Combined launch and mission vehicles

• US 9,758,247 B2
• Filed: 04/13/2015
• Issued: 09/12/2017
• Est. Priority Date: 06/10/2014
• Status: Expired due to Fees

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Alber, Mark R.
• Primary Examiner(s): O'Hara, Brian M
• Assistant Examiner(s): Woldemaryam, Assres H
• Application Number:
  US14/685,054
• Publication Number:
  US 20150353197A1
• Time in Patent Office: 883 Days
• CPC Class Codes: B64C 29/0008 having its flight directional axis horizontal when grounded
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64D 5/00 Aircraft transported by aircraft, e.g. for release or reberthing during flight flying units formed by separate aircraft B64C37/02
• CPC Class Codes: B64U 70/20 for releasing or capturing UAVs in flight by another aircraft

Abstract

An aircraft is provided and includes a mission vehicle configured to follow vertical take-off and landing (VTOL) operations and to execute forward flight, hover/loiter and landing operations and a launch vehicle configured to drive the mission vehicle through at least vertical take-off (VTO) operations. The launch vehicle is umbilically coupled to the mission vehicle during the VTO operations and releasable from the mission vehicle thereafter.

Claims

1. An aircraft, comprising:

a mission vehicle configured to follow vertical take-off and landing (VTOL) operations and to execute forward flight, hover/loiter and landing operations; and

a launch vehicle configured to drive the mission vehicle through at least vertical take-off (VTO) operations, the launch vehicle including;

a fuselage including an engine nacelle along the fuselage, and

alighting elements coupled to the fuselage proximate to the engine nacelle and configured to support the launch vehicle in a vertical orientation during ground operations,

the launch vehicle and the mission vehicle are umbilically coupled, in the vertical orientation prior to VTO operation and during the VTO operations; and

the launch vehicle is releasable from the mission vehicle thereafter,

wherein the launch vehicle at least partially drives rotations of rotors of the mission vehicle during at least the VTO operations.

2. The aircraft according to claim 1, wherein the aircraft is configured to perform unmanned operations.

3. The aircraft according to claim 1, wherein the launch vehicle is sized for the driving of the mission vehicle.

4. The aircraft according to claim 1, wherein the launch vehicle is configured to execute return flight operations following release.

5. The aircraft according to claim 1, wherein the mission vehicle comprises:

a fuselage;

wings extending outwardly from opposite sides of the fuselage, the wings respectively including first and second engine nacelles;

first and second rotors drivable by drive sections of the first and second engine nacelles, respectively, to thereby drive the mission vehicle during at least the forward flight, hover/loiter and landing operations; and

alighting elements coupled to each of the wings proximate to the engine nacelles and configured to support the mission vehicle during grounded operations.

6. The aircraft according to claim 1, wherein the launch vehicle further comprises:

a rotor drivable by a drive section of the engine nacelle to thereby drive the mission and launch vehicles during at least the VTO operations.

7. The aircraft according to claim 1, further comprising an umbilical by which the mission and launch vehicles are connectable, the umbilical comprising structural elements, a power coupling, a data coupling and release mechanisms.

8. The aircraft according to claim 1, further comprising a flight computer housed in one or both of the mission and launch vehicles,

the flight computer being configured to control the driving of the mission vehicle by the launch vehicle and to control launch vehicle release.

14. The aircraft of claim 1, wherein a longitudinal axis of the launch vehicle is in the vertical orientation during VTO operations.

9. A launch vehicle for use with a mission vehicle of a vertical take-off and landing (VTOL) aircraft, the launch vehicle comprising:

a fuselage including an engine nacelle;

a rotor drivable by the engine nacelle to thereby drive the mission and launch vehicles during at least vertical take-off (VTO) operations; and

alighting elements coupled to the fuselage proximate to the engine nacelle and configured to support the launch vehicle in a vertical orientation during ground operations,

the fuselage and the mission vehicle are umbilically coupled in the vertical orientation prior to VTO operation and during the VTO operations; and

the fuselage is releasable from the mission vehicle thereafter,

wherein a drive section of the engine nacelle of the launch vehicle at least partially drives rotations of mission vehicle rotors during at least the VTO operations.

10. The launch vehicle according to claim 9, wherein the mission vehicle is configured to perform unmanned operations.

11. The launch vehicle according to claim 9, wherein the launch vehicle is sized for the driving of the mission vehicle.

12. The launch vehicle according to claim 9, wherein the launch vehicle is configured to execute return flight operations following release.

13. The launch vehicle according to claim 9, further comprising an umbilical by which the mission and launch vehicles are connectable, the umbilical comprising structural elements, a power coupling, a data coupling and release mechanisms.