ABOUT The Launch System
The Shazbotdom Imperial Space Administration, after a large contract that was to launch multiple sattelites into Heliocentric Orbit, began the design of what was to become the HLS. This Launch System is designed so that the Empire can launch satellites and other payloads into High Earth Orbit and out of Earth's Orbit. As of right now, there are 2 Stages, with the Second Stage currently having 4 different types in operation while a 5th and 6th are in planning/testing phases.
1st Stage Booster
The 1st stage of the Shazbotdom Imperial Space Administration's Medium Lift Rocket consists of a liquid-fueled propulsion system. The rocket uses a combination of Liquid Oxygen (LOX) and Liquid Methane (CH4) as a propellant, giving the vehicle a high specific impulse and superior thrust-to-weight ratio. The propellant is stored in high-pressure tanks, which are housed in the rocket's lower section. The propulsion system of the 1st stage consists of a single engine, which is powered by a combination of Liquid Oxygen (LOX) and Liquid Methane (CH4). The combustion chamber of the engine is fed by propellant through injectors, which produce the thrust required for liftoff. The engine is equipped with an advanced turbopump system that efficiently transfers propellant from the storage tanks to the combustion chamber.
The 1st stage engine of the Shazbotdom Imperial Space Administration's Medium Lift rocket is designed to provide a maximum thrust of 200,000 Newtons (N). This level of thrust is necessary to overcome the gravitational pull of the Earth and achieve the required velocity for orbit insertion. The engine's performance is characterized by its specific impulse, which measures the efficiency with which propellant is converted into thrust. The Shazbotdom Imperial Space Administration's engine has a specific impulse of 450 seconds, which is well above the industry average.
2nd Stage Booster
The second stage propulsion system of the Medium Lift Rocket is designed to propel the rocket and its payload beyond the Earth's atmosphere. This stage utilizes a liquid-fueled propulsion system, consisting of Liquid Oxygen (LOX) and Liquid Methane (CH4). The choice of these propellants allows for high specific impulse (Isp), which is crucial for achieving efficient propulsion during the ascent phase. Additionally, the use of liquid propellants allows for precise control of the rocket's trajectory and allows for multiple burns during the flight.
The second stage structure of the Medium Lift Rocket is designed to withstand the extreme forces and vibrations experienced during the launch and flight. The structure consists of a lightweight yet robust framework, which houses the propulsion system and other critical components. The structure is designed to optimize weight distribution and minimize the mass fraction, ensuring optimal performance and cost-effectiveness.
Maintaining the appropriate operating temperature of the second stage propulsion system is essential for its proper functioning. The Shazbotdom Imperial Space Administration has incorporated advanced thermal management systems into the second stage design. These systems include insulation materials, cooling channels, and temperature control systems to maintain the appropriate operating temperatures throughout the flight. By effectively managing the heat generated during the rocket's ascent, the Shazbotdom Imperial Space Administration ensures reliable performance and reduces the risk of thermal-related failures.
To ensure accurate guidance and navigation during the second stage flight, the Shazbotdom Imperial Space Administration has implemented advanced guidance and navigation technologies. These systems utilize a combination of inertial measurement units (IMUs), Global Positioning System (GPS) receivers, and star trackers to provide precise information about the rocket's position, velocity, and attitude. This enables the rocket to be maneuvered accurately along its predefined trajectory and enables communication with the ground control station.
