Design, Analysis and Research Corporation (DARcorporation) ERRATA: Airplane Flight Dynamics and Automatic Flight Controls Part I

Transcription

1 Dsign, Analysis and Rsach Copoation (DARcopoation) ERRATA: Aiplan Flight Dynamics and Automatic Flight Contols Pat I Copyight 995 by D. Jan Roskam Ya of Pint, 995 (Eata Rvisd Fbuay 27, 207) Plas chck th wbsit fo updatd ata pag iii, lin 3 pag x, lin 4 pags vii xxviii Topic Rviw of Impotant Sign Convntions should b movd Th scond wod contol in th dsciption of th cl should b dltd Add th following symbols and dsciptions Symbol Dsciption Unit pag xxii X, Y, Z Body-fixd (otating) axis systm -- pag xxii X, Y, Z Eath-fixd (non-otating) axis systm -- pag xxvi, 2, 3 Eula otation squnc (th us of th symbol to dnot th fist Eul otation is usd only in Chapt ) pag xxvii P Oigin of th XYZ systm pag xiii pag xxii xxiii pag xxv, 6 th lin In th fouth lin fom th bottom, C X should b C Z Rmov th ngativ sign in all latal acclation quations. µ g should b dimnsionlss. pag 6, Eqn. (.7) p should b p. pag 7, bfo Eqn (.4) Should ad: Th tansfomation fomula...of both quations (.) and (.2). Fist, fo th l.h.s. of Eqn (.): pag 4, Sction.4 Last paagaph, st lin Θ= 90) should b Θ= 90 pag 7, Fig.7 Th aicaft of th lowst figu should b sn fom bhind, i.. a positiv bank angl should hav ight wing down. Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995

2 pag 26, Eq (.62) Fist quation st ω = kθ should b ω = j Θ 2 pag 28, Lin 9 pag 34, Lins pag 40, Lin 26 un should b in. Rfnc should b: Roskam, J.; Aiplan Dsign, Pats I though VIII; Dsign, Analysis, and Rsach Copoation, 440 Wakausa Div Suit #500, Lawnc, KS 66049, USA; 990 Should ad, apply to cambd (un-symmtical) aifoils. pag 43, Fig 2.6 S wf should b S wf 2 ( η ) o η i pag 44, Eqn. (2.6) S w f = S [ 2 ( λ)( ηi + ηo )] ( + λ) pag 47 pag 5 Fist paagaph und scond lin. In vaiant should b invaiant Scond paagaph 8 th lin. top should b to pag 55, Eq (2.27) should b dε dε d = d M M = 0 2 ( M ) pag 59, Figu 2.20 pag 63, Poblm 2.3 pag 67 pag 72, Eqn (3.5) pag 77, Eqn (3.2) pag 80, Eqn (3.29) Flap Chod, c f, should go fom hing lin to tailing dg th st of data und data st a should b data st c chang loos in los. CD 0 is th valu of C D fo: = i h = = 0 C is th valu of C L0 L fo: = i h = = 0 C is th valu of C m0 m fo: pag 84, Eq (3.30) in cos( + ε) i W should b i h i w pag 84, Eqn (3.32) Should b: Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 2

3 F H I K F C = C + C + C a x x m mac L wf 0 L cg ac wf a wf wf jl N= h C SS x x d La h ac i h h cg a o + H h da a K + + τ d pag 84 4 th lin fom bottom A fnc to Eqn (3.33) should b Eqn (3.32). j I O Q P pag 85 pag 95 pag 97, Figu 3.28 pag 98, th lin fom top pag 99, Figu 3.30 pag 04 pag 04 pag 06, Eqn (3.67) pag 08 9 th lin as wll a positiv should b as wll as positiv Last full paagaph, 4 th lin. Aft votics add (at high angls of attack) Nomal vlocity vcto on lft wing should not b psnt. th-vis should b th-viws. Axis labld as Z should b labld as X. chang loos in los. Last paagaph, last lin ight whl dflction a activatd should b ight whl dflction) a activatd K SW nds to b dfind: is th gaing constant btwn cockpit contol whl o stick and ailon o spoil dflction. Figu 3.38, th subscipts v should b takn out fom th two vaiabls Fa yudd and N A udd Pag 08 Eqn (3.7) pag 09, Eq (3.72) Sz v v C s l C L v η v Sb = placs Sx C v vs l CL q = v v Sb multiply ight sid quantity by qsb pag, Eqn (3.76) Should ad: F A y L y C qs C dσ = β = β q v S v v β v v dβ pag 3 Equation (3.78), th subscipts v should b takn out fom th vaiabls F a yudd pag 3 pag 5, Lin 4 Equation (3.80) should b multiplid by: qs Th yawing momnt du to th vtical tail m b wittn as: Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 3

4 should b Th yawing momnt du to th vtical tail may b wittn as: pag 7, Lin 20 Lin 20 should b btwn Lins 3 and 4. pag 8, Figu 3.46 pag 8, Figu 3.46,.) pag 2, Eq (3.9) Positiv olling momnt should b labld as Yawing momnt. inducs dag should b inducd dag multiply ight sid quantity by qsb pag 22, Eqn (3.92a) Should b Li = n LT = = T z y s = O... i T i cosφ T i siny T i T i sinφ T i j P cos +... i = 0 pag 22, Eqn 3.92a Th summation should say i = pag 22, Eqn 3.92b Th summation should say i = pag 22, Eqn 3.92c Th summation should say i = N= QP pag 22, Eqn (3.92c) Should b Li = n NT =... =... T z y s = i T i cosφ T i siny T i T i sinφ T i j sin i = 0 N= O QP pag 24, Eqn 3.95b Th summation should say i = pag 26, Tabl 3.4 V should b Q pag 27, Lin 4 Should ad, 2) patial divativs in Tabl 3.4 indicat th slop by which a paticula ptubd foc o momnt is affctd by a paticula ptubd vaiabl. pag 33, Figu 3.5 All V in this figu should b V p P CD CD pag 34, Figu 3.52 Equation actan > 0 should b actan < 0. M M = M2 Figu should b labld Exampl of Dtmination of: C / M at a constant angl of attack. D M M = M2 Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 4

5 pag 36, Eqn (3.9) C L should b C L pag 36, Eqn (3.22) Vaiabl M should b M A pag 37, 6 th lin fom bottom Should ad... a affctd by changs in angl of attack, :.... pag 39 Equation (3.33), chang th subscipt x to z in F Az pag 4, Eqn (3.42) chang aiplan, causd by to aiplan, CL causd by pag 43, ight aft Eqn (3.46) Should ad... multiplying by th non-dimnsional momnt... M pag 45, Eqn (3.56) chang A C = m qs = Cm q qs to qc qc 2U 2U M A C = m qsc = Cm q qsc qc qc 2U 2U pag 47 Equation (3.62), plac th vaiabl c c pag 47, Eqn (3.62) should b 2U 2U C L in (2,) nty to C D pag 48 pag 48, Sction Equations (3.63a, b, c), th ngativ signs should b movd Fist paagaph changs in sidslip, β should b changs in sidslip at, β Scond paagaph sidslip angl, β should b sidslip at, β pag 57, Eqn. (3.89) C y C 2xv S s v y v = CL η v v b S pag 62, Eqn (3.97) Cn p and Cn should b C and C n, spctivly. np pag 67, Eq (3.24) Inst + u in dnominato. Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 5

6 F Tx np550η pbhp = U + u pag 68, Eqn. (3.223) C X T u should b C T X u This chang should also b mad in txt abov Eqn. (3.223) pag 73 pag 74, Eqn (3.248) pag 82, Lins2-3, 7-8 Fist paagaph, 5 th lin. Th wod b is duplicatd and should b dltd should b 0 (zo). Rfnc should b: Roskam, J.; Aiplan Dsign, Pats I though VIII; Dsign, Analysis, and Rsach Copoation, 440 Wakausa Div, Lawnc, KS 66049, USA; 990 pag 86 Equation (4.3), mov th vaiabl U pag 89 Equation (4.7), mov th ngativ sign pag 89 Th lin blow Equation (4.7), chang (4.) to (4.6) pag 90 Lin 6, cition (4.) should b cition (4.0) pag 90 Lin, CZ T CL CT z CL pag 95 Equation (4.36), mov th vaiabl U pag 95, Lin 6 Tabl 5. should b Tabl 4.. pag 96, Lin 2 Tabl 5. should b Tabl 4.. pag 98, st lin (4.22) should b (4.42). pag 99, aft Eqn (4.45) Should ad: C L mg qs. Not that cosγ.0. pag 206 Last paagaph, 3 d lin, in Exampl. should b in Exampl ). pag 208, Fig. 4.0 In th gaph on th lft, x cg = 0. 5 should b x cg = and x cg = should b x cg = 0. 5 pag 209, Fig 4.b Th ngativ tail stall locus as shown in th diagam is wong. Th Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 6

7 tim diagam should hav a positiv tail stall locus at = 25 0 and a ngativ tail stall locus at = Both of ths lins a out of th ang of th diagam so non of thm should b shown. pag 2, th lin Th cosponding valus fo tail-stall should b 2 0 and 25 0, spctivly. Also, th tail stall locus should not b shown in Figu 4.b bcaus thy a outsid th ang of th diagam. pag 26 5 th lin, Appndix A.. should b Appndix A. pag 28, 8 th lin fom bottom F STO should b V STO. pag 29, Tabl 4.3 In Eqn. (4.76), chang a to pag 220, Eqn (4.8) chang Vmc ( N +DN ) 2 T D = to Cn q max Sb V mc = ( N N ) 2 T D +D C n max Sb pag 22, Fig. 4.5 pag 22, Fig 4.6a β = 5 should b β = 0 Th latal axis should b th Y-axis. Also, th bank angl is ngativ as shown. pag 225, Eqn (4.86b) C should b C. Y y pag 225 pag 226, Eqn (4.89) Lin 20, th of ths should b fou of ths On th ight-hand sid of th quation, tan φ should b in th dnominato pag 226, Eqn (4.90) ψ should ad ψ pag 226, Eqn (4.95) Should b mur = mgsinφ. pag 226, Eqn (4.06) Th ( in btwn n and C Ltim should b in font of n. pag 227, Eqn (4.96) C should b C. pag 227, Eqn (4.97)(4.03) Φ should b Φ Y y pag 227, Lin 6 Th fist sntnc should b movd Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 7

8 pag 228, Eqn (4.98) pag 228, Eqn (4.99) pag 228, Eq (4.00) Vaiabls a, b, and c should b a, b, and c Vaiabls a, b, and c should b a, b, and c a should ad, Vaiabls a, b, and c should b a, b, and c pag 228, Eqn (4.02) Φ should b Φ pag 228, Eqn (4.02a) Vaiabl a should b a. pag 228, Eqn (4.02b) Vaiabl b should b b. pag 228, Eqn (4.02c) Vaiabl c should b c. pag 232, Eqn (4.3b) γ should b Θ pag 232, Eqn (4.4a) γ should b Θ pag 233 Thid paagaph, 2 nd lin. Th wod fowad should b changd to aft pag 235, Conclusion fo Sc Th inquality should b Mac wf < Lwf xcg xac wf j. pag 235 Last lin, fo a convntional aiplan should b fo a canad aiplan pag 236, Conclusion fo Sc Th inquality should b Mac wf < Lwf xcg xac wf j. pag 237, Lin 7 in Eqn (4.0) should b in Eqn (4.3) pag 237, Lins 0- Should ad: Fom Eqn (4.33) it may b concludd that as long as L h is positiv (i.. up ) and ( x x ) is positiv th canad acwf load to tim, L c, will also b positiv (i.. up ). cg pag 242, Eqn (4.36) chang HM = ChqSc to HM = ChqhSc pag 244, Sction 4.5. pag 250, Eqn (4.47) q q Last paagaph, chang h h = to h h h = qh q Eqn (4.47) is divd fom Eqn (4.40) and it should b: Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 8

9 pag 252, 2 nd lin pag 252, Eqn (4.50) pag 252, Eqn (4.54) pag 253, Eqn 4.58 pag 253 pag 255 pag 256, Eqn (4.7) RCT d C = C + C i + C d d d h otim h C L = 0 h h o h CL = 0 C L F H R Ch Th I K F d Ch Cm C h C d H m dk d F H CL Cm C m C d Ld Should ad... diffntiating Eqn (4.48) with spct to th angl of attack. I b I K g U Vh Wh Th fist tm on th RHS of Eqn (4.50) should b C L xcg x a ac wf wf j. Scond ow: Dlt th ) aft C h τ. Ch Last ow: Dlt th τ and th ) aft it. Rmov th τ fom th quation. Last paagaph, st lin, found by by should b found by Last paagaph, 2 nd lin, fom Eqn 4.69) should b fom Eqn (4.69) Should b F C I h Scg MPf = xcg = NPf C W C Fs n G mq h J F H G I τ K J. / = 0. 4 H K UVW ο ο pag 259, Figu 4.36 In gaph a) = 2 should b = 2 t pag 259, Figu 4.36 pag 263, Lin 2 In gaph b) df/dv should b dfs/dv Scond th should b movd. pag 267 Dfinitions fo ach vaiabl should b: C, C, C ngativ, ngativ, positiv spctivly h h h β t v nomally pag 268 pag 268, Fig 4.43 β Includ in τ dfinition: τ = and is nomally ngativ Signs on hingmomnt divativs a vsd. C β > 0 h v Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 9

10 pag 269, Eqn C n β v f C < 0 h F H F HG S x C v v = G J C s hb v s Sv xv L h C s v v L Sb C h v v b τ h s Sb b pag 269, Eqn S x C v v Cn C C s h v b n L f b b fix h v v Sb C s h b τ H G pag 269, Eqn Ch β v σ Cn = Cn + Cn βf βfix Ch β I KJ I K F I K J pag 269, Eqn F = β GhvqScCh Cn C β n f pag 273, Lin 4 and (4.209) should b movd. pag 277, st lin aft Eqn (4.22c) Th symbol C D o should b C Do. pag 278, Lin 6 HM should f to Eqn (4.36). pag 278, Eqn (4.225) pag 278, Lin 22 Equation # is patd fo two diffnt quations. Should ad, Th hingmomnt cofficint quation pag 280, Lin 5 n F should b s n pag 28 pag 286, Eqn (4.24) pag 288, Lin 2 pag 288, Lin 4 pag Exta piod aft stick-foc tim List at nd of pag is inconsistnt with Figu 4.49 Ch β should b Ch βv Sntnc should ad Excptions to this a aiplans lik th B-52. Rmov! aft nos-ga. gound subscipt should b g Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 0

11 pag 29 pag 29, Eqn.(4.250) pag 292, Figu 4.52b Last paagaph, st lin. Th wod a should b aa θ should b θmg x labls should b vsd fo x = 38 ft and x = 39 ft cg g cg g cg g pag 299, Poblm 4.5 Eqn (4.55) should b Eqn (4.59). pag 307, Eqn (5.a) Inst θ aft mg. ( CD CL ) CD } u ( Du D ) ( Tx Tx ) u mu = mgqcosq+ qs C + 2C + C + 2C + U u U pag 307, Eqn (5.b) Inst θ aft mg. u ( ) sin ( L 2 L ) ( L D ) m w U q = mgq q + q S C + C C + C + u U c qc C C C L L q L 2U 2U pag 307, Eqn (5.c) pag 34, Figu 5.6 pag 36, Lin 9 Should b u I q = q Sc C + C + C + C + C + C + u {( 2 ) ( 2 ) yy m m m m m m U U u Tu T T c qc C C C + m + m + q m 2U 2U Solid black lin nds movd. Lin is th systm is zo should b th systm a zo pag 38, 5 th lin Should ad w = U. pag 322, Eqn. (5.34) Equation fo C should ad as follows: C = ( X u + X Tu ) M + + ( + ) q U Z Z M U Z q + M q Z ZuX + M gsinq ( M + M T )( U + Zq ) { } B = X U Z M + Z + M U + Z + Z X pag 322, Eqn (5.35) chang u ( ) q ( q) + Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995

12 { } B = X U Z M + Z + M U + Z + Z X to u ( ) q ( q) pag 324, Lin 6 Rmov th list numb ) and align ow to fa lft. pag 328, Eqn (5.48) > should b < pag 328, Eqn (5.49) > should b < pag 332, Eq (5.53) pag 333, Eq (5.54) th quation should hav a minus - bfo ζ,2 ω n,2 and ζ sp ω nsp th quation should hav a minus - bfo ζ 3,4 ω n3,4 and ζ ph ω nph pag 333, Lin 8 T = 0.35 and T 2 = 0.28 pag 333, Eq (5.56) pag 338 Equation (5.69), th quation should hav a minus - bfo ζ 3,4 ω n3,4 and ζ 3d ω n3d θ () s = () s ( Z s XuZ + X Zu) 2 gzu U s Xus U pag d lin. Th wod ation should b atio pag 340 Equation (5.76), th tm Z M should b Z M pag 340 Equations (5.76) to (5.78), chang D to D pag 342, Eqn (5.82a) pag 342, Eqn (5.82b) pag 342, Eqn (5.82c) In quation, 2 ζ ps ω should b 2 ζ ps n ω sp np In quation, 2 ζ ps ω should b 2 ζ ps n ω and 2 ζ should b sp n ω p n 2 ζ s ωn In quation, 2 ζ ps ω should b 2 ζ ps n ω sp np pag 344, Eqn. (5.88) Chang th tm gsin θ to g cosθ pag 344, Eqn (5.92) Should b Magnitud = n 2 num + ω 2 num n 2 dn + ω 2 dn pag 345, Fig 5.4 Th mod dsciptions a vsd. a) should b Phugoid Mod Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 2

13 Shap and b) should b Shot Piod Mod Shap pag 346, Eqn (5.94) Th (3,3) lmnt of th tansfomation matix should b cos2 instad of cos 2. pag 349, Tabl 5.8 Th lft-hand sid of Eqn. (5.96c) should b ψ φ pag 350, Lin 5 φ()/ s () s should b φ()/ s () s B pag 357, 2 nd lin pag 364, Eqn (5.20b) Th (pitching momnt of intia) should b placd by (momnts and poducts of intia). Th quation should b numbd as (5.9b). pag 364, Eqn 5.2 Cn qsb b Izz should b placd with Cn qsb b Izz pag 364, Lin 28 Eqn (5.20) should b Eqn (5.2) pag 37 Equations (5.36) to (5.38), chang D 2 to D 2 pag 372, last lin pag 38, Figu 5.24 pag 38, Figu 5.25 y(τ) should b y(t). Fo Damping Ratio -/T should b /T Fo Damping Ratio -/T should b /T pag 383 Rmov th two lins bfo Sction pag 396, Lin 25 pag 397, Sc pag 398, Lin 2 Should ad, say 0 dg/dg/sc, a 3 dg/s pitch at In th thid lin of txt chang ζ sp to ζ d lvato dflction should b udd dflction pag 398, Eqn. (5.6) On th ight-hand sid of th quation chang c to b. In th two paagaphs following Eqn. (5.62), chang all th fncs of pitch to yaw. Also, in th scond paagaph following th wods 0 dg/dg/sc, mov th phas a pitch. pag 399 In th paagaph following Eqn. (5.69), th quation dscibing th sulting inducd angl of attack should ad: 22x57.3/(.688x56)=.4 dg. Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 3

14 Also, in th following lin, th canad dflction command should b 2.6 dg. pag 400, 4 th lin abov Sc Eqns (5.76) should b Eqns (.76) instad. pag 40, Figu 5.44 On th Y B vcto, th small vcto should b labld q pag 403 In th lin of txt pcding Eqn. (5.94), chang ( P ) 2 4 to ( P ) pag 405, Lins24-28 Omit paagaph containd by lins pag 407, Lin 3 cosθ = fo small angls. pag 4, Poblm 5.3 pag 424, Tabl 6.4 Last sntnc should ad: How wll do ths sults ag with you conclusions fom poblm 5.2?. Th Civilian Rquimnts FAR-23 a updatd to th following: Fo whl contolls: Fs ( WTO 00) 20.0 > and n nlimit nlimit 50.0 but not mo than: n limit Fo stick contolls: Fs W 5.0 > and n 40 nlimit 35.0 but not mo than: n limit pag 427, Lin 6 pag 427, Lin 7 Rmov th tun so b and wittn a on th sam lin. tim to doubl should b tim-to-doubl. pag 434, Lin 2 Rfnc 6.5 should b Rfnc 6.6. pag 437, Tabl 6.2 pag 438, Tabl 6.4 Sixth lin of txt fom bottom of tabl, plac val with valu. All inqualitis involving th oll mod tim constant, T should b fo all Flight Phas Catgois and Lvls. Fo all Flight Phas Catgois and Aiplan Classs, Lvl 3 should ad T 0.0 sc. Also, disgad th footnot fing to MIL-STD- 797A. pag 453, Tabl 6.22 Th numb on th last column is fncd fom Figu 6.6 instad of Figu 6.5. Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 4

15 b S Sh pag 456, Eqn (6.26) Should b: = gust S pag 457, Fig 6.8 Th gust cuv is plottd with gust = 8. dg. h gust pag 460, Lins 2-22 pag 46, Lins pag 466, Lins pag 466, Lins29-3 Rfnc should b: Roskam, J.; Aiplan Dsign, Pats I though VIII; Dsign, Analysis, and Rsach Copoation, 440 Wakausa Div Suit #500, Lawnc, KS 66049, USA; 990 Addss should b: 440 Wakausa Div Suit #500, Lawnc, KS 66049, USA Tl Fax: Lins should ad Dsign, Analysis, and Rsach Copoation, 440 Wakausa Div Suit #500, Lawnc, KS 66049, USA Lins should ad Dsign, Analysis and Rsach Copoation, 440 Wakausa Div, Suit #500, Lawnc, KS 66049, USA Tl Fax: Appndix B Ch β should b Ch βv fo all xampls. pag 487, B2 pag 55, Appndix C pag 560, Lins8-9 C.G. location should b 0.33 c In th fist lin of txt mov th wod thos. Rfnc should b: Roskam, J.; Aiplan Dsign, Pats I though VIII; Dsign, Analysis, and Rsach Copoation, 440 Wakausa Div Suit #500, Lawnc, KS 66049, USA; 990 Eata: Aiplan Flight Dynamics and Automatic Flight Contols, Ya of Pint: 995 5