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• W2330608049 abstract "This paper presents the design rational and characteristics of a propulsion system for a fully reusable two-stage launch vehicle. Performance, life, and operability requirements are discussed and the configuration selection process to meet those requirements explained. Nominal operating characteristics and functional system schematics are provided. K-l Vehicle Overview The Kistler K-l vehicle is an intermediate size 2 stage launch vehicle targeted for the LEO communications satellite market. The 1 operational launch is scheduled for early 1999. The mission profile of the K-l vehicle is illustrated in figure 1. The 1 stage (LAP) powered by three Aerojet engines (two AJ26-58 and one AJ26-59) accelerates the vehicle to the desired velocity and altitude before releasing the 2 stage (OV) to continue to orbit. The LAP , after OV release, relights the center AJ26-59 engine and returns to the launch site where it lands using parachutes and airbags. The OV after release starts its single AJ26-60 engine and ascends to orbit. Using the Orbit Maneuvering System (OMS) to position the vehicle in the desired orbit the payload is released and the OV synchronizes its orbit to the plane of the landing area. At the appropriate time, the OV deorbits using the OMS ,reenters the earth's atmosphere and makes a soft landing using parachutes and air bags at a prescribed landing area near the launch site. The LAP and OV stages are checked out, re-mated and prepared for the next launch within 9 days. * Director of Propulsion, Member AIAA ** Integration Manager * Chief Engineer *** Lead Engineers Copyright © 1997 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Figure 1. K-l Mission Profile Propulsion System Requirements The requirements of the propulsion system are driven to meet the reusability, low cost and nine day turnaround vehicle requirements. • Full reusability increases the vehicle weight increasing propulsion system performance requirements. • Low cost and quick turnaround require simple systems with minimal maintenance, a comprehensive maintenance management system, and significant operations planning in the design and development phases. • Low cost reusable systems need long life LRU,s that are designed for easy changeout. AJ26-58. AJ26-59 and AJ26-60 Engines The Aerojet engines have higher performance than any booster engine now in service in the world and this performance enables the K-l vehicle concept. These engines are modified versions of the Russian NK-33 and NK-43 engines originally designed for use on the Russian Moon Rocket (N-l). The NK-33 and NK-43 engines are upgraded versions of the NK15 and NK-25 engines that actually flew on the Copyright© 1997, American Institute of Aeronautics and Astronautics, Inc. N-l and incorporate many modifications to increase margins, component life , and robustness. Starting from the NK-15/NK-25 base, these engines went through a 5 year development program demonstrating reusability (up to 17 firings before overhaul and 25 with overhaul.), extended life (>16,000 sec before and >25,000 sec with overhaul), and reliability (over 200 production engines tested with no failures). The AJ26-58 is a modernized version of the NK33 engine with updated electronics, ignition systems, controls, an electronic controller, EMA valves, and a ± 6° gimbaling system. The Aerojet engine characteristics are shown in table 1. Figure 2 presents an envelope characteristic for the Aerojet engines with an engine schematic provided in Figure 3. The AJ26-60 is identical to the AJ26-58 except for an increased area ratio nozzle. The AJ26-59 is identical except for the addition of restart capability. Thrust-lb Vacuum Sea Level Specific lap-see Vacuum Sea Level Pc-psia Mixture Ratio Length~inches Diameter-inches Weight-lb Area Ratio Thtottling~% Gimbal RangeFeatures AJ26-58" @default.
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• W2330608049 date "1997-07-06" @default.
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• W2330608049 title "An overview of the K-1 reusable propulsion system" @default.
• W2330608049 doi "https://doi.org/10.2514/6.1997-3120" @default.
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