PROGRESS REPORT PERIOD OF 1 SEPTEMBER 1965 TO 30 SEPTEMBER 1965 CONTRACT NUMBER AF33(600)40280 10 NOVEMBER 1965

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Document Number (FOIA) /ESDN (CREST): 
CIA-RDP67B00657R000200210008-5
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RIFPUB
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K
Document Page Count: 
13
Document Creation Date: 
December 22, 2016
Document Release Date: 
December 9, 2010
Sequence Number: 
8
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Publication Date: 
November 10, 1965
Content Type: 
REPORT
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PDF icon CIA-RDP67B00657R000200210008-5.pdf876.3 KB
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Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 'MW Copy 2 of 5. PROGRESS REPORT PERIOD OF 1 SEPTEMBER 1965 TO 30 SEPTEMBE CONTRACT NUMBER AF33 (6003) 4280 10 November 1965 DOC.Q.-- COPY- OF PAGES .__--...._.. 1965 BY WESTINGHOUSE ELECTRIC CORPORATION AEROSPACE D SION 0. Box 746, Baltimore, Maryland 21203 S -1E !AI HANDLING Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 TABLE OF CONTENT A P_10l Flight Test ht Tests ations and Ground Tests B Field Flight Test C System Recorder r r a . . r . Automatic Gain Control Transmitter s rr . N Low Noise Receiver Pre-Amplifier . Antenna r Spares Correlator Operation relator Mechanical Review Appendix A - Summary of Flights 4 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 A F-101 FLIGHT TEST FLIGHT TESTS Four missions were flown in September, producing data of the Wallops Island, Philadelphia, and Washington-Baltimore areas. Specific information on all four flights is tabulated in Appendix A. Flight 184 was planned as the first of a series of flights ng altitude and radar conditions of the Field Flight Test, ever, after the F-101 was airborne, ground control would allow a maximum altitude of only 35,000 feet and the flight was of no use for altitude comparison. The second flight of this series, flown the same day over the same path at 20,000 feet, was unsuccessful because of a transmitter TWT failure. The target area for the repeat flights for high altitude simulation was shifted from Philadelphia to Washington-Baltimore on flight 186 because of sonic noise considerations. TAME F-101 Program Summary September 1965 Flights Scheduled Flights Accomplished Productive Radar Flights No Results-Transmitter Tt+ T Failure Flights Cancelled Weather 3 Target Area Clearance 1 Aircraft Problems 1 Recorder i Transmitter 1 Receiver 1 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 n intermittent random striping or fading of video recorded on primary film was mated, similar to the problem experienced ate spring of 1964. Since the deliverable receiver used on this one flight is suspected of being the cause, the breadboard receiver will be installed for the next flight. Shortly after the end of the radar run on flight 186, a engine fire warning indication was observed. Post-flight checks revealed an insulating blanket located between the engine and fire warning sensors, had been punctured and insulating material displaced. The aircraft has been grounded since the flight, awaiting replacement of the blanket.- DP? operation was checked on flight 183. Up to. 15 db attenuation was inserted in the D IF amplifier with no noticeable racker operation. The improvement in M?T operation is due to replacement of a defective transistor In the Prequency fenerator as described in the August progress report. MODIFICATIONS AND GROUND TESTS ;Titter The transmitter failure of flight 185 was caused by a grid-t cathode short within the 7'. This tube was replaced. Internal arcing of the new TWT caused an overload of diodes .n the WT filament voltage switching circuit ., This circuit was modified to switch the diodes out of the circuit prior to th application of the TWT high voltage. Voltage can now be applied to the vac-ion pump of the TW during periods of transmitter inactivity to maintain its vacuum ithout applying full high voltage. Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Transmitter servo lookup has been improved by molding n external control into a pigmy connector and eliminating the connector cable. The deliverable transmitters have always had this Improvement. Receiver A defective stab in the breadboard receiver was discovered prior to flight 186. Receiver 003 was. installed in the aircraft. Although ground checks were satisfactory, the striping noted on flight 1.6 may have been caused by this receiver. After replacing a defective tube and relay, the breadboard receiver was re-installed in the F-101 for the next flight. Recorder is normally free to slide from side to side over the film take-up roller. However, several days exposure to high humidity caused film to stick to rubber rollers and eventually creep over the roller flanges. This problem was corrected by replacing the rubber take-up roller with an aluminum roller. After performing the 10-flight recorder adjustment and in- spection procedure per T-Spec 787137, the electronics package was led for 14 ke sweep operation in preparation for the fligh simulating field conditions. KA-45A Camera The A.-15A was returned to the manufacturer for investigation of the shutter malfunction. No difficulty was noted. Since being returned to Westinghouse, the camera has not operated properly and is still being checked in the laboratory. Instrumentation chile the aircraft is grounded for the fire warning problem several instrumentation channels are being calibrated. Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 FIELD FIGHT TEST A proposal was submitted in anticipation of the reactivation of the Field Flight Test. Supplementing this proposa request for replenishment of spares as they are used and for additional test equipment to test the parametric amplifier now being added to the systems. the completion of the extensive modifications to the electronic package, all three recorders are now operational. However, the first package used vector boards for initial testing. These will be replaced with. printed circuit boards as used on the later two units after Recorder 005 is removed from the F-101 next month. An Automatic Bias Control (ABC) was included in each recorders when delivered by Itek.. Because the circuit has be extremely noisy, erratic, and narrow in dynamic range, the ABC has never been operated closed loop to control the average light output of the cathode ray tube, but used only as a CRT light monitor for the failure circui, Several months ago, the film gamma was Increased to improve overall recorder signal linearity. This reduced the required grid drive to only 10-20 volts peak-to-peak,, causing two conditions which dictated improvements to the ABC: all variations in grid bias or CRT char?acteri.stics now cause a signif leant change In light output and the operating point on the bias-transmission curve. -6- Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 The more critical recorder set-up makes pre-flight checks all the more Important. The present cheek is a three-point bias check of film density, which requires developing and analyzing the film before correcting set-up. This undesirable time lag should be reduced. Several changes have been tried on one recorder to improve the BC performance 1. The light sensor increased in area by a factor of 7 and placed more advantageously, making a large improvement in the circuit signal/noise ratio 2. Input impedance to the ABC amplifier reduced from 10K to I K ohms providing the proper impedance match for the light sensor with improved stability and reduced noise. Input circuit tuned to the system PRF giving somewhat greater gain. Circuitry changed to allow switching from open loop (light meter operation) to closed loop (ABC) operation without requiring a change in the bias adjustment. Preliminary tests show the circuit to work well in closed loop. A means of adjusting the C1 light output operating point is being developed. Eventually these improvements will be incorporated in all three recorders. AUTOMATIC GAIN CONTROL A flyable breadboard of the AGC was built and installed but not connected in the F-101. Flight testing is delayed until sufficient time is available to cheek out the AGC performance in the receiver. Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 TRANSMITTER Based on the experience with the F-101 teats, three modifications have been designed for the transmitter and are to be incorporated in units. These are t Redesign of the TWT filament voltage switching circuit to improve reliability. TWT t s are subject to internal area under normal operation because of manufacturing imperfections and outgassing. In the past, this arcing has caused some lures in the filament switching c Simplification of this circuitry, with one component change, has eliminated the failures due to arcing with no change in function. 21 Addition of an external method of applying voltage to the TWT vac-ion pump when the transmitter is charged with Adding two high voltage diodes and using a spare ENC connector on the transmitter shell allow the TWT- to be vacuum pumped without applying high voltage to the CPA. The vac-ion pump is normally operated full-time when. the transmitter is in 64 Addition of a TiT overload circuit to prevent loss of suit components in the T'AT power supply and modulator when an overload occurs. With this change, either a TWT or CPA overload will shut off the transmitter and be in- dicated by the CPA failure light on the Control Panel. This overload circuit was deemed necessary because a T failure in the P-101 transmitter caused the Phase' C power supply fuse to blow, which in turn caused the two transmitter heat exchanger blowers, running on only phases, to overheat and fail. Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 OW NOISE RECEIVER PRE-AMPLI The parametric amplifiers for the two deliverable units are being assembled now. ANTENNA The heat-pressure life test on three array sticks bonded with i-40 resin was discontinued after 604 hours at 550?F and 30 psig internal pressure. The three sticks were then packed in dry ice for three periods of 8 hours each. No leakage was detected from any of the sticks either during or after the test. During the continuous heat pressure test, large bubbles developed on one stick and small bubbles on another. ation of the bond area showed that a residue of resin remained on both the fabric and the metal stick surface, thus indicating a resin deterioration. Based on these tests, life expectancy of the seal 500 to 600 hours at 5500F and 30 prig with no degradation at _65?F Bonding of the array sticks for Antenna 002 is complete on five of the six modules. All sticks will undergo a heat-pressure check at 550 or 8 hours before assembly to the module, Completion of Antenna 002 is planned for 1 November 1965. The feasibility of electron beam welding the joint between the array stick and the manifolds was discussed at Westinghouse Atomic Power Division. The complexity of the job evidently prevents the of welding in this application, No further Investigation is planned. LcAL HANDLING Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 The report on the bonding study at Westinghouse Research Labs was released as technical. memorandum STM-172 ' Polyimide Impregnated Glass Cloth Bonded to Nickel Surfaces for High Temperature, Oas Tight Seals". D SPARES After adding four transmitter spares items (two blo one motor, and an "C" ring), Amendment 11 to the system spar exhibit has been closed and prepared for submission for negotiation. The last of the spares for Ground Support Equipment was delivered in September. Status of spares is suzmmari ed t Items Shipped Items Per Cent in September open Complete System Basic list plus first 10 amendments 0 Amendment 11 0 Ground Support Equipment 1 E CORRELATOR OPERATION In addition to the regular flight support, some flight film was recorrelated to give optimum focus at particular areas of interes Flight 182 was rerun to obtain the optimum position of the output slit system. On the Detail Correlator, the tank platen assembly was Inter- changed with the unit located at Itek, which includes a pump and fluid filter system. The film now used In the Linhof camera back for making exposures on the Detail Correlator is Type 247 5,, the same used In the Correlator except for the 70 mm width. 17 99 99 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 CORRELA'FOR MECHANICAL R. ''IE As a result of the Correlator design investigation, five ations, are being proposed to improve the Correlator Performance. These are a new input alit mount to reduce stray light at the output film plane installation of a liquid filter to reduce scattering of light due to dirt in the liquid gate polishing of scratched lenses to eliminate stray light due to scratched surfaces procuring new platen glasses to allow repolishing the platens on a rotation basis new rainbow filters with the proper slope to reduce azimuth resolution errors when processing film from 22,500 foot altitude flights. In addition, a film cleaner to reduce scattering of light due to dust on the Input film was Justified by the study. This eaner was quoted as part of the normal maintenance costs of e correlator. Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 APP'17Y A Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 SIGNIFICANT S ti T a CHANGES a-a FLIGHT NO. 183 18k 185 DATE 9-3- 9-8-65 9--8 ALTITUDE 20000 35000 20000 AREA PURPOSES To evaluate W' opa rati High altitude simu- nigh altitude slm t- l and obtain radar map of j lation flight over lation flight over Wallops Island missile Philadelphia, Pa. Philadelphia, Pa. launching site. Repaired circuitry None None for video and D YT. a g 1 ES~MTS a Is a rc~m I'~m a 7 - i ~' 1 range. Contrast & map is best f ra m. near l No data. { resolution are good. S t t edge to 3A range . 5 ome arge s less than. Resolution is not tie 1 20 ft. ShadM3 are fair beat contrast is f a clean. Low density bands corres o d t IW Elementary dote are p n o T track- in error I t elongated as much as g s. ns r nt- 3 to 1 and change in I ation Information for direction from verti- deters .ng offset freq- cal to 2 o' clock. nr uency in error. was tole 't . Antenna W46 pulled around by acceler- ometer integrator. Suspect roll table, sity bands not as eonasty; Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 rsrrsurv. n, Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5 186 FLIGHT No. DATE 9-21-65 ALTITUDE 1 AREA PURPOSES over Washington, D.C. and Baltimore: . ?S FF ICANT C NOW transmitter TWT;, receiver package changed S O- ~M t .tH~i ? E i j C9 RE&SSIM.S.S Stripes on pr or # 04 to .12 see, duration not always uniform over range.- My be caused by Stale instability. In be t areas resolution and con mast is . jqap Is faced good ram gedge to 1/3 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210008-5