“Masse”33 pages
- 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…
Air-to-Space
(Ballistic Threats)
Air Launch:
H~12 km
V~M0.8
........... I
Enemy/
Ballistic Missiles
JI
Figure 15. Air-to-Space Concept: Appropriate rotation and translation of a high-energy laser
beam, emanating from a moving aircraft, guides and propels a Lightcraft toward a nearly
head-on collision with an incoming ballistic missile; intermittently, the laser illuminates the
target for guidance updates and for terminal semi-active seeker homing and end-game
maneuvering [26l.
ASSUMED LASER AND LIGHTCRAFT LIMITATIONS
Beamed power levels achievable with envisioned high-energy laser technology are
assumed to be no more than about 10 MW for ground/sea-based lasers, and no more
than about 2.0 MW for the much lighter and smaller airborne lasers installable on
Boeing 747, B-1 Lancer, or C-130 subsonic aircraft. Lightcraft takeoff masses no more
than about 20 kg can be accelerated to orbital velocities by maximum ground/sea-
based laser power levels, and Lightcraft takeoff masses no more than about 4 kg to 8
kg, depending on the magnitude of velocity and acceleration needed, can be
accelerated to very high velocities by the lower allowable masses and power levels of
airborne lasers.
LIGHTCRAFT TRAJECTORY AND MISSION LIMITATIONS
Identified trajectory and mission limitations C26l are:
• Small allowable angle between centerlines of the laser beam and Lightcraft
vehicle axes before significant thrust reduction occurs.
• Small allowable angles-of-attack (angle between Lightcraft centerline and velocity
vector) before significant thrust reduction occurs.
• Limited capability for engaging multiple missile or aircraft threats in allowable
time interval because of relatively long laser beam-riding time against each
threat.
Additional Lightcraft hardware needed for some tactical missions [26l include:
28
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