DESC:FIELD OF THE INVENTION

The present disclosure relates to fuel storing and refuelling assemblies and in particular, relates to an aviation-fuel tank assembly for storing aviation fuel and refuelling the aviation fuel in a vehicle.

BACKGROUND

Generally, various types of portable tanks are employed for storing and transporting liquefied gases under cryogenic conditions. However, with falling demand/ageing of tanks/ changes in chassis, such portable tanks are left unused. An in-depth study was done to conclude that the tanks can be put to use for storing aviation fuel, such as Jet A1 fuel. Currently, tanks, such as mild steel tanks, employed for storing the aviation fuel are complex in construction and fail to facilitate refuelling of a vehicle. Such mild steel tanks are internally coated with epoxy material. However, it is observed that storing the aviation fuel for prolong period of time within the mild steel tank may lead to erosion of the epoxy material. Quality Control of the aviation fuel is of paramount importance and the process mandates stringent storage conditions. This erosion is detrimental for the quality of the aviation fuel stored within the mild steel tank.

Therefore, there is a need for an improved solution for storing aviation fuel and for supplying the aviation fuel to a vehicle.

SUMMARY

This summary is provided to introduce a selection of concepts, in a simplified format, that are further described in the detailed description of the invention. This summary is neither intended to identify key or essential inventive concepts of the invention and nor is it intended for determining the scope of the invention.

In an embodiment, an aviation-fuel tank assembly is disclosed. The aviation-fuel tank assembly includes a tank adapted to store aviation fuel. The tank includes an inner vessel and an outer vessel. The aviation-fuel tank assembly includes a refuelling module in communication with the tank. The refuelling module is adapted to receive and store aviation fuel into the inner vessel of the tank and adapted to supply the aviation fuel from the inner vessel to a vehicle for refuelling. The refuelling module is connected to the inner vessel through an inlet port and an outlet port positioned at a top portion of the tank. Further, the aviation-fuel tank assembly includes a floating suction unit disposed within the tank and adapted to ensure that the aviation fuel is drawn by the refuelling module from the inner vessel. The aviation-fuel assembly also includes a sampling unit in communication with the refuelling module and operable to detect contamination in the aviation fuel. Further, the aviation-fuel assembly includes a sensing unit disposed in the tank and adapted to indicate a level of the aviation fuel in the inner vessel and to detect presence of the aviation fuel between the inner vessel and the outer vessel.

To further clarify advantages and features of the present invention, a more particular description of the invention will be rendered by reference to specific embodiments thereof, which is illustrated in the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. The invention will be described and explained with additional specificity and detail with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other features, aspects, and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:

Figure 1 illustrates a top view of an aviation-fuel tank assembly, according to an embodiment of the present disclosure;

Figure 2 illustrates a side view of the aviation-fuel tank assembly, according to an embodiment of the present disclosure;

Figure 3 illustrates a front view of the aviation-fuel tank assembly, according to an embodiment of the present disclosure; and

Figure 4 illustrates a schematic view of a refuelling module of the aviation-fuel tank assembly, according to an embodiment of the present disclosure.

Further, skilled artisans will appreciate that elements in the drawings are illustrated for simplicity and may not have been necessarily been drawn to scale. For example, the flow charts illustrate the method in terms of the most prominent steps involved to help to improve understanding of aspects of the present invention. Furthermore, in terms of the construction of the device, one or more components of the device may have been represented in the drawings by conventional symbols, and the drawings may show only those specific details that are pertinent to understanding the embodiments of the present invention so as not to obscure the drawings with details that will be readily apparent to those of ordinary skill in the art having benefit of the description herein.

DETAILED DESCRIPTION OF FIGURES

For the purpose of promoting an understanding of the principles of the invention, reference will now be made to the embodiment illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended, such alterations and further modifications in the illustrated system, and such further applications of the principles of the invention as illustrated therein being contemplated as would normally occur to one skilled in the art to which the invention relates.

It will be understood by those skilled in the art that the foregoing general description and the following detailed description are explanatory of the invention and are not intended to be restrictive thereof.

Reference throughout this specification to “an aspect”, “another aspect” or similar language means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. Thus, appearances of the phrase “in an embodiment”, “in another embodiment” and similar language throughout this specification may, but do not necessarily, all refer to the same embodiment.

The terms "comprises", "comprising", or any other variations thereof, are intended to cover a nonexclusive inclusion, such that a process or method that comprises a list of steps does not include only those steps but may include other steps not expressly listed or inherent to such process or method. Similarly, one or more devices or subsystems or elements or structures or components proceeded by "comprises... a" does not, without more constraints, preclude the existence of other devices or other sub-systems or other elements or other structures or other components or additional devices or additional sub-systems or additional elements or additional structures or additional components.

Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The system, methods, and examples provided herein are illustrative only and not intended to be limiting.

Embodiments of the present invention will be described below in detail with reference to the accompanying drawings.

Figure 1 illustrates a top view of an aviation-fuel tank assembly 100, according to an embodiment of the present disclosure. Figure 2 illustrates a side view of the aviation-fuel tank assembly 100, according to an embodiment of the present disclosure. The aviation-fuel tank assembly 100 may be employed for storing aviation fuel and for refuelling a vehicle. In an embodiment, the aviation-fuel tank assembly 100 may interchangeably be referred to as the tank assembly 100, without departing from the scope of the present disclosure. The tank assembly 100 may include a tank 102 and a refuelling module 104 in communication with the tank 102.

Referring to Figure 1 and Figure 2, the tank 102 may be adapted to store aviation fuel. The tank 102 may have a top portion 102-1, a bottom portion 102-2, a front portion 102-3 and a rear portion 102-4 distal to the front portion 102-3. The refuelling module 104 of the tank assembly 100 may be positioned at the front portion 102-3 of the tank 102. The tank 102 may include an inner vessel 106 and an outer vessel 108. In an embodiment, the inner vessel 106 may be formed of Stainless Steel (SS) 304, without departing from the scope of the present disclosure. Further, the outer vessel 108 may be formed of Mild Steel (MS) IS 2062, without departing from the scope of the present disclosure.

The inner vessel 106 and the outer vessel 108 may be positioned with respect to each other such that a predefined gap is defined between the inner vessel 106 and the outer vessel 108. In an embodiment, the inner vessel 106 and the outer vessel 108 may be positioned with respect to each other such that the predefined gap, such as a first predefined gap, is defined between the inner vessel 106 and the outer vessel 108. The first predefined gap may be defined between the inner vessel 106 and the outer vessel 108 at the top portion 102-1, the bottom portion 102-2, and the rear portion 102-4 of the tank 102.

Further, a second predefined gap may be defined between the inner vessel 106 and the outer vessel 108 at the front portion 102-3 of the tank 102. The second predefined gap may be larger than the first predefined gap. In an example, the first predefined gap may be approximately 10 cm. In such an example, the second predefined gap may be larger than the first predefined gap, i.e., 10 cm.

The tank 102 may include an inlet port 110 and an outlet port 112 positioned at the top portion 102-4 of the tank 102. The inlet port 110 and the outlet port 112 may be adapted to fluidly couple the inner vessel 106 of the tank 102 with the refuelling module 104. Referring to Figure 1 and Figure 2, in the illustrated embodiment, the inlet port 110 of the tank 102 may be coupled to the refuelling module 104 through an inlet conduit 114.

Similarly, the outlet port 112 of the tank 102 may be coupled to the refuelling module 104 through an outlet conduit 116. The tank 102 may also include at least one opening 118, interchangeably referred as manhole 118, for allowing a person to enter in the inner vessel 106 of the tank 102 for maintenance and for performing other similar tasks in the tank 102. The manhole 118 may be covered via a lid that prevents ingress of contaminants within the inner vessel 106 through the manhole 118.

Referring to Figure 2, the tank assembly 100 may include a floating suction unit 204 and a sensing unit 206. The floating suction unit 204 may be disposed within the tank 102. In particular, the floating suction unit 204 may be disposed within the inner vessel 106 of the tank 102. The floating suction unit 204 may be adapted to ensure that the aviation fuel is drawn by the refuelling module 104 from the inner vessel 106. In particular, the floating suction unit 204 may be provided to ensure that the aviation fuel is drawn-off just below a surface of the aviation fuel present in the tank 102. This prevents suction of the water/sediments/residual along with the aviation fuel, as the water/sediments/residual is settled down at a bottom of the inner vessel 106 of the tank 102.

In one embodiment, the floating suction unit 204 may be installed in a horizontal orientation within the tank 102. In another embodiment, the floating suction unit 204 may be installed in a vertical orientation within the tank 102. Further, the floating suction unit 204 may be installed above or below a ground storage tank, without departing from the scope of the present disclosure.

In the illustrated embodiment, the floating suction unit 204 may include at least one arm 208 and at least one floating suction cable 210 coupled to the at least one arm 208. The at least one arm 208 may be in fluid communication with the outlet conduit 116 connected to the refuelling module 104 through the outlet port 112. Further, the at least one arm 208 may be adapted to swing in an upward direction and a downward direction within the inner vessel 106 for supplying the aviation fuel to the vehicle for refuelling. In particular, the at least one arm 208 may be provided with swivel joints to enable movement in the upward direction and the downward direction based on a level of the aviation fuel within the inner vessel 106.

For instance, while receiving the aviation fuel through the inlet port 110, the level of the aviation fuel may increase within the inner vessel 106. In such an instance, the at least one arm 208 may swing in the upward direction. In another instance, while supplying the aviation fuel through the outlet port 112, the level of the aviation fuel may decrease within the inner vessel 106. In such an instance, the at least one arm 208 may swing in the downward direction.

Further, the sensing unit 206 of the tank assembly 100 may be disposed in the tank 102. The sensing unit 206 may be adapted to indicate a level of the aviation fuel in the inner vessel 106. Further, the sensing unit 206 may be adapted to detect presence of the aviation fuel between the inner vessel 106 and the outer vessel 108. In an embodiment, the sensing unit 206 may include a first sensing unit 206-1 and a second sensing unit 206-2. The first sensing unit 206-1 may be adapted to detect presence of the aviation fuel within a gap defined between the inner vessel 106 and the outer vessel 108. The first sensing unit 206-1 may detect presence of the aviation fuel between the inner vessel 106 and the outer vessel 108 at a low level, such as 115 Litres from the bottom portion of the tank 102.

The second sensing unit 206-2 may be adapted to detect the level of the aviation fuel in the inner vessel 106. In particular, the second sensing unit 206-2 may alert a user when the level of the aviation fuel reaches a safe level within the inner vessel 106. For example, the second sensing unit 206-2 may include a first level sensor and a second level sensor. In such an example, the first level sensor may be adapted to measure the level of the aviation fuel and notify the user if the level of the aviation fuel reaches to 95% of overall tank capacity. The second level sensor may be adapted to measure the level of the aviation fuel and notify the user if the level of the aviation fuel reaches 97% of overall tank capacity.

Further, the tank assembly may include a sump 212 formed at a bottom portion of the inner vessel 106. The sump 212 may be in fluid communication with a sampling unit 316 which is explained in detail in subsequent sections of the present disclosure. In the inner vessel 106, water/sediments/residual associated with the aviation fuel may be settled down in the sump 212 formed at the bottom portion of the inner vessel 106. The sampling unit 316 may receive a sample of water/sediments/residual from the sump 212 for further inspection.

Figure 3 illustrates a front view of the aviation-fuel tank assembly 100 depicting the refuelling module 104, according to an embodiment of the present disclosure. Figure 4 illustrates a schematic view of the refuelling module 104 of the aviation-fuel tank assembly 100, according to an embodiment of the present disclosure. As mentioned earlier, the tank assembly 100 may include the refuelling module 104 in communication with the tank 102. The refuelling module 104 may be connected to the inner vessel 106 through the inlet port 110 and the outlet port 112 positioned at the top portion 102-1 of the tank 102.

In the illustrated embodiment, the tank assembly 100 may include a cabinet 202 positioned at the front portion 102-3 of the tank 102. The cabinet 202 may be provided for accommodating the refuelling module 104 of the tank assembly 100. The cabinet 202 may include with at least three lockable doors provided to access the refuelling module 104 positioned within the cabinet 202. In an embodiment, each of the at least three lockable doors may be embodied as Aluminium roller shutter doors, without departing from the scope of the present disclosure.

The refuelling module 104 may be adapted to receive and store aviation fuel into the inner vessel 106 of the tank 100. Further, the refuelling module 104 may be adapted to supply the aviation fuel from the inner vessel 106 of the tank 100 to the vehicle for refuelling. In an embodiment, referring to Figure 3, the refuelling module 104 may include a first pumping mechanism 302 and a second pumping mechanism 304.

Each of the first pumping mechanism 302 and the second pumping mechanism 304 may be embodied as a single-stage centrifugal pump, without departing from the scope of the present disclosure. In one embodiment, each of the first pumping mechanism 302 and the second pumping mechanism 304 may be embodied as a self-priming pump. In another embodiment, each of the first pumping mechanism 302 and the second pumping mechanism 304 may be embodied as a non-priming pump.

In an embodiment, the first pumping mechanism 302 may be in communication with the inlet port 110 of the inner vessel 106 through the inlet conduit 114. The first pumping mechanism 302 may be adapted to supply the aviation fuel in the inner vessel 106. The first pumping mechanism 302 may be in communication with the inner vessel 106 through the inlet conduit 114. The second pumping mechanism 304 may be in communication with the outlet port 112 of the inner vessel 106 through the outlet conduit 116. The second pumping mechanism 304 may be adapted to draw the aviation fuel from the inner vessel 106 for refuelling the vehicle.

Further, the tank assembly 100 may include a plurality of motors coupled to the first pumping mechanism 302 and the second pumping mechanism 304. Each of the plurality of motors may be embodied as a Flame Proof (FLP) motor, without departing from the scope of the present disclosure. In the illustrated embodiment, the plurality of motors may include a first motor 306 and a second motor 308. The first motor 306 and the second motor 308 may be coupled to the first pumping mechanism 302 and the second pumping mechanism 304, respectively. The first motor 306 may actuate the first pumping mechanism 302 to supply the aviation fuel in the inner vessel 106. Further, the second motor 308 may actuate the second pumping mechanism 304 to draw the aviation fuel from the inner vessel 106 for refuelling the vehicle.

In an embodiment, the tank assembly 100 may include a micro filter vessel 309 vertically disposed upstream of the inlet port 110 of the inner vessel 106. The micro filter vessel 309 may be adapted to restrict contaminants from flowing within the inner vessel 106 through the inlet port 110. The micro filter vessel 309 may be in fluid communication with the first pumping mechanism 302.

The tank assembly 100 also includes a filter water separator 310 horizontally disposed downstream of the outlet port 112 of the inner vessel 106. The filter water separator 310 may be adapted to prevent sediments and water contamination in the aviation fuel flowing from the outlet port 112 of the inner vessel 106 to the vehicle. In an embodiment, the filter water separator 310 may include at least one filter elements including, but not limited to, coalesce and separator. In an example, the at least one filter may be embodied as a 1 micron filter which is designed for a minimum fluid flow rate of 920 Litre per Minute (LPM).

In the illustrated embodiment, the filter water separator 310 may be positioned downstream of the second pumping mechanism 304. The filter water separator 310 may be in fluid communication with the second pumping mechanism 304 through a conduit 312. The filter water separator 310 may be adapted to receive a flow of the aviation fuel from the inlet port 110 through the conduit. The filter water separator 310 may be in fluid communication with a hose reel 314 adapted to be connected to the vehicle for refuelling. In an embodiment, the hose reel 314 may be embodied as a Catherine type hose reel, without departing from the scope of the present disclosure.

Further, the refuelling module 104 may include a sampling unit 316 and strainers. The sampling unit 316 may be in fluid communication with a plurality of filters. The sampling unit 316 may also be in fluid communication with the inner vessel 106 through the inlet port 110 and the outlet port 112. In an embodiment, the sampling unit 316 may be provided for visual detection of contamination in the aviation fuel flowing within the tank assembly 100. In particular, the sampling unit 316 may be provided to receive samples of aviation fuel from a flow of aviation fuel flowing within the inner vessel 106 of the tank 102. In an embodiment, the sampling unit 316 may be provided for visual inspection of inlet/outlet/drain/tank sump drain samples, with provision for fitting a hydrometer, a thermometer, and a water detector device.

In an embodiment, the sampling unit 316 may be embodied as a closed-circuit sampler, without departing from the scope of the present disclosure. In the present embodiment, the sampling unit 316 may interchangeably be referred to as the closed-circuit sampler 316. The close circuit sampler 316 may be employed in the tank assembly 100 to monitor cleanliness of the aviation fuel without any spillage/body contact/contamination. In an embodiment, the closed-circuit sampler 316 may include a glass tube coupled to a conical base and provided with a hinged vented cover.

The conical base may be coated with a white epoxy material, without departing from the scope of the present disclosure. In an embodiment, the glass tube of the close circuit sampler may have a capacity of approximately 4 Litres and a diameter of approximately 100 mm, without departing from the scope of the present disclosure. The glass tube and the conical base may be formed of Borosilicate material and cast aluminium, respectively.

The close circuit sampler 316 may include an inlet port and a drain port. The inlet port may be in communication with the plurality of filters, the inlet port, and the outlet port of the inner vessel. In an embodiment, the inlet port may be in communication with the micro filter vessel 309. In such an embodiment, the inlet port may be connected to a plurality of sampling points provided in the micro filter vessel 309. The plurality of sampling points may be provided with valves for controlling a flow of sample aviation fuel to the inlet port of the close circuit sampler 316. When the sample of aviation fuel is drawn through the inlet port in the close circuit sampler 316, then the inlet port promotes vortexing of the sample fuel.

This leads to concentration of any contamination present in the sample fuel towards a centre of the base of the close circuit sampler 316 which enables easy detection of the contamination. Further, the tank assembly 100 may include a dump/recovery tank in fluid communication with the closed-circuit sampler 316. In an embodiment, the drain port of the close circuit sampler 316 may be connected to the dump/recovery tank. The close circuit sampler 316 may be connected to the drain/recovery tank in such a manner that draining operation may be assisted by gravity.

Further, in an embodiment, the tank assembly 100 may include an electrical system for monitoring and controlling various operations associated with the tank assembly 100. The electrical system may include, but is not limited to, flame proof starters for the first pumping mechanism 302 and the second pumping mechanism 304, switch board for LED lights inside the cabinet, and an emergency shutdown system. The tank assembly 100 may also include a plurality of valves connected to conduits employed in the tank assembly 100 for controlling a flow of the aviation fuel. The plurality of valves may collectively and individually be referred to as the valves and the valve, respectively. For example, referring to Figure 3, the valves 318 including, but not limited to, ball valves may be provided at the inlet conduit, the outlet conduit, and the conduit between the second pumping mechanism 304 and the filter water separator 310.

In an embodiment, the tank assembly 100 may also include a box stainer 320 and a 3 lug adopter 322 for performing Milipore testing to measure/verify cleanliness of sub-components. Further, the valve 318 may be disposed between the box stainer 320 and the 3 lug adopter 322. Also, the tank assembly 100 may include an air eliminator 324 coupled to the filter water separator. The air eliminator 324 may be adapted to eliminate air from the flow of the aviation fuel in the tank assembly 100.

The present disclosure also discloses a method of manufacturing the aviation-fuel tank assembly 100. In an embodiment, the method includes removing dish plates at both ends of an outer vessel of a cryogenic storage tank. Further, a Multi-layered Insulation (MLI) along with an inner vessel is removed from the configuration, i.e., the cryogenic storage tank. Subsequently, the inner vessel may be cut-open from one side. The method also includes removing straight baffles from the inner vessel. A channel of 100 mm may be carved out in between the stiffeners. This is done to enable that any water or particulate matter to drain down to the sump. Further, hydro-testing of the inner vessel is performed by using water at 0.365 kg/cm2. Thereafter, the inner vessel may be positioned within the outer vessel using a longitudinal plate and rollers. The method also includes welding of new plates to the inner vessel and the outer vessel, which enables bolting of the inner to the outer vessel. The outer vessel may be pneumatically tested at a pressure approximately equal to 0.35 kg/cm2. Further, the refuelling module 104 may be coupled to the tank.

The drawings and the forgoing description give examples of embodiments. Those skilled in the art will appreciate that one or more of the described elements may well be combined into a single functional element. Alternatively, certain elements may be split into multiple functional elements. Elements from one embodiment may be added to another embodiment. For example, orders of processes described herein may be changed and are not limited to the manner described herein.

Moreover, the actions of any flow diagram need not be implemented in the order shown; nor do all of the acts necessarily need to be performed. Also, those acts that are not dependent on other acts may be performed in parallel with the other acts. The scope of embodiments is by no means limited by these specific examples. Numerous variations, whether explicitly given in the specification or not, such as differences in structure, dimension, and use of material, are possible. The scope of embodiments is at least as broad as given by the following claims.

Benefits, other advantages, and solutions to problems have been described above with regard to specific embodiments. However, the benefits, advantages, solutions to problems, and any component(s) that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as a critical, required, or essential feature or component of any or all the claims.

While specific language has been used to describe the present subject matter, any limitations arising on account thereto, are not intended. As would be apparent to a person in the art, various working modifications may be made to the method in order to implement the inventive concept as taught herein. The drawings and the foregoing description give examples of embodiments. Those skilled in the art will appreciate that one or more of the described elements may well be combined into a single functional element. Alternatively, certain elements may be split into multiple functional elements. Elements from one embodiment may be added to another embodiment. ,CLAIMS:1. An aviation-fuel tank assembly (100) comprising:
a tank (102) adapted to store aviation fuel, wherein the tank (102) includes an inner vessel (106) and an outer vessel (108);
a refuelling module (104) in communication with the tank (102), the refuelling module (104) adapted to receive and store the aviation fuel into the inner vessel (106) of the tank (102) and adapted to supply the aviation fuel from the inner vessel (106) to a vehicle for refuelling, wherein the refuelling module (104) is connected to the inner vessel (106) through an inlet port (110) and an outlet port (112) positioned at a top portion (102-4) of the tank (102); and
a floating suction unit (204) disposed within the tank (102) and adapted to ensure that the aviation fuel is drawn by the refuelling module (104) from the inner vessel (106);
a sampling unit (316) in communication with the refuelling module (104) and operable to detect contamination in the aviation fuel; and
a sensing unit (206) disposed in the tank (102) and adapted to indicate a level of the aviation fuel in the inner vessel (106) and to detect presence of the aviation fuel between the inner vessel (106) and the outer vessel (108).

2. The aviation-fuel tank assembly (100) as claimed in claim 1, wherein the inner vessel (106) and the outer vessel (108) are positioned with respect to each other such that a predefined gap is defined between the inner vessel (106) and the outer vessel (108).

3. The aviation-fuel tank assembly (100) as claimed in claim 1, wherein the sensing unit (206) includes a first sensing unit (206-1) adapted to detect presence of the aviation fuel within a gap defined between the inner vessel (106) and the outer vessel (108), and a second sensing unit (206-2) adapted to detect the level of the aviation fuel in the inner vessel (106).

4. The aviation-fuel tank assembly (100) as claimed in claim 1, wherein the refuelling module (104) includes a first pumping mechanism (302) adapted to supply the aviation fuel to the inner vessel (106) and a second pumping mechanism (304) adapted to draw the aviation fuel from the inner vessel (106) for refuelling the vehicle.

5. The aviation-fuel tank assembly (100) as claimed in claim 4, wherein each of the first pumping mechanism (302) and the second pumping mechanism (304) is a single-stage centrifugal pump.

6. The aviation-fuel tank assembly (100) as claimed in claim 1, wherein the refuelling module (104) includes a sampling unit (316) in fluid communication with a plurality of filters, the inlet port (110), and the outlet port (112) of the inner vessel (106) for visual detection of contamination in the aviation fuel flowing within the aviation-fuel tank assembly (100).

7. The aviation-fuel tank assembly (100) as claimed in claim 6 further comprising a sump (212) formed at a bottom portion of the inner vessel (106), wherein the sump (212) is in fluid communication with the sampling unit (316).

8. The aviation-fuel tank assembly (100) as claimed in claim 1 further comprising a micro filter vessel (309) vertically disposed upstream of the inlet port (110) of the inner vessel (106), wherein the micro filter vessel (309) is adapted to restrict contaminants from flowing within the inner vessel (106) through the inlet port (110).

9. The aviation-fuel tank assembly (100) as claimed in claim 1 further comprising a filter water separator (310) horizontally disposed downstream of the outlet port (112) of the inner vessel (106), wherein the filter water separator (310) is adapted to prevent sediments and water contamination in the aviation fuel flowing from the outlet port (112) to the vehicle.

10. The aviation-fuel tank assembly (100) as claimed in claim 1, wherein the floating suction unit (204) includes at least one arm in fluid communication with an outlet conduit (116) connected to the refuelling module (104) through the outlet port (112) of the inner vessel (106), wherein the at least one arm is adapted to swing in an upward and a downward direction within the inner vessel (106), for supplying the aviation fuel to the vehicle for refuelling.