Patent Publication Number: US-2016236800-A1

Title: Network-based computing device and method for interactive aircraft maintenance procedures

Description:
BACKGROUND 
     This disclosure relates generally to network-based computing devices for interactive aircraft maintenance procedures and methods for using the same. 
     Today, interactive ground operations for an aircraft require an extensive manual effort. An interactive engine test, such as, for example, a power assurance check, requires an operator to look up information in tables, start the engine manually, adjust the throttle manually, perform engine sensor readings manually, and then make hand calculations to determine if an issue exists. This manual process is inefficient from a time perspective and may lead to human error. 
     Accordingly, there exists a need for improvements in aircraft maintenance procedures. 
     SUMMARY 
     In at least one embodiment, a method for interactive aircraft maintenance procedures comprises receiving an aircraft component operation request from a computing device, transmitting the aircraft component operation request to one or more aircraft components, receiving one or more aircraft component values based on the transmitting step, generating an aircraft status determination based on the receiving step at the computing device. 
     In at least one embodiment, the transmitting step is performed by a management system connected to the computing device via a wireless network. 
     In at least one embodiment, the aircraft status determination is further based on one or more known values. 
     In at least one embodiment, the aircraft status determination is further based on one or more acceptable value limits for the one or more aircraft component values. 
     In at least one embodiment, the method further comprising generating one or more derived attributes based at least in part on the one or more aircraft component values and one or more known values. 
     In at least one embodiment, the aircraft status determination is further based on the one or more derived attributes. 
     In at least one embodiment, a method for interactive aircraft maintenance procedures, comprises transmitting, from a computing device at a point of work, an aircraft component operation request to a management system, verifying the component at the point of work using the computing device, wherein the management system on the aircraft sends information to the computing device from the component and the verifying is based on the information. 
     In at least one embodiment, the verifying comprises viewing reports about the aircraft component displayed on the computing device. 
     In at least one embodiment, the verifying comprises combining the information with one or more known values at the computing device. 
     In at least one embodiment, the verifying further comprises assessing the information and the one or more known values against at least one minimum acceptable value. 
     In at least one embodiment, the computing device and the management stem communicate over a computer network. 
     In at least one embodiment, the computer network is a wireless network. 
     In at least one embodiment, the component is a plurality of components. 
     In at least one embodiment, an interactive aircraft component maintenance system comprises a computing device, a management system configured to receive an aircraft component operation request from the computing device, at least one aircraft component configured to receive the aircraft component operation request from the management device and transmit one or more values associated with the at least one aircraft component to the management system. 
     In at least one embodiment, the management system is further configured to transmit the one or more values to the computing device. 
     In at least one embodiment, the computing device is further configured to generate an aircraft component status determination based at least in part on the one or more values. 
     In at least one embodiment, the computing device is further configured to generate the aircraft component status determination based at least in part on one or more known values. 
     In at least one embodiment, the management system and the computing device communicate over a computer network. 
     In at least one embodiment, the computer network is a wireless network. 
     These and other features of the example disclosure can be best understood from the following specification and drawings, the following of which is a brief description: 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1A  is an architecture diagram displaying components of a system for execution for performance of interactive aircraft maintenance procedures with a network-based computing device according to at least one embodiment. 
         FIG. 1B  is an architecture diagram displaying components of a system for execution for performance of interactive aircraft maintenance procedures with a network-based computing device according to at least one embodiment. 
         FIG. 1C  is an architecture diagram displaying components of a system for execution for performance of interactive aircraft maintenance procedures with a network-based computing device according to at least one embodiment. 
         FIG. 2  shows a flowchart of an example method of performing interactive aircraft maintenance procedures with a network-based computing device according to at least one embodiment. 
     
    
    
     DETAILED DESCRIPTION 
     For the purposes of promoting an understanding of the principles, reference will now be made to the embodiments illustrated in the drawings, and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of this disclosure is thereby intended. 
     This detailed description is presented in terms of programs, data structures or procedures executed on a computer or network of computers. The software programs implemented by the system (i.e. on the computing device and/or aircraft module) may be written in any programming language—interpreted, compiled, or otherwise. These languages may include, but are not limited to, PHP, ASP.net, HTML, HTML5, Ruby, Perl, Java, Python, C++, C#, JavaScript, and/or the Go programming language. It should be appreciated, of course, that one of ordinary skill in the art will appreciate that other languages may be used instead, or in combination with the foregoing and that web and/or mobile application frameworks may also be used, such as, for example, Ruby on Rails, Node.js, Zend, Symfony, Revel, Django, Struts, Spring, Play, Jo, Twitter Bootstrap and others. 
     Referring now to  FIG. 1A , there is shown an architecture diagram detailing components of a system  100  for interactive aircraft maintenance procedures with a computing device according to at least one embodiment. As shown in  FIG. 1A , the system  100  includes one or more aircraft components  12 ,  14 , a computer network  15 , a management system  16 , and a computing device  18 . For purposes of clarity, only one computing device  18  is shown in  FIG. 1A , however, the system  100  may include any number of computing devices  18 . In addition, for clarity, only two aircraft components  12 ,  14  are shown in  FIG. 1A , however , the system  100  many include any number (including one) aircraft components  12 ,  14 . 
     Computing device  18  may be configured to transmit information to and generally interact with management system  16 . As shown in  FIG. 1A , management system  16  may be directly connected to the computing device  18 , such as, for example, through a serial connection. It should further be appreciated that management system  16  and computing device  18  may reside on a computer network (not shown) to enable connectivity, such as, for example, a wireless network. Computing device  18  may include a web browser, mobile application, socket or tunnel, or other network connected software such that communication with management system  16  is possible. 
     Computing device  18  includes one or more computers, smartphones, tablets, wearable technology, computing devices, or systems of a type well known in the art, such as a mainframe computer, workstation, personal computer, laptop computer, hand-held computer, cellular telephone, or personal digital assistant. Computing device  18  comprises such software, hardware, and componentry as would occur to one of skill in the art, such as, for example, one or more microprocessors, memory systems, input/output devices, device controllers, and the like. Computing device  18  also comprises one or more data entry means (not shown in  FIG. 1A ) operable by users of computing device  18  for data entry, such as, for example, voice or audio control, a pointing device (such as a mouse), keyboard, touchscreen, microphone, voice recognition, and/or other data entry means known in the art. Computing device  18  also comprises a display means (not shown in  FIG. 1A ) which may comprise various types of known displays such as a liquid crystal display, a light emitting diode display, and the like upon which information may be display in a manner perceptible to the user. 
     As described above, management system  16  may be configured to receive authentication information, communications, and other information from the computing device  18 . In at least one embodiment, management system  16  communicates with one or more of the aircraft components  12 ,  14  over computer network  15 . 
     Computing device  18  is further configured to provide input to the management system  16  to carry out one or more of the steps of the methods described herein. Management system  16  comprises one or more server computers, computing devices, or systems of a type known in the art. Management system  16  may be embedded within existing aircraft technology to provide a network access point for communication by computing device  18 . Management system  16  may comprise one of many well-known servers and/or platforms, or a custom server or platform. 
     In some embodiments, computing device  18 , management system  16 , and the one or more aircraft components  12 ,  14  all communicate over a single computer network  15 , such as, for example, the embodiment displayed in  FIG. 1B . In such an embodiment, computer network  15  may be a wireless network, virtual private network, or any other type of computer network. 
     Referring now to  FIG. 1C , there is shown an architecture diagram displaying components of a system  102  for interactive aircraft maintenance procedures with a computing device according to at least one embodiment. As shown in  FIG. 1C , the system  102  includes a computing device  18 , one or more aircraft components  12 ,  14 , and a management system  16 , similar to what is displayed in  FIGS. 1A  and  FIGS. 1B .  FIG. 1C  displays further sub-components of the system  102 . For the one or more aircraft components  12 ,  14 , the sub-components include an on-board maintenance system  110 , an aircraft engine  112 , a multi-function display  114 , and a health management unit  116 , according to an embodiment. For the management system  16 , the sub-components include a client tablet  120  and a ground station  118  in an embodiment. As shown in  FIG. 1C , the computing device  18  may communicate directly with the management system  16  and the one or more aircraft components  12 ,  14 . 
     In an exemplary embodiment, computing device  18  is a mobile computing device, connected via wireless network to management system  16  and configured to assist aircraft maintenance personnel in conducting interactive ground operations on the aircraft. The management system  16  is in communication with the one or more aircraft components  12 ,  14  and the sub-components, such as one or more controllers associated with the aircraft engine  112  and receives sensor and control status from the other installed devices, such as, for example, the multi-function display  114  and the health management unit  116 . The management system  16  can be configured to provide input to the computing device  18  using sensor readings and timer settings received from the sub-components of the one or more aircraft components  12 ,  14 . A user of the computing device  18 , then, can use the computing device  18  display to guide his or her actions in performing interactive maintenance procedures (i.e. moving the throttle, etc.) and record results of the actions either directly on the computing device  18 , paper, or otherwise. 
     It should be appreciated that using the combination of the management system  16  with the computing device  18  allows for rapid software development of software with rich interactive human interfaces. The computing device  18  can provide more flexible and informative displays than the current devices installed in the cockpit. By avoiding the devices installed in the cockpit, this system avoids the many limits to information flow between the cockpit devices and other aircraft devices. 
     Referring now to  FIG. 2 , there is shown a flowchart of a method  200  for interactive aircraft maintenance procedures using a computing device according to at least one embodiment. As shown in  FIG. 2 , the method  200  includes receiving an aircraft component operation request in step  202 , transmitting the request to an aircraft component in step  204 , receiving aircraft component(s) values in step  206 , transmitting component(s) values to the computing device  18  in step  208 , and generating an aircraft status determination in step  210 . It should be appreciated that the steps of method  200  may be executed in any order and at any time. It should further be appreciated that multiple steps of the method  200  may be executed contemporaneously (i.e. parallel computing). 
     According to at least one embodiment, the method  200  includes receiving an aircraft component operation request from a computing device  18  in step  202 . The computing device  18  transmits an aircraft component operation request to the on-board maintenance system  110 . As used herein, an aircraft component operation request may include, but is not limited to, a meter reading, an on/off request to the component, a change in a value for the component (i.e. throttle up/down), and others. It should be appreciated that an aircraft component operation request may include any command that can be issued to a component in an aircraft that is connected to a management system as discussed herein. For example, in the event that a technician is performing a power assurance check for an engine, an aircraft component operation request could be a temperature reading. In this example, an aircraft component operation request could also be an engine turn on command and a throttle up command, the steps often used to perform a power assurance check. 
     In at least one embodiment, the method  200  includes transmitting the aircraft component operation request to one or more aircraft components  12 ,  14 . In such an embodiment, the aircraft component operation request is received at a management system  16  and directed to the appropriate aircraft components  12 ,  14  to perform the operation. For example, an aircraft component operation request requesting a temperature reading from a sensor associated with the aircraft engine  112  would be sent to the sensor. 
     In at least one embodiment, the method  200  includes receiving aircraft component value(s) from the one or more components  12 ,  14  in step  206 . In response to receiving the aircraft component operation request, the one or more components responds with values requested or generated as a result of performing the aircraft component operation request to the management system  16 . For example, if the aircraft component operation request is a temperature reading from a sensor associated with the aircraft engine  112 , the value returned to the management system  16  would be a temperature value. In at least one embodiment, the component values returned to the management system  16  are transmitted to the computing device  18  by the management system  16  in step  208 . 
     In at least one embodiment, the method  200  includes generating an aircraft status determination based on the values returned to the computing device  18  in step  210 . In an embodiment, the values returned to the computing device  18  may be displayed to the operator directly on the computing device  18  (i.e. the computing device  18  may directly display a temperature). In other embodiments, the values may instead/also be entered into an equation to derive attributes related to the components and other known values, such as, for example, taking a temperature value from a component and adjusting it based on ambient temperature. In other embodiments, steps in the method  200  may be executed multiple times such that the computing device  18  holds multiple values from components that are combined together in an equation to derive attributes. 
     In other embodiments, the computing device may hold acceptable value limits for values and/or derived attributes, such as, for example, a minimum power assurance check (PAC) value. In such an embodiment, the computing device  18  may display a warning based on whether the derived attributes meet the acceptable limits. 
     The preceding description is exemplary rather than limiting in nature. A person of ordinary skill in this art may recognize certain variations and modifications to the disclosed examples that do not depart from the essence of this disclosure. For that reason, the following claims should be studied to determine the true scope of legal protection given to this disclosure.