MICROWAVE THERMAL ROCKETS
LASER THERMAL ROCKETS
Microwave and laser thermal rocket engines bypass the fundamental energy density limits of chemical propellants by using energy that is transmitted from the ground. The energy heats a layer (a heat exchanger) on the underside of the rocket, and this layer in turn heats an inert fluid that is used to propel the rocket.
Traditional rockets are marginal at space launch because traditional chemical propellants have too little energy to propel their own mass into orbit, let alone a tank and payload on top of that. To reach orbit at all, traditional rockets must jettison parts (stages) as they ascend. Traditional chemical propellants release their energy through combustion, but flowpaths must be exhaustively designed and tested to preclude explosions and instabilities, and to withstand corrosion at extreme temperatures and pressures.
By swapping traditional propellants for inert monopropellants, and combustion chambers for heat exchangers, rockets can be made safer and cooler, yet so energetic that they lift payloads to orbit in a single stage. They can lift so much more payload that costs fall from $10,000 per kilogram delivered to low earth orbit to less than $1,000/kg. For reusable rockets, payload costs fall from $3,000/kg to less than $300/kg. Whatever you believe conventional rockets will cost in the future, thermal rockets are an upgrade that offers the next level of economy, safety, and performance.
WHY ARE THEY NEEDED?
The U.S. government alone spends $170M per week on launch-related activities (GAO-13-802R). Of this, 25% is spent on R&D, and 75% on building rockets, launching them, and related non-R&D activities. Despite this remarkable and ongoing level of expenditure, the U.S. government launches payloads into orbit the same way it did in 1958; by chemical rockets. So does everyone else, for now.
Traditional chemical rockets achieve payload fractions of less than 4.2%. The rocket equation shows how this results from the relatively low specific impulse (Isp) of chemical propellants, which long ago reached a practical limit of 460 seconds by reacting hydrogen with oxygen. The LOX/LH2 reaction releases 16 MJ per kilogram of propellant mixture, whereas the specific energy of low earth orbit (LEO) is 32 MJ/kg. Traditional chemical rockets reach orbit only because the propellants they expel make them lighter as they go. Additionally, they have to be structured into multiple stages so that structural mass is periodically jettisoned as well. Even then, a slightly heavier-than-anticipated structure can displace the entire payload mass.
The price of payload delivery to low earth orbit (LEO) as a function of rocket payload capacity.
The price of launch remains above $10,000 per kilogram of payload delivered to low earth orbit for most models of rocket, as shown in the interactive chart above (click ‘1’ or ‘0’ to show or hide layers). The data points are rockets from many countries spanning 60 years and representing hundreds of billions of dollars in evolutionary R&D investment. In contrast, the payload’s energy would cost less than $1 per kilogram if it could magically be imparted to the payload. In practice, the energy cost of launch for a thermal rocket is below $100 per kilogram of payload, and potentially as low as $10 per kilogram.
Forms of propulsion organized by the main metrics of T/W ratio and Isp. Data points are actual engines, grouped by type.
Thermal rockets bypass key limitations of traditional chemical rockets, and in so doing are easily able to reach orbit using a single stage, as opposed to the traditional two to four stages. A microwave or laser thermal propulsion system combines the specific impulse of a nuclear thermal rocket engine with the thrust to weight ratio of a conventional rocket engine, and the result on system performance is profound: For a given rocket, the payload mass is 3-12 times heavier. In addition to this direct effect, which can be shown using the rocket equation, it saves additional money to use one propellant instead of two, and one stage instead of two to four stages. The combined effect is that the overall cost is 6-144 times cheaper than a conventional rocket, depending on the particular assumptions made.
ORIGINS OF THE 4 MAIN TYPES OF DIRECTED ENERGY PROPULSION
Konstantin Tsiolkovsky, the first to derive the rocket equation in 1897, proposed directed energy rocket launch via a “parallel beam of shortwave electromagnetic rays” in 1924 (Tsiolkovsky 1924). The two-pole magnetron had been invented only three years earlier, and the time average power output at that time was so low that it would take the coherently combined output of millions of such devices to power a microsatellite-class rocket to orbit. In his 1924 book, Tsiolkovsky estimated that, due to diffraction, a ground-based beam director required an aperture diameter of 12.6 km to produce a beam concentrated enough. He wondered how any receiving material could withstand the intense heat generated by the beam, and how it could be directed onto a rocket as it ascends to orbit, eventually concluding that “This method of imparting velocity raises quite a few difficult problems, the solution of which I shall leave to the future.”
In 1959, Willinski proposed for the first time a vehicle wherein “beamed power would be utilized to heat a propulsion fluid, such as hydrogen, ammonia, gasoline, or even water, which would then be expanded through a nozzle to produce thrust” (Willinski 1959). Noting the problems of large apertures and beam diffraction at longer wavelengths, and the opposing problem of atmospheric absorption at wavelengths shorter than 10 cm, Willinski dwelled predominantly upon a receiving antenna in the form of a large inflated balloon capable of focusing microwaves onto a central heat exchanger. Due to drag, the vehicle was constrained to operate as an upper stage above the atmosphere. Significantly, Willinski mentioned that “the skin of the vehicle itself could possibly be utilized as a surface antenna, thereby allowing operation in the atmosphere.” This line of reasoning is consistent with the later microwave lightcraft (Myrabo 1995).
In 1972, the idea of using a pulsed laser to propel rockets to orbit was proposed separately by Kantrowitz and Minovitch (Kantrowitz 1972, Minovich 1972). The laser had been invented only 12 years earlier, yet it took another 20 years before laser thermal rockets, shown on the bottom left of the figure below, were proposed by Jordin Kare (Kare 1992). The lower cost of microwaves relative to lasers motivated Kevin Parkin to invent the microwave thermal rocket in 2002 (Parkin and Culick 2003, Parkin, DiDomenico et al. 2003).
The four main approaches to directed energy propulsion form a grid. The bottom right approach was proposed in 1972 (Kantrowitz 1972, Minovich 1972), the bottom left in 1992 (Kare 1992), the top left in 2002 (Parkin, Culick et al. 2002), and the top right in 2003 (Oda, Nakagawa et al. 2003).
MICROWAVE VS. LASER
The case for microwave thermal rockets
Long wavelength microwaves sources led Tsiolkovsky and others to estimate aperture sizes exceeding a kilometer. After a century of microwave development, high-power short-wavelength sources now enable aperture sizes on the order of 100 meters and increase the beam irradiance at which plasmadynamic breakdown occurs by several orders of magnitude. At this time, microwaves have the advantage of being one to four orders of magnitude cheaper than lasers on a $/Watt basis ($0.1-10/Watt vs. $100-1,000/Watt), and they are unaffected by atmospheric scintillation and more tolerant to weather, particularly at the lower frequencies below 35 GHz.
The case for laser thermal rockets
In recent years, the cost per Watt of lasers has fallen, and there is no fundamental reason why they cannot be as cheap or cheaper than microwave sources. Commercially-available fiber lasers have high energy efficiency and do not require the high voltage power supplies that vacuum microwave sources do. Due to the shorter wavelength, lasers can employ a 1-meter primary aperture as opposed to 100 meters for microwaves. Not all the power is sent through a single aperture, and many such beam modules are trained on the rocket. This has the benefit of reducing thermal blooming, and unlike microwaves, the beam modules do not need to be in phase.
The case for both
Both approaches can work, there is a compelling need, and the minimum-risk strategy is to pursue both laser and microwave approaches. That gets results soonest without prejudging which approach will ultimately be economically superior. It is possible to develop a flexbeam thermal rocket that can be powered by laser or microwave sources, depending on what beam director is available at the time.
HOW IT WORKS
The current concept benefits from 16 years of feedback and design evolution. A single foil balloon tank holds a slush methane propellant. This propellant is then pumped through the heat exchanger, reaching close to the temperature of an incandescent light bulb filament just prior to being expanded through a plug nozzle to produce thrust. The beam tracks the heat exchanger, which faces the general direction of the beam throughout the ascent to orbit. There is only a single propellant, single tank, single turbopump, and single stage all the way from the ground to orbit.
Concept of how a microwave (or laser) thermal rocket will operate
The concept of operations for a microwave (or laser) thermal rocket is shown above. In the simplest implementation, launch begins from the ground and begins vertically upwards. After a short time, a long-range beam director acquires the rocket. The rocket turns and accelerates horizontally until it reaches orbit, and then the payload is released.
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A beam heats prototype heat exchanger tubes to > 2,000 K for the first time in tests conducted on the 13 August 2013 at the General Atomics DIII-D Fusion Reactor in San Diego as part of the DARPA-NASA Millimeter-wave Thermal Launch System Program.
The video above was a key milestone during a test campaign using a 110 GHz beam at the General Atomics DIII-D Fusion Reactor in San Diego California. This was the first time that Mullite heat exchanger tubes were heated to very nearly their melting point by the beam, thanks to an idea to coat them internally with a thin layer of graphite to act as an absorber. These tubes were used as the basis for a heat exchanger that was mounted to a small rocket and launched to just a few tens of meters altitude in early 2014. With refinement, their performance should be sufficient for the orbital rocket. Such tubes can be modified to absorb laser light as well.
WHAT IS THE ECONOMIC/BUSINESS CASE?
The feasibility and performance of microwave and laser thermal rockets are supported by many analyses over the past 16 years sponsored by Caltech, NASA, DARPA and the U.S. Air Force. Over this time, various methods have estimated that microwave and laser thermal rockets can reduce launch costs by one to two orders of magnitude. We periodically add new estimates, but there is little new to be gained and each week of delay costs $60-125M. Consequently, our focus has shifted to minimizing the infrastructure cost of an initial system. This focus on infrastructure begs the question; over a given payback period, how low must the initial infrastructure cost be for a directed energy launch to make economic/business sense?
Initial infrastructure cost is currently driven by the beam director cost, which itself is comprised of the cost of the microwave or laser sources plus the cost of reflecting aperture. Initial infrastructure cost can be expressed in $/Watt and is its most important figure of merit. The $/Watt value at which directed energy thermal launch becomes economically superior to present launch systems is calculated below under various assumptions and over a payback time of 20 years.
In the baseline case above, there continues to be no directed energy thermal launch system, and 100% of the market is served by families of traditional chemical rockets, the largest of which is capable of launching a 20 metric ton satellite to LEO. The cost of launch to continues to be $125M/week for the U.S. Government, excluding R&D. This equates to a $130Bn expenditure over the 20-year period.
In the pessimistic case, a directed energy thermal rocket with a 200 kg payload capacity to LEO captures 1% of the total revenue for satellite launch. It has a relatively poor jet power per unit payload mass (though not the worst), and a relatively poor cost reduction factor. Consequently, its initial infrastructure needs to cost less than $2/Watt in order to save money over the period. Current estimates of beam director cost are $1-5/Watt at this scale, and further research is expected to lower this value and its associated uncertainty.
In the optimistic case, a family of directed energy thermal rockets capable of launching up to 20 tons to LEO captures 100% of the revenue for satellite launch, replacing traditional rockets altogether. They have a relatively good jet power per unit payload mass (though not the best) and a relatively good cost reduction factor. Consequently, the initial infrastructure needs to cost less than $22/Watt in order to save money over the period. Current estimates of beam director cost are one to two orders of magnitude below this value, depending in part on the choice of frequency.
The interpretation of these results is that a business case does not yet exist for a 200 kg directed energy thermal launch system that fits within the cost, risk and schedule of private capital. More work is needed to lower technical risks, and in particular to define the beam director and constrain its associated costs. That being said, the economic case to replace traditional rockets with directed energy thermal rockets is compelling, and there is every reason for the U.S. Government to make substantial R&D investments toward the initial goal of a small directed energy thermal launch system. This would be a technology push without regard to the cost impact on launching small satellites, since the overwhelming economic compulsion originates from the rest of the market.
THE BOTTOM LINE
FREQUENTLY ASKED QUESTIONS
WHAT IS THE MAXIMUM PAYLOAD?
There is no maximum payload mass for the microwave thermal rocket. The launch system, which includes the beam director, can be scaled up to launch all payload classes, through 1 metric ton payloads and even above 100 ton payloads, if needed. Once a system is built that can launch small satellites, there is every reason to scale it up.
WHAT IS THE MAXIMUM BEAM DIRECTOR SIZE/POWER?
Due the physics of beam diffraction, beam directors become smaller as the rocket size (and payload capacity) increases. For these, the limiting factor is power density, or, depending on the way in which microwave sources are combined to form a single beam, it can be spectral characteristics that limit the number of microwave sources per beam director. However, these limits are for a single beam director. Once one beam director has been built, there is no reason a second cannot be built and reuse the same spectrum. Both can then be trained on a single rocket designed for double the power, and due to efficiencies of scale, the rocket payload mass will more than double. Any number of beam directors can be trained on a single rocket in the same way that overlapping spots from flashlights do.
WHAT IS THE MINIMUM BEAM DIRECTOR SIZE/POWER?
Due to the physics of beam diffraction, beam directors become larger as the rocket size (and payload capacity) decreases. Above a certain aperture size, it minimizes the overall cost to build more microwave sources and spill more energy than to further increase the beam director size. Curves for cost-minimized beam directors have been plotted and it turns out that lighter rockets always result in a cheaper beam director.
HOW MUCH POWER DOES IT TAKE?
10 MW of ‘wall plug’ power per kg of payload for the lightest rockets, falling to below 1 MW/kg for the heaviest rockets. This is because the payload fraction and transmission efficiency both improve as the rockets become heavier.
HOW MUCH OF THE PAYLOAD COST IS FOR POWER?
$10-100 per kilogram of payload, depending on electricity cost, the choice of propellant and the maximum temperature that it can be heated to, and the efficiency of energy transfer to the rocket, which increases with payload size.
HOW IS THAT MUCH POWER GENERATED?
The power needed by the thermal rocket engines is comparable with the power developed in conventional rocket engines of the same thrust, though of course this power is generated on the ground for thermal rockets. Up to 2 GW can be obtained directly from the electrical grid for beam directors that are located near to high capacity transmission lines, for example in California, and this is enough to launch a rocket with a payload of about 100 kg. This power would cost on the order of 10¢/kWh. For heavier payloads, on-site pulsed power is used. Several of the technologies used or being developed for grid energy storage, such as batteries and flywheels, are suitable for the beam director site. For these technologies, the amortized cost adds < 3¢/kWh to the electricity cost (Viswanathan, Kintner-Meyer et al. 2013). Capital cost is on the order of $1/Watt. In comparison, the capital cost of a solid-state microwave source is $0.5-10/Watt, and the capital cost of a millimeter-wave source (i.e. a gyrotron) including its power supply and supporting equipment is around $5/Watt. Costs will be reduced by further R&D and/or as production quantities increase.
IS PLASMADYNAMIC BREAKDOWN A PROBLEM?
At very high beam intensities, the atmosphere breaks down into a plasma, and this type of intensity limit was shown to be orders of magnitude greater than that needed for small satellite launchers (Parkin 2006). It is possible to approach this limit with very heavy payload rockets, but this is not really a limit either, as it is always possible to flatten the rocket and increase the receiving area to keep the beam intensity well below the breakdown threshold.
HOW IS THE ROCKET AND PAYLOAD SHIELDED FROM THE BEAM?
By metal foil. Aluminum kitchen foil is easily thick enough, and there are standard techniques to ensure that microwaves don’t propagate through holes or along any external cables or tubes through to the payload.
WHAT IF A BIRD/PLANE FLIES INTO THE BEAM?
Beam directors are located at arid, high-altitude sites in controlled airspace where there are few birds. If a bird flew just above the beam director during operation, the power density it would experience is 1,000 times lower than at the rocket, which is well above the altitudes of birds and planes. The bird would initially experience a growing sensation of heat on its underside, somewhat like opening an oven door, and would flee, it is hoped, in a different direction. The vicinity of the beam is monitored by radar, particularly objects that are capable of intercepting it within the duration of an ascent trajectory (3-6 minutes). If something is about to enter the beam, it can dodge, dim, or douse (Dickinson 1978) until the obstacle is clear, or it could hand over to a nearby unobstructed beam director. Migrating birds can achieve remarkable altitudes, and the North American flyways are quite well documented. Research on bird radar systems (King 2013) has resulted in commercially available solutions that are capable of the kind of short-range tracking needed, such as the Merlin Avian Radar System offered by DeTect Inc.
WHAT IS THE BEST PROPELLANT?
Ammonia and methane are best and exceed the performance of LH2. Methane is of greatest interest because it is nontoxic and soot formed by its thermal decomposition can potentially be used as a microwave absorber to post-heat the propellant to the melting point of carbon. Water does not perform nearly as well but is still a viable propellant.
HOW HOT DOES THE HEAT EXCHANGER NEED TO BE?
Hotter than 1,500 K for slush ammonia or methane. Hotter than 2,000 K for slush hydrogen. Hotter than 2,500 K for liquid water.
CAN SUNLIGHT BE USED INSTEAD OF MICROWAVES?
Not to launch rockets.
Similar to laser or microwave beams, longer distances require larger dishes due to the effect of optical diffraction. However, sunlight is only partially coherent (unlike lasers and masers), so regardless of the actual size of the reflector used, it behaves as if it was coherent light emitted from a reflector that is only 70 microns in diameter. It is possible to show that at a distance of 350 km, as would be needed for launching rockets to orbit, such a beam spreads out to a spot size that is 6 km in diameter. It turns out that 350 km was the altitude of the Znamya 2 Space Mirror, and its spot size (projected onto the Earth) was reported to be 5 km wide.
The spot size is massively larger than the rocket! This of course spills almost all of the energy from the beam, making it economically a bad idea. For a target that is 1 meter in diameter, a distance of 57 meters should give an energy transmission efficiency of 86%. Consequently, sunlight might be useful for close-range ideas but is unsuitable for long distance transmission to a small distant target like a rocket.