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Micro-satellite
and satellite formation for inverse and distributed proximity operations
- Stable
heli-borne vector platform for performing geophysical measurements
- Survivable
and reusable launch vehicle - Periodically
adaptive guidance and control - Tailboom-stabilized
VTOL aircraft - Lift
generator by continuously rotating impeller - Rotary/fixed
wing aircraft - Omni-directional
air vehicle personal transportation system - Apparatuses
and methods for preventing foreign object damage to aircraft engines
- Multi-positional
tail skids and associated methods of use - Thrust
reverser with sliding pivot joints - Self
stowing thrust reverser - Aircraft
canopy jettison apparatus with airbag - System
and methods for integrating a payload with a launch vehicle - High
efficiency spacecraft orbit transfer - Controlling
pointing for a flexible structure - Flywheel
prognostic health and fault management system and method - Prevention
of ice formation by applying electric power to a liquid water layer
- Miniature,
unmanned aircraft with onboard stabilization and automated ground
control of flight path
Micro-satellite and satellite formation for inverse and
distributed proximity operations
A method and apparatus for conducting proximity operations is
disclosed. The method called inverser proximity operations
includes maneuvering an active vehicle into general proximity to a
target vehicle, transmitting from the target vehicle to the active
vehicle data representing relative position and velocity between
the target vehicle and the active vehicle, and maneuvering the
active vehicle in accordance with the data to effect a desired
proximity operation. Another method called distributed proximity
operations includes maneuvering a carrier vehicle into general
proximity to a target vehicle, releasing one or more active
vehicles from the carrier vehicle, transmitting from the carrier
vehicle to the active vehicle(s) data representing relative
position and velocity between the target vehicle and the active
vehicle, and maneuvering the active vehicle(s) in accordance with
the data to effect a desired proximity operation. The proximity
operations are similarly suitable for aeronautical systems, such
as when using an active aircraft to re-fuel a target aircraft,
such as a drone. Whether for space, air, or other environments,
the proximity operations described can be used for re-fueling,
repairing, and replacing components and/or systems.
Byler, Eric Alan
Lockheed Martin Corporation; January 18, 02005
#6845303
Stable heli-borne vector platform for performing geophysical
measurements
A stable heli-borne vector platform capable of accepting a
range of different sensors or instruments, particularly, but not
exclusively, for the mapping and exploration of mountainous
regions is described. The platform enables the arrangement of the
sensors in three orthogonal directions, thus allowing the
restitution of the resultant vector. The geographical referencing
is provided by the use of a differential GPS receiver, whose
antenna is installed on the main body of the platform. This
platform distinguishes itself from its predecessors through the
use of a lateral pulling axis, the use of a heavy weight placed
underneath the main body, and by a perfectly symmetrical geometry
in the direction of pull, thus ensuring perfect in-flight balance
and stability.
Mouge, Pascal; Chalifoux, Emmanuel
Geophysique G.P.R. International Inc.; January 25, 02005
#6845936
Survivable and reusable launch vehicle
A reusable, mach-velocity mobile platform delivers a weapons
payload via vertical launch, powerless glide, weapons release, and
landing operation phases. The platform includes a generally
tubular shaped body having an aft and forward end, and a payload
section. An arch wing is supported by the body aft end. The arch
wing has an upper and a lower wing joined at distal ends by two
curved end plates. A nose assembly is connected at the forward end
having an upward directed fixed angle-of-attack to generate
forward end lift. Thermal tiles attached under the body and the
lower wing under-side radiate/dissipate heat generated during a
high angle-of-attack platform reentry. Radar absorptive or radar
translucent material is used. The platform preferably discharges
payload from the aft end for safe separation. A landing gear is
extended for the landing phase of operation.
August, Henry
The Boeing Company; January 25, 02005
#6845937
System and method for periodically adaptive guidance and control
A system and method that guides a device to an object using
periodically adaptive guidance. The guidance and control system
creates a reconstructed line-of-sight (LOS) vector to avoid system
destabilization associated with small angle approximation during
high bore sight engagements. The guidance system adaptively
estimates the periodic maneuver of evasive objects with a set of
harmonically balance Kalman filter banks. The Harmonically
Balanced Kalman filter banks generate a set of probabilities that
weight the effect of each individual Kalman filters on a resultant
guidance command signal. The guidance command signal generated by
the system acts perpendicular to the object LOS. The guidance and
control system uses vectored proportional navigation guidance
laws, optimal proportion navigation laws and periodically adaptive
augmented guidance laws to generate a guidance command signal to
supply to an autopilot.
Muravez, Randall J.
Lockheed Martin Corporation; January 25, 02005
#6845938
Tailboom-stabilized VTOL aircraft
A disclosed flying craft includes a suspension structure having
a first end and a second end, a lift unit, and a payload unit. The
lift unit includes a nacelle and a tailboom, and pivotally couples
to the first end of the suspension structure, and a payload unit
couples to the structure's second end. Thus the tailboom can
pivotally couple with respect to the payload unit, which
advantageously permits the tailboom to assume an orientation
desirable for a particular mode of flight. During vertical flight
or hover, the tailboom can hang from the lift unit in an
orientation that is substantially parallel to the suspension
structure and that minimizes resistance to downwash from the lift
unit. During horizontal flight, the tailboom can be orthogonal to
the suspension structure, extending rearward in an orientation
where it can develop pitching and yawing moments to control and
stabilize horizontal flight. Advantageous variations and methods
are also disclosed.
Baldwin, G. Douglas
January 25, 02005
#6845939
Lift generator by continuously rotating impeller
In order to continuously rotate an impeller having an axis
parallel to a ground surface in one direction to generate lift, a
cover close to a periphery in an opposite lift side is provided
within a half of an outer periphery of the impeller, and a
cylindrical scroll wheel integrally and concentrically rotating
with the impeller is provided in a cavity portion near a root of
the impeller, whereby a balance between the lift side and the
opposite lift side is broken aerodynamically.
Hashimoto, Kikushiro
January 25, 02005
#6845940
Rotary/fixed wing aircraft
A rotor system that allows an aircraft to operate as a
helicopter and as an airplane is disclosed. The invention
incorporates an annular airfoil attached at the tips of the rotor
blades. The rotor system stops and is secured from rotation for
operation at high forward speeds. The annulus acts as the primary
lifting surface in airplane mode at high speed. The rotor blades
incorporate leading and trailing edge flaps for control in
transitional and fixed wing flight modes.
Pica, Bret D.
January 25, 02005
#6845941
Omni-directional air vehicle personal transportation system
An omni-directional air vehicle having a pod with a connected
turbofan system, the pod has a body that contains a power source
for generating electrical power and a ducted fan with spherical
articulation mechanism having a projecting arm with
counter-rotating propellers and a ducted shroud around the
periphery of the counter rotating propellers and containing drive
motors for electrically driving the propellers.
Paul, Marius A.
January 25, 02005
#6845942
Apparatuses and methods for preventing foreign object damage to
aircraft engines
Apparatuses and methods for preventing foreign object damage (FOD)
to aircraft engines are disclosed. In one embodiment, a deployable
blocker is coupled to a wing portion and/or a fuselage portion of
the aircraft and is configured to prevent debris from travelling
on a direct trajectory from a landing gear wheel to an engine air
inlet. In other embodiments, the blocker can prevent debris from
bouncing off the wing lower surface into the engine inlet, or
sticking to the wing lower surface and falling into the engine
inlet. The deployable blocker can cover at least a portion of the
landing gear when the landing gear is retracted and the blocker
assembly stowed. In another embodiment, the blocker can be mounted
to the landing gear.
Chambers, David S.; Cottet, Justin D.; Foutch,
David W.; Simpson, Mark N.
The Boeing Company; January 25, 02005
#6845943
Multi-positional tail skids and associated methods of use
Multi-positional tail skid assemblies and methods for their
use. In one embodiment, a multi-positional tail skid assembly
includes a skid member and a skid deployment system operably
connected to the skid member. The skid member can include a first
portion attachable to an aft portion of a fuselage and a second
portion movable relative to the aft portion of the fuselage. The
second portion can support a skid surface configured to contact a
surface of a runway. The skid deployment system can be configured
to move the skid surface between first and second positions. When
the skid surface is in the first position, the skid surface is
closer to the aft portion of the fuselage than when the skid
surface is in the second position.
Bays-Muchmore, C. Byram; Brouwer, Todd B.; Bryant,
Malcolm S.; Burggraf, Warren D.; Little, Daniel S.; Miller, Douglas
G.; Tolzmann, Stanley E.; Withington, Martin M.; Zierten, Thomas A.
The Boeing Company; January 25, 02005
#6845944
Thrust reverser with sliding pivot joints
A target type thrust reverser is provided for reversing the
thrust of jet engines, particularly on aircraft. The thrust
reverser preferably has a plurality of doors that occupy a stowed
position about the nozzle of the jet engine until deployed. In the
stowed position, the doors are out of the exhaust stream of the
jet engine. The doors are mounted to pivot joints on the rear
portions of the doors. To deploy the thrust reverser, actuators
connected to the pivot joints cause the pivot joints to translate
linearly aft, and link rods attached to the forward portions of
the doors cause the doors to pivot about the sliding pivot joints.
In this manner, the distance between the doors and the engine
exhaust nozzle is minimized during deployment, which enables
significant weight savings due to reduced loads and fewer parts. A
novel lock is also provided for simultaneously locking the thrust
reverser doors and the actuators.
Smith, Craig M.
Aircraft Integration Resources, Inc.; January 25, 02005
#6845945
Self stowing thrust reverser
A thrust reverser includes forward and aft louvers pivotally
mounted in a compartment defining a flow tunnel through the outer
and inner skins of a fan nacelle. An aft flap is integrally joined
to the aft louver for rotation therewith. A unison link joins
together the forward and aft louvers. And, an actuator is joined
to the louvers for rotation thereof between a stowed position in
which the louvers and flap are closed in the nacelle skins and a
deployed position in which the louvers and flap are pivoted open
from the skins.
Lair, Jean-Pierre
The Nordam Group, Inc.; January 25, 02005
#6845946
Aircraft canopy jettison apparatus with airbag
A method of removing a canopy from a cockpit of an aircraft
comprising providing an airbag in the cockpit adjacent the canopy;
inflating the airbag; and as the airbag inflates, applying a force
to the canopy from the inflating airbag to thereby jettison the
canopy.
Reese, Jr., Milton L.; Tersine, Edward G.
The United States of America as represented by the Secretary of the
Navy; January 25, 02005
#6845947
System and methods for integrating a payload with a launch
vehicle
A system for providing an interface between a launch vehicle
and a payload of the launch vehicle includes payload integration
points of the launch vehicle that remain unchanged relative to
different payload configurations, such that a payload is
configurable apart from the launch vehicle. The system makes it
possible to de-couple payload installation and launch vehicle
turnaround operations. Payloads can be configured off-line from
launch vehicle processing, thus making it possible to accommodate
unique payloads while reducing wear and tear on the launch
vehicle.
Blackwell-Thompson, Judith C.; Graves, John A.;
Gale, Anita E.
The Boeing Company; January 25, 02005
#6845949
System for high efficiency spacecraft orbit transfer
The present invention relates generally to systems and methods
for transferring a spacecraft from a first orbit to a second
orbit. In accordance with one embodiment of the invention, the
method comprises calculating thruster-off regions within an orbit
transfer in which it is efficient to turn-off spacecraft
thrusters, and in those thruster-off regions, turning off the
spacecraft thrusters.
Goodzeit, Neil Evan; Ratan, Santosh
Lockheed Martin Corporation; January 25, 02005
#6845950
Method of controlling pointing for a flexible structure
A method of controlling pointing for a flexible structure such
as a satellite includes: providing feedforward and reference
inputs of a pointing control system with prefilters; and
scheduling the prefilters and a bang-bang input to the pointing
control system as a function of a desired input.
Herman, Paul Andrew
The Aerospace Corporation; January 25, 02005
#6845951
Flywheel prognostic health and fault management system and method
A prognostic health and fault management system and method that
accurately determines the health and rate of degradation of one or
more flywheel systems, by comparing actual and simulated responses
of flywheel systems to supplied command signals. Based on the
determined health status and degradation rate of the flywheel
systems, one or more unhealthy, active flywheel systems are
deactivated, and one or more healthy, deactivated flywheel systems
are activated. The system can be used in terrestrial applications,
or in vehicles such as satellites, spacecraft, or ships.
Abel, Stephen G.; Potter, Calvin C.; Brault,
Sharon K.
Honeywell International, Inc.; January 25, 02005
#6845952
Prevention of ice formation by applying electric power to a
liquid water layer
A first electrode is separated from a second electrode by an
interelectrode space. The interelectrode space does not exceed 3
mm, and preferably does not exceed 100 .mu.m. Liquid water fills
the interelectrode space, thereby electrically connecting the
first electrode and the second electrode. A power supply,
preferably low-frequency AC, is connected to the first and second
electrodes, generating a current through the water in the
interelectrode space. The applied electric power prevents freezing
of a thin liquid water layer in the interelectrode space, thereby
preventing ice formation.
Petrenko, Victor F.
Trustees of Dartmouth College; January 25, 02005
#6847024
Miniature, unmanned aircraft with onboard stabilization and
automated ground control of flight path
A miniature, unmanned aircraft for acquiring and/or
transmitting data, capable of automatically maintaining desired
airframe stability while operating by remote directional commands.
The aircraft comprises a fuselage and a wing, a piston engine and
propeller, a fuel supply, at least one data sensor and/or radio
transceiver, a microprocessor disposed to manage flight, a radio
transceiver for receiving remotely generated flight direction
commands, a GPS receiver, a plurality of control surfaces and
associated servomechanisms, for controlling flight stabilization
and direction, roll, pitch, yaw, velocity, and altitude sensors.
The microprocessor uses roll, pitch, yaw, and altitude data to
control attitude and altitude of the aircraft automatically, but
controls flight direction solely based on external commands. The
aircraft does not exceed fifty-five pounds.
Carroll, Ernest A.
January 25, 02005
#6847865
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