Helicopter target

Claim 2

A wheel less, hand launchable remote controlled autogyro having a fuselage section simulating the fuselage of a helicopter with stub, lift-providing, wings.

Claim 3

An autogyro as recited in claim 1 wherein said autogyro has a single, only aerodynamically controlled, fixed angle shaft rotor assembly.

Claim 4

An autogyro as recited in claim 2 wherein said rotor shaft comprises a bolt with a flat head part and a screw-threaded part remote from said head; and wherein said rotor assembly further comprises a relatively rigid piece of sheet material; means for mounting said shaft to said sheet material with said flat head portion abutting a face of said sheet material and with said screw-threaded portion upstanding above said sheet material.

Claim 5

An autogyro as recited in claim 1 further comprising a rotatable shaft; and manual launch means including a first gear mounted to said shaft for rotation therewith; a second gear; means for mounting the second gear in said fuselage for movement from a first position in which it is spaced from said first gear to a second position in which it engages said first gear to effect rotation thereof; and means for providing access to said second gear from the exterior of said fuselage in order to effect rotation of said first gear.

Claim 6

A remote controlled flying target simulating a helicopter with stub wings, and comprising the elements: a fuselage section simulating a helicopter and having fore and aft portions; a single rotor; a remote controlled engine for powering the target through the air, and mounted on said fuselage section; a horizontal stabilizer with elevators; a pair of wings each having an air foil, attached to said fuselage section and extending outwardly therefrom; said rotor including a rotor shaft upstanding from the fuselage and attached to a rotor head; said rotor shaft tilted aft an angle between about 5°-10°; said rotor head including air foil blades having a negative pitch angle between about 3°-9°; and remote control elevator, and roll and yaw structures; said elements constructed so that the target is capable of flight simulating combat maneuvering of a helicopter, and for use as a expendable target.

Claim 7

A remote controlled flying target simulating a helicopter with stub wings, and comprising the elements: a fuselage section simulating a helicopter and having fore and aft portions; a single rotor; a remote controlled engine for powering the target through the air, and mounted on said fuselage section; a horizontal stabilizer with elevators; a pair of wings each having an air foil, attached to said fuselage section and extending outwardly therefrom; said rotor including a rotor shaft upstanding from the fuselage and attached to a rotor head; said rotor shaft tilted aft an angle between about 5°-10°; said rotor head including air foil blades having a negative pitch angle between about 3°-9°; and remote control elevator, and roll and yaw structures; said elements constructed so that the target is capable of flight simulating combat maneuvering of a helicopter, and for use as a expendable target.

Claim 8

A target as recited in claim 5 wherein said engine is mounted at the front of said fuselage section, and makes a downthrust angle, with respect to a horizontal line of movement of the target, of between about 5°-12°.

Claim 9

A target as recited in claim 6 wherein said horizontal stabilizer is disposed at an angle, with respect to the horizontal line of movement of the target, of between about 3°-10°, sloping downwardly aft.

Claim 10

A target as recited in claim 7 wherein said wings have ailerons; and further comprising a tail at the aft-most portion of said fuselage, said tail having a rudder; and wherein said rudder and ailerons comprise said roll and yaw structures.

Claim 11

A target as recited in claim 8 wherein said ailerons and rudder are operatively linked together to cooperate to provide effective right or left roll and yaw control.

Claim 12

A target as recited in claim 8 wherein the span of said wings is between about 50-60 percent the length of said fuselage, so that said wings provide sufficient lift but do not significantly detract from the overall helicopter simulation the target presents.

Claim 13

A target as recited in claim 10 wherein the conning angle of said rotor blades is between about 3°-9°.

Claim 14

A target as recited in claim 11 wherein said rotor shaft angle is about 6°, and wherein said conning angle is about 7°, and wherein said downthrust angle of said engine is about 10°, and wherein said negative pitch angle of said rotor blades is about 5°, and wherein said angle of said horizontal stabilizer is about 4°.

Claim 15

A target as recited in claim 8 wherein said rotor is disposed horizontally along the fuselage at approximately the center of lift of the wings.

Claim 16

A target as recited in claim 7 wherein the conning angle of said rotor blades is between about 3°-9°.

Claim 17

A target as recited in claim 14 wherein said rotor shaft angle is about 6°, and wherein said conning angle is about 7°, and wherein said down thrust angle of said engine is about 10°, and wherein said negative pitch angle of said rotor blades is about 5°, and wherein said angle of said horizontal stabilizer is about 4°.

Claim 18

A target as recited in claim 5 wherein the dispositions of said rotor shaft and said rotor head are such that said rotor is only aerodynamically controlled.

Claim 19

A remote controlled autogyro flying target simulating a helicopter with stub wings, comprising: a fuselage section simulating a helicopter, and having fore and aft portion; a single rotor; a remote controlled engine for powering the target through the air, mounted at the fore portion of said fuselage; a horizontal stabilizer, said horizontal stabilizer making an angle, with respect to a line of horizontal movement of the target, of between about 3°-10°, sloping downwardly aft; a pair of wings connected to said fuselage section extending outwardly therefrom, each wing having an air foil; said rotor including a rotor shaft upstanding from the fuselage and attached to a rotor head; said rotor shaft tilted aft a fixed angle of between about 5°-10°; said engine making a downthrust angle, with respect to a line of horizontal movement of the target, of between about 5°-12°; said rotor head including air foil blades having a negative pitch angle between about 3°-9°; and said target constructed so that it is capable of flight simulating combat flight of a helicopter, and use as an expendable target.

Claim 20

A remote controlled autogyro flying target simulating a helicopter with stub wings, comprising: a fuselage section simulating a helicopter, and having fore and aft portion; a single rotor; a remote controlled engine for powering the target through the air, mounted at the fore portion of said fuselage; a horizontal stabilizer, said horizontal stabilizer making an angle, with respect to a line of horizontal movement of the target, of between about 3°-10°, sloping downwardly aft; a pair of wings connected to said fuselage section extending outwardly therefrom, each wing having an air foil; said rotor including a rotor shaft upstanding from the fuselage and attached to a rotor head; said rotor shaft tilted aft a fixed angle of between about 5°-10°; said engine making a downthrust angle, with respect to a line of horizontal movement of the target, of between about 5°-12°; said rotor head including air foil blades having a negative pitch angle between about 3°-9°; and said target constructed so that it is capable of flight simulating combat flight of a helicopter, and use as an expendable target.

Claim 21

A target as recited in claim 17 wherein said rotor is disposed horizontally along the fuselage at approximately the center of lift of the wings.

Claim 22

A target as recited in claim 18 wherein the span of said wings is between about 50-60 percent the length of said fuselage, so that said wings provide sufficient lift but do not significantly detract from the overall helicopter simulation the target presents.

Claim 23

A target as recited in claim 17 wherein the conning angle of said rotor blades is between about 3°-9°.