Abstract: A jet engine has an inlet 11 configured to introduce air, and a combustor 12 having a fuel injection port 30a that injects a fuel, and configured to combust the fuel injected from the fuel injection port 30a by using the air. The combustor 12 has a separation section 14 defining the air passage FA through which the air flows, between a rear end 15 of the inlet and the fuel injection port 30a. A plurality of turbulent flow generating sections (20;25) are arranged in the separation section 14 to makes the air flow turbulent. Each of the plurality of turbulent flow generating sections (20;25) contains a member (21;22;25B) which can restrain the turbulence of the air flow by moving or disappearing. It can be prevented that a high-pressure region reaches the inlet so that the thrust of the jet engine is reduced.

Abstract: A jet engine has an inlet which takes in air, a combustor which combusts fuel by using the air, and a fuel control section which controls supply of the fuel. The combustor has a fuel supplying section which supplies the fuel, injectors which inject the fuel. Each injector contains openings which inject the fuel. The fuel supplying section supplies the fuel to the injector in a flow rate according to a command of an autopilot. The fuel control section controls the injectors such that the number of the openings which inject the fuel or flow-path cross-section areas of the pipes which send the fuel in case of the low-speed is more than the number of the openings which inject the fuel or the flow-path cross-section areas of the pipes which send the fuel in case of the high-speed.

Abstract: According to some embodiments, there is provided a welding device for welding outer peripheral edges of two irregular shaped plates which are overlapped, including: a rotary table to which the two irregular shaped plates in an overlapped state are fixed; a torch unit, including a welding torch positioned to face the outer peripheral edges of the two irregular shaped plates fixed to the rotary table; a first torch actuator, capable of changing an orientation and a distance of the welding torch relative to the outer peripheral edges; and a first controller, configured to control the first torch actuator, so that the orientation of the welding torch relative to a tangential line of the outer peripheral edges and the distance of the welding torch from the outer peripheral edges are kept constant along a circumferential direction of the outer peripheral edges, during rotation of the two irregular shaped plates.

Abstract: A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.

Abstract: A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor (12) includes an injector (20) having a plurality of openings (31a, 31b) from which the fuel is injected. The plurality of openings (31a, 31b) are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (12). The plurality of openings (31a, 31b) include two types of openings different in area.

Abstract: A welding device according to some embodiments includes a rotary table fixing two irregular shaped plates which are overlapped, a torch unit including a welding torch positioned to face outer peripheral edges of the two irregular shaped plates fixed to the rotary table, a torch actuator configured to move the welding torch toward and away from the outer peripheral edges, an after-shielding part mounted to the welding torch on downstream side in a rotational direction of the rotary table and having nozzles arranged along the rotational direction, configured to jet shielding gas to the outer peripheral edges, and including a first nozzle positioned upstream and a second nozzle positioned downstream of the first nozzle in the rotational direction, and a controller configured to control an orientation of the nozzle in a direction of decreasing a shielding-gas-jetting distance between the second nozzle and the outer peripheral edges welded by the welding torch.

Abstract: The jet engine includes an inlet and a combustor. The inlet (11) takes air. The combustor burns fuel with the air. The combustor includes an injector (20). The injector (20) has an opening (31) through which the fuel is injected. The injector (20) includes a self-extinguishing member (32). The self-extinguishing member (32) self-extinguishes with time in a flight so that the injection direction of the fuel is modified.

Abstract: A combustor of a jet engine includes a fuel injector, an igniter for igniting a gas mixture of air and fuel, and a flame holder. The igniter is disposed in the flame holder. After an activation of the igniter, the igniter disappears, and a space after the disappearance functions as a flame-holding space.

Abstract: A welding device according to some embodiments includes a rotary table fixing two irregular shaped plates which are overlapped, a torch unit including a welding torch positioned to face outer peripheral edges of the two irregular shaped plates fixed to the rotary table, a torch actuator configured to move the welding torch toward and away from the outer peripheral edges, an after-shielding part mounted to the welding torch on downstream side in a rotational direction of the rotary table and having nozzles arranged along the rotational direction, configured to jet shielding gas to the outer peripheral edges, and including a first nozzle positioned upstream and a second nozzle positioned downstream of the first nozzle in the rotational direction, and a controller configured to control an orientation of the nozzle in a direction of decreasing a shielding-gas-jetting distance between the second nozzle and the outer peripheral edges welded by the welding torch.

Abstract: According to some embodiments, there is provided a welding device for welding outer peripheral edges of two irregular shaped plates which are overlapped, including: a rotary table to which the two irregular shaped plates in an overlapped state are fixed; a torch unit, including a welding torch positioned to face the outer peripheral edges of the two irregular shaped plates fixed to the rotary table; a first torch actuator, capable of changing an orientation and a distance of the welding torch relative to the outer peripheral edges; and a first controller, configured to control the first torch actuator, so that the orientation of the welding torch relative to a tangential line of the outer peripheral edges and the distance of the welding torch from the outer peripheral edges are kept constant along a circumferential direction of the outer peripheral edges, during rotation of the two irregular shaped plates.

Abstract: A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.

Abstract: A jet engine has an inlet 11 configured to introduce air, and a combustor 12 having a fuel injection port 30a that injects a fuel, and configured to combust the fuel injected from the fuel injection port 30a by using the air. The combustor 12 has a separation section 14 defining the air passage FA through which the air flows, between a rear end 15 of the inlet and the fuel injection port 30a. A plurality of turbulent flow generating sections (20;25) are arranged in the separation section 14 to makes the air flow turbulent. Each of the plurality of turbulent flow generating sections (20;25) contains a member (21;22;25B) which can restrain the turbulence of the air flow by moving or disappearing. It can be prevented that a high-pressure region reaches the inlet so that the thrust of the jet engine is reduced.

Abstract: A jet engine has an inlet, and a combustor with a fuel injection opening. The combustor has wall sections that define an air flow path. The wall section has a ramp section with a ramped surface and a first wall surface extending from an end of the ramped surface on the front side. The fuel injection opening is arranged in the ramp section. A ramped angle ? of the ramped surface to the first wall surface is equal to or more than 13.5 degrees. The height of the ramp section protruding from the first wall surface is equal to or less than ? of the height of the entrance of combustor. In this way, the ramp angle of the ramped surface of the ramp section is made large to promote mixing of fuel and air, and flame stabilization behind the ramp section is made possible.

Abstract: An armored vehicle includes: a basic armored vehicle having a predetermined basic external armor; a modularized armor structure exchangeably attached to the basic external armor; and an unmanned aerial vehicle loaded on the modularized armor structure. The modularized armor structure includes: an unmanned aerial vehicle loading section configured to load the unmanned aerial vehicle; an armoring material structure formed of armoring material; and an attaching section used to exchangeably attach the modularized armor structure to the basic armored vehicle.

Abstract: The jet engine includes an inlet and a combustor. The inlet (11) takes air. The combustor burns fuel with the air. The combustor includes an injector (20). The injector (20) has an opening (31) through which the fuel is injected. The injector (20) includes a self-extinguishing member (32). The self-extinguishing member (32) self-extinguishes with time in a flight so that the injection direction of the fuel is modified.

Abstract: A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.

Abstract: A combustor of a jet engine includes a fuel injector, an igniter for igniting a gas mixture of air and fuel, and a flame holder. The igniter is disposed in the flame holder. After an activation of the igniter, the igniter disappears, and a space after the disappearance functions as a flame-holding space.

Abstract: A jet engine has an inlet which takes in air, a combustor which combusts fuel by using the air, and a fuel control section which controls supply of the fuel. The combustor has a fuel supplying section which supplies the fuel, injectors which inject the fuel. Each injector contains openings which inject the fuel. The fuel supplying section supplies the fuel to the injector in a flow rate according to a command of an autopilot. The fuel control section controls the injectors such that the number of the openings which inject the fuel or flow-path cross-section areas of the pipes which send the fuel in case of the low-speed is more than the number of the openings which inject the fuel or the flow-path cross-section areas of the pipes which send the fuel in case of the high-speed.

Abstract: A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor (12) includes an injector (20) having a plurality of openings (31a, 31b) from which the fuel is injected. The plurality of openings (31a, 31b) are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (12). The plurality of openings (31a, 31b) include two types of openings different in area.

Abstract: An aerial vehicle includes an outer surface, an arithmetic unit and a control unit. The arithmetic unit calculates a control command using a control parameter. The control unit controls an attitude of the aerial vehicle or a thrust of the aerial vehicle based on the control command. At least a part of the outer surface of the aerial vehicle is composed of ablation material. The arithmetic unit changes the control parameter in response to an amount of shape change of the aerial vehicle caused by disappearance of the ablation material.