Abstract:
Systems and methods for navigation of a vehicle may carry out one or more operations including, but not limited to: obtaining coordinates of a vector connecting two points in space using carrier phase measurements from global navigation system satellites (GNSS); setting the vector as an intended path of a vehicle; storing carrier phase signals from a GNSS receiver received at a first position of the vehicle; receiving carrier phase signals from a GNSS receiver at a second position of the vehicle; and determining a position of the vehicle relative to the intended path from one or more carrier phase signals received at the second position and one or more stored carrier phase signals received at the first position.

Description:
BACKGROUND 
     Vehicles (e.g. unmanned aerial vehicles (UAVs)) may be required to perform automatic two-dimensional and/or three-dimensional navigation and guidance operations (e.g. automatic takeoffs and/or landings from a runway). 
     SUMMARY 
     Systems and methods for navigation of a vehicle may carry out one or more operations including, but not limited to: obtaining coordinates of a vector connecting two points in space using carrier phase measurements from global navigation system satellites (GNSS); setting the vector as an intended path of a vehicle; storing carrier phase signals from a GNSS receiver received at a first position of the vehicle; receiving carrier phase signals from a GNSS receiver at a second position of the vehicle; and determining a position of the vehicle relative to the intended path from one or more carrier phase signals received at the second position and one or more stored carrier phase signals received at the first position. 
    
    
     
       BRIEF DESCRIPTION OF FIGURES 
       The numerous objects and 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  illustrates a system for determining a vector associated with an intended heading of a vehicle; 
         FIG. 2  illustrates a system for determining a vector associated with an intended heading of a vehicle; 
         FIG. 3  illustrates a system for two dimensional navigation and guidance of a vehicle; 
         FIG. 4  illustrates a system for two dimensional navigation and guidance of a vehicle; 
         FIG. 5  illustrates a system for two dimensional navigation and guidance of a vehicle; 
         FIG. 6  illustrates a system for two dimensional navigation and guidance of a vehicle; and 
         FIG. 7  illustrates a system for three dimensional navigation and guidance of a vehicle. 
     
    
    
     DETAILED DESCRIPTION 
     Vehicles (e.g. unmanned aerial vehicles (UAVs)) may be required to perform automatic two-dimensional and/or three-dimensional navigation and guidance operations (e.g. takeoffs and/or landings from a runway). However, the runways used for such auto-takeoffs may be very narrow (e.g. a stretch of road) and located in remote locations away from pre-existing ground and flight control installations. As such, accurate &amp; reliable positioning information is needed to ensure that a vehicle continues to travel along an intended path. 
     Referring to  FIGS. 1 and 2 , an environmental view  100  of exemplary embodiments are shown. Prior to an attempted automatic takeoff for an aircraft, a survey of a runway  101  may be taken. For example, a survey device  102  may include a global navigation satellite system (GNSS) receiver  103 . The GNSS receiver  103  may sample GNSS measurements  104  from one or more GNSS satellites  105  at a first position  106  (e.g. the centerline at a takeoff start point on one end of the runway  101 ) and a second position  107  (e.g. a position at the other end of the runway  101  on the runway centerline). A vector  108  connecting first position  106  and the second position  107  may then be computed from the GNSS measurements gathered at first position  106  and the second position  107 . 
     In an embodiment, the survey of the runway  101  may employ time-relative positioning techniques to determine coordinates of a vector connecting two positions (e.g. the first position  106  at one end of the runway and the second position  107  at the other end of the runway). 
     As noted in U.S. Pat. No. 5,999,123 which is incorporated herein to the extent not inconsistent herewith, a measurement equation for the carrier phase associated with a given GNSS satellite  105  may be described mathematically as:
 
φ( t   k )−φ( t   0 )=[ r   k   +N]−[r   0   +N]   Eqn. 1
 
which is equivalent to:
 
[φ( t   k )−φ( t   0 )]−[ d ( x*,t   k )− d ( x*,t   0 )]= h ( t   k )·[ x ( t   k )− x*]−h ( t   0 )·[ x ( t   0 )− x*]   Eqn. 2
 
where:
         φ(t k ) is a carrier phase detected at a first time/position t k  (e.g. a second position  107 );   φ(t 0 ) is a carrier phase detected at a second point time/position t 0  (e.g. a first position  106 );   r k  is a range plus range bias at t k ;   r 0  is a range plus range bias at t 0      N is an integer cycle ambiguity;   h(t k ) are the direction cosines at t k ;   h(t 0 ) are the direction cosines at t 0 ;   x(t k ) is the position and range bias errors at t k      x(t 0 ) is the position and range bias error at t 0  (range bias error may be arbitrarily set to 0 at t 0 );   x* is a true position at t 0 ;   d(x*, t k ) is a geometric range from x* to a given GNSS satellite  105  plus deterministic biases at t k ; and   d(x*, t 0 ) is a geometric range from x* to a given GNSS satellite  105  plus deterministic biases at t 0 .
 
Written in a different way Eqn. 1 may be characterized as:
 
[φ( t   k )−φ( t   0 )]−[ d ( x*,t   k )− d ( x*,t   0 )]= h ( t   k )·[ x ( t   k )− x ( t   0 )]+[ h ( t   k )− h ( t   0 )]·[ x ( t   0 )− x*]   Eqn. 3
       

     The second term on the right-hand side representing the assumed position error [x(t 0 )−x*] may be ignored as no change in the term would be observable over a short time interval (e.g. 100 seconds). In addition, [h(t k )−h(t 0 )], is very nearly zero so its contribution is also small over a short time interval. Thus, ultimate solution of Eqns. 2 and 3, consists of solving for the term [x(t k )−x(t 0 )]. 
     Additionally, if the carrier phase observation and deterministic biases are incorporated into the term carrier phase φ(t), where φ(t)=φ(t)−d(x*,t) then Eqn. 2 reduces to:
 
[φ( t   k )−φ( t   0 )]= h ( t   k )·[ x ( t   k )− x ( t   0 )]  Eqn. 4.
 
     Once the carrier phase and direction cosine values for each of a group of GNSS satellites  105  (e.g. a group of at least 4 satellites 1-4) is known for the first position  106  and the second position  107 , the solutions for the relative position differences [x(t k )−x(t 0 )] between the first position  106  and the second position  107  may be computed by solving Eqn. 4 for the set of GNSS satellites  105 , simultaneously, as follows (where x 1  x 2  and x 3  are position components and x 4  is range bias): 
                     [               x   1     ⁡     (     t   k     )       -       x   1     ⁡     (     t   0     )                       x   2     ⁡     (     t   k     )       -       x   1     ⁡     (     t   0     )                       x   3     ⁡     (     t   k     )       -       x   3     ⁡     (     t   0     )                       x   4     ⁡     (     t   k     )       -       x   4     ⁡     (     t   0     )               ]     =         (       H   T     ⁢   H     )       -   1       ⁢       H   T     ·     [               φ   1     ⁡     (     t   k     )       -       φ   1     ⁡     (     t   0     )                       φ   2     ⁡     (     t   k     )       -       φ   2     ⁡     (     t   0     )                       φ   3     ⁡     (     t   k     )       -       φ   3     ⁡     (     t   0     )                       φ   4     ⁡     (     t   k     )       -       φ   4     ⁡     (     t   0     )                 ⋮         ]                 Eqn   .           ⁢   5               
where
 
     
       
         
           
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     Referring again to  FIGS. 1 and 2 , the survey device  102  including the GNSS receiver  103  may capture and store carrier phase values for each of the available GNSS measurements  104  at the first position (e.g. the first position  106 ) and the second position (e.g. the second position  107 ). The survey device  102  may process the obtained carrier phase values to compute an intended path vector  108  that represents a straight line adjoining the first position  106  and the second position  107 . 
     Following computation of the vector  108 , that vector  108  may be provided to a vehicle for use in two dimensional navigation and guidance operations. Though described herein with respect to navigational operations for an aircraft  109  it will be recognized that the systems and methodologies may be applied to any type of vehicle (e.g. a ground-based vehicle, a water-based vehicle, and the like) without departing from the scope of the present disclosures. 
     For example, as shown in  FIG. 3 , an aircraft  109  may include a time-relative navigation system  110 . The time-relative navigation system  110  may include a GNSS receiver  111 , a processing device  112 , and a vector database  113 . As noted above, at least one vector  108  associated with a prior survey of a geographic area (e.g. a runway  101 ) may be provided to the time-relative navigation system  110  and stored in the vector database  113 . 
     Referring to  FIGS. 4-5 , an aircraft  109  may be positioned at the first position  106  relative to the runway  101  facing in a direction of intended takeoff. The processing device  112  may retrieve a vector  108  previously computed for the runway  101  from the vector database  113 . Further, the processing device  112  may gather GNSS carrier phases at an initial position  114  of the aircraft  109 . 
     Referring again to  FIG. 3 , in order to retain the aircraft  109  within the bounds of the runway  101  during transit and takeoff, the processing device  112  may provide one or more control signals to a directional control system  115  to steer aircraft  109  toward the centerline of the runway (with the runway defined as the vector connecting the first position  106  with the second position  107 ). The directional control system  115  may be configured to control various directional control elements of the aircraft  109  during takeoff. For example, the directional control system  115  may control one or more flight control surfaces  116  (e.g. a rudder, elevators, ailerons, etc.) and/or one or more ground steering mechanisms  117  (e.g. brakes, nose wheel steering, etc.). 
     Referring to  FIG. 6 , as the aircraft  109  moves forward down the runway, the processing device  112  of the time-relative navigation system  110  may progressively compute a current position  118  of the aircraft  109  from the carrier phase of the GNSS measurements  104  as described above. After computation of the current position  118  of the aircraft  109 , the processing device  112  may determine a current relative position vector  119 . The processing device  112  may then compute the shortest distance between current aircraft position and runway centerline, and apply corrective control signals to steer the aircraft toward the runway centerline. 
     The time-relative navigation solution described above drifts at a rate of roughly 2 mm/sec, 1 sigma due to satellite clock drift (all other sources of errors canceling out). As typical takeoff roll is completed in less than 40 seconds, by the time of rotation, position error will be about 8 cm, 1 sigma, or relatively negligible compared to steering accuracy. 
     To make the algorithm reliable, a mechanism for detecting and excluding cycle slips may be employed. This can be done using residual monitoring, and if a dual frequency GNSS receiver  111  is available, using cross-frequency carrier phase check. For example, if L1 frequency is spoofed or jammed, the algorithm may use L2 carrier phase only. 
     In an alternate embodiment, the relative navigation and guidance methodologies described above may also be employed during flight of the aircraft  109 . For example, methodologies can also be used as a cross-check or a backup for ground tracking radar and/or inertial guidance used for automatic landing. For example, as shown in  FIG. 7 , aircraft  109  may employ ground tracking radar  120  to generate azimuth, elevation, and range of the aircraft  109  relative to a landing point  121 . From this azimuth, elevation, and range data, an intended path vector  108  between a present position of the aircraft  109  and the landing point  121  may be computed and saved to the vector database  113 . Similar to the methodologies described above, as the aircraft  109  proceeds towards the landing point  121 , the time-relative navigation system  110  may progressively determine the relative position vector  119  of the aircraft  109  from the carrier phase of the GNSS measurements  104  and compute a differential to the vector  108 . In one embodiment, a notification associated with the relative differential may be displayed to an operator (e.g. a pilot or UAV control officer) or provided to a monitoring system in order to provide a cross-check with respect to the operations of the ground tracking radar  120 . In another embodiment, the time-relative navigation system  110  may provide a redundant control system for automatic landings. For example, a now-malfunctioning ground tracking radar  120  may have previously determined a vector  108 . The computed relative differential between that vector  108  and a relative position vector  119  may be determined and corrective control signals may be provided to the directional control system  115  to turn the aircraft  109  towards the vector  108  to retain aircraft on the intended landing path. 
     While described above in the context of use of carrier phase measurements of GNSS satellites in vehicle navigation, GNSS velocity measurements may be computed based on such carrier phases differenced over short time segments (e.g. 1 second or less). As such, the present disclosures fully contemplate the use of such GNSS velocity measurements derived from carrier phases to perform vehicle navigation operations similar to those described herein. 
     Those having skill in the art will recognize that the state of the art has progressed to the point where there is little distinction left between hardware and software implementations of aspects of systems; the use of hardware or software is generally (but not always, in that in certain contexts the choice between hardware and software can become significant) a design choice representing cost vs. efficiency tradeoffs. Those having skill in the art will appreciate that there are various vehicles by which processes and/or systems and/or other technologies described herein can be effected (e.g., hardware, software, and/or firmware), and that the preferred vehicle will vary with the context in which the processes and/or systems and/or other technologies are deployed. For example, if an implementer determines that speed and accuracy are paramount, the implementer may opt for a mainly hardware and/or firmware vehicle; alternatively, if flexibility is paramount, the implementer may opt for a mainly software implementation; or, yet again alternatively, the implementer may opt for some combination of hardware, software, and/or firmware. Hence, there are several possible vehicles by which the processes and/or devices and/or other technologies described herein may be effected, none of which is inherently superior to the other in that any vehicle to be utilized is a choice dependent upon the context in which the vehicle will be deployed and the specific concerns (e.g., speed, flexibility, or predictability) of the implementer, any of which may vary. Those skilled in the art will recognize that optical aspects of implementations will typically employ optically-oriented hardware, software, and or firmware. 
     The foregoing detailed description has set forth various embodiments of the devices and/or processes via the use of block diagrams, flowcharts, and/or examples. Insofar as such block diagrams, flowcharts, and/or examples contain one or more functions and/or operations, it will be understood by those within the art that each function and/or operation within such block diagrams, flowcharts, or examples can be implemented, individually and/or collectively, by a wide range of hardware, software, firmware, or virtually any combination thereof. In one embodiment, several portions of the subject matter described herein may be implemented via Application Specific Integrated Circuits (ASICs), Field Programmable Gate Arrays (FPGAs), digital signal processors (DSPs), or other integrated formats. However, those skilled in the art will recognize that some aspects of the embodiments disclosed herein, in whole or in part, can be equivalently implemented in integrated circuits, as one or more computer programs running on one or more computers (e.g., as one or more programs running on one or more computer systems), as one or more programs running on one or more processors (e.g., as one or more programs running on one or more microprocessors), as firmware, or as virtually any combination thereof, and that designing the circuitry and/or writing the code for the software and or firmware would be well within the skill of one of skill in the art in light of this disclosure. In addition, those skilled in the art will appreciate that the mechanisms of the subject matter described herein are capable of being distributed as a program product in a variety of forms, and that an illustrative embodiment of the subject matter described herein applies regardless of the particular type of signal bearing medium used to actually carry out the distribution. Examples of a signal bearing medium include, but are not limited to, the following: a recordable type medium such as a floppy disk, a hard disk drive, a Compact Disc (CD), a Digital Video Disk (DVD), a digital tape, a computer memory, etc.; and a transmission type medium such as a digital and/or an analog communication medium (e.g., a fiber optic cable, a waveguide, a wired communications link, a wireless communication link, etc.). 
     In a general sense, those skilled in the art will recognize that the various aspects described herein which could be implemented, individually and/or collectively, by a wide range of hardware, software, firmware, or any combination thereof can be viewed as being composed of various types of “electrical circuitry.” Consequently, as used herein “electrical circuitry” includes, but is not limited to, electrical circuitry having at least one discrete electrical circuit, electrical circuitry having at least one integrated circuit, electrical circuitry having at least one application specific integrated circuit, electrical circuitry forming a general purpose computing device configured by a computer program (e.g., a general purpose computer configured by a computer program which at least partially carries out processes and/or devices described herein, or a microprocessor configured by a computer program which at least partially carries out processes and/or devices described herein), electrical circuitry forming a memory device (e.g., forms of random access memory), and/or electrical circuitry forming a communications device (e.g., a modem, communications switch, or optical-electrical equipment). Those having skill in the art will recognize that the subject matter described herein may be implemented in an analog or digital fashion or some combination thereof. 
     Those having skill in the art will recognize that it is common within the art to describe devices and/or processes in the fashion set forth herein, and thereafter use engineering practices to integrate such described devices and/or processes into data processing systems. That is, at least a portion of the devices and/or processes described herein can be integrated into a data processing system via a reasonable amount of experimentation. Those having skill in the art will recognize that a typical data processing system generally includes one or more of a system unit housing, a video display device, a memory such as volatile and non-volatile memory, processors such as microprocessors and digital signal processors, computational entities such as operating systems, drivers, graphical user interfaces, and applications programs, one or more interaction devices, such as a touch pad or screen, and/or control systems including feedback loops and control motors (e.g., feedback for sensing position and/or velocity; control motors for moving and/or adjusting components and/or quantities). A typical data processing system may be implemented utilizing any suitable commercially available components, such as those typically found in data computing/communication and/or network computing/communication systems. 
     The herein described subject matter sometimes illustrates different components contained within, or connected with, different other components. It is to be understood that such depicted architectures are merely exemplary, and that in fact many other architectures can be implemented which achieve the same functionality. In a conceptual sense, any arrangement of components to achieve the same functionality is effectively “associated” such that the desired functionality is achieved. Hence, any two components herein combined to achieve a particular functionality can be seen as “associated with” each other such that the desired functionality is achieved, irrespective of architectures or intermedial components. Likewise, any two components so associated can also be viewed as being “operably connected”, or “operably coupled”, to each other to achieve the desired functionality, and any two components capable of being so associated can also be viewed as being “operably couplable”, to each other to achieve the desired functionality. Specific examples of operably couplable include but are not limited to physically mateable and/or physically interacting components and/or wirelessly interactable and/or wirelessly interacting components and/or logically interacting and/or logically interactable components. 
     It will be understood by those within the art that, in general, terms used herein, and especially in the appended claims (e.g., bodies of the appended claims) are generally intended as “open” terms (e.g., the term “including” should be interpreted as “including but not limited to,” the term “having” should be interpreted as “having at least,” the term “includes” should be interpreted as “includes but is not limited to,” etc.). It will be further understood by those within the art that if a specific number of an introduced claim recitation is intended, such an intent will be explicitly recited in the claim, and in the absence of such recitation no such intent is present. For example, as an aid to understanding, the following appended claims may contain usage of the introductory phrases “at least one” and “one or more” to introduce claim recitations. However, the use of such phrases should not be construed to imply that the introduction of a claim recitation by the indefinite articles “a” or “an” limits any particular claim containing such introduced claim recitation to inventions containing only one such recitation, even when the same claim includes the introductory phrases “one or more” or “at least one” and indefinite articles such as “a” or “an” (e.g., “a” and/or “an” should typically be interpreted to mean “at least one” or “one or more”); the same holds true for the use of definite articles used to introduce claim recitations. 
     In addition, even if a specific number of an introduced claim recitation is explicitly recited, those skilled in the art will recognize that such recitation should typically be interpreted to mean at least the recited number (e.g., the bare recitation of “two recitations,” without other modifiers, typically means at least two recitations, or two or more recitations). Furthermore, in those instances where a convention analogous to “at least one of A, B, and C, etc.” is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., “a system having at least one of A, B, and C” would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.). 
     In those instances where a convention analogous to “at least one of A, B, or C, etc.” is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., “a system having at least one of A, B, or C” would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.). It will be further understood by those within the art that virtually any disjunctive word and/or phrase presenting two or more alternative terms, whether in the description, claims, or drawings, should be understood to contemplate the possibilities of including one of the terms, either of the terms, or both terms. For example, the phrase “A or B” will be understood to include the possibilities of “A” or “B” or “A and B.” 
     While particular aspects of the present subject matter described herein have been shown and described, it will be apparent to those skilled in the art that, based upon the teachings herein, changes and modifications may be made without departing from the subject matter described herein and its broader aspects and, therefore, the appended claims are to encompass within their scope all such changes and modifications as are within the true spirit and scope of the subject matter described herein. Furthermore, it is to be understood that the invention is defined by the appended claims.