The concept describes a booster for a launch vehicle that is simpler to make, transport and launch than current launch vehicles. IT is composed of two major components. The first being a booster…

This federal contract was awarded by the National Aeronautics and Space Administration (NASA) Shared Services Center to Frontier Astronautics LLC, a small business, under the Small Business Innovation Research (SBIR) Program Phase I. The contract, valued at $124,944.00, is for the development of a novel booster design for a launch vehicle. The booster uses a unique propellant combination of hydrogen peroxide and kerosene, along with a combination gas generator and electric pump-fed rocket engine, to achieve simplified construction and higher reliability compared to conventional designs. This contract is for the initial research and development phase of this booster concept.

The concept describes a booster for a launch vehicle that is simpler to make, transport and launch than current launch vehicles. IT is composed of two major components. The first being a booster structure and the second being a liquid rocket engine that uses a thermodynamic cycle that is a combination of two common cycles. Furthermore, the engine is actually fairly simple when compared to modern liquid rocket engines, thereby making IT less expensive and having more inherently reliably. The booster uses hydrogen peroxide and kerosene. This is a dense propellant combination that allows the booster to be made out of relatively inexpensive materials yet still have a high propellant mass fraction. This reduces cost. The booster will use four fixed rocket engines (non-GIMBALLING) that are angled slightly so that pitch, YAW and roll control can be achieved simply by throttling the engines differently. This eliminates the need for a gimbal mount, hydraulic actuators and related componets, flexible propellant feed lines and separate pressure tanks. Furthermore, with the use of dense, non-cryogenic, hypergolic propellants like hydrogen peroxide, all cryogenic compatible components (which are expensive), insulation and the entire ignition system may be eliminated. The engine combines a gas generator with an electric pump FED design. IT switches from one cycle to the other at the optimum time of flight allowing better performance than an engine using only one of the cycles exclusively. IT would use the gas generator mode for liftoff and early in the flight as IT can provide high power output at the cost of less specific impulse efficiency. By switching to a closed electric cycle doing boost the engine can then provide higher specific impulse with less thrust, which is acceptable because the booster will have consumed much of its propellant and is lighter. The combination of this booster and engine allows for a much simpler and reliable launch vehicle.