Further Improvements and Qualification Status of Astriums 10N Bipropellant Thruster Family

Schulte, Georg; Gotzig, Ulrich; Horch, Alois; Dreer, Thomas

doi:10.2514/6.2003-4776

Cited by 3 publications

(2 citation statements)

References 2 publications

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“…When the critical temperature is reached, gas resistance or even capillary explosion occurs [5]. In order to suppress the heat reflux for this microthruster, the European Astrium Company added a copper ring at the junction between the injector and the combustion chamber, which significantly mitigated this problem [6]. The two-phase flow problem was suppressed by the thermal control at the injector by ECAPS and BUSEK of the United States [7].…”

Section: Introductionmentioning

confidence: 99%

Effects of Heat Reflux on Two-Phase Flow Characteristics in a Capillary of the ADN-Based Thruster

Yan

Liu²,

et al. 2022

Micromachines

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During the working process of the ADN-based thruster, continuously, heat generated by the chemical reaction in the combustion chamber will transfer along the upstream capillary, the propellant in the capillary continuously absorbs heat under the effect of heat transfer from the wall and undergoes a phase change when the saturation temperature is reached. In this study, effects of the downstream heating temperature (623 K to 923 K) on mass flow rate and pressure change in the capillary were investigated based on the established test platform. Simultaneously, the VOF (volume of fraction) model, and the Lee phase transition model coupled with the Navier–Stokes method was utilized to simulate the spatial distribution of the gas-liquid propellant in the capillary. The results show that the ADN-based propellant firstly formed bubbles on the inner wall surface near the exit of the capillary, and these vapor bubbles moved and grew upstream along the capillary. Due to the cooling effect of the ADN-based propellant inflow, the temperature distribution of the front chamber and capillary gradually reached equilibrium. Bubbles were constantly generated in the capillary, and as the heat reflux intensified, the total volume of bubbles in the capillary continued increasing. Single-phase flow, annular flow, wave flow, and segment plug flow appeared sequentially along the axial direction of the capillary, and the proportion of gas phase volume fraction at the capillary outlet section gradually increased.

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Section: Introductionmentioning

confidence: 99%

Effects of Heat Reflux on Two-Phase Flow Characteristics in a Capillary of the ADN-Based Thruster

Yan

Liu²,

et al. 2022

Micromachines

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“…EADS' Astrium division's 10N bipropellant thrusters S10-01, S10-02, S10-18, etc. This series of thrusters uses swirling injectors and can work continuously in steady state or pulse mode [5][6][7]. Northrop Grumman has developed apogee engines such as TR-306, TR-308, TR-312, etc., with pintle injectors and MON-3/N 2 H 4 as propellant, suitable for dual-mode propulsion systems [8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on the New 100N Bipropellant Space Rocket Engine

Huang¹,

Zhang²,

Wang³

et al. 2022

Proceedings of the International Conference of Fluid Power and Mechatronic Control Engineering (ICFPMCE 2022)

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This paper developed experimental research on the new 100N bipropellant space rocket engine. The bi-centrifugal swirl injector with high degree of technological maturity, high reliability and properties is used on this engine. The cold flow test, steady-state hot firing, pulse-mode firing, long life hot firing and deflection firing test are carried out. The results show that, the flow and spray characteristics of injector keep stable; during the steady-state hot firing, the structure of engine is intact; the impulse is good and the heat back temperature can up to 220.2 °C; during the different pulse-mode firing, the engine response time (t90) is lower than 38 ms; after the 45000 s long life firing, the structure temperate is not high which can fit the demand of long life; the heat back temperature of weld can up to 232.0 °C.

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