Rotary wing device

Claim 2

An open-ended rotary wing device adapted to be rotated about its longitudinal axis and to be propelled forwardly relative to the surrounding fluid with its longitudinal axis having a small upward pitch angle of attack relative to the forward flight direction in order to generate an upward lifting biasing force on said device, the biasing force acting substantially perpendicularly to the longitudinal axis and in the plane which includes both the longitudinal axis and the forward flight direction, said rotary wing device comprising: (a) a plurality of longitudinally extending, laterally spaced-apart wing segments disposed in a hollow, open-ended, substantially cylindrical configuration, said wing segments being mounted for rotation about the longitudinal axis of said device; (b) each said wing segment having a longitudinal dimension greater than its lateral dimension; (c) the center of mass of said rotary wing device being located along the forward 25% to 45% of the longitudinal axis of said device, said device being statically and dynamically balanced relative to the longitudinal axis of said device; and (d) said wing segment shape and orientation constituting aerodynamic means for automatically and gradually increasing the effective wing span of said wing segments as the forward speed of said device slows, thereby causing the center of lift of said device to move longitudinally forward of the center of mass, thereby causing the pitch angle of said device to increase, and thereby causing substantially constant speed auto-rotation of said device, all thereby generating a substantially constant lifting force on said wing segments to produce a substantially flat trajectory flight path for said device.

Claim 3

The device of claim 1 wherein said substantially cylindrical configuration is a truncated cone having sides which form an angle with the longitudinal axis of said device in the range of 0.25° to 5°.

Claim 4

The device of claim 1 wherein said wing segments have longitudinal axes which are substantially parallel to each other.

Claim 5

The device of claim 3 wherein the longitudinal axis of each said wing segment is substantially parallel to the longitudinal axis of said device.

Claim 6

The device of claim 3 wherein the longitudinal axis of each said wing segment forms an angle of less than 45° relative to the longitudinal axis of said device.

Claim 7

The device of claim 1 wherein each said wing segment has a width which gradually increases towards the front end of said substantially cylindrical configuration.

Claim 8

The device of claim 1 wherein each said wing segment has a thickness which gradually increases towards the front end of said substantially cylindrical configuration.

Claim 9

The device of claim 1 wherein at least one mounting ring is provided for rotatably mounting said wing segments, said mounting ring engaging and stabilizing all said wing segments.

Claim 10

The device of claim 1 wherein front and rear mounting rings are provided for rotatably mounting said wing segments, said front and rear mounting rings engaging and stabilizing the front tips and the rear tips, respectively, of said wing segments.

Claim 11

The device of claim 9 wherein each said mounting ring has streamlined edges.

Claim 12

The device of claim 9 wherein the side edges of said wing segments are streamlined to enhance rotational speed, and the front and rear edges of said front and rear mounting rings are streamlined to enhance forward speed.

Claim 13

The device of claim 9 wherein said front mounting ring has a greater mass than said rear mounting ring.

Claim 14

The device of claim 1 wherein said substantially cylindrical configuration has a diameter to longitudinal length ratio in the range of 1:5 to 5:1.

Claim 15

The device of claim 1 wherein said substantially cylindrical configuration has an outer diameter to inner diameter ratio in the range of 3.00:2.50 to 3.00:2.95.

Claim 16

The device of claim 1 wherein said substantially cylindrical configuration has an inner diameter in the range of 6.5 to 9.0 cm. to permit said device to be conveniently slipped onto a person's wrist or arm.

Claim 17

The device of claim 1 wherein said substantially cylindrical configuration has an outer diameter in the range of 6.7 to 9.2 cm. to permit said device to be comfortably gripped for throwing.

Claim 18

The device of claim 1 wherein said plurality of wing segments includes from 5 to 15 wing segments.

Claim 19

The device of claim 1 further including a vehicle upon which said device is mounted.

Claim 20

The device of claim 1 further including a stationary support upon which said device is movably mounted.

Claim 21

The device of claim 1 further including means for carrying a payload.

Claim 22

The device of claim 1 further including a harness for mounting said device on a payload.

Claim 23

The device of claim 1 further including a tether attached at one end thereof to said device.

Claim 24

An open-ended rotary wing device adapted to be rotated about its longitudinal axis and to be propelled forwardly relative to the surrounding fluid with its longitudinal axis having a small angle of attack relative to the forward flight direction in order to generate a biasing force on the device, the biasing force acting substantially perpendicularly to the longitudinal axis and in the plane which includes both the longitudinal axis and the forward flight direction, said rotary wing device comprising: (a) a plurality of longitudinally extending, laterally spaced-apart wing segments disposed in a hollow, open-ended, substantially cylindrical configuration, said wing segments being mounted for rotation about the longitudinal axis of said device; (b) each said wing segment having a longitudinal dimension greater than its laterial dimension, each said wing segment having rounded streamlined lateral side edges, and each said wing segment being symmetrical in lateral cross-section wherein one side of said wing segment is the mirror image of the other side of the said wing segment; (c) front and rear mounting rings provided on said device for rotatably mounting said wing segments, said front and rear mounting rings engaging and stabilizing the front tips and the rear tips, respectively, of said wing segments, said front mounting ring having a greater mass than said rear mounting ring; and (d) the center of mass of said rotary wing device being located on the longitudinal axis of said device, said device being statically and dynamically balanced relative to the longitudinal axis of said device.

Claim 25

An open-ended rotary wing device adapted to be rotated about its longitudinal axis and to be propelled forwardly relative to the surrounding fluid with its longitudinal axis having a small angle of attack relative to the forward flight direction in order to generate a biasing force on the device, the biasing force acting substantially perpendicularly to the longitudinal axis and in the plane which includes both the longitudinal axis and the forward flight direction, said rotary wing device comprising: (a) a plurality of longitudinally extending, laterally spaced-apart wing segments disposed in a hollow, open-ended, substantially cylindrical configuration, said wing segments being mounted for rotation about the longitudinal axis of said device; (b) each said wing segment having a longitudinal dimension greater than its laterial dimension, each said wing segment having rounded streamlined lateral side edges, and each said wing segment being symmetrical in lateral cross-section wherein one side of said wing segment is the mirror image of the other side of the said wing segment; (c) front and rear mounting rings provided on said device for rotatably mounting said wing segments, said front and rear mounting rings engaging and stabilizing the front tips and the rear tips, respectively, of said wing segments, said front mounting ring having a greater mass than said rear mounting ring; and (d) the center of mass of said rotary wing device being located on the longitudinal axis of said device, said device being statically and dynamically balanced relative to the longitudinal axis of said device.

Claim 26

The device of claim 23 or claim 1 further having means for rotating said device about its longitudinal axis.

Claim 27

The device of claim 24 wherein said rotating means is mechanically powered.

Claim 28

The device of claim 24 wherein said rotating means is electrically powered.

Claim 29

The device of claim 24 wherein said rotating means includes a propeller.

Claim 30

The device of claim 24 further having means for propelling said device forwardly relative to the surrounding fluid.

Claim 31

The device of claim 28 wherein said propelling means is mechanically powered.

Claim 32

The device of claim 28 wherein said propelling means is electrically powered.

Claim 33

The device of claim 28 wherein said propelling means includes a propeller.

Claim 34

The device of claim 23 wherein the center of mass of said rotary wing device is located along the forward 25% to 45% of the longitudinal axis of said device.

Claim 35

An open-ended rotary wing device adapted to be rotated about its longitudinal axis and to be propelled forwardly relative to the surrounding fluid with its longitudinal axis having a small upward pitch angle of attack relative to the forward flight direction in order to generate an upward lifting biasing force on said device, the biasing force acting substantially perpendicularly to the longitudinal axis and in the plane which includes both the longitudinal axis and the forward flight direction, said rotary wing device comprising: (a) a plurality of longitudinally extending, laterally spaced-apart wing segments disposed in a hollow, open-ended, substantially cylindrical configuration, said wing segments being mounted for rotation about the longitudinal axis of said device; (b) each said wing segment having a longitudinal dimension greater than its lateral dimension, each said wing segment having rounded streamlined lateral side edges, and each said wing segment being symmetrical in lateral cross-section wherein one side of said wing segment is the mirror image of the other side of said wing segment; (c) the center of mass of said rotary wing device being located along the forward 25% to 45% of the longitudinal axis of said device, said device being statically and dynamically balanced relative to the longitudinal axis of said device; and (d) said wing segment shape and orientation constituting aerodynamic means for automatically and gradually increasing the effective wing span of said wing segments as the forward speed of said device slows, thereby causing the center of lift of said device to move longitudinally forward of the center of mass, thereby causing the pitch angle of said device to increase, and thereby causing substantially constant speed auto-rotation of said device, all thereby generating a substantially constant lifting force on said wing segments to produce a substantially flat trajectory flight path for said device.

Claim 36

An open-ended rotary wing device adapted to be rotated about its longitudinal axis and to be propelled forwardly relative to the surrounding fluid with its longitudinal axis having a small upward pitch angle of attack relative to the forward flight direction in order to generate an upward lifting biasing force on said device, the biasing force acting substantially perpendicularly to the longitudinal axis and in the plane which includes both the longitudinal axis and the forward flight direction, said rotary wing device comprising: (a) a plurality of longitudinally extending, laterally spaced-apart wing segments disposed in a hollow, open-ended, substantially cylindrical configuration, said wing segments being mounted for rotation about the longitudinal axis of said device; (b) each said wing segment having a longitudinal dimension greater than its lateral dimension, each said wing segment having rounded streamlined lateral side edges, and each said wing segment being symmetrical in lateral cross-section wherein one side of said wing segment is the mirror image of the other side of said wing segment; (c) the center of mass of said rotary wing device being located along the forward 25% to 45% of the longitudinal axis of said device, said device being statically and dynamically balanced relative to the longitudinal axis of said device; and (d) said wing segment shape and orientation constituting aerodynamic means for automatically and gradually increasing the effective wing span of said wing segments as the forward speed of said device slows, thereby causing the center of lift of said device to move longitudinally forward of the center of mass, thereby causing the pitch angle of said device to increase, and thereby causing substantially constant speed auto-rotation of said device, all thereby generating a substantially constant lifting force on said wing segments to produce a substantially flat trajectory flight path for said device.