1142 results about "Payload" patented technology

An unmanned aerial vehicle (UAV) is disclosed that includes a retractable payload delivery system. The payload delivery system can lower a payload to the ground using a delivery device that secures the payload during descent and releases the payload upon reaching the ground. The location of the delivery device can be determined as it is lowered to the ground using image tracking. The UAV can include an imaging system that captures image data of the suspended delivery device and identifies image coordinates of the delivery device, and the image coordinates can then be mapped to a location. The UAV may also be configured to account for any deviations from a planned path of descent in real time to effect accurate delivery locations of released payloads.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a gas-electric hybrid composite wing unmanned aerial vehicle system, which comprises an intelligent energy management module, a gas-electric hybrid composite wing unmanned aerial vehicle control module and a gas-electric hybrid composite wing unmanned aerial vehicle control module, the self-adaptive flight control module is used for optimizing the flight attitude, dynamically adjusting the flight route and improving the flight safety; the task adaptive scheduling module is used for adaptively adjusting a task execution strategy according to the task category, the load condition and the environmental parameters; the data monitoring and remote control module is used for collecting the operation state of the unmanned aerial vehicle in real time and storing and analyzing flight data; the intelligent safety management module is used for improving the autonomous safety of the unmanned aerial vehicle; and the environment perception optimization module is used for perceiving external environment factors in real time. According to the invention, the intelligent energy management module realizes intelligent scheduling of fuel and electricity power, and dynamically optimizes the power distribution of the battery and fuel oil, so that the flight time of the unmanned aerial vehicle is greatly prolonged.

Intelligent optimization of mission planning and execution for spacecraft through intelligent analysis of mission objectives and payload operation is disclosed. Values for mission objectives, payload operation, and / or vehicle conditions may be defined during given time periods, including variable values for repeat operations or other factors. These values may then be used through a vehicle / mission simulation agent to optimize the mission plan through maximizing the mission score according to the values. The simulation agent may identify possible mission plans based on vehicle capability, and then score the mission plan based on the total objective score.

A craft is provided comprising: a propulsion system; a fuselage coupled with the propulsion system, wherein the fuselage is configured to carry a payload and fuel for the propulsion system; and a pre-assembled wing coupled with the fuselage; wherein the craft is designed to take-off without using a runway and does not have landing gear to land.

The invention provides a new class of transportation with a partially aerostatically supported ram air cushion ship (PASRACS) that can provide safe, fast, efficient global transport services with extraordinary comfort, luxury and amenities. The PASRACS employs inventive synergistic combinations of lift from aerostatic, aerodynamic, hydrostatic and hydrodynamic forces for different modes of operation ranging from a stationary floating configuration on a water surface, to flight in ground effect at high speed. A propulsion system can utilize hydrogen as an energy source driving fluid-dynamic thrusters, to enable zero carbon emissions operations. A transition method is provided for a PASRACS to transition from a floating mode to a takeoff mode to a flight in ground-effect mode in an inventive optimized manner. A transport method for multimodally transporting payload is provided with PASRACS vehicles and systems, with quick turn time operations enabled by the use of payload transfer transport modules and transfer vehicles.

An autonomous flying device achieving a large payload and a long continuous flight time and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.

A UAV for transporting a payload comprising a vehicle body; a retractable rail exposed on an underside of the vehicle body; a retraction mechanism coupling the rail to the vehicle body for causing the rail to raise and lower relative to the vehicle body; and a barrier located on the vehicle body so as to confront the rail when the rail is in its raised position to block the removal from the rail of a payload slidably engaged with the rail. A mechanism for advancing a payload onto and along the rail and pushing it off.

The invention comprises an apparatus, method for using the apparatus and system for balloon altitude control by in-situ characterization and active energy management. The invention presented enables transportation, autonomous operation and use of a balloon beyond the limits of conventional high-altitude ballooning to the edge of the atmosphere, or about 100 km above the surface of the Earth. The apparatus comprises at least: an envelope containing lift-gas; an envelope and lift-gas characterizer; an altitude control system operated using active energy addition and lift-gas transfer or ambient air introduction into the system; and an external payload component. The invention is capable of operating in ascent, descent, or stationary mode; the altitudinal movement of the balloon is caused by measuring in-situ envelope and lift-gas characteristics, identifying the change in the lift-gas energy needed, and facilitating the required energy change for altitude control.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The first wing can be coupled to the boom by a (first) articulated joint. The propulsion assembly can be coupled to the boom by a (second) articulated joint. The articulated joints can provide various adjustments between the wing(s) and the boom (e.g., stowed, deployed, anhedral, dihedral, sweep, angle of attack, collective pitch control, the cyclic pitch control, etc.) and between the propulsion system and the boom (e.g., to move between vertical flight and horizontal flight). A payload can be connected to the boom with one of the articulated joints whereby the articulated joint adjusts a position of the payload during flight to maintain desired flight characteristics and stabilize the payload.

The invention relates to a coaxial multi-rotor unmanned aerial vehicle control method based on a Koopman operator, and the method comprises the steps: constructing a deep neural network based on the Koopman operator, and mapping a state variable to a high-dimensional observable space through an encoder; in a high-dimensional observable space, state variables are predicted through a linear connection layer based on dimension rising state variables and rotor rotating speeds; the decoder restores the prediction result to an original state space; training a deep neural network by using historical flight data to obtain codec parameters and a weight of a linear connection layer, and constructing a linear dynamic model of the observation function and the unmanned aerial vehicle; and the prediction controller predicts state variables of future multiple steps of the unmanned aerial vehicle by using a linear dynamics model, and enables the unmanned aerial vehicle to track a given trajectory by minimizing a cost function to obtain optimal control input. Compared with the prior art, the method has the advantages that complete data-driven modeling is realized, and the method can adapt to unmanned aerial vehicles with different sizes, loads and flight conditions.

The invention belongs to the technical field of boundary layer detection, and particularly relates to an unmanned aerial vehicle atmospheric boundary layer environment autonomous detection system and method.The unmanned aerial vehicle atmospheric boundary layer environment autonomous detection system comprises an unmanned aerial vehicle platform, a detection load subsystem, a flight control subsystem, a data processing subsystem and a ground station subsystem, and the unmanned aerial vehicle platform comprises an unmanned aerial vehicle, a flight control module and a communication module; the unmanned aerial vehicle is made of light-weight composite materials and has good structural strength and weather resistance, an equipment cabin, a battery cabin and a load cabin are arranged in a vehicle body, modular design is adopted, maintenance and upgrading are convenient, in addition, the unmanned aerial vehicle is further provided with an energy module and a power module, and energy and power are provided for the unmanned aerial vehicle; the flight control module comprises a flight control computer, an inertial measurement unit I MU and a GPS / Beidou dual-mode receiver. The unmanned aerial vehicle can effectively avoid movable obstacles such as birds in an atmospheric boundary layer and a strong turbulence area when carrying out environment detection, and the flight safety of the unmanned aerial vehicle during detection is guaranteed.

The disclosure is directed in part to variant capsid polypeptides that can be used to deliver payloads.

The disclosure is directed in part to variant capsid polypeptides that can be used to deliver payloads.

An embodiment herein provides a re-configurable unmanned aerial vehicle that re-configures its shape based on the shape, size, weight of a payload, and efficiently performs payload delivery in real-time. The re-configurable unmanned aerial vehicle includes one or more rotor units placed at corners and is connected by one or more scissor units. The re-configurable unmanned aerial vehicle approaches the payload in a first location, and analyses the position and dimension of the payload with a camera, that enables the one or more scissor units to adjust its length by at least one elongation or compression following size and shape of the payload and fit the payload within the re-configurable unmanned aerial vehicle. The re-configurable unmanned aerial vehicle takes off carrying the payload from the first location and lands at a second location.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

Disclosed here are unmanned aerial vehicle embodiments including some embodiments having a fuselage, tail, and wings including example embodiments with an adaptable payload section, alternatively or additionally, modular flight surfaces including tail, wings and motor, alternatively or additionally the vehicle configured for short landings with reversible thrust, alternatively or additionally, the unmanned aerial vehicle configured with direct connection to moveable flight control surfaces.

Systems, devices and methods related to unmanned aerial vehicles and landing systems are described herein. One example disclosed unmanned aerial vehicle comprises a vehicle body comprising an airfoil shape, a plurality of rotors, a payload void within the airfoil shape profile, and a rotatable payload bay disposed within the payload void. A payload delivery system is also described. The payload delivery system comprises a payload void, a payload bay, at least one actuator operative to rotate the payload bay with respect to the payload void, and a payload controller operative to eject a payload from the payload bay. Several landing systems and devices for unmanned vehicles are also described. One example landing device comprises a frame comprising a rear surface operative to attach the frame to a vertical glass surface and an aircraft support element operative to receive and support an unmanned aerial vehicle.

The present invention discloses a flapping-wing aircraft capable of catapult takeoff and having a sweep-torsion mechanism, belonging to the field of aircraft technology. The aircraft comprises: a fuselage frame, left and right flapping wings, a passive torsion mechanism, a sweep mechanism, a catapult takeoff mechanism, a transmission flapping mechanism, and a tail rudder, wherein: a passive torsion mechanism and a sweep mechanism are provided at the roots of the left and right flapping wings, the catapult takeoff mechanism is provided in the middle of the fuselage, and a hip joint, thigh, ankle joint, calf, foot, and toe joint are provided from top to bottom, the inner and outer sides of the hip joint are controlled by a servo motor for relative rotation, the ankle joint and toe joint are provided with elastic energy storage torsion springs, a synchronous pulley and its drive mechanism are provided between the outer side of the hip joint and the outer side of the ankle joint to control the relative rotation between the thigh and the calf, and perform energy storage for catapult takeoff. In summary, the aircraft can perform catapult takeoff flight, and can perform passive torsion and sweeping motions during the flapping of the wings, which helps to increase the flapping wing lift and the overall payload of the aircraft.

A method of assembling a delivery payload assembly configured to be deployed from an aircraft and travel along a flight path to a predetermined landing destination includes attaching a tail-kit assembly to a first end of a payload, the tail-kit assembly including a rotor blade assembly including a plurality of rotor blades having a central axis of rotation, and a flight control and navigation system configured to control a collective pitch angle of each of the plurality of rotor blades of the rotor blade assembly, configured to control an axial thrust force of the rotor blade assembly, the axial thrust force being at an angle with respect to the central axis of rotation of the rotor blade assembly, and configured to navigate the delivery payload assembly along the flight path to the predetermined landing destination. The method further includes removing the tail-kit assembly from the payload after the payload is delivered to the predetermined landing destination.

A payload including a housing provided with one or more toothed guides or with one or more docking mechanisms, each of which is configured to detachably toothedly interact with an unmanned aircraft apparatus being docked so as to enable the movement of said docked unmanned aircraft apparatus with respect to the housing of the payload, wherein the housing of the payload is further configured to detachably toothedly interact with yet another (other) unmanned aircraft apparatus so as to enable the action of said yet another unmanned aircraft apparatus onto said docked unmanned aircraft apparatus for withdrawal of the latter from interaction with the housing of the payload. Furthermore, embodiments of an air transport system include two or more unmanned aircraft apparatuses and one of the payload.

The utility model discloses a cylindrical launch folding wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a square fuselage and a conical nose cover, a concave platform is arranged below the middle rear section of the fuselage, foldable wings are arranged in the concave platform, foldable empennages are arranged on the two side faces, close to the tail, of the fuselage, and the tail of the fuselage is connected with the tail of the fuselage. A foldable propeller is arranged at the tail of the fuselage, two blades of the propeller can be folded and retracted into an upper arc-shaped groove and a lower arc-shaped groove, close to the tail, of the fuselage respectively, a pod, a parachute cabin and a GPS antenna cabin are integrated in the nose cover, and a load cabin, a battery cabin and an equipment cabin are sequentially arranged at the front section, the middle section and the rear section of the fuselage. According to the cylindrical launching folding wing unmanned aerial vehicle, the design of the conical nose cover, the square fuselage, the lower single wing and the V-shaped empennage is adopted, launching is carried out through the square launching cylinder during launching, a plurality of cabin sections are designed in the square fuselage, each cabin section is fully utilized under the condition that the gravity center of the unmanned aerial vehicle is proper, and the assembly efficiency is greatly improved.

The present invention relates to a ring-synchronized separation adapter for separating a payload in a space environment, and more specifically, to a ring-synchronized separation adapter for separating a payload in space environment, in which the ring-synchronized separation adapter has a configuration in which a plurality of segmented clamp portions are simultaneously fastened or unfastened by rotating a drive member making contact with all of the plurality of segmented clamp portions, so that accuracy in separation of the payload is improved, explosion is not utilized, and stability of the ring-synchronized separation adapter is improved as a whole.

A system for deploying a payload from an aerial vehicle onto a target surface includes a flywheel-stabilized delivery device that is detachably couplable to the aerial vehicle. The delivery device includes an axle, a flywheel, and a payload holder. The delivery device may additionally include an attachment portion and a floatation device. The payload holder may be detachably coupled to the payload such that the delivery device detaches from payload upon impact at the target surface. The system may additionally include a release mechanism for detachably coupling the delivery device to the aerial vehicle. The release mechanism may include a flywheel driver, a receiver, and a dropper device. The release mechanism may be remotely controlled by an operator to release the delivery device from the aerial vehicle.

An unmanned aerial vehicle system including an unmanned aerial vehicle (UAV); a tether having a first end positioned in a winch system of the UAV and a second end secured to a payload coupling apparatus; a payload coupling apparatus receptacle positioned in the UAV; a payload having a handle, wherein the handle of the payload is positioned within a slot in the payload coupling apparatus; wherein the UAV has a recessed restraint slot for receiving a top portion of the payload.

A tool for loading a payload on a payload retrieval apparatus includes a support body and a guide extending outward from the support body. The guide has an elongated configuration and a cross-sectional area that is narrower than the support body. The guide is configured to be inserted into a channel of the payload retrieval apparatus and to position the support body at an end of the channel adjacent to a payload holding structure. The tool also includes a hanger configured to hold the payload. The hanger is movable with respect to the support body between a closed position and a release position.

There is disclosed an autonomous docking system for aerial delivery of a payload from a ground station. The system may comprise an unmanned aerial vehicle (UAV) having one or more motors for powered flight and a pyramidal bottom surface opening downward to terminate in a base perimeter. A cargo pod may be included to carry the payload and may have a pyramidal top surface complementary to the pyramidal bottom surface of the UAV. The system may further include a latching system for locking the UAV to the cargo pod and one or more steering components for approaching the cargo to within a steering accuracy. The UAV may be configured to dock by steering downward until the base perimeter slidably contacts the pyramidal top surface of the cargo pod for gravity-aligning the UAV in azimuth and laterally. The system may be further defined by a capture radius of the base perimeter being greater than a lateral component of the steering accuracy.

An autonomous transport vehicle for transporting a payload comprising, a frame forming a transport payload area of the autonomous transport vehicle, the payload area includes a payload contact support surface that defines a payload support plane of the autonomous transport vehicle that supports the payload held in the transport payload area with vehicle traverse, a payload handling system connected to the frame, the payload handling system having, a payload transport disposed to engage the payload and transport the payload in at least one direction relative to the frame, and a drive section with at least one degree of freedom driving the payload transport in the at least one direction; and a controller operably connected to the drive section configured to register predetermined operating data embodying at least one dynamic performance variable output by the drive section effecting a predetermined motion, that defines a predetermined common motion manifold, of the payload.

Systems and methods for locating UAV. The methods comprise: causing a physical joining of a payload with a fuselage of the UAV (where the payload comprises a communication relay); using a power source to supply power to the payload that is independent from a main power source of the UAV; and continuing to perform relay operations by the communication relay and location operations by a first locator, when power is no longer being supplied by the main power source.

A system includes a platform interface having a base configured to be secured to a platform or integrated with the platform. The base is configured to rotatably engage with a support of a payload interface to secure the payload interface to the platform interface, the support being configured to be secured to a payload. A first electrical connector of the platform interface is configured to engage with a second electrical connector affixed to the support, and to rotate with the second electrical connector relative to the base as the support is rotated to engage the base. Other features, systems, and methods are also provided.

Combined aerospace system is a multi-stage technology to deliver payloads to orbit and to midair. The system comprises a carrier aircraft, a tow aircraft, a towed spaceplane or a rocket plane or a glider. The carrier aircraft, coupled with the spaceplane and / or the rocket plane or several gliders, takeoff from a runway and ascends to a staging altitude and speed under the carrier aircraft power. After staging, the tow aircraft will pick up the spaceplane or the rocket plane or the glider from the carrier aircraft in flight. The towed spaceplane or the rocket plane or the glider continues ascending and accelerating by the tow aircraft. The spaceplane or the rocket plane will disconnect from the tow aircraft and continue to ascend and accelerate in an atmosphere by using the ramjet engine. The spaceplane or the rocket plane equipped with a propulsion unit is used to place the spacecraft into the earth orbit. The glider will disconnect from the tow aircraft and lands in designated place. Gliders can be used for instantly delivering of correspondence, parcels, and civil goods from a supplier to wide variety of individual consumers or corporate customers.