FR2763310A1 - VTOL aircraft - Google Patents

Abstract

An aircraft with vertical take off and landing capacity has two contrarotating propellers (12, 13) which allow it to take off and land like a helicopter and are driven by separate engines with axes lying symmetrically with that of the aircraft. It has two cabins - a forward control cabin for its aircrew and a central passenger cabin (3) which is able to pivot within a sphere or cylinder so that its floor remains horizontal regardless of the angle of inclination of the fuselage. The aircraft has two wings (8, 9) which are movable about axes passing through their centre of thrust to maintain the aircraft in level flight, and rear fins which act as supports for feet (69, 70) on which the aircraft rests when standing vertically on the ground, and which are used to control the attitude of the aircraft about its roll, pitch and bank axes. The control surfaces are operated electrically with the aid of gyroscopes.

Description

-] - In patents 9611628 and 9701025 by the same authors. We have

patented a

vertical takeoff aircraft.

  The purpose of this new patent is to improve the structure as well as the new

  direction flaps of this aircraft taking off and vertical landing.

  According to a characteristic of the invention. the suspension feet in contact with the ground are supported by a beam each carrying a directional flap pivoting about an axis perpendicular to the axis of the aeronet, located in the vertical extension of the

beam, the aircraft being vertical.

  According to another characteristic of the invention, the aircraft comprises four feet of suspension in contact with the ground and therefore four beams and four directional flaps in the shape of a cross, the two flaps controlling the yaw axis being vertical when the aircraft

  flies horizontally, the other two flaps being perpendicular to the first two.

  According to another characteristic of the invention, the aircraft comprises three feet of suspension in contact with the ground and therefore three beams and three steering flaps. the flap controlling the yaw axis being placed vertically when the aircraft is flying horizontally. According to another characteristic of the invention, the aft cabin. remaining horizontal whatever the angle of inclination of the aircraft pivots within a volume which can be either a cylinder, a sphere or any volume According to another characteristic of the invention, the aft cabin has a staircase

  interior and exterior allowing pilots to access the front cabin.

  The invention and its advantages will be better understood thanks to the exemplary embodiments given by way of nonlimiting example for which: * FIG. 1 is a view in central section of the aircraft in vertical position comprising four feet,

  * Figure 2 is a perspective view of the aircraft with four feet of suspension.

  * Figure 3 is a perspective view of the aircraft with three feet of suspension.

  FIG. 1 represents the aircraft resting on the ground on its four feet in the starting position. We find the elements described above: - the motors (14) and (15) driving two counter-rotating propellers (12) and (13) equipped with their pitch variation (56) and (57), - a gyroscope (27) providing the indications of verticality of the aircraft either to the pilot or to the electrical flight control system making it possible to steer the aircraft - the two cabins (2) and (3), one (2) placed at the front at the level of the motors (14) and (1 5) housing the pilots, the other (3) placed in the center of the aircraft housing the passengers and pivoting inside either a sphere or a cylinder (83), either of any volume, as desired by the manufacturer, to produce the floor (50) of this cabin (3) which may be either rounded or rectangular, in the latter case, the front surface is slightly enlarged compared to a sphere but the floor area is larger. The aircraft rests on the ground by four suspension feet (69), (70). (71) and (72) based on the base (55) and on another base (551) in the form of a cross by means of reinforcements (67) and (68). Each leg has a flap (77). (78), (79) and (80) which will make it possible to control the three axes: - the pitch axis by acting on the flaps (77) and (78) walking together, the yaw axis by acting on the flaps (79) and (80) walking together, - the roll axis by acting on the flaps (77), (78), (79) and (80) either on one side or

  the other according to the desired direction of rotation.

  The flaps (77), (78), (79) and (80) controlled by jacks (74) and (75) placed in the

  tail (76) of the aircraft pivot about their axis (81) and (82).

  Note the interior and exterior stairs (97) starting from the floor (50) of the cabin (3) and rising to the limit of the volume of rotation of this cabin (3), and its extension by another space (98) at the edge of the cabin (2). which allows pilots, for large capacity aircraft, to access their cabin (2) from the inside

  of the aircraft, although the latter (2) is vertical.

  The operation of the aircraft is as follows: The pilot starts the motors (14) and (15) by canceling the pitch of the propellers (12) and (13). It accelerates the motors (14) and (15) to the rotational speed provided for takeoff and controls the increase in the pitch of the propellers (12) and (13) until takeoff. The gyroscope (27) provides the pilot with assistance in retaining the verticality of the aircraft. To land the pilot may either reduce the pitch of the propellers (12) and (13) or the speed

  motors (14) and (15) after placing the vertical convertible.

  Figure 2 is a perspective view of the aircraft with its four suspension feet.

  We find the main elements: - each engine (14) and (15), fixed between the wings (8) and (9), driving the propellers (12) and (13), - the cabin (2) of the pilots can be combined with the passenger cabin (3) for small convertibles,

  - the steering cross forming supports for the landing feet (69), (70), (71) and (72).

  Each leg corresponds to a flap (77), (78), (79) and (80) pivoting about its axis (81) and (82) and controlled by jacks (74) and (75), these flaps (77 ). (78), (79) and (80) used to steer the convertible while controlling the three pivot axes of the aircraft and being controlled either by the pilot or by an electrical flight control system. Note the reinforcement (99) which supports the suspension foot (70) which has not been

  drawn on the other feet for better visibility.

  In this figure 2, we have shown that two wings (8) and (9) each carrying a motor (14) and (15). We could also have four wings with the motors between the wings without departing from the scope of the invention. Figure 3 is a perspective view of the aircraft having three feet of suspension. The aircraft has only three suspension feet (69), (70). (71) and three steering flaps (77), (78), (79) making it possible to control the three steering axes: - the pitch axis by acting on the flaps (77) and (79), - I ' yaw axis by acting on the flap (78), - the roll axis by acting on the flaps (77), (78) and (79) either on one side. either of the other

  according to the desired direction of rotation.

  Note that the suspension foot (70) and its steering flap (78) must be

  vertical when the aircraft is horizontal.

  Of course the propellers (12) and (13) of the aircraft can be either counter-rotating if the motor shafts are centered on the same axis (case of FIG. 1) or simple and separate

  driven by two symmetrical motors (case of Figure 2).

  Note that we can install a room with toilets at the level of the pilot cabin (2) which will only be accessible when the aircraft is in position

  substantially horizontal for large capacity aircraft.

  It is also noted that the suspension feet (69), (70), (71) and (72) may include a seat which deploys for landing by increasing the contact surface of the aircraft with the ground, thanks to cylinders without departing from the scope of

the invention.

  Of course the aircraft may not have a pilot but an automatic system that

  which would allow the realization of a drone without departing from the scope of the invention.

-4-

Claims (4)

  1 - Takeoff and vertical landing aircraft having a passenger cabin (3) remaining horizontal regardless of the angle of inclination of the aircraft. characterized in that the suspension feet (69), (70), (71) and (72) in contact with the ground are each supported by a beam carrying a steering flap (77), (78 !. (79) and (80) pivoting about an axis perpendicular to the axis of the aircraft and located in the extension   vertical of the beam, the aircraft being vertical.   2 - aircraft taking off and vertical landing as in the first claim characterized in that the aircraft comprises four suspension feet (69), (70), (71) and (72) in contact with the ground and therefore four beams and four steering flaps (77), (78), (79) and (80) in the shape of a cross, the two flaps (79) and (80) controlling the yaw axis being vertical when the aircraft is flying horizontally, the two other flaps (77) and (78) controlling the pitch axis being perpendicular to the flaps (79) and (80) controlling the yaw axis.   3 - Takeoff and vertical landing aircraft according to the first claim characterized in that the aircraft comprises three suspension feet (69), (70) and (71) in contact with the ground and therefore three beams and three steering flaps (77). (78) and (79), the flap (78) controlling the yaw axis being placed vertically when the aircraft flies horizontally. 4 - Aircraft taking off and vertical landing conforms to the first claim characterized in that the flaps (77), (78), (79) and (80) are controlled either by the pilot or by an electrical flight control system thanks to cylinders (74) and (75)   positioned in the tail (76) of the aircraft and pivoting about their axis (81) and (82).   - Take-off and vertical landing aircraft gives the first two   claims characterized in that the passenger cabin (3) pivots inside a   volume can be either a sphere or a cylinder (83). either any volume.   6 - Takeoff and vertical landing aircraft conforming to the first two   claims characterized in that the passenger cabin (3) for the   large capacity comprises an internal and external staircase (97) starting from the floor (50) of this cabin (3) and rising up to the limit of the volume of rotation of this cabin (3) and extending by another space ( 98) at the edge of the cabin (2) for   allow pilots to access their cabin from inside the aircraft (2) -