RU147931U1 - FOLDABLE AIRPLANE - Google Patents

Abstract

1. A folding airplane containing an engine, a fuselage with a cockpit, a fuel tank, a wing including a center section and rotary consoles, which are connected to the center section using the main butt joints with the possibility of folding backward along the span with the possibility of rotation in one plane, and a landing gear, including main struts with wheels, characterized in that the engine is one of three possible options, and the cockpit is one of three possible options, located under the engine, either above the engine or over the elongated engine shaft spruce, fixed to the power frame of the fuselage; the main cockpit of the crew member, connected to the cockpit with the fixation elements of the crew member, - the main fuel tank installation compartment, located in the fuselage immediately behind the power frame - the centering range, is equipped with fixation elements for an additional easily removable fuel tank, load securing elements, dumped cargo, discharged weapons under which pylons of an outboard fuel tank are located; behind the cabins is the operator’s cabin of defense and attack devices; two open cockpit crew members are located on the right and left outer side surface of the fuselage and center section - the space of the fuselage and center section lanes, are equipped with crew member fixation elements; backup cabins for crew members are located in the right and left nacelles of the chassis and armaments, are equipped with elements for fixing crew members; the main part of the center section - a single unit with the fuselage - is in span equal to the rut of the main landing gear, the transformable part of the center section profile is the middle part of the wing, in terms of span

Description

A useful model of a folding airplane refers to airplanes that are suitable for transportation on any road and rough terrain, which are designed for short-term flight at extremely low altitudes (with take-off in the immediate vicinity of the flight operations area) and which provide direct support to ground forces (light attack aircraft) )

Known:

1. Aircraft with variable sweep (geometry) wing Mig 23 mld. The wing consists of a center section and two rotary wing consoles. Wing consoles fold in one plane. Synchronously, backward in scope. One swivel swivel assembly per console. Several fixed positions. The rotation device of the wing consoles is very complex and expensive;

2. Aircraft with variable sweep (geometry) of the wing F14A "Tomcat". The wing consists of a center section and two rotary wing consoles. Wing consoles fold in one plane. Synchronously, backward in scope. One swivel swivel assembly per console. Several fixed positions. The rotation device of the wing consoles is very complex and expensive;

3. Aircraft with variable sweep (geometry) wing Tu 22 m3. The wing consists of a center section, the middle part of the wing and two rotary wing consoles. Wing consoles fold in one plane. Synchronously, backward in scope. One swivel swivel assembly per console. Several fixed positions. The rotation device of the wing consoles is very complex and expensive;

The closest solution is Amphibian Sh-2 (VB Shavrov, The history of aircraft designs in the USSR until 1938, pp. 434-439. 1986, Fig. 221B).

Folding wing consoles. Back in scope. Folding the wing along the axis of the second (detachable) spar and the rear wing strut mounting bolt, the rear part of the center section chord from the second spar to the end stringer is previously raised before folding.

The wing is located relatively high, which complicates the folding work. The wing is strut, it is necessary to disconnect the struts. In the folded position, the wing additionally loads the butt assembly. The main butt nodes of the console when folding are constantly disconnected, which reduces the reliability of each node. The design does not provide for the failure of any node maintaining the performance of the airplane. Structurally, it does not have devices for loading - unloading.

The goal of the solution is to achieve extreme simplicity and speed of all work on the ground outside aerodromes and technical bases:

- to simplify the folding of the wing consoles, to provide additional structural solutions for reliability in case of failure of one or more nodes;

- simple and reliable cleaning - the release of the main landing gear;

- simple and reliable cleaning - the release of the tail landing gear;

- in the event of an emergency landing, provide the possibility of landing on the chassis in the retracted state;

- simplify installation on a vehicle for transportation;

- provide additional structural solutions to mitigate the impact (absorption of the total kinetic energy of the impact) on the surface, in the event of an emergency not releasing the main landing gear (emergency landing);

- provide for the solution of problems of emergency splashdown and stabilization on the surface of the water;

- provide for the simplest structural elements for loading onto a vehicle (as well as for lifting (landing gear before take-off);

- provide for the possibility of reducing the fuel supply and increasing the mass of weapons;

- provide for the possibility of installing an outboard fuel tank (additional easily removable fuel tank) when flying at a distance exceeding the calculated one;

- adapt the chassis design for operation from field, unpaved runways (runways), road sections;

- provide for the possibility of installing several engines, propellers in order to switch from a multi-purpose aircraft to a specialized narrow-purpose aircraft;

- provide for the installation of several cab options, depending on the engine and the task, to solve problems of improving visual visibility at extremely low altitudes;

- provide for the possibility of installing cargo, discharged cargo, discharged weapons;

1. To achieve the technical result, a folding airplane containing an engine, a fuselage with a cockpit, a fuel tank, a wing, including a center section and rotary consoles, which are connected to the center section using the main butt joints with the possibility of folding backward along the span with the possibility of rotation in one plane, and the chassis, including the main struts with wheels, is equipped with either a star-shaped air-cooled engine, or a V-shaped engine, or an in-line engine, the cockpit is located either under by the engine, either above the engine or above the elongated shaft of the engine, and the engine and the cabin are fixed to the power frame of the fuselage; the main cockpit of the crew member connected to the cockpit with the fixation elements of the crew member - the main fuel tank installation compartment is located in the fuselage immediately behind the power frame - the centering range, the cockpit is equipped with elements for fixing an additional easily removable fuel tank, load securing elements, dumped cargo, discharged weapons, under cabin crew members are pylons mounting an outboard fuel tank; behind which is the operator’s cabin of defense and attack devices; two open cockpit crew members are located on the right and left outer side surface of the fuselage and center section - the space of the fuselage and center section lanes, are equipped with crew member fixation elements; backup cabins of crew members are located in the right and left nacelles of the chassis and armaments equipped with elements for fixing crew members; the main part of the center section - the whole with the fuselage is equal in scope to the track of the main landing gear, the transformable part of the profile of the center section - the middle part of the wing is equal in scope to the distance from the side member of the wing center section to the end stringer, in which the rotary sections of the profile - left and right, are equal to the distance from the side member wing center section to the end stringer, fixed to the wing center section spar with the help of the upper wing axis and lower butt joints; two rotary

- the right and left wing consoles are attached to the center wing, with the help of the main butt nodes - hinged folding nodes - rotate the wing consoles that are installed on the wing center wing spar, the axis of the butt bolts is hollow inside, it is located vertically and the front auxiliary hinged butt nodes, the wing consoles connected to a synchronization reducer.

2. The airplane is equipped with an airbag, which is installed under the main cockpit of the fuselage and is made in the form of a float, two additional airbags are installed in the space of the landing gear and weapons.

3. The tail support of the chassis is equipped with a control and locking system.

4. The compartments of the gondolas of the chassis and armaments for the main wheels of the chassis are equipped with gates of the nacelles, the compartments for the racks are equipped with shields mounted on the rack.

5. The gondolas of the main landing gear and armaments additionally serve for the installation of defensive barrel cannon armaments; arms are controlled from all cabins.

6. In the gondolas of the main landing gear and arms, hatches were made for servicing the transformation of the wing consoles, on the rotary sections of the transformable part of the center section profile - the middle part of the wing, on the wing consoles there were handles - hand grips, steps - foot supports, for grip from the gondolas and for emphasis with the foot to duplicate the rotation of the wing consoles.

7. On the outer surface of the wing and fuselage, hand grips are installed for grabbing hands, and steps are also installed - foot supports for moving along the surface of the wing, fuselage, in the parking lot, when installed on a vehicle, in flight; in the space of the handles - grips for the hands, steps - supports for the legs installed elements of additional fixation at a given point of the wing, the fuselage - contact fixing tapes, hooks, etc.

8. In the cockpit and the cockpit of the defense and attack devices, levers and turning pedals for folding (rotary) wing consoles are installed.

9. Rotary sections - left and right, of the transformable part of the center section profile - the middle part of the wing, from the wing spar to the end stringer in order to simplify rotation, are made of several parts.

10 The airplane is equipped with a bracket for fixing the control handle in the far right position; and the ailerons control wiring located in the wing consoles and in the center section is equipped with turning units.

11. Throughout the entire scope of the center section, a landing guard is installed.

12. On the frames of the gondolas of the chassis and armaments, the struts are fixed in the folded - transport position of the folding - rotary wing consoles.

13. At the bottom of the power frame of the fuselage, towing towing loops are installed - right and left, and a through hole is made in the rear of the fuselage.

14. Upholstery, (cabin insulation) is made in the form of sets of clothes - pants, a suit, sweatshirt, mittens, etc.

The essence of the utility model is illustrated by drawings, where

FIG. 1. Schematic illustration of an airplane. View from above. Wing consoles laid out.

1 - left node folding (rotation) of the wing console;

2 - left folding (swivel) wing console;

3 - rotary section of the left transformable part of the center section profile - the middle part of the wing;

4 - left gondola chassis and weapons;

5 - flap simple landing;

6 - fuselage;

7 - horizontal plumage;

8 - vertical plumage;

9 - center section;

10 - right nacelle chassis and weapons;

11 - rotary section of the right transformable part of the center section profile - the middle part of the wing;

12 - the right node folding (rotation) of the wing console;

13 - right folding (swivel) wing console;

FIG. 2. Schematic representation of an airplane. View from above. The wing consoles are folded (rotated). The rotary sections (left, right) of the transformable part of the center section profile - the middle part of the wing - are conditionally removed.

14 - conditional image of the screw;

15 - cockpit (installation option - above the engine);

16 - operator’s cabin of defense and attack devices;

17 - the main cockpit cabin with fixing elements, the main fuel tank installation compartment, (the compartment for the additional easily removable fuel tank, the cargo compartment, the dumped cargo compartment, (equipped with the cargo fixation elements), the dumped weapons compartment (equipped with weapon holders), located under the cabin pylons of an outboard fuel tank (not shown conditionally);

FIG. 3. Schematic representation of the left transformable part of the wing center section profile - the middle part of the wing. Side view. Flight (folded) position.

18 - nasal profile of the center section;

19 - stiffener of the center section;

20 - hole for fixing on the stiffener of the center section;

21 - stiffener of the rotary section of the left transformable part of the center section profile - the middle part of the wing;

22 - hole for fixing on the rotary section of the left transformable part of the center section profile - the middle part of the wing;

23 - front auxiliary left hinged butt unit;

24 - lower butt node of the rotary section of the left transformable part of the center section profile - the middle part of the wing;

25 - upper butt joint, (the bolt of the butt joint is the axis relative to which the rotation section of the left transformable part of the center section profile — the middle part of the wing — rotates;

3 - rotary section of the left transformable part of the center section profile - the middle part of the wing;

FIG. 4. Schematic representation of the left transformable part of the center section - the middle part of the wing. Side view. Transport situation.

2 - left folding (swivel) wing console. Folded (rotated) position;

3 - rotary section of the left transformable part of the center section profile - the middle part of the wing. Rotated position;

26 - ear of the lower butt unit;

27 - fork of the lower butt assembly;

FIG. 5. Schematic illustration of a device for synchronously folding (turning) both wing consoles. Synchronization reducer.

28 - lever on the left folding (rotary) wing console;

29 - left thrust;

30 - synchronization reducer;

31 - a gear rack of a synchronization reducer;

32 - clip gear rack synchronization gear;

33 - a gear wheel of a synchronization reducer;

34 - the right shock-absorbing layer;

35 - lever folding (rotation) of the wing consoles;

36 - retainer (of two positions - “initial”, “folded”) of the folding lever (rotation) of the wing consoles (not shown conditionally);

FIG. 6. Schematic representation of the right pillar of the classic main (main) two rack chassis. Front view. The released position of the chassis.

37 - the right outer surface of the fuselage;

38 - the upper part of the right gondola;

39 - right defensive receiver cannon for protecting the front hemisphere;

40 - the lower part of the right gondola;

41 - axis of rotation of the right landing gear when cleaning - release;

42 - the right landing gear with hydropneumatic shock absorption;

43 - clamp fastening the rear breaking strut on the right suspension strut of the chassis;

44 - the main brake wheel;

FIG. 7. Schematic illustration of the kinematics of cleaning the classic main (main) two rack chassis. Left stance. Side view. Retracted chassis position.

45 - contour of the gondola;

46 - left landing gear with hydropneumatic shock absorption;

47 is a schematic illustration of the lower part of a breaking rear strut;

48 is a schematic illustration of the upper part of a breaking rear strut;

49 is a schematic illustration of a hinge (lock) breaking rear strut;

50 - a clamp of fastening of the rear breaking strut on the left suspension strut of the chassis;

51 - axis of the main wheel;

52 - the outline of the main wheel;

53 - the contour of the center section;

54 - cylinder lifting the chassis;

55 - axis of rotation of the left landing gear during cleaning - release;

FIG. 8. Schematic representation of the classic tail wheel. Side view. The released position of the tail wheel. (The control and locking devices are not shown conditionally.)

56 - tail wheel;

57 - tail wheel fork;

58 - shock absorber tail strut;

59 - tail wheel harvesting cylinder;

60 - lever;

61 - a frame of the rear fuselage;

62 - frame of the rear fuselage;

63 - frame of the rear of the fuselage;

64 - a niche (cutout contour) in the rear of the fuselage under the tail wheel;

FIG. 9. A schematic representation of an airplane. Front view. The released position of the landing gear. Wing consoles laid out. The cockpit on top of the engine.

FIG. 10. Schematic illustration of an airplane. Front view. Retracted chassis position. The wing consoles are folded (rotated). The cockpit on top of the engine. The diameter of the screw and the protruding part of the main wheel of the chassis are aligned.

FIG. 11. Schematic representation of the working space of the main cabin. (The cockpit, crew member, operator of defensive and offensive defense devices.) The workspace of the pilot under the engine is the first basic option.

65 - windshield flat armored cockpit;

66 - lines of the external constructive review forward - down;

67 - foot control post;

68 - pilot seat, parachute device;

69 - power frame of the fuselage;

70 - engine (engine mount conditionally not shown);

71 - flat armored glass of the operator’s cabin of defense and attack devices;

72 - defensive mobile barrel gun protecting the rear hemisphere (electro-hydraulic drive conditionally not shown);

73 - defensive front gun for protecting the front hemisphere;

74 - conditional image of the screw;

75 - operator's seat of defense and attack devices, parachute device;

FIG. 12. Schematic representation of the working space of the main cabin. (The cockpit, crew member, operator of defensive defense and attack devices.) The pilot's workspace above the engine is the second main option.

76 - windshield flat armored cockpit;

77 - the cockpit circuit (layout above the engine);

78 - control knob;

79 - conditional image of the screw;

80 - foot control post;

81 - power frame of the fuselage;

82 - pilot seat, parachute device;

83 - crew member seat, parachute device;

FIG. 13. Schematic representation of the working space of the pilot (cockpit) above the elongated engine shaft - the third main option).

84 - windshield flat armored cockpit;

85 - the cockpit circuit (layout over an elongated engine shaft);

86 - control knob;

87 - conditional image of the screw;

88 - foot control post;

89 - engine (mounting the engine frame to the power frame of the fuselage is not conventionally shown);

90 - pilot seat, parachute device;

91 - lines of the external constructive review forward - down;

92 - an elongated motor shaft;

93 - contour of a removable engine hood;

FIG. 14. Schematic representation of the working space of the pilot (cockpit) above the engine.

94 - engine shaft;

95 - contour of a removable engine hood;

96 - lines of the external constructive review forward - down;

97 - engine (mounting the engine frame to the power frame of the fuselage is not conventionally shown);

FIG. 15. A schematic representation of the main cockpit cabin with fixation elements — the main fuel tank installation compartment, (the compartment for the additional easily removable fuel tank, the cargo compartment, the dumped cargo compartment, the discharged weapons, the pylons of the suspended fuel tank (not shown conditionally).

98 - centering range;

99 - supporting platform for the legs;

100 - belts, crew member fixation elements;

101 - towing coupling loop (left), at the bottom of the fuselage power frame, for loading the aircraft on a delivery road train according to patent No. 127695 (RF) June 26, 2012;

FIG. 16. Schematic representation of two open cabins (left, right) crew members on the outer surfaces of the fuselage and center section (space zalizov).

102 - niche of the support platform for the legs;

103 - a niche under the elbow;

104 - crew member straps, parachute device

105 - a niche under the helmet;

106 - fairing helmet;

FIG. 17. Schematic representation of the left backup cab in the gondola of the chassis and armament of a crew member with fixation elements.

107 - a support platform for the legs;

108 - left defensive front gun for protecting the front hemisphere;

109 - fixing belt, parachute device;

110 - wing spar line;

111 - handle for hand grip;

FIG. 18. Schematic representation of the workspace of the operator of defense and attack devices. (Operator's cab).

112 - airbag under the main cabin (folded state);

A sketchy image of an airplane. Top view (see Fig. 1) Airplane of the classical (normal) aerodynamic design, the rectangular wing of which consists of a center section 9 and folding (rotary) wing consoles (left 2 and right 13). The center section is connected to the fuselage 6, on the rear of which is installed horizontal 7 and vertical 8 plumage. On the wing center section there is a landing shield 5.

On the track of the main landing gear on the center wing, left 4 and right 10 gondola chassis and weapons.

The center section 9 and the wing consoles (left 2 and right 13) are connected by means of butt joints, which at the same time are nodes of folding (rotation) of the wing consoles (left 1 and right 12).

A sketchy image of an airplane. Top view (see Fig. 2). Screw 14, cockpit (above the engine) 15, cockpit of the defense and attack devices 16, main cockpit cockpit with fixation elements - main fuel tank installation compartment, (additional easily removable fuel tank compartment, cargo compartment, dumped cargo compartment, (equipped with elements cargo securing), a compartment for discharged weapons, (equipped with arms holders), under the cabin there are pylons of an outboard fuel tank (not shown conditionally) 17. The wing consoles (left 2 and right 13) are folded (turned) (see Fig. 1). section and the center-of transformable part of the profile - the middle part of the wing (left and right 3 11) conventionally removed (see Figure 1..).

Wing consoles fold after landing an airplane (aircraft). The rotation of the wing consoles is made back in one plane, the axis of the spar of the wing consoles is parallel to the axis of the fuselage 6.

Rotation (rotation) of the wing consoles (left 2 and right 13) is carried out due to the left 1 and right 12 knots of folding (rotation). These nodes during operation are not disconnected.

Schematic representation of the left transformable part of the center section - the middle part of the wing. Side view (see Fig. 3). Flight (folded) position) On the nose profile of the center wing 18, there is a stiffener for the center wing 19, in which a hole is made for fixation 20. On the stiffener of the rotary section of the left transformable part of the center wing profile - the middle part of the wing 21, a hole for fixation 22 is made. Due to of the lower butt assembly 24 and the upper butt assembly 25, the rotary section of the left transformable part of the center section profile - the middle part of the wing 3 is attached to the center section spar.

A front auxiliary left hinged butt unit 23 is installed, which fixes the left wing console 2.

Schematic representation of the left transformable part of the center section profile - the middle part of the wing. Side view. Transport position (see Fig. 4). The left wing console 2 is folded (rotated). The rotary section of the left transformable part of the center section profile - the middle part of the wing (left 3) from the wing spar to the end stringer is raised upward, rotating near the bolt of the upper butt assembly 25, the lower butt assembly 24 (ear 26, plug 27) is disconnected. During rotation, the hole for fixing 22 on the stiffener of the rotary section of the left transformable part of the center section profile - the middle part of the wing 21 and the hole for fixing 20 (see Fig. 3) on the stiffener of the nose profile of the center section 19 coincide, after which the fixing element is installed. (Conditionally not shown).

Schematic illustration of a device for synchronous folding (rotation) of both wing consoles. The synchronization reducer, (see Fig. 5). Wing consoles left 2 and right 13 rotated synchronously at equal angles

A lever 28 is mounted on the left wing console 2, which is pivotally connected to the left link 29 and the gear rack 31 of the synchronization gear 30. The gear rack 31 is preloaded (clip 32 of the synchronization gear) and engages with the gear wheel 33. The right wing console is connected in the same way, it works synchronously left. In order to exclude a hard blow when opening the wing consoles in the area of the junction of the wing consoles and the center section, a shock-absorbing layer is installed (right 34). The device is driven by a lever 35, which is fixed in two positions: “initial” - the wing is in the take-off position and “folded” - the spar axis of the wing consoles is parallel to the fuselage axis. The latch 36 is conventionally not shown.

Schematic representation of the right pillar of the classic main (main) two rack chassis. Front view. The released position of the chassis (see Fig. 6). The mounting bracket of the rear breaking strut on the right suspension strut of the chassis 43. The right landing gear 42 and the main brake wheel 44, rotating about the axis 41, are removed to the lower part of the right nacelle 40. In the upper part of the right nacelle 38, the right defensive front gun for protecting the front hemisphere is installed 39.

Schematic representation of the kinematics of cleaning the classic main (main) two rack chassis, (see Fig. 7) Left pillar 46. Side view. The retracted position of the chassis, the main brake wheel 52, protrudes from the contour of the nacelle 45, (fixed to the center section 53) to ensure an emergency landing without releasing the chassis and for installation on a vehicle for transportation. The chassis lifting cylinder 54, the hinge (lock) of the breaking rear strut 49, the rear breaking strut is folded onto the lower 47 and upper part 48, the left suspension strut of the chassis 46, rotates around the axis of rotation of the left strut 55, the clamp for attaching the rear breaking strut to the left suspension strut 50 .

Schematic illustration of a classic tail wheel. Side view. The released position of the tail wheel, (see Fig. 8). The control and locking device for the wheel is not shown conditionally. The tail wheel 56 is installed in the fork 57, which is connected to the shock absorber of the tail pillar 58. The wheel is removed due to the chassis cleaning cylinder 59, which rotates the lever 60, the wheel retracts into a niche 64 in the rear of the fuselage, fastening is carried out on the frames of the fuselage 61, 62, 63. Kinematics in the retracted position ensures the protrusion of the tail wheel 56 from the contour of the cutout of the rear of the fuselage 64, to ensure an emergency landing without releasing the chassis and for installation a vehicle for transportation.

A sketchy image of an airplane. (see Fig. 9). Front view. The released position of the landing gear (right 42 and left 46). The main brake wheel 44, the center section 9, the wing consoles (left 2 and right 13) are unfolded. The cockpit 15 on top of the engine, (see Fig. 7). Horizontal plumage 7, vertical plumage 8. The aircraft is ready to take off.

A sketchy image of an airplane. Front view (see Fig. 10). The retracted position of the landing gear (right 42 and left 46). The wing consoles (left 2 and right 13) are folded (rotated). Cockpit 15 on top of the engine. The diameter of the screw 14 and the protruding portion of the main wheels of the chassis 44 are aligned. (i.e. with a four-bladed propeller, a gap is ensured between the chord (connects the ends of the propeller blades parallel to the surface of the runway) and the surface of the runway. The aircraft is ready for loading onto a motor vehicle according to patent No. 127695 (RF) of June 26, 2012 g.)

Schematic representation of the working space of the main cab. The pilot's working space under the engine is the first main option (see Fig. 11). (Cockpit, crew member, operator of defensive and offensive defense devices.) The main cockpit structurally includes the pilot's workspace (cockpit) under the engine. Pilot seat, parachute device 68. Seated pilot position. Provides an excellent overview of the lower front hemisphere - the lines of the external constructive review forward - down 66, through the glass windshield flat armored cockpit 65. Foot control post 67. Screw 74. The defensive receiver cannon for protecting the front hemisphere 73, is located above the engine 70 (engine mounting is conditionally not shown), which is fixed to the power frame of the fuselage 69.

The working space of the main cockpit includes the working space (main cockpit) of a crew member with fixation elements — the main fuel tank installation compartment, (the compartment for the additional easily removable fuel tank, the cargo compartment, the dumped cargo compartment (equipped with cargo fixation elements), the dumped weapons compartment (equipped arms holders), pylons of an outboard fuel tank (not shown conditionally) 17, after the power frame of the fuselage 69. The recumbent crew member is connected to the cockpit and cockpits ouch operator protection and attack.

Workspace of the operator of the defense and attack devices (operator’s cabin), located after the workspace (main cabin) of the crew member with fixation elements and the installation compartment of the main fuel tank 17. Equipment - operator’s seat of the defense and attack devices, parachute device 75 (sitting position of the operator) . A defensive barrel-mounted movable cannon for protecting the rear hemisphere was installed (electro-hydraulic drive is not shown conventionally) 72. The review is carried out through armored flat glass 71.

Schematic representation of the working space of the main cab. The pilot's working space above the engine is the second main option (see Fig. 12).

Cockpit, crew member, operator of defensive defense and attack devices. The main cockpit structurally includes the working space of the pilot (cockpit) 77 above the engine. Pilot seat, parachute device 82. Seated pilot position. A good external constructive forward-downward review is provided through the glass of the lower front hemisphere through the frontal flat armored cockpit of 76. Control stick 78, foot control 80. The engine (mount of the engine frame is not shown conditionally) is mounted on the power frame of the fuselage 81.

The working space of the main cockpit with the pilot's cabin 77 above the engine includes the working space (cabin) of the crew member (crew seat, parachute device 83) and the working space (cabin) of the operator of defensive defense and attack devices (operator's seat of defense and attack devices, parachute device 75 ), which are similar to the main cockpit with the cockpit under the engine.

A schematic representation of the pilot's working space (cockpit) above the elongated engine shaft is the third main option (see Fig. 13). The workspace of the pilot (cockpit) 85, above the elongated shaft of the engine 92, includes a pilot seat, a parachute device 90, is located above the elongated shaft 92 of the engine 89 (mount of the engine frame is not shown conventionally). The contour of the removable engine hood 93. Seated pilot position. Provides a good overview of the front hemisphere - the lines of the external constructive review forward - down 91, through the glass windshield flat armored cockpit 84. Control handle 86, post foot control 88. Screw 87.

Schematic representation of the working space of the pilot (cockpit) (see Fig. 14). Above the engine 97 includes a pilot seat, parachute device 82. Seated pilot position. Provides a good overview of the lower front hemisphere - the lines of the external constructive review forward - down 96, through the glass the frontal armored cockpit 76. Control handle 78, foot control 80. Engine 97 (mount the engine frame to the power frame of the fuselage is not conventionally shown) is fixed to the power the fuselage frame 81 (see Fig. 12). Engine shaft 94, removable engine hood 95.

Schematic representation of the main cockpit cabin with fixation elements - the main fuel tank installation compartment, (see Fig. 15) (additional easily removable fuel tank compartment, cargo compartment, dumped cargo compartment (equipped with cargo fixation elements), dumped weapons compartment (equipped arms holders), pylons of an outboard fuel tank (not shown conditionally) 17, (centering range of the wing) 98. After the power frame of the fuselage (at the bottom of which towing tow hinges are installed (right and left 101) for loading an aircraft on a delivery train according to patent No. 127695 (RF) of June 26, 2012. The recumbent crew member, fixing belts 100, is connected to the cockpit and the operator’s cabin of defense and attack devices. legs 99, a seat is installed, parachute device 83 (see Fig. 12).

Schematic representation of two open cabins (left, right) crew members (see Fig. 16). Located on the outer surfaces of the fuselage and center section (space zalizov). Lying (on the side) arrangement of crew members. Fastening - fastening belts 104, (equipment - parachute device), niches - supporting platforms for legs 102, niches for elbow 103, niche for helmet 105, fairing of helmet 106.

Schematic representation of the left backup cab in the left gondola of the chassis and armament of a crew member with fixation elements (see Fig. 17). Reclining crew member. Equipment - seat belts, parachute device 109, support platform for the legs of a crew member 107, a handle for gripping the wing (111) wing consoles 111 with a hand. A defensive receiver cannon for protecting the front hemisphere 108 is installed along the axis of the nacelle. weapons.

A schematic representation of the operator’s workspace of the defense and attack devices (operator’s cabin) (see Fig. 18) is located after the main cockpit of the crew member and the main fuel tank. (Compartment for an additional easily removable fuel tank, cargo compartment, compartment for discharged cargo, discharged weapons, pylons of an outboard fuel tank (not shown conditionally) 17. Equipment - seat and parachute device 75 (sitting position of the operator). A defensive rear-mounted mobile gun for protecting the rear hemisphere 72 is installed (electro-hydraulic drive conditionally not shown), the review is carried out through flat armored glass 71. In the event of an emergency landing, an airbag 112 is used.

The airplane is transported by road and rough terrain, in which the wing consoles are pre-folded (each console is folded in the same plane (rear span), the axis of the console spars is parallel to the fuselage axis (the position is “folded” - fixed position). partial protrusion of the wheels from the contour of the nacelles, the kinematics of cleaning the tail support of the chassis provides a partial protrusion of the rear wheel from the contour of the tail of the fuselage. mediate vicinity of the area of the flight being undertaken, (according to the patent №127695 (RF) from June 26, 2012);

Flight preparation:

1. The tail wheel. With the help of a jack (installed in the area of the rigth through hole on the rear of the fuselage) or manually, the tail of the fuselage is lifted and the tail wheel is released.

2. The main landing gear. With the help of jacks (installed in the area of the towing hitch loops (left and right), the airplane rises to the upper position and the main landing gear is released.

3. Engine, screw. An air-cooled star-shaped engine, or a v-shaped engine, or an in-line engine is installed, depending on the nature of the work performed, which is fixed to the fuselage power frame.

4. Cabin. The cockpit is installed under the engine, either above the engine or over the elongated engine shaft, which is also fixed to the fuselage power frame.

5. The wing console. The wing consoles are unfolded (rotated) and fixed in the “initial” position using the rotation lever or the rotation pedal (not shown conditionally). The initial position is the second fixed position of the wing consoles.

To carry out the rotation of the wing consoles, the fixation of the wing consoles (folded transport position) is preliminarily removed - struts connecting the power frames of the fuselage nacelles and the ears on the side members of the folding (rotary) wing consoles (not shown conditionally).

Unfolding (rotation) of the wing consoles is carried out from the cockpit using the rotation lever or the rotation pedal (the main solution, the control knob is previously fixed by the fixing bracket to the far right position) and from the landing gear and arms nacelle by turning one wing console. Through a system of levers and a synchronization gear, another wing console is rotated (auxiliary solution).

Fixing the consoles with the auxiliary front hinged butt assembly.

The rotation of the rotary sections of the transformable part of the profile of the center section - the middle part of the wing and the fixation of the lower butt assembly of the rotary sections of the transformable part of the profile of the center section - the middle part of the wing.

Folding the wing consoles is in the reverse order.

1. Disconnection of fixation of the lower butt nodes of the rotary sections of the transformable part of the center section profile - the middle part of the wing;

2. Turning sections and fixing rotary sections (with

using the lock) of the rotary sections of the transformable part of the center section profile - the middle part of the wing;

3. Disconnection of the fixation of the wing consoles (disconnection of the auxiliary front hinged butt unit);

4. Folding (rotation) of the wing consoles is made from the cockpit using the rotation lever or pedal (not shown conditionally) (basic solution) or by turning one wing console. Through a system of levers and a synchronization gear, another wing console is rotated (auxiliary solution);

5. After rotation of the wing consoles, struts are installed connecting the power frames of the fuselage nacelles and the ears on the side member of the folding (rotary) wing console;

In the “folded” position, the size of the airplane in width exceeds the permissible (permitted) width of the vehicle and cargo for transportation by road.

The main crew - classic - consists of a pilot and operator of defense and attack devices. The pilot is located in the cockpit under the engine or over the engine, or over the elongated shaft of the engine. The operator in the operator's cab. The location is classic. Back to each other.

The crew is additionally equipped with:

The first option is an additional one crew member:

A crew member occupies the main cockpit (with fixation elements). Lying position (on the chest). The main fuel tank is located under the cab. (In the centering range). In this cabin, it is possible to install an additional easily removable fuel tank, or it can be used as a cargo compartment, a compartment for discharged cargo, (equipped with elements for securing cargo), a compartment for discharged weapons, (equipped with arms holders). Under the cab there are pylons for an outboard fuel tank (not shown conditionally). And the installation of an outboard fuel tank is possible.

The second option is an additional two crew members:

Crew members occupy two open cockpits (left and right) on the outer surfaces of the fuselage and the center section (space zalizov). Lying position (on the side).

Above the fuel tank (in the centering range), it is possible to install and fix an increased volume of cargo (dumped cargo), in the lower part of the cabin it is possible to place on holders of dropped weapons, (equipped with weapon holders). Under the cab there are pylons of an outboard fuel tank (not shown conditionally). And the installation of an outboard fuel tank is possible.

The third option is an additional four crew members:

Two crew members occupy two open cockpits (left, right) on the outer surfaces of the fuselage and the center section (space zalizov). Lying position (on the side).

Two additional crew members occupy backup cabins in the right and left gondolas of the chassis and armament with fixation elements. Lying position (on the chest). An additional easily removable fuel tank can be installed in the main cockpit of a crew member with fixing elements — the compartment for installing the main fuel tank. Or it can be used as a cargo compartment, a compartment for discharged cargo, (equipped with elements for securing cargo), a compartment for discharged weapons, (equipped with arms holders). It is also possible to install an outboard fuel tank under the cab on pylons (not shown conditionally) 17. Or an additional crew member (Five crew members.) And regular installation of cargo and weapons.

During preparation for the flight, all crew members have the ability to move along the wing surface, the fuselage, plumage, due to the use of handles (grabbing by the hands) on the outer surface of the wing (fuselage, plumage), as well as installed steps (leg support). In the space of handles (hand grip), steps (leg supports) in the case of a long stay at a certain point of the wing, fuselage, additional fixation elements are installed at this point (belts, contact fixing tapes, hooks, etc.). An airplane (aircraft) is ready for takeoff. After take-off, all crew members (except the pilot and operator) have the ability to move along the surface of the wing and fuselage.

During landing, both the main supports and the tail landing gear are released.

In the event of an emergency landing, landing is possible without landing gear. The wheels of the main supports protrude beyond the contour of the gondolas of the chassis and armaments; the wheel of the tail support protrudes beyond the contour of the rear of the fuselage.

During an emergency landing, the absorption of impact energy is provided by the airbag, which opens under the main cockpit of the fuselage. For emergency release of the main landing gear and ensuring the necessary stabilization of the airplane on the water surface, two airbags are additionally deployed, which are installed in the space of the landing gear and weapons. Disclosure of these pillows is possible both before an emergency landing and after an emergency landing.

Creating a useful model of an airplane will allow us to solve the problems of simplicity, speed and reliability of all operations of folding an airplane - the survival of the airplane on the ground.

Claims (14)

1. A folding airplane containing an engine, a fuselage with a cockpit, a fuel tank, a wing including a center section and rotary consoles, which are connected to the center section using the main butt joints with the possibility of folding backward along the span with the possibility of rotation in one plane, and a landing gear, including main struts with wheels, characterized in that the engine is one of three possible options, and the cockpit is one of three possible options, located under the engine, either above the engine or over the elongated engine shaft spruce, fixed to the power frame of the fuselage; the main cockpit of the crew member, connected to the cockpit with the fixation elements of the crew member, - the main fuel tank installation compartment, located in the fuselage immediately behind the power frame - the centering range, is equipped with fixation elements for an additional easily removable fuel tank, load securing elements, dumped cargo, discharged weapons under which pylons of an outboard fuel tank are located; behind the cabins is the operator’s cabin of defense and attack devices; two open cockpit crew members are located on the right and left outer side surface of the fuselage and center section - the space of the fuselage and center section lanes, are equipped with crew member fixation elements; backup cabins for crew members are located in the right and left nacelles of the chassis and armaments, are equipped with elements for fixing crew members; the main part of the center section - a single unit with the fuselage - is in span equal to the rut of the main landing gear, the transformable part of the center section profile is the middle part of the wing, in scope it is equal to the distance from the wing center section spar to the end stringer, in which the left and right sections of the center section profile are equal the distance from the wing spar of the wing center section to the end stringer, are fixed on the wing spar of the wing center section using the upper ones - the rotation axis and the lower butt nodes; two rotary - right and left wing consoles - are attached to the center wing, using the main butt nodes - hinged folding nodes - rotate wing consoles that are mounted on the wing center wing spar, the axis of the joint bolts - hollow inside - is located vertically, and the front auxiliary hinged butt nodes ; wing consoles are also connected to the synchronization gear. 2. An airplane according to claim 1, characterized in that it is equipped with an airbag, which is installed under the main cabin of the fuselage and is made in the form of a float; an additional two airbags are installed in the space of the chassis nacelles and armaments. 3. An airplane according to claim 1, characterized in that the tail landing gear is equipped with a control and locking system. 4. An airplane according to claim 1, characterized in that the compartments of the landing gear gondolas and armaments for the main landing gear wheels are equipped with gondola flaps, the compartments under the racks are equipped with shields mounted on the rack. 5. An airplane according to claim 1, characterized in that hatches are made in the gondolas of the landing gear and armaments, on the rotary sections of the transformable part of the center section profile - the middle part of the wing, wing consoles are made hand grips for hands, steps - legs for legs. 6. An airplane according to claim 1, characterized in that defensive gun cannons are installed in the gondolas of the main landing gear and arms, arms control panels are installed in all cabins. 7. An airplane according to claim 1, characterized in that on the outer surface of the wing and fuselage are mounted handles - grips for hands, and also steps are installed - supports for legs, in the space of handles - grips for hands, steps - supports for legs - elements are installed additional fixation at a given point of the wing, fuselage. 8. An airplane according to claim 1, characterized in that in the cockpit and in the cockpit of the operator of the defense and attack devices, levers and turn pedals of folding - rotary wing consoles are installed. 9. An airplane according to claim 1, characterized in that the rotary sections — the left and right transformable parts of the center section profile — the middle part of the wing — are made of several parts. 10. An airplane according to claim 1, characterized in that it is equipped with a bracket for fixing the control handle in the far right, not in the working position; and the ailerons control wiring, located in the wing consoles and the center section, is equipped with turning units. 11. An airplane according to claim 1, characterized in that a landing flap is installed over the entire center-wing span. 12. An airplane according to claim 1, characterized in that the struts of fixation are fixed on the frames of the gondolas of the landing gear and armaments in the folded - transport position of the folding - rotary wing consoles. 13. An airplane according to claim 1, characterized in that at the bottom of the power frame of the fuselage towing towing loops are installed - right and left, and a through hole is made in the rear of the fuselage. 14. An airplane according to claim 1, characterized in that the upholstery - cabin insulation - is made in the form of sets of clothes.

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