A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A product may be stored in a protective container that is surrounded with a fluid. A heat-sensitivity rating for the product may be obtained, and a product energy for the product may be calculated. The calculating may include adjusting the longest dimension of the product based on the heat-sensitivity rating and defining a sphere of enthalpy around the product. The sphere's radius may be equal to the adjusted product dimension and the sphere may be centered at the product center. The calculating may also comprise multiplying the volume of the sphere by the air pressure inside the protective container. An environmental condition within the sphere during a first time period may be forecasted. It may be determined that the product is likely to deteriorate during the first time period based on the product energy and heat-sensitivity rating. The altitude of the protective container may be altered to mitigate this deterioration.

A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

A remotely controlled multirotor aircraft having a frame that includes a first and a second peripheral portions, to which at least one first and one second motor can be respectively coupled, and a central portion including a first end and a second end, to which the first peripheral portion and the second peripheral portion are respectively coupled, so that the first peripheral portion develops in a plane that is different from that in which the second peripheral portion develops; furthermore, the central portion also includes a coupling mechanism allowing the coupling between the central portion and a mobile device having video acquisition ability.

A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

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 propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.

Systems and methods for calculating launch sites for a satellite constellation are provided. A carrier aircraft may be configured to launch a first satellite into the first orbit and a second satellite into the second orbit. In some embodiments, information about an accessible range of the aircraft may be received. Based on the received information, a geographical area that the aircraft can access without landing may be calculated. Using received information and the orbit parameters of the first orbit and the second orbit, a first launch site for launching the first satellite and a second launch site for launching the second satellite may be calculated. The first launch site may comprise a first geographical position and a first launch time, and the second launch site may comprise a second geographical position and a second launch time. Both launch sites may be within the calculated geographical area.

A rectification structure body 100 of a flying vehicle is provided with a rectification section 30, a heat input control section 20 and a vacuum thermal insulation section 10. The rectification section 30 has a rectification surface 30a and a back surface 30b. The rectification surface 30a rectifies airflow 5 from a travelling direction. The back surface 30b is arranged opposite to the rectification surface 30a. The heat input control section 20 is connected to the back surface 30b. The vacuum thermal insulation section 10 is connected to the heat input control section 20 and its surface is formed of rigid body. In addition, the heat input control section 20 is sandwiched between the back surface 30b and the vacuum thermal insulation section 10.