“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/ il"9" 91"l"!e!lltt tl!IL 9HL I
• Weight: 0.25 kg.
• Input data rate: 2 kbits/sec.
• Output data rate: 100 kbits/sec.
• Data storage: 2 Gbits.
• Encoding: advanced convolutional.
• Processing speed: 12 MIPS.
• Radiation tolerance: > 100 krads total dose.
In order to develop a low mass C&DH, a lightweight and low power electronics
packaging method must be used. The packaging method that will be chosen must have
a small volume and small footprint (6 cm x 6 cm x variable height). The packaging
technique must provide data on programmable substrates and data on a compliant
interconnects for space use. A multi-chip module (MCM) has been successfully
produced by Pico Systems Inc.
A combined effort to reduce mass, power, size and cost led to the development of the
CMOS Ultra Low Power Radiation Tolerant (CULPRiT) system on a chip, and "C&DH in
your Palm" are technologies that enable the power reduction required for nanosats.
The goals of these technologies are a 20: 1 power reduction over current 5-volt
technology, foundry independence of die production, and radiation tolerance.
Another technology enabling a decrease in volume is the RHrFPGA, which reduces
volume by replacing many logic functions/circuits with one die. The RHrFPGA also
allows concurrent design by decoupling the logic design from the module, shortens the
design schedule, lowers the part count, and eases rework.
The above technologies allow for higher levels of electronic integration, effectively
combining spacecraft subsystem electronics and instrument electronics into the
smallest possible mass, power, and volume.
POWER SYSTEMS
Total spacecraft power is limited by the small satellite size. The Sun's power density is
1.35 kW/m 2. Assuming 15% conversion efficiency for a 0.3 m x 0.1 m disk shaped
nanosat (cross section of 0.03 m 2 ), with a 67% area coverage, this results in a total
electric power of only 4.0 watts. Lightweight, efficient solar array panels that minimize
the effective array mounting area are needed. Dual or triple junction GaAs solar cells
that give 18% conversion efficiency at end of life (EOL), and assuming a more
optimistic area factor of 85%, will result in only 6.2 Wat EOL. Small satellites that do
not have extended solar panels simply do not intercept a large solar power density and
must use the available power very efficiently. For a small spinning satellite, it is
expected that three solar cells will be connected in series along the spin axis, and
groups of three will be connected in parallel around the circumference. Each section
will generate 3.3 volts and rotate into and out of sunlight as a unit. Voltage drops at
3.3 volts, bus regulation, circuit protection (e.g., fuse or circuit breaker) and Lithium
ion battery discharge characteristics are being studied.
Highly elliptical orbits in the ecliptic plane where the apogee velocity is very low will
cause a several hour eclipse during part of the year. Spacecraft batteries to cover this
eclipse period presents a significant mass impact. However, only a 10° orbit plane
UNCLASSIFIED//F811. 8FFl81*L tl!IL 8HLY
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