# US 10,864,987 B2 · Counter rotating torque drive for rotary wing vehicle propulsion

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- Number: US 10,864,987 B2
- Document ID: US10864987B2
- Status: Granted
- Kind: B2
- Application number: 15/724,526
- Filed: 2017-10-04
- Published: 2019-04-04
- Granted: 2020-12-15
- Earliest claimed: 2017-10-04
- Assignees: The Aerospace Corporation
- Applicants: The Aerospace Corporation
- Inventors: Evan Robert Ulrich; Robert Edward Oberto
- Web page: https://patentgrep.com/patent/US10864987B2

## CPC

- B64C 27/82: characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64U 30/20: Rotors; Rotor supports
- B64U 50/19: using electrically powered motors
- B64C 27/78: in association with pitch adjustment of blades of anti-torque rotor
- B64C 2027/8272: {comprising fins, or movable rudders}
- B64U 2101/30: for imaging, photography or videography
- B64C: AEROPLANES; HELICOPTERS
- B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR

## Abstract

An aircraft that includes torque rotor and a lifting rotor, and generates torque from the torque rotor. The torque rotor may optimize drag production while the lifting rotor may optimize lift production limiting compromise between drag and lift production rotor.

## Claims

### Claim 1

An apparatus for generating torque, comprising:
a motor coupling a lifting rotor and a torque rotor, and configured to spin the lifting rotor in a first direction to generate lift for the apparatus and spin the torque rotor in a second direction generate drag-torque for the apparatus, wherein
the spinning of the torque rotor in the second direction is opposite to that of the spinning of the lifting rotor in the first direction, and
the torque rotor and the lifting rotor are decoupled from one another.

### Claim 2 (depends on 1)

The apparatus of claim 1, wherein a rotation rate of the lifting rotor is different than a rotation rate of the torque rotor due to drag generated by the spinning of the torque rotor.

### Claim 3 (depends on 2)

The apparatus of claim 2, wherein a moment of inertia for the lifting rotor is different from a moment of inertia for the torque rotor.

### Claim 4 (depends on 1)

The apparatus of claim 1, wherein the torque rotor is located above or below, the lifting rotor.

### Claim 5 (depends on 1)

The apparatus of claim 1, wherein the torque rotor has a parallel spin axis to that of, and is co-aligned or offset from, the lifting rotor.

### Claim 6 (depends on 1)

The apparatus of claim 1, wherein the motor is configured to temporarily de-spin the torque rotor, allowing the apparatus to land or hover.

### Claim 7 (depends on 1)

The apparatus of claim 1, wherein the lifting rotor has more mass and a higher moment of inertia than that of the torque rotor, allowing the apparatus to maintain flight without input from the torque rotor.

### Claim 8 (depends on 1)

The apparatus of claim 1, wherein the lifting rotor is configured to store kinetic energy from the torque rotor, allowing the apparatus to maintain flight when the torque rotor is temporarily de-spun or is stopped.

### Claim 9 (depends on 1)

The apparatus of claim 1, wherein the spin rate of the torque rotor is dependent both upon a length of moment arm of the torque rotor measured from a center axis of rotation of the apparatus and the drag produced by the torque rotor.

### Claim 10 (depends on 1)

The apparatus of claim 1, further comprising:
a plurality of variable pitch blades configured to rotate an angle of attack, providing lift as well as drag, wherein
each of the plurality of variable pitch blades are rotated to the angle of attack of up to 90 degrees or rotated to a lower angle of attack.

### Claim 11

An aircraft, comprising:
one or more motors coupling one or more lifting rotors and one or more torque rotors, and configured to spin the one or more lifting rotors in a first direction to generate lift for the aircraft and spin the one or more torque rotors in a second direction to generate drag-torque for the aircraft, wherein
the one or more motors decouples the one or more torque rotors and the one or more lifting rotors from one another by reducing or eliminating the driving torque allowing the one or more torque rotors to be de-spun.

### Claim 12 (depends on 11)

The aircraft of claim 11, wherein a rotation rate of the one or more lifting rotor to be different than of a rotation rate of the one or more torque rotors due to drag generated by the spinning of the one or more torque rotors.

### Claim 13 (depends on 12)

The aircraft of claim 12, wherein a moment of inertia for the one or more lifting rotor is different from a moment of inertia for the one or more torque rotors.

### Claim 14 (depends on 11)

The aircraft of claim 11, wherein the one or more torque rotors are located above, below, or above and below the one or more lifting rotor.

### Claim 15 (depends on 11)

The aircraft of claim 11, wherein the one or more torque rotors and the one or more lifting rotor are decoupled from one another.

### Claim 16 (depends on 11)

The aircraft of claim 11, wherein the one or more torque rotors have a parallel spin axis to that of, and are co-aligned or offset from, the one or more lifting rotor.

### Claim 17 (depends on 11)

The aircraft of claim 11, wherein, when the one or more motors temporarily de-spins the one or more torque rotors, the aircraft can land or hover.

### Claim 18 (depends on 11)

The aircraft of claim 11, wherein the one or more lifting rotor has more mass and a higher moment of inertia than that of the one or more torque rotors, allowing the aircraft maintain flight without input from the one or more torque rotors.

### Claim 19 (depends on 11)

The aircraft of claim 11, wherein the one or more lifting rotor is configured to store kinetic energy from the one or more torque rotors, allowing the aircraft to maintain flight when the one or more torque rotors are temporarily de-spun or is stopped.

### Claim 20 (depends on 11)

The aircraft of claim 11, wherein the spinning of the one or more torque rotors are dependent upon a length of moment arm of the one or more torque rotors measured from a center axis of rotation of the aircraft.

### Claim 21 (depends on 11)

The aircraft of claim 11, wherein the one or more torque rotors comprise
one or more counter-spun paddles mounted at the center of gravity of the one or more lifting rotor or located away from the center of gravity.

### Claim 22 (depends on 11)

The apparatus of claim 11, further comprising:
a plurality of variable pitch blades configured to rotate an angle of attack, providing lift as well as drag, wherein
each of the plurality of variable pitch blades are rotated to the angle of attack of up to 90 degrees or rotated to a lower angle of attack.