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Defense Intelligence Reference Document Laser Lightcraft Nanosatellites

Defense Intelligence Agency · 77 pages · text from the file's own layer

This Defense Intelligence Reference Document from the Defense Intelligence Agency, dated 1 November 2010, was produced under the Advanced Aerospace Weapon System Applications (AAWSA) Program. It describes nanosatellite technologies and proposes launching nanosats into orbit with laser Lightcraft propulsion. It also covers a weapon mission selection study and multi-megawatt laser options. The author recommends that the Department of Defense and NASA bring Lightcraft R&D back to the United States and restart the X-50LR flight demonstration program.

  • p. 4 …Influence of Target Velocity and Intercept Angle on Impact Energy and Required Mass .................................................................................................. 33 Table 5…
  • p. 5 …The term "minisatellite" refers to a spacecraft with a wet mass (including onboard propellant) of 100…
  • p. 7 …Nanosatellite Technologies OVERVIEW Nanosats require technologies that radically reduce the mass and power of components without…
  • p. 8 …nanosat presents some unique challenges, with low mass (0.25 kg) and low power (0.5…
  • p. 9 …In order to develop a low mass C&DH, a lightweight and low power electronics packaging…
  • p. 11 …RF COMMUNICATIONS The onboard RF subsystem must be small, low mass, and low power. The system…
  • p. 12 …additional strain on an already challenged nanosat mass and power budget. For this reason, the concept…
  • p. 13 …The material will be selected based on mass, cost, manufacturability, ease of assembly and integration, and…
  • p. 15 …for the spacecraft because a large propellant mass and heavy energy source are not carried onboard…
  • p. 17 …Current Lightcraft designs are limited to about 60 g mass and 15 cm in diameter by…
  • p. 21 …It requires a beam power of 0.1 to 1 MW per kg of vehicle mass…
  • p. 22 …The majority of the system mass required to launch a payload to orbit is left on…
  • p. 24 …Therefore, this would allow approximately 4 kg of mass to be placed into orbit with the…
  • p. 25 …same ply-thickness) to meet Lightcraft airframe mass requirements. Another important finding in the study was…
  • p. 31 …Additional estimated mass for performing the Lightsat function is no more than about 1 kg, if…
  • p. 32 …Lightcraft takeoff masses no more than about 20 kg can be accelerated to orbital velocities by…
  • p. 33 …for missile and maneuvering aircraft interception. • Additional mass along Lightcraft centerline for hardened target penetration. LIGHTCRAFT…
  • p. 34 …Lightcraft sizing assumed a propellant mass fraction of 0.5 and 1.0 MW of laser…
  • p. 35 …Hybrid Rocket Expendible Launch Vehicle - Assumed Perfonnance and Estimated Weights Payload Mass (kg) 1.00 5…
  • p. 37 …It is therefore estimated that the air-to-space Lightcraft dry mass would be about the…
  • p. 38 …Influence of Target Velocity and Intercept Angle on Impact Energy and Required Mass 2 61. Lightcraft…
  • p. 39 …Influence of Lightcraft and Target Velocity on Impact Energy and Required Mass 261. Lightcraft Lightcraft Impact…
  • p. 40 …The lower mass also saves launch costs, so the total system costs less for the same…
  • p. 41 …many spacecraft that the economics of true mass production will come into play in space for…
  • p. 44 …the local vertical, with its center of mass in GEO. The Fresnel zone plate has a…
  • p. 46 …wall plug and optical efficiencies, cost, complexity, mass, and size. Free-electron lasers are another class…
  • p. 47 …P = 2000 Pa (or 0.02 atmospheres). • Mass flow rate, Q = 60 kg/sec per module…
  • p. 48 UNCLASSIFIED//509 AEEJCJOP 11£5 O.-blf + Total mass flow rate, Qtota1 = 240 kg/sec for…
  • p. 50 …sec, and 15 kg/sec of CD2 mass flow represents 2.053 x 1026 molecules/sec…
  • p. 51 …The 60 kg/sec mass flow requirement of the 3: 1 N2/C02 lasing gases means…
  • p. 53 …mass (not including the prime power and cooling systems) to achieve the low specific mass (5…
  • p. 65 …is the undulator period, mis the electron mass, and c is the speed of light. 'MeV…
  • p. 72 …The Lightcraft specific impulse is essentially infinite (several thousand seconds in rocket mode), while payload mass…
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In order to launch a laser-propelled Lightcraft nanosat or picosat from the ground, sea,
or air, it will be necessary to control and steer the high-energy laser (HEL) beam, while
at the same time making real-time adjustments to account for platform motion, optical
train and atmospheric effects on beam propagation, so that the beam maintains high
quality, low-loss, precision contact with the Lightcraft from launch all the way up to
LEO. While the atmospheric effects on laser beam propagation were briefly discussed
in the Lightcraft Nanosatellite Configuration section of Chapter 2, a more in-depth
examination of this phenomenon can be found in Reference 32. In what follows, we
briefly discuss what a HEL beam control system is designed to do and what innovations
were recently developed by the various DoD directed energy weapons programs that
are just now being successfully tested and deployed.
A beam control system is designed to:tt
• Acquire and precisely track a designated target.
• Handles the HEL beam emitted from the laser:
- Aligns the HEL beam to the optical train's axis - from the laser resonator to the
beam director's exit aperture.
- Safely relays the HEL beam through the optical train with minimal loss of
energy and beam quality.
• Expands the HEL beam and focuses it at the range of the target.
• Places and maintains the HEL beam on the desired target's aimpoint.
• Corrects for beam quality degradations in the optical train or the atmosphere (if
needed).
HEL weapons usually have high-power optical trains containing more than a dozen
mirrors. However, these systems need to be far more compact with minimal high-
power trains. As directed energy weapon applications begin to employ smaller HEL
systems, the size, weight and complexity of the accompanying beam control system
has come down as well. The typical HEL beam control system includes:++ 1) a gimbaled
beam director, 2) tracking and pointing functions, 3) adaptive optics, 4) acquisition
sensors, and 5) target illuminators. Solutions have been recently developed to drive
towards a smaller, lighter and simpler beam control system while considering the entire
end-to-end system architecture. Existing beam control solutions are robust but large
and complex. The technical strides achieved in the past 20 years in wavefront sensing,
aperture sharing elements, beam tracking and beam correcting provide new tools to
offer a simplified low mirror count beam control system while retaining the ruggedness
of function necessary for a laser weapon.
Figure 33 and Figure 34 show schematics of a notional inertially-stabilized
pointer/tracker mount and beam control system that was developed by NAVSEA's
DE&EWS Program.
,-o. Kiel, Directed Energy Systems Symposium Short Course, Naval Post-Graduate School, Monterey, CA, 2010.
10
D. Kiel, Directed Energy Systems Symposium Short Course, Naval Post-Graduate School, Monterey, CA, 2010.
UNCLASSIFIED//F8A 8FFI&II k WEEii ,u1uc 63

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