Patent Document

FIELD OF THE INVENTION 
     The present invention is directed generally toward tactile force feedback systems, and more particularly to force feedback systems for critical events. 
     BACKGROUND OF THE INVENTION 
     In a combat aircraft, an onboard computer system may detect situations requiring the pilot&#39;s attention (critical events). By their nature, critical events may occur concurrently. In a system that alerts pilots of critical events via an audible warning, obtrusive visual warning, or both, the pilot may become distracted, or information necessary to manage one critical event may be obfuscated by the warning of another critical event. For example, useable area on a display is limited and displaying information pertinent to one critical event may prevent the display of information pertinent to another critical event, especially where critical events necessitate a prominent visual warning on the display to ensure the pilot is aware of the situation. 
     Modern infantry soldiers are highly connected and reliant on data communication through personal computing devices. However, in combat, where information is most critical, infantry soldiers are in closest proximity to enemy combatants and therefore may be in the greatest need of stealth. Lights or sounds indicating the receipt of critical information is undesirable. 
     Consequently, it would be advantageous if an apparatus existed that is suitable for providing a tactile indication of a critical event without causing unnecessary distraction. 
     SUMMARY OF THE INVENTION 
     Accordingly, the present invention is directed to a novel method and apparatus for providing a tactile indication of a critical event without causing unnecessary distraction. 
     In at least one embodiment of the present invention, force feedback elements are incorporated at various points in a flight helmet. An onboard computer system identifies critical events and translates such events into a force feedback pulse applied to one or more of the force feedback elements, warning the pilot of the critical event while at the same time suppressing more conventional critical event warnings that may distract a pilot. 
     In another embodiment of the present invention, force feedback elements are incorporated into a vest, bodysuit or body armor. A mobile, personal computing system may apply a force feedback pulse to one or more of the force feedback elements to indicate an event that might otherwise require an audible signal. 
     It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention claimed. The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate an embodiment of the invention and together with the general description, serve to explain the principles. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The numerous advantages of the present invention may be better understood by those skilled in the art by reference to the accompanying figures in which: 
         FIG. 1  shows a block diagram of a computer system useful for implementing embodiments of the present invention; 
         FIG. 2  shows a perspective, environmental view of a flight helmet including an embodiment of the present invention; 
         FIG. 3  shows a perspective, environmental view of a vest including an embodiment of the present invention; and 
         FIG. 4  shows a flowchart of a method for signaling a critical even with force feedback elements according to one embodiment of the present invention. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     Reference will now be made in detail to the subject matter disclosed, which is illustrated in the accompanying drawings. The scope of the invention is limited only by the claims; numerous alternatives, modifications and equivalents are encompassed. For the purpose of clarity, technical material that is known in the technical fields related to the embodiments has not been described in detail to avoid unnecessarily obscuring the description. 
     Referring to  FIG. 1 , a block diagram of a computer system useful for implementing embodiments of the present invention is shown. In at least one embodiment of the present invention, a processor  100  is connected to a memory  102  and one or more force feedback elements  104 . The processor  100  may be part of an on board flight computer, some other in-vehicle computer system, a mobile personal computing device, or any other mobile computing platform. Furthermore, the processor  100  may be connected to an antenna  106  for receiving data and a display  108  for displaying pertinent information. 
     In one embodiment of the present invention, an aircraft may house a computer system according to the present invention. The processor  100 , detecting a critical event or otherwise receiving data through the antenna  106  indicating a critical event, may determine a signal to apply to the one or more force feedback elements  104  to produce a tactile sensation. The tactile sensation may alert the pilot that a critical event has occurred. Different signals may produce different tactile sensations indicating different critical events or events of varying criticality. Furthermore, the processor  100  may display information pertaining to the critical event on the display  108  in a minimally intrusive way because obtrusive warnings are no longer necessary as the pilot is notified by alternative means. 
     In another embodiment of the present invention, the processor  100 , incorporated into personal computing device, may receive a signal through the antenna  106 . The signal may include embedded data indicating that the signal contains critical information. The processor  100  may detect such embedded data and determine a signal to apply to the one or more force feedback elements  104  to produce a tactile sensation. 
     Referring to  FIG. 2 , a perspective, environmental view of a flight helmet including an embodiment of the present invention is shown. A flight helmet  200  may include a plurality of force feedback elements  202 ,  204 ,  206  affixed to particular locations on or within the flight helmet  200 . For example, a first force feedback element  202  may be affixed or embedded at the left jaw line of the flight helmet  200 , a second force feedback element  204  may be affixed or embedded at the right jaw line of the flight helmet  200  and a third force feedback element  206  may be affixed or embedded at the rear of the flight helmet  200 . The force feedback elements  202 ,  204 ,  206  are positioned to produce a tactile sensation to the wearer; for example, in at least one embodiment, the force feedback elements  202 ,  204 ,  206  are embedded in the helmet so as to be in substantial physical contact with wearer. A person skilled in the art may appreciate that while  FIG. 2  shows the force feedback elements  202 ,  204 ,  206  on the outer surface of the helmet  200 , such illustration is only for clarity and should not be considered limiting. Each of the force feedback elements  202 ,  204 ,  206  is connected to a computing device such that the computing device may apply signals to each of the force feedback elements  202 ,  204 ,  206  to produce tactile pulses that may be felt and distinguished by the pilot wearing the flight helmet  200 . 
     Signals to each force feedback element  202 ,  204 ,  206  may indicate critical events that require a pilot&#39;s attention. Signals to each force feedback element  202 ,  204 ,  206  may also vary to indicate data pertinent to a critical event. For example, where an onboard computer system detects a critical event behind the aircraft or receives data pertaining to a critical event behind the aircraft, the computer system may apply a signal to the third force feedback element  206  to indicate to the pilot that a critical event has occurred behind the aircraft. 
     Likewise, where an onboard computer system detects a critical event to the left or right of the aircraft or receives data pertaining to such a critical event, the computer system may apply a signal to the first force feedback element  202  or the second force feedback element  204  respectively to indicate a location of the critical event. Alternatively, two or more force feedback elements  202 ,  204 ,  206  may be activated in sequence to indicate information pertaining to a critical event, such as a direction relative to the aircraft. For example, when attempting to re-acquire a target, the onboard computer system may active one of the force feedback elements  202 ,  204 ,  206  to indicate the relative direction of that target. 
     Furthermore, the onboard computer system may apply varying signals to the one or more force feedback elements  202 ,  204 ,  206 . For example, the onboard computer system may apply a signal to produce a pulse having a first frequency to indicate one level of criticality, or a pulse having a second frequency to indicate a different level of criticality. Alternatively, signals may vary the magnitude of a pulse. 
     In another embodiment, where an onboard computer system detects or receives data pertaining to multiple critical events, the onboard computer system may determine multiple disparate locations pertaining to each critical event relative to the aircraft. The onboard computer system may then apply signals to two or more of the force feedback elements  202 ,  204 ,  206  to indicate to the pilot the relative locations of each critical event. Furthermore, the onboard computer system may vary each signal to indicate relative levels of criticality associated with each critical event. 
     Referring to  FIG. 3 , a perspective, environmental view of a vest including an embodiment of the present invention is shown. The vest  300  may include a plurality of force feedback elements  304 ,  306  affixed to particular locations on or within the vest  300 . For example, a first force feedback element  304  may be affixed or embedded in the upper left quadrant of the vest  300  and a second force feedback element  306  may be affixed or embedded in the upper right quadrant of the vest  300 . The force feedback elements  304 ,  306  are positioned to produce a tactile sensation to the wearer; for example, in at least one embodiment, the force feedback elements  304 ,  306  are embedded in the vest so as to be in substantial physical contact with wearer. A person skilled in the art may appreciate that while  FIG. 3  shows the force feedback elements  304 ,  306  on the outer surface of the vest  300 , such illustration is only for clarity and should not be considered limiting. Each of the force feedback elements  304 ,  306  is connected to a portable computing device  302  such that the portable computing device  302  may apply signals to each of the force feedback elements  304 ,  306  to produce tactile pulses that may be felt and distinguished by the person wearing the vest  300 . 
     Signals to each force feedback element  304 ,  306  may indicate critical information received by the portable computing device  302  that may require attention. Signals to each force feedback element  304 ,  306  may also vary to indicate data pertinent to the critical information. For example, where a portable computing device  302  receives critical information, the portable computing device  302  may apply a signal to one or more of the force feedback elements  304 ,  306  depending on some data embedded in the critical information such as criticality or relative location if the portable computing device  302  has access to information pertaining to its own relative location. In another example, tactile pulses produced by force feedback elements may function as silent “friendly” indicators in a battlefield situation. 
     Furthermore, the portable computing device  302  may apply varying signals to the one or more force feedback elements  304 ,  306 . For example, the portable computing device  302  may apply a signal to produce a pulse having a first frequency to indicate one level of criticality, or a pulse having a second frequency to indicate a different level of criticality. Alternatively, signals may vary the magnitude of a pulse. 
     In another embodiment, each force feedback element  304 ,  306  may be specifically associated with one or more types of critical information. Where the portable computing device  302  receives multiple types of critical information, the portable computing device  302  may determine and apply multiple disparate signals to two or more force feedback elements  304 ,  306 . Furthermore, the portable computing device  302  may vary each signal to indicate relative levels of criticality associated with each type of critical information. 
     Referring to  FIG. 4 , a flowchart of a method for signaling a critical event with force feedback elements according to one embodiment of the present invention is shown. A computer system executing such method may receive  400  data pertaining to a critical event. Data pertaining to a critical event may include the existence of such critical event, the location of such critical event, the relative criticality of such critical event or other pertinent information. 
     The computer system may determine  402  one or more force feedback elements to activate based on the data. For example, where the data indicates the location of a critical event, the computer system may select a force feedback element indicating the relative location of the critical event. Alternatively, certain force feedback elements may be associated with certain critical events such that the activation of a force feedback element or combination of force feedback elements indicates a particular critical event or type of critical event. 
     The computer system may then determine  404  one or more signals to apply to the selected force feedback elements. The signals may be configured to produce a pulse in the force feedback elements having a desirable frequency, or some combination of frequencies in two or more force feedback elements. The signals may also vary the magnitude of pulses in the force feedback elements. The computer system may then apply  406  such signals to the selected force feedback elements. 
     It is believed that the present invention and many of its attendant advantages will be understood by the foregoing description of embodiments of the present invention, and it will be apparent that various changes may be made in the form, construction, and arrangement of the components thereof without departing from the scope and spirit of the invention or without sacrificing all of its material advantages. The form herein before described being merely an explanatory embodiment thereof, it is the intention of the following claims to encompass and include such changes.

Technology Category: g