Description:DETAILED DESCRIPTION

Before the present apparatus and its components are described, it is to be understood that this disclosure is not limited to the particular apparatus and its arrangement as described, as there can be multiple possible embodiments that are not expressly illustrated in the present disclosure. It is also to be understood that the terminology used in the description is for the purpose of describing the particular versions or embodiments only and is not intended to limit the scope of the present application. This summary is not intended to identify essential features of the claimed subject matter nor is it intended for use in detecting or limiting the scope of the claimed subject matter.

The present disclosure relates to a field of an air vehicle. Further, the air vehicle may be configured to operate on hydrogen-based fuel cells or batteries or bath hydrogen-based fuel cells and batteries, as well as configured with safety measures for the air vehicle, such as parachutes and airbags, which may be deployed during partial failure/complete failure of the air vehicle. Further, the air vehicle may include plurality of passenger seats or an open space for carrying the cargo.

FIG.1 illustrates a perspective view 100 of an air vehicle, as an illustrative configuration of the present disclosure. FIG.2 illustrates a top view 200 of the air vehicle, as an illustrative configuration of the present disclosure. FIG.3 illustrates a front view 300 of the air vehicle, as an illustrative configuration of the present disclosure, and FIG.4 illustrates a side view 400 of the air vehicle, as an illustrative configuration of the present disclosure.
In one configuration, and in continued reference to FIG.1, the air vehicle may include a front section 102, a fuselage 104, and a rear section 106. The fuselage 104 may be defined between the front section 102 and the rear section 106, essentially as a central body of the air vehicle. As defined conventionally, the fuselage 104 may be configured to store a payload of the air vehicle. The fuselage 104 may include an upper external portion, and a lower external portion oppositely disposed to the upper external portion. The front section 102 may include a nose, and the rear section 106 may include a tail. The rear section 106 may be oppositely disposed to the front section 102. As illustrated by Fig.1, the front section 102 may be designed in an aerodynamic shape in order to attain better efficiency and flight stability of the air vehicle. In the same configuration, the fuselage 104 may be equipped with a left wing 108a, and a right wing 108b, when seen from the front view 300 of the air vehicle (refer to FIG.3).

In one illustrative configuration, and again referring to FIG.2, the air vehicle may include a first propeller assembly housing with landing skids 202a, and a second propeller assembly housing with landing skids 202b. In the same configuration, the first propeller assembly housing 202a may include a first set of propeller guards 208a, 208b, 208c, and 208d (hereinafter collectively referred to as the first set of propeller guards 208). The first set of propeller guards 208 may be assembled in the first propeller assembly housing with landing skids 202a. In the same configuration, the second propeller housing with landing skids 202b may include a second set of propeller guards 210a, 210b, 210c, and 210d (hereinafter collectively referred to as the second set of propeller guards 210). In one configuration, the first set of propeller guards 208 and the second set of propeller guards 210 are configured to provide thrust to the aircraft in a vertical direction, preferably during vertical take-off and landing of the aircraft.

In another illustrative configuration, with continued reference to FIG.2, the first propeller assembly housing 202a may be adjoined to the nose, preferably at a lower section of the nose. Similarly, the second propeller assembly housing 202b may be adjoined to the lower external surface of the fuselage 104.

In another illustrative configuration, with continued reference to FIG.2, the rear section 106 may include a tail having a set of vertical stabilizers. The set of vertical stabilizers may include a first vertical stabilizer 214a and a second vertical stabilizer 214b, positioned offset and parallel to each other. Between the first vertical stabilizer 214a and the second vertical stabilizer 214b, a horizontal stabilizer 212 may be positioned. The horizontal stabilizer may further comprises an elevator 216. The elevator 216 may be configured to provide movement with respect to a vertical axis of the aircraft.

In another illustrative configuration, the left wing 108a, and the right wing 108b may include a first aileron 206b and a second aileron 206a respectively. The first aileron 206b and the second aileron 206a may be configured to assist rolling of the aircraft, i.e., movement along a longitudinal axis of the aircraft.

In another illustrative configuration, the left wing 108a, and the right wing 108b may be adjoined to the upper external surface of the fuselage 104. Further, the right wing 108b may be disposed opposite to the left wing 108a. In the same configuration, the left wing 108a may include a first set of electric ducted fan housing 204b, and the right wing 108b may include a second set of electric ducted housing 204a. The first set of electric ducted housing 204b and the second set of electric ducted housing 204a may include first set of electric ducted fans 508a and second set of electric ducted fans 508b respectively (refer to FIG.5), and configured to provide thrust to the air vehicle in a horizontal direction.
In another illustrative configuration, and in reference to FIG.3, the first set of electric ducted fans housing 204b and the second set of electric ducted fans housing 204a may be adjoined to proximal ends of the left wing 108a, and the right wing 108b. Similarly, first aileron 206b and the second aileron 206a may be adjoined to the distal end of the left wing 108a, and the right wing 108b respectively.

In another configuration, and in reference to FIG.4, the first vertical stabilizer 214a and the second vertical stabilizer 214b may include a rudder 304. The rudder 304 may be provided to control movement with respect to the lateral axis of the aircraft. Further, in another configuration, the air vehicle may include a parachute housing 302 mounted on the upper external surface of the fuselage 104. The parachute housing 302 may be configured to include a parachute 702 (refer to FIG.7).

FIG.5 illustrates an internal perspective view 500 of the air vehicle, as an illustrative configuration of the present disclosure. FIG.6 illustrates another perspective view 600 of disassembled components of the air vehicle, as an illustrative configuration of the present disclosure.

As explained above and with continued reference to FIG.5, the internal perspective view 500 of the air vehicle is illustrated. The air vehicle may include a fuselage 104. On the fuselage 104, a first set of motor propellers 502a, 502b, 502c, and 502d (hereinafter collectively referred to as first set of motor propellers 502) may be mounted. Further, in a similar configuration, a second set of motor propellers 504a, 504b, 504c, and 504d (hereinafter collectively referred to as second set of motor propellers 504) may be mounted on the fuselage 104. In another configuration, the first set of electric ducted fans 508b and the second set of electric ducted fans 508a may be individually driven by a motor.

In another configuration, the power source (506) may include a plurality of hydrogen cells with batteries, which may be configured to power the motor, which may drive the first set of motor propeller 502, and the second set of motor propellers 504. In another configuration, the power source 506 may also include a set of electric batteries. The set of electric batteries may include a Lithium-ion polymer battery, nickel-cadmium battery, solid-state battery, and the like.

In another configuration, with continued reference to FIG.5 the left wing 108a and the right wing 108b may be configured to support at least four electric ducted fans 508b of the first set of electric ducted fans housing 204b, and at least four electric ducted fans 508a of the second set of electric ducted fans housing 204a. The assembly of the at least four electric ducted fans 508b with the first set of electric ducted fans housing 204b, may constitute a first electric duct fan assembly. Further, the assembly of the at least four electric ducted fans 508a of the second set of electric ducted fans housing 204a may constitute a second electric ducted fan assembly.

In one configuration, in reference to FIG.6, each of the propellers in the first set of motor propeller 502 may be positioned in the first set of propeller guards 208 respectively. Each of the propellers in the second set of motor propeller 504 may be positioned in the second set of propeller guards 210 respectively. In a similar configuration, each of the fans of at least four electric ducted fans 508b may be positioned in the first set of electric ducted fans housing 204b, and each of the fans of at least four electric ducted fans 508a may be positioned in the second set of electric ducted fans housing 204a. In another configuration, the first set of propellers 502 and the second set of propellers 504 may be driven by a motor (not shown in the figure), thereby forming a configuration of 4 fans connected to 4 motors in each of the first propeller assembly housing 202a and the second propeller assembly housing 202b.
In an illustrative configuration, FIG.7 illustrates a right view 100 of ejected airbags and parachute from of the air vehicle, as an illustrative configuration of the present disclosure. As explained above, the air vehicle may include a parachute housing 302. The parachute housing 302 may be configured to store a parachute 702. Further, the vehicle may include a plurality of airbags 704a, 704b, 706a, and 706b mounted in the first propeller assembly housing with landing skids 202a and the second propeller assembly housing with landing skids 202b. The plurality of airbags 704a, 704b, 706a, and 706b may be configured to house individual airbags ranging between 8-12 airbags, to provide a soft cushion to the aircraft while emergency landing. In another configuration, a maximum of 4 parachutes may be mounted in the parachute housing 302. In another configuration, plurality of airbags 704a, 704b, 706a, and 706b from, and the parachute 702 may be deployed from their respective housings in events of partial failures of the propellers, motor or other component or system, thereby acting as a safety measure for the aircraft.

In another configuration, the length of the air vehicle, including but may not be limited to a passenger aircraft, or a cargo aircraft, may range between 2-30 meters. Further, the wingspan of the air vehicle may range between 2-30 meters. Further, the height of the air vehicle may range between 0.20-5 meters. Further, the air vehicle may maximum take-off weight in the range of 5-5000 kg. The air vehicle may achieve a flight duration ranging between 30-300 minutes. The air vehicle may be configured to cover a flight range of 20-1000 kilometers and may attain a maximum flight speed ranging between 50-600 km/hour.

Various modifications to the embodiment will be readily apparent to those skilled in the art and the generic principles herein may be applied to other embodiments. However, one of ordinary skill in the art will readily recognize that the present disclosure is not intended to be limited to the embodiments illustrated but is to be accorded the widest scope consistent with the principles and features described herein.

The foregoing description shall be interpreted as illustrative and not in any limiting sense. A person of ordinary skill in the art would understand that certain modifications could come within the scope of this disclosure.

The embodiments, examples, and alternatives of the preceding paragraphs or the description and drawings, including any of their various aspects or respective individual features, may be taken independently or in any combination. Features described in connection with one embodiment are applicable to all embodiments unless such features are incompatible.
, Claims:I/We Claim:

1. An air vehicle, comprising:
a front section (102) comprising:
a nose; and
a first propeller assembly housing with landing skids (202a) adjoined to the nose;
a rear section (106) oppositely disposed to the front section (102), comprising:
a tail comprising:
two vertical stabilizer (214a, 214b); and
a horizontal stabilizer (212) positioned between the vertical stabilizers (214a, 214b);
a fuselage (104) defined between the front section (102) and the rear section (106), comprising:
an upper external portion; and
a lower external portion oppositely disposed to the upper external portion;
a second propeller assembly housing with landing skids (202b) adjoined to the lower external portion of the fuselage (104);
a set of wings (108a, 108b) adjoined to the upper external portion of the fuselage, comprising:
a left wing (108a) comprising:
a left aileron (206b); and
a fist set of electric ducted fan housing (204b);
a right wing (108b) disposed opposite to the left wing (108a), comprising:
a right aileron (206a); and
a second set of electric ducted fan housing (204a); and
a power source (506) electrically connected and configured to power a first propeller assembly, a second propeller assembly, a first set of electric ducted fans and a second set of electric ducted fans.

2. The aircraft as claimed in claim 1, wherein the first propeller assembly comprises:
the first propeller assembly housing (202a) adjoined to the nose; and
a first set of propeller guards (208a, 208b, 208c, and 208d) symmetrically arranged in the first propeller assembly housing with landing skids (202a).

3. The aircraft as claimed in claim 1, wherein the second propeller assembly comprises:
the second propeller assembly housing with landing skids (202b) adjoined to the lower external region of the fuselage (104); and
a second set of propellers guards (210a, 210b, 210c, and 210d) symmetrically arranged in the second propeller assembly housing with landing skids (202b).

4. The aircraft as claimed in claims 2 or 3, wherein the first propeller assembly and the second propeller assembly are configured to provide thrust to the aircraft in a vertical direction, during a vertical take-off and landing.

5. The aircraft as claimed in claim 1, wherein the first set of electric ducted fan housing (204b) comprises at least four electric ducted fans (508b) arranged in a linear pattern on the left wing (108a) of the aircraft.

6. The aircraft as claimed in claim 1, wherein the second set of electric ducted fan housing (204a) comprises at least four electric ducted fans (508a) arranged in a linear pattern on the right wing (108a) of the aircraft.
7. The aircraft as claimed in claim 6 or 7, wherein the first set of electric ducted fans (508a) and the second set of electric ducted fans (508b) are configured to provide thrust to the aircraft in a horizontal direction, during a horizontal flight.

8. The aircraft as claimed in claim 1, wherein the vertical stabilizer (214a, 214b) comprises:
a first vertical stabilizer (214a); and
a second vertical stabilizer (214b) parallel and offset to the first vertical stabilizer (214a).

9. The aircraft as claimed in claim 1, wherein the each of the housing in the first propeller assembly housing with landing skids 202a and the second propeller assembly housing with landing skids 202b comprises a plurality of airbags (704a, 704b, 706a, and 706b).

10. The aircraft as claimed in claim 9, comprising:
at least one parachute (702) mounted on the upper external region of the fuselage (104), and housed in a parachute housing (302).