Remote sensing for resources development and environmental management: Remote sensing for resources development and environmental management

Damen, M. C. J.

Bibliographic data

Multivolume work

Persistent identifier:: 856342815

Title:: Remote sensing for resources development and environmental management

Sub title:: proceedings of the 7th international Symposium, Enschede, 25 - 29 August 1986

Year of publication:: 1986

Place of publication:: Rotterdam; Boston

Publisher of the original:: A. A. Balkema

Identifier (digital):: 856342815

Language:: English

Additional Notes:: Volume 1-3 erschienen von 1986-1988

Editor:: Damen, M. C. J.

Document type:: Multivolume work

Volume

Persistent identifier:: 856343064

Title:: Remote sensing for resources development and environmental management

Sub title:: proceedings of the 7th international Symposium, Enschede, 25 - 29 August 1986

Scope:: XV, 547 Seiten

Year of publication:: 1986

Place of publication:: Rotterdam; Boston

Publisher of the original:: A. A. Balkema

Identifier (digital):: 856343064

Illustration:: Illustrationen, Diagramme

Signature of the source:: ZS 312(26,7,1)

Language:: English

Usage licence:: Attribution 4.0 International (CC BY 4.0)

Editor:: Damen, M. C. J.

Publisher of the digital copy:: Technische Informationsbibliothek Hannover

Place of publication of the digital copy:: Hannover

Year of publication of the original:: 2016

Document type:: Volume

Collection:: Earth sciences

Chapter

Title:: 3 Spectral signatures of objects. Chairman: G. Guyot, Liaison: N. J. J. Bunnik

Document type:: Multivolume work

Structure type:: Chapter

Chapter

Title:: CAESAR: CCD Airborne Experimental Scanner for Applications in Remote Sensing. N. J. J. Bunnik & H. Pouwels, C. Smorenburg & A. L. G. van Valkenburg

Document type:: Multivolume work

Structure type:: Chapter

lir direction, : the interband ; for instance the combina- lired 9 bands r and aft :lly regis- iplied off-line ;ize and for The module i be tilted that a compact to the total 'indow in the atory air- .ESAR camera separation for minimized by void the intro- room scan prin- he object a for sea ob- em, the dy- ld be deter- ance, the bserved, the of the ima- ptics and the ty, band width, addition the role. For land the required lution of 0.5 of the mea- emperature calibration in ontrol would ents for the he same ervation 400-420 nm 435-455 nm 510-530 nm 555-575 nm 620-640 nm 675-695 nm 770-800 nm 990-1050 nm ed twice) £ 0,05% for all bands 10 and 20 m 5.7°. Fig. 1 Selection of spectral bands for land and sea observation by CAESAR. Fig. 2 CAESAR CCD camera module The main components are the standard objective, the spectral separation, bandfilters and CCD detectors and the selector electronics. From a market survey executed in 1982, three manu facturers of CCD's with 1728 detector elements were selected on basis of a set of primary criteria. A dedicated CCD testbench has been developed by the TPD. A detailed test programme has been executed with respect to the following characteristics: dark current (non-uniformity and temperature dependence), detector sensitivity, radiometric linearity and dy namic range, detector cross- talk, efficiency of signal conversion and charge transport. Finally one type of CCD was selected. DATA ACQUISITION AND REGISTRATION The NLR has developed a family of airborne analog to digital data conversion systems for different types of sensors like Side-looking Airborne Radar, Infra red line Scanner and Video camera. Based on the approach of a dedicated analog to digital convertor combined with a standardized programmable data for matter and an airborne high bit rate recording system, Fig. 3 Pushbroom scanning for land observation with 3 co-registered (central) channels of the modules; for sea observation all 9 channels (3x3 co-registered) are used. for CAESAR the multichannel convertor "CEDIG" has been developed. The maximum input data rate for the HBR has been upgraded to 8.4 Mbits per sec. The CEDIG system is programmable with respect to the number of pixels per scanline, the number of bits per pixel and the integration time. The number of samples per line is either 1280 or 1792. Electronic roll correction is realized by positioning the 1728 pixels within the 1792 samples or by selection of 1280 pixels from the 1728 measurements. By changing the integration time the number of scan lines per sec with corresponding along-track spatial resolutions can be changed stepwise. In such a way trade-offs are possible between intensity resolu tion, spatial resolution, swath width and number of channels. REALISATION AND FLIGHT TESTING Figure 4 shows the configuration of the CAESAR sensor system. Three identical CCD camera modules are moun ted on a common base plate and are aligned in paral lel in the optical laboratory of the TPD. The three modules are protected by means of a box. This down looking box is mounted in a support structure. The baseplate can be adjusted at the selected tilt angle. Beside the three modules, the forward-looking module is mounted within the support structure. The off-nadir direction can be varied with a number of discrete steps. The internal temperature of both modules can be maintained at a nominal level by means of a flow of dry cooled air. This is required in case of opera tions in tropical regions. The electronics, the inertial navigation platform and the high density recorder are mounted in remo vable racks inside the aircraft. The first in-flight tests have been executed in 1984 for initial perfor mance testing of the integrated system and for the generation of image data required for the develop ment and testing of the dedicated system correction (preprocessing) software. Figure 5 presents an example of one of the first images. No geometric and radiometric corrections have been applied, except the real time roll correction. After the first in flight tests a series of environmental tests have been executed, like vibration tests, temperature and electromagnetic interference tests. Some mechanical improvements of the support structure and modifica-

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