# US 9,751,619 B1 · Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations

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- Number: US 9,751,619 B1
- Document ID: US9751619B1
- Status: Granted
- Kind: B1
- Application number: 15/377,300
- Filed: 2016-12-13
- Granted: 2017-09-05
- Earliest claimed: 2014-10-03
- Applicants: John V. Howard
- Inventors: John V. Howard
- Web page: https://patentgrep.com/patent/US9751619B1

## CPC

- B64C 27/12: Rotor drives
- B64C 25/02: Undercarriages
- B64C 25/04: Arrangement or disposition on aircraft
- B64C 27/04: Helicopters
- B64D 1/22: Taking-up articles from earth's surface
- B64U 10/17: Helicopters (flying platforms B64U10/13)
- B64U 30/24: Coaxial rotors
- B64U 60/50: with landing legs
- B64C 2025/325: {specially adapted for helicopters}
- B64C 2211/00: Modular constructions of airplanes or helicopters
- B64U 50/12: using turbine engines, e.g. turbojets or turbofans
- B64U 2101/67: the UAVs comprising tethers for lowering the goods
- Y02T 50/10: Drag reduction
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

An unmanned rotorcraft has a lift module having a propulsion system and coaxial rotors driven in rotation by the propulsion system. The rotorcraft includes a payload support system adapted to couple an external payload directly to the lift module. The rotorcraft is devoid of provisions for human passengers.

## Claims

### Claim 1

A system for supporting an aircraft when landed, comprising:
at least three separate support members assembled in a radial array about an axis, each support member comprising:
a central flange; and
a support structure extending from the central flange;
wherein the central flanges are separably assembled together and cooperate to form a generally cylindrical aircraft centerbody, the support structures cooperating to support the aircraft when landed.

### Claim 2 (depends on 1)

The system of claim 1, wherein the support structures are generally identical to each other.

### Claim 3 (depends on 1)

The system of claim 1, wherein the support structures are configured to minimize vertical aerodynamic drag, in that each support member has an airfoil-shaped cross-section vertically disposed to reduce vertical drag from rotor downwash.

### Claim 4 (depends on 1)

The system of claim 1, wherein the flange and support structure of each support member are formed together as one structure.

### Claim 5 (depends on 1)

The system of claim 1, wherein the support members are formed from a composite material.

### Claim 6 (depends on 1)

The system of claim 1, wherein each flange comprises:
an arcuate frame member, the frame members forming a central ring when the support members are assembled together.

### Claim 7 (depends on 1)

The system of claim 1, wherein each flange comprises:
upper and lower arcuate frame members, the upper frame members forming an upper central ring and the lower frame members forming a lower central ring when the support members are assembled together.

### Claim 8 (depends on 1)

The system of claim 1, further comprising:
an upper fairing structurally coupling upper portions of the central flanges together.

### Claim 9 (depends on 1)

The system of claim 1, further comprising:
a lower fairing structurally coupling lower portions of the central flanges together.

### Claim 10 (depends on 1)

The system of claim 1, wherein the support members are configured for ease of assembly and disassembly, in that each support member is configured, such that the root section thereof forms a sector of the cylindrical aircraft centerbody, each sector being releasably attached to adjacent sectors.