The utility model provides an ellipsoidal aircraft, wherein the housing is provided with an upper cover and a pedestal, the pedestal is coaxial with the housing, a whirling arm is arranged at a junction between the upper cover and the housing, and a fixing sleeve internally equipped with a motor is arranged at a middle position of a lower side of the whirling arm. Such design effectively prevents blades and the motor from being damaged due to loosening of the whirling arm during transmission and solves the problem that conventional equipment is easily damaged.

A fixed-wing aircraft includes at least one passive landing assistance unit configured to be deployed in a first position used in normal flight and a second position used for emergencies. A trigger to activate the transition from the first position to the second position. The aircraft also includes landing gear made of memory foam.

A system for deploying an airbag when an unmanned aerial vehicle (UAV) has failed or is no longer able to sustain flight, comprising a triggering means which releases compressed air into a bag or bags which are configured to expand around the UAV for the purpose of reducing the deceleration forces of the UAV on impact. UAV's are provided that are configured with a system that includes a triggering mechanism that deploys one or more bags when there is a failure or when flight is no longer sustainable.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

Embodiments of the present invention provide an aircraft for vertical take-off and landing. In various embodiments, an aircraft assembly includes at least one first wing portion providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion and at least one thruster positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents positioned inside at least one of the wing openings. The air vents can further include louvres positioned over or under the air vents to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

An aircraft for vertical take-off and landing includes an aircraft assembly which includes at least one first wing portion providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion and at least one propeller-based thruster positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents positioned inside at least one of the wing openings. The air vents can further include louvres positioned over or under the air vents to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

Disclosed is a drone capable of operating in an aqueous environment. The drone may include a buoyant structure configured to provide buoyancy. Further, the drone may include one or more propulsion units configured to propel the drone. Furthermore, the drone may include an upper camera disposed on an upper side of the drone. Additionally, the drone may include a lower camera disposed on a lower side of the drone. Further, each of the upper camera and the lower camera may be configured to capture images. Furthermore, one or more legs configured to enable the drone to stand on a solid surface. Additionally, the drone may include one or more leg-actuators coupled to the one or more legs. Further, the one or more leg-actuators may be configured to change a state of the one or more legs to one of an extended state and a retracted state.

This disclosure describes an unmanned aerial vehicle (UAV) and system that may perform one or more techniques for protecting objects from damage resulting from an unintended or uncontrolled impact by a UAV. As described herein, various implementations utilize a damage avoidance system that detects a risk of damage to an object caused by an impact from a UAV that has lost control and takes steps to reduce or eliminate that risk. For example, the damage avoidance system may detect that the UAV has lost power and/or is falling at a rapid rate of descent such that, upon impact, there is a risk of damage to an object with which the UAV may collide. Upon detecting the risk of damage and prior to impact, the damage avoidance system activates a damage avoidance system having one or more protection elements that work in concert to reduce or prevent damage to the object upon impact by the UAV.

A fabric-based, soft-bodied aerial robot includes contact-reactive perching and embodied impact protection structures while remaining lightweight and streamlined. The aerial robot is operable to 1) pneumatically vary its body stiffness for collision resilience and 2) utilize a hybrid fabric-based, bistable (HFB) grasper to perform passive grasping. When compared to conventional rigid drone frames the soft-bodied aerial robot successfully demonstrates its ability to dissipate impact from head-on collisions and maintain flight stability without any structural damage. Furthermore, in dynamic perching scenarios the HFB grasper is capable to convert impact energy upon contact into firm grasp through rapid body shape conforming in less than 4 ms.