Solar balloon maneuvering system

• US 4,262,864 A
• Filed: 03/14/1979
• Issued: 04/21/1981
• Est. Priority Date: 12/15/1977
• Status: Expired due to Term

• Current Assignee: Fredrick Eshoo
• Original Assignee: Fredrick Eshoo
• Inventors: Eshoo, Fredrick
• Primary Examiner(s): Frankfort, Charles E.
• Application Number:
  US06/020,549
• Time in Patent Office: 769 Days
• Field of Search: 244/31, 244/33, 244/29, 244/30, 244/96, 244/97, 244/168, 244/171, 244/51, 126/425
• US Class Current: 244/31
• CPC Class Codes: B64B 1/58 Arrangements or construction of gas-bags; Filling arrangements
• CPC Class Codes: F24S 20/80 Airborne solar heat collector modules, e.g. inflatable structures
• CPC Class Codes: Y02E 10/47 Mountings or tracking

Abstract

A solar powered hot air balloon with a maneuvering system is disclosed. The balloon is formed of an envelope with an opaque portion and a transparent portion arranged so as to utilize solar heating to heat air within the envelope. The opaque portion of the envelope has a substantially black inner surface and a light reflecting outer surface with the black inner surface being positioned so as to receive a maximum amount of sunlight through the transparent portion for a given location of the sun. Ascent and descent maneuvering is accomplished by changing the rotational position of the balloon relative to the position of the sun so that more or less portions of the black inner surface receive sunlight to thus generate heating within the envelope. The maneuvering system includes a pair of propulsion units positioned on opposite sides of the balloon. In one embodiment, two light sensors may be provided which are connected to a control unit. The control unit either manually or automatically selectively activates the propulsion units depending upon the amount of light received by the respective sensor units. In another embodiment, a plurality of light sensors are spaced around the balloon at angular increments. Respective pairs of sensor elements are activated corresponding to desired angles of rotational position for the balloon so that the amount of sunlight received by the inner block surface can be varied so as to control ascent and descent.

Claims

1. A solar hot air balloon having a maneuvering system for ascent and descent, comprising:

(a) an envelope;

(b) a gondola suspended from the envelope;

(c) a highly translucent portion of the envelope;

(d) an opaque portion of the envelope, said opaque portion having a substantially light absorbing inner surface within the envelope positioned so as to receive a substantial portion of sunlight passing through the translucent portion;

(e) maneuvering system means for rotating the balloon about a vertical axis relative to level flight for controlling the amount of sunlight received by said light absorbing inner surface and for controlling ascent and descent;

(f) said maneuvering system means comprising a first propulsion means disposed on a side of the envelope; and

(g) said maneuvering system means including at least four light sensors positioned in spaced relationship around the balloon and circuitry means for simultaneously activating only two of said light sensors for automatically maintaining the balloon at a rotational position associated with the activated light sensors, said two sensors being positioned on opposite sides of the envelope.

2. The balloon of claim 1 wherein the at least four sensors are positioned substantially along an equator of the balloon and at least one of the sensors is positioned on the translucent portion of the envelope.

3. A solar hot air balloon having a maneuvering system for ascent and descent, comprising:

(a) an envelope;

(b) a gondola suspended from the envelope;

(c) a highly translucent portion of the envelope;

(d) an opaque portion of the envelope, said opaque portion having a substantially light absorbing inner surface within the envelope positioned so as to receive a substantial portion of sunlight passing through the translucent portion;

(e) maneuvering system means for rotating the balloon about a vertical axis relative to level flight for controlling the amount of sunlight received by said light absorbing inner surface and for controlling ascent and descent;

(f) said maneuvering system means comprising a first propulsion means disposed on a side of the envelope; and

(g) said maneuvering system means including a first light sensor positioned on the opaque portion of the envelope and adjacent a junction of the opaque and translucent portions, a second light sensor positioned on the opaque portion opposite the first sensor on the opposite side of the envelope, a third light sensor on the opaque portion, and a fourth light sensor opposite the third sensor on the translucent portion of the envelope.