SU835023A1 - Transport aircraft - Google Patents

Abstract

1. A TRANSPORTATION AIRCRAFT, comprising a hull-wing, made in the form of a circular search, vertical and horizontal onepe-ration, control system i chassis, crew cabin, propulsion system, fuel tanks, payload compartment, lt t and In order to improve aerodynamically > & <, technical and operational characteristics, the engines are installed on the upper surface of the wing body evenly over its span. 2 о Apparatus according to „1 , from l and h and yushi and with the fact that the profile of the hull-wing is made quasi RkriticmoZo Apparatus according to p. 1, of T l and c a yu-shi. and with the fact that, in order to transport large lots of equipment and large contingents of passengers and to increase the efficiency of loading and unloading, the payload compartment. It is double-decked and is divided along the axis of symmetry by a rigid partition, with the front and rear cargo doors on the lower deck, and the upper deck is connected to the lower deck by stairs, ^. The apparatus according to claim 1, clause 1 and 2 with the fact that, for the purpose of transporting bulky cargoes, OT'- the payload is made single-deck.5. The apparatus according to claim 1, tl and h Yu and y with the fact that the vertical tail is made in the form of two oblique carinae, which are in the place of intersection '; not connected to the horizontal tail B6, Apparatus according to claim, 5, of tl and h and y and c 'so that the horizontal tail is made in the form of a disk, 7o Apparatus of Po 3, about t of l and h of a- u and with the fact that, for the purpose of operational landing, there are hatches mounted on the rear cargo doors.

Description

The invention relates to aeronautical engineering and is intended for the transport of large quantities of passengers, cargo and equipment for various purposes with a large total weight with subsonic cruising flight speed.

long and medium range. TLA operation can be carried out from aerodromes and landing sites with both hard surface and ground.

coating.

I. ... A military transport aircraft made according to a high-winged layout and containing a fuse, a straight wing, T-shaped tail, a propulsion system, a control system, a fuel system, a crew cabin, a payload compartment and a landing gear; while two turbojet engines with a high degree of bypass ratio are installed on the upper surface of the wing, symmetrically with respect to the longitudinal axis, blowing a part of its upper surface; the wing has a thick supercritical profile and mechanization; Kruger shield with a boundary layer control system on the toe, flap with an engine-blown top surface, two-section two-slot double flap, interceptors and ailerons Fuel compartment tanks are located in the wing, the fuse is technologically divided into three sections: bow (crew cabin), central (cargo cabin) and tail, where the cargo door is made. The disadvantages of this aircraft are due to the local blowing of the upper surface of the wing with gas jets of engines, a small increase in the coefficient of lift and aerodynamic quality; the insufficient power of the aircraft and the limited dimensions of the cargo compartment do not allow transport; cargo and equipment of large weights and dimensions; low efficiency of loading the unloading of goods and equipment, as in the cargo compartment there is only one input-output through the rear cargo frame pu, which increases the loading time of the unloading and complicates the loading and loading times; short range (the maximum range with a load of 12.25 tons is about 2000 km). The closest of the known technical solutions is an aircraft, comprising a hull-wing made in the form of a circular disk, a propulsion system, a control system, fuel tanks, a compartment of a cargo load box, a crew cabin and a chassr, while there are two in the propulsion unit front and two rear turbojets installed on the upper surface of the casing-wing si P3 metrically relative to the longitudinal axis of the apparatus; there are also four fans installed in the casing-fender, which are driven by gas intake in from the main engines (gas drive), the fans are installed symmetrically relative to the longitudinal axis of the apparatus; the moats of the rear main engines mounted on the platforms have the ability to rotate around the vertical axis on to provide a vertical take-off (landing) rear main engines oriented 180 relative to the front main engines, and the exhaust gases of all. main engines are directed through branch ducts and ejected through the exhaust nozzles down under the bottom of the apparatus, creating together with the valve Field proof operation pressure under the bottom of the apparatus; The crew cabin and passenger cabin are mounted in the center of the vehicle, both cabins are a structure that is separated from the rest of the structure. apparatus and is equipped with four parachutes and brake rockets for fear in emergency situations. The drawbacks of this apparatus are as follows: the design and construction scheme of the apparatus does not ensure that it receives acceptable values of lift coefficient and aerodynamic quality in the range of medium and large heights and in the range of medium and large subsonic flight speeds (the device is designed for vertical take-off and landing 1 and flying at low altitudes with small subsonic speeds, where integraln1y with ground effect both due to the size and shape of the apparatus in the plan and by directing part gazovozdush- Nogo flow from the motors and the fans under the bottom of the apparatus); the lack of reliability of the system of stabilization and control of the apparatus, realized by means of ring gyroscopic masses associated with fans, creates dangerous emergencies in the event of failure of at least one fan; the location of the cockpit in the center of the apparatus makes it very difficult for the crew to take off during takeoff and landing, and especially for the lower hemisphere, which reduces flight safety; the complexity of the operation of the power plant, including in its. the composition of the main engines, gas-driven fans from the main engines and long channels for the removal and selection of gases; the layout of the device does not provide loading and unloading and transportation of goods and equipment of large weights, rats (this device is designed to carry only passengers). The purpose of the present invention is to improve the aerodynamic, flight technical and operational characteristics of the apparatus. This goal is achieved by the fact that the transport aircraft, comprising a wing-body, made in the form of a circular disc, has vertical and horizontal empennage. control system, chassis, cab ei-20 page, propulsion system, fuel tanks, payload compartment, engines are installed on the upper surface of the wing body evenly in its span. The wing profile is made quasi supercritical. In order to transport large quantities of equipment and large contingents of passengers and increase the efficiency of loading and unloading work, the payload compartment is double-decked and divided along the axis of symmetry by a rigid partition, with front and rear cargo doors on the lower deck, and the upper deck is connected to the lower deck ladder for transporting bulky cargo compartment payload made single-deck Vertical tail made in the form of two oblique carinae, which at the intersection is connected with .gorizon Talnoe plumage "In addition, the horizontal stabilizer is designed as a disk to prompt landing in the air in the rear cargo door's hatch mounted. Fig, 1 schematically shows a transport aircraft. bottom view; Fig 2 - the same, top view; FIG. 3 is the same, front view; in fig. j - the same, side view; in FIG. 5, the same, rear view; Fig. 6, the design of the Silyov apparatus; 5 the middle part of the ororpus-wing, along the passage of Figo 7, section A-A in Fig. 6; FIG. 8 is a section BB in FIG. 6; in fig. 9 is a sectional view BB in FIG. 6; in fig. 10 shows a section of YYY in FIG. 7; at 83502 0 15

axis, and for a better view, you are: carried forward.

In the central part of the wing-hull, the lower deck of the k / Fig. 11 - permitting D-D ia (ng 7 (view and plan of the bottom, cargo deck); in fig. 12 - section E-and nl of fig 7 (single-deck variant of the payload). The transport aircraft (TLA) is a dirkoplan whose hull-wing 1 is circular in shape, and the hull-wing profile is made quasi-supercritical; almost the entire upper surface of the hull-wing is blown by gas jets emanating from the profiled nozzles 2 of the engines 3 installed uniformly and discretely in proportion to the hull-wing on surface (Fig. 1-7). The rear part of the wing hull, on its upper surface, are located the keels with steering wheels 5, the keels are spaced symmetrically relative to the longitudinal axis of the TLL, fixed on the longitudinal power profiled trusses 6 of the wing structure and set at an angle so that at the intersection of their end chords a rigid console 7 is formed, and the horizontal tail assembly is mounted on it, which includes a stabilizer 8 and a four-section elevator 9 (FIG. 1-7); Such a combined arrangement of vertical-horizontal tail allows not only efficient use of vertical tail to create yaw control moments, but also partly on pitch and roll, which reduces the area of horizontal tail, increases the rigidity of vertical-horizontal tail, and also reduces the area of three sections. hanging ailerons 10, which are the main rolls on the roll and installed at the rear edge of the body of the wing symmetrically with respect to the longitudinal axis of the TLA; there are four sections between the kilks in the aft of the wing; four sections; akrylkov 11; to increase the lateral stability of TLA at low speeds; flight X during landing) on the end surface of the wing housing there are side flaps 12 deflecting down (Fig. 1-7). The cockpit 13 is installed in the upper passenger deck 15, which are interconnected by ladders 16, loading and unloading of cargo and equipment and disembarking passengers disembarking through the front 17 and rear 18 cargo ramps (doors) located symmetrically relative to the longitudinal axis The loading and unloading of vehicles and cargoes and the boarding / disembarking of passengers can be performed in parallel (simultaneously) through the front and rear cargo doors (Fig. 7, -11). Along the longitudinal axis of the apparatus, a vertical partition wall 15) is made, which divides the upper and lower decks into two sections, in each section of the cargo compartment the floor is marked with tracks 20 for installation of equipment and cargo For opening air in the rear cargo doors are mounted flying central Liu 21 (Fig „2.9-11). On the upper deck in the front part there are kitchens (buffets) 22, and between passenger seats 23 there are aisles 24, the rows of seats are separated by longitudinal tracks 25; smoking rooms are located in the rear part of the upper deck.26, from which there are exits along the corridors 27 of the toilet rooms 28 (figo 9,10); Emergency hatches (doors) 29 with folding ladders installed in them (Fig. 2, 6) were made on the ceiling of passenger compartments. To increase rigidity, design, reduce its weight and give the required shape to the TLA frame, the wing-body power circuit is included an annular. force profiled truss 30, with which a longitudinal-transverse power set (to which the skin is attached) is mounted, which includes longitudinal force profiled trusses 6, longitudinal reinforcements profiled elements 31 and transverse reinforcements other elements (stringers) 32; trusses 6 include shelves 33, spacers .3 and reinforcement struts 35 (Figs. 6-9). The Zb fuel tanks are installed in the area of the maximum thickness of the hull-wing profile, between the payload compartment and the annular power profiled truss, while the central tanks 37 are located above the compartments of the main landing gear supports (FIG. 6). The longitudinal-transverse power set of hanging ailerons and vertically -horizontal tail includes spars 38, stringers 39 and ribs AO (figs 6.7) with TLA has a three-support chassis, while the main pillars k include four two-wheel paired struts, and the nose support 42 has two three-wheeled twin racks; for cleaning the carriages of the chassis in the housing-wing TLA, niches are made respectively for the main supports 43 and for the nose support t (Fig. 1-7) o The payload compartment 5 is made in the central part of the wing-hull double-deck, however, in the variant TLA for the transport of large loads and equipment, compartment 45 is single-deck, without a stiffness partition along the longitudinal axis of the device (FIG. 7, 7, 12), the cargo compartment 46 is connected to the passenger compartment 47 with ladders 1b. Continuing rear cargo doors are side doors 4P, opening only on the ground at loading machinery and high-altitude cargo (fig about 1) The design and layout scheme of the proposed APS provides the following main advantages: the machine is completely anti-stopping, since the conditions for autorotation of the wing housing are not created for APS; the possibility of obtaining for the proposed apparatus with a small elongation (1 1.274) a high aerodynamic quality value in the cruise flight mode (K 17-19) due to application of the quasi supercritical hull-wing profile and continuous separation of virtually all its upper surface by gas jets emanating from the profiled nozzles of engines installed on the upper surface of the wing casing uniformly and discretely along its span (due to an increase in the velocity circulation around the wing wing contour almost all its time axy); mechanization of the wing hull practically throughout its span, taking into account the high value of the screen effect of the wing hull, provides high values of the lift coefficient, P3 on the take-off and landing modes of the TLA, reducing the speed of separation and landing (landing) by approximately 30, and the length of the run-up and run almost doubled; the use of a quasi-supercritical profile with a thickness of 12-1b for the TL hull-wing makes it possible to obtain large useful volumes inside the wing for accommodating fuel, equipment, chassis, payload, and the payload compartment is 2.5 times larger; The organic combination of the hull and wing properties in the TLA provides it with both a high structural rigidity and a more uniform distribution of all types of load on the structure in flight, which leads to a reduction in the weight of the structure approximately to the greater width of the payload compartment in the TLA. a compartment of a rear group and a group of front cargo doors, which significantly increases the efficiency of loading and unloading operations (loading and unloading from the front and rear cargo doors is parallel); high aerodynamic characteristics of TLA in combination with the selected power plant provide it with a high subsonic flight speed (at 850 km / h, H cruising mode 11 km); direct operating costs are reduced by 10 to 15 times in terms of tonne-kilometer of transported payload; the direct economic effect from the implementation of this proposal (based on the maximum payload of one vehicle, equal to about 80%) for the needs of transport in various parts of the national economy of the country is approximately 15 billion rubles per year; The proposed TLA, after its development, will have a high constructive-technological continuity, as it will allow as soon as the industry is ready to switch to hydrogen fuel, and later on to nuclear and modern energy; the implementation of this proposal will lead to a significant decrease in flight intensity on the country's domestic airlines, with a significant increase in traffic volume and increase in flight safety, as well as to a decrease in environmental pollution compared to the most powerful aircraft in terms of payload approximately 10 times per tonne of transported payload). j-ht /; / 7,412 ig.Z /. «.V fc.7

33 33 34 3

J6 J6 7e 6} / 5 fff fi 6-6 Figure 9

Claims (7)

1. TRANSPORT AIRCRAFT, comprising a wing-shaped body made in the form of a circular disk, vertical and horizontal operation, control system, landing gear, crew compartment, propulsion system, fuel tanks, payload compartment, tail with the fact that, in order to improve aerodynamic, flight-technical and operational characteristics, the engines are installed on the upper surface of the wing-body evenly in its span, 2, The apparatus according to claim 1, whether the rain and the second are due to the fact that the wing profile is quasi-supercritical, 3 "The apparatus according to claim 1, about T l and h a rain and. th with the fact that, in order to transport 2 ировки quotes of large batches of equipment and large contingents of passengers and increase the efficiency of loading and unloading operations, payload compartment. made of two-deck and divided along the axis of symmetry by a rigid partition, while the front and rear cargo upper deck are connected to the stairs on the lower deck, 4. The apparatus according to π, 1, from w and h with the fact that for the purpose of tirovaniye bulky goods, from * · sec payload is made single deck, 5. The apparatus according to claim 1, characterized in that the vertical tail is made in the form of two inclined keels, which are connected at the intersection with the horizontal tail, 6. The apparatus according to claim 5, is distinguished by the fact that the horizontal tail is made in the form of a disk, 7. The apparatus according to claim 3, with rain and the fact that, for the purpose of operational landing, hatches are mounted on the rear cargo doors. the doors, and the bottom run wild