• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a system which is adapted to measure topographic elevations, the system comprising: a pulse laser (1) for generating a laser light pulse (20); A primary mirror (5), which is adapted to oscillate back and forth in at least one axis in order to direct the laser light pulse (20) in a pattern to a target, and is further adapted to reflect (22) the laser light pulse ( 20) to receive from the target and to direct the reflections (22) of the laser light pulse (20) to a secondary mirror (13); the secondary mirror (13) being adapted to reorient the reflections (20) of the laser light pulse (20) towards a center of a detection device (3), the detection device (3) being configured to generate an electrical signal that is generated by a Receiver (4) is amplified; a time interval meter (6); and control electronics configured to measure the topographical surveys using the transit time.
    公开号:AT16690U1
    申请号:TGM9004/2016U
    申请日:2016-03-02
    公开日:2020-04-15
    发明作者:Verheggen Chris；Liadsky Joe；Sitar Michael；Hartsell Daryl
    申请人:Teledyne Digital Imaging Inc；
    IPC主号:
    专利说明:

    description
    TECHNICAL FIELD Embodiments of the invention generally relate to providing an improved device and method for 3D measurement of area topography from an airborne or land-based platform, and more particularly to a device and method that prevents the possible loss of data that can be caused by blind zones that can occur in existing laser terrain mapping systems.
    BACKGROUND ART Airborne laser terrain mapping (ALTM) systems use a time of flight (TOF) LiDAR to measure the distance from an aircraft-mounted system to the ground beneath the aircraft. A short pulse of visible light or infrared light is emitted by a light source, such as a laser, and directed to a target. The light pulse propagates to the target and a portion is reflected and moves back to the LiDAR system where it is detected by a high speed optical detector, such as an avalanche photodiode, which converts the light pulse into an electrical signal which is then amplified . By measuring the time interval from when the light pulse was emitted to when the return signal was received, the distance can be calculated using the known precise speed of propagation of the light pulse. The TOF can be measured by an electronic subsystem such as a time interval meter or other means by digitizing the received echo and analyzing the waveform.
    [0003] When the laser is triggered, there is a very short period of time in which the detection device can detect some scattered light. This can be caused by reflections from interior optical components, a window at the exit of the system or a window in the aircraft through which the system is operated, or backscattering from the first few meters of air under the aircraft. If the echo from a previously emitted laser pulse reaches the detector during this short period of time, it is indistinguishable from the scattered light pulse, and if the scattered light produces a signal with a much higher amplitude than the return pulse from the target, it covers the echo and hides the system for a period of time. The pulse of the unwanted scattered light leads to a blind zone during which the system is unable to respond to the return signal and measure the TOF. As a result, range data cannot be calculated and the laser shot is essentially wasted. This limitation currently applies to all existing airborne laser mapping systems.
    For an ALTM operation at a high pulse repetition frequency (PRF), the distance to the target can be such that the TOF is a multiple of the time interval between two successive triggerings of the laser. Triggering the laser before the return pulse is received by the target results in more than one pulse in the air at the same time. For example, if the target range and the laser PRF are such that there are five pulses in the air at the same time, there could be five blind zones, which would significantly increase the possibility of the echo being masked and the possibility of a valid one Get distance measurement would decrease. At high laser PRFs, it is almost impossible to plan the flight altitude to minimize the impact of blind spots, because the TOF varies with the height of the aircraft above the ground, the deflection angle of the scanner, the roll, the pitch or the direction of flight of the Aircraft and the topography of the actual site changes.
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    AT 16 690 U1 2020-04-15 Austrian patent office
    SUMMARY OF THE INVENTION In general, the disclosed embodiments relate to the challenge of dealing with multiple light pulses that are transmitted to and from the target simultaneously. The aim is to prevent the output and input pulses from entering the detector at the same time, which would make the system "blind" to incoming return pulses.
    [0006] Accordingly, the disclosed embodiments include a system or apparatus and one or more methods for preventing the negative effects of blind zones and enable the system to operate at high laser PRFs without data loss. Thus, the disclosed embodiments have the potential to collect valid data at the full laser PRF.
    In addition to blind zones generated by the undesirable scattered light described above, blind zones can also be created under certain atmospheric conditions when the system detects backscattered light from the first few meters of air under the aircraft. For example, the return signal could come from humid air 10 m below the aircraft, or it could be a ground return pulse from ten laser shots that ultimately arrives at the detection device. Thus, certain embodiments disclosed herein are configured to significantly reduce the likelihood of this occurring and the blind zone expanding. For example, certain embodiments may include special optical elements and a scanner that prevents the detection of unwanted back pulses from the first few meters of the atmosphere. Without the optical elements, the system would be blinded by unwanted signals. In one embodiment, the disclosed system reduces or prevents blind zones caused by backscattered light within 20-50 m below the aircraft.
    As further described, advantages of the disclosed embodiments are achieved in certain embodiments using an electronic circuit that detects the time interval between the emitted light pulse and subsequent optical signals that are incident on the detection device above a certain threshold value. These signals could be a result of: a) the light backscattered by optical surfaces from the output light pulse, b) the light backscattered by the atmosphere near the aircraft from the output light pulse, or c) a back pulse from the intended target. In certain situations, no return pulses are received (e.g. if the altitude is too high, the atmosphere is too cloudy, the target reflection is too low), whereas in other cases multiple return pulses can be received by a single laser pulse (from a wire or a crown of a tree or branches) below or from the floor). According to the disclosed embodiments, each of these detected events results in a TOF measurement. In certain embodiments, this is achieved through a hardware solution.
    [0009] In one embodiment, the detected signals are monitored in real time and the resulting distance to the ground is calculated. Output signals from back pulses are identified and differentiated by an algorithm. A signal that is a result of the scattering of the output pulse through the interior optical components or through windows is identified as such using the time at which it occurs. This time is synchronous with the emission time of the laser pulse. As described below, an algorithm checks for each return pulse whether there is a possibility that an output and an input signal can occur at the detection device at the same time; when this occurs, it is referred to herein as a collision. The length of time that this collision can occur is called a blind zone. If this is predicted to occur, the system will make a tiny adjustment to the timing of the next laser shot (the output signal) being sent (e.g., a fraction of a millionth of a second) to prevent the collision from occurring , and thus to prevent the blind zone. In fact, the triggering of the laser is either delayed or advanced so that the output laser pulse is placed in a period when the return signal is not expected to be on the
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    Detection device occurs. The results are continuously monitored and adjusted if necessary. In one embodiment, this is done from shot to shot at the laser activation rate, which can be over half a million shots per second.
    Another advantage of the disclosed embodiments includes an apparatus and a method for maintaining a constant swath width and point distribution on the ground, regardless of the altitude of the aircraft or the ground elevation of the terrain.
    [0011] As an exemplary embodiment, the disclosed apparatus may include a processor for executing computer-executable instructions and a computer-readable storage medium for storing the computer-executable instructions. These instructions, when executed by the processor, enable the device to perform features, including dynamically monitoring the transit time (TOF) of the laser light pulses transmitted and received by the laser scanning device; Determining whether there is a possibility that the output laser light pulse and an input signal will be detected from each other within a few nanoseconds; and adjusting a pulse repetition frequency (PRF) in response to a determination that the possible simultaneous detection (within a few nanoseconds) of the output laser light and input signal is likely to occur. Other instructions may include dynamically adjusting the scanner parameters to keep a point density relatively constant when at least one of an aircraft altitude and ground elevation of the terrain changes during an inspection mission to maintain a constant swath width using a laser scanning device.
    An example of the various embodiments disclosed herein includes a system adapted to be mounted on an airborne platform for measuring topographic elevations, the system including: a pulse laser for generating a light pulse; a primary mirror adapted to swing back and forth in at least one axis to direct the laser light in a pattern to the ground, and further adapted to receive reflections of the laser light from the ground and the reflections of the laser light to one directing the secondary mirror, the second mirror being adapted to reorient and hold the received laser light on a center of a detector, the detector configured to generate an electrical signal that is amplified by a receiver; a time interval meter configured to determine the transit time of the received laser light; and control electronics configured to determine the measurement of topographic surveys under the airborne platform using the travel time of the received laser light. In one embodiment, the secondary mirror is between the primary mirror and a reimaging module.
    Other embodiments and advantages of the disclosed systems and methods are further described in detail below.
    BRIEF DESCRIPTION OF THE DRAWINGS For a more complete understanding of the description provided and the advantages thereof, reference is hereby made to the following brief descriptions, which are to be considered in conjunction with the accompanying drawings and the detailed description, wherein like reference numerals represent like parts .
    [0015] Figure 1 10 is a block diagram illustrating a system according to an embodiment. FIG. 2FIG. 3 is a schematic view of the system in operation.FIG. 10 is an example of a timing diagram illustrating the case where only one pulse is transmitted at any given time in accordance with the disclosed embodiments.
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    AT 16 690 U1 2020-04-15 Austrian Patent Office [0018] FIG. 4 is an example of a timing diagram that illustrates the case in which, in accordance with the disclosed embodiments, two optical pulses are transmitted at the same time.
    Figure 5 is a flow diagram illustrating a method of changing the laser activation timing to prevent possible blind zones according to one embodiment.
    DETAILED DESCRIPTION The invention summarized above can be better understood by referring to the following description, which should be read in conjunction with the accompanying drawings. This description of an embodiment, set out below to enable one to make and use an implementation of the invention, is not intended to limit the invention, but rather to serve as a specific example thereof. For example, although certain embodiments described herein relate to an airborne application of the invention, other embodiments of the invention may include ground-based laser scanning applications using either a mobile or static platform.
    Those skilled in the art should understand that the concept and specific embodiments according to the disclosure can be readily used as a basis for modifications or design of other methods and systems to achieve the same purposes as the present invention. Those skilled in the art should also understand that such equivalent assemblies do not depart from the spirit and scope of the invention in the broadest sense.
    Furthermore, the drawing figures in the following description are not necessarily to scale and certain features may be shown in a generalized or schematic form for the sake of clarity and conciseness or for information purposes and do not limit the scope of the claims.
    In addition, although specific terms are used herein, they are used only in a general and descriptive sense and not for the purpose of limitation. For example, the term computer, as used herein, is intended to include the necessary electronic components, such as, among other things, storage and processing components that are configured to enable programmed instructions to be executed.
    As described herein, the disclosed embodiments include an improved laser scanning device and method configured to prevent blind zone data loss. For example, in one embodiment, the device includes a data acquisition computer or other electronics that, based on the TOF measurement from the previous laser shot or a sequence of previous laser shots, predicts whether the return signal from the next laser shot is likely to fall into a blind zone if operation continues with the current LaserPRF. If the device determines that the return signal from the next laser shot is likely to fall into a blind zone when operation continues with the current laser PRF, the device is configured to either advance or delay the laser activation timing to ensure that the return signal does not fall into the blind zone. In some embodiments, the shot-to-shot adjustment process is performed while maintaining the average data collection rate scheduled for the mission.
    In one embodiment, the device is configured to reduce the laser power to no more than that required to obtain reliable range measurements at the selected flight altitude to reduce the possibility of a backscattered atmospheric result. The device is also configured to control a small mirror that controls the pointing direction of the receiver. An advantage of this additional
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    AT 16 690 U1 2020-04-15 Austrian patent office mirror configuration and this additional control process is that the required field of view (FOV) of the receiver is reduced while it is still possible to optimize the detection of the received signal. For example, the scan rate is typically a few thousand degrees per second. For long-range targets, the scanner mirror has moved by a significant distance at the time the return signal is received. As a result, a larger receiver FOV than the optimal one is required to enable detection at both short and long distances. As disclosed herein, using a small mirror controlled by a computer, it is possible to adjust the receiver orientation with respect to the transmitter depending on the scan rate and the distance to the target. This enables a smaller, optimized receiver field of view.
    [0026] Starting with FIG. 1, a block diagram is shown, which shows an exemplary configuration of a topographic lidar imaging system 100 according to the disclosed embodiments. In this particular embodiment, the system 100 comprises a pulse laser 1 with a collimator attached to it for generating a beam with low divergence. An example of such a laser is a fiber laser which can generate a pulse energy in the two-digit microjoule range in a pulse with a width of 2 nanoseconds with a pulse repetition frequency in the three-digit KHz range and which has a beam divergence of less than one milliradian. The pulse laser 1 is triggered externally by a pulse generator 2 and generates an optical short pulse 20 which is directed onto a primary oscillating scanner mirror 5 which is driven by a galvanometer scanner motor 12. An optical scanner, which includes the primary oscillating scanner mirror 5, the galvanometer scanner motor 12, and scanner drive electronics 9, simultaneously deflects the output transmit pulse 20 and the received return pulse (s) 22 from a target. Different scan patterns (such as a sawtooth pattern, a sinusoidal pattern, etc.) can be used to obtain sample data points from the depicted terrain.
    A small portion of the transmitted pulse energy is reflected by the terrain and then reflected by the primary oscillating scanner mirror 5 onto an off-axis parabolic mirror 11 and onto a secondary scanner mirror 13 before passing through a reimaging module 15, the lenses and a spectral filter 14 contains, and is passed to a detection device 3, which generates an electrical signal, which is amplified by a receiver electronics 4. The TOF is measured by a time interval meter 6.
    In the illustrated embodiment, the system includes a positioning and alignment component 7 that includes positioning by a global positioning system (GPS) and inertial systems that are used for direct geo-referencing of the location of the laser spot in the terrain. A control and data acquisition computer 10 (which includes electronics, one or more processors and memory components for storing and executing instructions, and non-volatile memory for storing data generated by the system) controls the operation of system 100. In one embodiment, the controller collects and data acquisition computer 10, for example, the measured data when the laser is activated, the TOF, a scan angle, a sensor position (e.g. a longitude, a latitude, a height above an ellipsoid, etc.) and orientation (rolling, Nod or direction of flight). The control and data acquisition computer 10 is configured to time stamp each data item and store it in a data storage device, such as a solid state hard drive, among others. In one embodiment, system 100 may include a wired or wireless external interface, such as operator interface 8, that enables system 100 to communicate with an external device. For example, in one embodiment, control and data acquisition computer 10 may receive programming instructions and / or other data from a laptop for setting system parameters and monitoring performance. In certain embodiments, system 100 may be configured to communicate over one or more public or private networks (e.g., the Internet, an intranet, a mobile data network, etc.) for programming instructions
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    AT 16 690 U1 2020-04-15 Austrian patent office and / or other data from the system 100 and to be sent to it. In some embodiments, the control and data acquisition computer 10 is configured to also run the mission planning software, which provides the ability to plan the mission by graphically selecting the study area on an imported map to retrieve the flight lanes required to navigate the study area selected flight altitude, and to monitor the actual detection range and the actual system status in real time.
    As shown in Figure 1, in certain embodiments, the system includes a secondary scanner mirror 13 for implementing a method to reduce the likelihood of detecting atmospheric backscatter. In current systems, the primary oscillating scanner mirror 5, for example, has rotated a significant angle at the time the return pulse (represented by a received beam 22) returns to the primary oscillating scanner mirror 5 after the transmitted laser pulse (by a Transmission beam 20 shown) was reflected from the primary oscillating scanner mirror 5 to the target when the distance to the target is large and the scan rate is high. Without the secondary scanner mirror 13, the receiving light spot moves back and forth across the surface of the detection device 3 when the primary oscillating scanner mirror 5 swings back and forth. Thus, in current systems in which the size of the detection device 3 determines the receiver FOV, a relatively large detection device and thus a large receiver FOV is required. However, the result is a less than optimal signal-to-noise ratio.
    Thus, the secondary scanner mirror 13 according to the disclosed embodiments is used to keep the received light spot in the center of the detection device 3 so that a smaller receiver FOV can be used. In one embodiment, the secondary scanner mirror 13 is synchronized to and driven on the same scan rate as the primary oscillating scanner mirror 5. Since backscattered pulses from the atmosphere are more frequent in the close range, these undesirable backscattered pulses fall on the edge of the detection device 3 and are thus greatly weakened.
    In one embodiment, the device is configured to operate with reduced laser power, which is a value that is no higher than that required to obtain reliable distance measurements at the selected flight altitude further reduce the possibility of backscattered atmospheric results. In one embodiment, the minimum laser power required to obtain reliable range measurements at the selected flight altitude can be determined by executing an algorithm that reads a value from a lookup table that contains minimum laser power levels versus flight altitude. In some embodiments, this process is performed continuously in real time to adjust the laser power when the altitude or terrain changes. The advantage of reducing the laser power to a value no higher than that required to obtain reliable range measurements is that the amplitude of the unwanted backscattered signals from internal reflections and from the atmosphere is reduced. Signals below the receiver detection threshold produce no output from the receiver and thus do not result in a blind zone.
    A second advantage of the disclosed embodiments is that the secondary scanner mirror is positioned (rotated) for long-range targets that require maximum laser power with an offset with respect to the primary scanner mirror, so that the primary scanner is at the time to which the echo (after the TOF delay) is received has rotated such that the pointing direction of the receiver FOV is in the optimal position to direct the long range echo but is not properly aligned for short range atmospheric results. This reduces or prevents the likelihood of capturing atmospheric results.
    For example, it is assumed that the primary oscillating scanner mirror 5
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    Radiate in a range of 4,000 degrees / second, the target distance is 3,500 m and the receiver FOV is 1 milliradian. The TOF for the 2-way transmission of the optical pulse is approximately 23.4 microseconds. The scanner thus rotated the beam about 1.6 mrad at the time the echo was received. Consequently, the receiver FOV for near-range targets is misaligned by 1.6 mrad when the secondary scanner mirror 13 is operated as described above, which results in a significant attenuation of return signals from after-range targets, thereby reducing or preventing blind zones caused by backscattered pulses be brought into the atmosphere.
    FIG. 2 shows the system 100 in operation. System 100 is mounted in or on an airborne platform, such as an aircraft 200. System 100 uses a pulse laser to generate a swath 202 that is generated by an optical flyover scanner, and the forward movement of the aircraft leads to a detection area along one Train. As indicated above, system 100 uses GPS positioning and an IMU (inertial measurement unit) to directly geo-reference the location of the laser spot in the terrain.
    Figure 3 is an example of a timing diagram showing a sequence 301, which includes three sequential laser trigger pulses, and a corresponding sequence 302 of laser output pulses for the case in which only one optical pulse is transmitted at any one time. In the illustrated embodiment, a trigger pulse 311 generates a laser output pulse 312, a trigger pulse 314 generates a laser output pulse 315 and a trigger pulse 317 generates an output pulse 318. A sequence 303 illustrates the received return pulses from the target which are due to the laser output pulses. For example, an echo pulse 313 is due to the laser output pulse 312, an echo pulse 316 is due to the laser pulse 315 and an echo pulse 319 is due to the laser output pulse 318. The corresponding blind zones (i.e. the time that the system is blind to input signals) are shown as 320, 321 and 322. In a conventional system, the width of the laser pulse is 2 or 3 nanoseconds, while the blind zone can extend over a two-digit nanosecond range or more.
    Figure 4 is an example of a timing diagram showing a sequence 401 representing five sequential laser trigger pulses on the laser and a corresponding sequence 402 of laser output pulses for the case where the laser is triggered before the echo (in a sequence 403) from the previous pulse. As a result, there are two optical pulses in the air at the same time in this scenario. For example, a trigger pulse 411 generates a laser output pulse 412 in the illustrated embodiment, a trigger pulse 414 generates a laser output pulse 415, a trigger pulse 417 generates an output pulse 418, a trigger pulse 420 generates an output pulse 421, and a trigger pulse 422 generates an output pulse 423. A return pulse 413 is due to the laser pulse 412, a return pulse 416 is due to the laser pulse 415, a return pulse 419 is due to the laser pulse 418, etc. As stated above, the return pulse 413 is due to the laser pulse 412 and not the laser pulse 415 and is the return pulse 416 due to the laser output pulse 415 and not the output pulse 418 since the laser is triggered before the return pulse has been received by the previous pulse. In the illustrated embodiment, the corresponding blind zones are shown as 433, 434, 435, 436 and 437. If several pulses are transmitted at the same time, the number of blind zones increases; however, the length of the blind zones remains unchanged. As a result, the number of possibly wasted laser shots increases.
    Referring now to FIG. 5, a flow diagram illustrating an example of a method for changing the laser activation timing to prevent possible blind zones is shown in accordance with the disclosed embodiments.
    The laser is operated with a target PRF that is selected to provide the required density of laser spots on the floor. In addition to the laser PRF is the point
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    AT 16 690 U1 2020-04-15 Austrian patent office density depends on the range from a minimum to maximum scan angle, the scanner speed, the aircraft speed above the ground and the flight height above the ground. For each laser shot, the TOF is the 2-way distance to the target (there and back) multiplied by the speed of light. This TOF (which is measured accurately) determines when the return pulse is received by the laser from the target based on the emission time of the pulse.
    Since the laser is triggered externally and because the laser emission occurs at a fixed, repeatable time after the last laser trigger has been applied, the time is T between the optical outputs of successive laser shots (where T is the reciprocal of the PRF at that time ) known. Thus, the times at which the blind zones occur are also known and can be controlled by changing the laser trigger time. In particular, T can be increased or decreased slightly from shot to shot to ensure that a blind zone does not coincide with the time at which the return pulse is received. These changes in T are equivalent to slight changes in laser PRF that do not significantly change the laser spot position on the ground or the spot density.
    For example, there are blind zones every 5 microseconds, which can extend (for example) over 10 nanoseconds when the laser is operated at a PRF of 200 kHz. If the distance to the target is 740 meters, the TOF is approximately 4,938 microseconds. In this example, the echo is received 62 nanoseconds before the blind zone. The previous flow of TOF measurements may indicate that for any reason (terrain variation, aircraft position or orientation change, scan angle change, etc.) there is a high probability that the echo from the next laser shot will fall into the blind zone if the PRF is not adjusted is made. The software algorithm that controls the laser activation timing can then switch the blind zone by decreasing T by an amount of 100 nanoseconds (slightly increasing the PRF) so that the echo now occurs after the blind zone, or the algorithm can increase T (the Reduce PRF slightly) so that the back pulse occurs far before the blind zone. These decisions are based on knowledge from previous TOF measurements.
    The process or algorithm is implemented as computer-executable instructions and is performed using one or more processors of the disclosed systems. The process begins at step 501 by monitoring the reported TOF (transit time) of each laser output pulse in real time. This is determined based on the time at which the laser output pulse is generated and the time at which the corresponding return pulse is received by the system. In this embodiment, the sequence of TOF measurements is analyzed at step 502 to predict whether a planned TOF is near a blind zone. In certain embodiments, the PRF can be adjusted based on user preference or other parameters such as flight data, type of terrain, etc.
    At step 503, the PRF (up or down) is corrected if the process determines that a scheduled TOF is near a blind zone to prevent this. In one embodiment, if the back pulse arrives less than 30 nanoseconds before a blind zone, the next laser trigger pulse is advanced by 50 nanoseconds (the PRF is increased slightly) so that the blind zone occurs before the expected time of the return pulse, or the laser trigger pulse becomes 40 nanoseconds delayed (the PRF slightly decreased) so that the blind zone occurs another 40 nanoseconds after the expected time of the return pulse.
    If the PRF has not been adjusted to avoid a blind zone, the process at step 504 adjusts the PRF to be closer to the initial PRF setting programmed for the investigation mission to the to achieve the desired point spacing and the desired point density.
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    AT 16 690 U1 2020-04-15 Austrian Patent Office In some embodiments, the adjustment can be performed by adding or subtracting a constant value. Alternatively, in other embodiments, the adjustment can be performed by adding or subtracting a dynamic range of values based on the particular planned TOF. In one embodiment, the system makes at least one adjustment necessary to cause the planned TOF not to be near a blind zone.
    [0045] Although TOF measurements are monitored in a time sequence in the illustrated embodiments, the process can be expanded in alternative embodiments to extrapolate by referencing past laser shots depending on a scanner position or calculated 3D position of the point.
    In yet other embodiments, the system can be configured to dynamically adjust the detection area from a minimum to maximum scan angle to compensate for the changing height of the aircraft and the changing ground elevation of the terrain, for a constant swath width and laser spot distribution on the ground to provide. In one embodiment, this is made possible by using a programmable galvanometer-based scanner. The programmable galvanometer-based scanner is configured to execute a swath tracking algorithm for the purpose of maintaining the desired laser spot density on the ground. In systems without swath tracking, the swath width is a function of the programmable scan angle and the flight altitude above the ground. As a result, the point density is not constant with varying terrain heights. According to the disclosed embodiments, by dynamically adjusting the scanner parameters (e.g., the coverage area from a minimum to a maximum scan angle), the system is able to keep the point density relatively constant when the height of the terrain changes during the survey mission.
    [0047] Furthermore, in certain embodiments, the system may also be configured to compensate for changes in aircraft altitude and roll angle of the aircraft. For example, in one embodiment, the positioning and alignment component 7 is configured as described in FIG. 1 to calculate the aircraft roll angle in real time using inputs from the GPS receiver and the inertial measurement unit. Since the axis of rotation of the primary oscillating scanner mirror 5 is parallel to the roll axis of the aircraft, the control and data acquisition computer 10 is able to program the primary oscillating scanner mirror 5 in order to compensate for the rolling of the aircraft by correspondingly displacing the swath. As a result of this adaptation, the swath is kept symmetrically centered under the aircraft. The control and data acquisition computer 10 also monitors the TOF data for each laser shot as measured by the time interval meter 6 and calculates the slope distance to the terrain. The system calculates the vertical elevation above the ground using the calculated slope distance to the terrain in conjunction with the measured scan angle associated with each laser shot and an average value is used that is used to measure the detection area from a minimum to a maximum Adjust scan angle (swath).
    In a further embodiment, the difference median of the aircraft to the ground distance is used to adjust the swath width.
    In yet another embodiment, when mapping sloping terrain, the extent of the swath on the ground below the left side of the aircraft can be designed differently than the extent of the swath on the ground below the right side of the aircraft.
    As an example of swath tracking, scheduled inspection flights for a maximum scan angle of 20 degrees at an altitude of 1,000 meters above the ground are assumed when the distance from the aircraft to the ground is either due to a change in terrain height or a change in Altitude of the aircraft changes to 2,000 meters, with the system dyna the maximum scan angle
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    AT 16 690 U1 2020-04-15 Austrian patent office mix reduced to 10 degrees in order to keep the swath width constant.
    Thus, the disclosed embodiments provide system operators with the advantage of swath tracking. An advantage of this additional feature includes that no swath widths larger than necessary have to be planned to cover the possibility that the distance of the aircraft from the ground changes, which leads to cost savings.
    [0052] Accordingly, the disclosed embodiments provide one or more technical solutions to the problems associated with current airborne laser scanning systems. For example, in one embodiment, the disclosed embodiments provide an improved airborne laser scanning system that prevents or reduces blind zones caused by unwanted scattered light (e.g., from reflections from interior optical components, a window at the exit of the system, or a window in the system) Aircraft that operates the system, etc.) and backscattered light from the first few meters of air beneath the aircraft. Furthermore, as disclosed above, the disclosed embodiments provide an improved airborne laser scanning system that is capable of maintaining a constant swath width.
    [0053] While representative procedures and articles have been described in detail herein, those skilled in the art will recognize that various substitutions and modifications can be made without departing from the scope of what is described and defined by the appended claims. For example, although the foregoing description describes certain steps and functions performed in a particular order and by particular modules, the features disclosed herein are not to be construed as limited to any particular order or implementation limitation. For example, one or more components in the embodiment described in Figure 1 can be added, repositioned, removed, and / or combined without departing from the scope of the disclosed embodiments. As another example, the process described in Figure 5 can adjust the PRF without considering whether the PRF is in its target setting.
    [0054] Thus, it is to be understood that the invention is not intended to be limited to the specific embodiments disclosed. The scope of the claims is intended to broadly cover the disclosed embodiments and any such modification or combination as disclosed herein.
    权利要求:
    Claims (20)
    [1]
    Expectations
    1. A system adapted to measure topographic elevations, the system comprising:
    • a pulse laser (1) for generating a laser light pulse (20);
    A primary mirror (5), which is adapted to oscillate back and forth in at least one axis in order to direct the laser light pulse (20) in a pattern to a target, and is further adapted to reflect (22) the laser light pulse ( 20) to receive from the target and to direct the reflections (22) of the laser light pulse (20) to a secondary mirror (13);
    the secondary mirror (13) being adapted to reorient the reflections (20) of the laser light pulse (20) towards a center of a detection device (3), the detection device (3) being configured to generate an electrical signal that is generated by a Receiver (4) is amplified;
    a time interval meter (6), which is configured to calculate a transit time based on a point in time at which the laser light pulse (20) is generated, at which the reflections (20) of the laser light pulse (20) are received by the receiver (4), to determine; and control electronics configured to measure the topographical surveys using the transit time.
    [2]
    The system of claim 1, further comprising a reimaging module (15) including lenses and at least one spectral filter (14) configured between the secondary mirror (13) and the detector (3) in which the reflections from the laser light pulse from the secondary mirror (13) to the detection device (3).
    [3]
    3. The system of claim 2, wherein the secondary mirror (13) is between the primary mirror (5) and the reimaging module (15).
    [4]
    4. System according to claim 1, wherein the pulse laser (1) is triggered by an external trigger pulse and a delay between the external trigger pulse and an emitted optical pulse from the pulse laser (1) is exactly known and repeatable.
    [5]
    5. The system of claim 1, wherein the control electronics (10) is configured to control a pointing direction of the secondary mirror (13) by which the receiver orientation with respect to the reflections (22) of the laser light pulse (20) are adjusted to one Reduce the possibility of capturing atmospheric backscatter results.
    [6]
    The system of claim 1, wherein the control electronics (10) are configured to reduce a possibility of capturing atmospheric backscatter results by reducing laser pulse energy to a level determined to be sufficient for reliable range measurements.
    [7]
    7. The system of claim 1, wherein the control electronics (10) is configured to determine a possible collision of an output laser light pulse with an input signal and to adjust a time of the output laser light pulse to avoid the possible collision.
    [8]
    The system of claim 7, wherein the possible collision occurs when the transit time of the input signal is in a blind zone (320, 321, 322) that occurs every time the laser is activated.
    [9]
    9. The system of claim 7, wherein adjusting the timing of the output laser light pulse comprises adjusting the pulse repetition rate closer to an initial value when the adjustment has been previously adjusted to prevent a possible collision.
    11/17
    AT 16 690 U1 2020-04-15 Austrian patent office
    [10]
    The system of claim 7, wherein adjusting the timing of the output laser light pulse to prevent the possible collision comprises making a minimum adjustment so that the input signal is not in a blind zone (320, 321, 322) that occurs every time the laser is activated.
    [11]
    11. The system of claim 1, further comprising a programmable galvanometer-based scanner configured to generate a swath width that maintains a constant point distribution on the target.
    [12]
    12. The system of claim 11, wherein the programmable galvanometer-based scanner is configured to dynamically adjust a scanner deflection angle and a swath width to compensate for changes in elevation and elevation.
    [13]
    13. The system of claim 11, wherein the control electronics (10) is further configured to compensate for a system roll motion by adjusting the primary mirror (5) so that a laser output beam direction is not affected by the system roll motion.
    [14]
    14. A machine implemented method for reducing data loss due to blind zones (320, 321, 322) in a laser scanning device, the method comprising:
    Dynamically monitoring a transit time (TOF) of a laser light pulse (20) transmitted and received by the laser scanning device;
    Determining whether a possible collision of an output laser light pulse with an input signal is likely to occur; and
    Adjusting a pulse repetition frequency (PRF) in response to a determination that the possible collision of the output laser light pulse with the input signal is likely to occur.
    [15]
    15. The method of claim 14, wherein the possible collision occurs when a transit time of the input signal is within a blind zone (320, 321, 322) that occurs every time the laser is activated.
    [16]
    16. The method of claim 14, wherein adjusting the timing of the output laser light pulse comprises adjusting the pulse repetition rate (PRF) closer to an initial value when the adjustment has been adjusted to prevent a possible collision.
    [17]
    17. The method of claim 14, further comprising controlling particular optical elements and a secondary scanner to prevent detection of unwanted echoes from the atmosphere.
    [18]
    18. A machine implemented method for maintaining a constant swath width using a laser scanning device, the method comprising:
    Dynamic adjustment of scanner parameters to keep a point density relatively constant if at least one of an aircraft altitude and a ground elevation of the site changes during an investigation mission.
    [19]
    19. The method of claim 18, wherein the scanner parameters include a scanner deflection angle.
    [20]
    20. The method of claim 18, wherein dynamically adjusting the scanner parameters includes balancing a roll angle of a flying platform on which the laser scanning device is mounted.
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    US10795023B2|2020-10-06|
    WO2016138585A1|2016-09-09|
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    US20160259058A1|2016-09-08|
    US20180045830A1|2018-02-15|
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    法律状态:
    优先权:
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    US14/639,320|US10698110B2|2015-03-05|2015-03-05|Laser scanning apparatus and method|
    PCT/CA2016/050220|WO2016138585A1|2015-03-05|2016-03-02|Improved laser scanning apparatus and method|
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