Patent Publication Number: US-2023132570-A1

Title: Electronic Parachute Deployment System

Description:
This application claims the benefit of U.S. Provisional Pat. Application No. 63/279,429 filed on 15 Nov. 2021, titled “Electronic Parachute Deployment System,” and is a continuation-in-part of U.S. Patent Application No. 16/731,330 filed on 31 Dec. 2019, titled “Electronic Parachute Deployment System,” both of which are incorporated herein in their entirety for all purposes. 
    
    
     BACKGROUND 
     1. Field of the Invention 
     The present application relates to parachute deployment systems. In particular, the present application relates to electronic parachute deployment systems for the racing industry. 
     2. Description of Related Art 
     Currently, racecars, such as those used for drag racing, use manual levers for parachute deployment. For example, these racecars often include a manual lever located in proximity to the driver, which must be manually actuated at the end of the race or during an emergency situation to reduce vehicle speed. Race tracks are getting smaller as drag racing is beginning to be more available in a variety of different venues. Lever actuation requires at least three different driver actions, including reaching, grasping, and pulling. CO 2  release mechanisms require another step of priming the device before even going down the track. Requiring a driver to perform at least these three actions each time parachute deployment is necessary is time-consuming, which could have devastating consequences to operators or spectators. Manual actuation also involves adjusting cable tension, or otherwise manually actuating physical components, which can cause further delay between actuation and chute deployment. 
     Although current parachute deployment systems provide highly valued safety measures, they do not include additional safety features. Unfortunately, current parachute deployment systems provide few if any options for racecar drivers to have redundant electronic or physical safety measures. They also provide few options for monitoring functionality of specific safety features associated with parachute deployment. Foreseeing the need for shorter stopping distances, or attempting to meet existing safety requirements, racecar owners often install large, bulky bags and storage containers on the vehicle for parachute deployment. However, the ability to monitor specific safety features and proper chute deployment operation is nearly impossible or non-existent. Furthermore, deployment from the bulky bags can be slow, causing additional, unnecessary delay. Even the CO 2  deployment systems, which takes the least amount of time for the parachute to be deployed, will not be able to help if the driver is unable to do all the necessary steps in order to activate that system. 
     Although the aforementioned methods of parachute deployment represent great strides in the area of parachute deployment systems, many shortcomings remain. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The novel features believed characteristic of the invention are set forth in the appended claims. However, the invention itself, as well as a preferred mode of use, and further objectives and advantages thereof, will best be understood by reference to the following detailed description when read in conjunction with the accompanying drawings, wherein: 
         FIG.  1    is a block diagram of an electronic parachute deployment system according to the preferred embodiment of the present application; 
         FIG.  2    is a block diagram of an electronic parachute deployment system having a remote deployment feature; 
         FIG.  3    is a time sequence diagram of a method of electronic deployment using the remote deployment feature of  FIG.  2   ; 
         FIG.  4    is a schematic diagram of a network for remote electronic parachute deployment; 
         FIG.  5    is a perspective view of the internal driver compartment of a racecar having an electronic parachute deployment feature; 
         FIG.  6 A  is a perspective view of an actuation assembly and control module in a resting position; 
         FIG.  6 B  is a perspective view of the actuation assembly and control module of  FIG.  6 B  in an actuated position; 
         FIG.  7    is a cross-sectional view of a release mechanism and parachute container; 
         FIG.  8 A  is a cross-sectional view of a portion of the release mechanism of  FIG.  7    in a resting position; 
         FIG.  8 B  is a cross-sectional view of a portion of the release mechanism of  FIG.  7    in an actuated position; 
         FIG.  8 C  is a cross-sectional view of a portion of the release mechanism of  FIG.  7    in an actuated position; 
         FIG.  9    is a perspective view of a flexible parachute container; 
         FIG.  10 A  is a perspective view of a rigid parachute container; 
         FIG.  10 B  is a top view of gears of a release mechanism; 
         FIG.  11    is a block diagram of a control module; 
         FIG.  12    is a flow chart of a method for electronic parachute deployment using the control module of  FIG.  11   ; and 
         FIG.  13    is a perspective view of an alternative embodiment of the electronic parachute deployment system of the present invention as used to replace a conventional CO 2  launch system. 
     
    
    
     DETAILED DESCRIPTION 
     Referring to  FIG.  1    in the drawings, an electronic parachute deployment system  100  is illustrated. Electronic parachute deployment system  100  includes a control module  102  having memory and a processor, electronic actuator  104 , such as a pressure activated button, control-interfacing deployment actuator  106 , such as a push/pull solenoid, and chute-interfacing release mechanism  108 . In a preferred embodiment, the chute-interfacing release mechanism is configured to deploy a parachute. For example, electronic parachute deployment system  100  receives an electronic activation signal from electronic actuator  104 , converts the signal to a proper voltage for solenoid  106 , relays the signal to solenoid  106 , and solenoid  106  activates the release mechanism, thereby deploying the parachute. 
     Electronic actuator  104  includes a push button hard-wired to a control module, Bluetooth circuitry, radio frequency and circuitry, barometric pressure sensor circuitry, altimeter circuitry, infrared circuitry, pressure circuitry, or any combination thereof. 
     Solenoid  106  is connected to release mechanism  108 . Release mechanism  108 , includes but is not limited to, a ripcord, an altimeter, a Bowden cable, a lever, or combinations thereof. In a preferred embodiment, the chute-interfacing release mechanism is connected to a lever. 
     Release mechanism  108  is connected to parachute container  110 , and receives a manual activation or an electronic activation signal from solenoid  106 . The release mechanism is connected to parachute container  110  in order to deploy parachute  112 . Parachute container  110  is rigid, semi-rigid, flexible, semi-flexible, or a combination thereof. 
     Control module  102  is connected to power source  114 , redundant power source  116 , and voltage regulator  118 . Voltage regulator  118  is a fuse, circuit breaker, a capacitor, a resistor, or a combination thereof. Power source  114  and redundant power source  116  are direct current power sources. In a preferred embodiment, the power sources are batteries ranging from 12-24 volt batteries. 
     Although the power supply to control module  102  is depicted as a battery, the present application encompasses additional, and/or interchangeable power supplies. For example, the power supply to control module  102  includes a cell battery, lithium battery, capacitor, solar cells, monitoring/regulating integrated circuits, or any combination thereof. When power sources of different capacity, voltage, or amperage are connected, depending on the payload to which it is attached, one or more additional voltage regulators  118  may be added to the system. 
     Control module  102  includes power monitor  120  for monitoring voltages of the power sources and optimizing energy availability and usage. Preferably, power monitor  120  is a battery monitor. For example, the memory of the control module is pre-programmed with computer-executable instructions for determining a definitive battery voltage, comparing that voltage to a voltage of the redundant battery, and switching to the redundant battery as the power supply when the voltage of the redundant batter is beyond a threshold value or the first battery voltage is below a threshold value. 
     Control module  102  includes a processor, such as an ARM, or similar microprocessor and a memory unit, such as flash or other solid-state memory. The control module includes a circuit board having ports, modules, and integrated circuits, such as GPIO, Ethernet, transceiver, 12C bus, AUX, SPI, power supply, GSM/GPRS modem, and combinations thereof. 
     Preferably, each of the components of parachute deployment system  100  are located on or within payload  122 . In a preferred embodiment, payload  122  is a racecar, such as a drag racer with a roll cage. However, in alternative embodiments, payload  122  includes a drone or other unmanned aerial vehicle (UAV), a boat, a rocket, a Soyuz capsule, or a manned aircraft. 
     Control module  102  includes indicator  130 . Indicator  130  includes any user output capable of indicating at least two states of the control module. Preferably, indicator  130  includes a green LED indicating an idle state of the parachute deployment system. Indicator  130  further includes a red LED to indicate an active or deployment state of the control module. Indicator  130  further includes any means for providing a control state or status to an operator, including visual and audio output, such as an audible tone or voice alert. In at least one embodiment, indicator  130  includes a portion of a head-up display (HUD). 
     Referring now also to  FIG.  2    in the drawings, electronic parachute deployment system  200  includes control module  202  connected to payload transceiver  204 . Payload transceiver  204  is connected, wirelessly, to remote device  205  to receive a remote deployment activation signal. Control module  202  is further connected to deployment actuator  206  to send a deployment signal to release mechanism  208 . Release mechanism  208  receives the deployment activation signal from control-interfacing deployment actuator  206  to actuate a parachute connector. In a preferred embodiment, the activation of the release mechanism  208  further triggers opening of chute container  210 , which deploys parachute  212 . 
     In a preferred embodiment, deployment actuator  206  is a solenoid, as depicted in  FIG.  1   . In alternative embodiments, deployment actuator  206  includes a solenoid, a stepper motor, an actuator, a motor, a linear drive system, a servo motor or drive system, a proximity sensor, an altimeter, or any combination thereof. 
     In a preferred embodiment, the chute-interfacing release mechanism  208  is a second linear actuator connected to a puncture needle. The chute-interfacing release mechanism  208  further includes a Bowden cable, a second linear actuator connected to a cam locking device, a rod, a lever, a string, a ripcord, a strap, linkage, or any combination thereof. It is noted that the terms “release drive unit” and “release mechanism” are used interchangeably in the present application. 
     Control module  202  is further connected to battery  214 , redundant batter  216 , voltage regulator  218 , and battery monitor  220 . It is noted that although voltage regulator  218  is depicted as being associated in proximity to the batteries, such as on battery connectors, this depiction is not limiting. For example, voltage regulator  218  may also be placed on a circuit board of control module  202 . 
     Control module  202  further includes verifier  224 . For example, a set of computer-executable instructions are configured to receive an electronic activation signal from remote device, and verify that the remote device has authorization to communicate with the control module. The verification includes, but is not limited to, checking source identifiers such as MAC addresses, destination identifiers, Mobile Station Identity (IMEI) number, Mobile Equipment Identifier (MEID) number, unique device identifier (UDID), universally unique identifier (UUID), amplitude, frequency, signal type, modulation type, number of access attempts, access attempt frequency, and combinations thereof. The verification checking includes a comparison of received hardware or signal identifiers to expected values, including but not limited to, table entry values, administrator inputs, stored sequence values, and combinations thereof. If a signal does not pass the verification, it is blocked from components of the parachute deployment system, including the deployment actuator and the release mechanism. 
     Preferably, each of the components of parachute deployment system  200  are located on or within payload  222 , except for remote device  205 , which is remotely located relative to payload  222 . In a preferred embodiment, payload  222  is a racecar, such as a drag racer with a roll cage. However, in alternative embodiments, payload  222  includes a drone or other unmanned aerial vehicle (UAV), a boat, or a manned aircraft. 
     Referring now also to  FIG.  3    in the drawings, method  300  for remotely and electronically deploying a parachute from a payload using asymmetric encryption is illustrated. It is noted that although an asymmetric encryption algorithm is depicted, other forms of secure signal transmission are encompassed by the features of the present application, including but not limited to, symmetric encryption, Encryption as a Service (EaaS), Link-level encryption, and use of cryptographic hash functions. 
     Step  302  includes providing a private key to remote device  205 . For example, the private key is pre-programmed into a memory of the remote device. 
     Step  304  includes providing a public key to control module  202 . For example, the public key is pre-programmed into a memory of the control module. It is noted that although the public key is stored in the control module, in an alternative embodiment, the private key may be stored in the control module with the corresponding public key being stored in the remote device. 
     Step  306  includes activating remote device  205  to generate a request signal that includes a random number. For example, a key fob includes a pressure-activated button, which is pressed to generate the request signal. By way of another example, an interactive icon of a Ul of a mobile device is activated to generate the random number. 
     Step  308  includes sending the request signal including the random number to payload transceiver  204 . Payload transceiver  204  receives the request signal. 
     Step  310  includes sending, from the payload transceiver to remote device  206 , an access confirmation signal which includes the random number. 
     Step  312  includes receiving, at the remote device, the access confirmation signal including the random number. Step  312  further includes the remote device verifying that the random number received in the access confirmation signal is the same as the random number sent in the request signal. 
     When the random number is verified, step  314  includes generating a chute deployment activation signal. The generation of the chute deployment activation signal is automatic or is triggered by the initial user input as long as the random number initially generated has been verified. 
     Step  316  includes encrypting the chute deployment activation signal with the private encryption key. For example, a Rivest-Shamir-Adleman (RSA) algorithm may be used to encrypt the activation signal. 
     Step  318  includes sending the activation signal that has been encrypted with the private key to payload transceiver  204 . 
     Step  320  includes receiving, at the payload transceiver, the encrypted activation signal. 
     Step  322  includes sending the encrypted activation signal from the payload transceiver to control module  202 . 
     Step  324  includes receiving, at the control module, the encrypted deployment activation signal. 
     Step  326  includes decrypting the activation signal at the control module. For example, the public key stored in memory at the control module is used to decrypt the deployment activation signal. 
     Step  328  includes verifying the activation signal is in the proper form to be received by the deployment actuator. For example, step  328  may include verifier  224  converting voltages, changing frequency or amplitudes, or otherwise checking, modifying, and/or amplifying the activation signal such that the deployment actuator may receive the activation signal. 
     Step  330  includes sending the deployment activation signal from the control module to deployment actuator  206 . In a preferred embodiment, the deployment actuator is a solenoid. Step  330  further includes indicating at the control module a deployment state based on the state of the solenoid. For example, when no power is detected at, or supplied to, the armature, an indicator, such as a green LED, indicates that the payload device is in a racing mode and that the control module is in an idle state/mode. When power is detected at, or supplied to, the armature of the solenoid, the plunger pulls and a red LED indicator indicates that the state of the control module is a deployment state/mode. 
     Step  332  includes deployment actuator  206  receiving the deployment activation signal and deploying the parachute. 
     Referring now also to  FIG.  4    in the drawings, a distributed parachute deployment network  400  is illustrated. Network  400  includes administrator device  401 , control module  402 , electronic button actuator  404   a , lever actuator  404   b , and solenoid  406 , mechanically and/or electrically connected to racecar  422 . For example, control module  402  is mechanically connected to the roll cage of the car. By way of another example, the control module  402  is electrically or communicatively connected to a control sensor, such as a sensor connected to an engine control unit (ECU) or engine control module (ECM) of the racecar. 
     A first remote device  405   a , such as a smart phone having client software installed or downloaded thereto, is communicatively coupled to the racecar and to a wide area network (WAN), such as internet  409   a , or to a mobile network  409   b . Admin device  401  is connected to either Internet  409   a  or mobile network  409   b  to facilitate administrative functions, including password tracking and user interface (Ul) software updates. Preferably, admin device  401  includes a cloud server, a personal desktop computer, a gateway computer, a router, a switch, a hub, or combinations thereof. 
     In a preferred embodiment, first remote device  405   a  is used by a racing official or someone in the announcing box. In other embodiments, the first remote device  405   a  is used by military personnel, NASA technicians, and other ground crew to remotely deploy a parachute attached to a payload. 
     A second remote device  405   b  is communicatively coupled to the racecar and to the Internet or mobile network. Second remote device  405   b  is operated by a member of the pit crew, or at a different location than the first remote device. The first and second remote devices include, but are not limited to, mobile phones, tablet computers, personal digital assistants (PDAs), a laptop computer, a digital music player, or other similar media device. 
     Preferably, each UI of each remote device communicatively coupled to network  400  includes a status indicator, such as the MPH of racecar, as well as an interactive icon, allowing for remote deployment of the parachute from parachute release container  410  based on the status indicator as well as the observations of the remote device operator. The Ul may include multiple status indicators, including but not limited to, engine status, pressure gauge readings, RPMs, temperatures, fluid levels, and other data available to an ECM or ECU. Although not depicted, each Ul may also include a status indicator for operability of each component of the parachute deployment system. For example, a status indicator may provide current voltage level of the first battery  414 , voltage level of the redundant battery  416 , a racing mode of the control module, a deployment mode of the control module, and an actual deployment state of the parachute. For instance, a sensor associated with the parachute indicates when actual deployment occurs. 
     Each remote device connected to network  400  is also programmed or pre-programmed with authorization from admin device  401  to activate deployment of parachute  412 . For example, the admin device is used to install the private encryption key on each authorized remote device connected to the network. It is noted that although an application installed on a remote device includes all necessary and available features, the admin device is used to grant or deny permissions or access to certain features of the deployment executable application. For example, certain military personnel operating remote devices may have access to see status indicators, while only the commanding officer may have access to activate parachute deployment. 
     Referring now also to  FIG.  5    in the drawings, an interior portion of racecar  422  is illustrated. Racecar  422  includes electronic button actuator  504   a  and lever actuator  504   b . Button actuator  504   a  is a configuration used for retrofitting racecars without the electronic chute deployment system installed by a manufacturer. Lever actuator  504   b  is a control-interfacing deployment actuator that is installed by a manufacturer. 
     Preferably, each chute deployment actuator is located in proximity to hands of the driver relative to a driving grip to minimize reaching distances. For example, button actuator  504   a  is located on the steering wheel such that driver reach distance is at a minimum. By way of another example, lever actuator  504   b  is located near the steering wheel or hand of the operator to minimize reaching. It is noted that lever actuator  504   b  offers redundancy to the electronic actuation of button actuator  504   a . For example, the redundancy can be mechanical redundancy, electrical redundancy, optical redundancy, or combinations thereof. 
     In at least one embodiment, a driver attempts to pull the lever actuator  504   b  and realizes parachute deployment does not occur. Using audio input/output (l/O) user interface (Ul)  527 , such as a speaker and microphone, located in the helmet or on the dashboard of the racecar, the driver indicates to pit crew, racing officials, or an operator of a remote device that mechanical and/or electrical local deployment is not possible. Upon receiving this indication, the operator of the remote device provides user input to the remote device to remotely actuate deployment of the parachute. For example, an active icon for parachute deployment may be activated from a smart phone being used by the pit crew of the driver to remotely deploy the parachute. 
     In at least one embodiment, the audio I/O Ul  527  receives a voice command from the payload operator to deploy the parachute. The voice command may be a verifiable command, and may require user confirmation of the command. 
     Referring now also to  FIG.  6 A  in the drawings, a perspective view of control module  602 , button actuator  604 , solenoid  606 , and lever actuator  608  is illustrated. Lever actuator  608  pivots at a pivot point  611  when it is actuated. 
     In a preferred embodiment, lever actuator  608  is adjustable using adjustment holes  613 . Lever actuator  608  is connected to a plunger connection assembly, which connects the lever to solenoid  606 . In a preferred embodiment, solenoid  606  is a pull solenoid. 
     Solenoid  606  is attached to roll cage  626  of the car using U-bolts, clamps, braces, mounts, fasteners, and other attachment means. The redundant mechanical cable is attached to roll cage  626  using a cable mount or connector, including fasteners, zip ties, and other attachment means. 
     Control module  602  is attached to the roll cage of the car using U-bolts, clamps, braces, mounts, fasteners, and other attachment means. The control module includes indicator  630  to indicate the deployment status of the parachute, to indicate the control status of the control module, or a combination thereof. Mechanical cable  628  runs along the length of the car to a release mechanism located at the rear of the vehicle. 
     In at least one embodiment, cable  628  includes a wire so that an electrical pulse is sent from the control module down the wire and returned back to the control module. In the event cable  628  is cut, the return pulse is not received by the control module. When the pulse is not received, the control module receives an indication of mechanical actuator inoperability. The control module indicates this inoperability on the Ul of any remote device connected to the parachute deployment network. 
     Control module  602  includes port  632  on a single side of the module. The port  632  is used for all electrical ingress and egress. For example, ground wire  634  and power supply wire  636  each enter/exit the port and are connected to ground and the battery switch respectively. Coiled button actuator wire  638  enters/exits port  632  and is connected to the button actuator located on the steering wheel. 
     Lever actuator  608  receives force  640  to actuate deployment of the parachute. For example, force  640  is supplied by control module  602  sending an electronic activation signal to solenoid  606  to pull the plunger, thereby pulling and pivoting lever actuator  608 . By way of another example, force  640  is supplied by the driver reaching up and manually pulling the lever. 
     When the solenoid receives force  640  using an electronic activation signal, a second wireless activation signal is generated and sent simultaneous with receipt of the first activation signal at the control module. This second wireless activation signal is sent to a linear actuator of a release mechanism to deploy the parachute (see  FIG.  7   -8C below). 
     In a preferred embodiment, a control sensor  642  is communicatively coupled with the control module  602 . Control sensor  642  is configured to detect activation of an actuator or a component of an actuator. For example, control sensor  642  could be a hall-effect sensor, a proximity sensor, an optical sensor, or any combination of them. When cable  628  is activated, control sensor sends a signal to the control module  602  to indicate activation or a movement of the cable. In other embodiments, the control sensor  642  may be integral to an engine of the vehicle, and may indicate when a component, such as the engine solenoid, is active and/or inactive. 
     Referring now also to  FIG.  6 B  in the drawings, lever actuator  608  has received force  640  and has assumed an actuated position, which moves the plunger of the solenoid and increases the tension on cable  628 . The mechanical movement of the lever and increase in cable tension causes a redundant mechanical manipulation at the release mechanism to deploy the parachute in the event the electronic deployment is inoperable or delayed. Alternatively, the mechanical manipulation may be inoperable due to a cut or inoperable cable, in such circumstances the remote actuation feature of the parachute deployment system offers a redundant electrical manipulation at the release mechanism to deploy the parachute. 
     Referring now also to  FIG.  7    in the drawings, a preferred embodiment of the release mechanism of parachute container  110   a  is illustrated. Release mechanism  702  includes cable  704  attached to linear actuator  706  and puncture needle  708 . 
     Puncture needle  708  is biased by biasing means, such as spring  710 . Puncture needle  708  is in close proximity, adjacent to, or abutting a seal of CO2 canister  712 . It is noted that although canister  712  is depicted as a CO2 canister, other inert gases are encompassed by the features of the present application. For example, nitrogen or air may be used in lieu of CO2. 
     Preferably, when the release mechanism is actuated, puncture needle pierces the seal of CO2 canister  712 , allowing pressurized CO2 to pass through a channel created by first flange  714 , second flange  716 , third flange  718 , and fourth flange  720 . Third flange  718  and fourth flange  720  are removably connected to first flange  714  and second flange  716  and are associated with rigid parachute container  722 . 
     Rigid parachute container  722  includes lid  724 , gasket or rubber seal  726 , and beveled edge  728 . Gasket  726  and beveled edge  728  are formed of a specific shape to ensure a gauged release occurs when rigid parachute chamber  722  obtains a specific pressure. Lid  728  includes a connector  730  attached to the lid and parachute container  722  to retain the lid proximal to the parachute container after deployment of parachute  732 . 
     Parachute  732  includes leads, lines, or cables spooled onto spool  734 . Spool  734  includes a handle (not shown) and a crank attached to the spool and extending beyond the exterior of the parachute container in order to reel the lines back in and refold the parachute after deployment. 
     Parachute container  722  is mounted to, or within, the racecar using mount  736 . Mount  736  includes rubberized fasteners  738 , or self-sealing fasteners, such that the parachute chamber can remain pressurized without leaking. 
     In an alternative embodiment, such as when the parachute deployment system is installed on high-altitude surveillance drones, a pressurized parachute container is the component that is punctured or opened, exposing the inner contents to the lower pressure of the atmosphere. In this embodiment, the parachute deployment relies on the pressure differential between the pressurized parachute compartment and the low atmospheric pressure to emit the parachute into the atmosphere. 
     Referring now also to  FIG.  8 A  in the drawings, linear actuator  706  is mounted on an internal set of tracks  801 , or other movement means. Release mechanism further includes first cable stop  802 , second cable stop  803 , and third cable stop  804 . 
     Referring now also to  FIG.  8 B  in the drawings, when the release mechanism is mechanically actuated by cable  628  or cable  704 , third cable stop  804  prevents cable  628  or cable  704  from moving while the increased cable tension extends puncture needle  708  into the seal on CO2 canister  712 . It is noted that the mechanical actuation is redundant to the electrical actuation depicted below. 
     Referring now also to  FIG.  8 C  in the drawings, when a wireless activation signal is received by linear actuator  706 , the linear actuator moves a housing of the linear actuator which abuts first cable stop  802 . The movement of the housing corresponds with track  801 , and extends puncture needle  708  into the seal of CO2 canister  712 . 
     Referring now also to  FIG.  9   , a release mechanism of an embodiment of a parachute container  110   b  is illustrated. The parachute container  902  is a semi-rigid or flexible parachute container. Parachute container  110   b  is connected to car mount  904 , which has a distal end  906  attached to the racecar. Cable  908  is attached to car mount  904  and extends to parachute container  902 . 
     Parachute container  902  includes first pin loop  910  and second pin loop  912 . Pin  914  extends through first pin loop  910  and second pin loop  912 . Upon receiving mechanical or electrical activation at the solenoid, cable tension is created to pull pin  914  through the loops and release the parachute folded within the flexible container. Pin  914  includes a straight pin, detent pin, quick-release pin, and combinations thereof. 
     Parachute container  902  is attached to the racecar using axial car mount  916 , which runs along a center axis of the racecar. Mounting plate  918  is attached to car mount  916  and to flexible parachute container  902 . The attachment may include threaded attachment, clasps, rivets, pins, screws, bolts, glue, or a combination thereof. Mounting plate  918  includes one or more holes formed through the plate, enabling wind current, or pressurized gas from a canister attachment, to pass through the holes to help eject the folded parachute from the chamber. 
     Referring now also to  FIGS.  10 A and  10 B  in the drawings, a release mechanism for an embodiment of a parachute container  110   c  is illustrated. Parachute container  110   c  includes release mechanism sub-assembly  1000 . Release mechanism sub-assembly  1000  includes a semi-enclosed release box frame  1002 , parachute  1004 , and parachute holding plate  1006 . At least a back portion of a rear panel of release box frame  1002  is exposed, non-enclosed, or connected to a pressurized gas canister. In a preferred embodiment, parachute holding plate  1006  is attached to a top portion of the parachute and is made from light-weight, durable material, such as a titanium alloy or carbon composite fibers. 
     Parachute holding plate  1006  includes an elongated elliptical hole that corresponds to elliptical head  1010  of cam locking device  1012 . Cam locking device  1012  includes cam chamber  1014  and a cam housing. The cam housing is securely attached to the racecar and may include an opening to allow gears to translate back and forth, and an opening for a linear actuator interface. Cam chamber  1014  houses cam gears, including first bevel gear  1016  and second bevel gear  1018 . Second bevel gear  1018  includes a toothed edge that runs along track  1020 . When the gears rotate as the teeth of the second bevel gear move along track  1020 , cam shaft  1022  rotates. The rotation of cam shaft  1022  either locks or unlocks holding plate  1006  depending on the direction the cam locking device moves. Cam linear actuator  1024  connects, or is otherwise attached to, the cam locking device to move the locking device back and forth, respectively locking and unlocking the holding plate. Although not shown, release box frame  1002  may further include spools with crank handles for re-winding the parachute lead lines after deployment. Although the attachment of the parachute  1004  is depicted as being attached to the cam housing of the cam locking device, other attachment configurations are encompassed herein. For example, lead lines may be attached to spools with crank handles (not shown) that are attached to portions of the box frame  1002 . 
     Referring now also to  FIG.  11    in the drawings, a control diagram for control operation  1100  of control module  202  is illustrated. Control module  202  is communicatively coupled to payload transceiver  205 , a deployment actuator, such as deployment actuator  206  and/or release mechanism  208 , battery monitor  222 , and verifier  224 . Battery monitor  222  is coupled with first battery  214  and second battery  216  and includes a switch. Control module  202  is optionally communicatively coupled with control sensor  1140 . For example, a sensor of an ECM or ECU may be communicatively coupled with the control module to relay solenoid information from the ECM or ECU to the control module. The coupling of the control sensor  1140  is optional when retrofitted embodiments do not utilize ECM/ECU monitoring or redundant deployment actuator position monitoring. The communicative coupling of parachute deployment components to control module  202  can include wired, wireless, infrared, Bluetooth, and similar connections, as with a controlled area network (CAN). 
     Referring now also to  FIG.  12    in the drawings, method  1200  for remote electronic parachute deployment is illustrated. Method  1200  starts at step  1202  by an administrator providing public and private keys to the control module and the remote device. Step  1202  further includes a user installing the deployment client software onto appropriate remote devices, or installing necessary updates. 
     Step  1204  includes checking a control sensor. For example, the engine solenoid may be checked to ensure power is not still being sent to the engine solenoid to start the car. Step  1204  further includes checking the status of the engine ignition. These checks occur to determine a mode or state of the deployment control module. For example, if the ignition is on and the solenoid received power, but is no longer receiving power, then a racing mode is determined. 
     Step  1206  includes entering a control state based on a condition of the control sensor checked in step  1204 . For example, the control module determines the engine solenoid is still being powered, or is not off. Therefore, step  1206  includes entering a wait or delay state. 
     Returning to step  1204 , the condition of the control sensor is again determined. For example, the control module determines that the engine solenoid is off. 
     Step  1208  includes determining a state of one or more power supplies. For example, step  1208  includes determining that voltage available in the first battery is insufficient or below a threshold value. 
     Step  1210  includes activating a switch or relay based on the state of the one or more power supplies. For example, step  1210  includes switching the power supply from the first battery to the redundant battery. 
     Returning to step  1208 , includes entering a power control state based on the state of one or more power supplies. For example, the control module determines that power from the first battery is sufficient or above a threshold value and so a power control state using a primary power supply, or the first battery, occurs. 
     Step  1212  includes activating components of the parachute deployment system. For example, a control module indicator is activated. By way of another example, a payload transceiver is activated. 
     Step  1214  includes determining a state of a receiver or a transceiver of the payload device. For example, step  1214  includes determining that no remote deployment activation signal is received by the transceiver of the racecar. 
     Step  1216  includes entering a control state/mode based on the state of the receiver determined in step  1214 . For example, the control module may enter a wait or receive state until an activation signal is received. 
     Returning to step  1214 , the control module determines a second state of the receiver or transceiver of the payload device. For example, the control module determines that a remote deployment activation signal is received. 
     Step  1218  includes entering a control state based on the second state of the receiver or transceiver of the payload device. For example, the control module may enter a verification state, verifying the remote deployment activation signal is authorized or from a trusted source. 
     Step  1220  includes determining a condition of a signal using the verification state. For example, step  1220  includes determining that the source of a signal is not a trusted source. 
     Step  1216  includes entering a control mode/state based on the determination of the condition of the signal. For example, when the source is not trusted, the control module and the payload transceiver, at step  1216 , waits or remains in receive mode until an activation signal is received from a trusted or authorized source. In at least one embodiment, source identifiers associated with the untrusted source are stored to block future access attempts. 
     Returning to step  1220 , the control module determines that the deployment activation signal is authorized or from a trusted source. Step  1222  includes entering a control state/mode based on the determination that the source of the signal is a trusted source. For example, step  1222  includes a sending mode/state, where the control module activates the transceiver for sending a deployment actuator activation signal. 
     In at least one embodiment, the deployment actuator is a solenoid. Therefore, step  1222  includes determining power was sent to an armature of the solenoid, meaning that the plunger has been pulled. Simultaneous with sending power to the armature, power is sent to an indicator to indicate a deployment state of the control module. 
     Step  1224  includes ending the method of remote parachute deployment by resetting features of the system. For example, the parachute may need to be refolded and restored in its release compartment. By way of another example, short-term memory of the control module may be cleared to remove status indicators or sensory data that were applicable to an individual race. In an alternative embodiment, data associated with the individual race is sent to a data analytics unit. For example, admin device  411  is configured to receive statistics associated with each race performed by a racecar and operating conditions when parachute deployment occurred. After a threshold number of races and data analytics for those races are performed, the deployment executable application installed on a client device may include a feature that indicates suggested parachute deployment. For instance, if the MPH, RPMs, and time of engine operation above a certain level of RPMs coincides with corresponding average levels existing when previous parachute deployment happened, then the application may provide a suggested parachute deployment icon or other warning indicator. 
     It is noted that using the features of the present application allow payload operators, such as racecar drivers, pit crews, or racing officials, to quickly activate important safety measures, such as parachute deployment. This further enables redundant activation channels, including electronic and mechanical activation. Using these redundant channels, the safety of payload operators is significantly increased. These redundant channels further ensure the safety of the payload itself. For example, racecars, UAVs, personal items shipped by drones, and multi-million dollar aircraft each represent significant investments of money and time. The use of redundant mechanical and electrical deployment provides added security to these highly valued items. 
     It is further noted that embodiments of the present application use a server. In these embodiments, a server, for example, includes a data communication interface for packet data communication. The server also includes a central processing unit (CPU), in the form of one or more processors, for executing program instructions. The server platform typically includes an internal communication bus, program storage and data storage for various data files to be processed and/or communicated by the server, although the server often receives programming and data via network communications. The hardware elements, operating systems and programming languages of such servers are conventional in nature. Of course, the server functions may be implemented in a distributed fashion on a number of similar platforms, to distribute the processing load. 
     In some embodiments, a remote device includes a computer type user terminal device, such as a PC or tablet computer. These types of remote devices similarly include a data communication interface CPU, main memory and one or more mass storage devices for storing user data and the various executable programs. 
     In some embodiments, a remote device includes a mobile device type user terminal. These types of remote devices may include similar elements, but will typically use smaller components that also require less power, to facilitate implementation in a portable form factor. The various types of user terminal devices will also include various user input and output elements. A computer, for example, may include a keyboard and a cursor control/selection device such as a mouse, trackball, joystick or touchpad; and a display for visual outputs. 
     In some embodiments, a Ul includes a microphone and speaker to enable audio input and output. Some smartphones include similar but smaller input and output elements. Tablets and other types of smartphones utilize touch sensitive display screens, instead of separate keyboard and cursor control elements. The hardware elements, operating systems and programming languages of such user terminal devices also are conventional in nature. 
     Therefore, embodiments of the methods of managing information about content transmission or data analytics outlined above may be embodied in programming. Program aspects of the technology may be thought of as “products” or “articles of manufacture” typically in the form of executable code and/or associated data that is carried on or embodied in a type of machine readable medium. “Storage” type media include any or all of the tangible memory of the computers, processors or the like, or associated modules thereof, such as various semiconductor memories, tape drives, disk drives and the like, which may provide non-transitory storage at any time for the software programming. All or portions of the software may at times be communicated through the Internet or various other telecommunication networks. Such communications, for example, may enable loading of the software from one computer or processor into another. Thus, another type of media that may bear the software elements includes optical, electrical and electromagnetic waves, such as used across physical interfaces between local devices, through wired and optical landline networks and over various air-links. The physical elements that carry such waves, such as wired or wireless links, optical links or the like, also may be considered as media bearing the software. As used herein, unless restricted to non-transitory, tangible “storage” media, terms such as computer or machine “readable medium” refer to any medium that participates in providing instructions to a processor for execution. 
     Therefore, a machine readable medium may take many forms, including but not limited to, a tangible storage medium, a carrier wave medium or physical transmission medium. Non-volatile storage media include, for example, optical or magnetic disks, such as any of the storage devices in any computer(s) or the like, such as may be used to implement the application(s), etc. shown as implemented in the drawings (see, e.g.,  FIG.  4   ). Volatile storage media include dynamic memory, such as main memory of such a computer platform. Tangible transmission media include coaxial cables; copper wire and fiber optics, including the wires that comprise a bus within a computer system. Carrier-wave transmission media may take the form of electric or electromagnetic signals, or acoustic or light waves such as those generated during radio frequency (RF), Bluetooth, and infrared (IR) data communications. Common forms of computer-readable media therefore include for example: a floppy disk, a flexible disk, hard disk, magnetic tape, any other magnetic medium, a CD-ROM, DVD or DVD-ROM, any other optical medium, punch cards paper tape, any other physical storage medium with patterns of holes, a RAM, a PROM and EPROM, a FLASH-EPROM, any other memory chip or cartridge, a carrier wave transporting data or instructions, cables or links transporting such a carrier wave, or any other medium from which a computer may read programming code and/or data. Many of these forms of computer readable media may be involved in carrying one or more sequences of one or more instructions to a processor for execution. 
     Referring now also to  FIG.  13    in the drawings, another embodiment of the parachute release mechanism of the present application is illustrated. In this embodiment, an electronic parachute deployment system  1300  is used to replace a conventional CO 2  parachute deployment system. System  1300  is sized, shaped, and configured to have the same or similar dimensions as the conventional CO 2  parachute deployment system. System  1300  includes a housing  1302 , a mounting plate  1303 , a launcher rod  1304 , a parachute plate  1306 , a highly compressed spring mechanism  1308 , a locking device  1310 , and an electronic locking device  1312 . Mounting plate  1303  is mounted to the vehicle, preferably in the same location and orientation as the conventional CO 2  parachute deployment system. Housing  1302  holds the parachute. When system  1300  is activated as disclosed herein, electronic locking device  1312  is triggered, thereby releasing locking device  1310 , which allows launcher rod  1304  and parachute plate  1306  to quickly deploy the parachute. 
     It is apparent that an invention with significant advantages has been described and illustrated. Although the present application is shown in a limited number of forms, it is not limited to just these forms, but is amenable to various changes and modifications without departing from the spirit thereof.