US3474987A

US3474987A - Helicopter device

Info

Publication number: US3474987A
Application number: US655614A
Authority: US
Inventors: Ludwig F Meditz
Original assignee: Individual
Current assignee: Individual
Priority date: 1967-07-24
Filing date: 1967-07-24
Publication date: 1969-10-28
Anticipated expiration: 1986-10-28

Description

Oct. 28, 1969 F. MEDlTZ 3,474;987

HELICOPTER DEVICE 7 Sheets-Sheet 1 Filed July 24, 1967 INVENTOR Ludwig E Nedzz BY 477W 5 Oct. 28, 1969 F. MEDITZ 3,474,987

HELICOPTER DEVICE Filed July 24, 1967 7 Sheets-Sheet 5 A M 144 1% {w m m 79 a) 72g 172 170 152 1 ,11 in INVENTOR Oct. 28, 1969 L. F. MEDITZ HELICOPTER DEVICE 7 Sheets-Sheet 4 Filed July 24, 1967 INVENTOR Zach/4g F Nedzz BY ENG Oct. 28, 1969 L. F. MEDITZ 3,474,987

HELICOPTER DEVICE Filed July 24, 1967 7 Sheets-Sheet 5 zwe F/IV RUDDERS w Zudmjg f. Neatz BY W v An- Oct. 28, 1969 L. F. MEDITZ HELICOPTER DEVICE '7 Sheets-Sheet 6 Filed July 24, 1967 Ludwig I". Nedtz Oct. 28, 1969 L. F. MEDITZ 3,474,987

HELICOPTER DEVICE Filed July 24, 1967 7 Sheets-Sheet 7 201 EEE X,

INVENTOR Zudwig f NeczZZZ United States Patent 3,474,987 HELICOPTER DEVICE Ludwig F. Meditz, 419 E. 12th St., New York, N.Y. 10003 Filed July 24, 1967, Ser. No. 655,614 Int. Cl. B64c 27/00 US. Cl. 244-4 6 Claims ABSTRACT OF THE DISCLOSURE A helicopter device of the harness or platform type for transporting a single person through the air, having a supporting structure to carry a single person, connected to a second structure having a power unit with controls to direct movement of the person vertically and forward as desired. Interposed between the supporting structures is a universal type arrangement which permits the rotation of the person in either a vertical or a prone position. The device includes control of both the movement of the person in the two positions and in addition the control of the operation of the power unit and control system to guide the device through the air.

This invention relates generally to V/STOL aircraft and more particularly to helicopter devices of the harness or platform type for transporting a single person through the air.

Description of the prior art Present day devices of this type include complicated arrangements for directional control and for control of lift or vertical thrust. These arrangements make the helicopter devices heavy and prone to malfunction.

Summary of the invention An object of this invention is to provide a helicopter device of the harness of platform type which is light, rugged and has simple means for controlling direction and lift.

Another object of this invention is to provide a personal type helicopter in which the lift can be varied without adjusting the engine setting or propeller control.

And another object of this invention is to provide control means in the aforementioned device capable of directional control.

Yet another object is to provide an improved aircraft of the helicopter type having a fan unit for hovering, vertical landing and vertical take-off, and intermediate and vertical positions for forward flight and directional control.

Still another object is to provide a ducted fan unit in a helicopter that is adapted to be driven by the exhaust or a jet engine directed against the periphery of the fan.

A further object of the invention is to provide novel universal means for mounting the fan unit for pivotable adjustment relative to the occupant pilot of the aircraft.

For further comprehension of the invention and of the objects and advantages theerof, reference will be had to the accompanying drawings forming a material part of this disclosure:

FIGURE 1 is a front perspective view of a device constructed according to a preferred embodiment of the invention;

FIG. 2 is a side elevational view of the device shown in FIG. 1;

FIG. 3 is a fragmentary sectional view of an element of the device of section 3-3 of FIG. 2;

FIG. 4 is a sectional view of the element of FIG, 3 taken substantially along line 44 of FIG. 3;

FIG. 5 is a detailed perspective view of the universal drive coupling utilized in the device;

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FIG. 6 is an enlarged sectional view taken substantially along line 6-6 of FIG. 5;

FIG. 7 is a sectional view taken substantially along line 7-7 of FIG. 6;

FIG. 8 is a sectional view taken substantially along line 8--8 of FIGS. 1 and 2;

FIG. 9 is a perspective view showing a controlled dashboard of the device of FIG. 1;

FIG. 10 is a detailed fragmentary view of a portion of the controlled dashboard shown in FIG. 9;

FIG. 11 is a schematic perspective view of the control system of the device of FIG. 1;

FIG. 12 is a fragmentary side elevational view of the device constructed according to another embodiment of the invention;

FIG. 13 is a sectional view taken substantially along line 1313 of FIG. 12;

FIG. 14 is a side elevational view of the pilots seat in operative position;

FIG. 15 is a plan view of the device constructed according to still another embodiment of the invention;

FIG. 16 is a side elevational view of the device shown in FIG. 15;

FIG. 17 is a fragmentary front elevational view of the device in FIGS. 15 and 16.

Description of the preferred embodiments An aircraft adapted to travel through the air having three axes, a longitudinal or roll axis X-X which extends fore and aft, a lateral or pitch axis Y-Y which extends from side to side, and a vertical or yaw axis ZZ.

Referring now in detail to the various views of the drawings, an aircraft or a helicopter 10 made in accordance with the invention includes a combined control housing, air pump and pilot supporting apparatus or cradle platform assembly 12 for supporting a pilot P and a structure 14 for supporting a fan assembly 21 having an annular band 22 of arcuate-shape in cross-section. A pair of spaced

arms

24, 24 extend across the space between the body of the annular band 22 and are joined midway by a cross-piece 26. Across the top of the band are spaced arms 28 integrally joined at their ends to the top edge of the band. A cross-piece 30 extends across the middle arms 28 and is formed with a hub portion 32 having a bearing opening 34 therein. At one side of the band, a fiat piece 36 extends underneath the adjacent edge of the band 22 and is secured to the bottom edge thereof. A flat piece 38 extends across the periphery of the band 22 inwardly of the piece 36 and is secured at its ends to the bottom edge of the band.

A propeller fan 40 is rotatably mounted on a shaft 42 as best shown in FIG. 2, journalled in the aligned bearing holes in the

crosspieces

26 and 30. The fan 40 includes three blades 44 radially mounted on hub portion 46 which is rotatably mounted on the shaft 42. The free ends of the blades 44 extend outwardly to the band 22. Formed on the ends of the blades 44 there is annular vane 48 positioned inside the body of the band 22. At one side of the band 22, a pair of horizontally-disposed

elevators

50, 50 are hingedly secured to the outer long edge of the flat piece 36 by means of hinges 52. A verticallydisposed stabilizer 54 is secured to the cross piece 26 supporting a rudder 56 which is connected thereto by means of a hinge 58.

At the opposite side of the band 22 an enlargement 60 is formed on the outer surface of the periphery thereof. The enlargement 60 is formed with a central passage 62 extending therethrough and communicating with the interior of the band 22, as indicated at 64 as best shown in FIG. 3. A pair of pivoted louvres or

vanes

66, 66 as best shown in FIGS. 2 and 11 is pivotally supported on 3

stub shafts

68, 70 between spaced

brackets

72 and 74 respectively, and fastened to the

bottom arms

24, 24 at the ends thereof adjacent the

stabilizers

50, 50 on both sides of the fan assembly 21.

The combined control housing air pump and pilot supporting apparatus or cradle platform assembly 12 forming a rigid unitary structure is suspended from the fan assembly 21 of the structure 14 by means of an upright post 78, pivotally connected at its top end as viewed in FIG. 2, to the fan assembly 21 by a universal joint structure 80, and swingably connected at its bottom end to the cradle platform assembly or unitary structure 12 by means of gearing 82.

A control assembly 83 comprises a substantially rectangular shaped casing 84 closed at one end by an end wall 85 and supporting a closure plate 86 through which protrude knobs 87 as best shown in FIG. 9 for actuating reversible motors 88 in the casing 84 for driving the aircraft steering controls and tilt the fan assembly 21 as desired. A steering post 89 extends through the end Wall 85 and mounts a steering wheel 90 on its outer end and a bevel gear 91 on its inner end meshing with a bevel gear 92 on the end of a flexible shaft 112. The opposite end of the casing 84 is formed with an outlet opening 94 through which extend a plurality of flexible shafts leading from the motors 88 to the fan assembly 21, elevators 50, rudder 56 and louvres 66, and to the various connections of the upright post 78. Flexible shaft 93 also extends through the outlet opening to the gearing 82. A flexible shaft 104 leads to the left hand side of the universal joint 80 as viewed in FIG. 2 at the top of the post 78, flexible shaft 106 leads to the right hand side thereof, flexible shaft 108 leads to each of the

louvres

66, 66, flexible shaft 110 leads to the horizontal elevators 50, hinges 52 of the

horizontal elevators

50, 50 and flexible shaft 112 leads to the hinge connection 58 of the rudder 56.

As best shown in FIGS. 9 and an air pump or blower 114 comprises a cylindrical hollow casing 115 with a ventilating mesh-protected opening 116 at one end thereof with the other end being welded to the side wall of the casing 84. A tubular outlet 117 is formed on the periphery of the casing 115 tangentially thereof. One end of flexible metal air hose 120 is fitted in the outlet 117 with its other end in the inlet opening 62 in the enlargement 60 on the band 22 for supplying compressed air to the interior of the band 22. A bracket 122 may be fastened to the band 22 to support and guide the metal air hose 120.

The pilot supporting cradle apparatus 12 has a body section made of aluminum or fiber glass and arcuateshaped in cross-section. Opposed crosspieces 124 as best shown in FIGS. 1 and 8, extend across the space between the sides of the cradle body 12 leaving a space therebetween. The free ends of the crosspieces 124 are formed with enlargements having bearing members 121 for supporting a shaft 123. A worm gear 125 is fixed upon shaft 123. At one end of the cradle body 12, a pair of shoulder extensions 126 are formed on the sides thereof for supporting the shoulders of the pilot P and retains the pilot against any forward sliding movement in the cradle body. At its other end, the cradle body is formed with an extension 128 and depending from each side of the body there is a hollow cylinder 130 and a piston 132 movable therein; depending from each side of the extension 128 there is a link 134 pivotally connected thereto. The pistons and links pivotally support a seat 136 therebetween. A rod 138 is pivotally connected at one end to the center of the seat for supporting the seat on a horizontal supporting surface S as shown in FIG. 14. The control housing 84 is rigidly joined by welding or the like to the pilot-supporting cradle apparatus 12.

The connection between the bottom end of the post 78 and the combined supporting cradle apparatus as best seen in FIG. 8 includes a yoke member 140 having a pair of spaced members 142 joined by an integral crosspiece 144 having a central opening to receive the lower end of the post 78. The members 142 receive the enlarged ends 121 of the cross-pieces 124, and the space therebetween receives the worm gear on shaft 123. The crosspiece 144 is formed with a lateral enlargement 147 having a hole 146 therethrough, as shown in FIG. 8 to receive a shaft 148 mounting a worm 150 meshing with the worm gear 125. The flexible shaft 93 is operatively connected to the top end of the shaft 148.

As best shown in FIGS. 2, 57, the universal joint connection 80 between the fan assembly 21 and the top of the post 78 includes a lateral extension 152 on each side of the top of the post 78, each extension terminating in an upwardly extending bearing member 154. A joint member 156 having a solid rectangular body with

stubshafts

160, 161 extending from the ends thereof, is interposed between the bearing members 154 with the

stub shafts

160, 161 journalled in the bearing members 154. The ends of the joint member 156 are formed with upstanding

perforated lugs

162, 162 to receive a shaft 164 having a worm 166 formed therefrom. A worm gear 168 with hub portion 170 is mounted on the protruding end of stub shaft 161. Worm gear 168 is in mesh with a worm 171 mounted on shaft 172 journalled in lugs 174 extending from one of the lateral extensions 152. Flexible shaft 104 is operative connected to one end of the shaft 172 for turning the worm 171. Central stem portions 176 of the joint member 156 are formed with holes 178 which are aligned with a hole on the depending joint member 180 fixed on a bottom end edge of the arms 24 centrally thereof. The bottom depending end of the joint member 180 is formed with a worm gear 182 in mesh with the worm 166. A pivot pin 184 extends through the aligned holes in the

joint members

156 and 180.

For example, in operation, by pushing a knob 87 a cable, such as cable 93, would be actuated for rotating the combined apparatus including the control casing 83, air pump 114 and pilot supporting plate. That is the cradle platform assembly 12 may be moved to either a horizontal position as shown in FIG. 1 for flying or to a vertical position as shown in FIG. 2 for walking. When in horizontal position, the pilot P may lie prone on the supporting plate with his hands in reach of the control board and steering Wheel 90 and by pushing the proper buttons can actuate the universal joint 82 for tilting the fan assembly 21 as desired, and can adjust the rudder elevators and the side flaps 66 for propulsion or rearward movement.

The supported seat 136 can be readily manipulated manually to swing the seat either horizontally for sitting thereupon as shown in FIG. 14, or vertically when not in use, as seen in FIG. 2.

Due to the Worm and gear arrangement, the fan assembly 21 will remain in any position set by the pilot. Positive drive is maintained of the fan blades 44 in all adjusted positions of the fan assembly. On take-off, the fan assembly 21 is adjusted so that the fan blades 44 are disposed horizontally. Lifting air streams are produced to lift the aircraft. Once in the air the fan assembly 21 is tilted so that the blades are arranged vertically or at an angle to the horizontal. In order to obtain reverse movement of the aircraft, the blades are rotated rearwardly to a reverse position. Turning of the aircraft in horizontal flight is normally effected by the pilots control of the rudder and elevator in a conventional manner. The flaps 66 are provided for use in braking the aircraft.

The modification of the invention shown in FIGS. 12 and 13 differs from the form of FIG. 1 in that the band 22 is formed with a pair of closely spaced outlet ducts communicating with the interior of the band by openings 192. In this form also, the elevator 50' and stabilizers 54' are mounted on an L-shaped bracket 194 fixed on the post 78' by means of a sleeve 196.

Another modification of the invention as shown in FIGS. 15, 16, and 17 provides for a twin-type of propelling means such as

fan assemblies

200 and 201 supporting a combined control housing, air pump and pilot supporting apparatus or cockpit assembly 204. Interposed therebetween is an upright post 208, pivotally connected at its top end as viewed in FIG. 16 to a central portion of the

fan assemblies

201 and 200 by universal joint structure 210, and swingably connected at its bottom end to the pilot assembly 204, as more clearly described in the first embodiment of this invention.

A control assembly 212 with a steering wheel 213 having the knobs as hereinbefore described in the first embodiment actuate reversible motors not shown for driving the various steering controls and

fan assemblies

200 and 201.

Propeller fans

214, 215 are rotatably mounted on

shafts

216 and 217 respectively. Each

fan

214, 215 include three blades 218 mounted on the

shafts

216 and 217 for rotation.

As in the first embodiment a pair of horizontally disposed

elevators

220 and 221 with rudder 222 are hingedly secured to a body portion 224 of the aircraft.

As best shown in FIG. 16 an air pump or blower 225 connects an enlargement 226 in which is formed a central passage for communication with the interior of the

fan assemblies

200 and 201 for directing pressure gases to rotate

fans

214 and 215 for propulsion, through metal flexible hose 230.

The aircraft includes a pair of

skids

231 and 232 on which the aircraft may land.

In operation the aircraft of FIGS. to 17 is substantially the same as those of FIGS. 1 to 14 except that in this embodiment of FIGS. 15 to 17 is provided a mechanical means of landing rather than a pilots own two feet.

While I have illustrated and described the preferred embodiments of my invention, it is to be understood that I do not limit myself to the precise construction herein disclosed and that various changes and modifications may be made within the scope of the invention.

I claim:

1. A helicopter device comprising means for supporting a pilot, power means for providing downwardly extending vertical thrust to the device, universal means interposed between said power means and said means for supporting the pilot, and control means connected to said power means to displace the thrust from the vertical to a longitudinal or to a lateral direction relative to the device, said control means including flexure-gear means for selectively pivoting the power means from a vertical axis to a longtudinal axis or to a lateral axis of the device.

2. The structure of claim 1, wherein the means for supporting the pilot include flexure-gear operably controlled for positioning the pilot in either a prone or an upstanding position.

3. The structure of claim 1, wherein the control means include flexible shafts, and reversible motors operably rotating said flexible shafts and wherein said universal means include gearing means for positioning said power means for vertical, horizontal and lateral positions and said universal means including a worm and gear arrangement means for positioning the pilot in predetermined positions relative to the power means.

4. The structure of claim 1, wherein said power means includes a shaft, propeller fan rotatable on said shaft, annular band circumambient the periphery of said fan and in close proximity thereto, and air pump means directing air under pressure to said propeller fan for driving said propeller fan for use producing the thrust.

5. The structure of claim 4, wherein said propeller fan includes an annular vane means connecting the propeller fan at its outward radial edges adjacent said annular band for receiving compressed air from the air pump tangentially from said annular band and for rotating said propeller fan for producing the thrust.

6. The structure of claim 1, in which said universal means includes a post having an upper and a lower end interposed between said power means and said means for supporting the pilot, a universal yoke means positioned between said power means and the upper end of said post means for positioning said power means and a worm and gear means for positioning said pilot interposed between the lower end of said post and the means for supporting the pilot for positioning the pilot in any predetermined position.

References Cited UNITED STATES PATENTS 3,117,744 1/ 1964 Roman 244-4 FOREIGN PATENTS 673,964 4/1939 Germany. 556,837 2/ 7 Italy.

MILTON BUCHLER, Primary Examiner PAUL E. SAUBERER, Assistant Examiner US Cl. X.R. 244-17.ll