Airborne multiband imaging spectrometer

• US 5,276,321 A
• Filed: 09/12/1992
• Issued: 01/04/1994
• Est. Priority Date: 04/15/1991
• Status: Expired due to Fees

• Current Assignee: Internal Revenue Service (Government of the United States of America)
• Original Assignee: Geophysical & Environmental Research Corp.
• Inventors: Westfield, Mark J., Chang, Sheng-Huei
• Primary Examiner(s): Nelms, David C.
• Assistant Examiner(s): SHAMI, KHALED
• Application Number:
  US07/944,167
• Time in Patent Office: 479 Days
• Field of Search: 250/226, 250/234, 250/235, 250/236, 250/334, 358/109, 358/199, 359/218, 359/219, 359/221, 359/226, 356/320
• US Class Current: 250/226
• CPC Class Codes: G01C 11/025 by scanning the object
• CPC Class Codes: G01J 2003/2866 Markers; Calibrating of scan
• CPC Class Codes: G01J 3/021 using plane or convex mirrors, parallel phase plates, or particular reflectors
• CPC Class Codes: G01J 3/06 Scanning arrangements arrangements for order-selection
• CPC Class Codes: G01J 3/18 using diffraction elements, e.g. grating gratings per se G02B
• CPC Class Codes: G01J 3/2803 using photoelectric array detector
• CPC Class Codes: G01J 3/2823 Imaging spectrometer
• CPC Class Codes: G01J 3/36 Investigating two or more bands of a spectrum by separate detectors
• CPC Class Codes: G01V 8/02 Prospecting

Abstract

A multichannel imaging spectrometer for airborne geological, geophysical and environmental surveys in a moving vehicle. An optical scanner employs a rotating polygon allowing reduced scan optics with increased data acquisition efficiency. Multiple spectrometers integrally registered allow channelization of the received signal to optimize noise performance in the range from ultraviolet through infrared. Output data is in a form for recording and real time display. A staring mode configuration provides enhanced sensitivity by using a two-dimensional detector array and adjustable mirror orientation. A scanning mode embodiment employs a two-dimensional detector array with time delay integration and three-dimensional storage of temporal spatial data and spectral wavelength and intensity. Thus, all channels are acquired simultaneously, resulting in perfect band-to-band registration with continuous spectral curves over the field of view.

Claims

1. A geological, geophysical, and environmental survey instrument adapted for use in a moving vehicle, comprising:

optical imaging means, comprising;

wide-angle rotating mirror means having a plurality of reflective surfaces for providing a substantially continuous image with respect to time of radiant spectral emissions at a predetermined angular field of view, and first fixed mirror means for redirecting said image of spectral emissions from said rotating mirror means through an aperture to collimating means for providing a collimated output thereof;

spectrometer means, comprising second fixed mirror means angularly disposed for directing said collimated output to first beam splitter means, said first beam splitter means integrally located in the optical path of said collimating means for receiving said output and for providing at least first and second bands of spectral emissions having different predetermined wavelengths to frequency selective optical means, said frequency selective optical means selectively responsive to one of said first and second bands of spectral emissions for providing a predetermined angular dispersion of said one band of spectral emissions, the number and bandwidth of said dispersed spectral emissions selected for maximizing a temperature difference, and for transmitting at a second angular dispersion one other than said one band of spectral emissions;

detector means, comprised of a plurality of photoresponsive sensing elements configured in a line array, each of said sensing elements so constructed and adapted for responding to a given bandwidth of spectral emissions and spatially disposed for alignment with one of said angularly dispersed spectral emissions, said sensing elements being incrementally spaced in proportion to a given wavelength to which each of said elements are responsive, for providing a signal representative of a given spectral emission amplitude as a function of wavelength, said frequency selective optical means and said detector means cooperating in alignment to maintain registration of said angularly disposed spectral emissions with predetermined ones of said plurality of sensing elements; and

signal processing means simultaneously operative for each of said sensing elements, comprising means for averaging and holding a detected signal at a substantially constant value to provide a continuous signal output for a predetermined period of time, means for periodically sampling said continuous signal output in synchronism with rotation of said rotating mirror means and for producing an updated sample corresponding to the interval between successive pixels as said mirror means traverses said angular field of view, and an analog-to-digital converter, thereby to provide a continuous signal output in digital form at each of said sensed spectral wavelengths.

2. A geological, geophysical, and environmental survey instrument as set forth in claim 1, said spectrometer means further comprising:

imaging spectrometer means comprising second beam splitter means angularly disposed in the optical path of said first beam splitter means, for dividing said first band of spectral emissions into third and fourth bands of spectral emissions at different predetermined wavelengths;

said frequency selective optical means comprised of first, second and third frequency selective optical means operative at respective first, second and third subbands responsive to predetermined spectra;

said first frequency selective optical means disposed at a predetermined angle of incidence with respect to the horizontal plane such that spectrally dispersed emissions of said first subband are directed at first focusing lens means for focusing said spectrally dispersed emissions from said first frequency selective optical means to be incident upon a first plurality of corresponding sensing elements of said detector means, said first plurality of sensing elements responsive to predetermined bandwidths, said first subband comprising a first predetermined range of substantially contiguous wavelengths;

further comprising third beam splitter means angularly disposed with respect to the horizontal plane to respond to said fourth band of spectral emissions and to direct at least a first portion thereof to said second frequency selective optical means, said second frequency selective optical means angularly disposed with respect to the horizontal plane such that spectrally dispersed emissions of said second subband are directed at second focusing lens means for focusing said portion to be incident upon at least a second plurality of corresponding sensing elements of said detector means, said second plurality of sensing elements responsive to predetermined bandwidths, said second subband comprising a second predetermined range of substantially contiguous wavelengths;

said third frequency selective optical means angularly disposed with respect to said third beam splitter means to respond to a portion other than said first portion of said fourth band of spectral emissions and to direct said other portion to third focusing lens means for focusing emissions of said third subband to be incident upon at least a third plurality of corresponding sensing elements of said detector means, said third subband comprising a third predetermined substantially contiguous range of wavelengths; and

housing means enclosing each of said sensing elements and containing cooling means for cooling each of said first, second, and third plurality of sensing elements;

said second band of spectral emissions directed by said first beam splitter means to a fourth focusing means for focusing emissions incident thereupon to be incident upon at least one sensing element of said detector means responsive to a fourth predetermined range of substantially contiguous wavelengths.

3. Imaging apparatus for an airborne vehicle, said apparatus comprising:

mirror means having a plurality of reflective surfaces for providing an image of a field of view, said image being acquired transverse to the flight path of said airborne vehicle, said mirror means being adapted for disposal at a predetermined angle of reflection, said angle being variable with respect to the nadir,

spectrometer means, comprising optical collection means for receiving a reflected image of said field of view and for focusing said image upon a slit aperture oriented with its length in the cross-track direction of flight,

collimating means for applying said focused image to beam splitter means for reflecting a first predetermined spectral portion of said image and for transmitting a second predetermined spectral portion of said image,

grating means for directing said first and second spectral portions to lens means,

said lens means for focusing and applying said first and second portions of said image to respective first and second two dimensional detector arrays,

said detector arrays comprised of a matrix of sensor elements, said sensor elements being arranged in rows and columns, the number of rows in said arrays corresponding to a predetermined number of in-track picture elements, the number of columns corresponding to the number of spectral channels of a given average bandwidth,

wherein said image is resolved by said spectrometer means into a matrix of spectral channels as a function of the spatial image, each predetermined spatial increment along the cross-track direction corresponding to a continuous spectral distribution in the in-track direction, each spectral channel corresponding to a given plurality of sensor elements, each sensor element storing an electrical signal representative of said average band of wavelengths and an intensity corresponding to the temporal image incident thereupon,

means for reading all said electrical signals in parallel and digitally transferring said signals to storage means, and

means synchronized to the in-track motion of the airborne vehicle for clearing said electrical signals and energizing said sensor elements with a new image corresponding to the in-track displacement of the vehicle,

whereat said storage means is operative to provide a continuous spectral distribution temporally synchronized with a continuous spatial field traversed by said aircraft.

4. Imaging apparatus as set forth in claim 3, wherein said aperture comprises an elongated slit aperture and further comprising image corrector lens means disposed to focus upon said slit, and wherein said slit is disposed at the focal point of said collimating means, whereby spectral aberrations are urged to a corrective focus along the line of said slit.

5. Imaging apparatus as set forth in claim 4, wherein said image corrector lens means further comprises cylindrical lens means for forming a line image parallel to the axes of the cylindrical surfaces of said cylindrical lens and along the length of said slit.

16. Imaging apparatus as set forth in claim 3, wherein said mirror means comprises a regular prism having a pair of adjacent faces fixed in the nadir direction, a pair of auxiliary mirrors mounted on said adjacent faces of said prism for viewing the field of view, said optical collection means including parabolic mirror means for reflecting images from said auxiliary mirror means to said slit aperture, whereat said auxiliary mirror means has a reflective surface of such an area that said parabolic mirror means and said slit aperture is fully covered by the reflected image of the field of view.

17. Imaging apparatus as set forth in claim 3, wherein said detector arrays are CCD arrays and further comprising means for providing a signal for clearing and energizing said CCD arrays at a predetermined rate corresponding to the velocity of the vehicle.

6. Imaging apparatus for an airborne vehicle, said apparatus comprising:

scanning mirror means having a plurality of reflective surfaces for providing an image of a field of view, said image being acquired as said mirror is rotated transverse to the flight path of said vehicle over a predetermined lateral swath,

spectrometer means, comprising optical collection means for receiving a reflected image of said field of view and for focusing said image upon a slit aperture oriented with its length in the in-track direction of flight,

collimating means for applying said focused image to beam splitter means for reflecting a first predetermined spectral portion of said image and for transmitting a second predetermined spectral portion of said image,

grating means for directing said first and second spectral portions to lens means,

said lens means for focusing and applying said first and second portions of said image to respective first and second two dimensional detector arrays,

said detector arrays comprised of a matrix of sensor elements, said sensor elements being arranged in rows and columns, the number of rows in said arrays corresponding to a predetermined number of picture elements in the flight direction, the number of columns corresponding to the number of spectral channels of a given average bandwidth,

wherein said image is resolved by said spectrometer means into a matrix of spectral channels as a function of the spatial image, each predetermined spatial increment along the cross-track direction corresponding to a continuous spectral distribution in the in-track direction, each spectral channel corresponding to a given plurality of sensor elements, each sensor element storing an electrical signal representative of said average band of wavelengths and an intensity corresponding to the temporal image incident thereupon,

means for reading all said electrical signals in a given column in parallel as said mirror rotates and digitally transferring said signals to storage means, and

means synchronized to the in-track motion of the airborne vehicle for clearing said electrical signals and energizing said sensor elements with a new image corresponding to the in-track displacement of the aircraft,

whereat said storage means is operative to provide a continuous spectral distribution temporally synchronized with a continuous spatial field traversed by said aircraft.

7. Imaging apparatus as set forth in claim 6, wherein said aperture comprises an elongated slit aperture and further comprising image corrector lens means disposed to focus upon said slit, and wherein said slit is disposed at the focal point of said collimating means, whereby spectral aberrations are urged to a corrective focus along the line of said slit.

8. Imaging apparatus as set forth in claim 7, wherein said image corrector lens means further comprises cylindrical lens means for forming a line image parallel to the axes of the cylindrical surfaces of said cylindrical lens and along the length of said slit.

9. Imaging apparatus as set forth in claim 7, further comprising analog to digital convertor means for providing digitized signal from analog outputs of said sensor elements to said storage means, said storage means comprising ping-pong memory means for alternately and sequentially retrieving ones of said digital signals and providing said signals to recorder means, whereby signals are stored in a first portion of said memory means while a second portion thereof discharges its data to recorder means.

10. Imaging apparatus as set forth in claim 9, further comprising means for periodically shifting the stored electrical signal row-by-row in the in-track direction, the stored electrical signals in a given sensor element being summed with the stored electrical signal of the preceding sensor element, the stored electrical signal from the end sensor of each column of the array being provided periodically as an output signal, each successive output signal of a column being representative of the intensity of radiation from a predetermined contiguous band of frequencies from a portion of the field of view and being time delay integrated by all the elements in a given column in succession, the speed at which such output signals are periodically provided being a linear function of the velocity and altitude of the airborne vehicle.

11. Imaging apparatus as set forth in claim 10, wherein said storage means includes a register having inputs coupled to selected sensor elements for receiving the output of each element, and all said stored output signals are shifted in parallel at the end of each scan of the mirror,

further comprising encoder means for providing a signal corresponding to the rotational position of said scanning mirror means and multiplexer means for providing an output signal correlating spectral frequency and intensity with said positional signal and a signal proportional to a function of velocity and altitude of the airborne vehicle, whereby said output signal of said multiplexer means provides a spectral frequency and intensity for each pixel in said field of view.

12. Imaging apparatus as set forth in claim 11, wherein said first detector array comprises a silicon CCD sensor array and said second detector array comprises an indium antimonide sensor array.

13. Imaging apparatus as set forth in claim 12, wherein said first detector array comprises a matrix of 256×

150 sensor elements and said second detector array comprises a matrix of 256×

60 elements.

14. Imaging apparatus as set forth in claim 13, wherein each column of sensor elements is responsive to a different band of spectral frequencies, and each sensor element in a column is aligned in temporal registration with a corresponding picture element and associated spectral intensity in the cross-track direction.

15. Imaging apparatus as set forth in claim 14, said first and second detector arrays comprising a plurality of detector cells which provide a plurality of synchronously integrated signals representing the radiation impinging on the array at any given time,

multiplexer means having a plurality of multiplexer channels wherein each multiplexer channel is connected to one of the detector cells so as to receive the synchronously integrated signals,

means for digitizing said synchronous signals, and

memory means for storing the digitized radiation signals together with synchronous positional data including mirror displacement information corresponding in time to each portion of the digitized radiation signal and to the incremental position of the mirror with respect to changes in the in-flight field of view.