Small satellite electric propulsion options

In this study, an investigation of an exotic mixture of non-hazardous materials was conducted both in the solid and liquid states, which produced higher heat releases through chemical reactions augmented by low-power continuous wave lasers. Numerical evaluation of exothermic energies, or heat release, through chemical reactions of the target propellants was conducted with a chemical equilibrium calculation code. The results showed that the reaction temperature for B-mixed PTFE was 500 K higher than raw PTFE. In liquid propellants, the highest reaction temperature of over 2000 K was obtained for HFE at low specific energy of 3 kJ/g.

Section: Introductionmentioning

confidence: 99%

Exotic Propellant for Continuous Wave Laser Propulsion

Kondo

Horisawa

2014

“…[1][2][3][4] The significance in reducing launch masses has attracted growing interests in regard to a decrease in mission cost and an increase launch rate. Although, in the past, many very small spacecraft lacked propulsion systems, future microspacecraft will require a significant propulsion capability to provide a high degree of maneuverability and capability.…”

Section: Introductionmentioning

confidence: 99%

Characterization and Improvement of a Laser-Assisted Pulsed Plasma Thruster

Hosokawa

Yamada

Kobayashi

et al. 2014

To investigate mechanisms of high-specific impulse characteristics, or high speed plasma generation, of a laser-assisted pulsed plasma thruster, speeds of ions of plasma plumes exhausted from the thruster were measured with the time-of-flight (TOF) measurement. In the measurement, temporal variations of ion currents exhausted from the thruster were measured with a Faraday cup. From the results of single Faraday cup measurement, placed at 400 mm away from the thruster, the maximum speed of ions of 169 km/sec at charge voltage of 2000 V (or charge energy of 14 J) was obtained. On the other hand, with double Faraday cup measurement, installed at 400 mm and 600 mm, the maximum ion speed was 220 km/sec at charge voltage of 2000 V.

“…The current trend towards smaller spacecraft, which is not only mass limited but also power limited, has produced a strong interest in development of micropropulsion devices [1][2][3][4] . The significance in reducing launch masses has attracted growing interests in regard to reduction of mission costs and increase of launch rates.…”

Section: Introductionmentioning

confidence: 99%

Rectangular Pulsed Laser-Electromagnetic Hybrid Accelerator

Kishida

Katayama

Horisawa

2010

A fundamental study of newly developed PPT type rectangular laser-electromagnetic hybrid thrusters was conducted, in which laser-induced plasma was induced through laser beam irradiation onto a solid target and accelerated by electrical means instead of direct acceleration only by using a laser beam. The performance of the thrusters was evaluated by measuring the mass shot and the impulse bit, and calculating the specific impulse and the propulsion efficiency. As a result, specific impulse varied from 5,300 to 7,100 seconds with increase of charge energy to the capacitor from 2.2 to 8.6 J with a laser pulse energy of 266 mJ. The maximum thrust efficiency of 22% was obtained with the smallest charge energy case. In addition, to optimize the acceleration channel geometry, thrust performance of seven various thrusters with various geometries were compared. The maximum impulse-bit and specific impulse obtained with the 5 mm (width) x 10 mm (length) thruster were from 28 μN and from 7,200 sec for the charge energy of 8.6 J.