SCIENTIFIC ABSTRACT FR:HADAMEK, V. TO:HACHLER, E.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R000617800044-6
• Release Decision: RIP
• Original Classification: U
• Document Page Count: 1
• Document Creation Date: November 2, 2016
• Sequence Number: 44
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTR

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Ali`.~.iIOR: IIadar~olc, Vladic~i.r
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OG: lieta7lur~-i.cal Pro j�cts ~ Ostrava (llutni I'ro j~Ict) r
~1'IT:CL; II�a't lossr,s in boating of u3r for blast furnaco~,~~
SOt1)ZQia: Iiutnik, too. 12~ 196~~ .~3-527
TOF;I:(: `L'AGS: blast furnaco, 11a~,tinl;, Bout loss ~ Moat of cominzstion, Iaout insulation,
air ~oator
Rti'I;~;1~7.': The air tetrrp~arature influ~:~nctii~ the comb~istion t�mper--
at;ure on the Erato, and the consumption of Lhc3 colts. The causos
of boat loss�s from tho air bo~woon tho air hectors And the- air
in:Lot into tho fwrnaao aro aniilyzod. Locations o.f possiblo
lor~l~s of hot air to tho a-l;mosplloro ar� doscribad. Location of
spats wherQ boat is lost by radiation and conduction from the
air ducts is discussad. Suitablo areas wher� heat economy can
bo achieved by insulation, aro ~ivnn. The overall heat losses
from the duct aro about 12`~; substantial iml~rc~vc-,mont in olirrina- --
tion of those losses is not po:3sibin. '['h~. ~.a3avs in waste Erases
arru~unt to about 20~b of heat input; important reduction of tkte
lo::nos is not probable. When air temp�rraturos aro incroasod, M ---
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L 04879-67 J
Acc r~Ri APG0250G7 _ - ~-~~~~~~~~--~____._ __. a~
is usE~d together with the concept of "nondangerous" pants at the asymptotic stability boundary ~ I
to construct a mathematicf~l model of neutral stability. 'rwo cases of systems with variable
coefficients are examined ,which can be reduced to the ainear mcxtel with constant coefficients.
The f:trst case: is a relativE~, woak variation of the coefficients of linear approximation, and the
second, a sufficiently slow variation of those coefficients. Finally, the case is examined in ~
1
which the parameters do n~~t satisfy the necessary conditionfi for thE3 reduction o:f a system to a
linear system with constant coefficients. Characteristic for this case is the straight horizontal
flight at variable speed. using Lyapunov's direct metiioci, stabllity criteria are derived in the i
form of a necessary eondit;ion for asymptotic stability. The criteria indicate that stability lose
does not depend on velocity or acceleration, but is rattier aesociat~9 with a feature of the mo-
I
tion. Orig. art. has: 2 figures, 1 table, and 22 formiQa:s.
SUB MODE: 12,20/ SUBM DATE: 15IdovGS/ ORIG REIF: 002/ (JTH REF: 010/ SOV REF: 003
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a,cC wet AP6026oG7 -~~~ . _ .. __...._.~ ~~ .^ SOURCE COL-~; RU/0019/GG/011/002/03G3/p381
~~
AUTHOR: Hacker, T.
ORG: Institute o� Fluides I4Techanics, Acadomyof the Soci~tliat Rc~pulsllic -of Rumania, _Tucharest
(Instii~ut de Riec:snlquc~ dc~ i'luici du i'Ac7clemiC clc~ i~~ Re~~Eaubltc~cic 15ucinliste dQ Rbumsnie)
TTTI,;E: Some nonclassical problems of flight atability~ [Paper presented at the Conference on
Mechanics held.in Bucharest in September 19G5]
SOURCE: Revue Roumaine des sciences techniques. Serie do mecaniquo appliques, v. 11, no.
2, 19GG, 363-381
TOPI.G TAGS: motion stability, aerodynamic stability, mathematic maiel, stability equation,
11nea;r approximation
ABSTRACT; Several flight stability problems are discussed for wbach the mathematical model
based on linear equations with constant coefficients does not hold. The quasicriltical cars of
systems with constant parameters (autonomous systems) situatE~d at the interface between the ~
dom~~ins of asymptotic stability and instability (where linear appro~:imation no hanger describes
the actual process) is diac,ussed. Jn particular., the practical significance of the concept of
neutral stability is exar~it-ed, and the mathematical concept of prat:tidal stability (E O~st~bility")
i
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L 35874-66
ACC NR~ AFEi02~63q
,~
of thr~ fo:il.owlrtg prt.rnn~e:ters as control vt:irir~bil~r~: 1r3n~;itud.inti.l control. rnUm!~nt' the
mu.grtitude and the direction of the thru:~t, the lncidonr~e, and the slope c7f the
velocity vector with respect to the horizon. i~ptima]. tra~jectoriea of the c.g. which
are fortned by three types of curves corresponding to vertical ascent, level flight,
find fright with variat:~le flightpath att~le are ~presettted in graphs. Sotre aspects o~
the construction of thle mathematical algorithm are diel.ussed. Orig. art. hoe: 3
figures, 32 formulas ~tnd 6 tables. IAB]
8i18 CODE: 01i Ot.JIIM DAVE: 17Jen66/ ORIC} REF: OOl/ 11mD PRESSt,~~ ~~,
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At:C NR: AP6o22639 SoURGt; CO1~E
AUTHOR: Hacker, `f.
......_....-......__,.._......_._,..~_.a.._.. __ - -......___,.
Rc~/o~a19%66/0ll/00~l0~5~1ot;82 `~
OF,G: Ins3titute a_f 1{luid Meclianics~ Academy of ~tht~ ]oci.al.ist ~iepublic of F;umania (Inatitut
de Mecanique des fluides de 1'Academie de la RepubJ.iqu~a Socialists de Roumania)
TITLE: CPtimal control of a_SVTOL_aircr_aft ~~
SOURCE: Reese Roumaine~ des scienees technique9. Serie de mecanique appliques, v. ll.,
no. 3, 19bb, 659-682
TOPIC TAGS : viol aircraft , optimal control, tame optimal control, optimum tra,~ eetoz~v~,
thrust control
ABSTRACT: The problem of determining the laws of optimal control of VTOL aircraft
for ascent to a given altitude and aceeleratio~a to u given horizontal velocity in
minimum time or with minimum fuel consumption as considered. A thecretical definitior.
of the control variables according to the parameters wlaich determine the flight regin.~e
is presented on the ba~cis of the author's previous work. Adequate classification of
the variables is presented and their use in the construction of a mathematical model
based on the Pontryagin theory of the maximum is described. General equations are
derived for the case of a fixed thrust axis, then the laws of ascent and acceleration.
with minimum fuel consumption end in minimum time are established using one ar many
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APPROVED FOR RELEASE. 06/23/11 CIA-RDP86-005138000617800044-6

APPROVED FOR RELEASE: 06/23/11: CIA-R~P86-005138000617800044-6
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� � It Nitr~titxl proJucte of rtarch, lI. htvp~tration nt sUrch nilret~e from starch trtim.
� � r QIKer~nt rluutcra, II I it � ~ it a kal nvu I .nl;i ~:, I Nu t."!,1 !zKt. /.nn Teuuttss Uaowr:euu Rt>, the IuUtnvinK t.Ytiu�lusiunv atr l1faN'll
Aa inctraRe of the acid cOnC)i. cruses an (ncrrw!r cn( Utt N cuntrnt au~d +d thr v4+cusity ul
� � t ~ .. flit aitrata. Stabilizing boiling ul the nitrates lies a ticttimrntal eQtrt inducing -ie- ,~ ~
� � # i ~ nit)'ation and an isrse o+ the .t>ly. iu litAl{. '1'2-e N c.>.ttru! itirn'iw:~ with ituxeaKiug � ~ �
amR. d lIN(~ ua`d A riAC of the tcnll-, fnnn ll` ca-tae� A htwrtin~t ~>f the N ~Ymtent. Ott
� � #;'� tho yield rnd of Iho vix~f>,.ity ul the nittutrA, +-mnala-nittif t+y an inrnw+c� a( thr 1�:U-11 ~ ,~ �
� jl f rK1lU, The l'hatlijt'A Mlt prulwbly di-r to xtwu�It1arY u-iflutitu- if�urlituts mdu~r,1 br tht�
tiAr (u lr.nll-, 11'ith iucn`taing tinlr. u! cKtrtititrwu.ai th~� N Ct+nh�ut ul the ItnKlurt n+f�a ! ~ r,� �
� � ,~ i )atlbtlly at IuAt, uud thin lhr lu~rt�rt.c t~'onnrn s,trxdily anlallf r '1 hr incn�ra' �( tbt� ~ � ��
� � J ~ `~ nltrrtkui Ircthltl G-vurR aI:M1 the a11-tvtr IaYVnuluty n�actitat>0
CZECHOSLOVAKTII / Organic Chem:Lstry. Natural Sub~~taricF's G
and T!~cir ~ yntlletic li.na:lc~lt.t~~.~~
Ab s Jottr: ]i~:f Zlntr-1{himlya, No ~.3, 1)>ti, X1101
Abstract; corresponclin~ acids and c/ of the corresponding; I
and hydroc:hlor:tde of the corresponding acid in
CbH6 in the presence of aqueous P1a0H a.t about 20�.
-methoxytriptamine of PNA (V:T), meltin6 poin~
117� (from CH30H), Boas prepared of IV according;
to the method a, yielded 8~ Triptamide of 4-
metho,ty-PrTA (VTI), melting; point 155 to 156� (Cliff
OH}, ti~~as prepared of I and mcthoxy-FNA by the
rnethod b, ,yield 1+6~;, Triptam:id~~ of o(-ph~~nyliso-
but.yr'Lc acid (VIII}, inelti.n~; point 137 to 138�
(from benzene) , taas prepared of S acid IV by the
r~7ethod c, yield 91;6, Triptam:ide of PNA (IX), melt-
Card 1.G~':i.;_
APPROVED FOR RELEASE: 06/23/11: CIA-RDP86-005138000617800044-6

APPROVED FOR RELEASE. 06/23/11 CIA-RDP86-005138000617800044-6

APPROVED FOR RELEASE: 06/23/11: CIA-RDP86-005138000617800044-6

APPROVED FOR RELEASE. 06/23/11 CIA-RDP86-005138000617800044-6