Abstract: Method of and system for on-board substantially autonomous control for transferring a spacecraft from an initial orbit to a final geosynchronous orbit, by a trajectory that minimizes remaining transfer time and orbit transfer fuel. The spacecraft determines its orbit using a GPS-based system to determine the spacecraft orbital elements. Based on the measured orbit error, corrected co-state parameters are calculated and used to generate an updated thrust trajectory. The corrections are calculated using an innovative numerical procedure, carried out repetitively at a fixed interval until the target geosynchronous orbit is achieved.

Abstract: Trailing edge devices configured to carry out multiple functions, and associated methods of use and manufacture are disclosed. An external fluid flow body (e.g., an airfoil) configured in accordance with an embodiment of the invention includes a first portion and a second portion, at least a part of the second portion being positioned aft of the first portion, with the second portion being movable relative to the first portion between a neutral position, a plurality of upward positions, and a plurality of downward positions. A guide structure can be coupled between the first and second portions, and an actuator can be operatively coupled between the first and second portions to move the second portion relative to the first portion. In one embodiment, a flexible surface can track the motion of the second portion and can expose a gap at some positions.

Abstract: An aircraft landing gear door assembly includes a plurality of doors moveable between open positions, in which landing gear can be deployed through an aperture, and closed positions, in which the doors are closed across the aperture. The plurality of doors includes first and second doors arranged such that, when the landing gear is deployed, the second door is obstructed from moving between its open and closed positions while the first door is free to move between its open and closed positions. After the landing gear is deployed the first door is closed.

Abstract: A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack.

Abstract: Aircraft landing gear comprised of a wheel hub motor/generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The wheel hub motor/generator can provide motive force to the wheel when electrical power is applied, which may be applied prior to touch-down thus decreasing the difference in relative velocities of the tire radial velocity with that of the relative velocity of the runway thus greatly reducing the sliding friction wear of said tire. After touchdown the wheel hub motor/generator may be used as a generator thus applying a regenerative braking force and/or a motorized braking action to the wheel. The energy generated upon landing maybe dissipated through a resistor and/or stored for later use in providing a source for motive power to the aircraft wheels for the purpose of taxiing and ground maneuvers of said aircraft.

Abstract: The present invention discloses a system and a method for reducing plasma induced communication disruption utilizing electrophilic injectant and sharp reentry vehicle nose shaping. Injecting electrophilic gas into plasma accomplishes reduction of plasma induced communication disruption by removing free electrons in the plasma which causes the communication disruption. For reentry vehicles, a multi-section sharp nose also reduces plasma effect during reentry. By combining electrophilic gas injection and a multi-section sharp nose shaping, the present invention reduces and further eliminates plasma induced communication blackout, such as GPS communication blackout, for a reentry vehicle during reentry. As a result, the present invention improves targeting accuracy for a GPS-guided reentry vehicle by reducing plasma induced GPS blackout during the critical reentry phase.

Abstract: This invention relates to the design of a Modular Aerospace Plane (MAP) comprising a forward fuselage section, a main wing section, a tail section and wing attachments. Various sections can be integrated to offer a variety of aircraft characteristics, performance and missions. This modular design offers a new method of aircraft fabrication, maintenance, repair and ground handling to reduce costs for the manufacturers, owners and operators. The forward fuselage and tail sections may utilize a parachute device whereby these sections can separate in an emergency and safely lower the occupants to the ground.

Abstract: A flying vehicle-launching apparatus and method for launching a winged flying vehicle by accelerating the vehicle in a predetermined direction includes a flying vehicle-supporting platform, a guide device, and a driving device. The flying vehicle-supporting platform supports the winged flying vehicle so that it can lift off therefrom. The guide device supports the flying vehicle-supporting platform across two or more separated and parallel guide ways and guides the flying vehicle-supporting platform along the guide ways. In the flying vehicle-launching method, a propulsive engine of the winged flying vehicle is started after initiating acceleration with a flying vehicle-accelerating device. The winged flying vehicle is released from the flying vehicle-accelerating device in a predetermined angle of attack that is positive to a direction of acceleration after reaching a predetermined velocity.

Abstract: An improved seating apparatus for an aircraft comprising: a seat assembly and a positive lock device for securing the seat assembly to the aircraft. In the preferred embodiment, the positive lock device comprises: an adjustable force applicator for selectively applying force, a track fitting for insertion into an aircraft seat track, a rigid force bearer having a top region and for transferring force to an aircraft seat track, and a lock plate biased toward the applicator head. Also, in the preferred embodiment, the seat assembly includes a seat leg.

Abstract: Flaps, for example leading edge flaps and/or trailing edge flaps of an aircraft wing, are driven and adjusted by respective drive units. Drive shafts of neighboring flaps are coupled to each other by a differential gear. The differential gear is thus coupled to a main drive shaft which is driven by a main drive unit. Additionally, the differential gear is coupled to a secondary drive unit. The main drive power and the secondary drive power and thus the respective flap motions are super-imposable on each other, which permits operating the flaps independently of each other or in synchronism with each other.

Abstract: Aircraft landing gear comprised of a wheel hub motor/generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The invention can provide motive force to the wheel when electrical power is applied, e.g. prior to touch-down, thus decreasing the difference in relative velocities of the tire radial velocity with that of the relative velocity of the runway and reducing the sliding friction wear of the tire. After touchdown the wheel hub motor/generator may be used as a generator thus applying a regenerative braking force and/or a motorized braking action to the wheel. The energy generated upon landing maybe dissipated through a resistor and/or stored for later use in providing a source for motive power to the aircraft wheels for taxiing and ground maneuvers of the aircraft. Methods and apparatuses for nose gear steering and ABS braking using the disclosed invention are described.

Abstract: A ram air inlet includes a channel with an intake in a wing leading edge, front and rear flaps arranged in the channel for selectively closing or opening the channel, and an actuator connected to the flaps. A front end of the front flap is pivotably connected by a fixed bearing to an aircraft structure adjacent the intake. A rear end of the rear flap is moveably and pivotably mounted to the aircraft structure via a movable bearing arrangement, e.g. a pivot bearing linearly movable in guide tracks, or a flexible lever connected to a fixed pivot bearing, or a swinging bearing pivotably connected to a fixed bearing. The opposite ends of the flaps are pivotably connected to each other by a third bearing. The actuator drives the third bearing to pivot the front flap between opened and closed positions, while the rear flap pivots and moves in the wing chord and/or thickness directions.

Abstract: A method and apparatus are disclosed for treating fuel to temporarily reduce its combustibility, and thereafter restore its combustibility. As used in an aircraft, the method comprises the following steps: (a) treating aircraft engine fuel to substantially reduce its combustibility in open air; (b) carrying the treated fuel in a fuel tank of an aircraft; (c) increasing the combustibility of a portion of the treated fuel, as needed by the aircraft engine; and (d) supplying the increased restored combustibility fuel to the aircraft engine. Using this method, the preponderance of the fuel on board the aircraft is maintained at low combustibility for safety.

Abstract: A fluid-structure interactive analysis is performed while n types of wing structure models are caused to flap in accordance with a prescribed model of flapping manner. Based on an analysis, data 1, data 2, . . . data n of physical values related to fluid behavior and physical values related to structural behavior are calculated. Among data 1, data 2, . . . data n, a data having a prescribed parameter such as the lift force optimized is extracted. A prototype of a wing portion is formed, which has such a structure that is specified by various parameter values of the numerical model of wing structure corresponding to the extracted data. A driving unit 905 drives the prototype of the wing portion in a manner of flapping that is represented by the flapping motion model equivalent to the manner of flapping of an insect. At this time, the wing has a stiffness that is suitable for flapping flight so that prescribed parameters come to have optimal values.

Abstract: In one preferred embodiment, a structure is provided that includes a body having a first wall and a second wall. At least one appending component extends from an end of the body and includes a first skin and second skin. The structure additionally includes at least one actuator positioned within a cavity formed in the body first wall and the appending component second skin. The actuator includes at least one shape memory alloy (SMA) wire adapted to constrict when activated to move the first skin of the appending component from a first position to a second position.

Abstract: A reconfigurable interior sidewall system includes one or more simply curved sidewall panels, each curved around the fuselage but longitudinally linear and providing a consistent mating surface for monuments. Panel openings are provided in each panel so that inner window assemblies may be installed for opposing structural windows, each inner window assembly having outward sculpturing for additional cabin room. A cover plate is also provided for flush insertion into the opening to fill the opening when it is not needed and to provide a constant profile for cabin monuments whenever the layout of the cabin changes. This results in the production of fewer parts as well as facilitating faster and less expensive interior reconfigurations.

Abstract: A projectile for a weapon comprises an axially movable firing pin, an initiator actuable when impinged by the firing pin, a plurality of external peripheral fins movable from a radially inward position to a radially outward position when the projectile leaves the weapon, fin engaging means for moving each fin from the radially inward position to the radially outward position and for maintaining each fin in the radially outward position, and internal actuating means for actuating the fin engaging means to engage and thereby move the fins to deploy from the radially inward to the radially outward position as the projectile leaves the weapon.

Abstract: A munition is presented which includes an integrity verification system that measures the integrity of the munition. When an integrity threshold is not met, engagement of the munition with a predetermined target is aborted. Also presented is a methodology for gating the engagement of the munition with the target. The methodology includes performing an integrity check of the munition after it is deployed. The method further includes aborting the engagement of the target when the integrity check of the munition fails.

Abstract: An orbital debris shield for protecting the hull of a spacecraft is claimed. The shield is comprised of a number of flexible and releasably attached gores that substantially cover the hull. Interleafed between layers of the gores are layers of a spacing material. As debris collides with the gores, the material is shocked and breaks up to some degree. As the shocked debris disperses through a layer of the gore, the spacing material interacts with the debris. After dispersing through a number of layers of the gores and the spacing material, the debris transfers a significant portion of kinetic energy and the probability of the remaining particles piercing the hull is significantly decreased.

Abstract: A VTOL aircraft includes a wing, a propulsion system, and an air dam. The propulsion system is located in a central void formed in the wing to cause air flow from an outer perimeter of the wing over the wing and down through the void to generate lift. The air dam is located over the central void to promote flow of air over the wing. The aircraft also may utilize sub-atmospheric pressure gas to reduce the relative weight of the aircraft.