonnes upwards and 1000-tonne payload;
  • Modification of the first stage to launch the 600-tonne glider, carrying about 500 tonnes, without the second stage at all.
  • Besides the single-glider solutions, multiple gliders or suborbital aircrafts can be used, with as much as 7 gliders, each carrying 50 tonnes.

The V-9 class is planned to replace all existing heavy rockets and become the mainstay of Aerospace Logistics orbital launch system, as well as form the foundation for hypersonic suborbital military and civilian transport.

Currently work is underway on development of full V-9, but specifications and construction will depend on results of V-9P testing.