PROGRESS REPORT PERIOD OF 1 MAY 1965 TO 31 MAY 1965 CONTRACT NUMBER AF 33(600)40280

Document Type: 
Collection: 
Document Number (FOIA) /ESDN (CREST): 
CIA-RDP67B00657R000200210014-8
Release Decision: 
RIFPUB
Original Classification: 
K
Document Page Count: 
11
Document Creation Date: 
December 22, 2016
Document Release Date: 
December 9, 2010
Sequence Number: 
14
Case Number: 
Publication Date: 
January 1, 1965
Content Type: 
REPORT
File: 
AttachmentSize
PDF icon CIA-RDP67B00657R000200210014-8.pdf724.97 KB
Body: 
?/ AV P Ae Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 r. 1 +n- `ter, Copy of 5. PROGRESS REPORT PERIOD OF 1 MAY 1965 TO 31 MAY 1965 CONTRACT KMER AF 33(600)k0280 BY WESTINGHOUSE ELECTRIC CORPORATION AEROSPACE DIVISION BOX 746, BALTIMORE, MARYLAND 21203 SPECIAL HANDLING Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 TABLE OF CONTENTS A F-101 FLIGHT TEST FLIGHT TESTS MODIFICATIONS AND ORO SYSTEM REC ORDER QISE RpZEWER PRE-AMPLIFIER OTION COMPENSATION ANTENNA . . . . . ENVIRON TEST SPARES ? _ r < s r a GROUND SUPPORT EQUIPMENT ? a F CORRELATOR OPERATION CORR.ELATQR DESIGN RMEW , . . . . APPENDIX A - SCARY OF FLIGHTS TESTS . . r a ? s ? e ? 6 10 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 F-101 PLIG ht Tests Five fIigh flown during May, as Indicated in the program summary in Table I. Radar tests were devoted to evaluating the low noire pre-amplifier performance and obtaining data for linear receiver evaluation. The linear receiver data was acquired by varying receiver gain on repeated fly-'rya against a corner reflector pattern located at Soiling Field. An after-burner problem In the airoraf hta to allow engine tests at high altitude. None of the attempted have been effective in correcting the 'd mapping, burner misfi which occurs only above 30,000 feet. A summary of the individual flights appears in Appendix A. ht 165 was aborted due to a failure in the transmitter; flight 167 was unsuccessful because of a recorder fa lur TABLE I 101 PROGRAM SUMMARY may 1965 Flights Scheduled Radar hts Cancelled Weather Aircraft Transmitter aircraft hts Accomplished In-flight Failures mitter ecorder Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 flights to low altitude and reduced fligh r-. . , II? &If11 ILI f' 5F Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Transmitter ranamitt-er T developed a grid--to-cathode s hor during flight 165. Since the replacement tube was longer than the der defective tube, waveguide fittings and mounting braoketry had at ions and Ground Tests Bence. 't'ransm'itter 002 was then replaced by ? 1. Initial ~ts of drive, causing poor pulse shape and transmitter servo modified. The replacement tube would not saturate, even with power measurements were 26 watts average power. Changing the CPA high voltage increased power outpu of 69 watts with a pulse width oseconds. elver During preflight for 166, a noise figure o measured. Replacing a defective module in the Tunnel Di Amplifier restored the system noise figure to 6.5 db. After flight 166, the Tunnel Diode Amplifier was replaced by the Westinghouse Parametric Amplifier to complete the flight tests of this modification which were begun in January 1965. Inter- mittent gain variation and oscillations were noted during Flight ing WT in its normal configuration. Apparently the high The Par-Amp was retuned, this time while operating into the input VSWR of the TWT caused instabilities until compensated for by uni,ng Performance during flight 168 was excellent. System noise figure in 5.2 db; amplifier gain is 17 db. Bandwidth at the 1 db level is 157 mc, at the 3 db level, 233 me. owing flight 1.6h, the limiting IF ampi video channel was converted to a linear amplifier in order to demon- strate in-flight the effect of receiver non-linearity. Measurements SPECIAL HANDLING Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 rifled the received linearity. Sufficient flight data has not been gathered for complete evaluation of non-linearity effects. Failures During preflight for 168, the -(-60 volt power supply lost regulation. The breadboard power supply was installed on the mis door. The pressure window between the transmitter and antenna burned open during flight 164. The pressure system checked out and VSWR measurements of the system wavegu de and antenna did not indicate any existing conditions which could cause this failure.. The problem has not been encountered again; however, transmitter power output is now less than at the time of failure. SYSTEM Forward Look System No flights were made with the forward look system because abilities in their circuitry. Recorder roved flip-, l op circuitry has been wired into the electronics package from recorder 007. Tests have been encouraging. Following one more flight, this electronic package will be substituted Order 005 f 6r flight testing. Receiver Pre-Ampli.f etor supplies, pump tube, waveguide components, control mitry, and frame wiring are available and complete for the deliverable Par-Amp installation. Since circulator delivery has been delayed until mid-June, the system installation Is not expected to be complete until late July. Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Notices. Co npensation Aft ceiving the parts to reduce the peak transient resporaa of the integrator, one unit was mod if ied . Results of the transient response tests were as predicted. Frequency response measurements remain to be performed. Antenna Several investigations were started following the failure last ;h of the spare module at 275?C . A second module was temperature - pressu: ed to determine a different batch of Daryl adhesive would be satisfactory. This :odule failed at 200?C and 10 psig pressure in the same way as the first module. (2) special batch of Doryl without a wetting agent additive was obtained and applied to several sticks. Three test sticks held psig at 288?C., but all failed when the pressure was increased to 20 psig. Bonding with Doryl will be further tested,. with a chemical leaning process added to the procedure. Dupont states that no changes have been made to their ML fabric, the original material used on the antenna. Since it .s.,' expected to delaminate as before, no further tests are planned.with the ML. nghouse Research Labs proposed two new techniques. One involved bonding of a fiberglass film to a metal foil,, etching the foil to pond to the slot area.,., of an array stick, and the foil. to the array stick. The second procedure bonds the abric to the array sticks through heat and pressure without an adhesive. Since the second technique appears more feasible, experl- work has been authorized. Preliminary experiments will be -6- Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 performed on 12 waveguidea; if successful, 16 array stinks for one module will be bonded. (5) Vacuum will be inve d as a d ff erenll. of pre venting breakdown. Four test eticks were bonded conventionally the Dory l. Leakage rates will be checked on these sticks and coating applied to the fabric to reduce the leakage so that vacuums of approximately 10 mm. of mercury can be attained. Electrical tests allow. C EW RONM NT A-L TEST Recorder 006 passed a full explosion test. Since torque motors own to are in use, they were specially tested to prove that they would not cause an explosion. Details are reported in report ST14-169. D SPARES No items were added to either system or Ground Support Equipment spares this month. Status of spares is as follows: Items Items Per Cent' Shipped Open Complete 2 15 list plus first 10 amendments 2 Amendment 11 (remains open) 0 Ground Support Equipment 0 4 OTM SW'PPORT E QUIT After preliminary tests indicated the Film Evaluat c patible with the now optical bench components ral fabricated and the optical axis of the scanner changed to make the bench a practical test tool to measure azimuth resolution. Several plots of and multiple targets show -20 db sidelobes with a 4ynamic range greater than 30 db at low light levels. The _7 99 99 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 .UFf'IAI IaANfll INf; Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 -up is still being evaluated. CORRELATOR OPERATION in addition to processing the `-1011 flight film, one minor cation was made to the Correlator. The wedge interference filter holders were shortened to allow more motion to compensate for changes in the focal length across the field. Twice the range is now avail-- able, permitting compensations of + 5 per cent in focal length or approximately + 2 per cent in aircraft Velocity/film speed ratio. Royal X Pan Recording Film 5475 used, as the final film is no longer available. The replacement film type 2475 has similar speed but less dynamic range. When chemically processed as the 5)475, It has a higher gamma. By processing at 800 temperature rather than 900, a lower gamma and better dynamic range were obtained. All output films will now be processed in this manner. Much effort was spent on the Detail Correlator this month. A a of photographs were made using the designed 4,/ to I aspect tics, the 1.4 to 1 ratio obtained by inverting the cylinder conjugate and the 1.2 to 1 obtained by adding a small meniscus cylinder near the primary output plane. Both 4x and 18x magnifications were made. While the 1.2 and 1.4 aspect ratio were more pleasing;, the output d with these two set-ups was curved approximately 3 inches across inches. The field was flat for the 4.4 to 1 arrangement. Photographs of various targets on seven flights were teen on Polaroid Type 55 Positive/Negative film. This film allows fast resu for analysis and repetitive work, and gives a relatively high reso- lution negative for further enlargement. Because of the high gamma of the Type 55, it is not suitable for comparison of low return areas. I L HANDLING Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 SPECIAL HAKLING a CORRELATOR DESIGN VI1 The design review report is delayed because of information from Itek on their evrrelator noise and f'i and insufficient experimental time on the corre d ies nghousea SPECIAL HANDLING plete Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 "light w4V e 4 06 4 165 6 i l~ Date 5-3-65 5-11-65 5--10-65 Altitude s 22,500 22,500 22,500 Area !Washington, Washington, D. C. Washington, D. C. Purposes _ !Aircraft after-burner Aircraft afterburner and Receiver linearity test test, data acquisition. I receiver linearity tesus. Significant IF limiting eliminated Transmitter 001 in System stalled -26 watts Changes Resul Us APN- 102 Doppler Navigator d No data due to trans- Re- ,eiver gain switch left intermittent. Nest cart muter- failure = n in 0 db oo itio n on all Ii: e Etweer ha-If and full d r s a ;.sow level targets range . ontrast is good su 'i as grass or trees resolution is sligt-.Ulu be i- pp P }? conger t-`nar _,z, sal 'be- s'vs. !l ib a; - s L s low average, age, -Divergent gg k 'g ? e?3'1~.s of ri e receiver pclutter of bridges etc . ' ' , a in Detail like air- , !is strong Also strong . , lights, show up por targets blank out back- I ett ber than usual. .eso ground in az mutt . Some l~ ~t i on of road map is smearing over full range, good -15 were gt i- light d may be due to motion. mens~ons. Corner reflect Second and third runs are ors v' apart were separ- below average in both able. Cloud effects were contrast and resolution. checked; no discernible Dens ity variations ma-,- bel attenuation or scattering or scattering due to motion, Contrast at low levels very good. Strong target divergent clutter and az moth background blanking by strong targets was present APPENDIX A - SUMMARY OF FLIGWP S i Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 5-26-65 22,500 Purposes Aircraft after.-burner and receiver 1 inearit- tests Washington, D.C. ignif scant 63 watts average power 16.14 db less P gain ystem Far-Aro in glace of - 4 than fl t 16 _ hanges in receiver (5.db less receiver gain) 6 runs were made at -5, k 10, and -15 db IF (,:,rain. On most runs, low level contrast was verT good. Water and shadowed areas were cleaner than usual unless near a strong target which had some divergent clutter ;slight on Run #5, -15 db gain setting). Resolution was good over best areas Strong target halo did affect immediate surroundings. Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8