Progress is good in several areas. Our low mass Reaction Control System prototypes are going together well, with actuators, electronics and machined hardware in the prototypes. The 3.5 DOF unit will probably come in below the 40 grams mass expected, although additional mass reductions have been identified. These RCS units work with full pressure CO2 to eliminate the need for a pressure regulator. 3.5 DOF means the unit will provide bidirectional control of the “Angular” Three Degrees of Freedom involved in setting of the attitude of our small spacecraft, or Lunar Lander, before main engine ignition. The extra ½ Degree of Freedom represents the availability of a unidirectional linear acceleration – used to settle the liquid fuel before main engine ignition.

Two of these units will provide full 6 DOF, all direction linear and angular adjustments (Attitude and “Divert”) for rendezvous and docking operations. Our planned CubeSat demonstration will use exactly this 80 gram combination for primary control as it demonstrates our “Low Mass” “Formation Flying” technologies. These would be perfect for a small “Planetary Ascent Vehicle” in a sample return mission. With masses this small, multiple probes could be used to return samples from several areas on a planetary surface, as well as providing redundancy. This capability will also allow us to add Lunar Sample Return to our Google System as discussed previously.

Related to this, progress with our EMTB = “ElectroMagnetic Tractor Beam” is also good. This is our “Zero Propellant”, extreme precision technology for formation flying plus rendezvous and docking. We have a number of interesting demonstrations which we are in the process of videotaping. We will soon post these videos – pushing viewers well ahead of DOD SBIR “Experts”. Those who view these videos will know that this technology works – unlike the DOD “Experts” who evaluated our detailed discussion of the technology and our accomplishments with it – and concluded that “It Is Impossible”.

Good progress with the 6 DOF sensing portion of this technology was achieved today. This is also related to our very low interference, “Wireless Data Link” for use in small rocket systems. We achieved good passive sensing (for the “Wake Up” and Wireless Battery Charge functions at isolated nodes) and excellent signals at the maximum range needed for our small “Clustered” launch vehicles. The smallest “Cluster” is also one our more interesting applications. By using our wireless link between the satellite or spacecraft and the launch vehicle, the stabilization, communications and navigation resources necessary for the launch can be retained in the spacecraft with no duplication or mass penalties. Very high performance satellites can then be flown with very light propulsion systems.

Today's tests also verified the extreme precision of attitude measurement provided by this wireless system at moderate range (better than 1/1000 of a degree). At maximum range, noise does not allow this precision, but based on today's tests, the maximum range is space with 10 cm coils will exceed 100 meters. CubeSats separated by the length of a football field will be able to accurately determine their relative 6DOF positions using only this sensing system.

An unrelated technology, with related uses, has also made progress this week. We have achieved good performance from a compact version of one of the interferometers and associated sensors in our PCALI upgraded prototype. Our PCALI (PolyChromatic Absolute Laser Interferometer) produces an absolute distance measurement with sub nanometer resolution Without Moving the Target! Traditional Laser Interferometers require that the target be moved to a reference position very close to the Laser Source before measurements begin. They actually only quantify the change in position from this initial point, not absolute distance. Since the use of White = Polychromatic light is well known in classic optics as a way to detect an “Absolute Zero” path reference, we use a related technique to determine the absolute distance to any reflector. In a few seconds, this distance is determined and any changes from that position can be quantified in microseconds. This is valuable in satellite formation flying, where arranging the close initial position is very difficult. Note that without our Absolute measurement, any disruption of the light path or electronic function requires that this initialization be repeated. Combined with the gentle, infinite resolution forces produced by our EMTB system, satellite formations can be stabilized to nanometer accuracy.

We are actively seeking funding for our CubeSat demonstration of these combined technologies in space, and have small enough, low power lasers and optical systems for that purpose.

Since many Terrestrial measuring situations could also use this “Absolute” measurement capability, we are also looking for “Funded Demonstration” opportunities to showcase this technology. Laser Interferometers are the “Gold Standard” for precision Machine Tool linear measurements. But our variant will allow the measuring beam to be “Time Shared”. One beam can be redirected to measure the position of many reflector targets in a workspace – possibly a group of large robots when inspection or machining precision exceeds the accuracy that can be reliably sustained by these units. We also have arranged to work with “Spectron Engineering” (Denver, Colorado) to add precision “Robotic Theodolites” to optical measuring setups. These Theodolites have been used by DOD and commercial aerospace organizations for years to quantify performance of HUD and HMD displays. These units nicely compliment the capabilities of our PCALI interferometers, and add the beam steering for multiplexed use. Long range applications of the theodolite often produce better than 25 micron position resolution. When combined with the interferometer – even under poor atmospheric conditions – long range resolutions can be better 0.01 micron, and well below one nanometer under better conditions.