Flying apparatus, aircraft, and method for controlling flight of flying apparatus
A flying apparatus, an aircraft, and a method for controlling flight of a flying apparatus are provided. The flying apparatus may include a frame, including a front section and a rear section; a front tiltrotor, disposed on the front section of the frame; and a rear tiltrotor, disposed on the rear section of the frame; wherein the front tiltrotor is configured to tilt at a front tilt angle to a gravity direction to control a flight of the flying apparatus, and the rear tiltrotor is configured to tilt at a rear tilt angle to the gravity direction to control the flight of the flying apparatus.
1 . A flying apparatus, comprising:
a tandem tiltrotor system, comprising a front tiltrotor and a rear tiltrotor; and
a structural frame, configured to support the tandem tiltrotor system and comprising a front rotor-fixing support, a rear rotor-fixing support, and a linear support configured to connect and fix the front rotor-fixing support and the rear rotor-fixing support;
wherein the front tiltrotor is disposed at a middle portion of the front rotor-fixing support; and the rear tiltrotor is disposed at a middle portion of the rear rotor-fixing support;
wherein the front tiltrotor and the rear tiltrotor are arranged in a tandem manner;
wherein the front tiltrotor is configured to tilt at a front tilt angle to a gravity direction to control a flight of the flying apparatus, and the rear tiltrotor is configured to tilt at a rear tilt angle to the gravity direction to control the flight of the flying apparatus; and
wherein, in response to a failure of one of the front tiltrotor or the rear tiltrotor, another one of the front tiltrotor or the rear tiltrotor is configured to maintain controllability of the flying apparatus.
2 . The flying apparatus of claim 1 , wherein the front tiltrotor includes a front tilting axis that is generally parallel to an upper surface of the front rotor-fixing support, or the rear tiltrotor includes a rear tilting axis that is generally parallel to an upper surface of the rear rotor-fixing support.
3 . The flying apparatus of claim 1 , wherein at least one of the front tiltrotor and the rear tiltrotor is configured to tilt generally perpendicular to a ground level to drive taking off or landing vertically, or tilt generally parallel to the ground level to drive the flying apparatus take off, fly forward or backward.
4 . The flying apparatus of claim 1 , further comprising a controller configured to ensure that the front tiltrotor and the rear tiltrotor have identical rotation speeds and opposite rotation directions, or control the front tiltrotor and the rear tiltrotor to tilt synchronically.
5 . The flying apparatus of claim 1 , comprising:
at least one main wing disposed between the front rotor-fixing support and the rear rotor-fixing support and configured to provide lift and be coupled to a fuselage.
6 . The flying apparatus of claim 5 , further comprising:
a plurality of assistant lift fans, laterally disposed at both sides of the at least one main wing and configured to assist a vertical flight and balance control of the flying apparatus.
7 . The flying apparatus of claim 1 , wherein a diameter of a front propeller of the front tiltrotor is less than a length of the front rotor-fixing support, or a diameter of a rear propeller of the rear tiltrotor is less than a length of the rear rotor-fixing support.
8 . The flying apparatus of claim 1 , further comprising:
a retractable propeller, disposed at the linear support and configured to assist a vertical flight and balance control of the flying apparatus and retract into the linear support during a horizontal flight of the flying apparatus.
9 . The flying apparatus of claim 1 , further comprising:
a wing platform complex, disposed beneath the structural frame and configured to accommodate a power system and a transmission mechanism, and connect the structural frame to a fuselage;
wherein the power system is configured to provide power for the front tiltrotor and the rear tiltrotor.
10 . The flying apparatus of claim 9 , wherein the power system is powered by any one or any combination of following power resources: fuel, electricity, solar power, wind power, and nuclear power.
11 . The flying apparatus of claim 9 , wherein the power system comprises:
an electric generator; and
a gas engine assembly, configured to drive the electric generator;
wherein the gas engine assembly comprises two gas engines disposed on two sides divided by a central line of the structural frame.
12 . The flying apparatus of claim 9 , wherein the transmission mechanism is configured to transmit power and control signals among the power system, an operation system, and the tandem tiltrotor system, to control a flight state of the flying apparatus,
wherein the power system and the transmission mechanism are disposed on opposite sides of the wing platform complex.
13 . The flying apparatus of claim 1 , wherein the front rotor-fixing support comprises a front stabilizer, configured to control flight directions during a vertical flight, or
the rear rotor-fixing support comprises a rear stabilizer, configured to control flight directions during a horizontal flight.
14 . An aircraft, comprising:
a flying apparatus configured to carry a fuselage;
wherein the flying apparatus comprises:
a tandem tiltrotor system, comprising a front tiltrotor and a rear tiltrotor; and
a structural frame, configured to support the tandem tiltrotor system and comprising a front rotor-fixing support, a rear rotor-fixing support, and a linear support configured to connect and fix the front rotor-fixing support and the rear rotor-fixing support;
wherein the front tiltrotor is disposed at a middle portion of the front rotor-fixing support; and the rear tiltrotor is disposed at a middle portion of the rear rotor-fixing support,
wherein the front tiltrotor and the rear tiltrotor are arranged in a tandem manner,
wherein the front tiltrotor is configured to tilt at a front tilt angle to a gravity direction to control a flight of the flying apparatus, and the rear tiltrotor is configured to tilt at a rear tilt angle to the gravity direction to control the flight of the flying apparatus,
wherein the front tiltrotor is configured to, in response to a failure of the rear tiltrotor, maintain controllability of the flying apparatus, to ensure a controlled flight or a safe landing, or the rear tiltrotor is configured to, in response to a failure of the front tiltrotor, maintain controllability of the flying apparatus, to ensure a controlled flight or a safe landing.
15 . The aircraft of claim 14 , further comprising:
at least one main wing, disposed between the front rotor-fixing support and the rear rotor-fixing support and configured to be coupled to the fuselage.
16 . The aircraft of claim 15 , further comprising:
a plurality of assistant lift fans, laterally disposed at both sides of the at least one main wing and configured to assist a vertical flight and balance control of the aircraft; or
a retractable propeller, disposed at the linear support and configured to assist a vertical flight and balance control of the aircraft and retract into the linear support during a horizontal flight of the aircraft.
17 . The aircraft of claim 14 , wherein
the flying apparatus is detachable from the fuselage.
18 . The aircraft of claim 14 , wherein the flying apparatus is controlled by an external control terminal; or
the flying apparatus is self-controlled.
19 . A method for controlling flight of an aircraft, comprising:
receiving, from a control terminal, an instruction reflecting a flight trajectory; and
controlling, in accordance with the instruction, a front tilt angle, a front rotation speed, and a front rotation direction of a front tiltrotor, and a rear tilt angle, a rear rotation speed, and a rear rotation direction of a rear tiltrotor, wherein the front tiltrotor is disposed at a middle portion of a front rotor-fixing support; and the rear tiltrotor is disposed at a middle portion of a rear rotor-fixing support, the front tiltrotor and the rear tiltrotor are arranged in a tandem manner, and the front tiltrotor is configured to tilt at the front tilt angle to a gravity direction to control a flight of the aircraft, and the rear tiltrotor is configured to tilt at the rear tilt angle to the gravity direction to control the flight of the aircraft, and
in response to a failure of one of the front tiltrotor or the rear tiltrotor, controlling a remaining operable tiltrotor to maintain controllability of the aircraft, to ensure a controlled flight or a safe landing.