type private industry aerospace founded 2012 headquarters edmonton canada key people pradeep dass president products ssto propulsion systems pumps compressors gear boxes permanent magnet motors website spaceenginesystems.com space engine systems inc. ses is a canadian aerospace company led by pradeep dass and is located in edmonton alberta canada . 1 the main focus of the company is the development of a light multi fuel propulsion system dass engine to power a reusable single stage to orbit ssto and hypersonic cruise vehicle . pumps compressors gear boxes and other related technologies being developed are integrated into ses s major r & d projects . ses is collaborating with the university of calgary to study and develop technologies in key technical areas of nanotechnology and high speed aerodynamics . contents 1 company history 2 dass engine 2.1 engine details 2.2 engine comparison 2.3 incorporation of nanotechnology patent pending 2.4 heat exchanger patent pending 3 research 3.1 surface nano coatings on heat exchangers 3.2 nanoparticle suspensions for heat transfer 3.3 nanoparticle combustion 4 specialized products and services 5 references company history edit space engines systems inc. was established in 2012 by pradeep dass and other investors to develop the dass engine and related technologies in the aerospace sector . pradeep dass has been involved in the development of the engine for over 20 years . ses and the can k group of companies 2 work together to bring novel pumps compressors and gearbox systems to the aerospace industry as spin off applications . on may 10 2012 ses publicly announced the launch of their company at the farnborough air show july 9 15 2012 . 3 on august 6 they announced their participation in the auvsi s unmanned systems north america . 4 ses frequently attends major international trade shows in the aerospace sector including the paris air show in 2013 and the farnborough air show in 2014 . dass engine edit the dass gn 1 engine concept the dass engine is a pre cooled combined cycle propulsion concept that can produce thrust over a wide range of vehicle flight mach numbers rest to hypersonic . derivatives of the engine can be used for propulsion of an ssto vehicle long range missiles and hypersonic transport aircraft . the engine is being developed with the flexibility for various vehicles and mission profiles . the concept uses existing aerospace technologies including conventional gas turbine components and new developments in nanotechnology to overcome some of the key technical obstacles associated with overheating and fuel storage . in high speed flight the incoming air has a very high dynamic pressure and aerodynamic deceleration results in a rise in static pressure and temperature . temperatures can rise above the material limits of the compressor blades in a conventional turbojet . a strategy to alleviate this problem is to place a heat exchanger downstream of the inlet in order to reduce gas temperatures prior to mechanical compression . similar to the deep cooled turbojet 5 or the liquefied air cycle engine lace energy extracted from the incoming air in the dass engine is added back into the system downstream as sensible heat in the fuel stream . the dass engine concept improves upon the heat exchange process in multiple ways . surface nano coatings 6 are placed on the internal heat exchangers to enhance convective heat transfer rates reduce heat exchanger mass and reduce unwanted aerodynamic blockage . metallic nanoparticles are seeded into the intake air from the inlet cone 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 hydrogen and have excellent energy densities on a per volume basis . 7 a combination of hydrogen and nanoparticles of boron are being considered as the engine s fuel . the main advantage of the dass engine over conventional rocket engines for high speed flight is the use of atmospheric oxygen in its air breathing mode . the specific impulse isp of air breathing engines are superior to rockets over a wide range of mach numbers . these gains have the potential to realize a larger payload mass fraction e.g. 4 % for nasp to leo 8 vs 2.6 % for soyuz 2 to leo . the higher isp associated with air breathing engines is a major motivation for the development of supersonic combustion ramjet engines . airbreathing engines typically have a lower thrust to weight ratio 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 . 9 for transport the ability to travel at hypersonic speeds drastically decreases the time required to cover long distances . the altitude at which hypersonic cruise vehicles operate is usually much higher than conventional transporters 30 km for a2 10 vs 13.1 km for a380 . 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 100 km and much lower than low earth orbit 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 rocket motor in its flow path . the target is to achieve a major component of orbital velocity when operating in the airbreathing mode before switching to the rocket mode . engine details edit 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 patent pending allows large gaps to form between the heat exchanger which is not operating at this stage minimizing intake pressure losses . during this mode the bypass is closed and all air is processed through the turbojet core . the exhaust nozzle 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 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 can not 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 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 . 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 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 11 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 . 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 . engine comparison edit 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 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 patent pending or from the combustion of metallic fuel . a typical rocket specific impulse is between 250 500 seconds . engine comparison at mach 2 engine 10 km specific thrust m s specific fuel consumption g kns tmax to pmax po isp s dass gn1 4.23 30.9 15.1 23.9 3299 kerosene h2 ramjet 3.41 38.4 15.1 6.0 2654 h2 ramjet 3.44 28.5 15.6 6.0 3569 engine comparison at mach 4 engine 28 km specific thrust m s specific fuel consumption g kns tmax to pmax po isp s dass gn1 3.67 30.0 17.8 228 3410 kerosene h2 ramjet 3.64 30.1 17.8 57 3383 h2 ramjet 3.65 26.9 18.0 57 3786 incorporation of nanotechnology patent pending edit 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 . 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 % . 12 therefore it is feasible to use the available hydrogen as a carrier for the 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