CA2073525C - Propelling system for flying machine - Google Patents
Propelling system for flying machine Download PDFInfo
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- CA2073525C CA2073525C CA002073525A CA2073525A CA2073525C CA 2073525 C CA2073525 C CA 2073525C CA 002073525 A CA002073525 A CA 002073525A CA 2073525 A CA2073525 A CA 2073525A CA 2073525 C CA2073525 C CA 2073525C
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- 238000006073 displacement reaction Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/001—Flying saucers
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Abstract
A system for propelling a flying machine comprises a tube section rotatable onto a vertical shaft. A plurality of wings are each pivotally mounted on the tube section. Rotative wheels are mounted on the vertical tube section and on the wings.
The direction and axes of rotation of the wheels are selected to produce a recurrent cycle of precession that causes rotation of the tube section on the vertical shaft and pivoting of the wings on this tube section to thereby flap the wings and displace air in order to propel the flying machine.
The direction and axes of rotation of the wheels are selected to produce a recurrent cycle of precession that causes rotation of the tube section on the vertical shaft and pivoting of the wings on this tube section to thereby flap the wings and displace air in order to propel the flying machine.
Description
PROPELLING SYSTEM FOR FLYING MACHINE
BACKGROUND OF THE INVENTION
1. Field of the invention:
The present invention is concerned with a system for propelling a flying machine, of the flying saucer type. This propelling system uses the well known gyroscopic effect.
BACKGROUND OF THE INVENTION
1. Field of the invention:
The present invention is concerned with a system for propelling a flying machine, of the flying saucer type. This propelling system uses the well known gyroscopic effect.
2. Brief description of the prior art:
Humans have always been fascinated by the creatures capable, by means of sustaining of wings, and travelling through t he air. Over the years, they have imagined a multitude of concepts to allow them to fly. Examples of such concepts are described in the following United States patents:
- 210,238 (Cameron) 1878 - 361,855 (Beeson) 1887 - 727,377 (Kaehler) 1903 - 846,830 (Dufaux) 1907 - 881,836 (Warner) 1908 - 1,114,201 (Summers) 1914 - 1,450,072 (Goldschmidt) 1923 - 1,531,084 (Eckler) 1925 - 3,506,220 (Sbrilli) 1970 OBJECTS OF THE INVENTION
The main object of the present invention is a new concept for propelling a flying machine, this new concept using the well known gyroscopic effect.
SUMMARY OF THE INVENTION
More specifically, in accordance with the present invention, there is provided a system for propelling a flying machine, comprising:
a generally vertical pivot structure defining a generally vertical axis;
wing bearing means pivotally mounted on the generally vertical pivot structure about the generally vertical axis;
a plurality of wings each extending generally radially from the generally vertical axis, and each having a generally longitudinal wing axis intersecting the generally vertical axis;
for each wing, a hinge structure for pivotally mounting the wing on the bearing means about a generally horizontal hinge axis perpendicular to both the generally vertical axis and the generally longitudinal wing axis;
first and second rotative members mounted rotatable on the wing bearing means and a third rotative member mounted rotatable on each wing, the first rotative member being rotatable about (a) a first axis intersecting and perpendicular to the generally vertical axis and (b) a second axis intersecting and perpendicular to the first axis, the second rotative member being rotatable about (a) the first axis and (b) a third axis intersecting and perpendicular to the first axis, the second and third axes intersecting the first axis at diametrically opposed points with respect to the generally vertical axis, and each third rotative member being rotatable about a fourth axis intersecting the generally vertical axis; and driving motors connected to the rotative members for rotating in given directions the first rotative member about the first and second axes, the second rotative member about the first and third axes, and the third rotative member about the fourth axis to produce a recurrent cycle of precession that causes pivoting of the wing bearing means on the generally vertical pivot structure about the generally vertical axis and pivoting of the wings about the hinge structure to thereby flap the wings and displace air in order to propel said flying machine.
In accordance with preferred embodiments of the propelling system:
- the flying machine comprises a body including air deflecting means for directing air displaced by the flapping wings downwardly in order to sustain the flying machine in the air;
- the body of the flying machine comprises valve means for controllably producing horizontal jets of displaced air in order to control horizontal movement of the flying machine;
Humans have always been fascinated by the creatures capable, by means of sustaining of wings, and travelling through t he air. Over the years, they have imagined a multitude of concepts to allow them to fly. Examples of such concepts are described in the following United States patents:
- 210,238 (Cameron) 1878 - 361,855 (Beeson) 1887 - 727,377 (Kaehler) 1903 - 846,830 (Dufaux) 1907 - 881,836 (Warner) 1908 - 1,114,201 (Summers) 1914 - 1,450,072 (Goldschmidt) 1923 - 1,531,084 (Eckler) 1925 - 3,506,220 (Sbrilli) 1970 OBJECTS OF THE INVENTION
The main object of the present invention is a new concept for propelling a flying machine, this new concept using the well known gyroscopic effect.
SUMMARY OF THE INVENTION
More specifically, in accordance with the present invention, there is provided a system for propelling a flying machine, comprising:
a generally vertical pivot structure defining a generally vertical axis;
wing bearing means pivotally mounted on the generally vertical pivot structure about the generally vertical axis;
a plurality of wings each extending generally radially from the generally vertical axis, and each having a generally longitudinal wing axis intersecting the generally vertical axis;
for each wing, a hinge structure for pivotally mounting the wing on the bearing means about a generally horizontal hinge axis perpendicular to both the generally vertical axis and the generally longitudinal wing axis;
first and second rotative members mounted rotatable on the wing bearing means and a third rotative member mounted rotatable on each wing, the first rotative member being rotatable about (a) a first axis intersecting and perpendicular to the generally vertical axis and (b) a second axis intersecting and perpendicular to the first axis, the second rotative member being rotatable about (a) the first axis and (b) a third axis intersecting and perpendicular to the first axis, the second and third axes intersecting the first axis at diametrically opposed points with respect to the generally vertical axis, and each third rotative member being rotatable about a fourth axis intersecting the generally vertical axis; and driving motors connected to the rotative members for rotating in given directions the first rotative member about the first and second axes, the second rotative member about the first and third axes, and the third rotative member about the fourth axis to produce a recurrent cycle of precession that causes pivoting of the wing bearing means on the generally vertical pivot structure about the generally vertical axis and pivoting of the wings about the hinge structure to thereby flap the wings and displace air in order to propel said flying machine.
In accordance with preferred embodiments of the propelling system:
- the flying machine comprises a body including air deflecting means for directing air displaced by the flapping wings downwardly in order to sustain the flying machine in the air;
- the body of the flying machine comprises valve means for controllably producing horizontal jets of displaced air in order to control horizontal movement of the flying machine;
- each third rotative member comprise a wheel rotating about an axis perpendicular to both the generally longitudinal wing axis and the generally vertical axis;
- each third rotative member comprises a wheel rotating about an axis oblique with respect to the generally longitudinal axis of the wing.
- each wing comprises:
a wing frame mounted to the wing bearing means; and wing portions distributed radially on the wing frame from the generally vertical axis, each wing portion having pivots for pivotally mounting the wing portion on the wing frame about a generally horizontal axis perpendicular to both the generally vertical axis and the generally longitudinal wing axis.
The objects, advantages and other features of the present invention will become more apparent upon reading of the following non restrictive description of preferred embodiments thereof, given by way of example only with reference to the accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
In the appended drawings:
Figure 1 is a front elevational view of a flying machine equipped with a propelling system in accordance with the present invention;
Figure 2 is a top plan view of a set of four wings forming part of the propelling system of Figure 1;
- each third rotative member comprises a wheel rotating about an axis oblique with respect to the generally longitudinal axis of the wing.
- each wing comprises:
a wing frame mounted to the wing bearing means; and wing portions distributed radially on the wing frame from the generally vertical axis, each wing portion having pivots for pivotally mounting the wing portion on the wing frame about a generally horizontal axis perpendicular to both the generally vertical axis and the generally longitudinal wing axis.
The objects, advantages and other features of the present invention will become more apparent upon reading of the following non restrictive description of preferred embodiments thereof, given by way of example only with reference to the accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
In the appended drawings:
Figure 1 is a front elevational view of a flying machine equipped with a propelling system in accordance with the present invention;
Figure 2 is a top plan view of a set of four wings forming part of the propelling system of Figure 1;
5 Figures 3, 4a and 4b illustrate movement of the wings of Figure 2;
Figure 5, which is disposed on the same sheet of formal drawings as Figure 2 , is a top plan view of a set of twelve wings that can be used in the propelling system of the invention, each wing being formed of four wing portions;
Figure 6 is a front elevational view showing a pair of superposed conical arrangements of twelve wings, each wing being formed of four wing portions; and Figure 7, which is disposed on the same sheet of formal drawings as Figures 2 and 5, and Figure 8, disposed on the same sheet of formal drawings as Figure 6, show details of the wing portions of Figures 5 and 6.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
Figures 1 and 2 of the appended drawings illustrate a flying machine, generally identified by the reference numeral l0, comprising a propelling system in accordance with the present invention. As can be seen, the body 58 of the flying machine 10 presents the general configuration of a flying saucer.
The propelling system of the flying machine 10 comprises, as shown in Figures 1 and 2, a vertical shaft 11, motors 12 and 13, bevel gears 14 -19, vertical tube sections 20 and 21, a pair of diametrically opposed, horizontal shafts 22 and 23, transmissions (systems of gears) 24 and 25, rotative wheels 26 and 27, rotative wheels 28 - 31, flat wings 32 - 35, and hinges 36 - 39. Although the motors 12 and 13 can be electric motors, other types of motors, such as combustion engines, can be contemplated.
The housings of the two motors 12 and 13 are fixedly secured to a central floor portion 40 of the body 58 of the flying machine 10. Bevel gears 14 and 15 are respectively mounted on the free end of the horizontal, rotative shafts of the motors 12 and 13.
Tube section 20 is rotatively mounted on the vertical shaft 11, whereby it is free to rotate about the vertical geometrical axis 41 of that shaft 11. This tube section 20 comprises a lower end on which bevel gear 16 is mounted and an upper end on which bevel gear 17 is secured. As illustrated in Figure 1, bevel gears 14 and 15 are meshed with bevel gear 16.
Tube section 21 is also rotatively mounted on the shaft 11 whereby it is free to rotate about the vertical axis 41. The pair of diametrically opposed horizontal shafts 22 and 23 have proximate ends welded to the lower end of the tube section 21.
Bevel gear 18 comprises a central sleeve 44 rotatively mounted on the proximate end of the shaft 22 whereby gear 18 is free to rotate about horizontal axis 81. As shown, bevel gear 18 is meshed with bevel gear 17. The wheel 26 is rotatively mounted on a U-shaped bracket 82 itself mounted on the distal end of the shaft 22 through a sleeve 45 whereby the bracket 82 is free to rotate about axis 81. The wheel 26 therefore rotates about an axis 83 perpendicular to the axis 81, these two axes intersecting in the center of the wheel 26.
Rotational movement is transmitted to the sleeve 45 and therefore to the bracket 82 by the gear 18 through the sleeve 44 and the transmission 24. The wheel 26 is set in rotation about the axis 83 by a small electric motor (not shown) incorporated to this wheel.
In the same manner, bevel gear 19 comprises a central sleeve 46 rotatively mounted on the proximate end of the shaft 23 whereby gear 19 is free to rotate about horizontal axis 81. As shown, bevel gear 19 is meshed with bevel gear 17. The wheel 27 is rotatively mounted on a U-shaped bracket 84 itself mounted on the distal end of the shaft 23 through a sleeve 47 whereby the bracket 84 is free to rotate about axis 81. The wheel 27 therefore rotates about an axis 85 perpendicular to the axis 81, these two axes intersecting in the center of the wheel 27.
Rotational movement is transmitted to the sleeve 47 and therefore to the bracket 84 by the gear 19 through the sleeve 46 and the transmission 25. The wheel 27 is set in rotation about the axis 85 by a small electric motor (not shown) incorporated to this wheel.
In operation, the two motors 12 and 13 drive the tube section 20 through the meshed bevel gears 14, 15 and 16. The rotational movement of the tube section 20 is transmitted to the wheel 26 through the bevel gears 17 and 18, the sleeve 44, the transmission 24, the sleeve 45 and the bracket 82. In the same manner, rotational movement of the tube section 20 is transmitted to the wheel 27 through the bevel gears 17 and 19, the sleeve 46, the transmission 25, the sleeve 47 and the U-shaped bracket 84. As can be seen in Figure 1, the wheel 26 is rotated about axis 81 in direction 50 and about axis 83 in direction 86. Regarding wheel 27, it is rotated about axis 81 in direction 51 and about axis 85 in direction 87.
Figures 1 and 2 of the appended drawings illustrate a set of four wings 32 - 35. Each wing 32 - 35 is triangular and comprises a tapered proximal end mounted to the vertical tube section 21 through an hinge 36 - 39, respectively. These hinges enable pivoting (a) of wing 32 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 32' of this wing 32, (b) of wing 33 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 33' of this wing 33, (c) of wing 34 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 34' of this wing 34, and (d) of wing 35 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 35' of the wing 35.
The axes 32' - 35' intersect the vertical axis 41.
As shown in Figure 2, wings 32 and 34, and wings 33 and 35 form respective pairs of diametrically opposed wings. The distal edges of these wings 32 35 are semicircular to define a circle centered on the axis 41.
Wheel 28 is rotatively mounted on the wing 32 about the axis 32' at a predetermined distance from the axis 41, wheel 29 is rotatively mounted on the wing 33 about the axis 33' at said predetermined distance from axis 41, wheel 30 is rotatively mounted on the wing 34 about axis 34' at said predetermined distance from the axis 41, and wheel 31 is rotatively mounted on the wing 35 about the axis 35' again at said predetermined distance from the axis 41. Each wheel 28, 29, 30 and 31 are set into rotation in direction 52 (Figure 2), by means of an electric motor (not shown) incorporated to the wheel.
Operation of the propelling system in accordance with the present invention will now be explained.
The angular movement of the four wings 32, 33, 34 and 35 can be schematized as shown in Figures 3, 4a and 4b.
The three lines of Figure 3 represent the geometrical, generally radial axis 32', 33', 34' or 35' of one of the four wings 32, 33, 34 or 35 of Figure 2. R is the length of that wing. Point 53 5 (Figure 2) corresponding to the corresponding axis 32', 33', 34' or 35' at the free end of the wing oscillates along the dark portion 54 of the sinusoid of Figures 4a or 4b. The vertical amplitude A of the oscillatory movement of point 53 of each wing 32 - 35 10 therefore follows, in function of time, a sinusoid given by the following relation:
A = R sin(6Y/2) where 6Y/2 is the vertical angle between the geometrical axis of the wing and the horizontal.
The dark portion 54 of the sinusoid of Figures 4a and 4b represents the movement of the distal point 53 of the wing from one extreme position 55 to the other extreme position 56. Indeed, distal point 53 of each wing 32 - 35 will oscillate between the positions 55 and 56. More specifically, it will cyclically move from position 55 to position 56 and, then, from position 56 back to position 55.
As shown by Figures 4a and 4b, the maximum amplitude A of the sinusoid is constant in function of the power developed by the propelling system, but the period of the sinusoid varies, mainly in function of the rotational speed of the wheels 26 - 31. When the rotational speed of these wheels is low, the period of the sinusoid is long. Therefore, the higher is the rotational speed of the wheels, the shorter is the period of the sinusoid. It should be pointed out here that the term sin (6Y/2 ) is proportional to the ratio of the kinetic moment of the wheels 26 and 27 to the kinetic moment of the wheels 28 - 31 rotating on the wings. Other parameters may also influence the period of the sinusoid. The rotational speed of the wheels 26 - 31 can however be adjusted to compensate for such influence.
It should be pointed out that rotation of the tube section 21 on the vertical shaft 11 will allow the set of four wings 32 - 35 to rotate about the vertical axis 41. During this rotational movement, the bevel gears 17, 18 and 19 remain meshed together whereby the wheels 26 and 27 are continuously rotated through the motors 12 and 13 about axis 81.
To follow the dark portion 54 of the sinusoid of Figures 4a or 4b the wings 32 - 35 therefore turn about both the vertical shaft 11 and the hinges 36 -39.
The above described sinusoidal movement of the wings 32 - 35 does not produce any torsion in the plane of these wings. Indeed, the plane of each wing is not subj ected to any moment tending to turn the wing about its geometrical axis 32', 33', 34' or 35' . The hinge connecting the wing to the vertical tube section 21 is therefore subjected to no torsional force about the wing's geometrical axis. The reason is that the wheel 28, 29, 30 or 31 rotating on the wing 32, 33, 34 or 35 cannot induce a moment in its plane of rotation, that is a moment that would increase or decrease the rotational speed of the wheel.
The cause of the above described sinusoidal movement of the wings is the rotation of the wheel 26 about axes 81 and 83 and rotation of the wheel 27 about axes 81 and 85, in the respective directions 50, 86, 51 and 87, to produce centrifugal forces and therefore moments that subject these wheels to a precession to thereby turn the set of wings 32 -35 about the vertical shaft 11 and the hinges 36 - 39.
This is the well known gyroscopic effect. Obviously, the structure of the wheels must be chosen to give a sufficient moment of inertia while being light. It should also present sufficient rigidity to withstand the moments produced.
To reverse movement of the wings 32 - 35 along the dark portion 54 of the sinusoid of Figures 4a or 4b and thereby flap these wings 32 - 35, an opposite moment is required. This opposite moment is continuously generated by the wheels 28 - 31 rotating in the direction 52 on the wings 32 - 35.
Accordingly, movement of the set of wings will reverse after completion of a half-cycle of precession to thereby flap the wings along the above described trajectory (dark portion 54 of the sinusoid of Figures 4a or 4b). An advantage of the propelling system of the invention is that it requires very little anti torque compensation.
Of course, flapping of the wings 32 - 35 along the trajectory 54 will produce a displacement of air over the periphery of the body 58 of the flying machine 10. The displaced air (see arrows 59) is directed downwardly by the rounded shape of the peripheral portion 60 of the machine's body 58. This will produce the vertical, downward thrust required to sustain the flying machine 10 in the air. As can be appreciated, the portion 71 of the floor of the flying machine, around the central floor portion 40 supporting the motors 12 and 13, is open to enable production of the downward thrust 59.
The wheels 26 - 31 rotates at constant speed. The thrust sustaining the flying machine 10 in the air is controlled by adjusting the rotational speed of the wheel 26 in direction 50 about axis 81, and the rotational speed of the wheel 27 in direction 51 about axis 81. If the rotational speed about axis 81 decreases, the wings 32 - 35 will flap more slowly;
if this rotational speed increases, these wings will flap more rapidly. However, it should be pointed out that the angle 6y of Figure 3 remains constant whatever the speed of flapping of the wings 32 - 35.
The altitude of the flying machine will therefore be controlled through control of the above described thrust (see arrows 59). It should be pointed out here that the gyroscopic effect involved in producing the thrust 59 will also maintain the flying machine 10 horizontal.
Horizontal displacement of the flying machine 10 will be controlled by means of valves 61 distributed over the peripheral portion 60 of the machine's body 58. In the cockpit 62, controls will allow the pilot to open and close the valves 61 at will to displace the flying machine 10 horizontally.
Indeed, air displaced by the flapping wings 32 - 35 will pass through any open valve 61 to thereby produce thrusts such as 63 and 64 shown in dashed lines in Figure 1. Accordingly, opening of the appropriate valves 61 will propel the flying machine 10 horizontally in a given direction or will cause braking of the flying machine. Additional valves (not shown) can also be mounted on the peripheral portion 60 of the body 58 to control the angular orientation of the flying machine 10 in the horizontal plane.
The power developed by the propelling system, for a system of four full-length wings 32 -35, can be approximated by the following equations:
For the vertical thrust (sustenance):
P = 0 . 2 4 81 ( mq) 3~2 sin y 2 d For the horizontal thrust:
P = 0. 2481 (F) 3~2 ~ ~ 4~RZ sin (6y/2 ~
R sin ( y/2 cT
In the above equations:
m = the weight of the flying machine 10;
g = the acceleration of gravity;
R = the length of the wings 32-35 (see Figure 3);
6y = the vertical angle of flapping (see Figure 3);
do = the density of the air at sea level;
d = the density of the air at the altitude 5 of the flying machine 10;
F = the desired force of the horizontal thrust; and A = the area of opening of the valves 61.
10 Although Figure 1 illustrates a set of four full-length wings 32 - 35, each wing may be formed, as illustrated in Figure 5, of twelve wings such as 65 each formed of four wing portions such as 66 distributed radially over the length of the wing 15 65. These twelve wings 65 are distributed around the vertical tube section 21 (see Figure 1) and, as will be discussed in further details in the following description in connection with Figure 6, define a conical arrangement centered on the vertical tube section 21.
As shown in Figure 7 , each wing portion 66 is pivotally mounted on a pair of lateral metallic bars such as 67 and 68. The proximate end of each wing portion 66 is formed with lateral pivots 69 and 70 positioned in holes drilled in the bars 67 and 68, respectively. This will obviously enable rotation of the wing portion 66 about a generally horizontal axis passing through the pair of pivots 69 and 70. Of course, each bar such as 67 and 68 can receive the pivots of the wing portions 66 of two adjacent wings 65, respectively, situated on the opposite sides of this bar.
Figure 5, which is disposed on the same sheet of formal drawings as Figure 2 , is a top plan view of a set of twelve wings that can be used in the propelling system of the invention, each wing being formed of four wing portions;
Figure 6 is a front elevational view showing a pair of superposed conical arrangements of twelve wings, each wing being formed of four wing portions; and Figure 7, which is disposed on the same sheet of formal drawings as Figures 2 and 5, and Figure 8, disposed on the same sheet of formal drawings as Figure 6, show details of the wing portions of Figures 5 and 6.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
Figures 1 and 2 of the appended drawings illustrate a flying machine, generally identified by the reference numeral l0, comprising a propelling system in accordance with the present invention. As can be seen, the body 58 of the flying machine 10 presents the general configuration of a flying saucer.
The propelling system of the flying machine 10 comprises, as shown in Figures 1 and 2, a vertical shaft 11, motors 12 and 13, bevel gears 14 -19, vertical tube sections 20 and 21, a pair of diametrically opposed, horizontal shafts 22 and 23, transmissions (systems of gears) 24 and 25, rotative wheels 26 and 27, rotative wheels 28 - 31, flat wings 32 - 35, and hinges 36 - 39. Although the motors 12 and 13 can be electric motors, other types of motors, such as combustion engines, can be contemplated.
The housings of the two motors 12 and 13 are fixedly secured to a central floor portion 40 of the body 58 of the flying machine 10. Bevel gears 14 and 15 are respectively mounted on the free end of the horizontal, rotative shafts of the motors 12 and 13.
Tube section 20 is rotatively mounted on the vertical shaft 11, whereby it is free to rotate about the vertical geometrical axis 41 of that shaft 11. This tube section 20 comprises a lower end on which bevel gear 16 is mounted and an upper end on which bevel gear 17 is secured. As illustrated in Figure 1, bevel gears 14 and 15 are meshed with bevel gear 16.
Tube section 21 is also rotatively mounted on the shaft 11 whereby it is free to rotate about the vertical axis 41. The pair of diametrically opposed horizontal shafts 22 and 23 have proximate ends welded to the lower end of the tube section 21.
Bevel gear 18 comprises a central sleeve 44 rotatively mounted on the proximate end of the shaft 22 whereby gear 18 is free to rotate about horizontal axis 81. As shown, bevel gear 18 is meshed with bevel gear 17. The wheel 26 is rotatively mounted on a U-shaped bracket 82 itself mounted on the distal end of the shaft 22 through a sleeve 45 whereby the bracket 82 is free to rotate about axis 81. The wheel 26 therefore rotates about an axis 83 perpendicular to the axis 81, these two axes intersecting in the center of the wheel 26.
Rotational movement is transmitted to the sleeve 45 and therefore to the bracket 82 by the gear 18 through the sleeve 44 and the transmission 24. The wheel 26 is set in rotation about the axis 83 by a small electric motor (not shown) incorporated to this wheel.
In the same manner, bevel gear 19 comprises a central sleeve 46 rotatively mounted on the proximate end of the shaft 23 whereby gear 19 is free to rotate about horizontal axis 81. As shown, bevel gear 19 is meshed with bevel gear 17. The wheel 27 is rotatively mounted on a U-shaped bracket 84 itself mounted on the distal end of the shaft 23 through a sleeve 47 whereby the bracket 84 is free to rotate about axis 81. The wheel 27 therefore rotates about an axis 85 perpendicular to the axis 81, these two axes intersecting in the center of the wheel 27.
Rotational movement is transmitted to the sleeve 47 and therefore to the bracket 84 by the gear 19 through the sleeve 46 and the transmission 25. The wheel 27 is set in rotation about the axis 85 by a small electric motor (not shown) incorporated to this wheel.
In operation, the two motors 12 and 13 drive the tube section 20 through the meshed bevel gears 14, 15 and 16. The rotational movement of the tube section 20 is transmitted to the wheel 26 through the bevel gears 17 and 18, the sleeve 44, the transmission 24, the sleeve 45 and the bracket 82. In the same manner, rotational movement of the tube section 20 is transmitted to the wheel 27 through the bevel gears 17 and 19, the sleeve 46, the transmission 25, the sleeve 47 and the U-shaped bracket 84. As can be seen in Figure 1, the wheel 26 is rotated about axis 81 in direction 50 and about axis 83 in direction 86. Regarding wheel 27, it is rotated about axis 81 in direction 51 and about axis 85 in direction 87.
Figures 1 and 2 of the appended drawings illustrate a set of four wings 32 - 35. Each wing 32 - 35 is triangular and comprises a tapered proximal end mounted to the vertical tube section 21 through an hinge 36 - 39, respectively. These hinges enable pivoting (a) of wing 32 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 32' of this wing 32, (b) of wing 33 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 33' of this wing 33, (c) of wing 34 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 34' of this wing 34, and (d) of wing 35 about an horizontal axis perpendicular to both the vertical axis 41 and the geometrical, generally radial axis 35' of the wing 35.
The axes 32' - 35' intersect the vertical axis 41.
As shown in Figure 2, wings 32 and 34, and wings 33 and 35 form respective pairs of diametrically opposed wings. The distal edges of these wings 32 35 are semicircular to define a circle centered on the axis 41.
Wheel 28 is rotatively mounted on the wing 32 about the axis 32' at a predetermined distance from the axis 41, wheel 29 is rotatively mounted on the wing 33 about the axis 33' at said predetermined distance from axis 41, wheel 30 is rotatively mounted on the wing 34 about axis 34' at said predetermined distance from the axis 41, and wheel 31 is rotatively mounted on the wing 35 about the axis 35' again at said predetermined distance from the axis 41. Each wheel 28, 29, 30 and 31 are set into rotation in direction 52 (Figure 2), by means of an electric motor (not shown) incorporated to the wheel.
Operation of the propelling system in accordance with the present invention will now be explained.
The angular movement of the four wings 32, 33, 34 and 35 can be schematized as shown in Figures 3, 4a and 4b.
The three lines of Figure 3 represent the geometrical, generally radial axis 32', 33', 34' or 35' of one of the four wings 32, 33, 34 or 35 of Figure 2. R is the length of that wing. Point 53 5 (Figure 2) corresponding to the corresponding axis 32', 33', 34' or 35' at the free end of the wing oscillates along the dark portion 54 of the sinusoid of Figures 4a or 4b. The vertical amplitude A of the oscillatory movement of point 53 of each wing 32 - 35 10 therefore follows, in function of time, a sinusoid given by the following relation:
A = R sin(6Y/2) where 6Y/2 is the vertical angle between the geometrical axis of the wing and the horizontal.
The dark portion 54 of the sinusoid of Figures 4a and 4b represents the movement of the distal point 53 of the wing from one extreme position 55 to the other extreme position 56. Indeed, distal point 53 of each wing 32 - 35 will oscillate between the positions 55 and 56. More specifically, it will cyclically move from position 55 to position 56 and, then, from position 56 back to position 55.
As shown by Figures 4a and 4b, the maximum amplitude A of the sinusoid is constant in function of the power developed by the propelling system, but the period of the sinusoid varies, mainly in function of the rotational speed of the wheels 26 - 31. When the rotational speed of these wheels is low, the period of the sinusoid is long. Therefore, the higher is the rotational speed of the wheels, the shorter is the period of the sinusoid. It should be pointed out here that the term sin (6Y/2 ) is proportional to the ratio of the kinetic moment of the wheels 26 and 27 to the kinetic moment of the wheels 28 - 31 rotating on the wings. Other parameters may also influence the period of the sinusoid. The rotational speed of the wheels 26 - 31 can however be adjusted to compensate for such influence.
It should be pointed out that rotation of the tube section 21 on the vertical shaft 11 will allow the set of four wings 32 - 35 to rotate about the vertical axis 41. During this rotational movement, the bevel gears 17, 18 and 19 remain meshed together whereby the wheels 26 and 27 are continuously rotated through the motors 12 and 13 about axis 81.
To follow the dark portion 54 of the sinusoid of Figures 4a or 4b the wings 32 - 35 therefore turn about both the vertical shaft 11 and the hinges 36 -39.
The above described sinusoidal movement of the wings 32 - 35 does not produce any torsion in the plane of these wings. Indeed, the plane of each wing is not subj ected to any moment tending to turn the wing about its geometrical axis 32', 33', 34' or 35' . The hinge connecting the wing to the vertical tube section 21 is therefore subjected to no torsional force about the wing's geometrical axis. The reason is that the wheel 28, 29, 30 or 31 rotating on the wing 32, 33, 34 or 35 cannot induce a moment in its plane of rotation, that is a moment that would increase or decrease the rotational speed of the wheel.
The cause of the above described sinusoidal movement of the wings is the rotation of the wheel 26 about axes 81 and 83 and rotation of the wheel 27 about axes 81 and 85, in the respective directions 50, 86, 51 and 87, to produce centrifugal forces and therefore moments that subject these wheels to a precession to thereby turn the set of wings 32 -35 about the vertical shaft 11 and the hinges 36 - 39.
This is the well known gyroscopic effect. Obviously, the structure of the wheels must be chosen to give a sufficient moment of inertia while being light. It should also present sufficient rigidity to withstand the moments produced.
To reverse movement of the wings 32 - 35 along the dark portion 54 of the sinusoid of Figures 4a or 4b and thereby flap these wings 32 - 35, an opposite moment is required. This opposite moment is continuously generated by the wheels 28 - 31 rotating in the direction 52 on the wings 32 - 35.
Accordingly, movement of the set of wings will reverse after completion of a half-cycle of precession to thereby flap the wings along the above described trajectory (dark portion 54 of the sinusoid of Figures 4a or 4b). An advantage of the propelling system of the invention is that it requires very little anti torque compensation.
Of course, flapping of the wings 32 - 35 along the trajectory 54 will produce a displacement of air over the periphery of the body 58 of the flying machine 10. The displaced air (see arrows 59) is directed downwardly by the rounded shape of the peripheral portion 60 of the machine's body 58. This will produce the vertical, downward thrust required to sustain the flying machine 10 in the air. As can be appreciated, the portion 71 of the floor of the flying machine, around the central floor portion 40 supporting the motors 12 and 13, is open to enable production of the downward thrust 59.
The wheels 26 - 31 rotates at constant speed. The thrust sustaining the flying machine 10 in the air is controlled by adjusting the rotational speed of the wheel 26 in direction 50 about axis 81, and the rotational speed of the wheel 27 in direction 51 about axis 81. If the rotational speed about axis 81 decreases, the wings 32 - 35 will flap more slowly;
if this rotational speed increases, these wings will flap more rapidly. However, it should be pointed out that the angle 6y of Figure 3 remains constant whatever the speed of flapping of the wings 32 - 35.
The altitude of the flying machine will therefore be controlled through control of the above described thrust (see arrows 59). It should be pointed out here that the gyroscopic effect involved in producing the thrust 59 will also maintain the flying machine 10 horizontal.
Horizontal displacement of the flying machine 10 will be controlled by means of valves 61 distributed over the peripheral portion 60 of the machine's body 58. In the cockpit 62, controls will allow the pilot to open and close the valves 61 at will to displace the flying machine 10 horizontally.
Indeed, air displaced by the flapping wings 32 - 35 will pass through any open valve 61 to thereby produce thrusts such as 63 and 64 shown in dashed lines in Figure 1. Accordingly, opening of the appropriate valves 61 will propel the flying machine 10 horizontally in a given direction or will cause braking of the flying machine. Additional valves (not shown) can also be mounted on the peripheral portion 60 of the body 58 to control the angular orientation of the flying machine 10 in the horizontal plane.
The power developed by the propelling system, for a system of four full-length wings 32 -35, can be approximated by the following equations:
For the vertical thrust (sustenance):
P = 0 . 2 4 81 ( mq) 3~2 sin y 2 d For the horizontal thrust:
P = 0. 2481 (F) 3~2 ~ ~ 4~RZ sin (6y/2 ~
R sin ( y/2 cT
In the above equations:
m = the weight of the flying machine 10;
g = the acceleration of gravity;
R = the length of the wings 32-35 (see Figure 3);
6y = the vertical angle of flapping (see Figure 3);
do = the density of the air at sea level;
d = the density of the air at the altitude 5 of the flying machine 10;
F = the desired force of the horizontal thrust; and A = the area of opening of the valves 61.
10 Although Figure 1 illustrates a set of four full-length wings 32 - 35, each wing may be formed, as illustrated in Figure 5, of twelve wings such as 65 each formed of four wing portions such as 66 distributed radially over the length of the wing 15 65. These twelve wings 65 are distributed around the vertical tube section 21 (see Figure 1) and, as will be discussed in further details in the following description in connection with Figure 6, define a conical arrangement centered on the vertical tube section 21.
As shown in Figure 7 , each wing portion 66 is pivotally mounted on a pair of lateral metallic bars such as 67 and 68. The proximate end of each wing portion 66 is formed with lateral pivots 69 and 70 positioned in holes drilled in the bars 67 and 68, respectively. This will obviously enable rotation of the wing portion 66 about a generally horizontal axis passing through the pair of pivots 69 and 70. Of course, each bar such as 67 and 68 can receive the pivots of the wing portions 66 of two adjacent wings 65, respectively, situated on the opposite sides of this bar.
Each metallic bar such as 67 and 68 comprises a proximate end welded to the vertical tube section 21 (Figure 6) whereby the set of twelve wings 65 rotate about the vertical axis 41 along with the vertical tube section 21. The distal ends of the metallic bars 67,68 of the wing 65 is bent to slide in a circular channel member 72. This enables rotational movement of the metallic bars 67,68 about the vertical axis 41 while upward bending of these bars is prevented. Low-friction material will facilitate sliding of the distal ends of the bars 67, 68 in the circular channel member 72 to thereby reduce attrition. As can be seen in Figure 6, the channel member 72 is lying in an horizontal plane lower than the position of the proximal ends of the metallic bars 67,68 welded to the vertical tube 21 whereby the set of wings 65 defines a conical arrangement 73 having an apex angle oriented upwardly.
Figure 6 shows a second conical arrangement 74 of wings 65' situated above the conical arrangement 73; it comprises a set of twelve wings 65' each formed of four wing portions 66', each wing portion 66' being pivotally mounted on metallic bars 67',68'. However, the conical wing arrangement 74 has an apex angle which is equal to that of the arrangement 73 but which is oriented downwardly. The distal end of each metallic bar 67',68' of the upper conical wing arrangement 74 is mechanically connected to the distal end of a corresponding lower metallic bar 67,68, having a same angular position about the vertical axis 41, through a rigid metallic link 75 which can be either vertical or slanted (see 76).
Figure 6 shows a second conical arrangement 74 of wings 65' situated above the conical arrangement 73; it comprises a set of twelve wings 65' each formed of four wing portions 66', each wing portion 66' being pivotally mounted on metallic bars 67',68'. However, the conical wing arrangement 74 has an apex angle which is equal to that of the arrangement 73 but which is oriented downwardly. The distal end of each metallic bar 67',68' of the upper conical wing arrangement 74 is mechanically connected to the distal end of a corresponding lower metallic bar 67,68, having a same angular position about the vertical axis 41, through a rigid metallic link 75 which can be either vertical or slanted (see 76).
Rotating wheels such as 77 can be mounted only on the second wing portion 66 (from the tube section 21) of each wing 65. Flapping movement is then imparted to the other wing portions 66 and 66' through rigid links 78 interconnecting the free distal ends of the wing portions 66 or 66' of each wing 65 and 65', and through strings 79 interconnecting the free end of the second wing portion 66 (from the tube section 21) of each lower wing 66 and the free end of the second wing portion 66' of the corresponding upper wing 65'. Of course, the free ends of the wing portions 66 and 66' are pivotally connected to the different rigid links 78. The strings 79 will lower the upper wing portions 66' upon downward movement of the lower wing portions 66. Upward movement can be imparted to the upper wing portions 66' by torsional coil springs (not shown). Flapping movement of the wing portions 66 on which the wheels 77 rotate, which is imparted to the other wing portions 66 and 66' through the links 78 and strings 79 is described in the foregoing description with reference to the full-length wings 32 - 35 of Figures 1 and 2.
To prevent portion 57 (Figure 1) of the propelling system to interfere in the movement of the air, it can be covered with a conical wall (not shown) having the same slope as the lower conical wing arrangement 73 whereby any deviation of air by 180°
will be prevented.
It is possible, as illustrated in Figure 8, to flap the wing portions 66 and 66' about a central, non horizontal position 80 by orienting the plane of the wheels 77 obliquely with respect to the plane of the corresponding wing portions 66. This will however produce an undesirable additional horizontal thrust.
When full-length wings such as 32 - 35 are replaced by a plurality of radially distributed wing portions such as 66 and 66' to sustain a load in the air, it has been discovered that, for a same lift surface, the power required to perform this sustenance is as low as the wing portions are short in the radial direction. Indeed, the power required to accomplish the sustenance is proportional to the cube root of the length of the wings (or wing portions) if the total surface of all the wings remains the same.
The wing portions 66 and 66' may also be disposed to define at two superposed conical wing arrangements of which one is situated inside the other. If the two conical arrangements have the same apex angle, they must be separated by a given distance to enable air to flow between them. Their apex angles can however be different and eventually inverse as illustrated in Figure 6.
In operation, a centrifugal force is produced by the change in direction of the movement of the air as it displaces along a flapping wing.
Moreover, partial addition of air speeds is caused when air is transferred radially from one wing portion to the other. Also, as air is compressible, high frequency flapping of the wings will create zones of partial vacuum. These phenomena may reduce the ' 20 7352 519 efficiency of the wing structure of the propelling system in accordance with the present invention.
Although the present invention has been described hereinabove by way of preferred embodiments thereof, such embodiments can be modified at will, within the scope of the appended claims, without departing from the spirit and nature of the subject invention.
To prevent portion 57 (Figure 1) of the propelling system to interfere in the movement of the air, it can be covered with a conical wall (not shown) having the same slope as the lower conical wing arrangement 73 whereby any deviation of air by 180°
will be prevented.
It is possible, as illustrated in Figure 8, to flap the wing portions 66 and 66' about a central, non horizontal position 80 by orienting the plane of the wheels 77 obliquely with respect to the plane of the corresponding wing portions 66. This will however produce an undesirable additional horizontal thrust.
When full-length wings such as 32 - 35 are replaced by a plurality of radially distributed wing portions such as 66 and 66' to sustain a load in the air, it has been discovered that, for a same lift surface, the power required to perform this sustenance is as low as the wing portions are short in the radial direction. Indeed, the power required to accomplish the sustenance is proportional to the cube root of the length of the wings (or wing portions) if the total surface of all the wings remains the same.
The wing portions 66 and 66' may also be disposed to define at two superposed conical wing arrangements of which one is situated inside the other. If the two conical arrangements have the same apex angle, they must be separated by a given distance to enable air to flow between them. Their apex angles can however be different and eventually inverse as illustrated in Figure 6.
In operation, a centrifugal force is produced by the change in direction of the movement of the air as it displaces along a flapping wing.
Moreover, partial addition of air speeds is caused when air is transferred radially from one wing portion to the other. Also, as air is compressible, high frequency flapping of the wings will create zones of partial vacuum. These phenomena may reduce the ' 20 7352 519 efficiency of the wing structure of the propelling system in accordance with the present invention.
Although the present invention has been described hereinabove by way of preferred embodiments thereof, such embodiments can be modified at will, within the scope of the appended claims, without departing from the spirit and nature of the subject invention.
Claims (11)
1. A system for propelling a flying machine, comprising:
a generally vertical pivot structure defining a generally vertical axis;
wing bearing means pivotally mounted on the generally vertical pivot structure about the generally vertical axis;
a plurality of wings each extending generally radially from said generally vertical axis, and each having a generally longitudinal wing axis intersecting said generally vertical axis;
for each wing, a hinge structure for pivotally mounting the wing on the bearing means about a generally horizontal hinge axis perpendicular to both said generally vertical axis and said generally longitudinal wing axis;
first and second rotative members mounted rotatable on said wing bearing means and a third rotative member mounted rotatable on each wing, said first rotative member being rotatable about (a) a first axis intersecting and perpendicular to said generally vertical axis and (b) a second axis intersecting and perpendicular to said first axis, said second rotative member being rotatable about (a) said first axis and (b) a third axis intersecting and perpendicular to said first axis, said second and third axes intersecting said first axis at diametrically opposed points with respect to said generally vertical axis, and each third rotative member being rotatable about a fourth axis intersecting said generally vertical axis; and driving motors connected to the rotative members for rotating in given directions the first rotative member about said first and second axes, the second rotative member about the first and third axes, and the third rotative member about the fourth axis to produce a recurrent cycle of precession that causes pivoting of the wing bearing means on the generally vertical pivot structure about said generally vertical axis and pivoting of the wings about said hinge structure to thereby flap the wings and displace air in order to propel said flying machine.
a generally vertical pivot structure defining a generally vertical axis;
wing bearing means pivotally mounted on the generally vertical pivot structure about the generally vertical axis;
a plurality of wings each extending generally radially from said generally vertical axis, and each having a generally longitudinal wing axis intersecting said generally vertical axis;
for each wing, a hinge structure for pivotally mounting the wing on the bearing means about a generally horizontal hinge axis perpendicular to both said generally vertical axis and said generally longitudinal wing axis;
first and second rotative members mounted rotatable on said wing bearing means and a third rotative member mounted rotatable on each wing, said first rotative member being rotatable about (a) a first axis intersecting and perpendicular to said generally vertical axis and (b) a second axis intersecting and perpendicular to said first axis, said second rotative member being rotatable about (a) said first axis and (b) a third axis intersecting and perpendicular to said first axis, said second and third axes intersecting said first axis at diametrically opposed points with respect to said generally vertical axis, and each third rotative member being rotatable about a fourth axis intersecting said generally vertical axis; and driving motors connected to the rotative members for rotating in given directions the first rotative member about said first and second axes, the second rotative member about the first and third axes, and the third rotative member about the fourth axis to produce a recurrent cycle of precession that causes pivoting of the wing bearing means on the generally vertical pivot structure about said generally vertical axis and pivoting of the wings about said hinge structure to thereby flap the wings and displace air in order to propel said flying machine.
2. The propelling system of claim 1, in which said flying machine comprises a body including air deflecting means for directing air displaced by said flapping wings downwardly in order to sustain said flying machine in the air.
3. The propelling system of claim 1, wherein said flying machine comprises a body including valve means for controllably producing horizontal jets of said displaced air in order to control horizontal movement of the flying machine.
4. The propelling system of claim 1, wherein the generally vertical pivot structure comprises a fixed generally vertical shaft centered on the generally vertical axis, and said wing bearing means comprises a first tube section rotatable on the fixed generally vertical shaft about said generally vertical axis, said propelling system further comprising a pair of first and second fixed radial shafts perpendicular to and diametrically opposed with respect to said generally vertical axis, said first and second radial shafts having respective proximate ends secured to said first tube section and respective distal ends on which said first and second rotative members are mounted, said means for rotating said first and second rotative members comprising:
a second tube section rotatable on said fixed generally vertical shaft and comprising a first end on which a first bevel gear is fixedly mounted and a second end on which a second bevel gear is fixedly mounted;
first and second motors, said first motor comprising a rotative shaft with a free end bearing a third bevel gear meshed with said first bevel gear, and said second motor comprising a rotative shaft with a free end bearing a fourth bevel gear meshed with said first bevel gear, said shafts of the first and second motors being diametrically opposed with respect to said generally vertical axis;
fifth and sixth bevel gears rotatively mounted on the first and second radial shafts, respectively, and both meshed with said second bevel gear, said fifth bevel gear being connected to the first rotative member to rotate said first member, and said sixth bevel gear being connected to the second rotative member to rotate said second member;
whereby rotation of the shafts of said first and second motors will rotate said first and second rotative members through the third and fourth bevel gears, the first bevel gear, the second tube section, the second bevel gear, and the fifth and sixth bevel gears.
a second tube section rotatable on said fixed generally vertical shaft and comprising a first end on which a first bevel gear is fixedly mounted and a second end on which a second bevel gear is fixedly mounted;
first and second motors, said first motor comprising a rotative shaft with a free end bearing a third bevel gear meshed with said first bevel gear, and said second motor comprising a rotative shaft with a free end bearing a fourth bevel gear meshed with said first bevel gear, said shafts of the first and second motors being diametrically opposed with respect to said generally vertical axis;
fifth and sixth bevel gears rotatively mounted on the first and second radial shafts, respectively, and both meshed with said second bevel gear, said fifth bevel gear being connected to the first rotative member to rotate said first member, and said sixth bevel gear being connected to the second rotative member to rotate said second member;
whereby rotation of the shafts of said first and second motors will rotate said first and second rotative members through the third and fourth bevel gears, the first bevel gear, the second tube section, the second bevel gear, and the fifth and sixth bevel gears.
5. The propelling system of claim 4, wherein said fifth bevel gear is connected to the first rotative member through a first transmission means, and wherein said sixth bevel gear is connected to the second rotative member through a second transmission means.
6. The propelling system of claim 4, wherein:
said first rotative member comprises a first wheel-supporting bracket rotated by said fifth bevel gear about said first axis and a first wheel rotatively mounted on said first bracket;
said rotating means comprises a first electric motor interposed between said first bracket and said first wheel for rotating said first wheel about said second axis;
said second rotative member comprises a second wheel-supporting bracket rotated about said first axis by said sixth bevel gear and a second wheel rotatively mounted on said second bracket; and said rotating means comprises a second electric motor interposed between said second bracket and said second wheel for rotating said second wheel about said third axis.
said first rotative member comprises a first wheel-supporting bracket rotated by said fifth bevel gear about said first axis and a first wheel rotatively mounted on said first bracket;
said rotating means comprises a first electric motor interposed between said first bracket and said first wheel for rotating said first wheel about said second axis;
said second rotative member comprises a second wheel-supporting bracket rotated about said first axis by said sixth bevel gear and a second wheel rotatively mounted on said second bracket; and said rotating means comprises a second electric motor interposed between said second bracket and said second wheel for rotating said second wheel about said third axis.
7. The propelling system of claim 1, wherein each third rotative member comprise a wheel rotating about an axis perpendicular to both the generally longitudinal wing axis and the generally vertical axis.
8. The propelling system of claim 1, wherein each third rotative member comprises a wheel rotating about an axis oblique with respect to the generally longitudinal axis of the wing.
9. The propelling system of claim 1, wherein each wing comprises:
a wing frame mounted to said wing bearing means; and wing portions distributed radially on the wing frame from said generally vertical axis, each wing portion having pivots for pivotally mounting the wing portion on the wing frame about a generally horizontal axis perpendicular to both said generally vertical axis and said generally longitudinal wing axis.
a wing frame mounted to said wing bearing means; and wing portions distributed radially on the wing frame from said generally vertical axis, each wing portion having pivots for pivotally mounting the wing portion on the wing frame about a generally horizontal axis perpendicular to both said generally vertical axis and said generally longitudinal wing axis.
10. The propelling system of claim 9, wherein said wing portions define two superposed conical arrangements of wing portions.
11. The propelling system of claim 9, wherein, for each wing:
the wing portions include a first wing portion having a generally longitudinal wing portion axis intersecting the generally vertical axis, said wing portion having respective distal free ends;
said third rotative member comprises a rotative wheel mounted rotatable on the first wheel portion about said generally longitudinal wing portion axis;
an elongated member for connecting the free end of said first wing portion to the free end of the other wing portions in order to transmit flapping movement of the first wing portion to said other wing portions.
the wing portions include a first wing portion having a generally longitudinal wing portion axis intersecting the generally vertical axis, said wing portion having respective distal free ends;
said third rotative member comprises a rotative wheel mounted rotatable on the first wheel portion about said generally longitudinal wing portion axis;
an elongated member for connecting the free end of said first wing portion to the free end of the other wing portions in order to transmit flapping movement of the first wing portion to said other wing portions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002073525A CA2073525C (en) | 1992-07-09 | 1992-07-09 | Propelling system for flying machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002073525A CA2073525C (en) | 1992-07-09 | 1992-07-09 | Propelling system for flying machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2073525A1 CA2073525A1 (en) | 1994-01-10 |
| CA2073525C true CA2073525C (en) | 2001-07-31 |
Family
ID=4150129
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002073525A Expired - Lifetime CA2073525C (en) | 1992-07-09 | 1992-07-09 | Propelling system for flying machine |
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| Country | Link |
|---|---|
| CA (1) | CA2073525C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110789712A (en) * | 2019-10-31 | 2020-02-14 | 张富林 | Elbow power device and flying saucer |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108995808A (en) * | 2018-08-31 | 2018-12-14 | 耿天侃 | It can the annular wing disc-shaped flying craft that can hover of VTOL |
-
1992
- 1992-07-09 CA CA002073525A patent/CA2073525C/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110789712A (en) * | 2019-10-31 | 2020-02-14 | 张富林 | Elbow power device and flying saucer |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2073525A1 (en) | 1994-01-10 |
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