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Approved for public release; distribution isunlimited.

Distribution authorized to U.S. Gov't. agenciesonly; Test and Evaluation; MAY 1974. Otherrequests shall be referred to Air ForceArmament Laboratory, Attn: DLJF, Eglin AFB, FL32542.

AFATL ltr, 3 Jan 1977

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DESIGN AND DEVELOPMENT OF FZU.32/B BOMB FUZE INITIATOR

FAItCNllD CAMIIA AMO INSTIUMIHT CO»fOIATIOH

TICMMICAl »IPOIT Af ATl.TI.74-M

MAY 1974

Wrtrltotion ll^t«d to U. S. Govmmmt »«•»clw only; iS. roJJrt doc«««t. to.t «d ovaluation; ttjkrtbj^ lüdUtloTippU««! May 1974 . Jth« *******, SS docu^rt-wt bo Voforrod to the ^%^« A"S?lt

Uboratory 0>LJPL Uli* Air Porco Base. Florid» 32542.

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ABSTRACT

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The primary objective of this program under Contract No. F08635- 72-C-0152 was to develop a cost effective, production engineered FZU- 24/B Bomb Fuze Initiator. The initiator is an electric generating device which, when installed in the fuze charging well of general purpose bombs, is capable of deriving energy from the airstream passing the bomb in free fall and converting the energy into electric energy suitable for powering a bomb fuze. The objective was to be accomplished by means of a production engineering effort carried through the evolution of design, fabrication, assembly, test, and evaluation. The baseline for the design was Harry Diamond Laboratories' Drawing No. 11716160. A quantity of 60 units was fabricated and tested in accordance with the production engineered design. After some additional redesign to correct Identified deficiencies, 220 units were fabricated. These units were subjected to environmental, wind tunnel, and flight testing and performance requirements were met. ADTC- TR-74-J. FMU-114/B and FZU-32/B Initiator Functional Evaluftinn. January 1974, and ADTC.TR.74-52, Functional Test of tha FZU-32/B pomb F>»? hlttiWr» July 1974,document the results of these tests. The final unit design was designated the FZU-32/B Bomb Fuze Initiator.

Distribution limited to U. S. Government agencies only; this report documents test and evaluation; distribution limitation applied May 1974. Other requests for this document must be referred to the Air Force Armament Laboratory (DLJF), Eglln Air Force Base, Florida 32542

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TABLE OF CONTENTS

I

Section

I

II

Title

III

IV

INTRODUCTION

Appendix

TECHNICAL DESCRIPTION

2. 1 Installation 2.2 Operation 2. 3 Maintenance

PROGRAM PERFORMANCE

TEST PROGRAM

4. 1 Objectives and Procedures 4.2 Special Test Equipment 4. 3 Test Results

CONCLUSIONS AND RECOMMENDATIONS

5. 1 Conclusions 5.2 Recommendations

I. Detailed Test Data

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5

9 9 9

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15 17 19

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SECTION I

INTRODUCTION

The design and deve pment of this bomb fuze initiator was under- taken as part of the development of a proximity fuzing system for general purpose bombs. This fuzing system contains a proximity sensor (MK43 TDD), a fuze, and a bomb fuze initiator. Existing fuzes consi- dered capable of satisfying the requirements of this fuze system, namely, reliable safing and arming and above-ground detonation upon receipt of a signal from a proximity sensor, were those of the U.S. Navy M990 series of electric fuzes and the MK344/376 Electronic Bomb Fuzes.

These fuzes require electrical power to initiate their operation and are not in themselves compatible with the Air Force aircraft/fuze inter- face. A principal factor in the incompatibility was the unavailability of electrical power for the fuze, b an effort to solve this problem, Harry Diamond Laboratories (HDL) investigated the parameters and designed the FZU-24/B Bomb Fuze Ihitiitor.

The report, HDL-TM-70-21, Air Flow at the Centerwell Region of One Low-drag Bomb, dated September 1970, indicated the feasibility of extracting power from the slipstream by means of an air-driven generator installed in the centerwell, or fuze charging well, of general purpose bombs. There are cerUin problems inherent in this approach. These include limited space between the rack and the surface of the bomb, the presence of the suspension lug just forward of the charging well so as to obstruct the airstream, and the relatively high voltage output required. However, initial models of the FZU-24/B initiator were built by HDL and successfully drop tested at Eglin Air Force Base.

Fairchild Camera and Instrument Corporation was among those sub- mitting a proposal for the production engineering/development of the FZU-24/B Bomb Fuze Initiator. The product baseline for the development was the configuration designed and fabricated by Harry Diamond Laboratories.

The baseline device employs an air turbine that rotates the arma- ture of a four-pole generator. The generator output then passes through a transformer and rectifier circuit and finally to a regulator that limits the voltage to 300 VDC. The generator itself is approximately 7/8 inch in diameter by 1 inch long and is manufactured in Norway by Kongsberg V&penfabrlkk. The unit is shown in Figure 1 and a schematic of the electronic circuit is shown in Figure 2. Air is introduced into the turbine cavity through a 0.44.square inch orifice, ducted through the turbine

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ARMING WIRE

AIR INLET

RETAINING NUT AND LOCK SCREW

STANDARD NAVY CONNECTOR AND CABLE TO MK43 TDD

REMOVABLE CAP

TURBINE ALTERNATOR

ASSEMBLY

VOLTAGE DOUBLER

RECTIFIER AND LIMITER

STANDARD NAVY CONNECTOR AND CABLE TOM990E4

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Figure 1. Alternator-type Charging Device

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blades and exhausted downstream from two ports. Turbine velocity is dependent upon bomb speed and angle of attack. The turbine, generator, and electronic package are packaged in a metal container 1.9 inches in diameter by 1.4 inches long. It is sealed against moisture and other contaminants by O-ringo and epoxy sealants. The plastic cap that closes the air intake orifice projects 0.625 inch above the bomb surface when installed in the charging well. :

The contractor response was Proposal No. ORD-CP-84, dated 10 April 1972. This proposal contained five principal features in response to the fuze system and fuze initiator requirements. These were:

(1) Retention of the Kongsberg NVT generator, which is a well-proven, environmentally qualified, high production unit that is available at satisfactory costs and meets the performance requirements of the system.

(Z) Elimination of the voltage rectification and regulation requirement from the FZU-24/B.

(3) Relocation of associated electronics from the FZU-24/B to the fuze as a cost saving and space conserving feature.

(4) Allowing 190 VDC fuze operation, thereby eliminating a transformer from the electronics and reducing costs.

(5) Redesign of the mechanical parts to reduce material cost and assembly time.

The contract for this effort specified an effort that encompassed production engineering of the FZU-24/B Bomb Fuze Initiator through design, fabrication, assembly, tests, and evaluation. The final design of the initiator was designated the FZU-32/B Bomb Fuze Initiator.

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r SECTION II

TECHNICAL DESCPIPTION

• •.

The FZU-32/B Bomb Fuse Initiator is s non-explosive device for generating electrical energy, derived from the airstream, for initiating or charging an electronic bomb fuse. Mechanically, it is capable of being installed in the standard charging well of general purpose bombs. Elec- trically, it is compatible with the FMU-114/B Bomb Fuse. (See Figure 3 for a photograph of the unit, and Figure 4 for a cutaway view.)

The device is cylindrical in shape and is 2 inches long by 2 inches in diameter, excluding the projecting electrical connector shells at one end and the lanyard and attaching hardware fastened to the other end. The top end, where the lanyard is attached, is closed with a tear-off type cover. The lanyard, about 8 inches long, is attached to a bracket that is riveted to the tear portion of the cover. The other end of the lanyard is attached to a swivel-type D-ring that is compatible with bomb rack solenoids.

A decal on the tear-off portion of the cover has "FZU-32/B" lettering for identification and an arrow with the letters "FWD" pointing toward the front of the initiator. The cover is crimped onto the unit housing and cap- tivates a retaining ring that has an external 2-12 UN-3A thread. A No. 6- 32 hexagon socket set screw is used as a locking device for the retainer ring. The ntber end or bottom of the unit has two connectors projecting about 3/8 inch (see Figure 4). These connectors mate with cable connectors, from a fuse, threaded through the plumbing pf the bomb. When snap- ped together, the mated connector pairs fit within the two holes in the bottom of the charging well, thus preventing the device from rotating.

Internally, the FZU-32/B initiator contains a spring-loaded, pop-up air intake scoop under the cover, which deploys when the tear-off portion of the cover is removed. The direction of scoop inlet is coordinated with the decal arrow so that It faces the nose of the bomb when the initiator is properly inetf lied. The air intake scoop is attached to a flow partition that guides the air through the blades of the radial flow turbine 'part of the electric generator). The air is exhausted behind and to the sides of the air intake scoop.

The electric generator U manufactured by A/S Kon^aberg Vapenfabrikk of Norway and is their standard NVT-24 generator Part No. 343349. This is a permanent magnet-type, four-pole, AC generator that operates at an unregulated frequency. It is capable of producing 0. 5 to 1.5 watts, depend- ing upon turbine speed and electrical load.

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AIR INTAKE

TURBINE WHEEL

LANYARD

FLOW PARTITION

GENERATOR

LOWER PLATE

CONNECTORS

Figure 4. FZU-32/B Bomb Fuse Initiator

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There are three connector pins in each of the connector shells. These are wired so that corresponding pins have identical signals on each connector. Thus, power can be delivered to fuzes installed in either the nose or tail fuze wells. (See Figure 5 for the electrical schematic of the unit.) The bottom cavity of the unit between the connector plate and the generator is filled with a semi-flexible, epoxy potting compound. The top of the unit has an O-ring seal between the cover and the housing. The generator is, therefore, fully sealed from the outside environment.

2.1 INSTALLATION

•- The FZU-32/B Bomb Fuze Initiator is positioned so the orientation

arrow is pointing toward the bomb nose. The FZU-32/B is then installed by first attaching the cable end connector from the FMU-114/B Fuze, which is drawn through the bomb plumbing to the charging well, to the appropri- ate connector on the bottom of the initiator. The initiator, with connector mated, is than lowered into the charging well, allowing the cable to retract into the plumbing. The mated connector shells also fit into the internal plumbing when the initiator is completely installed. The retaining ring is screwed tight and locked by tightening a set screw.

When the bomb is installed on the aircraft, the swivel D-ring on the end of the lanyard is inserted into the arming solenoid of the aircraft bomb rack.

2.2 OPERATION

When a normal armed bomb release occurs, the lanyard D-ring assembly is retained by the bomb rack solenoid, thus pulling ihe tear-off top from the cover which allows the air intake scoop to rotate upward into the airstream. The resultant air pressure build-up cauaes the turbine to rotate and drive the generator. This produces an unregulated alternating current output of approximately 46 volts and 2 KHz at a calibrated airspeed of 280 knots into a 3000-ohm load when installed in a MK82 Bomb.

2.3 MAINTENANCE

The FZU-32/B Bomb Fuze Initiator is environmentally sealed until the tear-off cover is opened; therefore, it requires no field maintenance.


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SECTION III

PROGRAM PERFORMANCE

The objectives of thi« program were to develop a design for the bomb fuze initiator which wa. economically producible and would be ccmpatible with the FMU-114/B Fuze, to document the design, build test units, and evaluate the design by environmental and functional performance testing. These objectives were accomplished as described in the following para- graphs.

The first objectives were the generation of development specifications and program plans and making basic design decisions. Generally the design followed the ideas presented in the contractor proposal, ORD-CP- 84, dated 10 April 1972. A design review, which was held at the contractor facility on 1 and 2 August 1972, was attended by representatives of Eglin Air Force Base and Kongsberg, the selected generator manufacturer. During the meeting it was decided that the course of further action should include:

(1) Removal of the transformer from the unit, with the voltage step-up function being relegated to a less expensive quadrupler network (as opposed to the transformer) which is to be located within the fuze. This approach allows for more needed space within the unit. Since the quadrupler is added to an existing board there is an overall cost savings by in- cluding this electronics within the fuze.

(2) Change of the protective cap system to one which was less costly and would not protrude as high above the bomb surface. Accordingly, an inexpensive tear cover approach was selected. Reduction in protrusion directed the use of a pop-up type of air scoop. The scoop design includes sheetmetal parts that are less costly than the baseline system.

Generator characteristics were reviewed, and the decision was made to use the Kongsberg NVT-24 turbine generator. Further, an objective was established to find other means for establishing and controlling a fixed starting airspeed rather than using the locking torque of the generator. The generator manufacturer directed his design so as to obtain maximum power Independent of starting speed. For this application generator operation at low airspeeds Is Inconsistent with safety considerations. At that time It was expected that the unit would operate at low airspeeds. A means of preventing undesirable low speed operations was set aa a

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goal. The study to find such a means (consistent with low cost and high reliability) was not fruitful.

The Viking Thorkom Series connector was selected for use in inter- connecting with other system components. Purchase orders were re- leased for the initial 60 units. Concurrently, the design of assembly tooling and a wind tunnel test fixture was started. (Refer paragraph 4. 2 for the details of this test fixture.)

Eighteen completed units were shipped to Eglin Air Force Base on 2 November 1972, and two additional units were shipped on 22 November 1972. Environmental testing of 28 units was begun at the contractor facility on 27 November 1972. All contractor environmental testing was completed by 5 February 1973. Subsequently, the units were all performance tested in the aerodynamic test fixture. One FZU-32/B failed to function properly. This unit had been subjected to the 5-foot drop test along the generator axis, turbine end down. After the test, the generator could not be turned.

Failure analysis of the item revealed that the generator case had parted along its seams (the assembly is made with snap-fit parts), and this had jammed the rotor and turbine. The original Kongsberg installation for this device employed axial O-ring pressure, which held the generator case under compression. It was planned to employ a similar mounting using a snap-ring as the shoulder against the end of the generator. Unfortunately, the baseline drawing of the generator contained a dimensional error. To correct this discrepancy, it was necessary to re- move the shoulder from the housing. Thus, the generator case was not under compression and the case parted under the shock of the 5-foot drop test.

The design was corrected with a minimum expenditure of time by specifying the use of Eccobond 285 epoxy to reinforce the snap joints of the case.

Based on the results of the environmental and performance testing of the 38 units plus additional engineering evaluation tests, the design of the initiator was modified. Chiefly, the changes were:

(1) Redesign of the air intake and flow partition to improve the airflow.

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(2) Redesign of the housing to reduce fabrication costs and facilitate assembly.

A design review was held at the contractor facility on 28 March 1973. Ap- proval for the design was received on 2 April 1973, and purchase orders for the next 220 units were placed by 25 April 1973.

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Assembly of these units commenced on 4 June 1973. A potential inter- ference between the bottom of the generator and the connectors was en- countered during assembly of the units. This was resolved by adding a 0. 015-inch-thick shim under the connector flange. By Z July 1973, 200 units were delivered to Eglin Air Force Base. Environmental tests were completed on the 20 units retained by the contractor by 9 July 1973.

Copies of the test plan and environmental and performance test re- ports were submitted. This effectively completed the contractor's part in the program except for field test support for Air Force testing of the delivered units and delivery of documentation.

Assistance to Air Force personnel was rendered in the form of performance testing of 51 units, which had been subjected to various M1L- STD environmental tests by personnel at Eglin Air Force Base. A Special Post-Environment Test Report on the FZU-32/B Bomb Fuse Initiator was written on the results. One of the 51 units failed to perform properly. All primary objectives of the program were fulfilled, and the program was successfully completed.

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SECTION IV

TEST PROGRAM

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4. 1 OBJECTIVES AND PROCEDURES

.

A test program was conducted to verify design performance and environmental capabilities of the initiator. In this way, the final design could be established with more confidence. Accordingly, test procedure documentation was generated as described below.

4. 1. 1 Equipment Test Plan (FZU-32/B Initial Design)

The Equipment Test Plan for the FZU-32/B Bomb Fuse Initiator, Fairchild Document No. 564-001, was prepared to delineate the tests to be performed during the development phase of the initiator. Tests for establishing acceptance test levels, life tests, and re liability/environmental demonstration tests were included in this test plan. The Equip- ment Test Plan included details of the following tests to be perforraed:

(1) Test to establish acceptance test levels.

(2) Life tests - 450 KTAS/15 seconds.

4.1.2

(3) Environmental tests per MIL-STD-104 (Procedure 1), 105, 107 (48 hours), 109. Ill, 112, 113, 116, MIL-STD-SlOB, Method 514, Procedure II, curve H of sinosoidal vibration. Method 504, Procedure I and Method 516.

(4) Reliability tests at 250 to 450 KTAS and maximum attainable velocity.

Environmental Test Procedures

Fairchild Document No. 564-003, Environmental Test Procedures for the FZU-32/B Bomb Fuze Initator, was prepared to provide a method for evaluating the ability of the initiator to experience various environments without degradation of functional and/or safety requirements.

4.1.3 Test Plan for FZU-32/B Bomb Fuae Initiator (Final Design)

The Test Plan for the FZU-32/B Bomb Fuae Initiator, Fairchild Document No. 564-004, was prepared in order to provide a method for evaluating the final design of the bomb fuze initiator. This document describes the testing procedures, the test equipment, and the test data accumulation methods

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to be utilized in the environmental testing of the FZU 32/B Th* T.-* Plan xncluded details of the following te.f. to be perLmed; *

(1) MIL.STD.331. Test 104. Tran.portation Vibration.

(2) MIL-STD.331, Five-Foot Drop.

4.2

(3) Temperature cycling: 2 hours at +160'F followed by 2 hours at -65*F.

(4) Performance Test (Post-Environment).

(5) Engineering Evaluation.

SPECIAL TEST EQUIPMENT

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favestigation of the operating characteristics of the wind tunnel test fixture showed that the total or sUgnation pressure was TlwaTverv cloE.

^rhrher^ ^'T *** WhiCh the ** W" ^ ^Ä

where: Ap qc ps Pt po

differential pressure pitot-static impact pressure in tunnel static pressure in tunnel total or stagnation pressure room ambient pressure

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Ap in equal to the impact pressure, qc, the indicated or calibrated airspeed can also be determined from standard tables 1.

While this fixture performed well for all testing done, it must be emphasized that the only control is on the impact pressure. Altitude is essentially programmed by the nature of the equipment and is not subject to independent control. For the range of values (of qc) employed, the tunnel simulated altitudes between 3500 and 5000 feet. For purposes of duplication of results, it is important that the tixture to be used have the same characteristics as the one described herein. Impact pres sure (or Ap) was recorded in centimeters of mercury. (For purposes of cross reference and to indicate the tunnel operating altitude, refer to Table I. ) The values in Table I are based on the assumption that room ambient pressure, po, was standard sea level pressure and that the total stagnation pressure reaches room ambient pressure in all cases. Note that the wind tunnel test fixture can only attain a maximum impact pressure of 23 cm Hg.

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TABL.E I. CHARACTERISTICS OF SPECIAL PURPOSE WIND TUNNEL TEST FIXTURE

CALIBRATED IMPACT TUNNEL AIRSPEED PRESSURE ALTITUDE

(knots) (Cm Hg) (feet)

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6.06 7.25

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2^0 8.56 3250 9.98 3850

300 11.54 4500 320 13.22 5200 350 16.00 6400 400 21.34 8850 450 27.66 12.000 500 35.06 16,150 550 43.67 . 21,800 600 53.66 30,200

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Report No. 837, "Standard Nomenclature for Airspeeds with Tables and Charts for Use in Calculation of Airspeed", William S. Alken Jr., National Advisory Committee for Aeronautics.

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4.3 TEST RESULTS

Fifty-one units from the final lot were subjected to a number of environmental tests at Eglin ' Free Base. Subsequently, these units were

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Thirty-four initiators were subjected to environmental tests in accordance with the Equipment Test Plan, Document No. 564-001, and the Environmental Test Procedures, Document No. 564-003. Upon com- pletion of the environmental tests, the units were performance tested in the special purpose wind tunnel test fixture. The data resulting from these tests are summarized in Appendix I under the heading, "Initial Lot Development Tests. " Fifteen of the units were recapped and submitted to additional environments and then retestf d. The results after recapping did not indicate any significant change in performance. Maxi- mum output tests were conducted without the suspension lug present. The presence of the suspension lug reduces the air flow into the turbine. These recapped units averaged 95.6 volts output at an average airspeed of 400 knots. The starting speed for these tects averaged 240 knots. These same units were subjected to hot and cold temperature tests. The wind tunnel facility was not capable of introducing air at the hot or cold temperature extreme, thus the test items were soaked at the de- sired temperature and as quickly as practical run in the nirr.el with ambient air. The actual temperatures at the time of test were, therefore, either lower on hot units or higher on cold units. The test results at extreme temperatures showed a trend toward slightly higher outputs at cold temperature and lower outputs at hot temperature.

The units performed satisfactorily after all environments except for one failure (S/N 51) as a result of the 5-foot drop test. The cause of this failure and the corrective action taken were discussed in Section in.

After design modifications to correct deficiencies discovered in the first configuration, six units (S/N 1 to 6) from the final group of units fabricated were subjected to engineering evaluation tests in accordance with the Test Plan, Document No. 564-004. The data from these tests are summarized under the general heading "Final Design" (July 1973) in the data sheets included in Appendix I. These data show that satisfactory performance (i. e., output above 0. 5 watt when tied to a 3000-ohm load) under the conditions simulated in the special purpose wind tunnel test fixture begins at speeds of 250 to 270 knots. Thus, a minimum impact pressure of 9. 5 cm Hg in the wind tunnel test fixture should be established as a minimum acceptance test level.

Fourteen units were subjected to environmental tests in accordance with the Test Plan and subsequently subjected to functional testa at 300 knots. The data from these tests are also summarized under "Final Design" in Appendix I. All tr-'.s performed satisfactorily.

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performance tested at the contractor facility in the special purpose wind tunnel test fixture by Air Force and contractor personnel. A summary of the data is included in Appendix I under the heading "Post-Environ- mental Performance, Air Force Applied Environment." One item failed to perform properly after being exposed to MIL-STD-331, Test 105, Temperature Humidity. The item failed to start until approximately 400 knots airflow was achieved and then the output was very erratic. This failure was attributed to an unidentified form of metal contamination that caused corrosion of the magnetic rotor in the generator. This failure was judged to be a random failure and not caused by the environmental test.

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SECTION V

CONCLUSIONS AND RECOMMENDATIONS

5.1 CONCLUSIONS

It is concluded that the FZU-32/B Bomb Fuze Initiator design is a viable approach to the problem of providing power to operate an electronic fuze during bomb free fall. Units built to this design have ade- quately demonstrated ruggedness and reliability. After extensive environmental and performance testing, only two failures of completed units were observed. The cause of one was corrected in the design, and the cause of the other (some form of random material contamina,ion) is cor- rectable through stricter quality control. Thus, it is felt that the contrac tual requirements for safety, reliability, and physical and functional compatibility have been met. Specifically, the FZU-32/B initiator is a satisfactory means for supplying the electrical energy required by the FMU-114/B Bomb Fuze.

Another prime objective of the contractual requirements for the FZU- 32/B initiator specified the preparation of a cost analysis. This analysis, which is presented in Tables II and III, projects a unit production cost for quantities of 10,000, 30,000 and 50,000 units, with fabrication, inspection and assembly conducted on a one shift, 8-hour day, 5 days a week basis.

The costs are based on in-house estimates and vendor quotations and are valid only for the period June to September 1974, Inflationary conditions coupled with raw material cost or availability cannot be reliably estimated. The foreign source generator is also subject to wide varia- tion in costs. The quoted price in 1972 was $6. 75 each in lots of 50, 000. The most recent quotation (1974) is for $9.66 for the same lot size.

5.2 RECOMMENDATIONS

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The following recommendations are applicable to any future development and production programs:

The method of mounting the generator into the housing should be changed to that employed in the later configuration of the initiator fabricated for another contractor. This method presses the turbine end of the generator against an O-ring as in a typical Kongsberg installation and eliminates the necessity to epoxy the generator case together. This also improves assembly efficiency. The unit projects about 0. 025 inch higher above the bomb surface but this is an acceptable amount for the intended use of the FZU- 32/B.

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While it was impractical to employ expensive production tooling for this program because of the small quantity of units involved, the flow partition and lower plate assembly are suitable for high volume production processes by changes in material. The flow partition should be an investment casting. The plate should be a molded plastic part.

The generator is presently procured as a modified version of a standard production item, which normally has reduction gearing in the rear housing. For the initiator application, the gearing is left out but the housing remains. Cost and space advantages should be attainable with a special unit eliminating the rear housing, provided the quantity would justify the cost of retooling.

It is recommended that the acceptance performance requirements for the bomb fuze initiator be based on impact pressure, qc. It is suggested that a single, pre-capping acceptance test be performed on each unit to demonstrate satisfactory performance as indicated in the paragraph that follows.

In a wind tunnel operating with an impact pressure of 10 cm Hg, where the stagnation pressure is approximately equal to sea level pressure and the unit loaded with a 3000-ohm resistive load, the output voltage should be a minimum of 41 VAC and the frequency should be a minimum of 1800 Hz. The wind tunnel configuration must simulate the bomb charging well installation with the lug installed the proper distance forward of the initiator and oriented to permit flow through the eye hole.

II

24

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UNCLASSIFIED

DESIGN AND DEVELOPMENT OF FZU-32/B BOMB FUZE INITIATOR

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Final Report (23 June 1972 to 15 November 1973) ». «uTMoaitifriniaMM, BBER PiSH BSTSS^

John Miazza

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AFATL-TR-74.88

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...O..T«,«»TWN.TAT.-.NT Di8tribution limited to U.S. Government agencies only;this report documents test and evaluation; distribution limitation applied May 1974. Other requests for this document must be referred to the Air Force Armament Laboratory (DLJF). Eglin Air Force Base. Florida 32542.

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•a. •^•MMIHN« MIUTAUT ACTIVITY Air Force Armament Laboratory Air Force Systems Command Eglin Air Force Base. Florida 32542

The primary objective of this program was to develop a cost effective, production engineered FZU-24/B Bomb Fuze Initiator. The initiator is an electric generating device which, when installed in the fuze charging well of general purpose bombs, is capable of deriving energy from the airstream passing the bomb in free fall and converting the energy into electric energy suitable for powering a bomb fuze. The objective was to be accomplished by means of a production engineering effort carried through the evolution of design, fabrication, assembly, test, and evaluation. The baseline for the design was Harry Diamond Laboratories' Drawing No. 11716160. A quantity of 60 units was fabricated and tested, in accordance with the production engineered design. After some additional redesign to correct identified deficiencies, 220 units were fabricated. These units were subjected to environmental, wind tunnel, and flight testing and performance requirements were met. The final unit design was designated the FZU-32/B Bomb Fuze Initiator.

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FZU-32/B Bomb Fuze InitUtor General Purpose Bombs FZU-24/B Bomb Fuze Initiator MK344 Electronic Bomb Fuze MK376 Electronic Bomb Fuze FMU-114/B Bomb Fuze General Purpose Bomb Proximity

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