High altitude reconnaissance platform

• US 4,697,761 A
• Filed: 09/16/1985
• Issued: 10/06/1987
• Est. Priority Date: 09/16/1985
• Status: Expired due to Fees

• Current Assignee: David E. Long
• Original Assignee: David E. Long
• Inventors: Long, David E.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Corl, Rodney
• Application Number:
  US06/776,425
• Time in Patent Office: 750 Days
• Field of Search: 244/62, 244/53 R, 244/13, 244/45 A, 244/DIG. 1.4, 244/45 R, 244/89, 244/58, 244/59
• US Class Current: 244/62
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64D 27/353 using solar cells
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A high altitude, ultra lightweight aircraft has broad area relatively flat wings, and is provided with solar cells on its upper wing surfaces, and long wavelength, infrared responsive cells on its lower wing and fuselage surfaces, to provide enough power to maintain the aircraft aloft at high altitudes indefinitely. The aircraft is intended to fly at altitudes of about 60,000 feet to 110,000 feet, at speeds in the vicinity of 70 to 200 miles per hour. A battery or fuel cell and electrical system is provided to store excess electrical power and to supply electrical power when needed. A large, low speed, pusher propellor is driven by an electrical motor. The aircraft may be launched with an opaque balloon, which not only raises the aircraft to the desired elevation but also conceals it.

Claims

1. A high altitude, ultralight aircraft requiring no fuel comprising:

an aircraft having wings with broad area upper and lower wing surfaces,

a low speed propellor mounted on said aircraft;

electric motor means mounted on said aircraft and coupled to drive said propellor;

solar cell means for receiving solar energy and supplying electricity to power said motor means, said solar cell means being mounted on the upper surfaces of said wings;

long wavelength infrared (LWIR) responsive cell means for receiving albedo infrared energy from the earth and for supplying electricity to power said motor means, said LWIR cell means being mounted on the lower surfaces of said wings; and

means for storing excess electrical energy supplied by said solar and LWIR cell means beyond that needed for powering said motor means, and for supplying supplemental electrical power to said motor means when the power supplied from said cell means is inadequate;

whereby the aircraft may have a life at elevated altitudes of several years.

2. A high altitude, ultralight aircraft as defined in claim 1 further comprising opaque balloon means for raising said aircraft to the desired altitude, with the aircraft mounted within the balloon means.

3. A high altitude, ultralight aircraft as defined in claim 1 including front and rear wings, and means for deflecting at least one of said wings for controlling the flight of said aircraft.

4. A high altitude, ultralight aircraft as defined in claim 1 wherein said propellor is a low speed, large area propellor and said electric motor means powers said propellor solely from said solar cell means, said LWIR cell means and said storage means, to continuously drive said aircraft at a velocity of between 60 miles per hour and 200 miles per hour.

5. A high altitude, ultralight aircraft as defined in claim 1 wherein said aircraft has two wings having an effective upper surface area of at least 2400 square feet, and a substantially equal lower surface area.

6. A high altitude, ultralight aircraft as defined in claim 1 wherein said aircraft includes a fuselage, and wherein LWIR cell means are mounted on the bottom of said fuselage.

7. A high altitude, ultralight aircraft as defined in claim 6 wherein the bottom of said fuselage is substantially flat.

8. A high altitude, ultralight aircraft as defined in claim 1 further including means for transmitting signals from said aircraft, and means for receiving signals at said aircraft.

9. A high altitude, ultralight aircraft requiring no fuel comprising:

an aircraft having wings with broad area upper and lower wing surfaces;

solar cell means for receiving solar energy and producing electricity, said solar cell means being mounted on the upper surfaces of said wings;

long wavelength infrared (LWIR) responsive cell means for receiving albedo infrared energy from the earth and for producing electricity, said LWIR cell means being mounted on the lower surfaces of said wings;

means for the storage of excess electrical energy supplied by said solar and said LWIR cell means;

means for powering said aircraft to keep said aircraft aloft solely from the electricity from said solar cell means and said LWIR cell means, including means for supplementing the electrical power from said LWIR cells with power from said storage means at night, when no power is being generated by said solar cells; and

opaque balloon means for raising said aircraft to the desired altitude with the aircraft within said balloon means;

whereby the aircraft may remain aloft at elevated altitudes, day and night for extended periods of time.

10. A high altitude, ultralight aircraft as defined in claim 9 including front and rear wings, and means for deflecting at least one of said wings for controlling the flight of said aircraft.

11. A high altitude, ultralight aircraft as defined in claim 9 wherein said aircraft has two wings having an effective upper surface area of at least 2400 square feet, and a substantially equal lower surface area.

12. A high altitude, ultralight aircraft as defined in claim 9 wherein said aircraft includes a fuselage, and wherein LWIR cell means are mounted on the bottom of said fuselage.

13. A high altitude, ultralight aircraft as defined in claim 12 wherein the bottom of said fuselage is substantially flat.

14. A high altitude, ultralight aircraft as defined in claim 9 further including means for transmitting signals from said aircraft, and means for receiving signals at said aircraft.

15. A high altitude, ultralight aircraft as defined in claim 9 including a large, low speed, pusher propellor, and electric motor means for powering said propellor.

16. A high altitude, ultralight aircraft as defined in claim 9 further including power control means for receiving electricity from said solar cell means and said LWIR cells, for coupling electricity to and from said storage means, and for directing electricity to said aircraft powering means and to other systems on said aircraft.

17. A high altitude, ultralight aircraft requiring no fuel comprising:

an aircraft having wings with broad area upper and lower wing surfaces, and including both a rear wing and a front wing, said aircraft including a fuselage having a substantially flat lower surface;

means for deflecting at least one of said wings for controlling the flight of said aircraft;

low speed propellor means mounted for powering said aircraft;

electric motor means mounted on said aircraft and coupled to drive said propellor means;

solar cell means for receiving solar energy and supplying electricity to power said motor means, said solar cell means being mounted on the upper surfaces of said wings;

long wavelength infrared (LWIR) responsive cell means for receiving albedo infrared energy from the earth and for supplying electricity to power said motor means, said LWIR cell means being mounted on the lower surfaces of said wings and on the flat lower surface of said fuselage; and

means for storing excess electrical energy supplied by said cell means beyond that needed for powering said motor means, and for supplying supplemental electrical power to said motor means when the power supplied from said cell means is inadequate;

whereby the aircraft may have a life at elevated altitudes of several years.