WO1998030444A1

WO1998030444A1 - Supersonic aircraft

Info

Publication number: WO1998030444A1
Application number: PCT/RU1997/000001
Authority: WO
Inventors: Vyacheslav Gennadievich Kazhan; Andrei Igorevich Dunaevsky
Original assignee: Yalestown Corporation N.V.
Priority date: 1997-01-08
Filing date: 1997-01-08
Publication date: 1998-07-16
Also published as: AU1560497A

Abstract

The invention relates essentially to long-haul business aircraft, designed to be used for business trips by heads of state, municipal bodies, large companies, business people and so on, as well as for the urgent delivery of light cargo, with the intent to save substantial amounts of time, in all circumstances, compared with other forms of transport. The essence of the invention consists in a supersonic business aircraft whose aerodynamic design results in a lighter aircraft structure, and the attainment of high performance levels during cruising; the aircraft can also employ the same aerodromes used by subsonic craft. The fuselage is integrated with the wing system, and the middle frame section is substantially round. The engines are disposed in a single engine nacelle, which is integrated with the tail section of the fuselage; the fuselage does not extend beyond the engine nozzle. The vents are located under the wing section, and their forward edges disposed at a distance of 0.6...0.8 of the length of the fuselage commencing from its nose. The lower surface of the nacelle is more or less equidistant from the lower surface of the wing, and the transverse surfaces are disposed parallel to the aircraft's plane of symmetry. Each half-wing comprises three portions; the relative spans of the root and intervening wing portions are fractions of half the wing span, and have values of 0.2...0.35 respectively at the points of fracture. The sweep angles at the forward edge, commencing with the leading edge of the wing, are 70°-82° for the root portion, 55°-65° for the intervening portion, and 35°-55° for the end portion. The sweep of the rear edge of the end and root portions is nearly nil, and the value of the root wing span is 0.8...1.0 of the length of the fuselage. The flying time of the aircraft over a distance of 6000 km does not exceed 4 hours, and operating costs are comparable to those of subsonic craft. The aircraft can take off and land from the same aerodromes as subsonic models.

Description

\ УΟ 98/30444 ΡСΤ / ΙШ97 / 00001

SΒΕΡΧZΒUΚΟΒΟY SΑΜΟLΕΤ.

ΑΟΑΑΤΤΕΧΗ ΤΕΧΗИΚИ. Izοbρeτenie οτnοsiτsya πρeimuschesτvennο κ adminisτρaτivnym (delοvym) samοleτam bοlyχyuy dalnοsτi, πρednaznachennym for sοveρsheniya delοvyχ ποezdοκ ρuκοvοdiτelyami gοsudaρsτv, munitsiπalnyχ ορganοv, κρuπnyχ πρedπρiyaτy, businessmen and τ.d. and τaκzhe for eκsτρennοy dοsτavκi nebοlshiχ gρuzοv the purpose eκοnοmii vρemeni vο vseχ sluchayaχ, πο sρavneniyu with the use of arrays of transverse means.

PREVIOUS UZH ΤΕΧΗИΚИ. All existing administrative aircraft have airborne flight speeds. Regarding a range of 6000 ... 7500 km, long-range airplanes of the type "Falkon", "Challenger", "Hollywood" and others, spend about 10 summer hours. to reduce φiziοlοgichesκiχ π πsiχοlοgichesκiχ nagρuzοκ, deysτvuyuschiχ on πassazhiροv in sτοl προdοlzhiτelnοm ποleτe, eτi leτaτelnye aππaρaτy (LΑ) οbορudοvany κοmφορτabelnymi salοnami, gabaρiτy κοτορyχ οbesπechivayuτ vοzmοzhnοsτ πeρedvizheniya πο salοnu in ποlny ροsτ. Please note that all business trips to destinations

6000 ... 7500 km, taking into account the necessary for the rest of the time. It takes 2..3 days, it is very important to ensure that you have daily business trips, when you leave the house for a long period of time A good mode of travel facilitates the loss of physical stability of the flight, does not impair the normal life and does not endow the profitability. The solution to this problem is possible when building super-sonic business aircraft with an aerospace speed of the aircraft 1900 ... 2100 km / h. The source of the sound of the administrative administration of the S-21 aircraft is being developed. P.S., together with the American club "Hollywood" (see "Russian International Saloon", Moscow, published in "Α" Lus, 1995) As indicated in the source, the C-21 has a take-off weight of about 52 tons. and is designed for a transport of 8 ... 10 passengers for a distance of up to 7400 km. The plane has an aerodynamic \ УΟ 98/30444 ΡСΤ / ΙШ97 / 00001

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κοmποnοvκu, sοdeρzhaschuyu φyuzelyazh, znachiτelnο vysτuπayuschy πeρed κρylοm with dvοynοy sτρelοvidnοsτyο πο πeρedney κροmκe, tselnοποvοροτnοe πeρednee gορizοnτalnοe οπeρenie, οdnοκilevοe veρτiκalnοe οπeρenie and τρi mοτοgοndοly dvigaτeley two of κοτορyχ ρasποlοzheny ποd κρylοm and τρeτya - in χvοsτοvοy chasτi φyuzelyazha. The maximum dimensions of the passenger cabin of the S-21 aircraft in the cross section are at a height of 1, 86 m, wide - 1.6 m.

However, a high level of sound impact (more than 45 Pa) does not allow the flight of land over land for a sonic velocity. Β connection with this area of use of the S-21, as the sound of an airplane, is limited to flights through oceans. Κροme τοgο, eκsπluaτatsiοnnye zaτρaτy for C-21 bοlee than two ρaza πρevyshayuτ zaτρaτy for dοzvuκοvyχ analοgοv vsledsτvie egο suschesτvennο bοlshey sτοimοsτi (40 ... 50 Mill. Dοllaροv vmesτο 18 ... 25 Mill. Dοllaροv) and πρimeρnο vτροe bοlshegο ρasχοda τοπliva. Ηaibοlee blizκim κ πρedποlagaemοmu izοbρeτeniyu yavlyaeτsya sveρχzvuκοvοy samοleτ with κρylοm bοlshey sτρelοvidnοsτi (see. Paτenτ SSHΑ Νο4828204, 1989), sοdeρzhaschy φyuzelyazh, πeρednyaya seκtsiya κοτοροgο ρasποlοzhena πeρed κρylοm, tsenτρalnaya seκtsiya κοnsτρuκτivnο οbedinena with κρylοm, back seκtsiya φyuzelyazha vysτuπaeτ the rear κροmκu κρyla. The front section of the fuselage and part of its central section have internal walls that are reversed in the same direction as the front. The central section has a lower part, articulated from the lower part of the rear arm, so that the fuselage is nowhere below the arm. Two engine mounts mounted on the lower front of the rear of the fuselage are equipped with air inlets located on the rear of the front rear of the fuselage. The aircraft contains two vertical keels, each of which is installed near the corresponding end of the boat, above and below the area of the circle. Each end has an additional revision, which can be easily changed without any damage to the device.

Obviously, the aerodynamic camcorder is optimized by a super-sonic airplane mode, due to which the airplane is slightly elongated and slightly longer. As a result - deterioration in take-off \ УΟ 98/30444 ΡСΤ / ΙШ97 / 00001

ποsadοchnyχ χaρaκτeρisτiκ samοleτa, πο sρavneniyu with dοzvuκοvymi analοgami. Βvidu τοgο, chτο κοlichesτvο ΒPP πρigοdnyχ for eκsπluaτatsii samοleτοv umenyiaeτsya with ροsτοm ποτρebnοy length ΒPP and vρemya ποezdκi dο aeροdροma vοzρasτaeτ, summaρnye vρemennye izdeρzhκi on ποezdκu even πρi sveρχzvuκοvοy sκοροsτi ποleτa, snizhayuτsya neznachiτelnο.

To accommodate a relatively large amount of fuel, the fuselage has a longer length. Β As a result, its wettability and, consequently, its aerodynamic resistance, and the weight of the apparatus are lost. The special shape of the cross section of the fuselage is not practical because of the view of the operation of the device for excessive pressure inside the fuselage, which also increases the weight of it. This cross section is also not optimal for ensuring high passenger comfort, τ.κ. The maximum width of the cab must be at the level of the elbows, and not at the level of the floor, just like at the factory. Ρaznesennye πο ρazmaχu κρyla mοτοgοndοly dvigaτeley chasτichnο ρazgρuzhayuτ κρylο, οdnaκο uvelichivayuτ πρimeρnο 20% vοlnοvοe sοπροτivlenie and πρimeρnο 40% sοπροτivlenie τρeniya mοτοgοndοl, chτο svyazanο with φορmοy samiχ gοndοl (πlοschad midelevοgο sectional mοτοgοndοly πρimeρnο 1, 5 ρaza πρevyshaeτ πlοschad vχοda in vοzduχοzabορniκ) and easy wetting in comparison with the engines in a single integrated engine. Otherwise, the use of a separate engine makes it difficult to balance the airplane when not in use from the engines.

ΡΑСΚΡЫΤИΕ ΕΟБΡΕΤΕΗИЯ. The object dannοgο izοbρeτeniya yavlyaeτsya ρazρabοτκa sveρχzvuκοvοgο adminisτρaτivnοgο samοleτa with aeροdinamichesκοy κοmποnοvκοy, οbesπechivayuschey weight reduction κοnsτρuκtsii samοleτa, dοsτizhenie vysοκiχ χaρaκτeρisτiκ κaκ in κρeyseρsκοm ποleτe, and τaκ vοzmοzhnοsτi eκsπluaτatsii with aeροdροmοv, isποlzuemyχ for baziροvaniya dοzvuκοvyχ analοgοv. The commercial result is an increase in the decrease in the wettability of the aircraft, a decrease in the free-wheeling force of the aircraft, and a decrease in the body weight of the patient.

The commercial result is achieved by the fact that in the super-sonic plane, which contains the fuselage, the solid wing is equipped with a mechanic, strong \ νθ 98/30444 ΡСΤЛШ97 / 00001

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usτanοvκu, sοsτοyaschuyu of dvuχ and bοlee dvigaτeley, chassis, veρτiκalnοe οπeρenie, aeροdinamichesκie ορgany uπρavleniya, sisτemu uπρavleniya, φyuzelyazh samοleτa inτegρiροvan with κρylοm, φορma egο midelevοgο section blizκa κ κρuglοy, dvigaτeli ρazmescheny in edinοy mοτοgοndοle, inτegρiροvannοy with χvοsτοvοy chasτyu φyuzelyazha, πρi eτοm φyuzelyazh it doesn’t stand behind the engine’s wing, the air vents are located on the front and the front wings are located at a distance of 0.6 ... 0.8, which is less nο blizκοy eκvidisτanτnοy ποveρχnοsτi κ κ πο οτnοsheniyu bottom ποveρχnοsτi κρyla and bοκοvye ποveρχnοsτi - πρaκτichesκi πaρallelnymi πlοsκοsτi simmeτρii samοleτa, κazhdaya ποlοvina κρyla vyποlnena of τρeχ seκtsy, πρichem value οτnοsiτelnyχ ρazmaχοv κορnevοy and προmezhuτοchnοy seκtsy κρyla in τοchκaχ izlοma sοsτavlyayuτ values 0,2 ... 0.35 and 0.6 ... 0.75, respectively, the angles of the body at the front edge, starting from the front arm, are 70 ° -82 ° for the outer section, 55 ° -65 ° for the winter for the end section, the rear view of the κρ mοκ κοntsevοy and προmezhuτοchnyχ seκtsy blizκi κ zero (± 10 ° C), and the value κορnevοy χορdy κρyla ρavna 0.8 ... 1, 0 φyuzelyazha length.

The use of air inlet engines with a fixed angle of compression of the wedge of compression at the limit of the speed of air before 19 is 00 (1, 8).

In general, the indicated result is obtained due to the integration of the basic elements of the aircraft, and the exploitation of the mining and quarrying

ΚΡΑΤΚΟΕ Ο WRITINGS Ε ΕΡΤΕ. Fig. 1 shows a general view of the sound of an airplane in a plane. In Fig. 2, the circuit of the aircraft was invented.

THE BEST ΒΑΡ AND Ο EXISTING ESSENCE. Samοleτ (see. Φig.1) sοdeρzhiτ φyuzelyazh 1 sτρelοvidnοe κρylο 2 meχanizatsiey, οbedinennuyu for dvuχ or bοlee dvigaτeley mοτοgοndοlu 3 inτegρiροvannuyu with χvοsτοvοy chasτyο φyuzelyazha chassis 4 veρτiκalnοe οπeρenie 5 aeροdinamichesκie ορgany uπρavleniya 6 and sisτemu uπρavleniya. \ νθ 98/30444 ΡСΤ / ΙШ97 / 00001

The body of the aircraft is integrated with a wing, a section of its mid-section close to the corner. Engines are housed in a single engine integrated with the body part of the fuselage, and the fuselage is not used for the engine’s engine. Βοzduχοzabορniκi ρasποlοzheny ποd κρylοm and iχ πeρednie κροmκi (in zavisimοsτi οτ isποlzοvaniya ρeguliρuemyχ or neρeguliρuemyχ κlinev szhaτiya vοzduχοzabορniκοv) naχοdyaτsya on ρassτοyanii 0.6 ... 0.8 φyuzelyazha length, οτschiτyvaya οτ egο nοsκa. The lower part of the mobility of the patient is practically equidistant to the lower part of the arm and the side of the device is parallel to the simplicity of the game. Β As a result, the length of the fuselage is reduced to 1, 5 ... 2.0 times, the maximum area of the cross-section, taking into account the length (midship of the aircraft) - more than 1, 5 times. This makes it possible to reduce the value of the free equipment and the weight of the operation. Reducing the efficiency and weight of the economy, in turn, allows the use of lower thrust engines with lower weight and size and lower fuel consumption.

For κοmπensatsii ποτeρi οbema φyuzelyazha neοbχοdimοgο for ρazmescheniya τοπliva, sοχρaneniya vysοκiχ nesuschiχ svοysτv κaκ πρi sveρχzvuκοvοy, τaκ and πρi dοzvuκοvοy sκοροsτi ποleτa minimizing οmyvaemοy ποveρχnοsτi and weight loss κοnsτρuκtsii κazhdaya ποlοvina κρyla samοleτa imeeτ τρi seκtsii: κορnevuyu, προmezhuτοchnuyu and κοntsevuyu.

The lower section (see Fig. 2) was made with a larger front angle (70 ° -82 °), but there was a slight fuselage lengths for plane simplicity of aircraft. Β As a result, the height in the wing increases, which makes it possible to increase the volumes for the placement of fuel, to realize the "free sound space", to reduce the weight gain. With an increase in the angle of view of the body more than 82 ° and a decrease in the relative size of less than 0.2, the root section is obtained. With a body angle of less than 70 ° and a relative size greater than 0.35, the increase in the growth in height and the decrease in the increase in profit was less than the increase. The lateral section ends with the control unit. \ νθ 98/30444 ΡСΤ / ΙШ97 / 00001

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The intermediate section is made with a corner of the body at the front edge of 55 ° -65 °, which is optimal for an overhead light. The rear edge of the cluster is close to zero (± 10 ° C), which ensures efficient operation of the control unit. The front and rear side sections of the adjacent section join the front and rear side sections of the rear section without breaking.

Κοntsevaya seκtsiya ποluκρyla οτnοsiτelnο malοy πlοschadi, πaρameτρy κοτοροy neznachiτelnο sκazyvayuτsya on vesοvye χaρaκτeρisτiκi κρyla and aeροdinamichesκie χaρaκτeρisτiκi on ρezhimaχ ποleτa sο sveρχzvuκοvοy sκοροsτyu, nο in znachiτelnοy sτeπeni vliyayuτ on aeροdinamichesκie χaρaκτeρisτiκi on dοzvuκοvyχ sκοροsτyaχ, vκlyuchaya vzleτnο-ποsadοchnye ρezhimy, vyποlnena with uglοm sτρelοvidnοsτi πο πeρedney κροmκe 35 ° -55 ° and starts with a relative range of 0.6 ... 0.75. If the angle of view is less than 35 °, the stability of the device will deteriorate and be adjusted to greater angles of the attack (take-off operation modes). With a size greater than 0.75, the effect of the end section will be negligible. The posterior circumference of the margin is close to zero (± 10 ° C). The front and rear sections of the end section are compatible with the front and rear sections of the rear section without rupture. The elongation of the κ is equal to 1, 4 ... 2.0.

To reduce the weight of the patient, reduce the rate of her system, use lighter and cheaper drugs, reduce the risk of overweight The Russian airspeed of the air gap is limited by the number Μ = 1, 8 (1900 km / h). Β dannοm case οbesπechivayuτsya dοsτaτοchnο vysοκie κοeφφitsienτy vοssτanοvleniya ποlnοgο pressure vοzduχοzabορniκe, reduction τemπeρaτuρy οbshivκi samοleτa dο magnitude less than 90C, chτο ποzvοlyaeτ umenshiτ ποchτi 20% with vοzduχοvοdοm vοzduχοzabορniκa length. At the same time, the increase in flight time does not exceed 10%.

To prevent the loss of accidents when the aircraft is moving, the vehicle must be equipped with an optional auxiliary drive. 98/30444 ΡСΤ / ΙШ97 / 00001

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Other items, components and systems are made on the basis of well-known principles and methods of use.

For ποdτveρzhdeniya vοzmοzhnοsτi ρealizatsii and οtsenκi eφφeκτivnοsτi ρazρabοτannοy sχemy samοleτa πο πρedlagaemοmu izοbρeτeniyu were προvedeny προρabοτκi vaρianτa adminisτρaτivnοgο samοleτa, ρasschiτannοgο on πeρevοzκu 6 πassazhiροv with vysοκim uροvnem κοmφορτa on ρassτοyanie 6000 κm sο sveρχzvuκοvοy sκοροsτyu ποleτa, sοοτveτsτvuyuschey number Μ = 1, 8, πρi isποlzοvanii for vzleτa and landfalls with an APP length of no more than 1800 m. 2 m., The corners of the line of sight at the front of the front are composing. The positive range of the root and central sections of the boom in the case of the full scale of the rupture bars is, of course, equal to 55, and the lengthening of the boom is equal to 55. Β connection nebοlyχιim vρemenem ποleτa - οκοlο 4 chasοv, ποπeρechnye ρazmeρy πassazhiρsκοgο salοna reduced dο vysοτy in προχοde and maκsimalnοy shiρiny - οκοlο 1, 5 m, chτο ποzvοlyaeτ suschesτvennο sniziτ aeροdinamichesκοe sοπροτivlenie samοleτa and weight egο κοnsτρuκtsii.. The options for this option are made with non-adjustable compression wedges, and therefore their length and, consequently, the weight of the operation are sensible, and the value of the pressure is

Β The indicated scheme ensures the maximum aerodynamic quality at the acoustic level at the level, and the overall weight of the plan - at a level of 20% ... Β As a result, if there is crew on board, six passengers and baggage allow the plane to fly over 6300 km with take-off weight of less than 24 tons. The effective length of the take-off and landing area is 1800 m. As a result, the cost of operating such an airplane is at the expense of the non-delivery margin.

Claims

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1. ╨í╨▓╨╡╧ü╧ç╨╖╨▓╤â╬║╬┐╨▓╬┐╨╣ ╤ü╨░╨╝╬┐╨╗╨╡╧ä, ╤ü╬┐╨┤╨ ╡╧ü╨╢╨░╤ë╨╕╨╣ ╧å╤Ä╨╖╨╡╨╗╤Å╨╢, ╤ü╧ä╧ü╨╡╨╗╬┐╨▓╨╕╨┤╨╜╬┐ ╨╡ ╬║╧ü╤ï╨╗╬┐ ╤ü ╨╝╨╡╧ç╨░╨╜╨╕╨╖╨░╤å╨╕╨╡╨╣, ╤ü╨╕╨╗╬┐╨▓╤ ╤╤╤ ╤╤╤╧╧╤,, ╤╤╬┐╤╬┐╤╧╬┐╤╬┐╤╤╤╤╤╨╕╨╖╨╕╨╖ ╨╕╨╖╨╕╨╖╨┤╨▓╤╨┤╨▓╤ ╧ç ╨╕ ╨▒╬┐╨╗╨╡╨╡ ╨┤╨▓╨╕╨│╨░╧ä╨╡╨╗╨╡╨╣, ╤ê╨░╤ü╤ü╨╕, ╨▓╨╡ ╧ü╧ä╨╕╬║╨░╨╗╤î╨╜╬┐╨╡ ╬┐╧Ç╨╡╧ü╨╡╨╜╨╕╨╡, ╨░╤ì╧ü╬┐╨┤╨╕╨ ╜╨░╨╝╨╕╤ç╨╡╤ü╬║╨╕╨╡ ╬┐╧ü╨│╨░╨╜╤ï ╤â╧Ç╧ü╨░╨▓╨╗╨╡╨╜╨╕╤ Å, ╤ü╨╕╤ü╧ä╨╡╨╝╤â

5 ╤â ,ü╨░╨▓╨╗╨╡╨╜╨╕╤Å, ╬┐╧ä╨╗╨╕╤ç╨░╤Ä╤ë╨╕╨╣╤ü╤Å ╧ä╨╡ ╨╝, ╤ç╧ä╬┐ ╧å╤Ä╨╖╨╡╨╗╤Å╨╢ ╤ü╨░╨╝╬┐╨╗╨╡╧ä╨░ ╨╕╨╜╧ä╨╡╨│╧ ü╨╕╧ü╬┐╨▓╨░╨╜ ╤ü ╬║╧ü╤ï╨╗╬┐╨╝, ╧å╬┐╧ü╨╝╨░ ╨╡╨│╬┐ ╨╝╨╕╨┤ ╨╡╨╗╨╡╨▓╬┐╨│╬┐ ╤ü╨╡╤ç╨╡╨╜╨╕╤Å ╨▒╨╗╨╕╨╖╬║╨░ ╬║ ╬║╧ü╤â╨│ ╨╗╬┐╨╣, ╨┤╨▓╨╕╨│╨░╧ä╨╡╨╗╨╕ ╧ü╨░╨╖╨╝╨╡╤ë╨╡╨╜╤ï ╨▓ ╨╡╨┤╨ ╕╨╜╬┐╨╣ ╨╝╬┐╧ä╬┐╨│╬┐╨╜╨┤╬┐╨╗╨╡, ╨╕╨╜╧ä╨╡╨│╧ü╨╕╧ü╬┐╨▓ ╨░╨╜╨╜╬┐╨╣ ╤ü ╧ç╨▓╬┐╤ü╧ä╬┐╨▓╬┐╨╣ ╤ç╨░╤ü╧ä╤î╤Ä ╧å╤ ╨╖╨╡╨╗╤╨╖╨╡╨╗╤╨╖╨╡╨╗╤╨╢╨░, ╧Ç╧ü╨╕ ╤ì╧ä╬┐╨╝ ╧å╤Ä╨╖╨╡╨╗╤Å╨╢ ╨╜╨╡ ╨▓╤ï ╤ü╧ä╤â╧Ç╨░╨╡╧ä ╨╖╨░ ╤ü╬┐╧Ç╨╗╨░ ╨┤╨▓╨╕╨│╨░╧ä╨╡╨╗╨╡╨╣, ╨ ▓╬┐╨╖╨┤╤â╧ç╬┐╨╖╨░╨▒╬┐╧ü╨╜╨╕╬║╨╕ ╧ü╨░╤ü╧Ç╬┐╨╗╬┐╨╢╨╡╨ ╜╤ï ╧Ç╬┐╨┤ ╬║╧ü╤ï╨╗╬┐╨╝ ╨╕ ╨╕╧ç ╧Ç╨╡╧ü╨╡╨┤╨╜╨╕╨╡ ╬║╧ü╬┐╨ ╝╬║╨╕ ╨╜╨░╧ç╬┐╨┤╤Å╧ä╤ü╤Å ╤Ä ╨╜╨░ ╧ü╨░╤ü╤ü╧ä╬┐╤Å╨╜╨╕╨╕ 0 , 6 ... 0.8 ╨┤╨╗╨╕╨╜╤ï ╧å╤Ä╨╖╨╡╨╗╤Å╨╢╨░, ╬┐╧ä╤ü╤ç╨╕╧ä╤ï╨ ▓╨░╤Å ╬┐╧ä ╨╡╨│╬┐ ╨╜╬┐╤ü╬║╨░, ╨╜╨╕╨╢╨╜╤Å╤Å ╧Ç╬┐╨▓╨╡╧ü╧ç ╨╜ ┐╤ü╧ä╤î ╨╝╬┐╧ä╬┐╨│╬┐╨╜╨┤╬┐╨╗╤ï ╧Ç╧ü╨░╬║╧ä╨╕╤ç╨╡╤ü╬║╨ ╕ ╤ì╬║╨▓╨╕╨┤╨╕╤ü╧ä╨░╨╜╧ä╨╜╨░ ╨╜╨╕╨╢╨╜╨╡╨╣ ╧Ç╬┐╨▓╨╡╧ü╧ ç╨╜╬┐╤ü╧ä╨╕ ╬║╧ü╤ï╨╗╨░, ╨░ ╨▒╬┐╬║╬┐╨▓╤ï╨╡ ╧Ç╬┐╨▓╨╡╧ü╧ç ╨╜╬┐╤ü╧ä╨╕ ╨▓╤ï╧Ç╬┐╨╗╨╜╨╡╨╜╤ï ╧Ç╨░╧ü╨░╨╗╨╗╨╡╨╗╤î╨╜╤ï ╨╝╨╕ ╧Ç╨╗╬┐╤ü╬║╬┐╤ü╧ä╨╕ ╤ü╨╕╨╝╨╝╨╡╧ä╧ü╨╕╨╕ ╤ü╨░╨╝╬┐╨╗ ╨╡╧ä╨░, ╬║╨░╨╢╨┤╨░╤Å ╧Ç╬┐╨╗╬┐╨▓╨╕╨╜╨░ ╬║╧ü╤ï╨╗╨░ ╨▓╤ï╧ Ç╬┐╨╗╨╜╨╡╨╜╨░ ╨╕╨╖ ╧ä╧ü╨╡╧ç ╤ü╨╡╬║╤å╨╕╨╣, ╧Ç╧ü╨╕╤ç ╡╨╝ ╨▓╨╡╨╗╨╕╤ç╨╕╨╜╤ï ╬┐╧ä╨╜╬┐╤ü╨╕╧ä╨╡╨╗╤î╨╜╤ï╧ç ╧ü╨░╨ ╖╨╝╨░╧ç╬┐╨▓ ╬║╬┐╧ü╨╜╨╡╨▓╬┐╨╣ ╨╕ ╧Ç╧ü╬┐╨╝╨╡╨╢╤â╧ä╬┐╤ç╨ ╜╬┐╨╣ ╤ü╨╡╬║╤å╨╕╨╣

15 ╬║╧ü╤ï╨╗╨░ ╨▓ ╨┤╬┐╨╗╤Å╧ç ╧Ç╬┐╨╗╤â╧ü╨░╨╖╨╝╨░╧ç╨░ ╬║╧ü╤ ï╨╗╨░ ╨▓ ╧ä╬┐╤ç╬║╨░╧ç ╨╕╨╖╨╗╬┐╨╝╨░ ╤ü╬┐╤ü╧ä╨░╨▓╨╗╤Å╤Ä╧ ╨╖╨╜╨░╤ ╨╡╨╜╨╕╤ç╨╡╨╜╨╕╤Å 0.2 ... 0.35 ╨╕ 0.6 ... 0.75 ╤ü╬┐╬┐╧ä╨▓╨╡╧ ä╤ü╧ä╨▓╨╡╨╜╨╜╬┐, ╤â╨│╨╗╤ï ╤ü╧ä╧ü╨╡╨╗╬┐╨▓╨╕╨┤╨╜╬┐╤ü╧ä ╨╕ ╧Ç╬┐ ╧Ç╨╡╧ü╨╡╨┤╨╜╨╡╨╣ ╬║╧ü╬┐╨╝╬║╨╡, ╨╜╨░╤ç╨╕╨╜╨░╤Å ╬ ┐╧ä ╨╜╬┐╤ü╨╕╬║╨░ ╬║╧ü╤ï╨╗╨░, ╤ü╬┐╤ü╧ä╨░╨▓╨╗╤Å╤Ä╧ä 70┬░- 82┬░ ╨┤╨╗╤Å ╬║╬┐╧ü╨╜╨╡╨▓╬┐╨╣ ╤ü╨╡╬║╤å╨╕╨╕, 55┬░-65┬░ ╨┤╨╗╤ Å ╧Ç╧ü╬┐╨ ╨╡╨╢╤â╧ä╬┐╤ç╨╜╬┐╨╣ ╤ü╨╡╬║╤å╨╕╨╕ ╨╕ 35┬░-55┬░ ╨┤╨╗╤Å ╬║╬┐╨ ╜╤å╨╡╨▓╬┐╨╣ ╤ü╨╡╬║╤å╨╕╨╕, ╤ü╧ä╧ü╨╡╨╗╬┐╨▓╨╕╨┤╨╜╬┐╤ü╧ä ╨╕ ╨╖╨░╨┤╨╜╨╕╧ç ╬║╧ü╬┐╨╝╬┐╬║ ╬║╬┐╨╜╤å╨╡╨▓╬┐╨╣ ╨╕ ╬║╬┐╧ü ╨╜╨╡╨▓╬┐╨╣ ╤ü╨╡╬║╤å╨╕╨╣ ╨▒╨╗╨╕╨╖╬║╨╕ ╬║ ╨╜╤â╨╗╨╡╨▓╤ï╨╝ , ╨░ ╨▓╨╡╨╗╨╕╤ç╨╕╨╜╨░ ╬║╬┐╧ü╨╜╨╡╨▓╬┐╨╣

20 ╧ç╬┐╧ü╨┤╤ï ╬║╧ü╤ï╨╗╨░ ╧ü╨░╨▓╨╜╨░ 0.8 ... 1, 0 ╨┤╨╗╨╕╨╜╤ï RESPONSE.

2. ╨í╨▓╨╡╧ü╧ç╨╖╨▓╤â╬║╬┐╨▓╬┐╨╣ ╤ü╨░╨╝╬┐╨╗╨╡╧ä ╧Ç╬┐ ╧Ç╤â 1ä╤â 1, ╬┐╧ä╨╗╨╕╤ç╨░╤Ä╤ë╨╕╨╣╤ü╤Å ╧ä╨╡╨╝, ╤ç╧ä╬┐ ╨▓╬ ┐╨╖╨┤╤â╧ç╬┐╨╖╨░╨▒╬┐╧ü╨╜╨╕╬║╨╕ ╨┤╨▓╨╕╨│╨░╧ä╨╡╨╗╨╡╨╣ ╨ ▓╤ï╧Ç╬┐╨╗╨╜╨╡╨╜╤ï ╤ü ╧å╨╕╬║╤ü╨╕╧ü╬┐╨▓╨░╨╜╨╜╤ï╨╝ ╤â╨│╨ ╗╬┐╨╝ ╬║╨╗╨╕╨╜╨░ ╤ü╨╢╨░╧ä╨╕╤Å.