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Identification of the optimum channel size based on the variable η s for a monolith with 100 mm 2 cross sectional area
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Analysis of present and future missions concluded that a miniaturised hydrogen peroxide monopropellant rocket engine is the optimum solution for the increasing demand for small and low cost propulsion systems for small satellites. The attractiveness of monopropellant thrusters is based on its operational and structural simplicity. Additionally, the...
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... hydrogen peroxide mass flow was varied during the tests to investigate the dynamic behavior of the balance. Figure 12 shows the measured thrust obtained for different mass flow rates. The change in thrust is lacking behind the mass flow rate changes. ...
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... 12 shows the measured thrust obtained for different mass flow rates. The change in thrust is lacking behind the mass flow rate changes. This is believed to be due to the relative long feeding lines between flow meter and decomposition chamber. Since the mass flow rate is pressure driven, and the pressure increases only slowly (see right side of fig. 12), consequently, the mass flow rates and the thrust rises also only slowly. The oscillations observable in both the thrust and the pressure measurements are believed to originate from the decomposition. However, the already mentioned long feeding lines allow those oscillations to build up. By having shorter lines and a flow restrictor ...
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... left side of fig. 12 and fig. 13 show the variation of the thrust as a function of the mass flow rate. Thrust levels between 50 and 550 mN have been measured. These data, together with the mass flow rates, were used to calculate the specific impulse. The results show a yet unexplained variation of the specific impulse between 70 and 100 s. Investigation of this ...
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![Fig. 4. Samples of 98 %+ HTP [author, 2014]](profile/Pawel-Surmacz/publication/295098303/figure/fig2/AS:667816407597066@1536231247877/Samples-of-98-HTP-author-2014_Q320.jpg)
The paper presents results of research on the catalytic decomposition of 98 % hydrogen peroxide, using special structures called composite catalyst beds. Such configuration of a catalyst bed can be applied in future green monopropellant thrusters for attitude control systems as well as self-ignitable and restart-able bipropellant engines. A number...
Citations
... CubeSat-class chemical propulsion systems use a monopropellant that decomposes via a catalyst. For example, a miniature monopropellant thruster using hydrogen peroxide can generate 50 to 550 mN thrust with vacuum-equivalent specific impulse around 160 s, capable of delivering roughly 1880 N·s total impulse using 1.2 kg propellant (26). A green monopropellant thruster developed at BUSEK Co., Inc. was able to deliver 0.5 N thrust with specific impulse around 220 s (27). ...
This thesis investigates high-performance electrospray thrusters for nanosatellite applications. The thruster, termed Porous-emitter Electrospray Thruster (PET), consists of a porous emitter and a porous propellant reservoir made, allowing propellant to be transported passively. In order to increase the electrospray emission density and thrust density, different PET thruster emitters manufactured using low-cost techniques were studied using numerical simulations and by experiments. The electric field simulations suggest that the onset voltage of a porous emitter, contrary to capillary emitters, decreases with the size of the Taylor cone on the emitter tip. Based on multiple thruster tests in a vacuum, the onset voltages were between ±1800 to ±2200 V. The PET electrospray thrusters demonstrated high emission current, with the maximum values around 3 mA near ±3500 V. The per-tip emission current up to around 100 µN was high compared to most state-of-art development and was found mainly a result of the large emission tips that introduce more emission sites. Time-of-flight characterisations suggest that the emitted particles were mainly monomer ions and dimer ions with high specific impulse ranging from 3891 to 7459 s. The estimated thrust ranges from approximately 0.8 to higher than 263.5 µN, higher than most similar designs. The polydispersive efficiency due to the presence of multiple particles was calculated, ranging from 86.1% to 94.5%. The voltage losses of the thruster were measured using a retarding potential analyser, suggesting a non-kinetic efficiency from 92% at -2100 V to 86.7% at 2600 V. Evidence of the fragmentation from dimer ions to monomer ions was found in retarding potential analysis results, and their energy variations agree with theoretical calculations. The thruster plume angle increased from 12.4 degrees at low voltages of ±1800 V to approximately 60.8 degrees at high voltages of ±3500 V, with the angular efficiency decreased from 99.2% to 88.8%, correspondingly. The trajectory of charged particles in the plume is studied using numerical simulations, and the results suggest that the increase of the plume area is mostly a result of the expanded emission area at high voltages. By estimation, the thruster power efficiency ranges from 50% to 60%. The PET thrusters demonstrated a relatively high emission current and thrust at the cost of higher operating voltages and power. A PET thruster was tested continuously for 18 hours with relatively stable emission current and minor variations. The thruster performance was evaluated in two nanosatellite mission scenarios requiring high velocity-changes and precise thrust, and they show adequate manoeuvre performance. The preliminary studies in this thesis demonstrated that the PET electrospray thrusters have promising propulsive performance, and further development is recommended.
... Chemical propulsion systems applicable to interplanetary CubeSats include monopropellant thrusters [13,14], bipropellant thrusters [15], tripropellant [16], cold gas [17,3,10], warm gas [18], solid [19] and hybrid motor systems [20]. These systems have been manufactured and tested on-board large satellites but they face multiple issues over miniaturisation [21]. ...
Stand-alone interplanetary CubeSats to Mars require primary propulsion systems for orbit manoeuvring and trajectory control. The context is a 30 kg 16U Interplanetary CubeSat mission on a hybrid high-thrust & low-thrust trajectory utilising a Dual Chemical-Electric Propulsion System to achieve Earth escape (high-thrust) and perform autonomous deep-space cruise (low-thrust) to Mars. Mission analysis is performed to estimate the required ∆V (∼ 445 m/s) for Earth escape and Mars circularisation, and calculate the required thrusts and burn durations while minimising gravity losses, Van Allen belt crossings, and irrecoverable destabilisation. Design of an ADN-based mono-propellant thruster and an Ethanol-H2O2 based bipropellant thruster are performed and the critical design details regarding propellant characteristics, system sizes, operating pressures, material selection and geometry of feed systems, thrust chambers, and nozzles are delineated. Performances analysis of the monopropellant thruster yields a maximum thrust of 3.18 N (two thrusters with 1.54 N each) and an Isp = 259.7 s with nozzle area ratio of 100. Similarly, the bipropellant thruster yields a thrust of 2.91 N and an Isp = 303.15 s. The overall mass and volume of the monopropellant system are 5.6 kg (18.7%) and 7U, respectively. The bipropellant system weighs 4.85 kg (16.17%) while occupying 6.5U space.
... Although, much of the information is not available publicly. Chemical propulsion systems applicable to Interplanetary Cube-Sats include monopropellant thrusters [9,10], bipropellant thrusters [11], tripropellant [12], cold gas [2,6,13], warm gas [14], solid [15] and hybrid motor systems [16]. These systems have been manufactured and tested on-board large satellites but they face multiple issues over miniaturisation [17]. ...
Interplanetary CubeSats enable universities and small-spacecraft-consortia to pursue low-cost, high-risk and high-gain Solar System Exploration missions, especially Mars; for which cost-effective, reliable, and flexible space systems need to be developed. Missions to Mars can be achieved through a) in-situ deployment by a mothership and b) highly flexible stand-alone CubeSats on deep-space cruise. The current work focuses on sizing and establishing critical design parameters for dual chemical-electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high-thrust & low-thrust trajectory. High thrust is used to escape Earth whereas low-thrust is used in autonomous deep-space cruise, achieving ballistic capture, and emplacement on an areosynchronous orbit at Mars. Chemical propulsion characterisation is based on ∆V requirement and a heuristic optimisation of thrust, specific impulse and burn time while balancing transfer time and propellant mass. Limitations are set to minimise destabilising momentum. Electric propulsion characterisation is based on the ∆V , power consumption, and trajectory requirements for fuel-optimal and time-optimal strategies. The sizes amount to ∼ 16% and ∼ 21% of the assumed total mass (∼ 30 kg) for chemical and electric systems, respectively.
... Wartość obciążenia złoża katalitycznego wynika z masowego natężenia przepływu czynnika oraz pola powierzchni przekroju poprzecznego złoża. Zakres stosowanych wartości obciążenia złoża jest bardzo szeroki -od 4,8 kg/s/m 2 dla struktur monolitycznych [89] oraz 27,3 kg/s/m 2 dla granulatu [103] do 93,3 kg/s/m 2 dla granulek [21] oraz 560 kg/s/m 2 dla stosu siatek [98]. Dodatkowo, Wernimont i Durant [119] przedstawiają wyniki badań dla obciążenia, dochodzącego do 1000 kg/s/m 2 , przy czym nie podają jaki katalizator został użyty. ...
... Z długością złoża jest ściśle związany czas przebywania materiału pędnego w strefie oddziaływania katalizatora. Analiza dostępnych wyników badań wskazuje, że zakres długości złóż zawiera się zwykle w przedziale 13 ÷ 152 mm [21,89]. Zakres średnic złóż mieści się w przedziale 12 mm (dla natężenia przepływu 5 g/s) [40] do 64 mm (dla 900 g/s) [58]. ...
The thesis presents the analysis of results of experimental investigation which was a part of the research on the catalytic decomposition of highly concentrated hydrogen peroxide. Manganese oxide ceramic supported catalysts were used in the framework of research. Test and preparation stands as well as test equipment were designed in order to perform the activity. Catalyst beds, similar to those used in rocket propulsion, were utilized in the investigation.
The main task was to assess the possibility of application of various heterogeneous ceramic supported catalysts to decompose 98% hydrogen peroxide inside unheated catalyst beds of mono- and bipropellant rocket engines. In order to perform the activity, the number of catalysts supported mainly on α- and γ-alumina were prepared. The active phase for these catalysts were manganese oxides, doped with oxides of several transition metals.
The investigation consisted of four main stages. Initially 46 samples of catalysts were tested inside the catalyst chamber using the unified procedure and test sequence. That enabled to compare performance and select those catalysts that met defined criteria with the highest score. Selected catalysts were then applied to the second stage of the investigation that was performed using a new test setup. The crucial stage of the activity was to define, prepare and test composite catalyst beds. These structures were made by layered distribution of various ceramic supported catalysts, separated by wire mesh screens. Finally the lifetime test of one selected catalyst bed configuration was performed in order to assess the possibility of application of such a structure in a rocket engine.
Based on the results of the performed research the final conclusions were drawn. Further work for the extension of recent investigation was suggested as well.
The investigation was a part of the project "Research on composite catalyst beds for decomposition of hydrogen peroxide to be applied in a monopropellant thruster", funded by the European Space Agency in the framework of PECS programme. The project was realized in the Institute of Aviation by the research team from Space Technology Department.
... Liquid hydrogen peroxide is injected via an injector head (prepared filter element from Swagelok) and reacts to oxygen and steam under the presence of a catalyst. [119]. Based on this analysis, a square channel shape was chosen with a side wall length, S, of 1.mm. ...
... In the field of miniature HP thrusters, Scharlemann et al. 9 have developed a prototype operating with a monolithic catalyst able to significantly reduce the pressure drop across the catalytic bed compared to pellet configurations. The advanced catalyst has been able to decompose up to 1.2 kg of H 2 O 2 for a total catalyst lifetime of 1.25 hrs and a total impulse of 1600 Ns. ...
The present paper illustrates the results of an experimental campaign carried out using CZ-11-100 catalyst developed by ALTA S.p.A. in collaboration with the Department of Industrial Chemistry and Material Engineering of the University of Messina. It represents an unusual and innovative application of a Pt/Ce0.6Zr0.4O2/Al2O3 catalyst to H2O2 decomposition in rocket thrusters. The CZ-11-100 and the already tested CZ-11-600 catalysts differ in their pellets sizes, respectively 100 μm and 600 μm. The catalytic bed has been integrated into a hydrogen peroxide monopropellant thruster prototype and tested in ALTA's Green Propellant Rocket Test Facility. The bed has shown high decomposition and propulsive efficiencies, exhibiting C-Star efficiencies higher than 95%. The decrease in the pellets size has allowed for increasing the pressure drop across the catalytic bed with a consequent improvement of the cold start-up transient with respect to that experienced with the CZ-11-600 bed. © 2011 by the American Institute of Aeronautics and Astronautics, Inc.All rights reserved.
... Based on a similar philosophy as the bipropellant thruster, the development of a monopropellant thruster was initiated [23,24]. Although a monopropellant thruster delivers less specific impulse than a bipropellant thruster, it offers a lower system complexity. ...
The increasing application of microsatellites (from 10 kg up to 100 kg) as well as CubeSats for a rising number of various missions demands the development of miniaturized propulsion systems. Fotec and The University of Applied Sciences at Wiener Neustadt is developing a number of micropropulsion technologies including both electric and chemical thrusters targeting high performance at small scales. Our electric propulsion developments include a series of FEEP (field emission electric propulsion) thrusters, of which the thrust ranges from μN to mN level. The thrusters are highly integrated into clusters of indium liquid-metal-ion sources that can provide ultralow thrust noise and long-term stability. We are also developing a micro PPT thruster that enables pointing capabilities for CubeSats. For chemical thrusters, we are developing novel micromonopropellant thrusters with several hundred mN as well as a 1–3 N bipropellant microrocket engine using green propellants and high specific impulse performance. This paper will give an overview of our micropropulsion developments at Fotec, highlighting performance as well as possible applications.
... In the field of miniature HP thrusters, Scharlemann et al. 8 have developed a prototype operating with a monolithic catalyst able to significantly reduce the pressure drop across the catalytic bed compared to pellet configurations. The advanced catalyst has been able to decompose up to 1.2 kg of H 2 O 2 for a total catalyst lifetime of 1.25 hrs and a total impulse of 1600 Ns. ...
The present paper illustrates the results of an experimental campaign carried out using LR-III-106 catalyst developed by ALTA S.p.A. in collaboration with the Chemical Department of Pisa University. The catalytic bed has been integrated into a hydrogen peroxide monopropellant thruster prototype and tested in ALTA’s Green Propellant Rocket Test Facility. Endurance tests on LR-III-106 catalyst had been already performed with the same thruster prototype at a lower mass flux (G ≈ 12 kg/m2 s): the bed was able to decompose up to 13 kg of 90% hydrogen peroxide, equivalent to 2500 s of thruster continuous operation, exhibiting C-Star efficiency higher than 95%. The tests reported in the present paper have been aimed at investigating the performance of the catalyst and the thruster with a mass flux increased up to 55 kg/ kg/m2 s. The bed has shown high decomposition and propulsive efficiencies, well in excess of 90%. The cold start-up transient has been reduced to about 1 s, one order of magnitude lower than the previous obtained at lower G.
... The development of the Shell 405 catalyst and higher purity hydrazine led to a decreased use of HP due to the superior performance and long-term stability characteristics of hydrazine (Wucherer and Cook [4]). In the last decade HP has been receiving a renewed interest for application to cost and safety driven systems (Wernimont and Ventura [5], Scharlemann et al. [6]). Effective operation of HP monopropellant thrusters and gas generators is closely related to the availability of long-lived and reliable catalytic beds, able to provide repetitive performances both in continuous and intermittent operations. ...
The present paper illustrates different firing tests carried out on advanced catalytic beds for hydrogen peroxide decomposition in a new monopropellant thruster prototype designed for easier adjustment and control of the main operational and propulsive parameters. The tests refer to the comparison between a Pt/alpha-Al(2)O(3) catalyst (named FC-LR-87) and a similar commercially available space propulsion catalyst. Up to 2 kg of 87.5% hydrogen peroxide have been decomposed by a single sample of the FC-LR-87 catalyst. Both steady-state and pulsed firings have been carried out in the same reactor configuration. A fresh sample of the FC-LR-87 catalyst has also been tested at a different bed load. Both the FC-LR-87 and the commercial catalysts showed equivalent propulsive performances, with a slight advantage in favor of the FC-LR-87 catalyst in terms of the c* and temperature efficiencies (up to 94 and 93%, respectively).
... 7 Professor, Dipartimento di Chimica Industriale ed Ingegneria dei Materiali, Università di Messina; centi@unime.it 8 Professor, Dipartimento di Chimica Industriale ed Ingegneria dei Materiali, Università di Messina; perathon@unime.it T thrusters. ...
... T thrusters. In particular, both conventional alumina-based supports (extrudates, pellets, spheres) 6,7 and honeycomb monolith carriers 8 have been used for the preparation of catalysts. Under suitable conditions, the former supports can be directly impregnated using an active phase precursor, while the latter require surface impregnation of a thin and porous wash-coat layer, which is necessary to increase the relatively surface area of typical support materials, such as cordierite and mullite. ...
The capability of different Pt/Ce0.6Zr0.4/Al 2O3 catalytic systems of effectively decomposing H 2O2 has been studied in view of their application to monopropellant thrusters. BET surface area measurements, X-Ray Diffractometry (XRD) and Scanning Electron Microscopy (SEM) have been used together with catalytic tests in order to evaluate the advantages of using CeO 2-ZrO2 mixed oxide solid solution as an alternative to current three ways catalysts (TWCs). From the assessment of alternative solutions, a Pt/Ce0.6Zr0.4/Al2O3 catalyst suitable to effectively decompose H2O2 has been identified. SEM-EDX analyses ruled out the occurrence of phase segregation and selective deposition of Pt on Zr during the catalyst preparation. No changes in the crystalline arrangement of the catalyst samples after H2O 2 decomposition have been detected by XRD measurements, except for a slight crystallization or grain size growth as a consequence of the high temperatures experienced during the reaction. The use of Pt/Ce 0.6Zr0.4O2/Al2O3 catalysts for rocket-grade applications with much higher reaction rates than in automotive three-way converters has thus been successively demonstrated.
