567 results about "Payload" patented technology

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.

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.

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.

The invention is a flying object equipped with a loading part holding a delivery payload, and the loading part or the delivery payload is attached to an airframe so that the loading part or the delivery payload is tilted backward in the forward and backward direction in a landing state or hovering state. The loading part or delivery payload is attached to the airframe so that the loading part or delivery payload is substantially horizontal during cruising.

The invention relates to the technical field of hoisting load unmanned aerial vehicles, in particular to a hoisting load unmanned aerial vehicle load distribution algorithm, which comprises the following steps: acquiring attitude data, load position coordinates and quality of an unmanned aerial vehicle body in real time, and detecting environment wind field distribution; constructing a dynamic graph structure including the unmanned aerial vehicle attitude data, the load position coordinates and quality and the environmental wind field nodes; calculating a current total gravity center deviation, a physical residual error and a compensation weight matrix of each execution mechanism; generating a compensation instruction by using a space-time fusion prediction network, inputting historical wind field data and a current node state, and predicting a load offset in a future time window through a space-time fusion neural network; calculating a target displacement of a balancing weight and a flexible tentacle joint angle sequence; the balancing weight is controlled to move to the target displacement along the linear guide rail, and the flexible tentacle joint is driven to reach the target angle; incremental compensation is carried out based on the adjusted total gravity center position; vibration energy at a main resonant frequency is suppressed.

The invention provides a sub-orbital return type load cabin structure device, which adopts a blunt end cone integral structure and comprises an end cap, a main structure cone section, a pneumatic heat-proof arc bottom, a parachute cabin structure, a load mounting disc and a heat-proof system, the end cap is connected to the top of the main structure conical section, and the pneumatic heat-proof arc bottom is connected to the bottom of the main structure conical section. The end cap is used for adjusting the axial mass center of the whole cabin and bearing main impact load during landing; the parachute bay structure is located in the main structure conical section and is designed with the main structure conical section in an integrated configuration mode. The load mounting disc is connected with the main structure conical section; the heat protection system is arranged on the end cap, the main structure conical section, the pneumatic heat protection arc bottom and / or a parachute cabin cover of the parachute cabin structure and used for reducing the temperature in the cabin. The structure layout is reasonable, the structure efficiency is high, the pneumatic stability is good, and the partial reuse capacity is achieved.

The invention discloses a data link breakage data processing method, which aims at the problem of loss of return load information caused by instability of a data link in a flight platform, periodically detects a link communication state in real time, and stores received information in a memory in a classified manner when the link is interrupted. After the link is recovered, the information stored in the memory and the real-time data are respectively transmitted back to the ground according to the importance degree, so that the load information in the link breaking process is quickly retransmitted under the condition that no additional hardware device is added to the data link, the integrity of the transmitted back load information is ensured, and the problem of information loss in the traditional data link breaking period is solved.

An air drop rack assembly is mounted within the cargo compartment of a cargo aircraft and has a forward part secured to the load deck and an aft part secured to the aircraft cargo ramp. The rack parts have rollers in conveyor assemblies mounted between C-channels which engage skidboards which support smaller aircraft such as gliders or cruise missiles. When the ramp is up two rack parts are tilted with respect to each other. At payload drop, ramp is deployed to bring the rack part conveyor assemblies into alignment. Although the aligned rack parts are spaced apart, when the cargo aircraft is tilted upwardly, the individual payloads on skidboards are discharged out the aircraft aft opening. Cruise missiles or bombs may be supported on a skidboard with a deformable surface, a forward ballast weight, and a spring, such that once launched the skidboard is pushed away from the payload.

An aircraft having a plurality of independent yaw control mechanisms includes an airframe having a central fuselage sized to hold at least one operator or payload and a wing extending from the fuselage. The aircraft includes a distributed thrust array coupled to the airframe, the thrust array having at least a first, second, and third pair of propulsion assemblies. Each propulsion assembly includes a rotor and is operable for at least single-axis thrust vectoring. The aircraft further includes a flight control system operable to independently control and combine each yaw mechanism of the propulsion assemblies. The yaw mechanisms for inducing a yaw moment include: canting at least one pair of propulsion assemblies away from the fuselage, selectively tilting at least one pair of propulsion assemblies forwards and backwards, varying an aerodynamic control surface of at least one propulsion assembly, and varying a rotational speed of at least one propulsion assembly.

A payload container includes a nose cone electronics hub assembly, a collar assembly, a canister assembly, and a grid fin system. The nose cone electronics hub assembly has a nose cone housing electronic components in support of flight and detonator systems. The collar assembly includes a collar coupling the nose cone electronics hub and canister together. A canister of the canister assembly houses separate parts when in a shipping configuration that can be attached to an exterior of the payload container in a deployment configuration. A fin assembly facilitates vertical descent of the payload container when dropped from an unmanned aircraft.

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

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.

A system and method for managing autonomous aerial vehicle ingress and payload exchange is disclosed. A beacon unit receives a digitally encoded ingress request from an autonomous aerial vehicle, the request comprising an identity token. A smart contract engine evaluates the identity token against mission-specific conditions to authorize ingress. An environmental analysis processor generates a map of the region surrounding the beacon unit using data from multiple sensor modules, including LiDAR, radar, infrared, audio, and weather sensors. A trajectory guidance engine computes an ingress path based on the environmental map. A virtual protected area generation module defines a three-dimensional protected zone for descent, and a classification engine assigns a safety classification to the zone based on predefined criteria. A beacon control interface transmits the ingress path to the vehicle and monitors descent for compliance. A user authentication subsystem verifies the identity of a human user at the landing zone prior to payload release.

Spacecrafts are disclosed herein. The spacecraft can include a primary payload sensor, the primary payload sensor being aligned to capture images in a direction of a first axis, and at least one secondary imaging system for determining a position of the spacecraft, the at least one secondary imaging system being aligned to capture images in the direction of a second axis. The at least one secondary imaging system can include a housing, the housing including a first end and a second end, wherein the first end includes an opening into an internal portion of the housing, an image sensor positioned within the internal portion of the housing, and an optical element positioned within the internal portion of the housing, wherein the optical element has a length parameter and a width parameter, wherein one of the length parameter and the width parameter is larger than the other parameter.

Modular flying platform including an airship body defining an internal space and configured to achieve buoyancy, an internal structure supporting a transfer channel, an attachment mechanism positioned on the transfer channel to detachably connect with a second platform. The transfer channel is configured to permit transfer therethrough of a payload between the flying platforms when securely connected. A chain of modular flying platforms with one or more motors mounted to the airship body to control motion thereof. A method for managing a chain of modular flying platforms includes deploying a plurality of platforms, connecting the platforms to form the chain, transferring a payload through channels of the connected platforms and distributing at least one of propulsion, electrical power and computing across the chain.

Systems and methods for traffic inspection using payload offsets include performing inline monitoring between one or more endpoints and the internet; receiving a payload based on the inline monitoring; and performing traffic inspection of the payload based on one or more inspection offset values, wherein the one or more inspection offset values define one or more points within the payload for inspection to begin.

Embodiments of a payload attachment system secure a missile, a suicide drone, or other ordinance to a wing or fuselage of a combat drone (or another type of aircraft) using one or more vacuum mounting modules, wherein each vacuum mounting module comprises at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives an instruction corresponding to one of a vacuum cup actuation signal or a vacuum cup release signal.

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.

To provide a work machine that can reduce the effort involved in transmitting payload information from the operator of the work machine to the driver of the transport vehicle. [Solution] The work machine 100 comprises a lower traveling body 1, an upper rotating body 3 rotatably mounted on the lower traveling body 1, an attachment AT attached to the upper rotating body 3, an information acquisition device IAD that uses the attachment AT to acquire payload information, which is information regarding the weight of the goods loaded on the cargo bed of the transport vehicle 200, and a wireless communication device 50 that transmits the payload information to an operator's portable terminal device SP1 capable of wireless communication with the transport vehicle 200.

The invention provides a side vertical type deployable device for lunar surface load transfer. The side vertical type deployable device comprises a tripod, a rotary base, a large arm, a small arm, a large arm folding mechanism, a small arm folding mechanism and a grabbing mechanism. The side-standing type deployable device is in a folded state in the transportation process from the earth to the lunar surface, and the whole side-standing type deployable device stands on a lunar surface platform; the side vertical type deployable device is in an unfolded state in the lunar surface working process, the large arm and the small arm can be controlled to move, and load transfer is achieved. The device has the advantages of multi-target accurate capture, transfer and multi-point release, large bearing, large-range movement, large-tolerance capture, small occupied space of a spacecraft, light weight and capability of realizing multi-module transfer and release. In addition, the side vertical type deployable device is pressed through folding, and space transportation is facilitated.

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

The invention relates to a flexible connection load transfer function identification method based on active frequency sweep excitation, and relates to the field of spacecraft attitude control, and the method comprises the following steps: a plurality of three-super platform actuators sequentially output sine frequency sweep excitation moments of a load in three rotation directions, and a high-bandwidth fiber-optic gyroscope simultaneously measures the triaxial angular velocity of the load; the obtained time domain result is converted into a frequency domain result, and then load transfer function model identification is carried out; and adjusting controller parameters in the three-super platform control unit based on the identification model so as to increase the control bandwidth and improve the secondary control capability on the basis of ensuring the stability margin of the controller in the three-super platform control unit. And a technical basis is provided for ultrahigh-precision pointing, ultrahigh-stability control and high-quality imaging of optical loads of spacecrafts in the future.

A roll decoupling joint is provided for connecting a rocket motor to a payload. The joint includes a payload adapter, a motor sleeve, a rotational separator and a fastener. The adapter includes an annular socket and a cylindrical core. The socket is bounded by an opening lip and a bulkhead. The payload inserts into the socket through the lip. The core extends axially from the bulkhead opposite the lip. The sleeve is annularly axi-symmetric and inserts into the motor. This sleeve is disposed adjacent to the adapter and around the core supported by the separator. The fastener secures the core to the separator. In various embodiments, the separator constitutes a pair of bearings, and the fastener is a threaded bolt.

A payload retrieval system includes a support structure and a retriever guide coupled to the support structure. The retriever guide includes a body that forms a channel having an inlet end and an exit end and a tether slot that provides access to the channel. The retriever guide is adapted to receive, at the inlet end of the channel, a payload retriever secured to a tether and to direct the payload retriever to the exit end of the channel while the tether pulls the payload retriever through the retriever guide. The retriever guide also includes a first retaining wall extending upward from the body of the retriever guide along a first side of the tether slot and a second retaining wall extending upward from the body of the retriever guide along a second side of the tether slot. The payload retrieval system also includes a payload holder disposed at the exit end of the channel.

The invention relates to a method for securing transmission of payload (17) from a transmitter device (3) to a receiver device (4). The payload (17) is calculated by a primary module (7) of the transmitter device (3) and, redundantly thereto, corresponding payload is calculated by a secondary module (8) of the transmitter device (3). The payload (17) calculated by the primary module (7) and a check value (20) calculated by the secondary module (8) for the payload calculated by the secondary module are combined in an overall data record (21). This overall data record (21) is then transmitted from the transmitter device (3) to the receiver device (4), with a check being carried out as to whether the contained check value (20) matches the contained payload (17). If this is not the case, an error is identified. The invention also relates to a corresponding transmitter device (3) and to a motor vehicle (1) configured for the method.

In accordance with one aspect of the inventive concepts, provided is an autonomous mobile robot, comprising: at least one processor in communication with at least one computer memory device; at least one sensor positioned on the robot to acquire data indicating a position of a payload along fork tines of the robot, the data comprising at least one of discrete and continuous measurements; and a payload monitoring system comprising computer program code executable by the at least one processor to monitor one of pushing and dragging of the payload based on the data. A corresponding method is also provided.

An unmanned aerial vehicle (UAV) includes a UAV body constructed and arranged to carry a payload, a set of UAV wings coupled with the UAV body, and a set of undercarriage apparatus coupled with at least one of the UAV body and the set of UAV wings. The set of UAV wings is constructed and arranged to provide lift to the UAV. At least one undercarriage apparatus of the set of undercarriage apparatus includes an elastomeric vehicle mount, a leg, and a coupling constructed and arranged to couple the leg with the elastomeric vehicle mount. The elastomeric vehicle mount is constructed and arranged to absorb energy provided from the leg through the coupling.

This invention discloses an integrated assembly structure and operating method for a multi-rotor unmanned aerial vehicle (UAV) used for rescue reconnaissance. The structure includes: a main frame unit, a hierarchical integration unit, a mission execution unit, and an autonomous control and coordination unit. The main frame unit adopts an integrated structure to support various functional modules and ensure flight and landing stability. The hierarchical integration unit employs a layered layout design to achieve efficient integration and interference isolation of various functional modules. The mission execution unit includes a payload delivery mechanism for reliable mounting and precise release of standard rescue payloads. The autonomous control and coordination unit enables autonomous execution of the entire "identification-deployment-return" process, establishing a collaborative link between structure and function through algorithm deployment and protocol adaptation. This invention features a compact structure, convenient assembly and disassembly, high integration of core modules, and stable support for autonomous deployment and target identification tasks in rescue reconnaissance, demonstrating strong adaptability and practicality.

1. The name of the design product: Launch Vehicle (Chirei 6). 2. The use of the design product: used for space transportation, sending the payload such as artificial earth satellites, manned spacecraft, space stations or space probes into the predetermined space orbit. 3. The design points of the design product: the combination of shape, pattern and color. 4. The picture or photo that best shows the design points: perspective view. 5. The design claimed contains color.

A payload retrieval apparatus is provided including a channel having a first end and a second end provided with a curved portion, wherein the channel has a tether slot therein and is configured to receive a payload retriever attached to a tether suspended from a UAV; and a payload holder positioned at the second end of the channel on the curved portion, wherein the payload holder is adapted to hold a payload having a handle with an opening therein, wherein the curved portion is configured to change an exit angle of the payload retriever such that a lip of the payload retriever is angled upwardly to ease entry of the lip into the opening of the handle of the payload.