Removable battery compression device

Abstract

The present application is entitled “Removable Battery Compression Device.” Certain aspects of the present disclosure provide a vehicle comprising: a housing; a battery comprising a plurality of layers and disposed within the housing; and a first removable battery compression device disposed within the housing and configured to apply a compressive force to the plurality of layers of the battery via a first side of the battery.

Description

Technical Field

[0001] Aspects of the present disclosure relate to removable battery compression devices, and more particularly to removable battery compression devices that can be installed in an aircraft (such as in an aircraft wing) during battery transportation and charging and uninstalled prior to flight. Background Art

[0002] During normal use, such as during charging and discharging, batteries are susceptible to internal damage and wear. Batteries within vehicles are typically mounted in a manner that restrains the battery but does not stress the battery. As a result, during normal use, batteries within vehicles may become damaged or worn. Summary of the invention

[0003] Certain embodiments provide a vehicle comprising: a housing; a battery comprising a plurality of layers and disposed within the housing; and a first removable battery compression device disposed within the housing and configured to apply a compressive force to the plurality of layers of the battery via a first side of the battery.

[0004] A further embodiment provides an unmanned vehicle (UAV) comprising: a fuselage; a plurality of engageable wing sections, wherein: a first engageable wing section of the plurality of engageable wing sections is engaged to the fuselage, a second engageable wing section of the plurality of engageable wing sections is engaged to the fuselage, and each engageable wing section of the plurality of engageable wing sections comprises: a shell; a battery comprising a plurality of layers and disposed within the shell; and a first removable battery compression device disposed within the shell and configured to apply a compression force to the plurality of layers of the battery via a first side of the battery.

[0005] A further embodiment provides a method of using a removable battery compression device, comprising: installing the removable battery compression device in a container; charging a battery including multiple planar layers compressed by the removable battery compression device; removing the removable battery compression device from a vehicle; and after removing the removable battery compression device from the vehicle, operating the vehicle using power from the battery.

[0006] The following description and the associated drawings set forth in detail certain illustrative features of the one or more embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] The drawings depict certain aspects of one or more embodiments and therefore should not be considered to limit the scope of the disclosure.

[0008] Figure 1 Depicting an example of a removable compression device within a wing assembly.

[0009] Figure 2 Depicted is an example of a modular wing section including batteries and a removable battery compression device.

[0010] Figure 3A and Figure 3B Depicting an example of a removable battery compression device mounted within a wing cross section.

[0011] Figure 4 Depicting another example of a removable battery compression device within a wing.

[0012] Figure 5 Depicted is an example method of using a removable battery compression device as discussed herein.

[0013] To facilitate understanding, identical reference numerals have been used, where possible, to designate identical elements that are common to the figures. It is contemplated that elements and features of one embodiment may be beneficially incorporated in other embodiments without further recitation. DETAILED DESCRIPTION

[0014] Aspects of the present disclosure provide a removable battery compression device suitable for use in a craft, such as an aircraft.

[0015] Various types of batteries are constructed with a layered internal structure, such as: anode, cathode, separator, and separation layer. The performance of a battery can be particularly sensitive to the state of its internal layers. For example, if the layers of a battery become separated due to physical and / or chemical changes in the layers, the performance of the battery will degrade.

[0016] Rechargeable batteries are particularly susceptible to degradation of the layer state because repeated charging and discharging (especially at high current levels) generates heat and power, which in turn induces physical stresses on the battery's layers and chemical changes within the layer structure. For example, high-speed charging of a battery can cause bubbles to form between the layers, shifting the layers from uniform contact with each other. Such changes are generally irreparable, so normal use may significantly shorten the battery's useful life.

[0017] Methods that compress batteries so that their layers are less susceptible to deformation can significantly improve the performance and life of the battery. For example, compressing the battery during charging can significantly improve the battery's resilience to the stresses caused by charging, allowing the battery to go through more charge cycles before replacement. In some cases, sufficient compression can increase the charge cycle capacity of a battery from tens of charges to hundreds or even thousands of charges. This not only improves the life of the battery (and anything powered by that battery), but also reduces the need to replace the battery, which may be particularly advantageous when the battery is integrated into an aircraft ship in a way that replacement is expensive and laborious.

[0018] Batteries are increasingly used in aircraft and ships for both primary power (e.g., in unmanned vehicles) and backup, auxiliary, or accessory power. In various aircraft and ships, especially in aircraft, reducing weight generally improves performance. However, adding permanent structures or devices to the aircraft and ships to optimally compress the batteries to obtain the aforementioned battery performance improvements comes at the expense of increased weight, which may hinder the performance of the aircraft and ships.

[0019] Embodiments described herein relate to a removable battery compression device that can be installed in a ship at certain times (e.g., when the ship is being transported or charged) and removed at other times (e.g., when operating the ship, particularly when flying).

[0020] For example, a portable unmanned vehicle (UAV) may have a removable battery compression device installed to prevent damage to the battery during storage, transportation, and charging, but removed during flight of the UAV to improve flight characteristics, such as range and agility. In such an embodiment, the UAV may have wings (and other components) that can be separated into multiple sections to improve portability, and the removable battery compression device can be configured to fit within the wing sections of the UAV. In particular, where each wing section is separated, there can be access to the interior space of the wing, into which the removable battery compression device can be easily installed and removed. The same design configuration can be used for other aircraft components, such as detachable fuselage sections.

[0021] However, with the removable battery compression device described herein, the craft does not need to be portable or easily detachable. Instead, the craft only needs to have a way to access the space adjacent to the installed batteries in order to install and remove the removable battery compression device. For example, a conventional aircraft may have an access panel in a wing or fuselage section that allows the installation and removal of the removable battery compression device described herein. Similarly, electric vehicles on land or water may have access panels for installing and removing removable battery compression devices. Although many of the examples described herein relate to aircraft, the principles described herein are widely applicable to different types of craft.

[0022] Exemplary Removable Battery Compression Device Embodiments

[0023] Figure 1 An example of a removable compression device within a wing is depicted.

[0024] In particular, wing 102 is depicted as having a plurality of cells or housings 104A-C in which batteries 106A-C are placed. In this example, each housing 104A-C depicts a different kind of removable battery compression device to demonstrate the various ways in which battery compression can be accomplished. In other embodiments, all or a subset of housings 104A-C (and in Figure 1 The same type of removable compression device is used in other housings not shown.

[0025] The housing 104A includes a battery 106A having a layered structure as shown. In this example, the removable battery compression devices 108A and 108B include expandable (e.g., filled with air or fluid) bladders that press against the wall of the housing 104A and apply compression to the battery 106A as shown by the arrows. For example, the removable compression devices 108A and 108B can be easily installed in a deflated state and then inflated to a set pressure (e.g., in Pascals or pounds per square inch, etc.) in the housing 104A to compress the battery 106A in a direction perpendicular to the layers of the battery 106A. In this example, the layers of the battery 106A are flat and arranged parallel to each other. Because the removable compression devices 108A and 108B can be removed (i.e., unloaded) before flight, the battery 106A can be attached or fixed in the housing 104A by appropriate means (such as fastening hardware, straps, adhesives, hook-and-loop fasteners, etc.).

[0026] It should be noted that while battery 106A is depicted in this example as being shorter than the length of housing 104A, in other embodiments, battery 106A, as well as batteries 106B and 106C, may be equal to or approximately equal to the interior length dimension of housing 104A.

[0027] Housing 104B includes battery 106B, and this battery 106B has layered structure as shown in the figure.In this example, removable battery compression device 110A and 110B include spring-biased plate, wherein spring is pressed on the wall of housing 104B, and battery 106B is compressed by attachment plate as shown by arrow.Compared with separate spring, the plate attached to spring can produce more uniform force distribution on the whole compression surface of battery 106B.The spring attached to the plate can be any type of compression spring, such as conical, hourglass, barrel, constant pitch, variable pitch and spiral compression spring, wave spring, round wire spring, Belleville (belleville) spring, recurved or curved strip spring, and other or torsion spring.As mentioned above, because removable compression device 110A and 110B can be removed before flight, battery 106B can be attached or fixed in housing 104B by appropriate means such as above.

[0028] The housing 104C includes a battery 106C having a layered structure as shown. In this example, the removable battery compression devices 112A and 112B include biasing members 112A and 112B that press against the walls of the housing 104C and apply compression to the battery 106C through multiple interface points between the biasing members 112A and 112B and the battery 106C. The biasing members of the removable battery compression devices 112A and 112B can include springs such as those described above. However, in this example, the biasing members are not attached to the compression plate like those in the housing 104B.

[0029] Although several different types of compression devices are shown for housings 104A-104C, other compression devices are possible. For example, the removable battery compression device may include a threaded compression rod, a pneumatic or hydraulic piston (either alone or attached to a compression plate), a foam or rubber insert, opposing straps, other packaging materials, etc.

[0030] The removable battery compression devices 108A-108B, 110A-110B, and 112A-112B may all be installed when charging the batteries 106A-106C and when storing or transporting the aircraft with the wing 102 attached. In this way, the removable battery compression devices 108A-108B, 110A-110B, and 112A-112B may improve the durability of the batteries 106A-106C and may provide a reinforced structure to prevent damage to the batteries 106A-106C.

[0031] Batteries 106A-106C may be used for various purposes, such as powering electric propulsion system components (e.g., electric motors), or powering auxiliary or backup systems, such as providing backup power for avionics systems, fly-by-wire electric actuators, electric pumps for hydraulic systems, safety systems, lighting systems, communication systems, etc.

[0032] Although for simplicity in Figure 1 Not shown, the housings 104A-104C may include additional components, such as electrical connections for the batteries 106A-106C, electronics (eg, sensors), and the like.

[0033] Figure 2 An example of a modular wing section (or subassembly) including batteries and a removable battery compression device is depicted.

[0034] Figure 2202A includes aerodynamic control surfaces 216 (e.g., ailerons). Modular wing segment 202A may be connected or joined to other modular wing segments or assemblies at attachment points 214. For example, modular wing segment 210 may be attached to a wing end cap 218 (or a winglet in other embodiments) and another modular wing segment 202B. Although not shown for simplicity in FIG. Figure 2 Not shown, modular wing sections such as 202A and 202B may include electrical connections (eg, via connectors) that enable power and data to flow between wing section 200 and other systems within aircraft vessel 200 (which in this example is an aircraft).

[0035] In this example, the modular wing section 202A includes a plurality of internal structural members, including ribs 204A-204C, a front spar 210A, and a rear spar 212A. The internal structural members may be used as part of the shell, or may be used as a structure to hold and compress the battery using a removable battery compression device, such as described above with respect to Figure 1 Those described.

[0036] For example, a battery 206A including a layered internal structure as shown may be mounted, placed, held, secured, or otherwise positioned within a modular wing segment 202A and at least partially supported on a first side by ribs 204A, supported on a second side by front spar 210A, and supported on a third side by rear spar 212A. Additionally, a removable battery compression device 208A may be placed against the battery 206A on a fourth side and may be removed as described above with respect to Figure 1 The described manner provides a compressive force on the battery 206A as shown by the arrows. For example, the removable battery compression device 208A may include an expandable bladder that can be installed and inflated to apply compression to the battery 206A. In this example, the removable battery compression device 208A can be supported by the wing end cap 218 on its end opposite the battery 206A, or in other embodiments can be supported by another modular structure attached to the modular wing section 202A. In this example, the battery 206A is compressed in a direction along the span of the modular wing section 202A.

[0037] As another example, a battery 206B, also including a layered internal structure as shown, may also be mounted within the modular wing segment 202A and at least partially supported on a first side by the ribs 204C, on a second side by the front spar 210A, and on a third side by the rear spar 212A. Additionally, a removable battery compression device 208B may be placed against the battery 206B on a fourth side and may be removed as described above with respect to Figure 1The removable battery compression device 208B may include an expandable bladder that may be mounted and inflated to apply compression to the battery 206B. In this example, the removable battery compression device 208B may be supported by a structural connector of the wing or modular wing segment 202B at its end opposite the battery 206B. In this example, the battery 206B is also compressed in a direction along the span of the modular wing segment 202A.

[0038] As yet another example, a battery 206C, also including a layered internal structure as shown, may be mounted within the modular wing segment 202B and at least partially supported on a first side by the front spar 210B and on a second side by the rear spar 212B. Additionally, removable battery compression devices 208C and 208D may be placed against the battery 206C on a third side and a fourth side and may be removed as described above with respect to Figure 1 The described approach provides a compressive force to the battery 206C.

[0039] In this example, the removable battery compression device 208C is shown as being removed to illustrate its removability. As described above, the removable battery compression devices 208C and 208D may include expandable bladders that may be installed and inflated to apply compression to the battery 206C. In this example, the removable battery compression device 208C may be supported on its end opposite the battery 206C by a structural connector of the modular wing section 202A, while the removable battery compression device 208D may be supported on its end opposite the battery 206C by a structural connector of the fuselage 220 of the ship 200. In this example, the battery 206C is also compressed in a direction along the span of the modular wing section 202A.

[0040] In the modular wing segment 202B, the battery 206C may be mounted above, below, or through the ribs 204D-204F. In some embodiments, when mounted within the modular wing segment 202B, the battery 206C may act as a structural element and may eliminate the need for ribs that span the entire chord of the wing segment 202B.

[0041] like Figure 2 As shown, when the modular wing sections 202A and 202B are separated, the batteries 206A-206C are easily installed or removed from their respective mounting locations.

[0042] In some embodiments, the removable compression device may be installed during transportation, storage, and charging of the wing section with the installed batteries, but removed prior to flight. Figure 2In the embodiment of the present invention, the removable battery compression devices 208A-208D may be removed prior to fully assembling the modular wing components and launching the aircraft 200.

[0043] In some embodiments, the batteries 206A-206C can be mounted in such a manner that the removal of the removable battery compression device 208A-208D does not cause the batteries 206A-206C to move during flight or other movement of the aircraft 200. In other embodiments, a lightweight retaining element (not shown) can replace the compression device during operation of the aircraft 200. For example, the retaining element can be made of a lightweight foam or other durable low-density material. Although the retaining elements may not provide the level of compression provided by the removable battery compression device 208A-208D to the batteries 204A-204C, they can still provide sufficient force to keep the batteries 204A-204C in place during flight or other movement of the aircraft 200.

[0044] exist Figure 2 In the example shown, two modular wing sections 202A and 202B are shown as forming the wing structure of the ship 200, but in other examples, any number of modular wing sections may be used. The modular wing sections may include attachment points (e.g., 214) for connecting different modular wing sections, and additional structural elements (not shown) may further attach structural elements within each modular wing section, such as elements for linking the front spars 210A and 210B and the rear spars 212A and 212B. Thus, when linked together, the modular wing elements may form a structurally sound wing for the ship 200.

[0045] Figure 3A and Figure 3B Depicted is an example of a removable battery compression device mounted within a wing cross section.

[0046] exist Figure 3A 3, a battery 306 having a layered internal structure as shown is located within the cross-section of the wing 302 and within the housing 304 between the front spar 310 and the rear spar 312. In this example, a removable battery compression device 308A is located between the front spar 310 and the battery 306 and provides a compressive force on the battery 306 as indicated by the arrow. A removable battery compression device 308B is further located between the rear spar 312 and the battery 306 and provides a compressive force on the battery 306 as indicated by the arrow. Thus, in this example, the battery 306 is compressed along the chord of the wing 302.

[0047] Although in Figure 3A Not shown, additional structure (eg, walls, ribs, etc. of housing 304 ) may hold battery 306 from moving laterally along the span of wing 302 .

[0048] exist Figure 3B 306A having a layered internal structure as shown is located within a cross section of a wing 302 between a front spar 310 and a retaining wall 304A, which may form part of a shell. In this example, a removable battery compression device 308A is located between the retaining wall 304A and the battery 306A and provides a compressive force on the battery 306A as indicated by the arrows. Thus, in this example, the battery 306A is compressed along the chord of the wing 302.

[0049] Similarly, a battery 306B having a layered internal structure as shown is located within a cross section of the wing 302 between the front spar 310 and the retaining wall 304B, which may form part of the shell. In this example, a removable battery compression device 308B is located between the retaining wall 304B and the battery 306B and provides a compressive force on the battery 306B as shown by the arrows. Thus, in this example, the battery 306B is also compressed along the chord of the wing 302.

[0050] Although in Figure 3B Not shown, additional structure (e.g., additional retaining walls, ribs, etc.) may hold batteries 306A and 306B from moving laterally along the span of wing 302. Figure 3B Not shown, but a similar structural arrangement may be configured around the rear spar 312 for enclosing additional batteries.

[0051] Figure 4 Another example of a removable battery compression device within a wing is depicted.

[0052] In this example, the removable battery compression devices 408A and 408B are hollow extrusions with hexagonal cross-sections that can apply or not apply compression forces to the batteries arranged around the movable device when rotated to different positions. It is worth noting that although hexagonal in this example, the removable battery compression devices 408A and 408B can have different cross-sections in other embodiments, such as other polygonal cross-sections with more or fewer points, or other cross-sectional geometries (e.g., lobed).

[0053] In the depicted example, the removable battery compression device 408A is rotated so that six points of its cross-section are pressed against the walls of six corresponding battery housings 404A-404F, which respectively house six batteries 406A-406F having a layered internal structure as shown. In this case, the walls of the battery housings 404A-404F adjacent to the removable battery compression device 408A can be flexible or movable to transfer forces from the points of the removable battery compression device 408A to the batteries 406A-406F stored therein (as indicated by the force arrows).

[0054] Although in Figure 4 Not shown, but in some embodiments, points of the removable battery compression device 408A can engage with notches or other structures on the walls of the battery housing 404A-404F adjacent to the removable battery compression device 408A to hold the removable battery compression device 408A in place when in the compression providing arrangement.

[0055] A removable battery compression device 408B is shown in an alternative arrangement that does not provide compression to the adjacent battery housing. In this arrangement, the removable battery compression device 408B can be easily removed, thereby saving weight before the aircraft attached to the wing 402 is flown. In addition, the battery can also be easily removed from the housing without applying compression to the battery.

[0056] exist Figure 4 In the example shown, Figure 4 As shown, the inner wall of the battery housing (e.g., 404A-404F) forms a channel having the same number of cross-sections as the removable battery compression device (408A and 408B). In other words, in this example, the channels 410A and 410B also have a hexagonal cross-section that corresponds to but is larger than the cross-section of the removable battery compression device 408A and 408B. In other examples, the geometry of the cross-section of the removable battery compression device (e.g., 408A and 408B) may be different from the geometry of the channel (e.g., 410A and 410B) in which the removable battery compression device is installed.

[0057] Example Methods of Using a Removable Battery Compression Device

[0058] Figure 5 An example method 500 of using a removable battery compression device as discussed herein is depicted.

[0059] Method 500 begins at step 502, where for example, Figure 1 , Figure 2 , Figure 3A , Figure 3B and Figure 4As described, one or more removable battery compression devices are installed in a vehicle.

[0060] Method 500 then proceeds to step 504 where the one or more batteries compressed by the one or more removable battery compression devices are charged.

[0061] Method 500 then proceeds to step 506 where the one or more removable battery compression devices are removed from the vehicle.

[0062] The method 500 then proceeds to step 508 where the vehicle is operated. Operating the vehicle may include operating various aspects of the vehicle with the power stored in the battery.

[0063] Although in Figure 5 Not shown, but in other examples, method 500 may include additional and / or alternative steps.

[0064] For example, method 500 may include transporting and / or storing a vehicle having the battery compression device installed.

[0065] As another example, method 500 may include engaging a removable battery compression device after installation, such as by inflating the device, changing the orientation of the device, or otherwise causing the device to apply pressure to an adjacent battery.

[0066] As another example, method 500 may include using power stored in the battery to operate one or more systems of the vehicle, such as a propulsion system or an auxiliary or backup system (as described above).

[0067] Exemplary Embodiments

[0068] The following are exemplary embodiments. It should be noted that the reference numerals in the following examples are merely exemplary.

[0069] Embodiment 1: A vehicle comprising: a housing (104); a battery (106) comprising a plurality of layers and disposed within the housing (104); and a first removable battery compression device (108) disposed within the housing (104) and configured to apply a compressive force to the plurality of layers of the battery (106) via a first side of the battery (106).

[0070] Embodiment 2: The vehicle of embodiment 1, wherein the first removable battery compression device comprises an expandable bladder (108A).

[0071] Embodiment 3: The vehicle of Embodiment 1, wherein the first removable battery compression device comprises one or more springs (110A, 112A).

[0072] Embodiment 4: The vehicle of Embodiment 3, wherein the first removable battery compression device comprises a plate attached to one or more springs (110A).

[0073] Embodiment 5: The vehicle of Embodiment 1, wherein the first removable battery compression device comprises a hollow extrusion having a polygonal cross-section (408).

[0074] Embodiment 6: The vehicle according to any one of embodiments 1-5, wherein the housing is disposed within a wing of the vehicle.

[0075] Embodiment 7: The vehicle according to any one of embodiments 1-6 further includes: a second removable battery compression device (108), which is disposed in the housing (104) and is configured to apply a compressive force to multiple layers of the battery via a second side of the battery (106).

[0076] Embodiment 8: The vehicle of embodiment 6, wherein at least one wall of the shell comprises a structural element of a wing (102).

[0077] Embodiment 9: The vehicle of Embodiment 8, wherein the structural element is one of a spar (210, 212) or a rib (204).

[0078] Embodiment 10: The vehicle of any one of Embodiments 6-9, wherein the first removable battery compression device is configured to apply a compressive force to multiple layers of the battery in a direction along the span of the wing (102).

[0079] Embodiment 11: The vehicle of any one of Embodiments 6-9, wherein the first removable battery compression device is configured to apply a compressive force to the plurality of layers of batteries in a direction along the chord of the wing (102).

[0080] Embodiment 12: A vehicle according to any one of embodiments 6-11, wherein: the wing includes a plurality of engageable sections (202), the shell (104) is disposed within one of the plurality of engageable sections, and each of the plurality of engageable sections (202) includes a power connector configured to enable power to flow from one of the plurality of engageable sections to one of: another section of the plurality of engageable sections, or a fuselage (220) of the vehicle.

[0081] Embodiment 13: An unmanned vehicle (UAV), comprising: a fuselage (220); a plurality of engageable wing sections (202), wherein: a first engageable wing section of the plurality of engageable wing sections is engaged to the fuselage (220), a second engageable wing section of the plurality of engageable wing sections is engaged to the fuselage (220), and each engageable wing section of the plurality of engageable wing sections (202) comprises: a shell (204); a battery (206), comprising a plurality of layers and disposed within the shell (204); and a first removable battery compression device (208), disposed within the shell (204) and configured to apply a compression force to the plurality of layers of the battery (206) via a first side of the battery (206).

[0082] Embodiment 14: A UAV according to Embodiment 13, wherein the first removable battery compression device within each of the plurality of engageable wing sections comprises an expandable bladder (208A).

[0083] Embodiment 15: A UAV according to Embodiment 13, wherein the first removable battery compression device within each of the plurality of engageable wing sections comprises one or more springs (110A, 112A).

[0084] Embodiment 16: A UAV according to Embodiment 15, wherein the first removable battery compression device within each of the plurality of engageable wing sections comprises a plate attached to one or more springs (110A).

[0085] Embodiment 17: According to any one of Embodiments 13-16, the UAV further includes within each of the plurality of engageable wing sections (202): a second removable battery compression device (208) disposed within the housing (204) and configured to apply a compression force to multiple layers of the battery via a second side of the battery (206).

[0086] Embodiment 18: A UAV according to any one of embodiments 13-17, wherein at least one wall of the shell within each corresponding engageable wing segment of the plurality of engageable wing segments (202) comprises a structural element of the corresponding engageable wing segment wing.

[0087] Example 19: A method for using a removable battery compression device, comprising: installing (502) a removable battery compression device (208) in a vehicle (200); charging (504) a battery (206) including multiple planar layers compressed by the removable battery compression device; removing (506) the removable battery compression device (208) from the vehicle (200); and operating (508) the vehicle using power from the battery (206) after removing the removable battery compression device (208) from the vehicle (200).

[0088] Embodiment 20: The method of Embodiment 19, wherein the removable battery compression device (208) is mounted within a housing (204) in a section (202) of a wing of the vehicle (200).

[0089] The foregoing description is provided to enable any person skilled in the art to practice the various embodiments described herein. The examples discussed herein do not limit the scope, applicability, or embodiments set forth in the claims. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be applied to other embodiments. For example, the functions and arrangements of the elements discussed may be changed without departing from the scope of the present disclosure. Various examples may appropriately omit, replace, or add various processes or components. For example, the described methods may be performed in an order different from that described, and various steps may be added, omitted, or combined. Moreover, the features described with respect to some examples may be combined in some other examples. For example, a device may be implemented or a method may be practiced using any number of aspects set forth herein. In addition, the scope of the present disclosure is intended to cover such a device or method that is practiced using other structures, functions, or structures and functions that are additional to or different from the various aspects of the present disclosure set forth herein. It should be understood that any aspect of the present disclosure disclosed herein may be embodied by one or more elements of a claim.

[0090] As used herein, a phrase referring to "at least one of" a list of items refers to any combination of those items, including single members. For example, "at least one of a, b, or c" is intended to cover a, b, c, ab, ac, bc, and abc, as well as combinations of plural numbers of the same elements (e.g., aa, aaa, aab, aac, abb, acc, bb, bbb, bbc, cc, and ccc or any other ordering of a, b, and c).

[0091] Furthermore, the present disclosure includes embodiments according to the following clauses:

[0092] Clause 1. A vehicle comprising:

[0093] Housing (104);

[0094] a battery (106) comprising a plurality of layers and disposed within the housing (104); and

[0095] A first removable battery compression device (108) is disposed within the housing (104) and is configured to apply a compressive force to the plurality of layers of the battery (106) via a first side of the battery (106).

[0096] Clause 2. The vehicle of clause 1, wherein the first removable battery compression device comprises an expandable bladder (108A).

[0097] Clause 3. The vehicle of clause 1, wherein the first removable battery compression device comprises one or more springs (110A, 112A).

[0098] Clause 4. The vehicle of clause 3, wherein the first removable battery compression device comprises a plate attached to one or more springs (110A).

[0099] Clause 5. The vehicle of clause 1, wherein the first removable battery compression device comprises a hollow extrusion having a polygonal cross-section (408).

[0100] Clause 6. The vehicle of clause 1, wherein the housing is disposed within a wing (102) of the vehicle.

[0101] Clause 7. The vehicle of clause 1, further comprising: a second removable battery compression device (108) disposed within the housing (104) and configured to apply a compressive force to the plurality of layers of the battery via a second side of the battery (106).

[0102] Clause 8. The vehicle of clause 6, wherein at least one wall of the hull comprises a structural element of a wing (102).

[0103] Clause 9. The vehicle of clause 8, wherein the structural element is one of a spar (210, 212) or a rib (204).

[0104] Clause 10. The vehicle of clause 6, wherein the first removable battery compression device (108) is configured to apply a compressive force to the plurality of layers of the battery in a direction along the span of the wing (102).

[0105] Clause 11. The vehicle of clause 6, wherein the first removable battery compression device (108) is configured to apply a compressive force to the plurality of layers of batteries in a direction along a chord of the wing (102).

[0106] Clause 12. A vehicle according to clause 6, wherein:

[0107] The wing comprises a plurality of engageable sections (202),

[0108] The housing (104) is disposed within one of the plurality of engageable sections, and

[0109] Each segment of the plurality of engageable segments (202) includes a power connector configured to enable power to flow from one segment of the plurality of engageable segments to one of: another segment of the plurality of engageable segments, or a body (220) of a vehicle.

[0110] Clause 13. An unmanned vehicle (UAV), comprising:

[0111] Body (220);

[0112] A plurality of joinable wing sections (202), wherein:

[0113] a first joinable wing segment of the plurality of joinable wing segments joined to the fuselage (220),

[0114] a second joinable wing segment of the plurality of joinable wing segments joined to the fuselage (220),

[0115] Each of the plurality of engageable wing sections (202) comprises:

[0116] Housing (204);

[0117] a battery (206) comprising a plurality of layers and disposed within the housing (204); and

[0118] A first removable battery compression device (208) is disposed within the housing (204) and is configured to apply a compressive force to the plurality of layers of the battery (206) via a first side of the battery (206).

[0119] Clause 14. The UAV of clause 13, wherein the first removable battery compression device within each of the plurality of engageable wing sections comprises an expandable bladder (208A).

[0120] Clause 15. The UAV of clause 13, wherein the first removable battery compression device within each of the plurality of engageable wing sections comprises one or more springs (110A, 112A).

[0121] Clause 16. A UAV according to clause 15, wherein the first removable battery compression device within each of the plurality of engageable wing sections comprises a plate attached to one or more springs (110A).

[0122] Clause 17. The UAV according to Clause 13 further includes within each of the plurality of engageable wing sections (202): a second removable battery compression device (208) disposed within the housing (204) and configured to apply a compressive force to multiple layers of the battery via a second side of the battery (206).

[0123] Clause 18. A UAV according to clause 13, wherein at least one wall of the shell within each corresponding engageable wing segment of the plurality of engageable wing segments (202) comprises a structural element of the corresponding engageable wing segment wing.

[0124] Clause 19. A method of using a removable battery compression device, comprising:

[0125] installing (502) a removable battery compression device (208) in a vehicle (200);

[0126] charging (504) a battery (206) comprising a plurality of planar layers compressed by a removable battery compression device;

[0127] removing (506) the removable battery compression device (208) from the vehicle (200); and

[0128] After removing the removable battery compression device (208) from the vehicle (200), the vehicle is operated (508) using power from the battery (206).

[0129] Clause 20. The method of clause 19, wherein the removable battery compression device (208) is mounted within a housing (204) in a section (202) of a wing of the vehicle (200).

Claims

1. A means of transport, comprising: Wing (102); A housing (104) disposed within the wing (102); a battery (106) comprising a plurality of layers and disposed within the housing (104); and a first removable battery compression device (108) disposed within the housing (104) and configured to apply a compressive force to the plurality of layers of the battery (106) via a first side of the battery (106); wherein after the first removable battery compression device (108) is removed from the vehicle, the battery (106) provides power to the vehicle.

2. The vehicle of claim 1, wherein the first removable battery compression device comprises an expandable bladder (108A).

3. The vehicle of claim 1, wherein the first removable battery compression device comprises one or more springs (110A, 112A).

4. The vehicle of claim 3, wherein the first removable battery compression device comprises a plate attached to the one or more springs (110A).

5. The vehicle of claim 1, wherein the first removable battery compression device comprises a hollow extrusion having a polygonal cross-section (408).

6. The vehicle according to any one of claims 1 to 5, further comprising: A second removable battery compression device (108) is disposed within the housing (104) and is configured to apply a compressive force to the plurality of layers of the battery via a second side of the battery (106).

7. A vehicle according to claim 1 or 6, wherein at least one wall of the shell comprises a structural element of the wing (102).

8. The vehicle of claim 7, wherein the structural element is one of a spar (210, 212) or a rib (204).

9. A vehicle according to any one of claims 1 or 7-8, wherein the first removable battery compression device (108) is configured to apply a compressive force to the multiple layers of the battery in a direction along the span of the wing (102).

10. A vehicle according to any one of claims 1 or 7-9, wherein the first removable battery compression device (108) is configured to apply a compressive force to the multiple layers of the battery in a direction along the chord of the wing (102).

11. A vehicle according to any one of claims 1 or 7-10, wherein: The wing comprises a plurality of engageable sections (202), The housing (104) is disposed within an engageable section of the plurality of engageable sections, and Each of the plurality of engageable segments (202) includes a power connector configured to enable power to flow from one of the plurality of engageable segments to one of: another segment of the plurality of engageable segments, or a body (220) of the vehicle.

12. The vehicle of any one of claims 1 or 7-10, wherein the vehicle is an unmanned aerial vehicle (UAV).

13. A method of using a removable battery compression device, comprising: installing (502) a removable battery compression device (208) in a vehicle (200); charging (504) a battery (206) comprising a plurality of planar layers compressed by the removable battery compression device; removing (506) the removable battery compression device (208) from the vehicle (200); as well as After removing the removable battery compression device (208) from the vehicle (200), the vehicle is operated (508) using power from the battery (206).

14. The method of claim 13, comprising installing the removable battery compression device (208) within a housing (204) in a section (202) of a wing of the vehicle (200).

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