286results about "Aircraft stabilisation by gravity apparatus" patented technology

A glider system capable of sustained long-term flight includes a fixed-wing glider having a dual fuselage system. The top surface of the glider is covered with a plurality of photovoltaic cells capable of powering onboard sensors, propeller systems, and / or onboard processers. The glider includes wing spars with a composite material covering an inner foam core, with the type of foam core or use of reinforcement materials differs along the length or width of the wing spars. The glider is able to downward facing sacrificial winglets to provide a landing system without the need for bulkier landing gear.

A rotary wing vehicle has a vehicle body. A gimbal assembly mounted to or within the body. A propeller assembly is mounted to the gimbal. The propeller assembly has first and second fixed pitch propellers. The gimbal assembly has a first gimbal rotatable about a first axis and a second gimbal rotatable about a second axis.

A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

The invention relates to the field of unmanned aerial vehicles, and discloses a high-wind-resistance multi-rotor unmanned aerial vehicle which comprises a vehicle body and vehicle arm supports arrayed on the side face of the vehicle body, a first motor is arranged at the tail end of each vehicle arm support, a propeller part is installed on an output shaft of each first motor, and the propeller parts are driven by steering engines to change the inclination angle; when the unmanned aerial vehicle encounters strong crosswind, the resistance of the unmanned aerial vehicle to the crosswind is improved by changing the rotation angles of the corresponding propellers and the propeller parts, so that the stability of the unmanned aerial vehicle encountering the strong crosswind in the flying process is improved, the thrust vector direction is changed, and the compensation force opposite to the wind pressure direction is generated. According to the dynamic adjustment mechanism, the unmanned aerial vehicle can keep the flight path stable under the strong crosswind condition, and the problem of flight path deviation caused by the fixed thrust direction of a traditional unmanned aerial vehicle is effectively avoided.

The invention relates to the technical field of unmanned aerial vehicle control, and discloses a fire-fighting unmanned aerial vehicle flight attitude instability control device and a control method thereof. The device at least comprises a control module which is configured to estimate an equivalent disturbance torque vector generated by throwing a fire extinguishing bomb in real time by utilizing an expansion state observer according to an attitude state quantity, a load state parameter and a current motor control instruction, a self-adaptive sliding mode controller fuses the equivalent disturbance torque vector and a feedback control quantity obtained through sliding mode control based on the current attitude error, a total compensation torque instruction needed by the fire-fighting unmanned aerial vehicle to recover stability is generated, and the total compensation torque instruction is decomposed into a target displacement instruction and a differential speed adjusting instruction; and the execution module is configured to execute the target displacement instruction by using the movable counterweight mechanism to drive the counterweight block to move, and execute the differential speed adjustment instruction through the power fine adjustment mechanism to adjust the rotating speed of the motor. The problem of attitude instability after bomb dropping of the fire-fighting unmanned aerial vehicle is effectively solved.

An aerial vehicle system includes one or more actuators; a processor; and a non-transitory, computer-readable storage medium communicatively coupled to the processor. The processor is configured to: receive one or more predetermined state values, wherein the one or more predetermined state values include one or more user values associated with aerial instability including turbulence, motion sickness, or any combination thereof; receive one or more sensing parameters; compare the one or more predetermined state values with the one or more sensing parameters; generate, based on the comparison, one or more signals to stabilize an aerial vehicle; transmit the one or more signals to the one or more actuators; and control, in response to the one or more signals, stabilization of the aerial vehicle by the one or more actuators.

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 discloses an inspection unmanned aerial vehicle with a good damping effect, and relates to the technical field of damping of unmanned aerial vehicles. The unmanned aerial vehicle comprises an unmanned aerial vehicle body, two supporting frames are fixedly connected to the two sides of the unmanned aerial vehicle body correspondingly, connecting plates are fixedly connected to the bottom ends of the supporting frames correspondingly, supporting plates are arranged below the two supporting frames correspondingly, and buffering assemblies are arranged between the connecting plates and the supporting plates and used for damping the unmanned aerial vehicle body; when impact force vertically acts on the top end of the connecting plate, the first damping spring rapidly absorbs the impact force by means of the elastic deformation characteristic of the first damping spring, high-frequency vibration generated by impact of the unmanned aerial vehicle body is effectively reduced, meanwhile, the residual impact force is stably transmitted to the first mounting base, and the second damping spring is promoted to be compressed; the impact energy is secondarily absorbed through elastic deformation of the two-stage spring, the double damping effect is achieved through the linkage damping mechanism of the two-stage spring, the protection performance of the unmanned aerial vehicle is further enhanced, and the overall damping efficiency is remarkably improved.

A payload system for carrying a payload including a platform configured to support the payload, and a payload distribution sensor configured to sense the distribution of the payload on the platform. At least two autonomous aerial vehicles are provided, with coupling arrangements being configured to couple each vehicle to the platform. One or more processing devices configured to determine a payload distribution in accordance with signals from the payload distribution sensor and control operation of the vehicles in accordance with the determined payload distribution to thereby allow the platform and payload to be lifted.

The invention relates to the technical field of cameras, in particular to a camera angle adjusting mechanism which comprises a camera, a connecting frame, a balancing weight, an adjusting assembly and an agricultural unmanned aerial vehicle, the connecting frame is fixedly installed at the bottom of the agricultural unmanned aerial vehicle, the adjusting assembly is installed on the connecting frame, and the balancing weight is slidably installed on the adjusting assembly. The camera is rotationally installed at the bottom of the adjusting assembly. The shooting angle of the camera is changed through kinetic energy brought by inclined flight of the agricultural unmanned aerial vehicle, gravity inertia of the balancing weight and movement of the balancing weight, the rotation angle is changed along with the flight direction of the agricultural unmanned aerial vehicle, and angle adjustment by manually operating the camera is not needed; it is ensured that the camera monitors and calculates the operation area in the flight process of the agricultural unmanned aerial vehicle, the view blind area of the camera is reduced, the flight path of the unmanned aerial vehicle is planned, and the efficiency of pesticide spraying work is improved.

The invention relates to the technical field of police unmanned aerial vehicles, in particular to a police unmanned aerial vehicle loaded with a long-distance explosive destructor, which comprises an unmanned aerial vehicle, a destruction assembly is mounted on the unmanned aerial vehicle, the destruction assembly comprises a water tank, a floating plate is mounted in the water tank, and a push block is mounted at the lower end of the floating plate. According to the unmanned aerial vehicle, the horizontal plane in the water tank descends through the balance assembly, the floating plate descends along with the horizontal plane, the floating plate descends to drive the pushing block to descend, the pushing block descends to extrude the balancing weight to move, the moving direction of the balancing weight is opposite to the launching direction of the water cannon, and the balancing weight moves to one side of the unmanned aerial vehicle; the gravity of one side of the unmanned aerial vehicle is increased, then the recoil force generated by the water cannon is counteracted, and the situation that the unmanned aerial vehicle deviates or displaces due to the generated recoil force at the jetting moment of the water cannon, consequently, the flight angle deviates, the explosive jetting position of the water cannon is affected, and then the working effect of destroying the explosive is affected is prevented.

A hover-capable flying machine such as a drone includes a robotic arm extending from the body, and an instrumentality for balancing the machine in response to disturbances such as those caused by picking up and dropping of the payload by the extended robotic arm. In embodiments, the end of the arm is equipped with a balancing rotor assembly that may provide lift sufficient to counteract the weight of the payload and / or of the arm. In embodiments, the machine's power pack is shifted in response to the disturbances. The power pack may be moved, for example, on a rail within and / or extending beyond the machine in a direction generally opposite to the extended arm. The power pack may also be built into a bandolier-like device that can be rolled-in and rolled out, thus changing the center of gravity of the machine.

The present invention relates to the field of unmanned aerial vehicles, and discloses a highly wind-resistant multi-rotor unmanned aerial vehicle, comprising a fuselage and an arm bracket arrayed on the side of the fuselage, wherein a motor 1 is arranged at the end of each arm bracket, and a propeller part is installed on the output shaft of the motor 1, so as to drive the propeller part to change the inclination angle through a servo, and when the unmanned aerial vehicle encounters a strong crosswind, the corresponding propeller and the rotation angle of the propeller part are changed to improve the resistance of the unmanned aerial vehicle to the crosswind, thereby improving the stability of the unmanned aerial vehicle when encountering a strong crosswind during flight, changing the thrust vector direction, and thus generating a compensation force opposite to the wind pressure direction. This dynamic adjustment mechanism enables the unmanned aerial vehicle to maintain a stable track under strong crosswind conditions, and effectively avoids the track deviation problem caused by the fixed thrust direction of traditional unmanned aerial vehicles.

The invention discloses an unmanned aerial vehicle remote sensing device for detecting glacier climate change, and relates to the technical field of unmanned aerial vehicle remote sensing. Comprising fluctuating units which are hung below an unmanned aerial vehicle body at equal angles and change in a self-adaptive fluctuating mode according to rising turbulence. The center supporting rods are arranged at the centers of the multiple sets of fluctuating units and fixedly connected with the lower surface of the unmanned aerial vehicle body, and the eccentric balance weight balls are distributed in the fluctuating units at equal angles and used for adjusting the centrifugal distance in a self-adaptive mode according to ascending airflow so as to adjust and control the gravity center of the unmanned aerial vehicle body. The left side fluctuating unit ascends preferentially and extrudes the eccentric counterweight ball in the horizontal direction through the inclined surface on one side of the cavity, so that the eccentric counterweight ball gradually and horizontally slides in a telecentric manner along the outer wall of the positioning rod and compresses the first spring; at the moment, the eccentric counterweight ball in the left fluctuating unit is gradually telecentric to preliminarily balance the condition that the gravity center of the unmanned aerial vehicle body deviates rightwards.

To provide an unmanned flying body that can move the center of gravity of the airframe so as to take a posture suited to such as parachute injection in emergency circumstances.SOLUTION: An unmanned flying body includes: a body part; a lock mechanism for maintaining a state where a center-of-gravity control body is in a first position relative to the body part; and a movable guide for moving the center-of-gravity control body to a second position in accordance with release of a maintenance state by the lock mechanism.SELECTED DRAWING: Figure 3

The invention relates to a transport unit (1) for a vertical take-off and landing aircraft (100) for transporting people and / or loads. The transport unit (1) comprises a transport facility (2), at least one fastening element (3), configured for fastening the transport unit (1) to a flight unit (10) of the aircraft (100), and a positioning device (4). The positioning device (4) is configured for changing and fixing an inclined position of the transport facility (2) with respect to the at least one fastening element (3). In addition, a vertical take-off and landing aircraft for transporting people and / or loads, having a flight unit (10) and a transport unit (1) fastened to the flight unit (10), and a control unit (16) for controlling such an aircraft (100) are specified.

The invention relates to an active gravity center adjustment control method for an advanced aircraft variant process, and the method comprises the steps: collecting the variant state information of an aircraft in real time, synchronously obtaining the flight state information, and obtaining an input vector; wherein the variant state information comprises a wing sweep angle, a span-chord ratio and a flap deflection angle, and the flight state information comprises an attack angle, a flight speed, a height, a pitch angle and an acceleration; according to the input vector, an initial pneumatic center position is calculated through a pneumatic center prediction function, and the pneumatic center position is determined according to the pneumatic center position variable quantity; calculating a target gravity center position according to the longitudinal static stability through the average pneumatic chord length of the aircraft and the pneumatic center position, and obtaining a target gravity center position adjustment amount; and adjusting the center of gravity of the aircraft to the target center-of-gravity position through a center-of-gravity adjustment executing mechanism. Active gravity center adjustment can be provided for the advanced aircraft variant process, attitude disturbance is restrained through information collection, pneumatic center calculation and the like, and flight safety is guaranteed.

The invention relates to an unmanned aerial vehicle for barren mountain greening, and belongs to the technical field of afforestation. Comprising a shell, a flying mechanism is arranged in the shell, the flying mechanism comprises a gravity center adjusting assembly, the gravity center adjusting assembly comprises four first sliding plates, second sliding plates are slidably arranged at the upper ends of the first sliding plates in the longitudinal direction, and third sliding plates are slidably arranged at the upper ends of the second sliding plates in the transverse direction; a functional frame is fixedly arranged at the lower end of the flight mechanism, a power supply assembly is arranged in the functional frame, and the power supply assembly comprises an oil tank, an internal combustion engine and a generator; a seedling throwing frame is arranged below the functional frame, and the seedling throwing frame is connected with the flying mechanism through four groups of hook rope assemblies; a seedling throwing mechanism is arranged in the seedling throwing frame, the seedling throwing mechanism comprises a spiral frame in a planar spiral shape, and a transmission belt is arranged in the spiral frame; the problem that an existing unmanned aerial vehicle is poor in seedling throwing effect is solved.

A system and method are disclosed and may be used for controlling (e.g., stabilizing) a suspended load. The system may include a hoist, an imaging sensor configured to capture images of a swinging of a load suspended from the hoist, and a controller. The controller may include one or more processors configured to execute a set of program instructions stored in a memory. The program instructions may be configured to cause the one or more processors to receive the images, determine positions of the load over time based on the images, calculate swing data of the swinging of the load based on the positions, determine flight control commands based on the swing data, and direct a flight control system configured to adjust a flight of an aircraft based on the flight control commands.

There is provided an improved weight-shift control flexible wing aircraft and improved systems and methods for recovering or preventing a spiral dive or a stall of a weight-shift control flexible wing aircraft. The aircraft including a frame; a wing assembly defining a flexible sail extending from port to starboard sides of the vehicle, the flexible wing assembly comprising: a wing keel extending from fore to aft ends of the wing assembly; a pair of wings, wherein each side of said pair of wings has a strut coupled to and extending away from the wing keel and defines a leading edge and a trailing edge when the wing assembly is moved though air, wherein the trailing edge of each side of said pair of wings is configured for actuable reversible billowing in at least a portion along a length of the trialing edge.

A water counterweight system control method based on liquid level and flow comprises the steps that 1, the gravity center of a target aircraft is input, a target gravity center difference threshold value is set, and an adjusting program is started; 2, acquiring the flow of the transmitted liquid counterweight medium through a flow sensor, calculating the current gravity center position of the aircraft based on the flow, acquiring the liquid level of each water tank through a liquid level sensor, and calculating the current gravity center position of the aircraft based on the liquid level; 3, the center-of-gravity position of the aircraft obtained based on the flow and the center-of-gravity position of the aircraft obtained based on the liquid level are monitored in real time; and 4, under the condition that at least one of the difference value between the aircraft gravity center position obtained based on the flow and the target gravity center position and the difference value between the aircraft gravity center position obtained based on the liquid level and the target gravity center position is smaller than a target gravity center difference value threshold value, it is determined that the target gravity center is adjusted. By means of the dual-redundancy control method, the gravity center adjusting result can be reliably guaranteed.

The invention discloses an unmanned aerial vehicle surveying and mapping high-precision positioning device, and relates to the technical field of unmanned aerial vehicle surveying and mapping, the unmanned aerial vehicle surveying and mapping high-precision positioning device comprises an unmanned aerial vehicle body and a surveying and mapping probe, vertical plates and undercarriages are arranged on two sides of the bottom of the unmanned aerial vehicle body, the vertical plates are fixedly connected to the bottom of the unmanned aerial vehicle body, and the undercarriages are fixedly connected to the bottoms of the vertical plates; an adjusting assembly used for adjusting the landing stability of the unmanned aerial vehicle body is arranged on the undercarriage, the adjusting assembly comprises grounding plates, the grounding plates are arranged in the undercarriage and can vertically slide in the undercarriage, and three groups of grounding plates are uniformly distributed in the horizontal direction of the undercarriage on one side in an array manner; three groups of telescopic grounding plates are arranged at the bottom of the landing gear on the same side, so that the unmanned aerial vehicle body can stably land on uneven ground and soft sand in Gansu region, meanwhile, the condition that the unmanned aerial vehicle body is blown over by wind during landing can be further prevented by matching with a counterweight adjusting module, and the surveying and mapping precision is indirectly improved.

Rib plates are fixedly installed at the two ends of a cross beam, a second lead screw is installed between the lower ends of the two rib plates, a balance weight ball is connected to the second lead screw in a penetrating mode, and a displacement dial is fixedly installed at the front ends of the two rib plates together. The first lead screw is installed in the center of the cross beam, the upper end of the first lead screw is fixedly connected with a dial fixing block, a corner dial is arranged on the dial fixing block, and a rotating shaft is rotationally connected between the dial fixing block and the connecting block through a bearing. Adjustment of the gravity center of the unmanned aerial vehicle is achieved through horizontal movement of the balance weight ball and angle rotation of the rotating shaft, a pure mechanical gravity center changing structure reduces dependence of electronic elements, reduces long-term maintenance cost, simplifies the gravity center adjusting process, improves adjusting efficiency and accuracy, and is suitable for large-scale popularization and application. And powerful support is provided for flight control and stability of the unmanned aerial vehicle.

An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor. The payload rail allows mechanical connection of payloads to the fuselage and positioning of the payloads such that a center of gravity of the payloads is alignable with the axis of rotation. A system for controlling the unmanned helicopter includes a processor and a memory for providing instructions to the processor. The processor can receive a task, dynamically determine a route for the task and autonomously perform the task including flying along at least part of the route. The route is based on the task, geography and terrain.

A multiple hoist system is used with an unmanned aerial vehicle (UAV) for delivering parcels. An example of the multiple hoist system comprises two or more hoists that are independently operable, meaning that a first hoist can lower or raise a first line independently of using a second hoist to raise or lower a second line. The hoists can independently raise and lower their associated lines to allow the UAV to deliver multiple parcels to multiple delivery locations, or the hoists can synchronously raise and lower the associated lines together so that larger parcels can be delivered using the UAV. The hoists can be comprised within a body of the multiple hoist system. The body can further include a securing device for releasably securing the multiple hoist system to the UAV.

The present invention discloses a tilt-rotor platform, which relates to the technical field of rotorcraft and includes at least one rotor mounting mechanism; the tilt-rotor platform includes a tilt mechanism and a rotation mechanism; the tilt mechanism includes an input sleeve, an output sleeve, and a tilt driver; the upper end of the input sleeve and the lower end of the output sleeve are rotatably connected about a first axis; a traction portion is provided on the outer wall of the output sleeve, and the tilt driver can pull the traction portion to rotate the output sleeve about the first axis; the rotation mechanism includes a rotation driver, an input drive shaft, a universal joint assembly, and an output drive shaft; the output end of the rotation driver is fixedly connected to one end of the input drive shaft; one end of the input drive shaft is fixedly connected to one end of the universal joint assembly, and one end of the output drive shaft is fixedly connected to one end of the universal joint assembly. This enables the rotor to tilt, better simulates the tilt transition state of the tilt-rotor, and ensures that the test results are more in line with actual conditions.

The invention discloses a self-balancing express delivery unmanned aerial vehicle system and a discharging balancing method, and relates to the technical field of unmanned aerial vehicles. The four-rotor unmanned aerial vehicle comprises a four-rotor unmanned aerial vehicle body and a landing platform. An induction rod arranged on the bottom face of each rotor wing driving part of the four-rotor-wing unmanned aerial vehicle and an induction channel in a corresponding landing platform are utilized. The four-rotor unmanned aerial vehicle is in a suspended state by utilizing an electromagnet in a driving channel, and then the four-rotor unmanned aerial vehicle after unloading is leveled by utilizing a leveling mechanism; the problems that after an existing express delivery unmanned aerial vehicle is unloaded for a single time, the balance of the unmanned aerial vehicle is easily damaged, and normal take-off and flight are affected are solved.

The invention relates to a method (100) for correcting a thrust vector. The thrust vector is generated by a thrust unit associated with an electrical correction means for said thrust vector. Such a thrust unit comprises a mechanical rotor which is rotated by a rotating shaft of an internal combustion engine (12a-e) according to a power command (PC). Such a method (100) comprises a step (110) of generating this power command (PC) to reduce a deviation (RSE) between a rotational speed setpoint (RSI) and a measured rotational speed (RSM) of the shaft of the internal combustion engine (12a-e) and thus correct the speed of the shaft of said internal combustion engine (12a-e). The method further comprises a step (120) of generating an activation command (AC) of an electrical correction means for thrust vector (19a-e) which is generated on the basis of said deviation (RSE) independently of said speed correction of the shaft of the internal combustion engine (12a-e).

The utility model relates to the field of unmanned aerial vehicle protection, in particular to an anti-collision gyroscope external protection frame which comprises an unmanned aerial vehicle body, a gyroscope, a fixing block, a supporting rod, a protection assembly and the like. A cover plate is arranged on the unmanned aerial vehicle body; a gyroscope is mounted in the unmanned aerial vehicle body; a plurality of fixing blocks are mounted on the unmanned aerial vehicle body; a plurality of mounting frames are arranged on each fixing block; a protection assembly used for protecting the unmanned aerial vehicle body is installed on the unmanned aerial vehicle body. A plurality of unmanned aerial vehicles are stacked together and are uniformly placed in a special protective box body, so that a plurality of protective box bodies are not needed, the transportation and production cost is reduced, and meanwhile, the short rod end parts of the supporting rods protrude out of the side surface positions of the folded wings of the unmanned aerial vehicles, so that the unmanned aerial vehicles can be conveniently and quickly folded. Wing damage caused by scratching and collision between the wings and the inner wall of the protection box body is avoided, and therefore protection of the wings of the unmanned aerial vehicle is improved.

A system may include an object having a rotational axis. The system may also include a first mass movably mounted to the object and configured to adjust a moment of inertia of the object by translating relative to the object along an inertial path having a first component that is perpendicular to the rotational axis. The system may additionally include a second mass movably mounted to the object and configured to: apply to the object a first torque in a first direction along the rotational axis while the moment of inertia is adjusted above a threshold value and apply to the object a second torque in a second direction along the rotational axis while the moment of inertia is adjusted below the threshold value, by translating relative to the object along a torque path having a second component that is perpendicular to the rotational axis and the first component.