Flying vehicle
A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.
1 . A flying vehicle, comprising:
an aircraft body;
a rotary wing connected to the aircraft body by a rotary axis;
a main wing connected to the aircraft body,
wherein the main wing is fixed at a forward tilt relative to the aircraft body,
wherein, during landing, the rotary wing is configured to be driven with the rotary axis at an angle directed upward;
a spring connected between the main wing and the aircraft body, the spring configured to exert a force that tilts the main wing forward; and
a support member configured to hold the main wing against the force of the spring during cruising, and
the support member is releasable during landing to allow the spring to tilt the main wing forward.
2 . The flying vehicle according to claim 1 , wherein the angle of the rotary axis of the rotary wing is controlled so that the main wing tilts forward more during landing than during cruising.
3 . The flying vehicle according to claim 1 , wherein the rotary wing includes at least one rotary wing connected at an angle that generates propulsion and lift during cruising.
4 . The flying vehicle according to claim 1 , wherein the rotary wing includes at least one rotary wing connected such that the rotary axis is horizontal during cruising.
5 . The flying vehicle-according to claim 1 , wherein the main wing further comprises a moving surface configured to deploy above the main wing during landing.
6 . The flying vehicle according to claim 1 , further comprising a fan configured to generate an upward wake during landing.
7 . A landing method for a flying vehicle having a plurality of rotary wings and a main wing fixed at a forward tilt relative to an aircraft body, the method comprising:
driving the plurality of rotary wings during landing with rotary axes of the plurality of rotary wings directed upward; and
maintaining the main wing in a forward-tilted state relative to a horizontal of the aircraft body.
8 . The flying vehicle according to claim 1 , wherein the main wing is configured to be tilted to a stall angle of attack during an emergency to force a crash.
9 . The flying vehicle according to claim 1 , wherein a frame or arm supporting the rotary wing is bent or curved to avoid interference with the main wing when the rotary wing tilts.
10 . The flying vehicle according to claim 1 , wherein the main wing comprises a variable retractable mechanism or a variable forward blade mechanism configured to deform the main wing to reduce lift during landing.