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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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that has runways of reasonable length. An air-launched Lightcraft launch vehicle
mission, involving the transport of lasers and Lightcraft on medium-sized bombers or
transport aircraft, is also recommended if additional funding would become available.
FUTURE NANO-/PICO-SATELLITE MISSION CONCEPTS
Coherently cooperating "swarms" are a novel innovation for replacing structures with
information by placing many formation-flown small satellites into a loose "swarm" and
cause them to cooperate coherently. This is very different from the so-called
distributed small satellite LEO constellations currently pursued in which individual small
spacecraft perform essentially the same functions as larger satellites but at lower
spacecraft mass ( or weight) and cost. These smaller spacecraft can be proliferated to
provide greater geographical coverage for the same cost. The lower mass also saves
launch costs, so the total system costs less for the same function performed with larger
spacecraft.
In contrast, the swarms, as described in the following sections, cooperate coherently
and form a real distributed system in which the whole is more than the sum of the
parts. A generic description would be a constellation of small spacecraft each
performing its separate function, but these functions combine to create at a central
location a much larger virtual spacecraft, or sensor aperture, that exists solely because
of the cooperation of the spacecraft. The following sections provide several examples
of the implementation of such systems in which each of a large number of small
satellites in a swarm or other constellation will radiate or receive signals and combine
them in phase, or coherently, regardless of their actual location in orbit. This creates
coherent RF or optical apertures that are essentially unlimited in size.
Each satellite's position is only crudely station kept, and the satellites adjust the time
delay or phase delay of the signals they repeat to compensate for their position errors,
causing their repeated signals to add coherently at a collection point. This technique
can be easily applied to RF transmitters and receivers, and with more demanding
accuracy to optical transmitters and receivers. The result in either case is a large
"swarm" or loose constellation of satellites that act as one large antenna or optical
array, even though they are separate and their positions are neither constant nor lie
along a parabola or plane in space. The individual satellites can be as simple as one-
element flying chips or as complex as today's self-contained sensing spacecraft of
various sizes.
The advantage of coherently cooperating distributed systems is that they can form
sparse RF antennas and optical sensors with diameters so large that they would be
impossible to implement with filled apertures even if formed with adaptive membranes;
and have orders of magnitude smaller mass. The relative locations of individual
spacecraft in the swarm can be controlled by MEMS FEEP propulsion, tethers, or by
cleverly conceived orbits in which the elements of the array appear to orbit a common
center within it, thus eliminating the need to use propulsion at least for first order
station keeping.
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Report, from the dia collection. The PDF is mirrored here; the original link is under it. 77 pages are in the text index: search them above, or from the library's search.