NAC • C I STI J. H. PARlan °,; r odym:mic chord length = 362.6 inches. '.;e .. t r e " T ~Vit .' is a t .JOJc 4 ,11, Pitching ~foment cue to Eng\ne Thrust The notation and method suggested in report 70/AD/l (section 6) was employed. For PS-13 Engines: k1 = 19.485 - he: 19.485 + ,303 x 30.218 = 28.64 ft, k1 + k2 = 53.71 k2 = 25,07 ft. DATE Se t. ' 8 - DATE • UNCLASSIFIED AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO REPORT NO. _7c..:2:..,,/..::ST:..=..:..:AB~/4:::.L5 _____ _ SHEET NO. TECHNICAL DEPARTMENT PREPARED BY AIRCRAFT: D.L. Martin Aii.RCM 2A CHECKED BY 4 .4 (Cont'd) = 25.07 X .0451 + (9.79 - 8.64) X 1/12 X •9990 = l.lJO + .096 = L226 ft. The static thrust of the engines has been obtained from 72/PCMER/2 Temp Thrust 120"F 40000 lb 770F 44000 lb -65"F 45600 lb Therefore on a standard day (77°F) the pitching moment due to the engine thrust= 44000 x 1226 = 53,944 lb. ft. 4.5 Offset of Booster Thrust Line In order to balance the pitching moment from the aircraft engines at the instant of firing, the rocket booster thrust line will be offset from the combined centre of gravity position. Let the required perpendicular offset be fJ feet. Then for balance of moments 2TR cos 28 fJ = Tgross f2 Where TR is the thrust of one booster rocket and Tgross is the gross thrust of both engines. The rocket thrust, TR, varies with temperature as shown in the table: Temp TR 120°F 143,500 lb 77°F 130,000 lb -65°F 101,500 lb DATE Seot. 1 8 - DATE • · UNCLASSIFIED EK AVNO AIRCRAFT LIM/TEO MALTON - ONTARJO REPORT NO. _ .... 7...=2u.l.,,.ST.....,ABOLJ..:.(4L5.,__ ____ _ SHEET NO. TICHMICAL D!PARTMlMT PREPARED BY AlRCRAl'T: D,L, rtin AR,RCW 2A /-" __ C_H_E_CK_E_D_BY ____ +-_ __::.:..:..:.=-.__ 5,1 (Cont'd) Cm =Cm+ cm ill,, cg q 2v Values of the coefficients CL, Co and Cm were obtained from P/vlr /96, sheets l,lc, 2.5 and 8.1 respectively. The value of C~ was obtained from sheet 1,8.1 of report P / AIJ/98. Equations (1, (2, and (J were used to determine u, w, and e. These gave values for Vanda. a. = tan - 1(;) j 2 2' V = w + u The trajectory was obtained by using the equations s = V cos (e - ~) . h = V sin (e - a) 6, Lateral Response 6,1 Equations of Motion A step by step analysis which is based on the following equations r.a s "~"' e"'!)loyed: v = Y + mpw - mru m P = L + E r A r = N + Ep C The notation is standard and refers to datum line body axes. The terms Er and Ep have been assumed to be n~gligible. (7 (8 (9 (10 (ll (12 (13 Y = mg (i cos 0 + t sine)+ qS(CyQ~ +cyn ~ + Cy rb) .., , 2v r 2v + 6.N (14 • AIRCRAFT: MK AVR0 AIRCRAFT LIM/TEO MALTON - ONTARIO TECHNICAL DEPARTMENT UNCLASSIFIED REPORT No. 22 /srAa /l+s SHEET NO, PREPARED BY ARR.(Jtl 2A CHECKED BY 6.1 (Cont' d) L = qSb (Cl pi3 + Cl ~ + Clr r b) + 61 p + Z'v N = qSb (C~S +C~ 12.Q + Cnr r b) + l'.N 2V 2V The terms mg 1lt sine and qS ( Cyp ~ + Cyr ~~) have been assumed to be negli gi ble, The variation of t he longit udinal terms wi th t ime has been assumed to 'ce tha t obtained for t t e trimmed case, The lateral derivatives have all been taken from P/.AJJ/97, and no allowance was made for t he undercarriage • Equations (11, (12, and (lJ giving the acceleration in v, p, and r were used to determine the responses in v, S, p, and V. The equations ginng the lateral coordinates of the centre of gravity in space are: ,t, = u cos e cost + V (sin p sin e cos t - cos p sin t) + w (cos p sin e cos t - sin p sin t) • I u cos e sin t y = + V (sin p sin e sin t + cos p cos t) +w (cos p sin e sin t sin p cos t) These are simplified to: • I X = u cos e cost • I Y = u cos e sin t + v cos p cost to give t he tra jectory in plan view 7. Misalignments in Longitudinal Plane (Standard Day, 77°F) Variations in t he d irections of the booster rocket, thrust axes, and movement of the aircraft centre of gmvity• allow pitching moments to be produced which cause the trajectory to vary from the optimum path. (15 (16 (17 (18 (19 (20 DATE DATE • AIRCRAFT: MK AVRO AIRCRAFT LIM/TEO MALTON - ONTARIO TECHNICAL • DEPA RTM ENT UNCLASSIFIED REPORT NO. _7~2~/~STc.=AB=-../ ... 4_._5 _____ _ SHEET NO. PREPARED BY D.L. M n ARRO#l 2A CHECKED BY 7.1 Misalignment of the rocket thrust axes by fifteen minutes of arc and a vertical displacement of the e . g. of 1 inch Displacement of the t hrust axis from t he nominal e.g. position is 12 200 . 6f3 = ± 60 x 57 _ 3 = ± .872 inch Pitching Moment=± 2TR (1 + 6ff) 7~s280 cos6° =_±2x 130000 X •\ 2 x .8830 x 9945 = .± 16,600 lb ft. 8. Misalignments in Lateral Plane (Standard Day 77°F) 8.1 Misalignments of rocket booster thrust axes by 0°15 1 to give a yawing moment, + 5% variation of rocket thrusts and e.g. offset in Y direction to give additive yawing moment The care considered is illustrated in figure 3. a= .872 inch b = 10872 cos28° ~ la6,54 inch = -950 - 3050 = -4000 lb 6N = .95 x 2TR l+a cos28° cos6° + .05 x 2TR x l2 cos6° 12 + Tgross x tz = 33800 + 1782 + 3665 = 39,247 lb. ft, 6L = .95 x 2TR i;a cos28° sin6° + ,05 x 2TR ~2 sin6° + Tgross cos¥ x i 2 ~ 3550 + 190 - 165 = 3575 lb. ft. 8.2 Misalignment of rocket booster thrust axes by 0°15 1 to give a rolling moment: 5% increase in rocket thrusts and e.g. offset in Y direction to give additive rolling moment It is assumed that the booster rocket, thrust axes are de flected 0°15 1 in opposite directions in the Z,X plane to give a positive rolling moment, • • • Ll NCLASSIFIED AVR0 AIRCRAFT LIM/TEO MALTON -ONTARIO REPORT NO, -~7'-'2"-'/'-'ST=-=A.,,.B.,./..;,4'-'5'-------- SHEET NO, 10 TECHNICAL DEPARTMENT PREPARED BY AIRCRAFT, D.L. Martin ARRCW 2A CHECKED BY 8.2 (Cont'd) t::,_y = 0 t:J.L = 1.05 x 2TR R sin0°15 1 ·cos6° + 1.05 x 2TR x L cos28° 12 = 2,100 + 8,480 = 10 1 ~80 lb. ft. t:J.N 1 cos28° cos6° = 20 1 000 lb. ft. = 1.05 x 2TR x 12 Where R is distance between booster rocket nozzle and aircraft datum, measured in the Y direction. Conclusions sin6° The initial 5 seconds of flight of the zero length launch has been investigated'-unde? standard conditions: with various misalignments. and at extreme temperature conditions. The results indicate that the maxi~um acceptable tolerences of e .g. positions and rocket motor thrust misalignment should be as follows: Aircraft e.g. Longitudinal Lateral Vertical .:t Sf, M.A.C. .:t 1 inch .:t l inch Rocket nozzle misalignment: 15 minutes of arc. Assuming that no corrective action is initiated by the pilot prior tot= 3 sees (approx V = 160 knots) then , at standard temperature conditions, the above tolerences will produce the following flight envelope : at t = 3 sees Height above ground 53 ft< h < 120 ft Angle of pitch +80 <;. e < +38° Angle of incidence +20 <.. a. <. +16° Flight path angle +50 " 'I<. +23° 'v. Pitch rate q < .:t 100/sec Normal acceleration +.3 <. ll <: 1.4 Longitudinal acceleration 0 "- llx< 3.2 Sideslip angle ~ < ±. 70 Bank angle J ( ±. 19° ev. Roll rate p <. ±. 15°/sec Yaw rate r ( .:t 10°/sec Lateral acceleration lly < ±. .8 • • UNCLASSIFIED AIRCRAFT: >iK AVRO AIRCRAFT UM/TEO MALTON - ONTARIO TECHNICAL DEPARTMENT ARROW 2A 9. (Cont'd) REPORT NO • ....,7-=2~/-=3Tc..-;..!.AB=,./.;:,:4'-'5'---,----- SHEET NO. ll PREPARED BY D.L. Mart · n CHECKED BY No allowance ha s been made for the effect of t he damper system. The responses calculated for t he no-misal ignment case on hot (120°F) and cold (-65°F) days have been used to estimate the following envelope which allows for temperature variation as well as e.g. movement and thrust misalignment. This has been obtained by simple addition of two i ndividual responses, but will be fairly accurate. Height above ground Angle of pitch Angle of incidence Flight path angle Pitch rate At t = J sees: Normal acceleration Longitudinal acceleration + 18 ft. ( h ,: + 124 ft +40 < 0 <. +440 0° < a. <. +19 .5° -40 < '( < +230 q ( ± 12°/sec + .2 i. 1) <. + 1.5 O .,,_ ".:> -.. T "' R U : S HEE T "lo /0 • f I I I,} IJ DATE TECHNICAL DEPARTMENT L---------'-'--'--'--=..:...:.:::_. - - ---------, PREPA RED B Y ,____ ----+-----I A IRCRAFT I 1 F1G I BASIC GEOMETRY OF BOOSTER ROC.K.£T5 ~OCSTIR "ROCKET c.G . AIRCRAFT C.G . l_ £UVATIO"-.J I 5TN ST"N 53o·b ,4S7 5fN t5I • • UNCLASSIFIED I 72 / ~TA,..~+/,.__,~ S'..__ _ _ S HE ET N o __ /~O~· l~-- - - - - R EPO R T N O ---i PRE P ARED B 'r' DAT E - - ---------1----- ~ D ._ L ._ MARTI N--'-----_-+-5_£_P_r __ S6_ C 1-"1E C KEO a v DATE LONGITuntNAL Axis I I I t L :: UFi D::. DRAG L V ... \:E'LOC!TY \.J = W[IGHT -----s X ::: Fo~c.E ALDt-JG A/c. DA-ruM. Z:: FoRcf:. PERP~ TO Ak DATUM u .. :: VnoLJTY ALONG Ale llATU"1 W"= VE.LDc1TY -P£RPP. -ro Ale DATIJM M:: PITl.li IN{, MOHE'tvT ~ "' HOR.l'lO"-lTAL DIS'TA.ls!CE T"tiAVl:LLE'n BY C.C,. f:_-= Vl::R11C.AL 1J1S,ANCI'.: TIUVEU..CD 'By C::,G-. I • I A IR C RAFT I I • UNCLASSIFIE D I REPO R T N o _72._µTAB /4,'5 i ~ :or:J ~ / // ~ ~ r'/,./u /ILIIIIIJ SHE E T ~ o /CJ•'3 -~~ "------------ TECHNICAL DEPART_:__:M.:.c..=...EN'-'-T'--------- ---i p R E p ARE D By DATE FIG 3 X t A/C DATUM I 7H Po"RT RCOtRU:ST TD : M1~1GN MCNT PITCHING MOMENTS . - 1 __ - - - - 1 (NL CCNTROL ANGL£S lCRO' - II : I . I Ml_SALlGNM(NT C.G,, DISPLM:fD I IN 2.D1~U.TJON __ - l -- (_ -'.---: _ 1 I • I • ' j ! I I I \ • ; ~ - I - ' I ' I i , _ _ I___;___ f- -J.. - RAJfCTORY ___ i __ ; ___ ~ ___ J__ _ •--•-J---f - --i--~ - 7 I I ' ' I ! ' ' I I I ! ! l t ' ' I I ' - . I - ' ' ' I ' I I. I ; I I , : l I I I ' ! : ; . i I l ! - :--: :-··i--- l ---l----+---: -- -· i_---- l -1- I ··( -:- --- ~ -- ( I ' ' I ' ' ' I I I I • I J\'r-RTl-,,.l'd Ds.-r-AU/'C I I j. ' I I I : ! ' ' I f""'- - ...,,.\1- - I HSl.l'IL..L .. _..j __ - - -- -- -- ----, --7- -- t -- · ·- -,-- __ , ____ . --- + --1 ----~ I I i I I I : I i {FT) ! I I WtTH . NO~£ VP I : ~ ~---1 -- , -- -- /--- -- ~-- I -~ i_ __ - i r , --~-- __ j -----; __ -~ _Mt5AUGNMa:NT PrTC. ~ ING __ i- __ [ ____ : _ , , , 1 1 i 1 , , , , I , 7 l I ' I - T : ' - I • - l ' I I : / I ! I : - ; -- ~ li __ _L_ j_~ __ ; I- ~---- _I-~ ___ ; ___ __ _ ]__, -'.-----~-~--l- --- j__~ __ ! __ ~_) __ -t- , --i-,--- -1:_, ____ l_L__ : I I ! : I ; t ' i I ·I ; I I I I I I I I I -1 - I - i - - I ' ' ' - 1 ! ' - - • i : ; i - : I · I · : ~ ' I ' I : I I I I I ' I I ' ' I I ' ' I ~~ --i·-- 1· --r - -t· -··r' - r- - +--. -~--1--,--L-1~;--~----i---r - -l-----1- _ __ I ~ - i-~- 1 I , , 1 1 , , 1 , I , 1 1 , , , M1SA1.ic~f'1eNr ~ , 1 I I ! I ! ' I ' ........ ' - ·I I !-- i -;-j - I -1 - : : '. - 1= -- -·--;-· !-; -1 : 1 : ' I - I _ : I _' ' ' I • + 1· ' l 'H j I ' 1 1 I I : 1 I ~ ---T -: --i------t- . - - -~. --r- r-1---1 - ,--t-r--:-·- - 1 -- ~ - , --- • I I I ' I I : I I ' ' I i I -1- 1~-:-- - - + ,- ·-;· -- ---- : ! - " i --1 -l --- I - ! i . ' • I I I ' ! t t ' - ----t------i-- -+--r-- - -,-i -,--- - r ---f 7--W___,__,__-+-.,...f-t- -r-t-;--- j-- - i --+--- --~ -- - j ___ ;_~-- ' i I I ' I I l I I I I I I I I • ' • I - - - • ,- -. -- ; - -, - - - - - - '. t - - L. i ; - - - r WITh i Ncr.,E- • DO'-'l>.l .. - • ' I I I I ' I I I ' ' I ..l.. , I I ' i I : - +---+ M•~LIG-N MENT P1 ,._111NG ~Hf ieo:-- - -~: --'. r · ·:- -r- -, - -1· --- -1-- -- ---- ~---1 i- -~- -, I : I ~ ' I ' I • I I I I I I ' ' I ! - ·1 • 1· - i--- 1 -- -J .... t-·- - ---r-- -j ; ! ·• 1 -- , ' I I I I T ! I I I I I I , I I j___ ' I i - -+--t--- I j ' j ' I 1 ! : ! -f- --i--1- --- -·- -- . i - 7-- t-1 T---i- --i-i -- --1 -,-- T - ' - I - -;- --r· ''; ·;-7 - I -:- _J __ ; - - . - : I I --I - ! ! ' ' I j I I ' I l i : I : I ! I ; I ' ' I • I , '!· • • I i I I . • T- I ' I t 3410 t I .,lr~ ' I sr' ! I : I.«) 1' I , 7in [ tJto : ; ..9p.J I ' i-- L ., I·: ll 1-: ,---- -- ! tL :. 1-~RIZONTA~ n1rANCf(Fr) .1 _J ___ :_ J_i C z () r ;bt en CJ> - " -n, 0 --.J f\) ~ --1 )> tll ~ VI -\110 "' ' -,.-f' '\..: - - • UNCLASSIFI ED ~ ~-~-};~f~2t- -_; ~~ 7 1~~ _LA+~~ -: + ~f ~"1T'> Fl~ 4 • J1SPL!'\C.£1> : I 11 1N 2 t>IRfC'nc.,tJ . I r I i __ - I - qO -· - lO I I 1 I , 2.. VARIATION - · Of . __ ;AlR.5.PEED _ b/LT\-i TtME .. L _ ____ , ------·-7 -·- --- - ---- ' ' i - I . , : T I I I -- - ·'--- -+-- - : I L _____ ! . -- -- - -· - I ___ - 2 . -- - ------ I -- • --- ~ UNCLASSIFIED 72. / STAB / 1;5 /0· 4< Stl'T .,-5 ----- - ·-·- ·- ----- - - - - - - -- -i------- - ----·- ~ - --~- - . ARl,.Q, - ----- - -.-----. --,---:--- . I , ~ ;If,!! I 1 •• 1 1 I ,, t-~-~-:----~~~+-~-__ :_c ___ ~ ARR~~:-2~ J--,-+~-=-- ·: --L ~~-~~ -~-1=--1 [ ____ l_ -- --~ --~-~i z"ri_LfrJG-r~. -LALJNc ~1 ~~C1fil,· -:1Ls.A\, 1~J ~~ ~Ts=· I I ' ' I i-- -~ I ! I i I . i .... i r • - I --- - I i I. I i i L__ _ _;:,r; s . _ [f F [C..t. ___ QP_ . lE.MPE"RATURE ________________ _ ( 11L4 C0N1ROL • ANGLE!S I - • • -j --- - ·· - _J -- ' -- ---- J_ _ ◄ • • UNCLASSIFIED ')(:pr, f8 f- -_i _· +-- ' • ARROW. -~ , ·zrd..o. __ LENGTH. . LAUNCH --r- , ! 1 J,,. ~~~"; ~ M1'-'~NM<~T5 ws~G _M,C<;MU>LYAWING l"'UM ~'"'"" ~MTM/ 45 /0 · 7•3 ~E'PT, 58 UNC LASSIFIED 72/sr,-.~/4s 10•1·4 SEP,. 58 ·:: :- • ·f:: . 'i !--' :: .: , h :· .•. L . :, i-, '::I'. I.. . :·L . ::: : \ i i • ! i.: ~!. :h - . • UNCLASSIFIED UNCL t"\S S IFI ED 72. /STAI:, /45 S~Pi. ~8 • L '5 • • UN~LA SSIFIED 1. 9umar7 2. ..Cntroduction J. Description of :: .Juster Ao""lplic:iti:>n 4. Att.l. tude of A!rcrart. 5. .fodif:.c:.ti ms to Airframe 6. .Jroun:i Sup art Equipment 7. ·,leigbt An.:u~rsis 1 , . Dyna,ic C11:.racteristics lo. Ref"lrencea (a) Fi1,"llN 1 - Trajectory Envelor,4i (b) Fi .::ure 2 - Inoid-.ce F.nvelope (o) P'igu.N J - A1rspeo1 Ecvelope (d) Figure 4 - Anglea of Roll, Pit.oh and '{av 12. Drawing• (a) Boost0r Arr:ln~e 'lent (1:) 0.naral ~rit of Launohing Posit.ion • UNG LASS IFI ED l. SOlfilAI! An iIJYesti~ation has been made of a sero 1-,gth launchi.nc method tor the Arrov. The method adepts:! consists or aountin& two JATO Type 121 Onita wxier the wings, the take-oft bei.Jli acc0111pl1shed t'rolll a raap support.il"li the airaratt. b7 meana ot ita wxieroarnaa•• Th• poera]. oon1'1guration or the airorat\; aiethod ot IIOW!tinc tM bootrt.c- unit.a, arrange!ll9flt or the raq:is,,ani method ot •Jeotinl \be boon.re) are ahown on the referanced jnvings. A. preliminary study or the dynaino ohanct.4riat1ca ot tbe lAwDlb baa • be«l niade by the Aerodynamics Depart,aent (Ret. ~ lo. 72/S'!AB/4,). Tbie st~ inol\Jded .rreota or aialali~t ot thrun, wriation ot o.,. poeitioa, and et!eot.a ot t..pentuN. The repon 1Diioatff the bponanoe ot o.,. poa1t.1oa toleranoe, in partiow.ar, u wll u boost. thrust u:la al~. The axiwi■ aoceptabl• toleranoe tor the !CJZ"W' 1a ot the ordar ot t_ l 1n,ab and tor the lattar, 15 Id.nut. .. ot U'O. • ba■1nat.1on ot ~ ard strw.. 1.nlloat.ed t.ba\ _... adlt1oat.1ma would be NqQ1Nd in the TicinU~ ot the booatar at.t.Atbaln\ ~ t.o tbe vine, but. t.beae do not appear t.o be ot a Nr1.0118 nat.uro • • • • - l - UNCLAS S IF ! ED 2. .Iii1'Jl000CTil)I 2.1 A NqQe8t baa 'bNa !!lBd• that th• ~ 1nveat1gate tM teasib111ty oE a .tbod of launching the Arrot1 t.o flying ~eed without the uae of arq growxi run. It waa assumed in this study that the zero laui.oh operation would be required t.o be looate:1 at any point 1n tM ooun1:.I7 ani would be set. up on a 24 hour ~at t.he read¥" baah. 2.2 The pUl"pO■e or thie report. is t.o preaent the reaul.t• of thh inYe.U gation. The rusons for the equip.at Ml.eot.ed and 1u ldapta\ion t.o the Arrow are d1souac1ed. !iod1!1cat1ona that WOKet toosters for the zero-launch or,er -1 t1':>l'I. i\n a:'9roxi:;i;.te value for the roeket. thru3t requ~rei oan be obtained by oonsldering the fore.a 1,nvolve:1, ne&lect.1.ng IWJla9flta an:l a~o loada. Eng1na Thruat AU\.111l8d " 44,000 Lb. • Ti Gron Weight o! Aircraft = 88 • 20o Lb. Palanoe Vertical Forces: &'\200 + 264,6oo sin 10° - 44,ooo sin 17° 2.5' - Ta sin c( • o 88,200 + 45,900 - 1J,16o - TR IJiJl c( • 0 TR sin c( • 120,946 • • • UNCLASSIFIED Balance Horisontal P'oro.: 2641 6oo oo• 10° _ 44,ooo co• 17° 25' - TR ooa Q"' O 26o,06o - 42 1 000 - TR 0011 <( = o tan c( = • .555.5 c( C 290 2' sin ~ " .L;.;532 TR ,. 249,000 2.4 Exazuination or the airfra.'1l& st.ructu..---e Nftaled that. lt would be extre,:iely un.li ~:ely thJt suoh a si r;;_:le thru.3t could eoo~oall.¥ be applied. !t was rosolved. 1 th'lrefore1 to use t'-10 rocket boo•tv•, t'll0\.ll1ted synl1lfltr1Call,y to the lower sii 9 or the vine . The eoonoadca of c,10091ng an existing boost.er tor wb1oh pert~rna~ an.:1 rollahilit.y \lent known, l$1 to the seleot1on ot JATO Unit. l2l, fy--. 40.5-13()000 X226Al.. Thia booster h UMd OD Snutc am the oharaot.eristice an ae follows:- \./eight per Boost.ff Thru.-tat77°F a\ 120°F at. .65°F Burning Tile at 77°F at 120°F at. -650, • 5,125 Lba. =- 1321 000 Lba. • 14:3.500 Iha. • 101,.500 I.bat. • J.72 MOOnJ.a • J.45 eeoonda • 4.55 eeooma • • • - .5 - UNCLASSIFIED 2.6 It etlOlll.d be pointoo out that !1.gurea given ror -6,oY te·~>GM.ture are extnpolated, whereas tt is reoornen:ied thAt the boost.er be stored am fired at a min!..:urn environrfl"l~ tct~er-.iture of -ZO°F. I~rovud propellants .--:;ay extenJ. this temperature to low.,-,r 111111 ts. 2.7 The tol~anoas on thr • . t an.i turn .. out ti• for tn1s boost.ar are not '>.xactly i-mcYwn and further infor:l'.ition on lateirt. ,bta vO\lld be recpired for oon!'ir·iation. It c:in be asB'J.med that, aa propellant• are being continuously developec.11 the tol.,r:moea would be :,uffioient.l.y oloH to ninim.ze a..-iveroo ef!eot:3 wban using two boost.era. '.3.l Joo JAT:) Unit, Type 40.5-130000 X226Al is d18P')aed on each wi~, Mob t.ing rao-J.nt~l 'cene-'ith the "lain l::ox ~ar, arxi attached to the v1.nc structure by three si:.ruts. The t::>niard at.rut. which 1e ~ attaoh«l to the booster, is pinned to a wing !1tt1ng at the juncture ot \he sin :,par arxi rib no. 4. Two rear struts, eaob pinned to the boost.r nNl" t.i.e :1rt en:1, pick ur on fitti~, ~t the juncture ot the l"9U' apar at rite nu.'!lher 4 a.rd S. The bodiea ot the JATO units are substant.~ parallel t.o the a1roratt. dat1.a whereaa the axis or the booster nozzlu are oriented ao tb&\ the thNat. linlll projectoo ;,assea :1l;no:!t, but not quit.e, through ~ air oraft grosa oentN nf gr,ivity, They meet, o! course, ai. the plan,, ot ~ anl hence l:l ter:il ~nts c:mc.i eaob oth.-. The urt..-. section on the vcrtio:il. and fore :ini art. oo..ordinatN 1a 91.lOb as to pro:iuce the Je9ired trajeotory, this positiv• mal..al.1gnaaal. be1Jll nece:1sary to balance engine thrust. IS>oenta about the 0.1. • • • UNCLASSIFIED 3.2 Both boo.ten all8t be jetti!IOned at the point or burn..out. Im-,sti gatioa of jettboni:,g by free ro!ease showed that ;:,owertul pit.oh-up aarodJnaiuc forces ·..:ere resent. -.nich liOuld cause interference with the aft urx:ler 3Urface of t he wing and result in da.:age. Hence, ;,,,si tive d.Jwnward e j ection -:,r t.he boosters is :-; rovided. Saah booster strut ls loc.~ed into its fitting on the wing by rDe9Jl.8 or a hook lever. The three levers are oonneot.ed to a single operqting source on the top oentl~ or the r:icket t--y ·'lean5 of ro-ja arrl bellcranired the mini- to pronde 'l(l8q1.Ute cl ear:inoe for the launch. At. the $1aae t1.• a ad.nilaa b'aJeo\ory requires ~n1.mua boost thrust an:i recL1cea tba tima to oontrollabl• n1cb\ speed. Tm de~ wu chos4ill in oonsiJeration of theN two ob&r.loteristica. • • • - 1 - UNCLASSIFIED 4.o (Com.1.nuied) At the period in the launch at w!·,1oh oontroll:lble flight speed 1s reached, or at the s11ghUy :1 lgher speed at which h.irn-out ot the boosters occurs, it is deairabl~ t);., t the inci:ienoe ot the airerart be the nor-sl one for that speed. This provides a 111110oth trnnsition from toosted launch to oor1i.:u oli ·:t, ~ .)l:viawa a su.i Jen :e:nand on the r,Uot to corT'8ct for inoirienoe, at a t1:m when he is ;:-robably OOIT9Ct1ng for other deviation.a. Combining the trajectory with the 1noidenoe givea a 20° attitl.l(W for the aircra.rt. :1atum an:! t.'11:s a,,;,liea to the st.atio posi t1 on on the mill'•• The airora.ft is supported on thr~ r:unpa, one tor Moh un1ercarr1.ap. Dua to the 20° btum angle, it is necessar-.r to rabe the main underoarrlap al:ove the gro\ll"d to HVoid ir.t.erterenc• of the rear of the jet pip• vitb the grouni. The aircrart is .rt.nc.hed up onto the r&.'1')1!1, the !TJllin wheel.a nre loalcad to ;:iravent roll.back, nn:i the noH gear then elnated to giv. the deai.Nd datum angle. The nosewhffla iai.st be looked to the rup duriJlC elention an:i sul:sequ.nt.17 l:eaause the o.g. norel to the iJ'0'1nd pas ... 'fW7 oloN to the main gear ful.orum poin\. At the inatant ot firing the boost.era, all lOOka betvNn airor&ft ani raapa are rel-...d am the nose ~ear r&!ll) 1a quickly 101o19Nd to allow the NIU" bottoia t'uNlage to olen.r on take-ott. 5.0 MODITICAT:.ON TO AIRr'r,XiE Consideration ot the re3ctiona in::iuced in the 31rl'raa 'b.T booat& t.hrust ani acceleration, :w:l the :::ianr:er in wMoh they an disviblt«l through the main wt~ t.orsion box, 1.rrlicat. .. that no sC'ioua prot,l• regarding tho atructure exist.•. The '.)1"81'.ainary tiD:linga are aa tollove:- - 7A - UNCLASSIFIED ,5.1 Rib 4 - A Nde•liD 1e protably necessary to i.ncoroorate a(1l1t1onal web ·Sterial am nange at.ftrial b lif.'u3e the !'oro :url aft booster thrust lo.id• into the skins over a consUerable chornwise length. I! the rih t.e Dl8de ca:·able of J:::i t.ributir.g the lo·iJins s to the s..'1.n ov.-u- 1 ts •.ih:.ile length, no 9kin thick:enine ,.uul::i 1:e necossary. 5.2 Front 91?!:: Local Ndesign likely required to suit booster strut ;lick-up fitting just out.boaro or Rib. 4. Local strengthening between rlba 7 am 4 in the rona ot 1ncJ'eued web th1c! ness :m:i flar.ge ::11r.es 18 indicated to aaooinodate local 'l1''.l!'llmt .:m.i differential sh~ lo.:wa applied by the rear 110Wlt.1nc ::ioints. - .5.4 ~ 'lb.-. 1a a possibility that. ar>J1.t1cation 1s requir«i frOII the rear spar to the centre 59:ir an. to provide a bnlance :·,ath for loaca i'l'0lU rear out~ard !"1.tting. A possible increase 1n thicl-<;nesa aft or the centre spar aft. betwe«l ribs 4 and 6 to accoanooate local difte.-ent.ial shears between the an. mounting points. 5.6 Fuselage SUew:uli, ?oseible increase in skin v,auge below rib 4 to longeron to carry that ;,ortivn ot thrust loads which h reacted by !Unla1e s.n.-tiu. 5.7 Deflections Ana.ly!lis indicates the fallowing wing :ieneot.iona UDiell" launchinc cortlitiorus. a. for,,.rard pick-up point dCJWTAilal"d defiwtion • 0.12 1nab b. Rear intx>ard pick-up point. downward d.neotion • o.411.nab o. Rear outtoard pick-up point downward cu.tleotioo • 1.80 inah. Thb result• 1D a noN up -,vement or the boost.er t.hruat. uia of about. o.'.}6 dagreea due to wing defleotion.s only. ~ uw,uar .,.._ :ait. noN outboard 'd1.ll acc~any this deflection an:1 vUl be of the S8.lM order. Daflections of the booster struts am the boo•ter body will be add1- tior.al to the above. - 9 - UNCLASSIFIED 5.7 (Cont.imed) It. 1• aubaitted that t.,ose d.nectiona can be entered !or v\ th regard to 11111-aligment. cy pre~ttini the booster thrust UN to cancel de00Ct.ions while uniar thrust loooa. As pointed out el:381o,'h,.n-e, thtit [Jl'Oblem of thrust anl-a11,:n:~1t ts allav-btad to 30!18 J.9grae by illllintaining a very close toler 0.ooe on a stan1ard. e.g. position for the sircra!'t.. 6.o G,~:J.Jlill &JPPORT i i..UD' s;r '."1.nimm groun:.i 5UI ,r;ort equ1;,:nent will inolu:io the !ollowing:- 6.1 :~1n gear an:i nose ,:ear ra'.%·s, together with tie downa, winohi.nc gear ard nose elevating :ini release goar. " .2 T~r,:.ture control of boosters, 11liss1lea aIXi radar. Thi• -.y be aoc~l1shed by a unit heater supplying oontrolled temperature air to the un1t3, or by ourroun.iing the airora.t."t with an inaulat.ed ha.near, the ,iir and O)ntent.a of the hang:.1.r beil"li ~ntained at the 1'9qUin4 ~)el"~ture by moana or a heating unit aJXi oontrola. 6.J Equip:nent for hanilinc the booster unit.a on the bue, aapable ~ rai•ini tha to a position !or ooupl1ng to the airorat\. Al.ao requind are booster alignment tool• for alignin£ the booater thrust to within requind toleranoea. G.4 Grouni st3rti.ng equipment f'or the ,sin engine•• 6.5 Grourxi crow :mi flight orew quart.era. - 10 - UNCL ASS IF IED 6.6 An imul&t.ed hangar !or the aircraft. Thi• 1• r«;uired to b8 u small and aa light '.ls posnble and be or pre!abrioated oonatruotion. It !91.st. be possible to transport. the p::lnela of whioh it is a:Jsembled to the site by .ihate-fflr transport is sneoiffo-J for this operati'.)n. V:>li.we an:i sur.f;.oe area :iu:,t be a ~ni!:».llll to keep the (l'?Vironmental hoating or cooling load aa low as possible. It is not oonaid81'ed possible to nnre" the aircr:i..ft. out of the hangar wan though both •.ms be open. Too energ'l es 0£ engine et'lwc: :U'd bo-Jster ernux WOIJl 1 be 311.f.!"-oient to ,1emol1sh :. lit,h:, structure. lianc., it is propos«i to t110ve the h'1.rigar side-.. ays out of the -la:iaE; ·• zone. Thie r.quirea t..'lat :me side be re,oovad, which aan be cione by !oldinc the ai~ a.~col'd1.an fashion am D\OVing 1t side-way:1 with the hangar. Prarlnoo would be necessary to remove any ancillacy tiqui r.,mnt contained in the banpJ' at the sa..'38 t1:,,a, either si':lewaya with the hangar or to ~ otlMr prot8Cted area. 6.7 It. is prell\mwd thnt facilitiea exist. r-,r fuelllrlc th• airor'aft, or w,,uld be provided. This dooe not neoeasarily 1.molv• U.. launahinc :)!"Ocedure wxler disous.sion. Weiaht of Arrow 2A with Jrop tank X.... weight of drop tank aoi fuel Plus 2 .JATO Roosten P1ua Booster Stru~ and G.,ar ?lua '.bis. to Alrcra.t't Total Grose Weight 81,000 200 • - ll - UNCLASSIFIED 8.0 ImlAMIC C'riARACT~I.3TIC,c., A prel1ainary 1nvealiL~t1?n ;-~1s b<:>en done fJr th2 z~-l enet,h launch, the result.a are jesoribod in Avro &.rort. No. 72/3tab/45. ).1 In this reµort.. t,j1e trajectory an:l. tbie !1i3t.Jries or the incidence, ;:, itch angle, ac.~elP.rations, .:!l)et'd• :,awing ar..:i rolling !ID'llents, rate• or y-:i.w :mi roll etc. have been worked out. !or 3t.m:i&rd con::l1.ti0na am !or non-st.arrlard corrll. ti::ms. The latcer incl.ude e!!ecta ot teuiperaturi,, of :Tall-al.ign.-,,ent or thru:it ;uea arrl ;QOVQ1110nta or centre or gravity. E!i'ects or !)ilot control or -:i~i~ s-Jstem ..,... not considered. ~.2 Although the final Jesi;,_;n ~Y differ in ~. weight, eto. rrca that ass,.1-nlrl in the analysis, ani hence, t.h• ro!pOJ\Ma "1ll dtrtw, the aoc.ptable tolez'3ncea ot 'boost aliginant an:i o.g. position eati ,11.'lt.oo. in tht'l re;\ort give a representative range of valUff to be ~ an:i ~H their i~ortanoe, i3.J This investig:ltion indicatAid that the ~xi- ~t.able tolell"'RJlON ot e.g. positions am boos1.er thrust -1..aU~ ahowd bea B,),l Airo1'aft Centre ot Oraviey Longit\Xiinal :!:, O.~ ,4.A,C.-::!:, 1,8 1nCb .!, 1.0 inch :!: l.J inch 8.J.2 Booster t.hril~t axes .J.-alignaent: 1.5 ainut.ea ot aro • - 12 - UNCL ASSIFIED 8 0 4 Thue · t.ol..-.naea produce dffiationa 1n ~ flight erJTelope u shown on F1gurea 1, 2 0 ). am 4. Further det.:.lla cay be !oum 1n Avro Report. 72/STAF/45. ~. 5 Combining the responses 1ue to ,:; w ·.etrtc :nal-al1grnent w1. th thoae due to the naxir:runi te-ir,erature range, will produce ros;,ons..a :..h1oh are oo::iewhat wider in spread t t.an for eaoh one separ:..tely. A very rough est1iste roay l::e en.le by OO!¥l1n1ng theia addi.Uvely as shown 1n the above reference. '1.6 'nl8 l::ooster thrust a116,11ment tolerance ';)f 15 :ninutea will be difn cult to :wt..>t. This a11r,r-"!10Tlt. is aggravated ao~t 1::7 ramoa P.• :nal.-align:uent ot the 't::oostw0 a .;uant1 ty ~l!"ediot.abl.e except b7 r..7 Report. 72/'5IAB/45 show• that !or p1toh1ng ani ya~ responaa pro duced cy thrust :inl-aligrnent,0 a thrust sl-aligrl11181lt ot 1.5 .ainutea h equ1valmrt. to a o.,. aovement of o.8 1nab. u.no., a t1chtar tolerance on e.g. ,oovenwent. would allow an 1~ 1n thrust ial alignnent, 0 e.g. Uthe tolerance on e.g. 1a !1xed at! 0.2, 1nob0 thruS't. mal..al~nt ma,' be 1.nCNCl8ed to 11Dprox.i.-atel7 !, OO )) 1 • 8.8 A oonaidC"at1on ot the respona.,.• showa up t-wo cr1t.1oal po1nt.ac- a. A.ttAil:' 3 seooma, height .;atned 't\T be aa low u 18 ft. b. Ino1denoe ~ be 19.5° These irrlicato the ;,!gnifloance ot ,:llll-al.ignmlnt. ani the c.,. poa1t1on. 3.9 F1i!u-e J •how• that at 2 ~rxi• from zero. th• air apftd 1• 108 ~~ta arrl at three aec·nda, lt i.s 165 knot.a. Hal0e0 up t.o 2 seoonda0 contrnls will c• ineffective and from 2 to 3 NO- i ~ - - --+- A'> ~4L~•y _j -~ -r , _:__ I_.; _J_~· ,. ___ I . ..:. . . -. ;s:nwp4@ f>' 7.f r. J ___ ~ .. __ : __ _ ' ' ~ ' . , 7ld : I , 1 11,1 , ~ . 1 1 i~ r-- - + -,/-1- 1- .-- , , ~ _p..,,.,i -,~ic: ,-- 1 - : 1~ \ • - I I ,, ' I f ' ' I I I ' I --+,,;---+..,...._~ - L,;,.7·~-4- .. L... l---, -+- ·-·J . ._.._L---t ·-'+ - - .. _·---r ' .r . i I r I , ' i I , . I :-1 r r r+ , •• ,,,. -'./[ + ! 4- •j•-:- -1- :- I - 1-- 1-:-- '--J 96~~- -'tti I A 1 1 •! j r I I I I 1 ; --- , , 1 -- - .!-.-..<~--l - , _ I ---r:- - ·-1- ,- ·1- J. -L-----l --r-- - -·- - - i I I ,, I I I I i ' i I I 'I I ' I ' ~ • c- ··1 --1- l I · - .. ,,~~1 -T-~ - ]-+ -~A(RSfflP : vi 11,ve I -, i ·:· <-o ~r. _J_ i -1· /,,'f~i- -·: '~~- ;;l , ~--;PAt-u.ee--r-· ;:;-,...,..--Ji -c ;ft +,[, ' I ·, ·. :, ., ,, l : 1 ~_...:. , .. --- ' -' :., ., I _J ' C ·; : '' j · · ,-:--r----T-r- --1- ,--- - I + ·- ' ' I ' ' I I ' z ---- -.. :._i_.....: - • -+---+-•~~ I • -1 --: ~ I - r ; I i 7 · -,- ! - a:, I --]__ () __ __j_ __ j__T, __ , ___ i _j_ -l---t · --~ __ L __ I r I I I I I ' I ' ' I I I , , '-7 - I I ' I I ' ' ' I - 0 ' '. - l> 1 1 ' ·4•11 :. ' L · I ' d±' :- --1-- 2o , - • -JJ~ ~-c--t--+-~.... . . - +- -f -+- . T1 -!f -~...L._ ~ - '- - - ' en j+ , ! , ' I I I 1 1 ' ' en ~-- -· - :-;-_ - - · ~-'--'--~'---- , -r--: ---1 : : - 1 l --:-- -+~ - ~-~- ··. s s IFIE D Reed. from Astia July 29, 1958 Test of zero length launcher f~r OQ-19 target drones 31 July 1956 33 p. incl. illustrations •A description is presented ot evaluations on a zero launcher for OQ-19 target drones and of procedures for aligning the jato bottle onto the drone. The launcher is of a simple steel framework construction which can be trained in the vertical plane to various preset angles. The 2½ x 7 foot launcher can be mounted on a trailer truck or a fixed foundation. The jato carrier consists of 2 circular supports and a cup to house the jato bottle and two support anns which are attached to fittings installed on the drone sides. The jato bottle is positioned at the aft end of the drone as an extension d: the centreline axis of the fuselage. Fifteen zero-length launchings of OQ-19 target drones prov- ed the feasibility of the launcher for use by RCAT detach ments. The elimination of the time consuming jato alignment procedure was considered possible by the redesign of the carrier components along with marking the location for the installation of components during production of the target drone. The zero-length launcher system when modified could be considered as a supplement to the RL-2 rotary launcher and as a replacement for the cumbersome A-7 catapult.• Design and manufacture of air launching racks for Sparrow I and rework of existing racks for the evaluation program. "The first launching rack was a narrow pylon-type structure w~ich supported the missile at three points by hook-like devices which were inserted into recesses on the bcdy of the missile, When the missile was modified its centre of gn1vity was in front of the forward recesses and the first launcher design was abandoned. Ten new launchers of zero~ length were designed and built which employed 2 short- pronged fcrrks to engage 2 retractable spring-loaded buttons on the missile. The second design restricted missile launching conditions and a launcher of finite length, designated Aero llA, was conceived. Eleven Aero llA launchers were designed and built. Prior to completion of the Aero IlA launchers it was decided to rework the 10 zero length launchers ihto a design resembling the Aero IlA. In both configurations the missile is fastened to a sled which rides in a long rail on the bottom of the launcherJ on firing, the missile and sled move forward three feet, when the sled is snubbed to a stop and the missile continues forward. In the reworked launchers the dynamic impact loads on the sled were in excess of its strength, The Aero IlA launcher rack is narrow, stref'sed skin structure approximately 3~5• wide by 6• high by 101• long. It weighs about 58 lbs. Major component assemblies of the launcher are:1.structure assembly, 2. sled assembly, 3. buffer assembly, 4. detent assembly, 5. umbilical plug and lifting mechanism, 6. jettison assembly, 7. landing lock assembly, 8. sway brace assembly, 9. cable assembly and 10. indicator switch assembly. Fur.ctions and design details of the components are described; ,. AD-41 041 Northrop Aircraft Inc. U wet:.IJ!:~15'1 FIE D • '- AD-26 037 Northrop Aircrat'il Inc. UNet:~~S'tFIED AD-18 367 Northrop Aircraft Inc. li ~~·l~~~ ! F l ED • Page 2 Clearance study of N-69 C, D, alld E missiles with zero-length and short rail launchers (using reduced thrust boosters) F~G. England Nov. 53. IDus. JB-62 preliminary analysis of a zero length launching with jetavator control. L.E. Hamilton & R.A. Branker. 13 Jan. 54 •taunching of the XB-62 missile is accomplished by a zero length launching system which uses a rotating arm or a short rail type launching platfonn with 2 jatos attached directly to the fuselage . .1 preliminary analysis was donducted to det ennine the relative merits of an auxiliary control for the present system. This control is a ring type jet reflector (jetaw.tor) which is mounted on the jato nozzles. Analysis inc.icated that the sidewind tolerance is increased from 6 to 20 knots by using the jetaw.tor. For a 20 knot tail-wind tolerance, the allowable alignnent error in pitch is increased from 0.38 deg. to 0.55 deg. A headwind produces no adverse effects on the launching. The wind tolerances and allowable alignnent errors can occur simultaneously or in any combin ation that does not exceed any of these tolerances separate ly. A more effective jetaw.tor is under study.• Design test of snubbing eystEl!l and instrumentation OD N-73 zero launcher. F.Q. Banker, R.D. Glascock & H.F. Kale 2 Feb. 53 47 P• Incl. lllus. •This test was conducted f>o establish the pressures required in the snubbing system and the suitability of design of the launcher instrumentation. A secondary test of Northrop relief valve shear pin 2114796 was conducted to establish shear data required 1n the design of the snubbing system relief valve. The test specimen consisted of Northrop Zero Launcher 3508 including 5001162 launcher assembly,5ID022 mechanical installation, 5111578 potenticmeter installation and 5111577 camera installation. The test setup and procedure are out lilled. Five free-fall tests were conducted as a functional check of the snubbing cylinders and the pressure relief valve mechanisms. The fifth free-fall with a precharge pressim of 15 pc and an effective rod length of 2144• actuated the relief valves Accelerated fall tests were also conducted. Part of these tests were constructed to produce a tangential velocity of 31 fps vith a minimum mechanical rebound. The remaining tests were perfonned to cover a tangential-velocity range. The test con ditions, the resulting tangential velocity and the mechanical rebound of the accelerated falls are given. Precharge press- ures greater than those indicated by the safe-operation range may result in non-operation of the snubbing system. Precbarge pressures less than those indicated by the safe -operation range may cause excessive mechanical rebound. Tolerances in the system do not permit consistent operation at pressures low enough to give rebounds of less than•6 deg. A memorandum report on zero launcher 35CY7 is included. AD-38 587 Naval Personnel Research Unit, - u;er&fflrFiEo AD-6177 Naval Air Missile • Test Center, Point Mugu AD-19 633 Chance Vought Aircrai't Urre'E~IFIED • Page 3 Basic occupational data on guided missiles .III Regulus :XSS~-N-8 (Revised) Paul W. Athan & Robert P. Green Sep. 53 Illus. •A compilation is given of info:nnation on the Regulus missile obtained from several sources with the use of various data gathering techniques. The Regulus is a surface to surface ·: guided missile whose general configuration is similar to a small jet aircraft. The missile which ie se.pable of carrying a 3000 lb payload 500 naut. mi. has a 21 ft. wing spread and an overall length of 34 ft. The missile will exist as a tact ical and assault weapon, a drone pilotless aircraft and a night-test vehicle. The major components of the missile are slillllllsrized and the tasks involved in the operation of these components are described. Charts are given which present the overall Regulus missile ptogram. The catalog also includee a general overview of the missile program and a discussion of the general considerations involved in performing research during the test and evaluation phase; a series of charts which discuss the overlap of related duties performed by existing ratings and the duties required by Regulus missile personnel; a chart which traces the now of the missile from the time it leaves the manufacturer until it is launched; a glossary of guided missile terms as well as all terms encountered in the Regulus study; and a bibliography of technical materials.• Tests of Regulus short-length launching configuration. Donald E. Power 16 Feb. 53 Illu:s. "A rail-type launcher designed and built by the Naval Air craft factory at Philadelphia provides a guided travel of 12 ft, is fixed in azimuth and elevates to JO deg. for missile launching. The weight of the launcher is 18,650 lb. The operatic n of the launcher, using dUlillllY i;iseiles, was satisfactory during teets. The night paths of the missiles were satisfactory in both azimuth and elevation. The jato units separated cleanly frcm the first two missiles, but did not separate from the third missile. Newly developed igniters with low ignition-schock characteristics were used in the jato boosters.• XSSM-N-8 Regulus. Tech. progress report No. 5 1 Jan - JO June 53 124 p. Illus. •The Regulus program for 1 Jan. 53 through JO June 1953 is reviewed. The Regulus is a transonic, turbojet powered surface-to-eurface guided missile. Tactical Regulus can be launched from a short-rail launcher located aboard a sub marine, a cruiser, an aircraft carrier or a mobile plat- forn at any desired point. The night-test version of Regulus can be launched in the same manner and, in addition is equipped with a landing gear for conventional rtll'.lWay take-off and recovery. As of JO June 1953 a total of 53 nights were attempted, 43 of which were considered success ful. Thirty seven of the Regulus nights ended with recovery of the vehicle tested, and six of the nights were intentional dive-to-impact missions." AD-4840 Chance Vought Aircraft e U~IIA~IFI ED AD-48 512 Air Proving Ground Command UN C~~Srs¥F' I ED AD-142 434 Northrop Aircraft Inc. c?~~~SSJFfED Page 4 XSSM-N-8 Regulus Prog. Rapt. No. 2 1 July - 31 Dec. 51 158 p. lllus. •Regulus is transonic, turbojet-powered, surface-to-surface guided missile designed to carry a special-type 3000 lb war head to major targets at ranges up to 500 naut. mi. Tactical Regulus can be launched from a short-range launcher located aboard a submarine, a cruiser, an aircraft carrier, or a mobile platform at any desired point.The fiight-test version of Regulus can be launched in the Balle manner and is equipped with a landing gear for conventional runway take offs and recovery. A total of 15 flights were attempted, 14 of which were considered highly successful and 13 of which ended with complete recovery of the vehicle.• Operational suitability teat of the B-61.A weapon system. Flash Rept. No. 1 12 July 54 lllus. •Tests were conducted to evaluate the B-61.A ~re-length _ _ launcher blast shields and the RATO booster ejector head. With and without the blast shields on the launcher, damage occured to the external power and fire control cables and to the warhead winch cover. It was concluded that the blast shields which are a part of the B-61.A tactical launcher and the ejector head which separates the expended Rate booster fran: the Airborne B-61.A can be eliminated, Recommendations were made that, 1. the blast shields and too ejector head be eliminated and 2. the modifications described be incorp orated in future B-61.A launchers.• XSM-62 missile AF53-8184 (N-3321) Unclassified title by D.J. Deering Flight Test Rapt. 23 Aug. 57 Illus. A night teat was proposed for the AF53-8176 missile to detennine tp.e integrated missile systems operating char acteristics. The missile was successfully launched fran a short rail mobile launcher, remained in night 3.4 sec. and impacted about 680 ft. downrange from the launcher. Data were obtained to partially evaluate the operation of the Mk. I guidance system in an N-69E series missile. All major sµbsystems functioned satisfactorily except the flight control syst.an. A reorientation of the pitch-rate gyro between the D and E series missile with neither a wiring or a check-out procedure modification resulted in a reversed polarity of the pitch rate signal; this caused divergent control response of the jetavators and elevens which resulted in the loss of the missile. The loss of 115-v, 400-c power to the afterbody telemetry system resulted in the loss of all cc:mmutated data at 1,15 sec.• '- AD-49 413 Air Force Missile teat Centre e u~;rsr;,FtEo AD-23 360 Northrop Aircraft Inc. - U OOt!TA SS IF I ED Fage 5 Modified B-6U night teat results -Aug. 53 - April 54 (Unclassified title) R.M. Gray, and David W. Jones Summary rept. Aug. 54 70 P• Illua. •Flight test data were obtained fran 40 launchings of the modified B-61A weapon system in an evaluation of the in-night reliability and accuracy of the B-61.A system (excluding the warhead). The airborne portion of the system consists of pilotlesa aircraft utilizing a turbojet engine for cruise and a solid booster rocket for takeoff from a zero-length launcher. Of 27 nights covered, 13 were successful; 6 of these fell within 3175 ft. and 7 within 3500 ft. of the mean point of impact. On the haais of these nights, the minimum in-night reliability of the system accuracy is that 50% of the successful missiles launched can he expected to strike within 3400 ft. of the target if the target is the mean center of impact. The innight reliability and accuracy of the B-61A weapon system are considered to limit its com bat effectiveness. The missile control and guidance systems appear to he the predominant contributors to the system unreliability, and the guidance error and the terminal dive error are major contributors to the system miss-distance. The major cause of the guidance error came from the MSQ guidance system's inability to determine aircraft location in space during night.• Clearance study of N-69 C,D and E missiles with zero length and short rail launchers (using reduced thrust boosters) F.G. England Nov. 53 72 P• Illua. A study was made of the conditions that must he met at ambient temperatures of -10 deg. F to permit the missile to clear the launcher satisfactorily. The X226Al boosters are used on the Northrop N69C missile to launch it from a zero-length launcher. The X226A3 boosters are used on the Northrop N69D and N69E missiles to launch them f'rom a abort-rail launcher. Equations were derived for the motion of the N69C missile and the motion was plotted as a funtion of booster forces at -lOOeg r. The basic geanetry showing the felationahip het\leen the boosters and the missile was determined.• -------0-------

Arrow 2A Zero length launch Report No. 72/STAB/45

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