TECHNICAL FIELD

[0001] The present disclosure generally relates to the field of Aerial vehicles. In particular, it pertains to camera control mechanism in an aerial vehicle that enables pan and tilt movements of the camera as also movement of the camera between its deployed and retracted positions.

BACKGROUND

[0002] The background description includes information that may be useful in understanding the present invention. It is not an admission that any of the information provided herein is prior art or relevant to the presently claimed invention, or that any publication specifically or implicitly referenced is prior art.

[0003] Aerial Vehicles including Unmanned Aerial Vehicles (UAVs) are well known in the art. Many such vehicles are required to carry a camera as pay load for reconnaissance purposes including military applications (for reconnaissance and attack) as well as civil applications such as firefighting, police observation of civil disturbances and scenes of crimes, and reconnaissance support in natural disasters. Under many such applications, UAVs may be a preferred choice to mitigate risk to human life.

[0004] However, configuration of a camera as payload in a UAV has to take into consideration weight and maneuverability of the camera. Weight of a UAV is a critical parameter in its overall effectiveness, and one of the major goals of UAV design is to reduce the weight of the vehicle. Therefore, it is desirable to minimize weight of the camera and associated camera assembly. It should also be movable to provide coverage to targeted area as well as move to a retracted position within belly of the aircraft fuselage during take-off and landing.

[0005] Conventionally for retracting of camera payload and its pan and tilt rotation in an

Aerial Vehicle, at least three actuators are used one for each of the three movements that leads to complicated mechanism and higher weight.

[0006] United States Patent number US9309006 discloses a gimbaled pan and tilt camera payload assembly that moves about a pivot point/axis or hinge to retract within the housing. Thus, it incorporates three separate mechanisms for pan, tilt, and retraction movements. [0007] United States Patent numbers US7841783, US8000588 and US8137007 disclose a camera mounting assembly that provides tilt and pan of a camera, and the camera assembly is mounted on an extension/retraction assembly to retract the camera unit when desired. Thus the cited patent reference also includes a separate mechanisms for retraction movements besides pan and tilt mechanisms.

[0008] United States Patent number US 8140200 discloses a turret assembly for a payload such as a camera payload that incorporates a gimbal system to carry the payload. The gimbal system includes a first support coupled to a first actuator to rotate about a first axis, and a second support carried by the first support and coupled to a second actuator to rotate about a second axis generally transverse to the first axis. The cited patent reference does not provide for any retraction mechanism for the payload as it proposes to protect the payload during landing by one or more protective portions carried by housing of the payload and positioned to engage ground or another external structure during landing operations.

[0009] Thus, it can be seen that conventionally, if a camera payload in an Aerial Vehicle is to be retracted for preventing any damage during landing or take-off, a separate mechanism for retraction movements of camera is provided besides pan and tilt mechanisms. This makes system for belly mounted retracted camera payload complicated and heavy.

[00010] Hence, there is a need in the art for a camera payload control mechanism in Aerial Vehicles that allows for a retractable compact camera with less number of actuators/mechanisms to provide retraction, pan and tilt rotation for reduced weight, simpler retracting mechanism and better reliability.

[00011] All publications herein are incorporated by reference to the same extent as if each individual publication or patent application were specifically and individually indicated to be incorporated by reference. Where a definition or use of a term in an incorporated reference is inconsistent or contrary to the definition of that term provided herein, the definition of that term provided herein applies and the definition of that term in the reference does not apply.

[00012] In some embodiments, the numbers expressing quantities of ingredients, properties such as concentration, reaction conditions, and so forth, used to describe and claim certain embodiments of the invention are to be understood as being modified in some instances by the term "about." Accordingly, in some embodiments, the numerical parameters set forth in the written description and attached claims are approximations that can vary depending upon the desired properties sought to be obtained by a particular embodiment. In some embodiments, the numerical parameters should be construed in light of the number of reported significant digits and by applying ordinary rounding techniques. Notwithstanding that the numerical ranges and parameters setting forth the broad scope of some embodiments of the invention are approximations, the numerical values set forth in the specific examples are reported as precisely as practicable. The numerical values presented in some embodiments of the invention may contain certain errors necessarily resulting from the standard deviation found in their respective testing measurements.

[00013] As used in the description herein and throughout the claims that follow, the meaning of "a," "an," and "the" includes plural reference unless the context clearly dictates otherwise. Also, as used in the description herein, the meaning of "in" includes "in" and "on" unless the context clearly dictates otherwise.

[00014] The recitation of ranges of values herein is merely intended to serve as a shorthand method of referring individually to each separate value falling within the range. Unless otherwise indicated herein, each individual value is incorporated into the specification as if it were individually recited herein. All methods described herein can be performed in any suitable order unless otherwise indicated herein or otherwise clearly contradicted by context. The use of any and all examples, or exemplary language (e.g. "such as") provided with respect to certain embodiments herein is intended merely to better illuminate the invention and does not pose a limitation on the scope of the invention otherwise claimed. No language in the specification should be construed as indicating any non-claimed element essential to the practice of the invention.

[00015] Groupings of alternative elements or embodiments of the invention disclosed herein are not to be construed as limitations. Each group member can be referred to and claimed individually or in any combination with other members of the group or other elements found herein. One or more members of a group can be included in, or deleted from, a group for reasons of convenience and/or patentability. When any such inclusion or deletion occurs, the specification is herein deemed to contain the group as modified thus fulfilling the written description of all Markush groups used in the appended claims.

OBJECTS OF THE INVENTION

[00016] A general object of the present disclosure is to provide a simple, lighter, cost effective and reliable mechanism for pan, tilt and retraction movements of a belly-mounted retractable payload in an Aerial Vehicle that additionally improves performance of the Aerial Vehicle.

[00017] An object of the present disclosure is to provide a payload control mechanism for Aerial Vehicles that provides pan, tilt and retraction movements with reduced number of actuators and corresponding mechanisms.

[00018] Another object of the present disclosure is to provide retraction movement of payload by one of pan and tilt mechanisms so as to reduce number of actuators and corresponding mechanisms.

[00019] Another object of the present disclosure is to provide retraction movement of payload by one of pan and tilt mechanisms without compromising the pan and tilt movements of camera payload.

[00020] Another object of the present disclosure is to provide a payload control system that causes only a small portion of the payload to protrude out of Aerial Vehicle fuselage thereby minimizing aerodynamic impact of the protruding payload on the Aerial Vehicle.

SUMMARY

[00021] Aspects of the present disclosure relate to a payload system mounted in belly of fuselage of an Ariel Vehicle. In particular, the present disclosure pertains to an improved control system for the belly mounted retractable payload, such as a camera payload, that enables retraction, pan and tilt movements of the payload. Specifically, the disclosed control mechanism for the belly mounted retractable payload provides retraction, pan and tilt movements for the payload with reduced number of actuators and corresponding mechanisms. The disclosed control mechanism thus reduces weight, cost and complication; and in the process also improves performance of the Aerial Vehicle by minimizing projection of the payload out of the belly thereby reducing aerodynamic impact of the protruding payload on the Aerial Vehicle.

[00022] In an aspect, the disclosed control system for retraction, pan and tilt movements of a retractable belly mounted payload in an Aerial vehicle comprises: a first mechanism to rotate the payload about a vertical axis (also referred to as first axis) for the pan movement of the payload; and a second mechanism to rotate the payload about a horizontal axis (also referred to as second axis). In an aspect, the rotation of the payload about the horizontal axis provides movement of the payload between a retracted position within belly of the Aerial Vehicle and a deployed position out of the belly of the Aerial Vehicle; and also provides the tilt movement of the payload in its deployed position. Thus the disclosure provides a control system that enables retraction, pan and tilt movements using only two mechanisms and associated actuators as against three used in conventional system to meet similar objectives.

[00023] In an aspect, retraction movement and tilt movement of payload by a single mechanism is achieved by mounting the payload about second axis in an offset manner such that the payload is fully within belly of Aerial Vehicle i.e. in retracted position when the second mechanism is in a zero position; and when the payload is rotated about the second axis, it partly projects out of fuselage belly of Aerial Vehicle without having to lower the system that otherwise would have required a third mechanism with associated actuator. In an aspect, the payload, the horizontal axis and the offset are configured such that when the payload partly projects out of fuselage belly of Aerial Vehicle, its functional part is positioned out of fuselage thereby putting it in its deployed position.

[00024] In an embodiment, the payload can be a camera and its functional part that needs to come out of belly can be lens aperture; and its deployed position can correspond to position of the camera when the lens is out of the belly with clear line of sight for the camera to capture images. The line of sight of the camera can be horizontally oriented in retracted position of the camera, and the lens can be fully out of the fuselage up to a rotation of 180 degrees thereby providing a clear line of sight for the camera to capture images. In an aspect, rotation of the camera by the second mechanism to positions at less than 180 degrees provides the tilt movements to the camera payload.

[00025] In an aspect, the first mechanism incorporates a mounting bracket configured to be fixed to Aerial Vehicle within its belly; a payload casing configured to rotate relative to the mounting bracket along a vertically oriented first axis; a transmission mechanism comprising a drive member driven by a first servo motor and a driven member and a driven member fixed to the mounting bracket concentric to the first axis. The drive member and the first servo motor are mounted on the payload casing; and are configured for planetary rotation about the driven member and in the process rotate the casing about the first axis; wherein the first axis is vertically oriented and provides the pan movement to the payload mounted on the payload casing.

[00026] In an embodiment, the transmission mechanism can be a set gears comprising a pinion working as driven member and fixed to the mounting bracket, and a drive gear working as drive member and fixed to first servo motor. [00027] In an alternate embodiment, the transmission mechanism can be a is a pulley and belt mechanism comprising a driven pulley working as driven member and fixed to the mounting bracket, and a drive pulley working as drive member.

[00028] In an aspect, payload is pivotally mounted on payload casing for rotation about a horizontally oriented second axis (i.e. perpendicular to the first axis) to work as second mechanism. Rotation of the payload about the second axis provides movement of the payload between a retracted position within belly of the Aerial Vehicle and a deployed position out of the belly of the Aerial Vehicle; and as explained above the rotation of the payload about the horizontally oriented second axis also provides the tilt movement of the payload in its deployed position.

[00029] In an aspect, the control system further includes a second servo motor mounted on the payload casing and directly coupled to the payload to rotate the payload about the second axis, and works as actuator for second mechanism.

[00030] In an aspect, payload casing remains fully within fuselage of Aerial Vehicle and does not have any linear/translatory movement to retract or project out of the fuselage.

[00031] In an aspect, mounting bracket is mounted within the belly of the Aerial Vehicle by suitably positioned hardware. In an aspect, the mounting bracket and payload casing incorporate spring loaded contacts to provide electrical connectivity between the Aerial Vehicle and the payload casing for the first servo motor and the second servo motor even as the payload casing rotates about the first axis.

[00032] In an aspect, proposed control system using just two mechanisms for retraction, pan and tilt movements of a payload in an Aerial Vehicle, does not in any way restrict pan and tilt capabilities of the payload. For example, pan movement of 360 degrees can be achieved by suitable selection of pinion and drive gear sizes even with first servo motor having limited range of rotation. Likewise, retraction and tilt movement requiring 180 degrees rotation by second mechanism can be easily achieved with directly coupled servo motor having at least 180 degrees range of rotation. The pan movement of 360 degrees coupled with tilt movement from horizontal orientation at 180 degrees (from zero or retracted position) to a position less than 90 degrees (vertical position) by second mechanism can enable the payload, such as a camera payload, to cover complete lower hemispherical space below the Aerial Vehicle.

[00033] In an aspect, reduced number of mechanisms and actuators result in reduced weight and cost as also improved reliability of the system. Further, only partial projection of the payload out of fuselage of Aerial Vehicle also results in reduced aerodynamic drag on the Aerial Vehicle thereby improving its performance.

[00034] Various objects, features, aspects and advantages of the present disclosure will become more apparent from the following detailed description of preferred embodiments, along with the accompanying drawing figures in which like numerals represent like features.

BRIEF DESCRIPTION OF DRAWINGS

[00035] The accompanying drawings are included to provide a further understanding of the present disclosure, and are incorporated in and constitute a part of this specification. The drawings illustrate exemplary embodiments of the present disclosure and, together with the description, serve to explain the principles of the present disclosure.

[00036] FIG.1 illustrates an exemplary schematic arrangement of a payload and its control system within fuselage of an Aerial Vehicle with payload in accordance with an exemplary embodiment of the present disclosure.

[00037] FIG. 2 illustrates an exemplary exploded view of fuselage of an Aerial Vehicle and payload along with its control system in accordance with an exemplary embodiment of the present disclosure.

[00038] FIG. 3 illustrates an exemplary schematic view of camera payload control system along with a camera showing its mounting parts in accordance with embodiments of the present disclosure.

[00039] FIG. 4 illustrates an exemplary schematic arrangement of different parts of control system in accordance with embodiments of the present disclosure.

[00040] FIG. 5A and 5B illustrate exemplary side and top views of an alternate arrangement for pan motor in accordance with an embodiment of the present disclosure.

[00041] FIG. 6A and 6B illustrate exemplary side and top views of yet another alternate arrangement for pan motor in accordance with an embodiment of the present disclosure.

[00042] FIG. 7A and 7B illustrate working of pinion and drive gear to rotate payload casing for pan movement in accordance with an exemplary embodiment of the present disclosure. [00043] FIG. 8 illustrates rotation of camera payload about second axis for retraction and tilt movements of the camera in accordance with an exemplary embodiment of the present disclosure.

DETAILED DESCRIPTION

[00044] The following is a detailed description of embodiments of the disclosure depicted in the accompanying drawings. The embodiments are in such detail as to clearly communicate the disclosure. However, the amount of detail offered is not intended to limit the anticipated variations of embodiments; on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the present disclosure as defined by the appended claims.

[00045] Each of the appended claims defines a separate invention, which for infringement purposes is recognized as including equivalents to the various elements or limitations specified in the claims. Depending on the context, all references below to the "invention" may in some cases refer to certain specific embodiments only. In other cases it will be recognized that references to the "invention" will refer to subject matter recited in one or more, but not necessarily all, of the claims.

[00046] Various terms as used herein. To the extent a term used in a claim is not defined, it should be given the broadest definition persons in the pertinent art have given that term as reflected in printed publications and issued patents at the time of filing.

[00047] Embodiments explained herein pertain to an improved control system for a payload mounted in belly of fuselage of an Ariel Vehicle that enables retraction, pan and tilt movements of the payload. Specifically, the disclosed control mechanism for the belly mounted retractable payload provides retraction, pan and tilt movements for the camera with reduced number of actuators and corresponding mechanisms; thereby reducing weight, cost and complication. In an embodiment, the payload in its deployed position projects out of the belly only partially there by reduces aerodynamic impact of the protruding payload on the Aerial Vehicle with corresponding improvement in performance of the Aerial Vehicle.

[00048] It is to be appreciated that term retraction movement has been used in the present disclosure to mean movement of payload between a retracted position and a deployed position in either direction and is not limited to movement to the retracted position. [00049] It is to be further appreciated that while various embodiments have been explained herein with reference to a camera payload, they with suitable modifications that would be evident to those skilled in art, can as well be applied with other types of payloads; and all such applications are well within the scope of the present disclosure without any limitations whatsoever.

[00050] In an aspect, the disclosed control system for retraction, pan and tilt movements of a retractable belly mounted camera payload in an Aerial vehicle is based on two mechanisms - a first mechanism to rotate the payload about a vertically oriented first axis for the pan movement of the payload, and a second mechanism to rotate the payload about a horizontally oriented second axis for retraction and tilt movements of the camera payload. In an aspect, the rotation of the camera payload about the second axis provides movement of the payload between a retracted position within belly of the Aerial Vehicle and a deployed position out of the belly of the Aerial Vehicle, as well as the tilt movement of the payload in its deployed position

[00051] In an embodiment, retraction movement and tilt movement of payload by a single mechanism is achieved by mounting the camera payload about second axis in an offset manner such that when the second mechanism is in a zero position, the camera payload along with its lens aperture and line of sight is fully within belly of Aerial Vehicle i.e. in retracted position. On the other hand, when the camera payload is rotated about the second axis, it partly projects out of fuselage belly of Aerial Vehicle such that its functional part i.e. its lens aperture and line of sight are positioned out of fuselage thereby putting it in its deployed position.

[00052] In an embodiment, line of sight of the camera can be horizontally oriented in retracted position of the camera, and the lens can be fully out of the fuselage up to a rotation of 180 degrees thereby providing a clear line of sight for the camera to capture images. In an aspect, rotation of the camera by the second mechanism to positions at less than 180 degrees from retracted position can provide the tilt movements to the camera payload.

[00053] In an aspect, the first mechanism can incorporate: a mounting bracket configured to be fixed to Aerial Vehicle within its belly; a payload casing configured to rotate relative to the mounting bracket along vertically oriented first axis; a transmission mechanism comprising a drive member driven by a first servo motor and a driven member and a driven member fixed to the mounting bracket concentric to the first axis. The drive member and the first servo motor are mounted on the payload casing and are configured for planetary rotation about the driven member and in the process rotate the casing about the first axis; The transmission mechanism can be a set of gears or pulley bet arrangement

[00054] In an aspect, payload can be pivotally mounted on payload casing for rotation about horizontally oriented second axis to work as second mechanism, and a second servo motor working as actuator can be mounted on the payload casing and directly coupled to the camera payload to rotate the camera about the second axis.

[00055] In an aspect, mounting bracket can be mounted within belly of Aerial Vehicle by hardware. In an aspect, the mounting bracket and payload casing incorporate spring loaded contacts to provide electrical connectivity between the Aerial Vehicle and the payload casing for the first servo motor and the second servo motor even as the payload casing rotates about first axis.

[00056] In an aspect, proposed control system using just two mechanisms for retraction, pan and tilt movements of a payload in an Aerial Vehicle, does not in any way restrict pan and tilt capabilities of the payload. For example pan movement of 360 degrees can be achieved by suitable selection of pinion and drive gear sizes even with first servo motor having limited range of rotation. Likewise, retraction and tilt movement requiring 180 degrees rotation by second mechanism can be easily achieved with directly coupled servo motor having at least 180 degrees range of rotation. The pan movement of 360 degrees coupled with tilt movement from horizontal orientation at 180 degrees (from zero or retracted position) to a position less than 90 degrees (vertical position) by second mechanism can enable the camera payload to cover complete space below the Aerial Vehicle.

[00057] FIG. l illustrates an exemplary schematic arrangement of payload and its control system within fuselage of an Aerial Vehicle with payload in accordance with an exemplary embodiment of the present disclosure. The control system and payload assembly 104 can be housed within belly of fuselage 102 of an Aerial Vehicle. Shown herein is fully retracted position of the payload such that nothing projects out of fuselage belly.

[00058] FIG. 2 illustrates an exemplary exploded view of control system and payload assembly 104, and fuselage 102 of an Aerial Vehicle in accordance with an exemplary embodiment of the present disclosure. As shown the control system and payload assembly 104can include a control system 202 and a payload such as a camera payload 204 (also referred simply as camera 204). In an aspect, the control system 202 remains within belly under both deployed and retracted positions of the camera payload 204 and can provide a rotary pan movement to the camera payload 204 by rotation within the belly of the fuselage 102. The control system 202 can also provide rotary movement to the camera payload 204 about a horizontal axis, wherein the rotary movement about the horizontal axis (from a zero position that corresponds to retracted position as shown in FIG. 2) causes the camera payload 204 to move to deployed position as well as tilt movement. Reverse rotation of the camera payload 204 can move the camera 204 back to retracted position shown in FIG. 2.

[00059] FIG. 3 illustrates an exemplary schematic view of payload control system 202 along with a camera payload 204 showing its mounting parts in accordance with an embodiment of the present disclosure. In an embodiment, the control system 202 can include a mounting bracket 302 and a payload casing 304 (also referred to simply as casing 304) configured to rotate relative to the mounting bracket 302 along a vertically oriented first axis such as axis Y-Y. The mounting bracket 302 can be configured to be fixed to Aerial Vehicle within its belly by means of hardware such as 306 located suitably. The mounting bracket 302 and casing 304 can incorporate spring loaded contacts 308 to provide electrical connectivity between the Aerial Vehicle and different actuators located within the casing 304 even as the casing 304 rotates about first axis.

[00060] In an embodiment, camera payload 204 can be pivotally mounted within casing 304 for rotation about a horizontal axis (not shown here). The camera payload 204 can be within the casing 304 in a zero position corresponding to retracted position as shown in FIG. 3, such that line of sight LS of the camera payload 204 passing through its lens aperture 310 is in horizontal orientation and within the casing 304.

[00061] FIG. 4 illustrates an exemplary schematic arrangement showing further details of different parts of control system 202 in accordance with embodiments of the present disclosure. Shown herein are details of first mechanism that provides rotational movement to casing 304 about vertically oriented first axis Y-Y and thereby pan movement of camera 204; and second mechanism that provides rotational movement to the camera 204 about horizontally oriented second axis (shown as X-X in FIG. 4) for retraction as well as tilt movements. The first mechanism can include a pinion gear 402 fixed to mounting bracket 302 concentric to the first axis Y-Y, a drive gear 404 in engagement with the pinion gear 402 and driven by a first servo motor 406. The drive gear 404 and the first servo motor can be mounted on the casing 304 and configured for planetary rotation about the pinion gear 402 and in the process rotate the casing 304 about the first axis Y-Y. In an embodiment, using a slip ring can provide 360 degrees continuous pan motion.

[00062] In an alternate embodiment in respect of first mechanism, there can be a set of two pulleys in place of set of pinion gear 402 and drive gear 404 as shown in exemplary side view and top view illustrated in FIG. 5A and 5B respectively. The set of pulleys can comprise a smaller pulley 502 connected to a brushless motor508 that is mounted on casing 304 and electrically powered through a slip-ring electrical contact 510. A second larger pulley 504 can be fixed to the mounting bracket 302 (not shown here) concentric to the first axis Y-Y that works as pan axis. The set of smaller pulley 502 and larger pulley 504 can be connected by a flexible belt 506 which can be any of different types of transmission belts such as but not limited to timing belt, friction belt, flat belt, V-belt etc.

[00063] In an embodiment, the pulley-belt configuration may use open-belt configuration as shown in FIG. 5B, or crossed-belt configuration (not shown). In the open-belt configuration the casing 304 shall rotate in same direction as direction of rotation of the brushless motor 508, whereas in the crossed-belt configuration direction of rotation of the casing 304 shall be opposite to that of the brushless motor 508. Thus if the brushless motor 508 rotates in clockwise direction, depending on the open-belt configuration or the crossed-belt configuration, the casing/ payload can make continuous 360 degrees panning rotation in clockwise or anticlockwise direction, enabling continuous 360 degrees panning of the payload.

[00064] In an aspect, with the proposed embodiment, it is possible to meet torque required for pan movement with a brushless motor of any torque rating, i.e. high or low rating, by suitable selection of sizes of the pulleys 502/504 to get a suitable reduction ratio. Thus, the embodiment enables use of a low torque lightweight motor. In addition, it also provides continuous 360degrees pan rotation. In an exemplary embodiment, reduction ratio of 1.6: 1 is used for the brushless motor to provide required torque to rotate payload pan to continuous 360degrees.

[00065] FIG. 6A and 6B illustrate exemplary side and top views of yet another embodiment of the first mechanism, wherein a brushless motor 602 can be directly mounted concentrically to the first axis Y-Y that works as pan axis and coupled to the casing 304. Since the brushless motor 602 is connected directly to the casing/payload, there is no scope of changing output torque of the motor to meet the requirement, and therefore a high torque motor that meets the torque requirement is to be used. Further, since the brushless motor 602 is connected directly to the casing/payload it rotates the payload 360degrees continuously. [00066] FIG. 4 further shows mounting of camera payload 204 within casing 304 about second axis X-X and working of second mechanism. As stated earlier rotary movement of the camera payload 204 about the horizontal axis X-X from a zero position that corresponds to retracted position as shown in FIG. 2 as well as in FIG. 3 and 4, causes the camera payload 204 to move to deployed position as well as provides tilt movement. In an aspect, retraction movement and tilt movement of camera payload 204 by a single second mechanism is achieved by mounting the camera payload 204 such that there is an offset between the second axis X-X and the line of sight LS of the camera 204 as shown in FIG. 4. In an embodiment, the lens aperture 310 and line of sight LS can be located above the second axis X-X so that when the camera payload 204 is rotated about the second axis X-X by 180 degrees, the lens aperture 310 and line of sight LS move below the axis X-X to a position projecting out of the casing 304 and belly of fuselage 102 bringing the camera to a deployed position. In an embodiment, the offset causes the camera payload 204 to only partly projects out of casing and fuselage belly of Aerial Vehicle as shown in FIG. 7B and 8.

[00067] In the preferred embodiment shown in FIG. 7B, pan position of 0 degree can be defined as front looking position in direction of flight, 0 to +90 degree can be towards right and 0 to -180 degree can be towards left of Aerial Vehicle. However, direction can be reversed depending on requirement.

[00068] In an aspect, rotation of the camera204 by the second mechanism to positions at less than 180 degrees provides the tilt movements to the camera payload 204. Thus a single second mechanism can provide retraction movement in addition to tilt movements to the camera payload 204without having to lower the system that otherwise would have required a third mechanism with associated actuator.

[00069] In an embodiment, the second mechanism can further include a second servo motor 408 directly coupled to the camera payload 204 to provide rotational movement to the camera payload 204. As the second mechanism is required to move the camera payload 204 at most by 180 degrees, a servo motor having 180 degrees range of rotation can be used to meet the requirement.

[00070] FIG. 7A illustrates top view of first mechanism showing working of pinion gear 402 and drive gear 404 to rotate payload casing 304 for pan movement in accordance with an exemplary embodiment of the present disclosure. In an aspect, the sizes of the pinion gear 402 and the drive gear 404 can be selected based on amount of pan movement required and range of rotation of first servo motor 406. For example if the first servo motor 406 has a range of 180 degrees and pan rotation required is 360 degrees, the drive gear 404 and the pinion gear 402 can have a ratio of 2: 1. In a preferred embodiment where the range of rotation of the first servo motor 406 is 180 degrees and pan movement required is 270 degrees, ratio of the drive gear 404 and the pinion gear 402 have been selected with a ratio of 1.6: 1. The preferred embodiment is shown in FIG. 7B wherein 0 degree of pan position is front looking in the direction of flight, 0 to +90degree is towards right and 0 to -180degree is towards left of Aerial Vehicle.

[00071] FIG. 8 illustrates extent of rotation of camera payload about second axis for retraction and tilt movements of the camera in accordance with a preferred embodiment of the present disclosure. As shown 180 degrees rotation of the camera 204 about X-X axis from its zero position makes it to look towards front inline of Aerial Vehicle. Rotation of 90 degrees from its zero position makes the camera look vertically downward direction perpendicular to fuselagel02 of the Aerial Vehicle. FIG. 8 further shows partially projected position of the camera 204 below casing 304 which can enable installation of the complete payload system in fuselage 102 such that the camera 204 projects out of the fuselage 102 only partially. Only partial projection of the camera 204 out of fuselage 102 of Aerial Vehicle also results in reduced aerodynamic drag on the Aerial Vehicle thereby improving its performance.

[00072] Thus, the present disclosure provides a control system for a payload such as a camera payload for Aerial Vehicles that can enable retraction, pan and tilt movements using just two mechanisms and associated servos, thereby reducing weight, cost and complications with corresponding improvement in performance of the Aerial Vehicle. Performance of the Aerial Vehicle is further improved by reduced aerodynamic impact of the protruding payload on the Aerial Vehicle on account of only partial projection of the payload out of fuselage 102 in its deployed position.

[00073] While the foregoing describes various embodiments of the invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof. The scope of the invention is determined by the claims that follow. The invention is not limited to the described embodiments, versions or examples, which are included to enable a person having ordinary skill in the art to make and use the invention when combined with information and knowledge available to the person having ordinary skill in the art. ADVANTAGES OF THE INVENTION

[00074] The present disclosure provides a simple, lighter, cost effective and reliable mechanism for pan, tilt and retraction movements of a belly-mounted retractable camera payload in an Aerial Vehicle that additionally improves performance of the Aerial Vehicle.

[00075] The present disclosure provides a camera payload control mechanism for Aerial Vehicles that provides pan, tilt and retraction movements with reduced number of actuators and corresponding mechanisms.

[00076] The present disclosure provides retraction movement of camera by one of pan and tilt mechanisms so as to reduce number of actuators and corresponding mechanisms.

[00077] The present disclosure provides retraction movement of camera by one of pan and tilt mechanisms without compromising the pan and tilt movements of camera payload.

[00078] The present disclosure provides a payload camera control mechanism that causes only a small portion of the camera to protrude out of Aerial Vehicle fuselage thereby minimizing aerodynamic impact of the protruding camera payload on the Aerial Vehicle.