Airship powered aerospace vehicle

Abstract

The present invention relates to an aerospace vehicle comprising an airplane or spacecraft, operatively coupled to an airship balloon containing lighter than air gas adapted to elevate the vehicle. A control system adapted to deflate the balloon upon reaching a predetermined altitude by directing the gas for powering the vehicle at greater speed. The balloon can be re-inflated for decreasing the speed of the vehicle upon reaching a destination and deflated in a controlled manner for landing the vehicle or disengaged from the vehicle upon transferring the gas from the balloon to a propulsion system of the vehicle.

Claims

1. An aerospace vehicle comprising: an airplane comprising a propulsion system; a balloon containing hydrogen configured to elevate the airplane; and a control system configured to: deflate the balloon upon reaching a predetermined altitude, by directing hydrogen into the propulsion system and at least one gas chamber, for powering the airplane; re-inflate the balloon using the hydrogen stored in the at least one gas chamber for decreasing the speed of the airplane; and deflate the balloon in a controlled manner for landing the airplane.

Description

BRIEF DESCRIPTION OF DRAWINGS

(1) FIG. 1A is a side view of an airplane with balloon inflated during takeoff, according to an embodiment of the invention.

(2) FIG. 1B is a side view of the airplane with balloon beginning to deflate upon reaching a predetermined altitude.

(3) FIG. 1C is a side view of the airplane with balloon completely deflated and retracted to achieve an aerodynamic shape.

(4) FIG. 1D is a side view of the airplane with balloon re-expanded upon reaching a destination.

(5) FIG. 1E is a side view of the airplane showing controlled deflation of the balloon during landing.

(6) FIG. 2A is a perspective view of a spacecraft with balloon inflated during takeoff, according to an embodiment of the invention.

(7) FIG. 2B is a perspective view of the spacecraft with balloon deflating and emptying the contents into a propulsion system.

(8) FIG. 2C is a perspective view of the spacecraft with the balloon completed deflated.

(9) FIG. 3 is a block diagram showing the airplane 110 and a control system 150, according to an exemplary embodiment of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

(10) The following detailed description of the preferred embodiments presents a description of certain specific embodiments to assist in understanding the claims. However, the present invention is intended to cover alternatives, modifications and equivalents, which may be included within the spirit and scope of the invention as defined by the appended claims. Furthermore, in the following detailed description of the present invention, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be evident to one of ordinary skill in the art that the present invention may be practiced without these specific details.

(11) The present invention generally relates to an aerospace vehicle comprising an aircraft or a spacecraft powered by an airship. In one embodiment, an airplane is operatively coupled to a balloon structure containing lighter than air gas, which elevates or provides lift to the airplane from ground surface. Upon reaching a predetermined altitude, a control system within the airplane deflates the balloon and directs the gas to a propulsion system for powering the aircraft. Further, the control system retracts the balloon structure into the aircraft, thereby achieving a better aerodynamic shape for high speed flying. Upon reaching a destination point, the balloon is re-expanded for reducing the speed of the aircraft and further deflated in a controlled manner for landing.

(12) Referring to FIG. 1A-1E, which shows side view of an airplane coupled with a balloon, during different stages of flight. FIG. 1A shows the airplane 110 with the balloon 120 completely inflated with lighter than air gas during takeoff. The aerospace vehicle of the present invention acquires initial lift or elevation provided by lighter than air gas such as hydrogen or helium and doesn't require a runway or airstrip for takeoff or landing purposes. FIG. 1B shows the balloon 120 coupled to the airplane 110, beginning to deflate upon reaching a predetermined altitude.

(13) The gas from the balloon is directed to a propulsion system of the airplane for increasing the speed and the balloon structure is collapsed and retracted in order to achieve a better aerodynamic shape. FIG. 1C shows the airplane 110 with the balloon 120 completely deflated and retracted to achieve the aerodynamic shape. The shape of the airplane along with the propulsion powered by lighter than air gas enables high speed flight. In an embodiment, the propulsion system may comprise an engine, high pressure containers or gas chambers, adapted to power the airplane.

(14) FIG. 1D shows the airplane 110 with balloon 120 re-expanding upon reaching a destination point. In an embodiment, the balloon is re-inflated with lighter than air gas, in order to reduce the speed of the airplane. FIG. 1E shows controlled deflation of the balloon coupled to the airplane during landing. Controlled deflation allows floating or descend of the airplane towards a landing area, which can be relatively small and eliminates the need for vast and expensive runways for landing purposes. Airplane 110 with the balloon 120 can be completely deflated by the control system 150 by transferring the lighter than air gas to the propulsion system and/or to the gas chamber (storage unit) for future use.

(15) In another embodiment, the aerospace vehicle may comprise a spacecraft containing a propulsion system powered by the airship. The spacecraft is coupled to a balloon comprising lighter than air gas such as hydrogen or helium, adapted to lift the spacecraft to an altitude. Upon reaching a maximum altitude, the balloon is deflated by a control system present within the spacecraft and the gas from the balloon is directed towards the propulsion system of the space craft for further powering the space craft to a greater altitude.

(16) FIG. 2A shows the spacecraft 110 comprising a propulsion system 130 and high pressure chambers or gas tanks 140 and a control system 150. The spacecraft 110 is coupled to the balloon 120 inflated with a lighter than air gas 122. During takeoff, the spacecraft overcomes the highest force of gravity due to the fact that the spacecraft fuel is lighter than air. FIG. 2B shows a-perspective view of the spacecraft 110 with the balloon 120 and the control system 150 for deflating and emptying the contents (lighter than air gas or gases) 122 into the propulsion system 130 and/or to the high pressure chambers 140 for future use as a fuel for further ascending the spacecraft to a greater altitude. The transfer of gas from the 120 balloon to the propulsion system 130 and storage unit 140 is indicated by dotted arrow lines.

(17) FIG. 2C shows a perspective view of the spacecraft 110 with the balloon 120 completely deflated by the control system 150 by transferring the contents (gas) 122 to the propulsion system 130 and/or to the storage unit 140 for future use. In an embodiment, the propulsion system 130 may comprise an engine, adapted to power the spacecraft 110 towards further altitude by utilizing the gas from the storage unit 140 as a fuel source.

(18) The aerospace vehicle comprising manned or unmanned aircraft or a spacecraft coupled with an airship powered by lighter than air gas provides numerous advantages including eliminating the need for runway for takeoff or landing for aircrafts and eliminating the need for expensive launch base for space crafts. Another advantage includes elimination of fuel that may contain potentially hazardous pollutants which contaminates the environmental air and otherwise lead to dumping of toxins in fields or residential areas surrounding airports.

(19) In an embodiment, the balloon 120 coupled to the aerospace vehicle, acts as an emergency floatation tool. For example, the gas 122 within the storage unit comprising high pressure gas chambers or gas tanks 140 can be used by the control system 150 for re-inflating the balloon 120 during emergency landing and the inflated balloon enables the spacecraft 110 to remain afloat in the air or to float on a waterbody. In another example, the collapsed or deflated balloon 120 can be re-inflated using the gas 122 stored in the storage unit 140 in the event of failure of the spacecraft engines or propulsion system 130.

(20) The present invention has been described with a preferred embodiment thereof and it is understood that many changes and modifications to the described embodiment can be carried out without departing from the scope and the spirit of the invention that is intended to be limited only by the appended claims.