A lifting system includes an unmanned aerial vehicle, a thruster device, a first wire, a first reel, a second thruster device, a second wire, a second reel, and a controller. When the unmanned aerial vehicle is in a position separated from the ground, the controller detaches the first thruster device and the second thruster device from the unmanned aerial vehicle, causes the first reel to reel out the first wire, detaches the second thruster device from the first thruster device, and causes the second reel to reel out the second wire.

An information processing apparatus includes a control unit that controls a first flying vehicle and a second flying vehicle. The first flying vehicle captures an image of a surface of a road. The second flying vehicle emits light onto the surface, such that a spot where a level difference is estimated, in advance, to occur on the surface, an image capturing direction in which the first flying vehicle captures an image of the spot, and a light emitting direction in which the second flying vehicle emits the light onto the spot have a relationship that causes, when the level difference exists, a shadow to occur at the spot and the shadow to be captured.

An information processing apparatus includes a control unit that controls a first flying vehicle and a second flying vehicle. The first flying vehicle captures an image of a surface of a road. The second flying vehicle emits light onto the surface, such that a spot where a level difference is estimated, in advance, to occur on the surface, an image capturing direction in which the first flying vehicle captures an image of the spot, and a light emitting direction in which the second flying vehicle emits the light onto the spot have a relationship that causes, when the level difference exists, a shadow to occur at the spot and the shadow to be captured.

Herein provided are methods and systems for a method for controlling autothrottle of an engine. A digital power request is obtained from an autothrottle controller, the digital power request based on an autothrottle input to the autothrottle controller. A manual input mode for the engine is terminated, the manual input mode based on a second power request obtained from a manual input associated with the engine. An autothrottle mode for the engine is engaged to control the engine based on the digital power request.

Herein provided are methods and systems for a method for controlling autothrottle of an engine. A digital power request is obtained from an autothrottle controller, the digital power request based on an autothrottle input to the autothrottle controller. A manual input mode for the engine is terminated, the manual input mode based on a second power request obtained from a manual input associated with the engine. An autothrottle mode for the engine is engaged to control the engine based on the digital power request.

A micro detecting device includes a flying main body, at least one fluid actuation system, an image capture system and a controller. The fluid actuation system is disposed within the flying main body and includes a driving module, a flow guiding channel, a convergence chamber, plural valves and a fluid discharging zone. The driving module is consisting of plural flow guiding units for transporting fluid. The flow guiding channel includes plural diverge channels which are in fluid communication with plural connection channels. The convergence chamber is in fluid communication between the corresponding diverge channels. The valves are respectively disposed in the corresponding connection channels and controlled in open/closed state for the corresponding connection channels. The fluid discharging zone is in communication with the connection channels. The image capture system is used to capture external image. The controller is connected to the valves to control the valves in the open/closed state.

A micro detecting device includes a flying main body, at least one fluid actuation system, an image capture system and a controller. The fluid actuation system is disposed within the flying main body and includes a driving module, a flow guiding channel, a convergence chamber, plural valves and a fluid discharging zone. The driving module is consisting of plural flow guiding units for transporting fluid. The flow guiding channel includes plural diverge channels which are in fluid communication with plural connection channels. The convergence chamber is in fluid communication between the corresponding diverge channels. The valves are respectively disposed in the corresponding connection channels and controlled in open/closed state for the corresponding connection channels. The fluid discharging zone is in communication with the connection channels. The image capture system is used to capture external image. The controller is connected to the valves to control the valves in the open/closed state.

In an embodiment, an aircraft includes a pilot input device, a position sensor coupled to the pilot input device, a flight condition sensor and a flight control computer (FCC). The FCC includes a first microprocessor and a second microprocessor. The first microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a first output. The second microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a second output. The FCC is configured to compare the first output and the second output to yield resultant data. Responsive to a determination that the first output and the second output do not match, the FCC is configured to execute first remediation logic if the resultant data satisfies first error criteria and to execute second remediation logic if the resultant data satisfies second error criteria.

In an embodiment, an aircraft includes a pilot input device, a position sensor coupled to the pilot input device, a flight condition sensor and a flight control computer (FCC). The FCC includes a first microprocessor and a second microprocessor. The first microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a first output. The second microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a second output. The FCC is configured to compare the first output and the second output to yield resultant data. Responsive to a determination that the first output and the second output do not match, the FCC is configured to execute first remediation logic if the resultant data satisfies first error criteria and to execute second remediation logic if the resultant data satisfies second error criteria.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.