Description:TECHNICAL FIELD
[0001] The present disclosure relates, in general, to the field of aerospace technologies. More particularly, embodiments of the present disclosure relate to a high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications.

BACKGROUND
[0002] The background information herein below relates to the present disclosure but is not necessarily prior art.
[0003] Among the latest aerospace technologies, there has been a growing pace of activity around High Altitude Pseudo Satellites or HAPS platforms that are emerging as a disruptive technology that could revolutionise near-space operations. A high-altitude Pseudo Satellite (HAPS) is a long endurance, high altitude aircraft able to offer observation or communication services similar to an artificial satellite. Mostly fixed wing unmanned aerial vehicles (UAVs) remain aloft through an atmospheric lift, either aerodynamic like airplanes or aerostatic like airships or balloons.
[0004] Compared to ground based communication networks, HAPS can cover larger areas with less interference. They could also help ease data transfer when used as an intermediate conduit between satellite and ground based telecom networks. For surveillance, monitoring, imaging, and communication applications, the flight range and time of flight are important factors to be considered in HAPS.
[0005] The major players in HAPS are NASA Helios (wingspan of 75.28m and mass of 599kgs), Airbus Zephyr 8/S (25m and 65kg), Boeing Odysseus (74.1m and 880kg) and Solar Impulse (63.4m and 1600kg). With a huge size, the existing HAPS has implications for launching, maintaining, and ensuring safe operations, altogether leading to regulatory delays. On the other hand, the small HAPS’ aerodynamic performance should be improved to attain long endurance.
[0006] Therefore, it is felt a need for a high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications.
OBJECTS
[0007] Some of the objects of the present disclosure, which at least one embodiment herein satisfies, are as follows.
[0008] It is an object of the present disclosure to ameliorate one or more problems of the prior art or to at least provide a useful alternative.
[0009] The main object of the present disclosure is to provide a high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications.
[0010] Another object of the present disclosure is to provide a light weight high-altitude unmanned pseudo satellite.
[0011] Another object of the present disclosure is to provide a high-altitude unmanned pseudo satellite having a main wing and tail wing with a high lift-to-drag ratio (Cl/Cd).
[0012] Another object of the present disclosure is to provide a high-altitude unmanned pseudo satellite with improved aerodynamic performance to attain long endurance.
[0013] Another object of the present disclosure is to provide a to the high-altitude unmanned pseudo satellite to reduce energy consumption.
[0014] Another object of the present disclosure is to provide a high-altitude unmanned pseudo satellite to reach high altitudes with long soaring.
[0015] Another object of the present disclosure is to provide a high-altitude unmanned pseudo satellite to eliminate regulatory delays.
[0016] Another object of the present disclosure is to provide a very cost-effective high-altitude unmanned pseudo satellite.
[0017] Another object of the present disclosure is to provide a high-altitude unmanned pseudo satellite with minimum maintenance requirements.
[0018] Another object of the present disclosure is to provide a high-altitude unmanned pseudo satellite with the design parameters that can vary to scale up or scale down.

[0019] Another object of the present disclosure is to provide a high-altitude unmanned pseudo satellite in which the wing span (ML) can be selected as per the air speed of the glider.
[0020] Other objects and advantages of the present disclosure will be more apparent from the following description when read in conjunction with the accompanying figures, which are not intended to limit the scope of the present disclosure.

SUMMARY
[0021] This summary is provided to introduce concepts related to a high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications. The concepts are further described below in the following detailed description. This summary is not intended to identify essential features of the claimed subject matter nor is it intended for use in determining or limiting the scope of the claimed subject matter.
[0022] The present disclosure envisages a high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications. The high-altitude unmanned pseudo satellite comprises a main wing structure, and a tail wing structure. The tail wing structure is connected to the main wing structure via a connecting tube.
[0023] The main wing structure is having a main wing span (ML) and a main chord lengths (MC1, MC2 and MC3). Further, the main wing structure is provided with a plurality of taper ratios and a plurality of non-monotonic dihedral angles. The tail wing structure is having a horizontal stab chord length (HC) and a horizontal stab span (HL).
[0024] In an aspect, each of the plurality of the main chord lengths varies at various axis of the main wing span (ML).
[0025] In an aspect, the main wing chord lengths include a main wing chord length 1 (MC1), a main wing chord length 2 (MC2), and a main wing chord length 3 (MC3).
[0026] In an aspect, the plurality of non-monotonic dihedral angles includes a main wing first dihedral angle (MA1), and a main wing second dihedral angle (MA2).
[0027] In an aspect, the first dihedral angle (MA1) is a positive angle, and the second dihedral angle (MA2) is a negative angle.
[0028] In an aspect, the main wing span (ML) of the main wing structure is divided into three parts: a main wing span before the first dihedral angle (ML1), a main wing span of the first dihedral angle (ML2), and a main wing span of the second dihedral angle (ML3) and a main wing span of the second dihedral angle (ML3).
[0029] In an aspect, the plurality of taper ratios includes taper ratio (T1) before the first dihedral angle (MA1) and taper ratio (T2) at the second dihedral angle (MA2).
[0030] In an aspect, the main wing span is 4.5m and air speed is 9 m/s.
[0031] In an aspect, the lift-to-drag ratio (Cl/Cd) for both the main wing structure and the tail wing structure is around 35 at an air speed of 9m/s.
[0032] In an aspect, a modified airfoil for the main wing structure is WE 3.5-40-10-30.
[0033] In an aspect, an airfoil for the tail wing structure is NACA0012 symmetric.
[0034] In an aspect, the wing span (ML) is selected as per the air speed of the glider.
[0035] In an aspect, the design parameters varies to scale up or scale down.

BRIEF DESCRIPTION OF THE ACCOMPANYING DRAWING
[0036] A high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications of the present disclosure will now be described with the help of the accompanying drawing, in which:
[0037] Figure 1 illustrates an isometric view of a high-altitude unmanned pseudo satellite, in accordance with an embodiment of the present disclosure;
[0038] Figure 2 illustrates aspect ratio of a main wing structure, in accordance with an embodiment of the present disclosure;
[0039] Figure 3 illustrates a detailed drawings of the high-altitude unmanned pseudo satellite, with reference to Figure 1;
[0040] Figure 4 illustrates a representation of the improved lift-to-drag ratio (Cl/Cd) of the main wing structure and tail wing structure, in accordance with an embodiment of the present disclosure; and
[0041] Figure 5 illustrates the simulated results for the high-altitude unmanned pseudo satellite, in accordance with an embodiment of the present disclosure.

LIST OF REFERENCE NUMERALS USED IN THE DESCRIPTION AND DRAWING:
100 Unmanned pseudo satellite
102 Main wing structure
104 Tail wing structure
106 Connecting tube
ML Main wing span
HC Horizontal stab chord length
HL Horizontal stab span
MC1 Main wing chord length 1
MC2 Main wing chord length 2
MC3 Main wing chord length 3
MA1 First dihedral angle
MA2 Second dihedral angle
T1 Taper ratio before first dihedral angle
T2 Taper ratio at the second dihedral angle

DETAILED DESCRIPTION
[0042] Embodiments, of the present disclosure, will now be described with reference to the accompanying drawing.
[0043] Embodiments are provided so as to thoroughly and fully convey the scope of the present disclosure to the person skilled in the art. Numerous details are set forth, relating to specific components and methods to provide a complete understanding of embodiments of the present disclosure. It will be apparent to the person skilled in the art that the details provided in the embodiments should not be construed to limit the scope of the present disclosure. In some embodiments, well-known apparatus structures, and well-known techniques are not described in detail.
[0044] The terminology used, in the present disclosure, is only for the purpose of explaining a particular embodiment and such terminology shall not be considered to limit the scope of the present disclosure. As used in the present disclosure, the forms “a”, “an”, and “the” may be intended to include the plural forms as well, unless the context clearly suggests otherwise. The terms, “comprises”, “comprising”, “including” and “having” are open-ended transitional phrases and therefore, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not forbid the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
[0045] When an element is referred to as being “embodied thereon”, “engaged to”, “coupled to” or “communicatively coupled to” another element, it may be directly on, engaged, connected or coupled to the other element. As used herein, the term “and/or” includes any and all combinations of one or more of the associated listed elements.
[0046] The major players in HAPS are NASA Helios (wingspan of 75.28m and mass of 599kgs), Airbus Zephyr 8/S (25m and 65kg), Boeing Odysseus (74.1m and 880kg) and Solar Impulse (63.4m and 1600kg). With a huge size, the existing HAPS has implications for launching, maintaining, and ensuring safe operations, all together leading to regulatory delays. On the other hand, the small HAPS’ aerodynamic performance should be improved to attain long endurance.
[0047] To this, the present disclosure envisages a high-altitude unmanned pseudo satellite 100 for surveillance, monitoring, imaging, and communication applications. The basic structure of the high-altitude unmanned pseudo satellite 100 is described herein in reference to Figures 1 to 5.
[0048] Figure 1 illustrates an isometric view of a high-altitude unmanned pseudo satellite 100, in accordance with an embodiment of the present disclosure.
[0049] The high-altitude unmanned pseudo satellite 100 comprises a main wing structure 102, and a tail wing structure 104. The tail wing structure 104 is connected to the main wing structure 104 via a connecting tube 106.
[0050] Figure 2 illustrates aspect ratio of a main wing structure 102, in accordance with an embodiment of the present disclosure.
[0051] The aspect ratio of a wing is defined to be the square of the span divided by the wing area. Therefore the aspect ratio of the main wing structure 102 is the square of the main wing span (ML) divided by the wing area of the main wing structure 102.
[0052] Figure 3 illustrates a detailed drawing of the high-altitude unmanned pseudo satellite 100, with reference to Figure 1.
[0053] The main wing structure 102 is having a main wing span (ML) and a main chord lengths (MC1, MC2 and MC3). The main wing structure 102 is provided with a plurality of taper ratios and a plurality of non-monotonic dihedral angles. The tail wing structure 104 is having a horizontal stab chord length (HC) and a horizontal stab span (HL).
[0054] The main chord lengths of the main wing structure 102 vary at various axis of the main wing span (ML). The main wing chord lengths include a main wing chord length 1 (MC1), a main wing chord length 2 (MC2), and a main wing chord length 3 (MC3).
[0055] The plurality of non-monotonic dihedral angles includes a main wing first dihedral angle (MA1), and a main wing second dihedral angle (MA2). The first dihedral angle (MA1) is a positive angle, and the second dihedral angle (MA2) is a negative angle.
[0056] The main wing span (ML) of the main wing structure 102 is divided into three parts: a main wing span before the first dihedral angle (ML1), a main wing span of the first dihedral angle (ML2), and a main wing span of the second dihedral angle (ML3).
[0057] The plurality of taper ratios includes taper ratio (T1) before the first dihedral angle (MA1) and taper ratio (T2) at the second dihedral angle (MA2).
[0058] Figure 4 illustrates a representation of the improved lift-to-drag ratio (Cl/Cd) of the main wing structure 102 and tail wing structure 104, in accordance with an embodiment of the present disclosure.
[0059] An efficient aerodynamic design of the main wing structure 102 and tail wing structure 104 with high lift-to-drag ratio (Cl/Cd) is implemented to reduce the energy consumption of the satellite 100 and reach high-altitude with long soaring. The high Cl/Cd in the present disclosure is obtained by optimizing the aerodynamic design of the main wing structure 102 and tail wing structure 104. This reduces the energy consumption to ensure the long endurance of the satellite 100.
[0060] In an aspect, the lift-to-drag ratio (Cl/Cd) for both main wing structure 102 and tail wing structure 104 is around 35 at an air speed of 9m/s.
[0061] In an aspect, the high-altitude unmanned pseudo satellite 100 of the present disclosure with improved Cl/Cd has a wingspan of 4.5m and ~7kg of mass.
[0062] To improve the aerodynamic performance of the satellite 100, the camber’s position and thickness of the airfoil in the main wing structure 102 is slightly modified.
[0063] In an aspect, a modified airfoil for the main wing structure 102 is WE 3.5-40-10-30.
[0064] In an aspect, an airfoil for the tail wing structure 104 is NACA0012 symmetric.
[0065] In an aspect, the wing span (ML) is selected as per the air speed of the glider.
[0066] In an aspect, the design parameters varies to scale up or scale down.
[0067] The foregoing description of the embodiments has been provided for purposes of illustration and is not intended to limit the scope of the present disclosure. Individual components of a particular embodiment are generally not limited to that particular embodiment but, are interchangeable. Such variations are not to be regarded as a departure from the present disclosure, and all such modifications are considered to be within the scope of the present disclosure.

WORKING EXAMPLE
[0068] The aerodynamic parameters of the high-altitude unmanned pseudo satellite 100 disclosed in the present disclosure are listed in Table 1 as given below:
[0069] Following table illustrates the aerodynamic design parameters to prototype the high-altitude unmanned pseudo satellite 100 disclosed in the present disclosure. The main wing span (ML) and air speed of the satellite 100 may vary depending on the requirements.
 
TABLE 1
Referral numerals Description Aerodynamic design parameters
1 Main wing -
2 Tail wing -
3 Fuselage -
4 Connecting tube between main and tail wing -
A Area of the wing 2m2
AR Aspect ratio of main wing ML2/A
CG Centre of gravity 0.25*MC1
HC Horizontal stab chord length 0.64*MC1
HL Horizontal stab span 0.24*ML
LF Fuselage nose span 1.5*MC2(Mean chord length will come here)
LT Distance between CG and tail wing 0.3*ML
MA1 Main wing dihedral angle 1 10o
MA2 Main wing dihedral angle 2 5o
MC1 Main wing chord length 1 0.12*ML
MC2 Main wing chord length 2 0.1*ML
MC3 Main wing chord length 3 0.077*ML
ML Main wing span 4.5m
ML1 Main wing span before dihedral angle 0.4*ML
ML2 Main wing span of the 1st dihedral angle 0.12*ML
ML3 Main wing span of the 2nd dihedral angle 0.18*ML
T1 Taper ratio 1 at ML1 0.8
T2 Taper ratio 2 at ML3 0.8
VC Vertical stab chord length 0.64*MC1
VH Vertical stab height 0.12*ML

[0070] The high-altitude unmanned pseudo satellite 100 disclosed in the present disclosure is scaled to the existing small HAPS designs and performed a comparative study and the results are listed in Table 2 as given below:

TABLE 2
Referred designs (Cl/Cd)max of competitor designs (Cl/Cd)max of Invented design(Scaled to competitor wingspan)
Invented design
(wing span = 4.5m, air speed = 9m/s) - 35
SkySailor design
(wing span = 3.2m, air speed = 8.3m/s) 23.5 34
SunSailor design
(wing span = 4.2m, air speed = 11m/s) 23 36
SoLong design
(wing span = 4.75m, air speed = 12m/s) 30.11 42
AtlantikSolar design
(wing span = 5.69m, air speed = 8.6m/s) 24 37
Pluton design
(wing span = 4.25m, air speed = 21m/s) 22.5 42.5

[0071] In this disclosure, e.g., the invented design is scaled to the SkySailor’s wingspan for the same air speed (3.2m and 8.3m/s). The aerodynamic study of the scaled model is simulated and plotted as shown in Figure 4. The maximum lift-to-drag ratio (Cl/Cd)max of different existing small HAPS were compared and listed in Table 2.
[0072] From the comparative results shown in Figure 4 and Table 2, it is clearly evident that the high-altitude unmanned pseudo satellite 100 disclosed in the present disclosure is scalable to the competitor designs and produced improved Cl/Cd when considering the wing span and air speeds of the satellites made by competitors.
[0073] Figure 5 illustrates the simulated results for the high-altitude unmanned pseudo satellite, in accordance with an embodiment of the present disclosure.
[0074] The simulation result of the invention shown in Figure 4 is acquired by a simulation software (Xflr5). Higher lift-to-drag ratio (Cl/Cd) of around 35 at 4-degrees of angle of attack (AOA) at 9m/s is clearly observed from the simulation results. At zero-degree AOA, it produces the Cl/Cd of around 26. Experimental validations are conducted on the same.
[0075] According to the listed aerodynamic parameters in Table 1 and the Figures 1-3, the wing span (ML) and air speed of the glider may vary depending on the requirements, the wing span (ML) is selected as per the air speed of the glider.
[0076] The combination of aerodynamic parameters including wing span or air speed e.g may be modify like 4.5m wing span to 7m wing span. The design parameters may vary to scale up or scale down.

TECHNICAL ADVANCEMENTS AND ECONOMIC SIGNIFICANCE
[0077] The present disclosure described herein above has several technical advantages including, but not limited to, high-altitude unmanned pseudo satellite, which:
• provides the user(s) with a high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications;
• is efficient, compared to the state-of-the-art high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications;
• is power-saving, compared to the state-of-the-art high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications; and
• is cost-effective, compared to the state-of-the-art high-altitude unmanned pseudo satellite for surveillance, monitoring, imaging, and communication applications.
[0078] The embodiments herein and the various features and advantageous details thereof are explained with reference to the non-limiting embodiments in the following description. Descriptions of well-known components and processing techniques are omitted so as to not unnecessarily obscure the embodiments herein. The examples used herein are intended merely to facilitate an understanding of ways in which the embodiments herein may be practiced and to further enable those of skill in the art to practice the embodiments herein. Accordingly, the examples should not be construed as limiting the scope of the embodiments herein.
[0079] The foregoing description of the specific embodiments so fully reveal the general nature of the embodiments herein that others can, by applying current knowledge, readily modify and/or adapt for various applications such specific embodiments without departing from the generic concept, and, therefore, such adaptations and modifications should and are intended to be comprehended within the meaning and range of equivalents of the disclosed embodiments. It is to be understood that the phraseology or terminology employed herein is for the purpose of description and not of limitation. Therefore, while the embodiments herein have been described in terms of preferred embodiments, those skilled in the art will recognize that the embodiments herein can be practiced with modification within the spirit and scope of the embodiments as described herein.
[0080] The use of the expression “at least” or “at least one” suggests the use of one or more elements or ingredients or quantities, as the use may be in the embodiment of the disclosure to achieve one or more of the desired objects or results.
[0081] Any discussion of documents, acts, materials, devices, articles or the like that has been included in this specification is solely for the purpose of providing a context for the disclosure. It is not to be taken as an admission that any or all of these matters form a part of the prior art base or were common general knowledge in the field relevant to the disclosure as it existed anywhere before the priority date of this application.
[0082] The numerical values mentioned for the various physical parameters, dimensions or quantities are only approximations and it is envisaged that the values higher/lower than the numerical values assigned to the parameters, dimensions or quantities fall within the scope of the disclosure, unless there is a statement in the specification specific to the contrary.
[0083] While considerable emphasis has been placed herein on the components and component parts of the preferred embodiments, it will be appreciated that many embodiments can be made and that many changes can be made in the preferred embodiments without departing from the principles of the disclosure. These and other changes in the preferred embodiment as well as other embodiments of the disclosure will be apparent to those skilled in the art from the disclosure herein, whereby it is to be distinctly understood that the foregoing descriptive matter is to be interpreted merely as illustrative of the disclosure and not as a limitation. , Claims:WE CLAIM:
1. A high-altitude unmanned pseudo satellite (100) for surveillance, monitoring, imaging, and communication applications, said unmanned pseudo satellite (100) comprising:
a main wing structure (102) having a main wing span (ML) and a main chord lengths (MC1, MC2 and MC3); and
a tail wing structure (104), having a horizontal stab chord length (HC) and a horizontal stab span (HL), connected to the main wing structure (102) via a connecting tube (106);
wherein the main wing structure (102) is provided with a plurality of taper ratios and a plurality of non-monotonic dihedral angles.
2. The unmanned pseudo satellite (100) as claimed in claim 1, wherein the main chord lengths vary at various axis of the main wing span (ML).
3. The unmanned pseudo satellite (100) as claimed in claim 1, wherein the main wing chord lengths include a main wing chord length 1 (MC1), a main wing chord length 2 (MC2), and a main wing chord length 3 (MC3).
4. The unmanned pseudo satellite (100) as claimed in claim 1, wherein the plurality of non-monotonic dihedral angles includes a main wing first dihedral angle (MA1), and a main wing second dihedral angle (MA2).
5. The unmanned pseudo satellite (100) as claimed in claim 4, wherein the first dihedral angle (MA1) is a positive angle, and the second dihedral angle (MA2) is a negative angle.
6. The unmanned pseudo satellite (100) as claimed in claim 4, wherein the main wing span (ML) of the main wing structure (102) is divided into three parts: a main wing span before the first dihedral angle (ML1), a main wing span of the first dihedral angle (ML2), and a main wing span of the second dihedral angle (ML3).
7. The unmanned pseudo satellite (100) as claimed in claim 4, wherein the plurality of taper ratios include taper ratio (T1) before the first dihedral angle (MA1) and taper ratio (T2) at the second dihedral angle (MA2).
8. The unmanned pseudo satellite (100) as claimed in claim 1, wherein main wing span is 4.5m and air speed is 9 m/s.
9. The unmanned pseudo satellite (100) as claimed in claim 1, wherein the lift-to-drag ratio (Cl/Cd) for both main wing structure (102) and tail wing structure (104) is around 35 at an air speed of 9 m/s.
10. The unmanned pseudo satellite (100) as claimed in claim 1, wherein a modified airfoil for the main wing structure (102) is WE 3.5-40-10-30.
11. The unmanned pseudo satellite (100) as claimed in claim 1, wherein an airfoil for the tail wing structure (104) is NACA0012 symmetric.
12. The unmanned pseudo satellite (100) as claimed in claim 1, wherein the wing span (ML) is selected as per the air speed of the glider.
13. The unmanned pseudo satellite (100) as claimed in claim 1, wherein the design parameters varies to scale up or scale down.

Dated this 6nd day of June, 2023

_______________________________
MOHAN RAJKUMAR DEWAN, IN/PA – 25
of R.K.DEWAN & CO.
Authorized Agent of Applicant

TO,
THE CONTROLLER OF PATENTS
THE PATENT OFFICE, AT CHENNAI