Systems, devices, and methods for an aircraft autopilot guidance control system (100, 300) for guiding an aircraft having a body, the system comprising: a processor (101) configured to determine if a yaw angle difference and a pitch angle difference meet corresponding angle thresholds; a skid-to-turn module (105) configured to generate a skid-to-turn signal if the corresponding angle thresholds are met; a bank-to-turn module (102) configured to generate a bank-to-turn signal having a lower bandwidth than the generated skid-to-turn signal; a rudder integrator module (104) configured to add a rudder integrator feedback signal to the bank-to-turn signal, where the rudder integrator feedback signal is proportional to a rudder integrator; and a filter module (103) configured to filter the generated bank-to-turn signal, wherein the filter module (103) comprises a low-pass filter configured by a set of gains to pass the bank-to-turn signal if a side force on the body meets a side force threshold (111).
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
Systems, devices, and methods for an extruded wing protection and control surface (126) comprising: a channel (206) proximate a leading edge (202) of the control surface, a knuckle (210) disposed about the channel, a leading void (212), a trailing void (214), and a separator (216) dividing the leading void and the trailing void; and a plurality of notches (200) disposed in the extruded control surface proximate the leading edge of the control surface.
Systems, devices, and methods for a safety system including: selecting an unmanned aerial vehicle (UAV) command (602, 604, 606) on a controller (104), the controller comprising a first processor (1324) with addressable memory (1327); presenting a first activator (430) and a second activator (420) on a display (400) of the controller for the selected UAV command, wherein the second activator is a slider (410); and sending the UAV command to a UAV (100) if the first activator and the second activator are selected, the UAV comprising a second processor (1324) with addressable memory (1327).
Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both si des of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
A lidar system, including a base, a sensor body, and a motor having a shaft. The motor is affixed to the base, and can drive the sensor body in rotation with respect to the base. An LED device and a light sensor are each mounted upon the sensor body. A data processing device is also mounted upon the sensor body, and is programmed to produce range information based upon the sensor data. The shaft carries two slip rings. The LED, the sensor and the data processing device all receive electrical power via the two slip rings. The data processing device is configured to transmit the range information via the two slip rings using pulse width modulation.
A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor (102) on a first aircraft (100); transmitting the first video (232) and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate (226) for a second aircraft (116) in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target (114) corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.
A shock resistant fuselage system includes first and second fuselage side walls (804, 806), each of the first and second fuselage side walls (804, 806) having a plurality of guide posts (802, 1006), and a printed circuit board (PCB) 800 rigidly attached to at least one of the first and second fuselage side walls (804, 806), the PCB 800 having a plurality of guide slots 1008, each of the plurality of guide posts (802, 1006) slideably seated in a respective one of the plurality of guide slots 1008 so that elastic deformation of the PCB 800 is guided by the guide slots 1008 between the first and second fuselage side walls (804, 806).
A remote targeting system includes a weapon (110), a display (120) on the weapon (110), a radio frequency (RF) receiver (140), a sensor (150) remote from the weapon (110), wherein the sensor (150) is configured to provide image metadata of a predicted impact point B on the weapon display (120), and a targeting device (130) including a data store (537) having ballistic information associated with a plurality of weapons and associated rounds, and a fire control controller (532) wherein the fire control controller (532) determines a predicted impact point B based on the ballistic information, elevation data received from an inertial measurement unit (534), azimuth data received from a magnetic compass (535), position data received from a position determining component (536), wherein the fire control controller (532) is in communication with the inertial measurement unit (534), the magnetic compass 535, and the position determining component (536).
A flight control apparatus for fixed-wing aircraft includes a first port wing (115) and first starboard wing (120), a first port swash plate (145) coupled between a first port rotor 155) and first port electric motor (135), the first port electric 5 motor (135) coupled to the first port wing (115), and a first starboard swash plate (150) coupled between a first starboard rotor (130) and first starboard electric motor (140), the first starboard electric motor (140) coupled to the first starboard wing (120).
B64C 15/02 - Commande de l'assiette, de la direction du vol ou de l'altitude par jets réactifs les jets étant des jets propulsifs
B64C 11/46 - Aménagements ou caractéristiques de construction des hélices multiples
B64C 27/26 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
10.
SYSTEM FOR DETACHABLY COUPLING AN UNMANNED AERIAL VEHICLE WITHIN A LAUNCH TUBE
A method of launching an unmanned aerial vehicle (UAV) launch, comprising: restraining a sabot in a launch tube; introducing gas to a high-pressure side of an expandable sabot skirt of a sabot to break said restraint of said sabot in said launch tube; pushing said expandable sabot skirt against an inner circumferential wall of said launch tube using said gas; and driving said sabot up said launch tube using said gas.
B64U 70/00 - Dispositions pour le lancement, le décollage ou l'atterrissage
F41B 11/80 - Armes de tir à gaz comprimé, p.ex. armes de tir à air comprimé; Armes de tir à vapeur spécialement adaptées à des utilisations particulières
An unmanned aerial vehicle (UAV) launch tube apparatus and method, including: a tube; a sabot disposed in an interior of said tube, said sabot having a first clasp tab, where said sabot further comprises an expandable skirt, and where said expandable skirt is axially restrained within said tube by an adhesive; and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube; where said clasp is rotationally constrained by said inner circumferential wall and said first clasp tab.
B64U 70/00 - Dispositions pour le lancement, le décollage ou l'atterrissage
F41B 11/80 - Armes de tir à gaz comprimé, p.ex. armes de tir à air comprimé; Armes de tir à vapeur spécialement adaptées à des utilisations particulières
In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.
In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.
A UAV which includes a payload module comprising a deployable payload. The UAV also includes a retraction mechanism apparatus capable of moving the payload from a stowed position within a UAV to a deployed position extending out of the UAV. The retraction mechanism is configured such that the payload retracts back into the UAV upon contact with a landing surface if the payload is not retracted before the UAV contacts the landing surface so as to reduce at least one of a probability, or a severity of damage to a deployed payload upon landing.
An unmanned aerial vehicle (UAV) launch tube (100) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture (305), and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).
B64C 13/20 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant des émissions de signaux
F41F 3/04 - Lanceurs de roquettes ou de torpilles pour roquettes
Described in one aspect an aerial vehicle comprising: a fuselage housing a first fuselage-mounted effector; a first airfoil comprising a first control surface resiliently mounted to the first airfoil, wherein the first control surface is opposed by the first fuselage-mounted effector; a second airfoil, rotatably attached to the fuselage housing; and a second fuselage-mounted effector disposed within the fuselage housing and extendible in part to engage the second airfoil, wherein the first fuselage-mounted effector is a first actuator horn extendible via a first fuselage aperture.
B64C 9/34 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments
B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 13/28 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques
An unmanned aerial vehicle (UAV) launch tube is provided for launching, for example, a non-cylindrical UAV. The tube defines a right rectangular aperture, and inner and outer layers of prepreg substrate are disposed about the aperture. At least four structural panels are disposed between the inner and outer layers of prepreg substrate The panels are disposed apart from one another, with there being space between the lateral edges of adjacent panels. Accordingly, the inner and outer layers of prepreg substrate contact one another at the corners of the right rectangular aperture.
An unmanned aerial vehicle (UAV) launch tube (100, 400, 600, 1010, 1310) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about an aperture (305), and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100, 400, 600, 1010, 1310) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).
B64C 13/20 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant des émissions de signaux
F41F 1/00 - Appareils de lancement éjectant des projectiles à partir d'un tube, p.ex. canons; Canons lance-harpons
F41F 3/04 - Lanceurs de roquettes ou de torpilles pour roquettes
19.
DYNAMIC TRANSMISSION CONTROL FOR A WIRELESS NETWORK
In one possible embodiment, a wireless network with dynamic transmission control is provided that includes a multiple of nodes. The nodes include an arbiter and multiple client nodes. The arbiter is configured to control an operation of the client nodes by defining communications operation cycles and allocating a bandwidth to each of the client nodes on a cycle by cycle basis in response to requests for bandwidth from the client nodes.
A system comprising an unmanned aerial vehicle (UAV) (100) configured to transition (520) from a terminal homing mode (510) to a target search mode (530), responsive to an uplink signal (451) and/or an au-tonomous determination of scene change.
An unmanned aerial vehicle (UAV) including a processing unit configured to transition the UAV from a trajectory approaching the target volume to a trajectory away from the target volume. The UAV is configured to maintain sufficient energy and maneuverability to transition from a trajectory approaching the target volume to a trajectory away from the target volume.
In one possible implementation, a method for forming a motor winding is provided which includes compressing a Litz wire to form a compacted Litz wire and forming the winding with the compacted Litz wire. In one possible embodiment, a motor winding is provided that has a high density multi-conductor wire bundle comprises of compacted Litz wire.
H02K 15/04 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques d'enroulements, avant leur montage dans les machines
H02K 3/04 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre
A charging system for simultaneously charging the batteries of a plurality of battery powered vehicles. The charging includes one or more DC-DC power converters having one or more charging ports configured to plug into the batteries. The DC-DC power converters are each configured to selectively connect to more than one charging port to selectively provide for higher port power levels. The DC-~DC power converters connect to an AC rectifier through a DC bus. The AC rectifier connects to an AC power source having a limited power rating. The AC charging system also has a controller that controls the operation of the DC-DC power converters such that the total power draw on the AC rectifier does not exceed the power rating. The system is further configured such that the DC-DC power converters can drain selected batteries to obtain power for charging other batteries, thus allowing for batteries to be cycled.
H02J 7/02 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries pour la charge des batteries par réseaux à courant alternatif au moyen de convertisseurs
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p.ex. batterie tampon
brevets
