JUNE 1957 Classification cancella~r~w .. 2 ... ,~~ By authority of ... .. ....... . ...... ... ................... ....... fb!f?.2. ...... . Date ARMAMENT .SYST.E~ Signature .... . REPORT .Noi 77/SYSTEMS"26/ 8·~ Unit/ Rank/ Appo inlmrnt ......... ... ..................... .. ~ ENGINEERING DIVISION Class ification cance lled / Chang~d to ~ .v~ By authority of l?r1f_C!-.5 ... • .. .. . Date ---~ "Q$ ....... · ........ . Signature .... ..... ... ~~ .. • ....... • • .. . .. ~ ........ . '.lr:il /Ha nk/ AppLi:i:m~;;t ... . -/nltf?SS.. .. .. .. SECURI TY WARNING AN"'T y-r This document is classified '~T" and is intended solely for the use of t he re c ipient and such per sons as have been delegated to use it in the course of thei r duty and may only be used in connection with work per fo rmed for or o n b e half of Her M a jesty ' s Canadian Government . The unauthorize d retention or destruction of this document or disclo sure of it s contents to a ny unauthorized person 1s forbidden . F ailur e to comply w ith any of the above inst ructions is an infraction of the Offic ial Secrets Act . A n y u:, a uthori z ed per s on obtaining possession of this do c ument , by finding or otherwi s e , m us t for ward it , together with his name and address , in a reg1s tere d e n ve l ope , to the En gineering Division AVRO Aircraft Ltd . Malton , Ontario Canada . This i s copy number Iss ued to Dat e NRC-C l•TI AERO/ M. E. LIBRARY 89:- OS- 1 2 BIBLIOTHEQUE AERO / G.M. CNRC - ICI.ST P ara. 3. 15 P ara. 3. 18 Para. 5. 1 ERRATA SHEET Armament System D e l e te all a fter " - at a later stage. " Mi ss ile Malfunction Indicator R e place existing sentence with - - "This indicator will s how when a missile has failed to fire a fter it h as rece ive d a firing pulse. " R e pla ce - " and Missile Malfunction indicator s " wi t h "indicator ". ARROW 2 ARMAMENT SYSTEM REPORT NO. 72/ SYSTEMS 26/ 8 JUNE 1957 This brochure is intended to provide an accur ate description of the system(s) or service(s) for purpose s of the Arrow 2 Mock-up Confer ence, and is not to be considered binding with respect to changes which may occur subsequent to the date of publication. COMPILED BY i t ~ APPROVED BY 4~ R. 3~ ENGINEERING DIVISION AVRO AIRCRAFT LIMITED MALTON ONTARIO FOREWORD On an aircraft there a re many aspects of the des ign which, after ade - quate preliminary work, can be firmly specified and described with little chance that later d evelopment work will r e sult in any change . It is the exp e rience of A vro Airc raft L imited, that armament installa - tions ~o not fall into thi s c ategory . An armament installation evolves through out the various stages of preliminary design , analysis , detail design , ground test and flight test. The Sparrow 2D installation is c urrently between the detail design and ground test phases of its evolution. This brochure describes the installation as it c urrently appears . Late r work will result in changes which cannot presently be for e seen . No de c isions, whi ch would render the making of these changes moredifficult,should be made on th e basis of the con- tents of this brochure . SECTION 1.0 2 0 3.0 Introduction TABLE OF C O N TEN TS TIT LE The Sparrow 2D Missile General Description of the Installation 3 . 1 Missile Configurat ion 3 . 2 Attack Modes 3 . 3 Operating Envelope 3. 4 The Pack Concept 3. 5 Pack Structure 3 . 6 Extension Mechanism 3. 7 Launcher 3. 8 Wing and Fin Doors 3 . 9 Drag Link Doors 3 . 10 Hydraulic Systems 3 . 11 Electrical Power Supplies 3 . 12 Ele ctrical Control Circuits 3 . 13 Missile Auxiliaries 3. 14 Cooling P AGE 1 2 3 3 3 4 5 6 6 7 8 9 9 10 1 1 1 1 12 3 . 15 P rotection of Exposed Portions of the M issi l e 12 3 . 16 Sealing 3 . 17 Services C onnections to P ack 3 . 18 Cockpit Con t r ols and Indicators 3 . 19 Missile Preparat ion for Firing 13 13 15 16 SECTION 3 . 0 (Cont'd) 4 . 0 5 . 0 6 . 0 TAB LE OF CONTENTS (Cont'd) TITLE 3 . 20 Missile Jettisoning 3 . 21 Installation Weight Missile Launch 4 . 1 Salvo Type 4 . 2 Salvo Effectiveness 4 . 3 Missile Firing Order 4 . 4 Firing Circuit Flight Operation of the Installation 5 . 1 Lead Fur suit Mode 5 . 2 Lead Collision Mode 5 . 3 Optical Mode Servicing and Ground Handling 6 . 1 Dolly Hoist 6 . 2 Lifting Wire Attachments 6 . 3 Changing a Pack 6 . 4 Hydraulic System 6 5 Pack Inte rchangeability 6 . 6 Rear Attachment 6 . 7 Forward Attachment 6 . 8 Firing Circuit Safety 6 . 9 Pack Servicing 6 . 10 Rearming on the Aircraft SECRET P A GE 17 18 20 20 20 21 21 23 23 24 24 25 25 25 25 27 27 28 29 29 30 30 ii TABLE OF CONTENTS (Cont'd) SECTION TITLE PAGE 7 . 0 The Development Program 31 7 . 1 Design Confirmation Tests 31 7 . 1. 1 Pack Seal Test 31 7 . 1. 2 Mechanism Wear T e st 31 7 . 1. 3 Launcher Rail Test 31 7 . 1. 4 Electrical Breadboard 31 7 . 1. 5 Door Test Rig 32 7 . 1. 6 Single Missile Test Rig 32 7 . 1. 7 Mock-Up 32 7 . 2 Missile Launch and Jettison Tests 32 7 . 3 Launch ers 32 7.4 Test Packs 32 7 . 5 Flight Development 33 FIGURE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 LlS T O F ILL US T RATIONS TlT LE The Sparrow 2D Miss ile Missile Configuration Pac k Structure Missile Extens ion M echanism Wing Doors Fin Doors H ydraulic Actuation Single Missile Pack Seals Mis sile Seals Missile Pack Dolly Armament Pack Pac k and Hoist Rear A ttachment Front Attachment SECRET PAGE 35 36 37 38 39 40 41 42 43 44 45 46 47 48 iv ,IY/10 AIIICIIA FT l/MITEO - - --------------------AVRO 1. 0 INTRODUCTION The installa t ion consists of four Sparr ow 2D mi ssile s c arried in a semi - subme r ged pos i tion , (in a q u ickly inte r changeable pac k ), unde r the centr e fu selage of th e ai r c r a f t. T he m i ssiles a r e m ounted on launching rails , w i c h a re extended for fir ing . AYRO AIRCRAFT /IMITEO 2. 0 THE SPARROW 2D MISSILE The Sparrow 2D is a fully active K - band gu.ided missile weighing 430 lbs . pre launch, which is attached to its launcher by a forward button and a r ear pair of hooks (See Fig . 1) . The current model of the missile is not fully compatible with the ARROW 2 in that it was designed for carriage on lowe r performance aircraft . In the design of the missile installation , it has been assumed that the missile will be upgraded to be compatible with the environment it will encounter when c arried on the ARROW . Future development will determine tJ,e optimum compromise between missile modification and aircraft modification to ensure full compatibility . Proposals have been made to the RCAF for these studies to be undertaken . 2 AYNO A/NCNAFT l/MITED 3 . 0 GENERAL DESCRIPTION OF THE INSTALLATION 3, 1 Missile Configuration (Fig . 2) Four Sparrow ZD missiles are carried in a semi-submerged position with their centrelines on the aircraft skin line . This configuration was chosen to give an optimum extension mech anisrn and a practical mounting structure . Adjac e nt missiles are staggered fore and aft such that two missiles are forward of the remaining pair . This configur ation was c aused by restrictions on fuselage width which made it necessary to alternate the wings and fins of adjacent missiles . Missiles are carried with their wings and fins a t 45 degrees to the aircraft skin line . This configuration was chosen t o ensure maximum stiffness of the launching mechanism. On other armament installations it has been found that launching mechanism stiffness is a prerequisite for succe ssful launch . 3. 2 Attack Modes Provision is made to attack with either the two rear missiles or the two forward missiles , or to attack with all four mis siles . Provision is made for either automatic or manual attacks using the full facilities of the fire control sub -sys tem , and for optical attacks. 3 AYRO AIRCRAFT l/MITED 3. 3 Opera ing Envelope The installation is designed to permit carriage of the missiles in the stowed position , at all speeds and accelerations within the flight envelope oft - e aircraft. Lowering and extended carriage of missiles, is permitted at all speeds within t e flight envelope and at normal accelerations between - lg and + 4 g. T is envelope was chosen after investigation had dis losed that considerable weight saving would result from a reduc tion in normal acceleration below t at of which the aircraft is capable. As + 4g might well be exceeded in a breakaway manoeuvre on an actual attack it is intended that any mis - sile whic h has not fired at tl: e end of an attack sequence will be jettisoned automati ally before the normal acceleration exceeds + 4g This automatic jettison feature can be dis - abled for training missions when it can be guaranteed that the operating limits for extended carriage will not be exceeded. For retraction of empty launchers, the system is designed for all speeds and accelerations within the aircraft flight envelope. For retraction of hangf1res on training missions, the system 4 IIY/10 AIIICIIAFT LIMITED is designed to retract at any speed and at normal accelera tions between - 1 and + 2g. Should the acceleration exceed + 2g , but be less than + 4g, the missile will pause in its motion until the acceleration is once again withm limits . 3 . 4 The Weapo n Pack Concept When the basi aircraft configuration was bein g laid down, several different weapons were consider ed for us e with the ai r craft. Each of these weapons r equire d a different carrying structure. In order to finalize the d esign of the fuselage , it was decided that it would b e designed to accom modate an armament pack . All flight induced loads would be carried b y the fuselage and the pack structure would carry only the loads induced by the armament itself In this way , changes of weapon could take place with out seriously changing the basic aircraft. It was determined that requirements for c leaning , checking circuits, and indiv idual loading of missiles resulted in the specified r earmin g period b eing exceeded. It was decided that to meet the requirement s, rearming should be carried out by pack inte rchange. T he pack was therefore designed as a r a pidly interchangeable item. An incidental advan- tage accruing from this decision is that armamen t instal lation unserviceability no longer means a ircraft uns e r v ice ability as a serviceable pack can be rapidly installed in place 5 JYl/il J/1/CIIAFT 1/MITED - - -------------------AV RO ARROW of an unserviceable one . 3 . 5 Pack Structure The pack structure c onsists of longitudinal and transverse members as shown in Fig . 3. The pack is attached to the fuselage at its four corners by bomb release type attach ments . Vertical loads are taken out by all four attach ments . For e and aft loads are taken out by the rear attachments only. Side loads are taken out on one front attachment and one rear attachment . These attachments have been designed such that true interchangeability will be attained . 3 . 6 Extension Mechanism The missiles are mounted on rail type launchers w h ich must be extended to the firing position . It is a requirement that all four .missiles shall be extended for launch at the same time . Because of the proximity of the wings and fins of adjacent missiles, the rear pair of missiles are extended further than the forward pair of missiles as shown in Fig. 2 . In this way, any missile can be launched without fouling any other missile . A twin jack with drag link mechanism was adopted after investigation had clearly shown its superiority over other mechanisms . This mechanism is shown in Fig . 4 T he AYIID A/I/Cl/AFT LIMITED two jacks are synchronized and regulate ve rtical distance below the skin line, while t e drag link, which is a rigid member, regulates fore and aft position . In order to minimize the period in which the launche rs are extended, the extension t ime was also minimized consistent with availability of power and missile strength . T e selec t e d extension time is 1 . 25 seconds . Considerations of mini.mum weight and prac t icability resul ted in the choice of the utility hydraulic system as the source of power for the extension system . In the course of th e design, it was determined that small diameter hydrau lic jacks would satisfactorily take out end loads . After furth er investigation, these jacks were housed in telescopic structural members designed to take out lateral loads . Missiles are held in the launch position by hydraulic pres sure . Missiles are held rn the retracted position by hydrau lic pressure and by a hydraulically actuated up - lock . 3 7 Launcher After launch, the gap in the skin previously occupied by the missile is filled by retrac ting the launcher part way . The launcher itself is of the same planform as the missile, and the refore seals the gap. 7 AYl/1 AIICIAFT l/M/TEO - ----------------------A The Sparrow 2D is rail launched . The c aptive t ravel in the ARROW installation h as been m ad e a s long as possible (60 inches) in order to per:mit firing of one missile a djacent to another without encountering trouble due to wing and fin collisions. The missile may be jettisoned from the launcher by dropping The portions of the rail on which the missile rests in its pre launch posi ion are attached to the launche r by explos - ive bolts . The missile is prevented from moving forward by a hook which is held in position by a shear pin. T his pin will break when the thrust of the missile ·motor builds u p to 30 0 0 lbs (7g) 3. 8 Wing and Fin Doors In order. to extend the missile for launch, it is necessary to open doors to permit the wings and fins t o pass through the skin line Multi-ele:ment sliding doors were adopted. These doors are hydraulically actuated and run on rolle r s in tracks as shown in Figs 5 and 6. Each pai r. of wing o r fin doors, which open or close in approximately 0 . 35 seconds, is actuated by a hydraulic jack. T he doors are opened fo r missile exten s ion and closed during firing They a re reopene d during launcher r etraction a nd clo s e d when the launcher has been r etra cted . 8 AV/10 AI/ICIIAFT IIMITEQ 3 . 9 Drag Link Doors 3. 10 In the case of a forward missile, the drag link swings in an arc such that is passes through the gap left by the missile body in the pack skin line . In the case of a rear missile, the drag link passes through the skin line ahead of the body gap . Ahead of each rear missile there is provided a pair of short chord, hinged, inwardly opening doors actuated by a single jack . These doors are opened prior to missile extension and closed after launcher retraction . Hydraulic System All actuation is hydraulic . Oil is supplied through quick disconnect fittings, at the rear of the pack, from the utility hydraulic system . This system contains two 20 gpm pumps deliv ering oil at 4,000 psi. This supply is us ed directly in the pack, no accumulators being provided. Electrically controlled valves are used throughout, sequenced by her metically sealed micro switches . Aerodynamic and inertia loading on the missiles is such that, under almost all conditions, the forward extension jack is in compression while the rear jack is in tension. On the rare occasions when one or both of these loads are reversed, the magnitude of the r eversal is small. This 9 ___ , _r _R_o_,_i_R_c_R_A_F_r_1_1_M_1_r_E_o ___________________ A V R O 3 . 11 peculiarity of loading has enabled the adoption of a variant of the Exacter control for missile extension and retraction. For extension , oil from the pump is delivered to the head end of the rear jack, causing oil to be expelled from the annular end of the rear jack . This oil is piped to the head end of the forward jack . The annular volume of the rear jack matches the head v olume of the forward jack, hence, these two jacks move in synchronism . At the end of each stroke, the 11 series 11 hook-up is changed to a parallel one, and pump pressure is applied directly to each jack. A diagram of the hydraulic actuation of a single missile linkage is shown in Fig. 7. On the ground, w ith the engines stopped, hydraulic power for door and missile actuation will be obtained by connecting a ground hydraulic supply into the normal utility system ground connections . Electrical Power Supplies Electric power for control of door operation and missile extension comes from the emergency DC bus, which is energized at all times except when the aircraft is on the ground with engines stopped and ground power supply dis connected. Electric power for missile jettisoning also comes from the 10 3 . 12 3 . 13 emergency DC bus but is fed through an interlock so that power will not reach the explosive bolts unless weight is off the nose undercarriage leg. Electric power for missile firing comes from the main DC bus and is fed through an interlock so that power cannot reach the firing circuit until all undercarriage legs are up and doors are closed . Electric power for missile preparation comes from the main buses which are energized whenever the engines are running or the ground supply is plugged in . Electrical Control Circuits The relay network associated with door opening and closing and missile extension, and the network associated with missile firing and jettison are located at the forward end of the pack between the two inboard missiles . Missile Auxiliaries The missile auxiliaries associated with the preparation of the missiles for launch are located at the forward end of the pack, in the bays between the inboard and outboard missiles . It is intended that the auxiliaries will stay with the pack and that, when a new pack is installed, its auxiliar ies will not require any additional adjustment . 11 JYRO JIRCRJFT IIMITED 3 . 14 3 . 15 Cooling Discharge air from the cockpit is used for "area cooling" of the pack . Air from the equipment cooling supply of the air conditioning system is used to cool the missile auxiliaries . When the pack is installed in the aircraft, these two supplies are automatically connected . The cockpit discharge air enters a gallery pipe running athwartships at the forward end of the pack. Outlets are provided into each missile bay, and the air is exhausted to atmosphere at the rear end of each bay. This air will maintain the general temperature level in the pack between 0°F and 130°F . Cooling air will be piped direct to the missile auxiliaries, and will be exhausted to atmosphere directly from the bays in which they are located . Protection of Exposed Portions of the Missile Although it is known that the present model of the m is sile will not withstand carriage at M = 2 . 0 for the full period of which the aircraft is capable, no attempt has yet been made to protect the missil e from external temperature . This will b e done, if necessary , at a later stage . It is necessary , ho.weve r, to protect missile radomes from 12 AYII D Ail/Cl/AFT LIMITED L - ~ :__------------------AV RO ARR 3 . 16 3. 17 stones, slush etc . thrown up by the aircraft nosewheel and from the effects of rain erosion in flight. This is accom plished by fitting fibreglass fairings over the radomes, which will blow clear on missile extension . A rear fairing, to reduce drag, is fitted to each missile . This fairing will also blow clear on missile extension . Sealing Particular attention has been paid to ensuring good sealing between the pack and the fuselage, and between the missiles and the pack. Considerable relative motion can take place between the pack and the fuselage . Sealing along the edges of the pack is accomplished as shown in Fig . 8. The seals are inflated when the access door to the firing circuit safety disconnect is closed and deflated when the door is opened. Due to the large tolerances on the missile, the special seal shown in Fig. 9 was de signed . This seal runs the entire length of the missile, except around the radome . Seals around the radome and along the transverse edges of doors are not yet fully designed . Schemes exist which must be developed on the test rigs prior to design being commiUed . Services Connections to Pack The following services connect into the pack: (a) hydraulic oil supply and return -~. ~If, !tET AYIIII Al!ICIIAFT LIMITED ~ _ _:_.. __________________ AV RO ARROW ..,,,,,,--- (b) cooling air (cockpit discharge and equipment cooling) (c) pressure air for seal inflation (d) electric power supplies . (e ) inputs from fire control sub -system circuits The hydraulic oil supply and return connections are of the quick disconnect type which are manually connected and disconnected. They are mounted on universal joint type swive ls and are manually positioned for mating . Access is through a hinged door at the rear of the pack on the star board side. The door is held closed by quick release fasteners . Cooling air supplies enter the pack through the roof. The connections are automatically made as the pack is installed in the aircraft, and are of the spring loaded butting type. Pressure air, electric power and fire control circuits enter the pack at the forward end, through a hole in the roof. A cce ss to make and break the connections, is through a hinged door equipped with quick release fasteners, on the underside of the pack. The pressure air connection is of the quick release type . Both electric power and fire con trol wiring are in the same large connector which is man- ually inserted . 14 3 . 18 Cockpit Controls and Indicators The following cockpit controls and indicators are provided: ( 1) On the armament control panel, which is located on the pilot's starboard console: (a) A safe-arm switch - No power is applied to the firing circuits or to the missiles when this switch is in the SAFE position . {b) A first pass selector switch - This switch is labelled FRONT-REAR - ALL . In the event of a first pass being made with only two missiles, the switch is rendered inoperative after these two missiles are fired . The remaining two missiles are then available for a second pass regardless of whether or not the switch is positioned . (c) A mode selector switch - This switch is labelled VISUAL IDENT - LEAD PURSUIT - LEAD COL- LISION - SNAP UP. {d) An extend - retract switch - This switch is of the momentary contact type and is provided to extend mi s siles for optical attacks, and to retract hang- fires on training missions . (2) On the master warning panel : A hangfire light is pro vided on the master warning panel. This light is intended to advise the pilot of hangfires . The light will 15 1 sec11.e:J - ~ :___-----------------AV RD ARR D W JY /11 JI/IC/IJfT LIMITED ► 3 . 19 come on when the missiles start to extend, and will go off when the missiles leave the launchers. (3) On the main panel : (a) A missile ready indicator . This indicator will show when one or more of the selected missiles are locked on to the target. (b) A missile malfunction indicator . This indicator will show when one or more of the selected mis- siles are not locked on . (c) A stores jettison switch . This switch is used to jettison the external tank or missiles . ( 4) On the control column - A trigger is provided on the control column . This trigger enables firing pulses to reach the selected missiles . Missile Preparation for Firing Missiles can be carried on the aircraft in four conditions : ( 1) OFF - In this condition, now power is applied to the missile . Missiles will normally be carried in this con- dition until an attack is committed . (2) Condition 1 - In this condition, the missile is readied for extension and immediate lock on . The current minimum time for condition 1 is 2 minutes . During this period : power is applied to the missile, the tur bine motor is synchronized with aircraft power, the 16 _ _::..~-----------------AV RO ARROW JY/8 1/ICIIAff LIMITED ► 3 . 20 antenna gyro is run up, the glow plug is energized, the thyratron filament is switched on, and the antenna is angle slaved . When condition 1 is complete, the missile is ready for extension to the firing position . The time spent in condition 1 will be ekpt to a minimum to avoid missile overheating. (3 ) Condition 2 - This condition is initiated when the mis sile is extended half way to the firing position . In this condition, the missile is transmitting, the range gates are slaved, and the missile achieves lock . ( 4) Condition 3 - - This condition is initiated by a firing pulse from the intervalome ter . The condition lasts while gyros are uncaged, and the missile is transferred to internal power . When this sequence is complete , a control r e lay is automatically closed to apply power to the igniter , Missile Jettisoning A missile can be jettisoned by exploding bolts in the launcher which will disconnect the portions of launcher track to which the missile is attached and allow it to drop . Wind tunne l tests have been carried out to establish jettison ing techniques. In an emer gency, when it is desired to jettison all four missiles from the stowed position, the 17 u ~Cl [Jt~ \~_f ~~ r.: iJECRET _ _ _:':_:Y_:ll.:,D_:_':.._'_11 _,11_A_F_r_u_M_1_r_E_o __________________ A V R'O A::::•► 3 . 21 stores jettison control in the cockpit is actuated ,.,the doors will open and all four missiles will extend to the firing position. The explosive bolts in the rear launchers (lower missiles) will be exploded simultaneously. As soon as the missiles are clear, the rear launchers will retract in order to give the forward missiles a clear jettisoning path . As soon as the rear launchers are clear, the forward missiles will be jettisoned in a similar fashion to the rear missiles . The forward launchers will then retract. Following a two-missile attack, on which one missile fails to fire, the hangfire will be automatically jettisoned, and the empty launchers will be retracted . Following a four-missile attack on which one missile fails to fire, it will be automatically jettisoned . If the hangfire is on a rear launcher, it will be jettisoned forthwith, and all four launchers will be retracted . If the hangfire is on a forward launcher, the rear launchers will be retracted suf- ficiently to give the hangfire a clear jettisoning path, and it will then be jettisoned, followed by retraction of the remain- ing launchers. Installation Weight An armament pack complete with four Sparrow 2D missiles 18 U~~CL ·.~ !~ ~ -...'.'~Y::_R:_Q .:':.:' 11:...:c __ ,_,_,_, _,_, M_I ,_E_o _________________ A VD O A D D O ;, r is expected to weigh 3726 lbs . as follo w s: Structure Hydraulics Mechanisms Ele ctric al Missile auxiliaries Missiles This weight is broken down Total 875 lbs 332 lbs 583 lbs 64 lbs 143 lbs 1, 728 lbs 3, 726 lbs 19 4. O MISSILE LAUNCH 4 . 1 Salvo Type When guidance cuts in , shortly after launch , the Sparrow ZD has a tendency to go into a considerable manoeuvre . In order to minimize the risk of mid-air collisions, missiles are fired in train . To maximize the effectiveness of a salvo, th e interval b e tween missile s should be kept to a minimum. One - half second has been chosen as the interval. 4 . Z Salv o Effectiveness Within its design envelope, the Sparrow ZD can be fired, with roughtly constant effectiveness, from a c ertain volume of space . Outside this volume , missile effectiveness falls off sharply . At the higher altitudes and against higher perform ance targets, this volume shrinks . Placement problems may r e sult in the interceptor cutting across a corne r of such a v olume . In order to maximize effectiveness , a salvo should be conc entrated into the minimum period of time possible. For this reason, a 4 x 4 system has been adopted . In the 4 x 4 system, angle and range slav ing of all four mis s iles is done simultaneously All four missiles ar e extended simultaneously at the beginning of the attack . All four mis siles can, therefore, be fired at half second intervals. Information available to AVRO indicates that a serviceable zo !__::.:..:__-----------------AV RO ARROW AYIP Af/1&/IAFT LIMITED ► mis s ile w ith s e r viceable auxiliar ies, and within mis s ile radar range, will lock on t o a target within one half secon d of sighting it. Any missile, which has not locked on to a target in a per i od slightly greater than one half second, will probably never achieve lock becausE: it is itself unservice able, or because its associated equipment is unserviceable . If not fired as a rocket , the missile becomes a hangfire , and will ultimately be jettisoned. The firing circuit should not, therefore, lose any time waiting for missiles to lock, but should, after a reasonable period, fire the missiles . 4 . 3 Missile Firing Ord er The installation is des i gn ed so that missiles may be launched in any order . 4 . 4 Firing Circuit One half second after the first missile achieves lock, an intervalometer will start generating firing pulses . These pulses will be routed to each missile in turn and in a fixed order . If, at the time of receiving a firing pulse, a mis sile has achieved lock, it will fire . If the missile has not achieved lock, it will remain on its launcher . The inter valometer will continue to generate pulses until the aircraft has closed to a range at which it is apparent that there is little hope of any of the remaining missiles achieving lock . At this time an override will be operated which will route 21 AYK D A/fi&/ilFT JIM/TED _ _:_:_~-----------------AV RD ARROW future pulses to the motor ignitors, bypassing the interlocks within the hangfire missile(s) , In the unlikely event that a hangfire remains after this operation, it will be automatic ally jettisoned . Since information on the variation in lock on rang e between individual missiles is not yet available, the circuit design can not be finalized . When this information is available, the design will be in accordance with the foregoing philosophy . 22 AYl8 JIICIAFT l/MITED 5. 0 FLIGHT OPERATION OF THE INSTALLATION Missiles are kept in the OFF condition until entering the combat area . On selecting ARM on the safe-arm switch, power will be applied to the missiles which have been selected on the first pass selector switch, and the firing circuit will be readied. Note that the present minimum time between applying power to the missiles and firing them is two minutes . An attempt will be made to develop a method of switching on the missiles automatically in a later por tion of design program . The pilot will then select the desired attack mode . 5. l Lead Pursuit Mode Two seconds before entering the firing area, the selected missiles will be extended to the launch position . Half way to the extended position, the missiles will be put into Condition 2 . From knowledge of the attack situation as displayed on the scope and guide d by the missile ready and missile mal function indicators , the pilot can judge the most opportune time to fire . When he decides that this moment has arrived, he will press his trigger and the selected missiles will be fir ed at half second intervals. After all the missiles have left, the launchers will be automatically retracted until they are flush with the skin line. In the unlikely event of hang fires being present, they will be automatically jettisoned. On training missions, in the event of hangfires, all launchers will remain extended until the pilot selects retract. 23 _ _ _:A:_:fl~8-' __ 1 _ 1 _''-'-'-'-'-'_M_,_r_E 9 ------------------ A V RO ARR O W 5. 2 Load Collision Mode The difference between the lead pursuit mode and the lead collision mode, in addition to the type of course flown, is that the fire control sub-system will select the moment of firing. Pilot action will be the same as in the lead pursuit mode, except that he will depress the trigger prior to enter ing the firing zone. Firing will be initiated by the fire con trol sub-system,however, the attack can be aborted by releasing the trigger. Otherwise the lead collision attack sequence is identical to the lead pursuit attack. 5. 3 Optical Mode When the pilot wishes to make an optical attack, selection of OPTICAL on the mode selector switch will slave the antenna of the selected m i ssiles straight ahead. To extend the m i ssiles for launch, the pilot must select EXTEND on the extend-retract switch. Half way to the extended position the missiles will be put into Condition 2, when the range gates will be swept over a wide range . From this point on, the attack will proceed as in the lead pursuit mode. 24 _ __:_':r''.:.'.''....'::',:':_c::..1"::..:F_r_,_1_M_1_,_,_u __________________ A 6. o SERVICING AND GROUND HANDLING As previously described, the pack was desgined for easy removal and replacement with the objective of rearming by interchange of packs . C arefu l at t ention has, the r efo re, ,been paid to the design of the pack attachments . The pack is installed in the aircraft, remove d from the aircraft, and transported on a combined dolly/hoi st. 6. 1 Dolly Hoist (Fig . 10) The combined dolly/ hoist is equipped with four d ouble tire pneumatic wheels, and can be towed either forward or side ways . For hoisting the pack, there are four lifting wires which attach to the aircraft. These lifting wires are pneumatically extended and retracted by controls on the dolly. Pneumatic power is cont aine d in bottles, which are a part of the dolly, and sufficient air is stored for six raisings and lowerings, before recharging is necessary. 6 , 2 Lifting Wire Attachments 6. 3 Lifting wires are attached to the aircraft by hooking fittings over retractable lugs on the sides of the fuselage . These lugs are spring loaded to extend and are locked and unl ocked by a half turn with a screwdriver (or a coin) . Changing a Pack (Figs. 11 and 12) To change a pack an empty dolly is wheeled underneath the aircraft, and the lifting wires are attached to the fuselage . JY/6 Af/1&//Aff LIMITED _.:;.:_~----------------A By operation of the hoist controls, the dolly is lifted until it is firmly up against the package . While the dolly is being lifted the hydraulic connections at the rear of the pack, and the electrical and air connections at the forward end of the pack are broken . The pack attachments to the fuselage are then unlocked. The hoist controls can next be manipulated to lower the pack and dolly . When the dolly wheels are firnly on the ground, the lifting wires are disconnected from the aircraft and the pack and dolly can be towed away. The dolly, with the replacement pack, can then be wheeled under the aircraft and the lifting wires attached . By opera tion of the hois t controls, the pack can then be lifted verti cally into the armament bay . Guide rails, on the rear pack attachment, mate with rollers on the aircraft part of the rear attachment. If the pack has been correctly placed on the dolly, the guide rails will mate with the rollers automatically. If however, the pack has not been correctly placed on the dolly it will be necessary to manhandle it to get the guide rails to engage . Retractable handling bars are provided at the rear of the pack. Once the rails are engaged in the rollers, hoisting can continue and all four attachments will mate automatically . The attachUJ.ents are then locked and the dolly can be lowered to the ground. During dolly lowering, the hydraulic, electrical and air connections can be made and 26 w~ Pl~ 9 - -~AY~J::_Q~,l~/ l/:C::.:/1:..:,l~f.:..'...:1.:..':...M_I_TE_D __________________ A V R O A R )f O W J the access doors to them closed. When the dolly is on the ground, the lifting wires are disconnected and the aircraft lugs locked in the retracted position . The dolly can then be wheeled away. Trials with mock-up packs have resulted in pack inter change times of less than 3½ minutes . 6. 4 Hydraulic System 6. 5 When the pack is removed from the aircraft, changes of temperature will result in changes in the volume of the oil in the hydraulic system. A relief valve is fitted such that pres - sure can be relieved in the event of a temperature rise. A drop in temperature will result in cavitati on . It is not anticipated that cavitation will cause any problems . If, however, cavitation shoul d later prove to be a problem, a reservoir which would be a piece of ground equipment, would be required. This reser voir would mount on top of the pack and connect into the hydraulic system at the connections at the rear of the pack. Pack Interchangeability In the design of the installation, particular attention was paid to pack interchangeability. The rear pack attachments mate with fixe d fittings on the aft bulkhead of the armament bay. One of these fittings takes load in all three planes, and is, 27 Ur Cl~~ 1 AY60 At 8CRAFT l/M/TEO AV RO ARR Ow therefore , a snug fit'. On installing a pack, engagement of the guide rail will ensure correct mating. The other rear fitting takes only vertical and fore and aft loads . There is adequate lateral clearance in this fitting to allow for toler ~ ances and temperature changes. The forward pack attachments mate with s winging link attachments in the aircraft. The swinging links are spring - loaded to their theoretically correct position . The pack attachments contain leads which wil l engage with the links, as the pack is being offere d up, and which will guide the links into the forward attachments . 6. 6 Rear Attachments These attachments are of the bomb release type . They are manually actuated both to close and open. To unlock, a screwdriver is inserted- in the locking bar and pushed hard home to remove the detent from the hook attachment. The screwdriver is then turned to unlock the hook. To lock the attachment, the screwdriver is inserted in the locking bar and turned . This will lock the ho ok . When the bar has been fully turned , the screwdriver should be removed, and the bar will spring out until one end is flush with the skin line . When the end of the bar is flush with the skin, the hook detent is fully home and the attachment is secure. 28 _ _ _:'.:_r,:_:D:__'_' 11_c_11_-'_'_'_'_'_M_,_r_E_o ___________________ A V R D - ;; ct~ OS ECRET ARROW ~ 6. 7 ,Forward Attachments {Fig. 14) These attachments are of the bomb release type . They are manually actuated to close and open . To unlock, the detent is pressed in and the lever pulled . To lock, the lever is pressed in until it engages with the detent . A small tab is attached to the hook which, when flush with the skin line , forms visual evidence that the hook is home. 6. 8 Firing Circuit Safety Towards the rear of the pack, on the port side, there is a hinged panel held closed by two Hartwell latches . When this panel is closed, it depresses a plunger which, through relays, permits electric power to enter the pack. When the door is open the plunger is released, thus removing all power from the pack. That the door is open is evidence to ground personnel that there is no danger of inadvertent actuation of doors or missiles . For door operation and missile exten- sion or r.etraction on the ground, the plunger may be manually depressed . Adjacent t o the plunger are manual extend and retract switches. The access door also gives access to the firing and jettison circuit safety plug. The final link in each missile firing and jettison circuit is led through the safety plug which should be disconnected at all times when the aircraft is on the ground. The plug itself is on a chain, and can hang clear of the 29 _ _ ::..':.:ra:.,:o_, __ ,_,_c_, _,_F_r _,_,_M_,_r_E o ___________________ A V R 0 pack as evidence of fiting and jettison circuit safety. 6. 9 Pack Servicing 6. 10 When it is separated from the aircraft, it is intended that the pack shall be serviced in a stand. This stand would contain replicas of the aircraft pack attachments and lifting wire attachments and would also have hydraulic and electric power supplies. In the stand, the pack coul d be cleaned after firing, inspec ted and functioned. Test boxes to check out the auxiliaries , the actuation circ uitr y and the firing circuitry will be required. Rearming on the Aircraft Although rearming by replacing i ndividual missiles will not meet the t urnround requirements, it is recognized that occasions may arise when it is necessary to rearm on the aircraft. The single m issile hoist , which was designed for use ~ith the CF-100 MK . 6, can be used for loading single missiles on to the pack whil e it is installed in the aircraft. 30 ,, fr RET _ _:.':..:.r_,_o _,_1R_&_R_A_1_r_1_1 M_i_r E_o __________________ A V RO ARR O W ~ 7.0 DEVELOPMENT PROGRAM As stated in the forewo r d, the evoluti on of an armament installation cannot be broken down rigidly into design and test . Right up to the moment that an installation goes into squadron service the design is being continually refined. The means of refining the des i gn is the development program . 7. 1 Design Confirmation Tests Several tests will be carried out in the near future to con- firm design decis i ons . These tests will not be complete before the first pack details have been made , They will however, give the necessary lead time for re - design, should the decisions prove to be unsound. 7 . 1. 1 P ack Seal Test This will be a full scale test of the front pack seal. 7 . 1. 2 Mechanism Wear Te s t This will be a life te s t on the extension mechanism struc- tural telescopic member . 7 . 1. 3 Launcher Rail Te s t This will be a wear test on a launching rail giving sixty inches of captive travel. 7 . 1. 4 Ele ctrical Breadboard This will be a test of the soundness of the design of the actuation and firing circuits. 31 L..-:...':..:0 ~6_ 1_1_11_c_11 ,_,_,_,_,_M_,_,_E_o __________________ A V R O A R R O W 7. 1.5 DoorTestRig This will be a test of the so undness of the design of the sliding wing doors . 7. 1. 6 Single Missile Te s t R i g This will be a test of the extension mechanism of a single ..missile . Si mulated loading will be applied during actuation . 7. 1.7 Mock-Up The mock up pack will be used to check out assumptions made during the design of the pack. 7. 2 Missile Launch and Jettison Tests Wind tunnel tests have a lready been carried out on mis sil e launch and jettison. Further work, yet to be done, consists of interpr e t i ng the results. These results will be used in e stablishing missile tra jectory and in c onfi rming the load ing on the launch mechanis m and that the stiffness, as desi gne d . is satisfactory . 7 . 3 Launchers The launchers, although based on a Douglas Aircraft Company design, are new items. They will be subjected to simulate d firing, actual firing, strength, stiffness, vibration, and environmental tests in addition to jettison tests . 7 • 4 Test Packs Three test packs will be built. The first pack will be used only on the ground. The third pack will be used only in the SECRET t' • . J" --· 32 .,.· !il Ji CRET '---.:,'_:_r:.:1u~A1_1_c_, _,,_,_11_M_1_r_E_o __________________ A VII O A /I II O W ~ air. The second pack will be used for some ground tests prio r to being used in the flight program. The ground program will consist of: - (a) A period in which the servicing and maintenance features can be assessed. {b) a check on the l aunching mechanism stiffness (c) functioning tes ts without simulated loading {d) functioning tests at h i gh and low temperature (e) vibration tests (f) firing tests with simulated aircraft structure ahead of and behind the pack. These tests will combine the ground firing tests, which, on previous similar instal lations, have been carried out on both component and the aircraft. {g) leakage tests on seals (h) structural strength 7. 5 Flight Development Flight development will be carried out on aircraft number 3 after completion of the damping system development. The program will roughly follow this pattern; (a) integrity-missiles retracted (b) integrity- missiles extended (c) integrity-raising and lowering (d) jettison 33 Jfl l lfl(IJIT IIMITE/1 (e) firing- subs onic (f) fir ing-s uper s onic ( g) fi r ing- transonic 34 0 "' 0 <( .... w 0 I ~ "' <( ~ 0 z <( w N ~ z 0 6 w z .... z g 0 0 co u ii: 0 < .... u ::, :a <( a5 -0 ~ M GS ::, M 0: ;': (X) ~ ~ 0 0.. .., 0.. ::, V, "' w ~ 0 0.. "' w u: 6 w "' 0 z <( w u z <( w 0 5 ~ \'.) 0 0 <( "' /8 FIG. l THE SPARROW 2 MISSILE 35 JYII J/ /1&/IIFT I/MITE/I c C C C I --+-- 1 I d] d]~ ~ d] d]~ ~ PLAN VIEW - MISSILES STOWED FRONT ELEVATION • MISSILES EXTENDED ~ ~ ' L I C C FIG. 2 MISSILE CONFIGURATION C C FIG. 2 MISSILE CONFIGURATI ON SECRET AVRO ARROW► ------- SIDE VIEW- MISSILES STOWED SIDE VIEW-MISSILES EXTENDED ---, I I I ' I ----, I I I I ' \ /8 36 JY /1 1/IUAFT JIM /TIii FORWARD ATTACHMENT FIG. 3 PACKAGE STRUCTURE REAR ATTACHMENT GUIDE ------------------------- A VR O ARROW FORWARD ATTACHMl:NT FIG. 3 PACKAGE STRUCTURE REAR ATTACHMENT GUIDE /8 37 AYII All&#A ff IIMITF/1 FORWARD JACK AFT JACK DRAG LINK FORWARD MISSILE II VIEW ON ARROW 'A' FIG. 4 MISSILE EXTENSION MECHANISM AFT JACK FORWARD MISSILE EXTENDED FIG. 4 MISSILE EXTENSION MECHANISM FORWARD MISSILE RETRACTED -- SECTION 8- 8 / 8 38 SECRET •~VN~O~ Al'!._ll:_C:_11:11'...'.T~ Ll~M::..:'.:...' ..:.. 1 .:. O _________________ A V RO ARR O w ► • DOORS OPEN DOORS HALF OPEN • / • DOORS CLOSED '- /8 FIG. 5 MISSILE WING DOORS 39 ,vNO 11 NCRAfT /IMITED FWD JACK DRAG LINK RETRACTED CARRIAGE MISSILE SELECTOR VAL VE COMPENSATING VALVE 14---------AFT JACK --=--1--"C>----~-o _L__ ___ --, ~ LOWERING EXTENDED CARRIAGE FIG. 7 HYDRAULIC ACTUATION - SINGLE MISSILE RETRACTION /8 41 SECRET , ,_:_09__0~11~1:Cl~J~f~f ~//~M'._'.1.:__Tl:_:0:,__ ___________ _____ A V R O A R ,f1 0 w ► (.'.) ..., V, 3 c.. < :E "" 0 z Q V, :::, z i FIG. 8 MISSILE PACKAGE SEALS < w VI w C iii w (!) <( >< u <( c.. (.'.) ..., V, 3 c.. < :E "" 0 z Q V, :::, z i .... < w VI .... z 0 "" ... w (!) <( >< u < g. /8 42 /8 FIG. 10 MISSILE PACK DOLLY 44 Jfll lflfl,IIT l/11/TEJI Q < g ElEORICAt DISCONNECT ACCESS DOOR 0 < g 3 .:: "" w > FORWARD ATTACHMENT ----- ACCESS TO ELECTRICS VISUAL INDICATOR FRONT LATCH RELEASE ACCESS TO HYDRAULIC FILTER FIG. 11 ARMAMENT PACKAGE • ACCESS DOORS n ~r il i.. S t_1;.R ET - - - - -------- ---------- -- A VR O ARROW► VISUAL INDICATOR FRONT LATCH RELEASE ACCESS TO HYDRAULIC FILTER ROUND HANDLING BAR /1~ ACCESS TO HYDRAULIC DISCONNECT ARMAMENT PACKAGE • ACCESS DOORS Cl g j ;:: "' w > REAR ATTACHMENT /8 45 Jrll J!ltlA IT //MJTE/1 -------- HOIST ATTACHMENT POINTS HOIST FIG, 12 ARMAMENT PACKAGE AND HOIST L HOIST CONTROL PANEL SECRET AVRO ARROW► ___________ _____ ____ ____ _______ GROUND LINE --- -- ----- ARMAMENT PACKAGE HOIST -----~---''---________ _ ....:::,,..:..,L ______________ GROUND LINE /8 FIG, 12 ARMAMENT PACKAGE AND HOIST 46

Arrow 2 armament system

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