Patent Publication Number: US-2023159166-A1

Title: Payload Delivery Device

Description:
The current application claims a priority to the U.S. provisional patent application Ser. No. 63/282,295 filed on Nov. 23, 2021. 
    
    
     FIELD OF THE INVENTION 
     The present invention relates generally to transportation and delivery systems. More specifically, the present invention provides a payload delivery device designed to facilitate the delivery of desired payloads via manned or unmanned aerial vehicles. 
     BACKGROUND OF THE INVENTION 
     Emergency medical services are generally delayed to emergency situations and scenes due to different factors such as distance, location of patient/victim, terrain, etc. Military providers that are engaged in Prolonged Field Care (PFC) or Prolonged Casualty Care (PCC) are required to treat and maintain a single patient in remote and austere environments for up to 72 hours on their own with limited gear. The idea of using both manned and unmanned aircraft to reduce the time to initial response of medical supplies or resupply to forward military operators in hazardous situations is a current challenge in the medical field. 
     A survey was completed at the University College Cork in 2020 where 94% of participants agreed that a payload harness that can be integrated into manned and unmanned aircraft is something that would both be useful and is currently needed in the medical response field. Participants also agreed that on the civilian side using a brightly colored parachute with alternating colors (i.e., bright orange/white, red/yellow, etc.) would assist in locating a victim during search and rescue operations. Therefore, there is a need for an improved payload harness and parachute device that may overcome one or more of the above-mentioned problems and/or limitations. 
     An objective of the present invention is to provide a payload delivery device designed to be transported by an Unmanned Aerial Vehicle (UAV). The present invention can be transported by a UAV to a target area where the payload delivery device can be deployed. Another objective of the present invention is to provide a payload delivery device that safely delivers the desired payload to the target location. The present invention is designed to securely hold the payload while the payload is descending towards the target location. Another objective of the present invention is to provide a payload delivery device that protects the payload from any external forces resulting from the landing of the payload. Additional features and benefits of the present invention are further discussed in the sections below. 
     SUMMARY OF THE INVENTION 
     The present invention provides a payload delivery device designed to safely and securely deliver desired payloads. The present invention may be used with both unmanned and manned aircraft to increase the survivability of patients and victims in emergency situations. For example, the present invention may sustain and resupply military operators engaged in Prolonged Field Care (PFC) or Prolonged Casualty Care (PCC) and support Tactical Combat Casualty Care (TCCC) operations including the tactical evacuation phase (TECEVAC) by providing medical support supplies to operators. At the same time, the present invention could sustain victims in a remote civilian mountain environment. The present invention may be capable of carrying upwards of 20 pounds (lbs) for an unmanned aircraft and 30 to 60 lbs or greater depending on the aircraft requirements of emergency operators which can allow for greater payloads that offer better care in the field, increased survival, and lower mortality rates. The present invention may also assist in the rescue and sustainment of astronauts exploring other planetary bodies when natural rescue operations are currently limited, presently extended, and time is of the essence. The present invention can be used on other planetary bodies for immediate intervention while other rescue plans are being considered and acted on. 
     In some embodiments, the payload delivery device preferably includes means to safely and securely deliver the payload to target location, such as a parachute. Further, the payload delivery device protects the payload as the payload lands on the target location from any external forces the payload may experience while landing. Accordingly, in the preferred embodiment, the payload delivery device may include a stirrup or saddle-type harness with at least four cross arms. The four cross arms may be reinforced with single or dual layers of material. Further, the payload delivery device may include a top connection point with an anchor to be used to secure a parachute connection. The top connection also enables the attachment to manned or unmanned aerial vehicles, where the four cross arms each act as fail-safe for the device. In other embodiments, the payload delivery device may include a harness with an incorporated parachute. 
     Further, the payload device may be made from material with 5,000-pound tensile strength and is fireproof-rated up to 660 degrees Fahrenheit. The present invention may include various connectors such as metal clasps. The metal clasps are rated for a breaking strength of 18 kilonewtons (kN) (4,046.56 pounds per clasp). Each clasp is also ANSI-approved. Furthermore, the incorporated parachute of the present invention may be deployed upon release of the harness from the aerial vehicle giving the vehicle time to clear the area and to allow the proper deployment of the parachute. The present invention may be designed to deliver payloads from a hover position or in motion position to providers, patients, or victims on the ground. 
     Further, the present invention is designed to retain the payload securely while the parachute facilitates the controlled descent of the payload to the ground to reduce injury and/or damage to property included in the payload. This fits the guidelines posted by the FAA for part 107.23 concerning dropping items from unmanned aircraft. In some embodiments, the present invention may include inflatable attachments that are capable of being deployed upon contact with water to ensure the payload stays afloat. The payload and the inflatable attachments may create a personal flotation platform for rescuers, patients, or victims in the water. Further, the payload delivery device may include a back spine having two layers of webbing to allow for adjustment of the cross arms for oblong payloads as needed. Each opening and overlay of the cross straps may have a reinforced box stitch above and below to ensure that the cross arms are secure. Furthermore, the present invention may include an Automatic Deployment System (ADS) or Automatic Trigger System (ATS) that allows the payload to free fall as the aircraft safely moves away from the area before the parachute is deployed based on either time or altitude. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    is a top front perspective view of the present invention, wherein a plurality of cargo straps and the plurality of holder straps are shown unfastened. 
         FIG.  2    is a bottom rear perspective view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown unfastened. 
         FIG.  3    is a top front perspective view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown fastened, and wherein a chute canister and a payload are shown mounted. 
         FIG.  4    is a bottom rear perspective view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown fastened, and wherein a chute canister and a payload are shown mounted. 
         FIG.  5    is a front view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown fastened, and wherein the chute canister and the payload are shown mounted, and wherein a second base flotation device is shown inflated. 
         FIG.  6    is a rear view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown fastened, and wherein the chute canister and the payload are shown mounted, and wherein a first base flotation device is shown inflated. 
         FIG.  7    is a side view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown fastened, and wherein the chute canister and the payload are shown mounted, and wherein a plurality of cargo flotation devices is shown inflated. 
         FIG.  8    is a front view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown fastened, and wherein the chute canister and the payload are shown mounted, and wherein the present invention is shown connected to a releasable suspender. 
         FIG.  9    is a front view of the present invention, wherein the plurality of cargo straps and the plurality of holder straps are shown fastened, and wherein the chute canister and the payload are shown mounted, and wherein the present invention is shown connected to the releasable suspender. 
         FIG.  10    is a side schematic view of the chute canister of the present invention, wherein a parachute and an automatic deployment system are shown mounted within the chute canister. 
     
    
    
     DETAIL DESCRIPTIONS OF THE INVENTION 
     All illustrations of the drawings are for the purpose of describing selected versions of the present invention and are not intended to limit the scope of the present invention. 
     The present invention is a payload delivery device designed to facilitate the delivery of emergency items to a target location via aerial vehicles. As can be seen in  FIGS.  1  through  4   , the present invention comprises a base strap  1 , a plurality of holder straps  4 , and a plurality of cargo straps  11 . The base strap  1  serves as the central structure of the present invention that supports the plurality of holder straps  4  and the plurality of cargo straps  11 . The plurality of holder straps  4  includes several straps designed to retain a parachute  19  and the devices necessary to facilitate the deployment of the parachute  19 . The plurality of holder straps  4  is also designed to facilitate the operation of the parachute  19  while securing the parachute  19  to the base strap  1 . The plurality of cargo straps  11  include several straps that secure the payload to the present invention. The plurality of cargo straps  11  can also be arranged to accommodate the shape and size of the payload to be delivered. In some embodiments, the base strap  1 , the plurality of holder straps  4 , and/or the plurality of cargo straps  11  can have civilian and military specifications capable of sustaining 20 pounds (lbs.) of weight while suspended from an unmanned aircraft up to 400 feet (ft) and able to sustain drop forces when a parachute  19  is deployed at or near terminal velocity. The present invention can be capable of being able to slow a 20 lb. payload to 4 meters per second (m/s). 
     The general configuration of the aforementioned components enables a more secure and safe way of payload delivery via various aerial vehicles such as Unmanned Aerial Vehicles (UVAs). As can be seen in  FIGS.  1  through  4   , the base strap  1  is preferably a wide, long strap that is made from strong material able to retain the parachute  19 , associated devices, as well as the payload. Due to the overall flat shape of the base strap  1 , the base strap  1  comprises a first base face  2  and a second base face  3 . The first base face  2  and the second base face  3  correspond to the opposite flat faces of the base strap  1 . To assemble the present invention, the plurality of holder straps  4  is positioned parallel to each other. Further, each of the plurality of holder straps  4  is positioned perpendicular to the base strap  1 . This way, each of the plurality of holder straps  4  forms a “T” shape with the base strap  1 . In addition, the plurality of holder straps  4  is distributed along the base strap  1  to distribute the load from the parachute  19  on the base strap  1 . Further, the base strap  1  is centrally positioned to each of the plurality of holder straps  4  to evenly distribute the load subjected by the corresponding holder strap on the base strap  1 . Each of the plurality of holder straps  4  is connected onto the first base face  2  to secure the various holder straps to the base strap  1 . In a similar manner, the plurality of cargo straps  11  is positioned parallel to each other. In addition, the plurality of cargo straps  11  is positioned perpendicular to the base strap  1 . This way, each of the plurality of cargo straps  11  also forms a “T” shape with the base strap  1 . In addition, the plurality of cargo straps  11  is distributed along the base strap  1  to distribute the load from the payload on the base strap  1 . Further, the base strap  1  is centrally positioned to each of the plurality of cargo straps  11  to evenly distribute the load subjected by the corresponding cargo strap on the base strap  1 . Furthermore, each of the plurality of cargo straps  11  is connected onto the second base face  3  to secure the various cargo straps to the base strap  1 . 
     Further, the base strap  1 , the plurality of holder straps  4 , and the plurality of cargo straps  11  may be black. The style associated with the present invention may be Amp 5000 lbs. rated heavy-duty mil-spec military-grade nylon fastening. Further, the height associated with the present invention may be a minimum of 1.75 inches and the length may be 13.5 inches. Further, the weight associated with the present invention may be 8 pounds. A width associated with the present invention may be 13.5 inches. Further, a material type associated with the present invention may be nylon, a nylon blend (i.e. nylon/Kevlar), or nylon webbing. In some embodiments, the plurality of cargo straps  11  may be two or four cargo straps, and each cargo strap may be reinforced and include a second layer. Further, the base strap  1 , the plurality of holder straps  4 , and the plurality of cargo straps  11  can be made from 5,000-pound tensile strength material and be fireproof up to 660 degrees Fahrenheit. In other embodiments, the present invention may include spider straps that are for patient restraints to a long backboard but may use hook and loop fastener connections with a corresponding design. 
     In some embodiments, the present invention can be provided with an incorporated parachute  19  as well as the devices necessary to facilitate the deployment of the parachute  19 . As can be seen in  FIGS.  3  through  7  and  10   , the present invention may further comprise a chute canister  18  designed to readily retain a parachute  19  that is deployed according to predetermined conditions. To incorporate the chute canister  18  onto the base strap  1 , the chute canister  18  is positioned along the base strap  1  to evenly secure the chute canister  18  onto the base strap  1 . Further, each of the plurality of holder straps  4  is laterally positioned around the chute canister  18  so that the chute canister  18  is restrained against the first base face  2  by the plurality of holder straps  4 . This way, the chute canister  18  is safely secured to the base strap  1  while the present invention is being transported. Further, the present invention may further include a parachute  19  and an automatic deployment system (ADS)  20 . The chute canister  18  can be equipped with the parachute  19  prior to the present invention being mounted onto the desired aerial vehicle. Accordingly, the parachute  19  is positioned within the chute canister  18  while the present invention is being transported by the chose aerial vehicle. Similarly, the ADS  20  is mounted within the chute canister  18  so that the ADS  20  can be engaged to deploy the parachute  19 . The ADS  20  is operatively coupled to the parachute  19 , wherein the ADS  20  is used to automatically deploy the parachute  19  from the chute container at a specified altitude. For example, the ADS  20  can include a controller equipped with several sensors, such as an altimeter, a timer, etc., that engages the ADS  20  according to predetermined thresholds. In addition, the ADS  20  can be equipped with a mechanism that releases the chute canister  18  to enable the parachute  19  to be deployed. Further, the ADS  20  can include a mechanism that forces the parachute  19  out of the chute canister  18 , such a pyrotechnic or mechanical device that moves the parachute  19  out of the chute canister  18 . Alternatively, the ADS  20  may be attached to a canister or similar device allowing for a spring-loaded, CO2, or similar activation system to rapidly deploy the parachute  19  to allow for appropriate speed control. In alternate embodiments, the present invention can utilize different mechanisms to automatically deploy the parachute  19  at predetermined conditions. 
     As previously discussed, the present invention further secures the safe delivery of the payload by protecting the payload from undesired damage during the landing of the payload. As can be seen in  FIGS.  1  through  9   , the present invention may further comprise a first landing riser  21  and a second landing riser  22  that reduces the landing forces that may compromise the payload. The first landing riser  21  and the second landing riser  22  are designed to be attached or made part of the present invention to accommodate and protect the payload. Accordingly, the first landing riser  21  and the second landing riser  22  are positioned parallel to each other and separate from each other to accommodate the size. In addition, the first landing riser  21  is terminally connected to the base strap  1  to secure the first landing riser  21  to the base strap  1 . Similarly, the second landing riser  22  is terminally connected to the base strap  1 , opposite to the first landing riser  21 , to secure the second landing riser  22  to the base strap  1 . This way, when the payload is secured to the base strap  1  using the plurality of cargo straps  11 , the payload is positioned between the first landing riser  21  and the second landing riser  22 . Further, the first landing riser  21  and the second landing riser  22  are overall larger than the payload so that when the payload lands on the target location, the first landing riser  21  and the second landing riser  22  receive most of the load from the landing. 
     As can be seen in  FIGS.  1  through  4   , to facilitate the fastening of the chute canister  18  to the base strap  1 , each of the plurality of holder straps  4  may comprise a holder strap body  5  and a holder strap fastener  8 . The holder strap body  5  corresponds to the body of every holder strap, while the holder strap fastener  8  corresponds to the fastening mechanism that enables every holder strap to be fastened around the chute canister  18 . To secure the holder straps using the corresponding holder strap fastener, the holder strap body  5  comprises a first holder strap end  6  and a second holder strap end  7  corresponding to the terminal ends of the holder strap body  5 . Further, the holder strap fastener  8  may comprise a first holder interlocking piece  9  and a second holder interlocking piece  10  corresponding to the separate interlocking pieces of the holder strap fastener  8 . For example, the holder strap fastener  8  can be a snap-fit buckle with a male member and a female member. Further, the holder strap fastener  8  can withstand the drop and pull forces of a deployed parachute  19 . To secure the first holder interlocking piece  9  to the holder strap body  5 , the first holder interlocking piece  9  is connected adjacent to the first holder strap end  6 . Similarly, the second holder interlocking piece  10  is connected adjacent to the second holder strap end  7  to secure the second holder interlocking piece  10  to the holder strap body  5 . This way, once the holder strap body  5  is positioned around the chute canister  18 , the user can engage the first holder interlocking piece  9  with the second holder interlocking piece  10  to fasten the chute canister  18  to the base strap  1  using the various holder straps. 
     Similar to the plurality of holder straps  4 , each of the plurality of cargo straps  11  may comprise a cargo strap body  12  and a cargo strap fastener  15 . As can be seen in  FIGS.  1  through  4   , the cargo strap body  12  corresponds to the body of every cargo strap, while the cargo strap fastener  15  corresponds to the fastening mechanism that enables every cargo strap to be fastened around the payload. To secure the cargo straps using the corresponding cargo strap fastener, the cargo strap body  12  may comprise a first cargo strap end  13  and a second cargo strap end  14  corresponding to the terminal ends of the cargo strap body  12 . Further, the cargo strap fastener  15  may comprise a first cargo interlocking piece  16  and a second cargo interlocking piece  17  corresponding to the separate interlocking pieces of the cargo strap fastener  15 . For example, the cargo strap fastener  15  can be a snap-fit buckle with a male member and a female member. Further, the cargo strap fastener  15  can withstand the drop and pull forces of a deployed parachute  19 . To secure the first cargo interlocking piece  16  to the cargo strap body  12 , the first cargo interlocking piece  16  is connected adjacent to the first cargo strap end  13 . Similarly, the second cargo interlocking piece  17  is connected adjacent to the second cargo strap end  14  to secure the second cargo interlocking piece  17  to the cargo strap body  12 . This way, once the cargo strap body  12  is positioned around the payload, the user can engage the first cargo interlocking piece  16  with the second cargo interlocking piece  17  to fasten the payload to the base strap  1 . The holder strap fastener  8  and the cargo strap fastener  15  can be D-Ring COBRA ProStyle rated at 18 kilo-Newtons (kN). Further, the size of the holder strap fastener  8  and the cargo strap fastener  15  may be 1.75 in/45 mm black D-Ring. Further, the minimum breaking load of the holder strap fastener  8  and the cargo strap fastener  15  may be 18 kN. The material body of the holder strap fastener  8  and the cargo strap fastener  15  may be aluminum. Further, characteristics associated with the holder strap fastener  8  and the cargo strap fastener  15  specifications may include standard clips, one side adjustable, integrated D-Ring with color matte black. Further, the holder strap fastener  8  and the cargo strap fastener  15  may include Cross Arm Connections COBRA ProStyle 18 kN with a size of 1.75 in/45 mm and minimum breaking load of 18 kN. Further, the material body of the base strap  1  may be 12 mm aluminum with the color KTL black. 
     As previously discussed, the present invention provides means to protect the payload once the payload lands on the target location. If the payload lands on a body of water, the present invention can further provide means to maintain the payload afloat. As can be seen in  FIG.  7   , the present invention may further comprise a plurality of cargo flotation devices  23 . The plurality of cargo flotation devices  23  is designed to automatically deploy once the payload is in contact with a body of water. Accordingly, the plurality of cargo flotation devices  23  is positioned offset from the base strap  1  along the cargo strap body  12 . In addition, each of the plurality of cargo flotation devices  23  is connected adjacent to a corresponding cargo strap from the plurality of cargo straps  11 . This way, once the payload enters the body of water, the plurality of cargo flotation devices  23  is engaged to maintain the payload floating on the body of water. Further, the plurality of cargo flotation devices  23  can enable the payload to be used as a flotation device by the users whom the payload is delivered too. For example, a rescue package can be sent to overboard passengers who can use the floating rescue package to float while the rescue operation is deployed. 
     In addition to the plurality of cargo flotation devices  23 , the present invention can also include additional flotation devices distributed along the base strap  1  to help maintain the payload floating in a desired orientation. As can be seen in  FIGS.  5  and  6   , the present invention may further comprise a first base flotation device  24  and a second base flotation device  25 . The first base flotation device  24  is terminally connected to the base strap  1  to secure the first base flotation device  24  to the base strap  1 . Likewise, the second base flotation device  25  is terminally connected to the base strap  1 , opposite to the first base flotation device  24 , to secure the second base flotation device  25  to the base strap  1 . This way, the first base flotation device  24  and the second base flotation device  25  provide additional support to the payload to remain afloat while also preventing the payload from turning over. In addition to the flotation devices, the present invention may include means to separate the parachute  19  from the present invention. For example, the connection between the parachute  19  and the chute canister  18  can be mechanically separated once the payload enters the body of water. A controller with several sensors can be included to detect the submersion of the payload in the body of water which engages the mechanical device that releases the parachute  19  from the chute canister  18 . This way, the parachute  19  does not drag the payload along the current of the body of water. Similarly, the different flotation devices can be engaged by the controller once the payload has been detected to be submerged in the body of water. 
     As previously discussed, the present invention is designed to be transported by an aerial vehicle to a target area where the present invention is released to descend towards the target location. As can be seen in  FIGS.  8  and  9   , to enable the controlled release of the present invention on the target area, the present invention may further comprise a releasable suspender  26 . The releasable suspender  26  secures the present invention to the aerial vehicle during transportation and can be selectively engaged to release the present invention. To do so, the releasable suspender  26  is operatively coupled to the base strap  1 , wherein the releasable suspender  26  is used to readily release the base strap  1  from an aerial transportation vehicle. For example, the releasable suspender  26  can include a mechanical connection that tethers the base strap  1  to the aerial vehicle during transportation. The aerial vehicle&#39;s onboard computer or a remote computer can engage the releasable suspender  26  to release the base strap  1 , which enables the present invention with the payload to free fall until the ADS  20  engages and deploys the parachute  19 . 
     The present invention may be tested for maximum breaking points for the entire structure. The test may be performed to see if the plurality of cargo straps  11  can hold the payload if the stirrup or the base strap  1  breaks. A test may be performed to see how many cargo straps can fail before failure is catastrophic. Further, success criteria of the present invention may be evaluated by static platform tests at 50 ft, 100 ft, static unmanned aircraft tests at 100 ft, 200 ft, and 300 ft, dynamic tests being dropped from manned and unmanned aircraft at different altitudes approved by the Federal Aviation Administration, and Compliance with FAA Part 91.15, Part 105 and Part 107.23. The present invention may be associated and in compliance with FAA Part 135. The present invention may also be associated with universities and technical organizations for evaluation, design assistance, testing facilities, and technical standards order filing with the FAA, IAA, CAA, and European Union Aviation Safety Agency (EASA). Further, the present invention may undergo testing for the ADS  20  or similar for the deployment of the parachute  19 . 
     Further, medical providers may review testing data, providing input as to needs and requirements per specific working environment. Law enforcement providers may also review testing data, providing input as to needs and requirements per specific working environment. Further, FAA, IAA, CAA, and European Union Aviation Safety Agency (EASA) may review testing data, providing input as to needs and requirements per specific working environment. Further, evaluators outside of the normal requests include approved Imperial College London faculty or identified experts, approved Oxford faculty or identified experts, approved College Cork faculty or identified experts, United Kingdom Civil Aviation Authority officers, Irish Aviation Authority officers, and other approved field experts. 
     Furthermore, the present invention can be provided in different dimensions to accommodate different payload sizes. For example, in a medium-size embodiment, the base strap  1  can have a length of 4.75 ft (57 in.) and a width of 1.75 in. The plurality of holder straps  4  and the plurality of cargo straps  11  can have a length of 4.17 ft (50 in.) and a width of 1.75 in. Further, the webbing used can be AMP 5000 lbs. heavy duty industrial, with a fastening webbing width of 1.75 in. The medium-size embodiment can include a pocket to secure the chute canister  18 . The pocket can be 1.57 in. in diameter and 6.05 in. in length. In a large-size embodiment, the base strap  1  can have a length of 5.17 ft (62 in.) and a width of 1.75 in. The plurality of holder straps  4  and the plurality of cargo straps  11  can have a length of 3.5 ft (42 in.) and a width of 1.75 in. Further, the webbing used can also be AMP 5000 lbs. heavy duty industrial, with a fastening webbing width of 1.75 in. The large-size embodiment can include a pocket to secure the chute canister  18 . The pocket can be 1.57 in. in diameter and 6.05 in. in length. 
     Although the invention has been explained in relation to its preferred embodiment, it is to be understood that many other possible modifications and variations can be made without departing from the spirit and scope of the invention.