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During this mode, the bypass is closed and all air is processed through the turbojet core. The exhaust nozzle (PCT patent pending) contracts in the subsonic mode for optimal specific thrust. As the engine accelerates to supersonic velocities, the articulated portions of the intake direct flow into the heat exchanger (PCT patent pending). Liquid hydrogen fuel is passed through the heat exchanger, decreasing the temperature of the air prior to engine compression. Some of the air bypass the turbojet core, and is mixed with the hydrogen exiting the heat exchanger in the afterburner section. Note that the magnitude of heat transfer is coupled to the amount of hydrogen available for combustion in the afterburner. The combustion products are then expanded through a supersonic nozzle, variable geometry nozzle. The engine will be designed to completely consume the air to optimize for thrust. The level of bypass changes throughout the supersonic flight regime. The engine can operate at Mach 4 and provide thrust in excess of a conventional ramjet. At high Mach numbers (~4.88) air cannot be cooled below the turbojet limit (1200K). As a result, no combustion can occur in the core turbojet and the engine must transition into a pure ramjet mode. The variable inlet continues to articulate (PCT patent pending) to completely block air access to the turbojet, while optimizing intake to exit area ratios for ramjet combustion using hydrogen. The engine still realizes an efficiency boost from the cooling effects of the heat exchanger (albeit much less in this mode). The terminal flight speed is limited to that of a hydrogen fueled ramjet.
390:
operate on multiple fuels (hydrogen, hydrocarbons, and metallic fuels). Each type of fuel has an advantage. The hydrocarbon fuel is typically used in turbojet/turbofan engines, which are considered mature/conventional technology. This engine will provide thrust at low-speeds. Hydrogen has a large heat capacity (~14 kJ/kgK), so it is an excellent heat sink for the heat exchanger (patent pending). It also has the best energy content per unit mass of any fuel and is a light molecule. As a result, it can provide large thrust levels with a low specific fuel consumption. Metallic fuel has excellent storage qualities, high energy content per unit volume, and can assist in convective heat transfer. It also has good combustion properties at nano-scale.
742:
stored at very high pressures, cooled cryogenically, or absorbed in other materials in order to accumulate a practical amount of mass. In contrast, metal particles can be packed and stored efficiently and safely. Since the overall rate of combustion is proportional to surface area, the use of smaller scale particles can improve combustion and increase engine performance. It has been found that nanoparticles typically have a lower melting point, ignite at lower temperatures, and have a higher burning rate than larger scale particles. Therefore, the use of a particle fuel or a particle supplement to a conventional fuel is being considered in SES's new aero-engine design.
689:
particles. Care must be taken to ensure that the hydrogen content stays below the lean flammability limit to prevent uncontrolled ignition before reaching the combustor. A 1:1 mass ratio mixture of nanoparticles and hydrogen will be injected into freestream to achieve 0.1% mass loading of nanoparticles and hydrogen in air. The injected mixture will cool the freestream air such that a gain in stagnation pressure is realized as the flow decelerates inside of the engine. Not only does heat transfer occur from the particles to the air, heat transfer will also occur along in the intake cone surface.
403:
hydrogen. It is clear that at the lower Mach number, the DASS engine provides a higher specific thrust. This is due to higher pressure that can be utilized by the turbojet. At Mach 4 the DASS GN1 performs similarly to a ramjet. At this speed, the DASS GN1 engine would likely convert to a pure ramjet. The specifications listed do not include any gains that might be realized through heat transfer on the intake cone (PCT patent pending), or from the combustion of metallic fuel. A typical rocket specific impulse is between 250 – 500 seconds.
720:
the nanoparticles act as small scale fins, which are known to improve heat exchanger effectiveness. Since these nano-scale fins are small, the pressure drop is also much less than when compared to the pressure losses of a large scale fin. This reduces the work requirements in pumping or compressing the fluid as it passes through the heat exchanger. The presence of surface roughness associated with nanoparticle deposits also promotes mixing, which directly affects convective heat transfer.
198:
369:(~200 km). Therefore, for the DASS Engine to operate beyond the target 30 km and Mach 5 operating conditions, the design will be modified. At higher altitudes the air density decreases and the vehicle must travel faster to achieve a sufficient inlet mass capture. At even higher altitudes, the DASS engine will need to store onboard oxidizer to be used with a
361:). The lower air density at these higher altitudes reduces the overall vehicle drag, which further improves efficiency. Current research and development is focused on engine operation at Mach 5 cruise at an altitude of 30 km. Note that 30 km is still significantly lower than what is considered to be the edge of space (
719:
Coating a solid body with nano-particles has been shown in the scientific literature to enhance the convective heat transfer rate from solid bodies. Several mechanisms have been proposed, including the increase in the overall surface area associated with nano-coating. Essentially, it is possible that
402:
The table below shows a comparison of the DASS engine to more conventional high-speed engines (Ramjet) at two Mach numbers. Two types of
Ramjets were considered. The first Ramjet uses a combination of fuels (Kerosene and hydrogen) in similar proportions as the DASS engine. The second Ramjet uses pure
741:
Metal powders have been considered as alternative fuels for air-breathing engines because of their large energy content per unit mass and per unit volume in comparison to liquid hydrocarbon fuels. Although hydrogen has a larger energy content per unit mass than metal fuels, hydrogen fuel needs to be
701:
The proposed structure of the heat exchanger is a nano-porous foam. The foam will strengthen the nano-porous structure while maximizing the heat transfer and minimizing the pressure drop. This in combination with the added effect of nano-particle dispersion should allow for a smaller heat exchanger.
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Some nanoparticles outperform hydrogen (per unit volume) and hydrocarbons (per unit mass and volume) in terms of energy storage. Two important metrics are the energy per unit mass and energy per unit volume. Vehicles are usually designed on a per unit volume basis (for drag considerations). On a per
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compared to rockets. That is why the DASS engine will be integrated into a lifting-body vehicle. For an SSTO vehicle, reduced vehicle mass and increased payload mass fraction translates to lower operation costs. For transport, the ability to travel at hypersonic speeds drastically decreases the time
176:
Space
Engines Systems Inc. was established in 2012 to develop the DASS engine and related technologies in the aerospace sector. Space Engine Systems's promoters have been involved in the development of the engine for over 20 years. work together to bring novel pumps, compressors, and gearbox systems
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The suspension of a large amount of small scale solid particles in a gas results in a large surface-area-to-volume ratio. Studies in the scientific literature have shown that there is a unique interaction between the properties of solid nanoparticles and those of carrier fluid. The result, which is
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At low flight speeds the DASS engine relies solely on the on-board turbojet that runs on a conventional hydrocarbon fuel. The variable geometry intake (PCT patent pending) allows large gaps to form between the heat exchanger (which is not operating at this stage), minimizing intake pressure losses.
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Only a small amount of nanoparticles are required to provide the heat transfer gains required by the engine. It was found that even with very small mass loadings (0.1%), large gains in heat transfer can be achieved (40%). Therefore, it is feasible to use the available hydrogen as a carrier for the
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Space Engine
Systems is developing a ground testing facility capable of simulating high temperature inlet flow at high altitudes associated with supersonic flight. The facility, named the Multi-Fuel Jet Engine testing facility, is highly modular and can easily be adapted for many applications. The
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The goals of the DASS GN X and DASS GN1 engines are to provide efficient thrust from rest up to hypersonic speeds (M~5) and high altitudes (h~30 km) with a low specific fuel consumption along the entire flight path, and a small rocket stage to bring the vehicle into orbit. The engine will
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Major technology hurdles for the DASS engine are related to the implementation of nanotechnology in the engine components. In a partnership with the
University of Calgary, SES will assess the feasibility of using surface nano-coatings on the heat exchangers, study the effect of nanoparticle
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unit volume basis, Boron outperforms both hydrogen and hydrocarbons. On a per unit mass basis, Boron outperforms hydrocarbon fuels but is not as good as hydrogen. Therefore, the DASS engines will take advantage of the excellent properties of Boron along with hydrocarbon, and hydrogen fuels.
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not observed with larger scale particles (i.e. micron), is the alteration of the properties of the bulk fluid. For example, Lee et al. (1999) and Wang et al. (1999) have shown, experimentally, that the suspension of 24 and 23 nm diameter CuO particles in water enhance the
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Key technology components of the DASS GN 1 and DASS GN X are quite similar. The DASS GN1 is meant exclusively for aerospace and the DASS GN X is meant for space applications only. An engine prototype is planned for ground and flight testing.
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S. Satyapal; J. Petrovic; C. Read; G. Thomas & G. Ordaz (2007). "The U.S. Department of Energy's
National Hydrogen Storage Project: Progress towards meeting hydrogen-powered vehicle requirements". Catalysis Today, Vol. 120, pp.
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Specialized planetary gear box (ultra-light) with capability to run up to 420 deg
Celsius ambient temperature (tested for 45 minutes under full load and oil completely pulled out by vacuum). No metallurgical or mechanical
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to further enhance heat transfer. The particles act as a supplemental fuel and assist the operation of flow control devices downstream. It is known that metallic fuels have desirable storage properties in comparison to
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suspensions on convective heat transfer, and assess the feasibility of using metallic nanoparticles as a supplemental fuel. The
Canadian Government (through NSERC funding) is also a partner in the DASS Engine project.
181:(July 9–15, 2012). On August 6, they announced their participation in the AUVSI's Unmanned Systems North America. SES frequently attends major international trade shows in the aerospace sector including the
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Working with the CAN-K Group of
Companies, SES offers a selection of aerospace components and services. All manufacturing is done to AS 9100 C and ISO 9001 quality management standards. Products include:
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One of the main challenges is to develop a technique to inject the nano-particles in a manner which promotes homogeneous mixing. Second, characterize the heat transfer properties of the flow mixture.
1187:
R. Senthilkumar; A. Nandhakumar & S. Prabhu (2013). "Analysis of natural convective heat transfer of nano coated aluminum fins using
Taguchi method". Heat and Mass Transfer Vol. 49, pp. 55-64.
1219:
S. Kumar; S. Suresh & K. Rajiv (2012). "Heat transfer enhancement by nano structured carbon nanotube coating". International
Journal of Scientific and Engineering Research Vol. 3, pp. 1-5.
235:. The engine is being developed with the flexibility for various vehicles and mission profiles. The concept uses existing aerospace technologies, including conventional
1266:
S. Lee; S. Choi & J. Eastman (1999). "Measuring thermal conductivity of fluids containing oxide nanoparticles". Trans. ASME J. Heat Transfer, Vol. 121, pp. 280-289.
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Y. Huang; G. Risha; V. Yang & R. Yetter (2009). "Effect of particle size on combustion of aluminum particle dust in air". Combustion and Flame, Vol. 156, pp. 5-13.
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required to cover long distances. The altitude at which hypersonic cruise vehicles operate is usually much higher than conventional transporters (30 km for A2 vs
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downstream of the inlet in order to reduce gas temperatures prior to mechanical compression. Similar to the deep-cooled turbojet or the liquefied air cycle engine (
1363:
R.A. Yetter; G.A. Risha & S.F. Son (2009). "Metal particle combustion and nanotechnology". Proceedings of the Combustion Institute, Vol. 32, pp. 1819–1838.
995:
W. Heiser (2010). "Single-Stage-to-Orbit Versus Two-Stage-to-Orbit Airbreathing Systems". AIAA Journal of Spacecraft and Rockets, Vol. 47, No.1, pp. 222-223.
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The DASS engine concept improves upon the heat exchange process in multiple ways. Surface nano-coatings are placed on the internal heat exchangers to enhance
877:
846:
1298:
X. Wang; X. Xu & S. Choi (1999). "Thermal conductivity of nanoparticle-fluid mixture". J., Thermophys. Heat Transfer, Vol. 13, pp. 474-480.
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140:. The main focus of the company is the development of a light multi-fuel propulsion system (DASS Engine) to power a reusable spaceplane and
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of water by 34%. SES will investigate the potential enhancement of the thermal conductivity of gases with suspended nanoparticles.
156:, and other related technologies being developed are integrated into SES's major R&D projects. SES has collaborated with the
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Trivedi, Maulin; Jagannathan, Rangesh; Johansen, Craig (2016-07-17). "Convective Heat Transfer Enhancement with Nanoaerosols".
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to the aerospace industry as spin off applications. On May 10, 2012, SES publicly announced the launch of their company at the
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641:• Direct Connect System to supply high temperature air flow to the engine to simulate supersonic air flow up to Mach 5.
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644:• Fuel System to supply multiple fuels to the engine, including liquid hydrogen, jet fuel, and solid nano-particles.
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275:), energy extracted from the incoming air in the DASS engine is added back into the system downstream as
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337:. These gains have the potential to realize a larger payload mass fraction (e.g. 4% for NASP to LEO vs
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Combined propulsion for SSTO rocket – From conceptual study to demonstrator of deep cooled turbojet
957:
S. Goroshin; A. Higgins & M. Kamel (2001). "Powdered metals as fuel for hypersonic ramjets".
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to overcome some of the key technical obstacles associated with overheating and fuel storage. In
920:. Space Plane and Hypersonic Systems and Technology Conference, AIAA-96-4497 Norfolk, Virginia.
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Hydraulic multiple screw pumps for automatic torque changer or other aerospace applications;
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for high-speed flight is the use of atmospheric oxygen in its air-breathing mode. The
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rates, reduce heat exchanger mass, and reduce unwanted aerodynamic blockage. Metallic
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961:. 37th Joint Propulsion Conference and Exhibit, AIAA-2001-3919 Salt Lake City, Utah.
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Liquid/multiphase twin screw and three screws pump for aerospace/space applications;
647:• Measurement Suite to allow data collection and analysis of all tested equipment.
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associated with air-breathing engines is a major motivation for the development of
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Permanent Magnet motor system adaptable for aerospace and space requirements;
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The Multi-Fuel Jet Engine testing facility can be used to better understand:
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when operating in the airbreathing mode before switching to the rocket mode.
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Aerospace and space sub-assemblies custom made to customer's requirements;
656:• Temperature limitations of various turbine engine materials/components
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concept that can produce thrust over a wide range of vehicle flight
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Nanocoatings and ultra-thin films: technologies and applications
659:• Multi-fuel combustion (conventional, solid, and rocket fuels)
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in its flow path. The target is to achieve a major component of
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Drive systems with sophisticated constant velocity (CV) joints;
223:). Derivatives of the engine can be used for propulsion of an
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to study and develop technologies in key technical areas of
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13th International Energy Conversion Engineering Conference
1087:"Forced Convective Heat Transfer in Al2O3-air Nanoaerosol"
1042:. 2nd European Conference For Aerospace Sciences (EUCASS)
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F. Jivraj; R. Varvill; A. Bond & G. Paniagua (2007).
259:. Temperatures can rise above the material limits of the
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The main advantage of the DASS engine over conventional
267:. A strategy to alleviate this problem is to place a
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Makhlouf, Abdel Salam Hamdy; Tiginyanu, Ion (2011).
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Custom light weight and high temperature materials;
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251:and aerodynamic deceleration results in a rise in
916:V. Balepin; J. Cipriano & M. Berthus (1996).
1137:International Journal of Heat and Mass Transfer
780:Vacuum operational equipment (custom designed);
774:Custom bearings (hydrodynamic and hydrostatic);
352:. Airbreathing engines typically have a lower
1253:Fundamentals of Heat and Mass Transfer 4th Ed
8:
959:37th Joint Propulsion Conference and Exhibit
674:• Engine test-stand and mounting mechanisms
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1166:(Illustrated ed.). AIAA. p. 587.
311:are being considered as the engine's fuel.
984:. AIAA Educational Series. pp. 20–21.
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724:Nanoparticle suspensions for heat transfer
668:• Thrust characteristics at high altitude
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1085:Trivedi, Maulin; Johansen, Craig (2015).
1149:10.1016/j.ijheatmasstransfer.2016.07.017
759:High-speed gear box for turbine engines;
715:Surface nano-coatings on heat exchangers
518:
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303:on a per volume basis. A combination of
290:are seeded into the intake air from the
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795:DASS Lander for space applications; and
653:• Pre-cooled combined cycle propulsion
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1037:"The Scimitar Precooled Mach 5 Engine"
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876:: CS1 maint: archived copy as title (
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665:• Engine start modes at high altitude
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350:supersonic combustion ramjet engines
239:components, and new developments in
818:Space Engine Systems Inc. Main Page
762:Efficient and light heat exchanger;
247:, the incoming air has a very high
1251:Incropera, F.; DeWitt, D. (1996).
1164:Hypersonic Airbreathing Propulsion
982:Hypersonic Airbreathing Propulsion
943:. Woohead Publishing in materials.
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746:Specialized products and services
531:Specific Fuel Consumption (g/kNs)
418:Specific Fuel Consumption (g/kNs)
333:to rockets over a wide range of
185:in 2013, 2015, and 2017 and the
681:Incorporation of nanotechnology
329:) of air-breathing engines are
980:Heiser, W.; Pratt, D. (1994).
520:Engine Comparison at Mach = 4
407:Engine Comparison at Mach = 2
1:
892:"Space Engine Systems - News"
233:hypersonic transport aircraft
201:The DASS GN 1 engine concept
798:Nano oil for long term use.
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1061:"Hydrogen – Specific Heat"
777:High temperature bearings;
662:• Multi-fuel afterburners
128:company and is located in
16:Canadian aerospace company
263:blades in a conventional
189:in 2014, 2016, and 2024.
118:Space Engine Systems Inc.
20:Space Engine Systems Inc.
671:• By-pass ratio control
284:convective heat transfer
72:Pradeep Dass (President)
737:Nanoparticle combustion
677:• Flow characteristics
633:Ground Testing Facility
339:2.6% for Soyuz-2 to LEO
166:high-speed aerodynamics
100:Permanent Magnet Motors
1016:Cite journal requires
365:) and much lower than
354:thrust-to-weight ratio
202:
110:SpaceEngineSystems.com
1434:Single-stage-to-orbit
528:Specific Thrust (m/s)
415:Specific Thrust (m/s)
307:and nanoparticles of
205:The DASS engine is a
200:
158:University of Calgary
731:thermal conductivity
279:in the fuel stream.
227:vehicle, long-range
187:Farnborough Air Show
179:Farnborough Air Show
1102:10.2514/6.2015-3799
1065:Engineering Toolbod
1001:10.2514/6.2001-3919
967:10.2514/6.2001-3919
926:10.2514/6.1996-4497
638:facility includes:
525:Engine (28 km)
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299:and have excellent
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217:Mach numbers
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53:Headquarters
25:Company type
257:temperature
237:gas turbine
193:DASS engine
150:compressors
92:compressors
1410:|url=
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1111:1880/51125
1046:2014-07-01
902:2014-07-09
863:2014-07-09
803:References
583:Kerosene/H
470:Kerosene/H
292:inlet cone
261:compressor
221:hypersonic
213:propulsion
207:pre-cooled
154:gear boxes
142:hypersonic
96:gear boxes
84:propulsion
68:Key people
219:(rest to
126:aerospace
86:systems,
39:Aerospace
1428:Category
1401:cite web
1369:cite web
1337:cite web
1331:246-256.
1304:cite web
1272:cite web
1225:cite web
1193:cite web
1096:: 3799.
1070:27 April
872:cite web
706:Research
563:DASS GN1
450:DASS GN1
331:superior
305:hydrogen
297:hydrogen
265:turbojet
229:missiles
130:Edmonton
77:Products
35:Industry
756:damage;
134:Alberta
106:Website
45:Founded
29:Private
1170:
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611:Ramjet
587:Ramjet
498:Ramjet
474:Ramjet
363:100 km
231:, and
138:Canada
61:Canada
1090:(PDF)
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626:3786
602:3383
578:3410
513:3569
489:2654
465:3299
309:Boron
146:Pumps
88:pumps
1414:help
1382:help
1350:help
1317:help
1285:help
1238:help
1206:help
1168:ISBN
1116:ISBN
1072:2016
1022:help
878:link
620:18.0
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614:3.65
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445:(s)
273:LACE
255:and
225:SSTO
164:and
81:SSTO
48:2012
1145:doi
1141:102
1106:hdl
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546:max
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