Performance Characteristics Of Thruster Research Articles

Effect of multiply charged ions on the performance and beam characteristics in annular and cylindrical type Hall thruster plasmas

Plasma plume and thruster performance characteristics associated with multiply charged ions in a cylindrical type Hall thruster (CHT) and an annular type Hall thruster are compared under identical conditions such as channel diameter, channel depth, propellant mass flow rate. A high propellant utilization in a CHT is caused by a high ionization rate, which brings about large multiply charged ions. Ion currents and utilizations are much different due to the presence of multiply charged ions. A high multiply charged ion fraction and a high ionization rate in the CHT result in a higher specific impulse, thrust, and discharge current.

우주발사체 자세제어용 하이드라진 추력기의 정상상태 추력 특성

우주발사체 자세제어용 하이드라진 추력기의 지상연소시험을 수행하였다. 시험에 사용된 추력기는 추진제 주입압력 2.41 MPa (350 psia) 에서 정상상태 공칭추력 67 N (15 <TEX>$lb_f$</TEX>) 을 목표로 설계/제작 되었다. 개발모델 추력기의 성능특성 검토를 위해 정상상태 연소모드에서의 추력, 추진제 공급압력, 질량유량, 추력실 압력, 그리고 온도 등의 성능변수를 이용한다. 시험결과, 실제의 성능이 이론 요구규격 대비 89.1% 이상의 성능효율을 만족하는 것이 확인되었다. An ambient hot-firing test was carried out for the hydrazine thruster which may be employed in the space launch vehicles. The thruster is designed to produce 67 N (15 <TEX>$lb_f$</TEX>) of nominal steady-state thrust at an inlet pressure of 2.41 MPa (350 psia). A scrutiny into the performance characteristics of thruster is made in terms of thrust, propellant supply pressure, mass flow rate, chamber pressure, and temperature at the steady-state firing mode. As a result, it is ensured that the practical performance efficiencies are above 89.1% compared to its ideal requirements.

Performance Characteristics of a Cluster of 5-kW Laboratory Hall Thrusters

5 Torr-Xe). Comparison of the cluster and the monolithic thruster performance characteristics for conditions of nearly equal operating pressure shows that for the 5:25 mg=s anode flow rate, the clusterthrustisequaltotheadditionofthetwomonolithicthrustersandtheanodeefficiencyandspecificimpulseare approximately equal to those of the monolithic thruster. An improved backpressure correction technique based on incremental current change was demonstrated to predict thrust changes within 4% to 2%, significantly better than a simple random flux calculation that uses the facility pressure and chamber wall temperature.