Lopsided payload carriage gimbal for air and water-borne vehicles

Abstract

The Lopsided Payload Carriage Gimbal in al its embodiments allow Aerial Vehicles and Water-borne vehicles to carry payloads far from the vehicle Geometric Center without significant travel of the vehicle's overall Center of Gravity. Large travel of the CG limits vehicle's performance or renders it inoperable. The embodiments rely on the interaction of the payload and the counter balancing weight through the payload link 18, balancing link 10 main link 14 and battery pylon 8 to substantially reduce the torque generated by the payload in a lopsided position. The embodiments also allow the vehicle carrying the payload to change thrust direction agilely. Finally, the embodiment acts as a mechanical stabilization device for the payload as well. This invention is adaptable to all forms of hover-capable aerial vehicles as well as water-borne vehicles.

Claims

1. A device for carrying lopsided loads such that the travel of Center of Gravity of the device and the vehicle the said device is attached to is restricted to the vicinity of the carrying vehicle's Geometric Center, such that the load is stabilized, such that the load can pivotally change orientation independent of vehicle movement, comprising: a. A series of four linkages in a polygonal arrangement, pivotally linked and contiguous to each other at four pivots. b. A payload mounting device attached anywhere along one of the linkages c. A counter balance weight attached to any one of the linkages d. Any number of sets of parallel linkages sharing identical pivots

2. A device for maintaining orientation of the payload attached to a linkage capable of changing orientation pivotally, comprising: a. A linkage parallel to the said link, such that it maintains parallelism with the said link, such that it has the identical length as the said link. b. A payload mount that is pivotally attached to the said link, and that is pivotally attached to the said parallel linkage.

3. A device for shifting the position of a load comprising: a. A rotary or linear actuation force generation device b. At least one guide track c. A mounting device attaching the counter weight to the said guide track

Description

DESCRIPTION OF DRAWINGS

[0017] FIG. 1 A-C show and compare the behavior of the CG of a conventional aerial vehicle and of an aerial vehicle equipped with one of the embodiments. FIG. 1A shows the relationship of an aerial vehicle's Center of Gravity and Geometric Center when the payload is positioned near the Geometric Center; FIG. 1B shows the relationship of an aerial vehicle's Center of Gravity and Geometric Center when the payload is positioned away from the Geometric Center; FIG. 1C shows the reduced CG travel when the aerial vehicle uses one of the embodiment to carry Identical payload in identical position as shown in FIG. 1B.

[0018] FIG. 2 shows the front isometric view of an embodiment comprising a conventional gimbal configuration installed on a quad-copter aerial vehicle.

[0019] FIG. 3 shows back isometric view of an embodiment comprising a conventional gimbal configuration installed on a quad-copter aerial vehicle.

[0020] FIG. 4 shows the side view of the gimbal embodiment in conventional configuration.

[0021] FIG. 5 shows the free body diagram of the gimbal in conventional configuration.

[0022] FIG. 6 shows the details of one embodiments of the battery position adjustment system.

[0023] FIG. 7 A-B show how the vehicle can quickly change angle of thrust despite higher moment of inertia. FIG. 7A shows one position of the gimbal system when the aerial vehicle quickly pitches down; FIG. 7B shows one position of the gimbal system when the aerial vehicle quickly pitches up;

[0024] FIG. 8 A-B show the range of motion of the gimbal in pitch up and pitch down posture. FIG. 8A, shows the gimbal in a pitched down posture while the aerial vehicle remained level; FIG. 8B shows the gimbal in a pitched up posture while the aerial vehicle remained level.

[0025] FIG. 9 A-D show various embodiments in side view, of inverted and conventional configuration, installed on quad-copter and coaxial copter vehicles. FIG. 9A shows one embodiment in conventional configuration, installed on a quad-copter aerial vehicle; FIG. 9B shows one embodiment in inverted configuration, installed on a quad-copter aerial vehicle; FIG. 9C shows one embodiment in inverted configuration, installed on a coaxial copter aerial vehicle; FIG. 9D shows one embodiment in conventional configuration, installed on a coaxial copter aerial vehicle.

[0026] FIG. 10 shows embodiment as fitted on a waterborne vehicle looking from the front or rear.

DETAILED DESCRIPTIONFIRST EMBODIMENTFIG. 2-FIG. 8

[0027] FIG. 2 and FIG. 3 show an isometric view of a conventional version of the gimbal 5, installed on a generic quadcopter aerial vehicle with H frame 1. The gimbal comprises of multiple linkages. FIG. 2 depicts the gimbal system facing the front, with a payload mount 20 in clear view, holding a dummy payload. FIG. 3 shows the gimbal system facing the back, with a battery 11, battery pylon 8, battery position adjustment system 6 and a balancing pivot 9 clearly visible. This embodiment uses flight battery 11 as the counter balancing weight. The embodiment of FIG. 2 and FIG. 3 have a double beam design, where every linkage in the gimbal has a second redundancy, providing rigidity against torsion that could be experienced under heavy payload. The double beam design could be replaced with single beam design in other embodiments. The payload mount 20 is positioned beyond the tip of the aerial vehicle's propellers.

[0028] FIG. 4 shows the gimbal system 5 from the side, clearly identifying the linkages that form a closed-chain loop pivotally connected at four pivots. The four pivots 9, 16, 13 and 23 allow links to move in parallel planes. In FIG. 4, the vehicle payload is installed on the payload mount 20 attached to one end of the payload link 18. The second end of the payload link 18 is pivotally connected to a balancing link 10 through the balancing pivot 9. Main pivot 16 is positioned between the payload mount 20 and balancing pivot 9. The payload link 18 is pivotally connected to a drive servo 17 and main link 14 through main pivot 16. The drive servo 17 is of a rotation servo type, anchored to the main link 14 and with the servo blade fixed to the payload link 18. The pitch drive servo 17 axis of rotation is identical to axis of the main pivot 16. The main link 14 also contains the power pivot 13, which pivotally connects a battery link 7. The power pivot 13 is designed to act as a bearing and slip ring capable of handling high current flow as well as allowing the battery link 7 and the main link 14 to pivot against each other under the load of battery balancing force 21. The battery link 7 connects a battery position adjustment system 6 and a battery pylon 8 to the power pivot 13. The battery link 7 is pivotally connected to the balancing link 10 through the counter weight pivot 23. The counter weight pivot 23 is situated between power pivot 13 and battery pylon 8. The gimbal 5 attaches to the vehicle's airframe at the vehicle attachment point 15, situated at one end of the main link 14.

[0029] Shown in FIG. 5, the main pivot 16 acts as a fulcrum, dividing the payload link 18 into two torque arms, identified as payload torque arm 24 and balancing torque arm 25. FIG. 5 also shows the effective length of the drive servo and the main link 42, which is from the main pivot 16 to the power pivot 13.

[0030] FIG. 4 embodiment also contains additional support features to add additional functionality. Parallel bar 21, payload pivot 19 and 22, and main link parallel pivot 12 can be added to keep the payload oriented in a nominal angle, despite any changes in payload link 18 pitch angle. The parallel bar 21 is equal in length to the payload torque arm 24. The parallel bar 21 is pivoted at both ends by payload mount parallel pivot 22 and by main link parallel pivot 12. The payload pivots 19 and 20 are vertically aligned; the main pivot 16 and main link parallel pivot are vertically aligned. The vertical distance between both sets of pivots are identical.

[0031] Another support feature shown in FIG. 4 is the pitch drive servo 17 that is used to drive payload link 18 pitch angle to a certain position. The pitch drive servo 17 is of a rotation servo type, anchored to the main link 14 and with the servo blade attached to the payload link 18. The pitch drive servo 17 axis of rotation is identical to axis of the main pivot 16.

[0032] FIG. 6 is a detailed view showing one embodiment of worm-screw-driven battery position adjustment system 6. It automatically adjusts gimbal counter torque to react to variation in payload weight. As shown in this embodiment, the battery position adjustment system 6 comprising of a screw shafts 43, a drive gear 44, a drive motor 45, a guide shaft 46 and a battery pylon with interior thread 8. A electronics controller may command the drive motor 45 to drive the gear 44 and screw shaft 43, which moves the battery position linearly towards or away from the counter weight pivot 23. While rotating, the screw shaft 43 transfers linear forces to the battery pylon 8 through the threads. Rotation of the screw shaft 43 would also transfer rotational force to the pylon 8. The guide shaft 46 is designed to dissipate the rotational force. The guide shaft 46 design as shown in this embodiment can be simplified to a smooth guide without the threads.

[0033] Operations

[0034] FIG. 5 shows the free body diagram of the gimbal system linkages, used in demonstrating how the gimbal 5 balances lopsided loads and limiting CG travel of the aerial vehicle.

[0035] When the gimbal 6 is in static state, the payload torque 26 is equal to the balancing torque 27. The payload torque 26 is defined as the payload torque arm 24 multiplied by payload weight 49. The balancing torque 27 is calculated by multiplying the balancing torque arm 25 with the product of sine of balancing force angle 28 and battery balancing force 29. Trigonometric operator sine is used because the balancing force component perpendicular to the payload link 30 generates the balancing torque 27. The balancing force component parallel to the payload link 50 is calculated by multiplying the balancing torque arm 25 with the product of cosine of balancing force angle 28 and battery balancing force 29. This parallel force component is transferred to the main link 14 as the payload link to main link shear reaction force 51.

[0036] The battery balancing force 29 is a reactive force that retains the battery in a static position. In a static position, battery balancing torque 52 is equal to battery weight torque 53. The battery balancing force component perpendicular to the battery link 32 and the battery balancing force torque arm 34 generate battery balancing torque 52. The battery weight component perpendicular to the battery link 54 and the battery weight torque arm 35 generate battery weight torque 53. The perpendicular force components 32 and 54 are calculated using sine of battery force angle 31 and sine of battery pitch angle 37 respectively.

[0037] The gimbal system as shown in this embodiment can balance a heavier payload using a lighter counter weight and shorter balancing torque arm 25 because the relationship between battery balancing force torque arm 34 and battery weight torque arm 35. By placing the counter weight pivot 23 as close to the power pivot 13 as possible, the battery balancing force torque arm 34 becomes shorter. The battery weight torque arm 35 is measured from the power pivot and the Center of Gravity of the battery. In order to maintain static positions, the battery balancing force 29 has to be increased to compensate for the shorter battery balancing force torque arm 34. The battery position adjustment system 6 is used to extend or shorten the battery weight torque arm 35. Extending the battery weight torque arm 35 further increases battery balancing force 29.

[0038] Battery balancing force component parallel to the battery link 33 is calculated by multiplying cosine of battery force angle 31 and battery balancing force 29. Battery weight component parallel to the battery link 38 is calculated by multiplying cosine of battery angle from vertical 37 and battery balancing weight 35. Both force components 33 and 38 are transferred to the main link 14 as the battery link to main link shear reaction force 39.

[0039] Payload link to main link shear reaction force 51 and battery link to main link shear reaction force 39 generate a lopsided torque 40 that is transferred to the aerial vehicle 1 through the vehicle attachment point 15. The lopsided torque is felt by the aerial vehicle 1 as the sum of the two shear forces 39 and 51 applied at a distance equivalent to the effective main link distance 42 in front of the attachment point. The effective main link distance 42 is the maximum distance in the movement of the aerial vehicle's CG 2. By shortening the effective main link distance 42 to a minimum possible through mechanical design, the shift in CG can be reduced further. The effect of the gimbal 5 on a multi-copter aerial vehicle is shown in FIG. 1C. In order to control vehicle attitude, the aerial vehicle 1 generates a counter torque 41 to cancel out the lopsided torque 40.

[0040] When maneuvering in flight, a generic multi-rotor type aerial vehicle changes the vehicle pitch or roll in order to vector the thrust in a different direction. A maneuver in changing the vehicle pitch is shown in FIGS. 7A and B. When the payload is attached far from the vehicle's Geometric Center 3, the moment of inertia increases. Moment of inertia resist the pitch maneuver, increasing the time it takes to complete the maneuver. FIGS. 7A and B show that with the embodiment of the gimbal, the angle of the payload link 18 relative to the quadcopter frame 1 is allowed to change. The gimbal 5 effectively decouples the pitch of the payload link 18 from the motors and propellers of the vehicle, allowing the vehicle to maneuver quickly. After the maneuver, the changes in the angles between the gimbal links generates a net return force that automatically returns the payload link 18 to the nominal or neutral angle relative to the quadcopter frame 1.

[0041] The ability to automatically return to nominal position could also provide mechanical stabilization to the payload.

[0042] As shown in FIG. 8A, when the payload link 18 is pitched down, the battery pivots upwards about power pivot 13, lowering battery force angle 31; when the payload link 18 is pitched up as shown in FIG. 8B, the battery pivots downwards about power pivot 13, increasing battery force angle 31. When the battery force angle 31 is small, the battery balancing force 29 is increased in order to generate enough vertical force component 32 to the retain equilibrium of battery link 7 position. Vice versa, when the battery force angle 31 becomes large, the battery balancing force 29 is decreased. Because of the change in the battery force angle 31 and the resulting change in battery balancing force 29, the payload link 18 will always seek to return to the preset neutral position. Payload mount 20 as shown in FIGS. 8A and B maintains the orientation of the payload despite the changes in payload link 18 pitch angle.

[0043] With the aerial vehicle remaining in hover, the payload link 18 could be forced into a pitch up or pitch down angle. Pitch drive servo 17 is used to drive payload link 18 pitch angle to a certain position, working against the battery balancing force 29 that seeks to return the payload link 18 to the preset neutral position.

[0044] During the tuning and system setup of the gimbal, adjustment can be made to the position of the balancing pivot 9 along the payload link 18. This adjustment changes the length ratio of the payload torque arm 24 to the balancing torque arm 25. A longer balancing torque arm 25 could help the gimbal carry heavier payload mounted to the payload mount 20. At the same time, adjusting balancing pivot 9 position also changes the payload link 18 range of motion. Placing balancing pivot 9 as far away as possible from the main pivot 16 reduces range of pitching motion. Extending the length of the balancing link 10 increases the range of pitching motion. However, the pitch range is ultimately restricted by the range of motion of the counter balancing weight, which is the battery 11 in this embodiment.

[0045] Using battery as the counter weight requires the transfer of electrical power from the battery to the vehicle's electric motor control electronics. The electrical current of this electrical flow is high and thus requires the use of low gauge wires. Low gauge wires are rigid due to it's larger cross section diameters. Rigid wire severely degrades the flexibility of the gimbal system, transferring additional torque to the vehicle frame 1. As a result, the lopsided torque 40 is increased, exacerbating the travel of Center of Gravity. Therefore, the power pivot 13 is designed to transfer high current flow while functioning as a bearing.

Alternative Embodiments

[0046] Alternative embodiments can be created by changing the effective lengths of the linkages and changing the location of the pivots. Changing the effective length modifies the torque arm created by counter weights.

Alternative Embodiments

[0047] The counter weights could be any heavy flight equipment besides the battery 11.

Alternative Embodiments

[0048] The aerial vehicle attachment point could be above the gimbal system, resulting in the inverted configuration shown in FIG. 9B.

Alternative Embodiments

[0049] The payload mount 20 could be modified to carry variable weight payloads or change payload during flight. The battery position adjustment system 6 could be used to change the battery balancing force 29, automatically restoring the payload link 18 to the nominal or neutral angle during flight without changing setup and configuration.

Alternative Embodiments

[0050] The gimbal system can be installed on the aerial vehicle in an inverted or conventional configuration on multi-copter or Single Rotor (SR)/Coaxial Counterrotating Dual Rotor (CCDR) type vehicle frames as shown in FIG. 9C and FIG. 9D.

[0051] The gimbal must be placed in a position where the range of motion of both the battery and the payload link 18 are not restricted by any part of the vehicle frame 1. The gimbal could be place above or below the motors and propellers. The selection of configuration is purely based on the space that is available for the gimbal system and the inherent stability that's required by the vehicle system. If mounted in conventional configuration below a SR or CCDR copter as shown in FIG. 9C, an aerodynamic cowling may be necessary to shield the gimbal system from high speed airflow.

Alternative Embodiments

[0052] Using material and payload link 18 geometry that provides sufficient bending and torsional rigidity, the payload link 18 of a single rail design can be used instead of double rail design.

Alternative Embodiments

[0053] An embodiment of the gimbal could be used on a water borne vehicle such as that shown in FIG. 10.

Advantages

[0054] From the description above, a number of high level functional advantages of some embodiments of my gimbal system become evident: [0055] 1. The gimbal provides aerial vehicles a way to carry substantial payload weight in a position, including positions beyond the tip of the propellers. [0056] 2. The use of the battery position adjustment system 6 allows the aerial vehicle to adjust for variation in payload weight automatically during flight [0057] 3. The various embodiments can be applied to coaxial aerial vehicle, multi-copter aerial vehicle and water-borne vehicle alike. [0058] 4. Decoupling of the payloads from the drone frame preserves the agility and maneuverability of the aerial vehicle. [0059] 5. Decoupling of the payloads and the ability to automatically return to nominal position provides mechanical stabilization to the payload.

CONCLUSIONS, RAMIFICATIONS AND SCOPE

[0060] Accordingly, the reader will see that the gimbal system of various embodiments can be used to help aerial and water borne vehicles carry payloads away from the vehicle Geometric Center and avoid large travel of the location of the Center of Gravity. In addition, the system can adjust for variation of payload weight during flight to maintain control of the location of the vehicle's Center of Gravity.

[0061] The various embodiments allow the vehicles to carry many types of payloads in a lopsided position: [0062] Graphical, touch and aural user interface for visual, face to face, and touch input communication [0063] Graphical visual display for advertising [0064] Dispensing of liquid horizontally [0065] Installing equipment onto walls, including sensors and markers [0066] Sensors requiring clear FOV [0067] Sensors requiring mechanical stabilization [0068] Robotic hand, grabber or crane

[0069] Aerial vehicles armed with some of these payloads could see use in the following applications requiring interfacing with humans, dispensing payloads horizontally, as well as applying force or making contact against vertical surfaces. A few of the possible applications include:

[0070] Police and Security Use: [0071] Virtual investigation of situation through conversation with persons on site [0072] Situation de-escalation through body language and communications [0073] Establishing visual communication channel between security forces and dispatch center/tactical command [0074] Help law enforcement enter rooms by opening doors or placing tactical charges Remote Real-Estate Viewing: [0075] A real estate agent conducting face-to-face virtual property tour with his client, who is connected remotely.

[0076] Social Media and Self-Broadcasting: [0077] Record footages using on board screen as tele-prompter/view finder direct controls. [0078] Used to conduct interviews

[0079] Search and Rescue: [0080] Use contact sensors to attempt to discover persons trapped in spaces [0081] Place markers, beacons or tactical charges on walls

[0082] Inspection: [0083] Use contact sensors to find fatigue cracks, especially on vertical surfaces such as wind turbines.

[0084] Warehouse Inventory Management [0085] Scanning packages or detecting RFID tags [0086] Pull stock from shelves

[0087] Water-borne vehicles armed with some of these payloads could see use in the following applications:

[0088] Cargo Loading: [0089] Load or unload cargo without land based crane system [0090] Load or unload smaller boats unto the deck

[0091] Although the description above contains many specificities, these should not be construed as limiting the scope of the embodiments but as merely providing illustrations of some of several embodiments. Thus, the scope for the embodiments should be determined by the appended claims and their legal equivalents, rather than by the examples given.