Abstract: A VTOL UAV comprising a chassis, a propulsion system mounted on the chassis, electronics including a flight control system, and a 3D LIDAR sensor mounted on the chassis. The 3D LIDAR sensor has a laser beam 360° rotation axis (R) and an azimuthal scanning angle (?) in a range of 70° to 110°. The propulsion system comprises a plurality of propellers with motors configured for flight without wings, including static hovering flight, the VTOL UAV comprising a yaw axis (Z) about which it can rotate upon itself. The 3D LIDAR sensor is statically mounted on the chassis such that the LIDAR laser beam 360° rotation axis (R) is inclined at a LIDAR inclination angle (?) with respect to the yaw axis (Z) in a range of 35° to 50°.

Abstract: A VTOL UAV comprising a chassis, a propulsion system mounted on the chassis, electronics including a flight control system, and a 3D LIDAR sensor mounted on the chassis. The 3D LIDAR sensor has a laser beam 360° rotation axis (R) and an azimuthal scanning angle (?) in a range of 70° to 110°. The propulsion system comprises a plurality of propellers with motors configured for flight without wings, including static hovering flight, the VTOL UAV comprising a yaw axis (Z) about which it can rotate upon itself. The 3D LIDAR sensor is statically mounted on the chassis such that the LIDAR laser beam 360° rotation axis (R) is inclined at a LIDAR inclination angle (?) with respect to the yaw axis (Z) in a range of 35° to 50°.

Abstract: Vertical take off and landing unmanned aerial vehicle (UAV) comprising a multi-propeller propulsion system (“the system”), an outer protective cage surrounding the system, an autonomous power source, a sensing system, and a control system. The sensing system has an orientation sensor and a displacement sensor. The system has at least two propellers spaced apart in a non-coaxial manner. The control system controls the flight or hovering of the UAV. The control system reverses thrust on at least one propeller distal from a point of contact with an obstacle while controlling a motor of a proximal propeller from the contact point to generate lift, the thrust of the distal and proximal propellers being controlled to exert lift on the UAV to counteract gravitational force thereon and apply a moment of rotation about the point of contact to stabilize the position of the UAV or to counteract torque resulting from inertia.

Abstract: Unmanned aerial vehicle (UAV) including an inner frame, an inner flight propulsion system mounted on the inner frame, an outer frame, a gimbal system comprising at least two rotational couplings coupling the inner propulsion system to the outer frame, a control system, a power source, and an outer frame actuation system configured to actively orient the outer frame with respect to the inner frame.

Abstract: Unmanned aerial vehicle (UAV) including a flight propulsion system and a support system coupled to the flight propulsion system, the support system comprising a protective outer cage configured to surround the flight propulsion system, wherein the outer cage comprises a plurality of cage frame modules that are manufactured as separate components and assembled together to form at least a portion of the outer cage configured to surround the flight propulsion system.

Abstract: Vertical take off and landing unmanned aerial vehicle (UAV) comprising a multi-propeller propulsion system (“the system”), an outer protective cage surrounding the system, an autonomous power source, a sensing system, and a control system. The sensing system has an orientation sensor and a displacement sensor. The system has at least two propellers spaced apart in a non-coaxial manner. The control system controls the flight or hovering of the UAV. The control system reverses thrust on at least one propeller distal from a point of contact with an obstacle while controlling a motor of a proximal propeller from the contact point to generate lift, the thrust of the distal and proximal propellers being controlled to exert lift on the UAV to counteract gravitational force thereon and apply a moment of rotation about said point of contact to stabilize the position of the UAV or to counteract torque resulting from inertia.

Abstract: Unmanned aerial vehicle (UAV) including an inner frame, an inner flight propulsion system mounted on the inner frame, an outer frame, a gimbal system comprising at least two rotational couplings coupling the inner propulsion system to the outer frame, a control system, a power source, and an outer frame actuation system configured to actively orient the outer frame with respect to the inner frame.

Abstract: Unmanned aerial vehicle (UAV) including a flight propulsion system and a support system coupled to the flight propulsion system, the support system comprising a protective outer cage configured to surround the flight propulsion system, wherein the outer cage comprises a plurality of cage frame modules that are manufactured as separate components and assembled together to form at least a portion of the outer cage configured to surround the flight propulsion system.

Abstract: A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame.

Abstract: A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame.

Abstract: A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame.

Abstract: A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The control system being able to control the orientation of the inner frame. The gimbal system connecting the inner frame to the outer frame with at least two rotation axis allowing rotation freedom between the outer frame to rotate independently from the inner frame.

Abstract: A new method for the estimation of ego-motion (the direction and amplitude of the velocity) of a mobile device comprising optic-flow and inertial sensors (hereinafter the apparatus). The velocity is expressed in the apparatus's reference frame, which is moving with the apparatus. The method relies on short-term inertial navigation and the direction of the translational optic-flow in order to estimate ego-motion, defined as the velocity estimate (that describes the speed amplitude and the direction of motion). A key characteristic of the invention is the use of optic-flow without the need for any kind of feature tracking. Moreover, the algorithm uses the direction of the optic-flow and does not need the amplitude, thanks to the fact that the scale of the velocity is solved by the use of inertial navigation and changes in direction of the apparatus.