“BEAMS”49 pages
- p. 3 …Free-Electron Laser Electron Beam Phase-Space Evolution ....................... 59
Figure 31. Recirculating-Beam FEL System ........................................................... 60…
- p. 4 …HEL Beam Pointer/Tracker ................................................................... 65
Figure 35. Basic Shared Aperture Beam Control System ......................................... 66
Figure 36…
- p. 7 …This can only be achieved via laser propulsion in
which the laser beam energy that is…
- p. 15 …By launching
spacecraft on a beam of electromagnetic radiation, researchers will have developed the
first new…
- p. 16 …The laser beam's pulse
interacts with the mirror, spreading out and focusing into an annular…
- p. 17 …1) power supply; 2) high-power (megawatt-class)
laser beam generator/transmitter using novel beam optics…
- p. 20 …is to the right and the laser beam strikes the stretched-out parabolic
mirror/propulsion section…
- p. 21 …It
requires a beam power of 0.1 to 1 MW per kg of vehicle mass…
- p. 22 …The ground-based
megawatt-class laser beam generator is state-of-the-art technology. The cost…
- p. 25 …Figure 8 illustrates the adverse beam
propagation geometry associated with ETO laser propulsion by means of…
- p. 26 …Attenuation Effects on Captured Laser Beam Power 261.
0.4
0.J
0.2
0.1…
- p. 27 …Unfortunately the demonstrated laser beam power levels for the attractive 1.62 μm
wavelength, which suffered…
- p. 28 …Beam combining
of several 1 MW (or higher) FELs can achieve a total combined beam output…
- p. 31 …Appropriate rotation of a high-energy laser beam,
emanating from a ground/sea-based laser, guides…
- p. 32 …Appropriate rotation and translation of a high-energy laser
beam, emanating from a moving aircraft, guides…
- p. 33 …But
multiple target interception within allowable time is limited by relatively long beam-
riding time needed…
- p. 37 …In this case, it is envisioned that the high-
pulsed power within high-energy laser beams…
- p. 39 …In this case, airborne laser beams at 12 km altitude will not suffer the
significant propagation…
- p. 41 …sidelobes, creates multiple beams, and steers the ensemble of the
individual beams anywhere on Earth. The…
- p. 42 …Each picosat is gravity-
gradient stable, has a dipole array facing Earth, and a broader beam…
- p. 43 …Commands for beam sweep delays are superimposed on the time delays of each
nanosat. Each nanosat…
- p. 44 …piezoelectric membrane kept flat by an electron beam in response to an optical figure
sensor. MEMS…
- p. 46 …technical issues include large wavelength and
atmospheric absorption of the laser beam.
• Carbon Monoxide (CO) Laser…
- p. 47 …125 Hz@ 20μs.
• Laser power, P = 2.5 MW/beam x 4 beams = 10 MW.
• Laser…
- p. 50 …Each power oscillator optics module transmitting a 2.5 MW beam of
10.6 μm wavelength…
- p. 52 …Adding an eight amplifier chain that the system was designed for will
increase the beam power…
- p. 53 …However,
BSSSL beam power can be scaled up further by improving presently known gain media
and…
- p. 54 …scalable
to 1 MW beam power within 2 years.
Typical solid-state lasers have the following…
- p. 55 …A new technology that enables the scaling-up of BSSSL beam power is a recently
developed…
- p. 56 …at the same time increasing the average
beam power.
Figure 21. Phase Change Materials Allow Storage…
- p. 57 …This exponential growth in beam output power is the result of many factors,
including the parallel…
- p. 58 …Microlens -O _
,:1
Incoherent Beam Combining 'Ind1vidually Incoherent Gaussian Beams i=L
Controlled
/_/Steering • ... o~bined…
- p. 59 …Neodymium
Thulium (Tm 3+), Holmium
- Range of beam wavelengths(),) produced: 0.48 μm to 2.9…
- p. 61 …Multlmode Fiber Lasers
50kW Multimode
Output beam quality BPP-1 o
M"2-33
DC EDE…
- p. 62 …The resulting laser beam photon energy depends on the
electron energy, the undulator period, and (weakly…
- p. 63 UNCLASSIFIED/ /F8~ 8FFl&I.«1k WliEii a,.klf
electron beam
( \ I,:--- ■■>ti■--
undulator
)
resonator mirror
0…
- p. 64 …The superconducting accelerator gives good
efficiency and gradient while recirculation of the electron beam recovers beam…
- p. 65 UNCLASSIFIED/ /F&~ 8FFHiil.«1k 1!181! &••kY
- K"' 1.5.t
• Electron Beam:
- Photocathode injector creates…
- p. 66 …HIGH ENERGY LASER BEAM CONTROL
··costs could be reduced to as low as $20 per kg…
- p. 67 …The typical HEL beam control system includes:++ 1) a gimbaled
beam director, 2) tracking and pointing…
- p. 68 UNCLASSIFIED//F&II. &FFiii,111!! l!llili &HI!¥
A novel new HEL beam control architecture being…
- p. 69 …HEL Beam Pointer/Tracker (courtesy of the Directed Energy Professional
Society).
In summary, this new architecture…
- p. 70 …The BILL is a solid-state, kilowatt-class laser
that measures atmospheric conditions, allowing the beam…
- p. 71 …All of these HEL beam control innovations can be quickly adapted to laser propulsion
applications with…
- p. 72 …The entire Lightcraft launch
system is comprised of a ground, sea, or airborne laser beam generator…
- p. 73 …New beam
control devices and high-power optical train combinations have a resulting beam line
that…
- p. 75 …N. (1983), "Advanced Beamed-Energy and Field Propulsion Concepts,"
BDM/W-83-225-TR, BDM Corp…
- p. 76 …N. (2001), "World Record Flights of Beam-Riding Rocket Lightcraft:
Demonstration of 'Disruptive' Propulsion Technology," AIAA…
- p. 77 …of the 6 th Int'! Symposium on Beamed Energy
Propulsion, edited by C. R. Phipps, AIP…
UNCLASSIFIED/ ,'P91t 91"1"1!1111L l!l!il! 811L¥
Miniaturized solid propellant gas generators could be used as ACS thrusters. Forty-
eight SO mN-sec pulses are required to reorient the nanosat after it achieves the
required orbital altitude. Although this could be achieved either by a monopropellant or
a cold gas thruster, it could also be achieved using an array of gas generators. Such
miniaturized gas generators have already been successfully built and commercialized by
companies such as MOOG and Lockheed-Martin Space Systems. By incorporating
micro-electromechanical systems (MEMS) techniques, the devices have been produced
relatively inexpensively. Miniaturized electric propulsion ACS thrusters, such as pulsed
plasma and MEMS field-emission electric propulsion (MEMS FEEP) thrusters, have been
developed and are now emerging into widespread commercialization.
GUIDANCE, NAVIGATION AND CONTROL
Guidance Navigation and Control (GN&C) subsystem key technologies and concepts
have been identified to enable successful altitude determination of spin-stabilized and
three-axis-stabilized nanosats for future missions. They include miniaturization of a
sun sensor and horizon crossing indicator. The miniature precision "fan" sun sensor will
pinpoint the sun virtually everywhere in the entire celestial sphere with every satellite
rotation. The sun sensor will be required to weigh less than 0.25 kg, draw less than 0.1
watt, operate on no greater than a 3.3 volt bus, and meet a 0.1° resolution
requirement. The miniature horizon crossing indicator has a small bore-sight field of
view that is mounted at an angle off the spin axis. As the spacecraft rotates, a cone of
coverage is formed. The sensor must be capable of detecting Earth over a range of
orbital radii with a pointing accuracy of 0.05°. Total horizon crossing indicator weight
and power will be less than 0.2 kg and 0.1 watt, respectively.
Of particular interest to Constellation missions is the incorporation of GPS onboard the
nanosats, to eliminate ground-based ephemeris generation. This allows for increased
autonomy and simpler, more accurate time resolution onboard the spacecraft. For GPS
to fit within the constraints of a nanosat, the receiver electronics need to be
miniaturized into a layer within the C&DH module.
COMMAND AND DATA HANDLING
Developing the C&DH subsystem for a nanosat presents some unique challenges, with
low mass (0.25 kg) and low power (0.5 W) requirements being the biggest drivers.
Advanced microelectronic solutions are being developed to meet these challenges. The
microelectronics developed must be modular and of scalable packaging to both reduce
cost and meet the requirements of various missions. This development will utilize the
most cost effective approach, whether infusing commercially driven semiconductor
devices into spacecraft applications or partnering with industry in the design and
development of high capacity data processing devices. The major technologies will
include: lightweight, low power electronics packaging; radiation hard, low power
processing platforms; high capacity, low power memory systems; and radiation hard,
reconfigurable, field programmable gate arrays (RHrFPGA).
The C&DH requirements are as follows:
• Power: 0.5 watts.
4
UNCLASSIFIED//FQA: QFFI&l11J.k W&liii Q•lklf