Session
Technical Session VI: Enabling New Technologies and Methods I
Abstract
Rocket Propulsion Engineering (RPe) is developing the first in a family of two low-cost, two stage, small rocket vehicles suitable for target, suborbital, and small-sat orbital applications. The first of these two launch vehicles, the Prospect LV-1 will have an orbital payload of 300-400 lb. The larger vehicle, the Prospect LV-2, uses about 80% of the components and technology of the LV-1 and will orbit payloads of 1500-1700 lb. Two engines are being developed. A first stage 30,000 lbf class engine (R1-30L) and a second stage engine of approximately 2400 lbf (R1-2H). The engine designs are essentially identical except for size. Propellants are hydrogen peroxide/kerosene. The engines are ablatively cooled with additional film cooling. Chamber pressure is approximately 715 PSIA. Both engines use centrifugal turbopumps driven by an open cycle, bipropellant gas generator. Medium-technology pump-fed rockets have significant advantages over pressure fed alternatives, provided the pump technology remains simple. Among these advantages are: smaller, lighter, more efficient engines; less propellant use; and simpler and smaller ground-handling equipment. Most importantly, propellant tank structure is lighter and much simpler to engineer and manufacture, and high-pressure helium tankage is greatly reduced. RPe therefore decided to put the engineering effort into developing the turbopump rather than pressure-fed vehicle structures. To be practical and cost effective, the turbopump must be simple by modern rocket engine standards. To this end, RPe has been pursuing a very modular, scalable pump design, utilizing as few components as possible – all components being readily available through standard commercial supply and manufacturing processes. The result is a very simple, very low-cost pump design that significantly enhances the overall vehicle design and greatly reduces vehicle structural weight and propellant requirements. Vehicle structure employs weight-saving features such as the use of a common propellant tank bulkhead and the extensive use of modern composites. Storable, ambient temperature propellants eliminate many of the material, embrittlement, and strain-related design problems that typically accompany cryogenic vehicles. The engines for these vehicles, especially the smaller R1-2H, should also be attractive candidates for use as the main propulsion engines on orbital transfer upper stages and as storable spacecraft engines.
Rocket Propulsion Engineering Company Small Launch Vehicle
Rocket Propulsion Engineering (RPe) is developing the first in a family of two low-cost, two stage, small rocket vehicles suitable for target, suborbital, and small-sat orbital applications. The first of these two launch vehicles, the Prospect LV-1 will have an orbital payload of 300-400 lb. The larger vehicle, the Prospect LV-2, uses about 80% of the components and technology of the LV-1 and will orbit payloads of 1500-1700 lb. Two engines are being developed. A first stage 30,000 lbf class engine (R1-30L) and a second stage engine of approximately 2400 lbf (R1-2H). The engine designs are essentially identical except for size. Propellants are hydrogen peroxide/kerosene. The engines are ablatively cooled with additional film cooling. Chamber pressure is approximately 715 PSIA. Both engines use centrifugal turbopumps driven by an open cycle, bipropellant gas generator. Medium-technology pump-fed rockets have significant advantages over pressure fed alternatives, provided the pump technology remains simple. Among these advantages are: smaller, lighter, more efficient engines; less propellant use; and simpler and smaller ground-handling equipment. Most importantly, propellant tank structure is lighter and much simpler to engineer and manufacture, and high-pressure helium tankage is greatly reduced. RPe therefore decided to put the engineering effort into developing the turbopump rather than pressure-fed vehicle structures. To be practical and cost effective, the turbopump must be simple by modern rocket engine standards. To this end, RPe has been pursuing a very modular, scalable pump design, utilizing as few components as possible – all components being readily available through standard commercial supply and manufacturing processes. The result is a very simple, very low-cost pump design that significantly enhances the overall vehicle design and greatly reduces vehicle structural weight and propellant requirements. Vehicle structure employs weight-saving features such as the use of a common propellant tank bulkhead and the extensive use of modern composites. Storable, ambient temperature propellants eliminate many of the material, embrittlement, and strain-related design problems that typically accompany cryogenic vehicles. The engines for these vehicles, especially the smaller R1-2H, should also be attractive candidates for use as the main propulsion engines on orbital transfer upper stages and as storable spacecraft engines.
