TECHNICAL FIELD:
The present invention generally relates to the field of unmanned aerial vehicles. More
particularly, it relates to an electro‐mechanical device that is an unmanned aerial
vehicle comprising of pneumatic servo valves instead of rotors for creating lift such
that it overcomes various limitations of the existing unmanned aerial vehicles/drones.
BACKGROUND OF THE DISCLOSURE:
The following description of the related art is intended to provide background
information pertaining to the field of the disclosure. This section may include certain
aspects of the art that may be related to various features of the present disclosure.
However, it should be appreciated that this section is used only to enhance the
understanding of the reader with respect to the present disclosure, and not as
admissions of the prior art.

The unmanned aerial vehicles (UAVs) i.e., drones are aerial vehicle that does not carry
a human operator. These can fly autonomously or be piloted remotely. Due to the
unmanned flying capabilities, now a days the drones are used for various purposes
such as for aerial photography, environmental monitoring, gathering information,
crop monitoring, and infrastructure inspections etc. Therefore, to efficiently use the
drones for these and other use cases a number of drone specific solutions have been
developed over the past few years.
For the design and development of a drone fluid dynamics plays a significant role. A
drone has multiple rotors, where each rotor generally consists of a propeller attached
to a motor. The propellers of the drone spin and create an airflow to build a pressure

3
difference between the top and bottom surfaces of the propeller, which further
results in the lifting the drone by counteracting the force of gravity. Usually, Yaw, Pitch
and Roll movement for drone is achieved by changing the speed and direction of the
rotation of the propellers. A rotation around front‐to‐back axis of a drone is called
roll. A rotation around side‐to‐side axis of the drone is called pitch and a rotation
around vertical axis of the drone is called yaw.
To operate a drone in a most efficient manner, for instance to accurately move a
drone in a particular direction, a proper synchronization of all the rotors of the drone
is required. However, the currently known drones are quite inefficient for flight
purposes because of the way these drones are designed. Also, in the currently known
drones, exposed propellers raise an operational risk – even if they are not lethal. As
the propellers have sharp edges, there are safety concerns of having sharp moving
parts exposed to the general public, for instance, a cutting damage may be caused by
a physical contact to a moving propeller. Additionally, currently known drones have a
lot of electrical components that results in an increased cost, complexity, heating
issues and reliability.
Although the existing technologies have provided solutions to enhance the unmanned
aerial vehicles, but these currently known solutions have many limitations and
therefore, there is a need for improvement in this area of technology. In the light of
the aforementioned, there is a need for an efficient electro‐mechanical device (i.e.,
unmanned aerial vehicle (UAV) or drone) that is safe and that has an improved
performance over the existing UAVs or drones.
SUMMARY OF THE DISCLOSURE

4
This section is intended to introduce certain aspects of the disclosed system or device
in a simplified form and is not intended to identify the key advantages or features of
the present disclosure.
An aspect of the present disclosure relates to an electro‐mechanical device i.e., an
unmanned aerial vehicle (UAV) or drone. The electro‐mechanical device comprises: a
housing unit defining a top surface, a bottom surface, a pair of first vertical surfaces
and a pair of second vertical surfaces; and the housing unit is divided into a first
chamber and a second chamber. The electro‐mechanical device also comprises: one
or more propellers; a control unit; one or more sensors; an energy storage unit; one
or more actuators; and a plurality of pneumatic tubing with one or more flow control
means (i.e., one or more valves) placed therein. The first chamber of the electro‐
mechanical device defines one or more first openings on the bottom surface of the
housing unit and fluidly communicating with the one or more propellers housed
within the first chamber to suck a fluid into the first chamber. Also, the first chamber
defines one or more second openings on the bottom surface to controllably exhaust
a fluid to generate lift, roll and pitch motion. Additionally, the first chamber houses
the energy storage unit enabled to supply power to one or more sensors, the control
unit and one or more actuators coupled with one or more propellers. Further, the
second chamber of the electro‐mechanical device is connected to the first chamber.
Also, the second chamber houses the control unit enabled to communicate with at
least one of the one or more sensors, the one or more actuators, the one or more first
openings equipped with one or more first valves, the one or more second openings
equipped with one or more second valves and the one or more flow control means.
The second chamber also defines one or more pairs of third openings on each of the
pair of first vertical surfaces to controllably exhaust the fluid to generate lateral
motion of the electro‐mechanical device. Additionally, the second chamber defines

5
one or more pairs of fourth openings on each of the pair of second vertical surfaces
of the housing unit to controllably exhaust the fluid to generate yaw and longitudinal
motion of the electromechanical device. Moreover, the second chamber also houses
the plurality of pneumatic tubing with the one or more flow control means placed
therein such that the plurality of pneumatic tubing receives the fluid from the first
chamber and supplies the fluid to the one or more third openings and the one or more
fourth openings by controllably operating the flow control means.
BRIEF DESCRIPTION OF DRAWINGS

The accompanying drawings, which are incorporated herein, and constitute a part of
this disclosure, illustrate exemplary embodiments of the disclosed systems in which
like reference numerals refer to the same parts throughout the different drawings.
Components in the drawings are not necessarily to scale, emphasis instead being
placed upon clearly illustrating the principles of the present disclosure. Some
drawings may indicate the components using block diagrams and may not represent
the internal circuitry of each component. It will be appreciated by those skilled in the
art that disclosure of such drawings includes disclosure of electrical components,
electronic components or circuitry commonly used to implement such components.
Figure 1 illustrates a top view of the electro‐mechanical device, in accordance with
exemplary embodiments of the present disclosure.
Figure 2 illustrates a bottom view of the electro‐mechanical device, in accordance
with exemplary embodiments of the present disclosure.

6
Figure 3 illustrates a view of the first (i.e., lower) chamber of the electro‐mechanical
device, in accordance with exemplary embodiments of the present disclosure.
Figure 4 illustrates a view of the second (i.e., upper) chamber of the electro‐
mechanical device, in accordance with exemplary embodiments of the present
disclosure.
The foregoing shall be more apparent from the following more detailed description
of the disclosure.
DESCRIPTION OF THE INVENTION

In the following description, for the purposes of explanation, various specific details
are set forth in order to provide a thorough understanding of embodiments of the
present disclosure. It will be apparent, however, that embodiments of the present
disclosure may be practiced without these specific details. Several features described
hereafter can each be used independently of one another or with any combination of
other features. An individual feature may not address any of the problems discussed
above or might address only some of the problems discussed above. Some of the
problems discussed above might not be fully addressed by any of the features
described herein. Example embodiments of the present disclosure are described
below, as illustrated in various drawings in which like reference numerals refer to the
same parts throughout the different drawings.
The ensuing description provides exemplary embodiments only, and is not intended
to limit the scope, applicability, or configuration of the disclosure. Rather, the ensuing
description of the exemplary embodiments will provide those skilled in the art with
an enabling description for implementing an exemplary embodiment. It should be

7
understood that various changes may be made in the function and arrangement of
elements without departing from the spirit and scope of the disclosure as set forth.
Specific details are given in the following description to provide a thorough
understanding of the embodiments. However, it will be understood by one of ordinary
skill in the art that the embodiments may be practiced without these specific details.
For example, circuits, systems, networks, processes, and other components may be
shown as components in block diagram form in order not to obscure the
embodiments in unnecessary detail. In other instances, well‐known circuits,
processes, structures, and techniques may be shown without unnecessary detail in
order to avoid obscuring the embodiments.
The word “exemplary” and/or “demonstrative” is used herein to mean serving as an
example, instance, or illustration. For the avoidance of doubt, the subject matter
disclosed herein is not limited by such examples. In addition, any aspect or design
described herein as “exemplary” and/or “demonstrative” is not necessarily to be
construed as preferred or advantageous over other aspects or designs, nor is it meant
to preclude equivalent exemplary structures and techniques known to those of
ordinary skill in the art. Furthermore, to the extent that the terms “includes,” “has,”
“contains,” and other similar words are used in either the detailed description or the
claims, such terms are intended to be inclusive—in a manner similar to the term
“comprising” as an open transition word—without precluding any additional or other
elements.
As used herein, a “control unit” or “processor” or “processing unit” includes
processing unit, wherein processor refers to any logic circuitry for processing
instructions. A processor may be a general‐purpose processor, a special purpose

8
processor, a conventional processor, a digital signal processor, a plurality of
microprocessors, one or more microprocessors in association with a DSP core, a
controller, a microcontroller, Application Specific Integrated Circuits, Field
Programmable Gate Array circuits, any other type of integrated circuits, etc. The
processor may perform signal coding data processing, input/output processing,
and/or any other functionality that enables the working of the system according to
the present disclosure.
The present invention obviates the aforementioned drawbacks and deficiencies
associated with conventional unmanned aerial vehicles i.e., drones, by providing an
electro‐mechanical device (i.e., drone) having a closed structure. The electro‐
mechanical device as disclosed in the present disclosure is divided into two separate
chambers i.e., a lower chamber (or first chamber) and an upper chamber (or second
chamber). Also, said electro‐mechanical device comprises one or more propellers; a
control unit; one or more sensors; an energy storage unit; one or more valves; and a
plurality of pneumatic tubing with one or more flow control means. In an
embodiment, the electro‐mechanical device controls thrust and its direction of
movement with dual propellers (arranged in the lower chamber for pulling fluid (i.e.,
for e.g., air) inside the lower chamber), and operating servo valves (arranged on either
side from the four sides of the electro‐mechanical device).
More specifically, the first chamber of the electro‐mechanical device is a
pressurization chamber that acts as a thrust unit of the electro‐mechanical device
(i.e., the drone), where in this chamber the fluid is pulled in by the propellers and
generates thrust for levitation. The pressurization chamber also includes mechanism
to maintain and adjust the elevation of the drone. Additionally, the pressurization
chamber includes mechanism that helps in tilting the drone forward or backwards for

9
various use cases. Also, the second chamber of the electro‐mechanical device is a
control chamber that controls a direction of movement of the electro‐mechanical
device through side booster(s) provided on all four sides of the electro‐mechanical
device. More particularly, the side booster(s) are controlled by means of servo
valve(s) and by operating these servo valves the electro‐mechanical device can be
moved forward, backward, left, right and diagonally. The second chamber includes
electronic components/units such as including but not limited to a flight control unit
or various sensors to perform various operations.
Therefore, the present invention provides a novel electro‐mechanical device, that is
a novel unmanned aerial vehicle comprising of two chambers such that it overcomes
various limitations of the existing unmanned aerial vehicles/drones. This novel drone
is technically advanced over the currently known drones, as electrically operated
pneumatic servo valves used in this drone reduce the number of moving parts
required for the drone to operate. These pneumatic servo valves are also small in size,
and a more precise control can be achieved through these pneumatic servo valves as
compared to traditional multi‐rotor systems of flight. Also, the present invention is
technically advanced over the currently known UAVs as controlling a servo valve is a
matter of controlling a single electrical signal, versus a brushless dc motor (BLDC)
motor which requires a complex and expensive control system to operate.
Furthermore, the cost of pneumatic servo valve itself is orders of magnitude cheaper
than a motor and a rotor required for traditional multi‐rotor systems of flight.
Moreover, the present invention provides technical advancement due to an increased
reliability, mainly due to the overall simplification of the components and systems,
the reliability of the relatively cheap and easily available component being utilized by
the present electro‐mechanical device.

10
Hereinafter, exemplary embodiments of the present disclosure will be described in
detail with reference to the accompanying drawings so that those skilled in the art
can easily carry out the present disclosure.
Figure 1 illustrates a top view of the electro‐mechanical device, in accordance with
exemplary embodiments of the present disclosure. Also, a bottom view of the electro‐
mechanical device is illustrated in Figure 2, in accordance with exemplary
embodiments of the present disclosure. The electro‐mechanical device is a drone (i.e.,
a UAV) having a closed structure. More specifically, the electro‐mechanical device
comprises a housing unit defining a top surface [102], a bottom surface [104], a pair
of first vertical surfaces [106a‐106b] and a pair of second vertical surfaces [108a‐
108b]. In an embodiment, the housing unit is made of acrylonitrile butadiene styrene
(ABS) plastic, but the disclosure is not limited thereto and other materials as obvious
to a person skilled in the art may be used in different embodiments. Also, the housing
unit is divided into a first chamber [110] and a second chamber [112]. The housing
unit also defines one or more wiring ducts [134] (i.e., inter chamber wiring ducts as
shown in Figure 3 and Figure 4) on the pair of first vertical surfaces [106a‐106b] and
the pair of second vertical surfaces [108a‐108b], wherein each of the one or more
wiring ducts [134] comprises a sealant applied at an entry point in the first chamber
[110] and the second chamber [112]. Therefore, wiring ducts [134] are considered on
all four sides of the electro‐mechanical device for dressing the wires going from one
chamber to another and the sealant is used on the wiring entry points in the
chambers.
The electro‐mechanical device also comprises one or more propellers [114]; a control
unit [116]; one or more sensors [118]; an energy storage unit [120]; one or more
actuators; and a plurality of pneumatic tubing [122] with one or more flow control

11
means [124]. Although in the present disclosure, only a few units/components of the
electro‐mechanical device are shown or disclosed, however, the electro‐mechanical
device may comprise multiple such units/components or the electro‐mechanical
device may comprise any such numbers of said units/components, that are obvious
to a person skilled in the art to implement the features of the present disclosure.
Further, to provide the electro‐mechanical device with an improved performance and
to overcome the limitations of the existing electro‐mechanical devices i.e., existing
drones, the units/components of the electro‐mechanical device are arranged in
different chambers of the electro‐mechanical device, wherein such arrangement of
the units in the different chambers is based on a functionality of said units. For
instance, a separate chamber for the electronic components (i.e., upper chamber
[112]) ensures that the heat generated from the battery and motors (placed in the
lower chamber [110]) does not have an adverse effect in the long term. A view of the
first (i.e., lower) chamber of the electro‐mechanical device is illustrated in Figure 3, in
accordance with exemplary embodiments of the present disclosure. Also, a view of
the second (i.e., upper) chamber of the electro‐mechanical device is illustrated in
Figure 4, in accordance with exemplary embodiments of the present disclosure.
Also, as depicted in Figure 2 and Figure 3, the first (i.e., the lower) chamber [110] of
the electro‐mechanical device defines one or more first openings [126] on the bottom
surface [104] of the housing unit. The one or more first openings [126] are fluidly
communicating with the one or more propellers [114] housed within the first chamber
[110] to suck a fluid into the first chamber [110]. In an implementation the one or
more first openings [126] are equipped with one or more first valves for fluidly
communicating in an automatic manner with the one or more propellers housed
within the first chamber to suck the fluid into the first chamber. In an embodiment,

12
the propellers [114] may be driven by one or more BLDC motors in opposite
directions, with a basic speed control mode, this nullifies the impact of one propeller
on the other. Also, a sealing ring [138] may be placed on each of the one or more first
openings [126] to enable unidirectional fluid flow therethrough. As used herein the
term “fluid” is a substance that can flow smoothly, for instance in a preferred
embodiment the term “fluid” refers to air. Also, the first chamber [110] defines one
or more second openings [128] on the bottom surface [104] to controllably exhaust
the fluid from the first chamber [110], to generate lift, roll and pitch motion of the
electro‐mechanical device. In an implementation the one or more second openings
[128] are equipped with one or more second valves to controllably exhaust the fluid
in an automatic manner to generate the lift, roll and pitch motion. Additionally, the
first chamber [110] houses the energy storage unit [120] enabled to supply power at
least to the one or more sensors [118], the control unit [116] and the one or more
actuators coupled with one or more propellers [114]. The energy storage unit [120]
may be a lithium‐polymer (LiPo) battery, but the disclosure is not limited thereto and
the energy storage unit [120] may be such any other battery that is obvious to a
person skilled in the art. Also, the energy storage unit [120] and the BLDC
Motor(s)/actuator(s) are placed in the first chamber [110] to regulate heat generated
during operations of the electro‐mechanical device and to maintain balance of the
electro‐mechanical device, considering these are the heaviest components on board.

Therefore, the first chamber [110] acts as the thrust unit of the electro‐mechanical
device, where: the fluid (such as air) pulled in by the propeller(s) [114] generates
thrust for levitation, and elevation of the electro‐mechanical device is maintained and
adjusted by the fluid (such as air) flow from the openings (i.e., the one or more second
openings [128]) provided at the base plate with servo valve‐controlled louvres. The
present disclosure therefore discloses the use of valves to provide thrust instead of

13
propellors as are used in all the prior existing iterations of drones. In the present
disclosure while the propellor(s) [114] are used to pull in the fluid (such as air), the
actual thrust to provide lift and motion of the electro‐mechanical device is provided
by pneumatic servo valves that can be electrically controlled to provide a precise
amount of airflow needed to generate the thrust. Also, the fluid flow mechanism of
the first chamber [110] may also be used for tilting the electro‐mechanical device
forward or backwards for various use cases such as for capturing images from desired
angles etc.
Furthermore, Figure 1 depicts that the second chamber [112] is connected to the first
chamber [110]. Also, Figure 4 depicts that the second chamber [112] houses the
control unit [116] enabled to communicate with at least one of the one or more
sensors [118], the one or more actuators, the one or more first openings [126]
equipped with the one or more first valves, the one or more second openings [128]
equipped with the one or more second valves, and the one or more flow control
means [124]. In an implementation, the control unit [116] may be an advanced
PX4FMU card configured to ensure seamless flying experience of the electro‐
mechanical device. Also, each actuator from the one or more actuators is a brush‐less
direct current (BLDC) motor. The second chamber [112] also defines one or more pairs
of third openings [130a‐130b] (say first side boosters) on each of the pair of first
vertical surfaces [106a‐106b] to controllably exhaust the fluid to generate lateral
motion of the electro‐mechanical device. Also, the second chamber [112] defines one
or more pairs of fourth openings [132a‐132b] (say second side boosters) on each of
the pair of second vertical surfaces [108a‐108b] of the housing unit to controllably
exhaust the fluid to generate yaw and longitudinal motion of the electromechanical
device. In an implementation, the fluid flow from the first chamber [110] to the first
side boosters and/or the second side boosters may be controlled by means of one or

14
more servo valves. More specifically, the second chamber [112] houses the plurality
of pneumatic tubing [122] with the one or more flow control means [124] placed
therein such that the plurality of pneumatic tubing [122] receives the fluid from the
first chamber [110] and supplies the fluid to the one or more third openings [130a‐
130b] and the one or more fourth openings [132a‐132b] by controllably operating the
one or more flow control means [124]. In a preferred embodiment the flow control
means [124] is a servo valve. Therefore, the second chamber [112] controls the
direction of movement of the electro‐mechanical device through the first and/or
second side boosters provided on all four sides of the electro‐mechanical device.
Further, in an embodiment, the one or more flow control means [124] are adapted to
vary the volume of fluid exhausted from the one or more pairs of third openings
[130a‐130b] and the one or more pairs of fourth openings [132a‐132b]. Also, in an
embodiment the one or more flow control means [124] are adapted to vary
dimensions of the one or more pairs of third openings [130a‐130b] and one or more
pairs of fourth openings [132a‐132b], to control the movement of the electro‐
mechanical device. Therefore, in an implementation of the present disclosure, the
one or more servo valves control air flow for the one or more side booster openings
at each side of a drone, and by operating these servo valve(s) in combination or
individually, the drone may be moved forward, backward, left, right or diagonally.
In an embodiment, the housing unit of the electro‐mechanical device comprises one
or more mounting means [136] to mount and hold at least one of a payload and the
one or more sensors [118]. The one or more sensors [118] may include one or more
camera units, but the disclosure is not limited thereto and the sensors [118] may
include other sensors that are obvious to a person skilled in the art for different use
cases.

15
Furthermore, the electro‐mechanical device also comprises a communication unit
[140] for receiving and transmitting a signal. In an example, the communication unit
[140] may be a transceiver unit comprising a transmitter and a receiver for
transmitting and receiving signals, respectively, from an operating console on ground.
Moreover, a calculation of a force required to fly the electro‐mechanical device i.e.,
the drone in accordance with the implementation of the features of the present
disclosure is provided as below:
Let’s assume:
Drone MassൌM
g ൌ Acceraltion due to gravity
Aperture Radius Propeller ൌ R ሺi.e.,of 2 first openings ሾ126ሿሻ
Aperture Radius Thrust Boosters ൌ r ሺi.e.,of 4 second openings ሾ128ሿሻ
Input Propellor speed ൌ ω ሺvariableሻ
Exhaust Air flow Speed ൌ 𝑣 ሺControlled by modifying “r”ሻ
Further,
𝑃𝑟𝑜𝑝𝑒𝑙𝑙𝑒𝑟 𝐴𝑖𝑟 𝑓𝑙𝑜𝑤 𝑆𝑝𝑒𝑒𝑑 𝑓 ൌ 𝑘𝜔𝑅
Controlled by modifying “ω” and k is a design constant dependant on the aperture
size of the valve
𝐼𝑛𝑝𝑢𝑡 𝐴𝑖𝑟 – 𝑀𝑎𝑠𝑠 / 𝑢𝑛𝑖𝑡 𝑇𝑖𝑚𝑒 ൌ 2𝜋𝑅ଶ𝑓𝜌
𝑂𝑢𝑡𝑝𝑢𝑡 𝐴𝑖𝑟 – 𝑀𝑎𝑠𝑠/ 𝑢𝑛𝑖𝑡 𝑇𝑖𝑚𝑒 ൌ 4𝜋𝑟ଶ𝑣𝜌
𝑆𝑖𝑛𝑐𝑒 𝐼𝑛𝑝𝑢𝑡 𝑣𝑜𝑙𝑢𝑚𝑒 ൌ 𝑂𝑢𝑡𝑝𝑢𝑡 𝑉𝑜𝑙𝑢𝑚𝑒
⇒ 2𝑅ଶ𝑓 ൌ 4𝑟ଶ𝑣
⇒ 𝑣 ൌ 0.5𝑓
𝑅ଶ
𝑟ଶ

16
⇒ 𝑣 ൌ 0.5𝑘𝜔
𝑅ଷ
𝑟ଶ
Mass ሺmሻ ൌ ρV ሺi.e., Air density * volumeሻ
Momentum ൌ mv ሺi.e., mass * velocityሻ
Therefore, force generated (F) by exhaust, given k, ω, R & r are fixed is:
𝐹 ൌ 𝑑ሺ𝑚𝑣ሻ
𝑑𝑡 ൌ
𝑑ሺρV𝑣ሻ
𝑑𝑡 ൌ ρ𝑣
𝑑V
𝑑𝑡
And propeller downward pull (P) due to pulling in air is given by
𝑃 ൌ 𝑑ሺ𝑚𝑣ሻ
𝑑𝑡 ൌ
𝑑ሺρVfሻ
𝑑𝑡 ൌ ρf
𝑑V
𝑑𝑡
Furthermore ௗ௏
ௗ௧ is the volume of air being pulled in or pushed out per unit of time,
hence
𝑑𝑉
𝑑𝑡 ൌ 𝑐𝑅𝜔
where c is a design constant dependent on the design of the propellors.
Hence the drone flies if:
𝐹 ൐ 𝑃 ൅ 𝑀𝑔
⇒ ρ𝑣
𝑑V
𝑑𝑡 ൌ ρf
𝑑V
𝑑𝑡 ൅ 𝑀𝑔
⇒ Mg ൏ ρ
𝑑V
𝑑𝑡 ሺ𝑣 െ 𝑓ሻ
⇒ Mg ൏ ρcRωሺ0.5𝑘𝜔
𝑅ଷ
𝑟ଶ െ 𝑘𝑅𝜔ሻ
⇒ Mg ൏ ρc𝑘Rଶωଶሺ0.5
𝑅ଶ
𝑟ଶ െ 1ሻ

17
Thus, the present invention provides a novel electro‐mechanical device, that is a novel
unmanned aerial vehicle comprising of two chambers such that it overcomes various
limitations of the existing unmanned aerial vehicles/drones. This novel drone is
technically advanced over the currently known drones, as electrically operated
pneumatic servo valves used in this drone reduce the number of moving parts
required for the drone to operate. These pneumatic servo valves are also small in size,
and a more precise control can be achieved through these pneumatic servo valves as
compared to traditional multi‐rotor systems of flight. Also, the present invention is
technically advanced over the currently known UAVs as controlling a servo valve is a
matter of controlling a single electrical signal, versus a brushless dc motor (BLDC)
motor which requires a complex and expensive control system to operate.
Furthermore, the cost of pneumatic servo valve itself is orders of magnitude cheaper
than a motor and a rotor required for traditional multi‐rotor systems of flight.
Moreover, the present invention provides technical advancement due to an increased
reliability, mainly due to the overall simplification of the components and systems,
the reliability of the relatively cheap and easily available component being utilized by
the present electro‐mechanical device.
While considerable emphasis has been placed herein on 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 invention. These and other changes in the preferred embodiments of the
invention 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 to be
implemented merely as illustrative of the invention and not as limitation.

18
I/We Claim:
1. An electro‐mechanical device, the electro‐mechanical device comprising: a
housing unit defining a top surface [102], a bottom surface [104], a pair of first
vertical surfaces [106a‐106b] and a pair of second vertical surfaces [108a‐
108b], such that the housing unit is divided into a first chamber [110] and a
second chamber [112]; one or more propellers [114]; a control unit [116]; one
or more sensors [118]; an energy storage unit [120]; one or more actuators;
and a plurality of pneumatic tubing [122] with one or more flow control means
[124] placed therein; such that:
‐ the first chamber [110]:
defines one or more first openings [126] on the bottom surface [104]
of the housing unit and fluidly communicating with the one or more
propellers [114] housed within the first chamber [110] to suck a fluid
into the first chamber [110];
defines one or more second openings [128] on the bottom surface
[104] to controllably exhaust a fluid to generate lift, roll and pitch
motion; and
houses the energy storage unit [120] enabled to supply power to one
or more sensors [118], the control unit [116] and one or more
actuators coupled with one or more propellers [114].
2. The electro‐mechanical device as claimed in claim 1, wherein the one or more
first openings [126] are equipped with one or more first valves.
3. The electro‐mechanical device as claimed in claim 1, wherein the one or more
second openings [128] are equipped with one or more second valves.
4. The electro‐mechanical device as claimed in claim 1, wherein the second
chamber [112] connected to the first chamber [110]:

19
houses the control unit [116] enabled to communicate with at least
one of the one or more sensors [118], the one or more actuators, the
one or more first openings [126] equipped with the one or more first
valves, the one or more second openings [128] equipped with the one
or more second valves, and the one or more flow control means [124];
defines one or more pairs of third openings [130a‐130b] on each of the
pair of first vertical surfaces [106a‐106b] to controllably exhaust the
fluid to generate lateral motion of the electro‐mechanical device;
defines one or more pairs of fourth openings [132a‐132b] on each of
the pair of second vertical surfaces [108a‐108b] of the housing unit to
controllably exhaust the fluid to generate yaw and longitudinal motion
of the electromechanical device; and
houses the plurality of pneumatic tubing [122] with the one or more
flow control means [124] placed therein such that the plurality of
pneumatic tubing [122] receives the fluid from the first chamber [110]
and supplies the fluid to the one or more third openings [130a‐130b]
and the one or more fourth openings [132a‐132b] by controllably
operating the flow control means [124].
5. The electro‐mechanical device as claimed in claim 1, wherein the housing unit
also defines one or more wiring ducts [134] on the pair of first vertical surfaces
[106a‐106b] and the pair of second vertical surfaces [108a‐108b], and wherein
each of the one or more wiring ducts [134] comprises a sealant applied at an
entry point in the first chamber [110] and the second chamber [112].
6. The electro‐mechanical device as claimed in claim 1, wherein the housing unit
comprises one or more mounting means [136] to mount and hold at least one
of a payload and the one or more sensors [118].

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7. The electro‐mechanical device as claimed in claim 6, wherein the one or more
sensors [118] are one or more camera units.
8. The electro‐mechanical device as claimed in claim 1, wherein the flow control
means [124] is a servo valve.
9. The electro‐mechanical device as claimed in claim 4, wherein the flow control
means [124] is adapted to vary the volume of fluid exhausted from the one or
more pairs of third openings [130a‐130b] and the one or more pairs of fourth
openings [132a‐132b].
10. The electro‐mechanical device as claimed in claim 4, wherein the flow control
means [124] is adapted to vary dimensions of the one or more pairs of third
openings [130a‐130b] and one or more pairs of fourth openings [132a‐132b].
11. The electro‐mechanical device as claimed in claim 1, wherein the actuator is a
brush‐less direct current (BLDC) motor.
12. The electro‐mechanical device as claimed in claim 1, wherein the housing unit
is made of acrylonitrile butadiene styrene (ABS) plastic.
13. The electro‐mechanical device as claimed in claim 1 comprising a sealing ring
[138] placed on each of the one or more first openings [126] to enable
unidirectional fluid flow therethrough.
14. The electro‐mechanical device as claimed in claim 1, wherein the energy
storage unit [120] is a lithium‐polymer (LiPo) battery.
15. The electro‐mechanical device as claimed in claim 1 comprising a
communication unit [140] for receiving and transmitting a signal.