The invention relates to an aircraft with vertical takeoff and landing and its operation method. Aircraft with vertical takeoff and landing of aerodyne type according to the invention comprises a circular symmetrical aerodynamic body (1) having an internal stiffening platform (2) located on the chord of the aerodynamic profile and which supports the components of the aircraft, at least four vertical ducted propellers (3a), (3b), (3c), (3d) arranged symmetrically to the central vertical axis of the carrier body (1), but also to the predetermined flight axis and to the transverse axis of the carrier body (1), propellers (3a) and (3c) having the same rotational direction opposite to that of propellers (3b) and (3d) at least two horizontal ducted propellers (4) with opposite rotation directions located inside the carrier body or outside of it, placed parallel symmetrical with the predetermined flight axis and on both sides of it, vector nozzles (5), one for each horizontal propeller (4), which provides vector orientation to jets of the horizontal ducted propellers (4), the means of power supply (6), which are designed to provide electricity necessary to operate all engines and all electrical and electronic devices on board, an electronic control and management flight module (7) and a landing gear (9), which aims to promote contact between the aircraft and the ground.

A device for launching an object is described. The device comprises a frame affixed to the launch pad, a push element for pushing an object detached from the launch pad, and a flexible force storing element for turning the push element in relation to the frame. The device has a casing fixed to the frame at a fixing point for holding the object in place against the push element. The device has a lock element for locking the casing in standby position. The frame and the push element are superposed and connected to each other at one edge of the device. The frame and the push element are substantially parallel. Force stored in the force storing element is releasable for displacing the push element at a moment of launch. The force storing element may be at least one spring or elastic band or an extension spring.

According to at least one example a launch system is provided, including a carrier vehicle and at least one payload vehicle. The payload vehicle includes a payload propulsion system and aerodynamic lift surfaces designed for providing the payload vehicle with aerodynamic powered flight at a design subsonic cruise speed at a desired altitude. The carrier vehicle is configured for carrying the at least one payload vehicle at least up to the desired altitude, and further includes a solid rocket propulsion system for propelling the launch system to the desired altitude. The carrier vehicle is configured for providing a predetermined forward speed at the desired altitude, correlated to the design subsonic cruise speed. The carrier vehicle is configured for releasing the payload vehicle with respect to the carrier vehicle at the desired altitude and the predetermined forward speed. The design subsonic cruise speed is less than 0.7 Mach number, and, the desired altitude is greater than 3 km.

The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

Safety systems for unmanned vehicles are disclosed. An example vehicle includes a housing and a propulsion system supported by the housing. The propulsion system to generate lift. An anti-crash module is coupled to the housing. The anti-crash module has a compressible foam that is to deploy to protect the propulsion system from an impact.

A life protection device system is proposed. More particularly, the life protection device system includes: a shock absorbing device provided with a shock absorbing part, a shock absorber, and an airbag that are mounted on a moving object so as to absorb impact to protect the life of passengers in a crash or collision of the moving object; a measuring device detecting the shock applied to the moving object; a controller generating a preset driving control signal according to the detected shock of the measuring device; and an artificial intelligence part notifying of an occurrence of a disaster and asking for help from a designated disaster center in response to the driving control signal of the controller, wherein the impact on the passengers is minimized even when the moving object such as a drone, autonomous aircraft, and autonomous vehicle crashes or collides, or falls into a river or sea.

Methods, systems and devices for connecting computer aided dispatch (CAD) systems for providing improved emergency response services are described. An example method includes connecting to a first CAD system and a second CAD system, wherein the information exchange interfaces associated with the first and second CAD systems are incompatible, and performing, using a common user interface overlay, the following operations: receiving an indication of an emergency situation, transmitting a list of available assets to the first CAD system, wherein the list of available assets comprises at least a set of available assets that are controlled by the second CAD system, receiving, from the first CAD system, a set of active assets designated to respond to the emergency situation, wherein the set of active assets is selected from the list of available assets, and transmitting, to the second CAD system, the set of active assets.

An asymmetric aircraft and an aircraft that can operate from small ships and be stored in high density with three aircraft or more in one helicopter hangar without needing a landing gear or wing fold. These aircraft slide into and out of the hangar on dollies like circuit boards in a computer and are launched and recovered using a large towed parafoil.

Provided is a landing apparatus which guides an unmanned aircraft to avoid obstacles and lands the unmanned aircraft at a low-risk spot. The landing apparatus has a dangerous object position detecting device, a movement target spot calculating device, and a parachute control device. The dangerous object position detecting device detects the position of a dangerous object that is present in the vicinity of the unmanned aircraft attempting to land using a parachute. Based on the position of the dangerous object, the movement target spot calculating device calculates a movement target spot to which the unmanned aircraft should move at each instance in order to avoid colliding with the dangerous object and landing on a dangerous site. The parachute control device controls the parachute so that the unmanned aircraft moves to the movement target spot calculated by the movement target spot calculating device.

An apparatus an unmanned aerial vehicle recovery system is provided. The apparatus includes a base to mount to an unmanned aerial vehicle. The apparatus further includes a housing to engage the base. In addition, the apparatus includes a parachute disposed within the housing. Also, the apparatus includes a deployment mechanism to deploy the parachute. The deployment mechanism is to eject the housing away from the base upon a triggering event.