Monopropellant hydrazine propulsion systems have compiled an enviable record of operational success over the last 30 yr for a large number of spacecraft missions. These missions include near earth, low altitude satellites, geosynchronous orbiting spacecraft, and deep space probed. Many of these flight propulsion systems have demonstrated very long life times (10 to 15 yr) and high mission reliability over a wide range of environmental and operating conditions. However, even with all of the flight success experienced to date, many questions still arise in the spacecraft/user community about the suitability of hydrazine for certain space system applications. The majority of these questions focus on concerns about contamination of highly sensitive optical (mirrors) and thermal control surfaces as well as long total mission life capabilities (with respect to duty cycles, thruster throughput, total operating times, and total mission times). These concerns are addressed by describing past experiences with specific long-life spacecraft that demonstrate the suitability of hydrazine for use in future highly specialized and sensitive mission applications. Other future concerns are also addressed such as space basing, reusability, and micrometeroid/debris protection. In addition, a short discussion is included on future performance growth possibilities such as the use of hydrazine in dual mode propulsion systems.
Monopropellant Hydrazine Spacecraft Propulsion Systems: 30 Years of Safe, Reliable, Flexible and Predictable Performance
1990
16 pages
Report
No indication
English
Rocket Engines & Motors , Space Launch Vehicles & Support Equipment , Contamination , Hybrid propulsion , Hydrazines , Monopropellants , Propulsion system configurations , Propulsion system performance , Spacecraft propulsion , Technology utilization , Control surfaces , Geosynchronous orbits , Mirrors , Reliability , Synchronous satellites , Temperature control
British Library Conference Proceedings | 1990
|