A rocket engine nozzle includes an aerospike having a plurality of adjustable airfoil vanes distributed around a central longitudinal axis of a rocket engine combustion chamber. The aerospike is integrated on an exit plane at an exit end of the combustion chamber. The adjustable airfoil vanes and an inner perimeter of the combustion chamber define a plurality of apertures which choke an exhaust exiting the combustion chamber and cause the exhaust to expand supersonically along the adjustable airfoil vanes, creating a supersonic jet. An actuator is configured to adjust a position of each of the adjustable airfoil vane relative to each other so as to direct the exhaust exiting the rocket engine combustion chamber as the exhaust expands supersonically over the airfoil vanes without causing a shockwave to be imparted on the supersonic jet that is created. Accordingly, performance of the rocket engine is improved over conventional systems.

A drone includes a frame and a fuselage. The fuselage is coupled to the frame extending away from the frame. The fuselage has a front panel and a bottom panel, and the front panel is positioned at an angle between the bottom surface of the frame and the bottom panel of the fuselage. A first wing is opposite a second wing and are coupled to the frame. The first and second wings extend outwardly from opposite sides of the frame. A first and second mounting member are coupled to the frame and extend outwardly from opposite sides of the frame. A plurality of power generator systems are included and each system is coupled to the first or second mounting member. Each power generator system comprises a power source coupled to a propeller.

A combustion engine (10) comprises a radial compressor (16) in flow communication via a flow passage (22) with a compressor-combustor array (20) radially outward of the radial compressor (16), both rotatable around a central axis (12). The compressor-combustor (20) comprises an array of rotor blades (26). The walls of the blades (26) define a plurality of chambers (28, 30). Each chamber (28, 30) has a flow inlet (32) to receive fluid from the radial compressor (16), and a flow outlet to exhaust fluid radially outwards from the compressor-combustor (20). The plurality of chambers (28, 30) comprises a first pilot combustion chamber (28a) and a second pilot combustion chamber (28b). The first pilot combustion chamber (28a) is provided with a first fuel injector (40a), and the second pilot combustion chamber (28b) is provided with a second fuel injector (40a). The first fuel injector (40a) is in flow communication with a first fuel reservoir (70a), and the second fuel injector (40b) is in flow communication with a second fuel reservoir (70b). The first fuel reservoir (70a) and the second fuel reservoir (70b) are each in fluid communication with a flow regulator (100), the flow regulator (100, 200, 300) operable to vary fuel flow delivery rate to the first reservoir (70a) and vary fuel flow delivery rate to the second reservoir (70b). The differential regulation of fuel flow between pilot combustion chambers results in different levels of thrust being generated downstream of the combustion chambers. In this way the engine is operable to produce vectored thrust.

The present disclosure provides systems, apparatuses, and methods relating to a fan apparatus including a lift fan mounted in a duct and a cover for the lift fan. In some examples, a fan apparatus has a louvered cover including louvers having different chord lengths and/or different projection distances relative to one another when the louvers are in an intermediate (transitional) position. In some examples, a fan apparatus includes a louver actuation assembly configured to move louvers of the fan apparatus rotationally and translationally between open and closed positions. In some examples, a fan apparatus includes a fluid-actuated sealing assembly configured to form a seal between a sealing member and a cover, such as a louvered cover.

A rocket engine nozzle includes an aerospike having a plurality of adjustable airfoil vanes distributed around a central longitudinal axis of a rocket engine combustion chamber. The aerospike is integrated on an exit plane at an exit end of the combustion chamber. The adjustable airfoil vanes and an inner perimeter of the combustion chamber define a plurality of apertures which choke an exhaust exiting the combustion chamber and cause the exhaust to expand supersonically along the adjustable airfoil vanes, creating a supersonic jet. An actuator is configured to adjust a position of each of the adjustable airfoil vane relative to each other so as to direct the exhaust exiting the rocket engine combustion chamber as the exhaust expands supersonically over the airfoil vanes without causing a shockwave to be imparted on the supersonic jet that is created. Accordingly, performance of the rocket engine is improved over conventional systems.

A multi-pulse rocket propulsion motor for use with vehicles, such as space vehicles like satellites, rockets, and the like. The propulsion motor is a modular system that is capable of providing a plurality of discrete, controllable propulsion pulses. The propulsion motor can be used for primary propulsion of the vehicle and/or as a maneuvering thruster of the vehicle. The propulsion motor includes a plurality of propellant housings each containing a combustible propellant grain, a discharge plenum defining a plenum volume in communication with the discharge of each propellant housing, and a nozzle downstream from and in fluid communication with the plenum volume.

A drone includes a frame and a fuselage. The fuselage is coupled to the frame extending away from the frame. The fuselage has a front panel and a bottom panel, and the front panel is positioned at an angle between the bottom surface of the frame and the bottom panel of the fuselage. A first wing is opposite a second wing and are coupled to the frame. The first and second wings extend outwardly from opposite sides of the frame. A first and second mounting member are coupled to the frame and extend outwardly from opposite sides of the frame. A plurality of power generator systems are included and each system is coupled to the first or second mounting member. Each power generator system comprises a power source coupled to a propeller.

A novel structural arrangement for the various components of an Ultra-Micro Gas Turbine Generator, based on a single part impeller element which comprises the compressor, the turbine and the electrical generator core in a single annular structure, produced as a single piece by an additive manufacturing process. The single annular structure has a hollow shell structure, with a supporting structure within in. The internal hollow space of the shell structure provides for a flow of cooling air from the outside through the internal space, for cooling the turbine region of the impeller. This air flow could be assisted by the use of internal blades, which can also serve as the supporting structure to increase the strength of the shell structure. The air flow can either be ejected at the center of the turbine, or can provide a high pressure supply for air bearings of the impeller element.

A mixer is mounted in an aircraft. A rear end part of a cylindrical portion of the mixer is divided by a guide vane into a plurality of divided tubular portions. In the plurality of divided tubular portions, a notch nozzle is formed on an outer wall of the cylindrical portion. A plurality of guide holes are formed to extend from the outer wall of the cylindrical portion to a rear end surface of the guide vane.

A fuselage for an aircraft. The fuselage has a control element with an integrated engine outlet. The control element is integrated at a rear end of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage. An outer wall of the control element surrounds the engine outlet wherein the engine outlet is directed towards an open rear side of the control element. The control element is connected to the fuselage such that the control element jointly the engine outlet is pivotable about a rotation axis with respect to the fuselage. The rotation axis runs transversely to a longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis.