RU185603U1 - Ultralight multi-purpose aircraft outside the field - Google Patents

Abstract

The utility model relates to aviation. An ultralight multipurpose non-aerodrome-based aircraft consists of four units: a classic two-seat aeromodule equipped with a pushing propeller, direct-acting duplex control system from both seats, two wing halves with flaperons designed according to the strut-brace pattern, and a tail with the provided mutual fastening aggregates. The cabin is made expanded to accommodate two seats in width, allowing their transformation and movement, and is equipped with full-sized single-leaf doors. Expanded the existing doorway in the starboard side. The two halves of the wing are made with the separation of the flaperon into the flap and aileron to regulate the bearing capacity of the wings. The technical results achieved by the implementation of the claimed utility model include transportation of a person (“injured”) in a lying or sitting position, cargo delivery and flight stability at low speeds and low altitudes. 5 ill.

Description

The utility model relates to aviation and can be used to create ultralight multi-purpose aircraft designed to perform a wide range of tasks (passenger transportation, patrolling, search and rescue and reconnaissance operations, air-borne evacuation, cargo delivery, landing, for training flights, airchemical works, postal, etc.), operation from unprepared takeoff and landing ground and water sites, in various geographical areas, natural and climatic conditions Barrier-with providing mobility aircraft during assembly / disassembly, transportation and storage.

An analogue of the S-2 Sintal airplane is known from the existing level of technology. It is a double-strut high-wing aircraft with a T-tail. The wing is straight with a constant chord. The cockpit is made of fiberglass. The door is located on the starboard side and opens up. The pilot seats are located in tandem, the co-pilot is located in the center of gravity of the aircraft. Chassis fixed, tricycle with self-orienting nose wheel. The main chassis spring type. The aircraft equipment allows you to fly during the day in simple weather conditions according to the rules of visual flights (patent RU 2336200 C2, publ. 20.10.2008).

The disadvantage of this technical solution for use in airborne medical evacuation is the tandem arrangement of the pilot seats in a narrow cockpit in the midship section, which does not allow a stretcher chair to be placed.

The analogue is known as an ultralight two-seat aircraft with a thrust propulsion system Beaver rx 550. A closed cockpit with a tandem arrangement of pilots (Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, pages B-9, B-70, B-103 & E-6. Cybair Limited Publishing, 2001. ISBN 0-9680628-1-4).

The disadvantages of this technical solution for use in airborne medical evacuation are insufficient doorway to accommodate oversized cargo, tandem arrangement of pilot seats, which does not allow to place a stretcher chair.

The closest technical solution chosen for the prototype of the claimed utility model in all its variants, similar in design, aerodynamic layout and functional purpose is an ultralight two-seat aircraft of modular design R-20 “Chick-2”, consisting of four units: a two-seater aeromodule of classical layout equipped with a pushing propeller, with a direct-acting duplex control system from both seats, two wing halves with flaperons designed to strut brace pattern, and tail, provided for their mutual fastening (see. "Bronze medalist of the World Cup", A. Timchenko, V. Khribkov, magazine "Modelist-Constructor" 2001, No. 5, 6).

The disadvantages of this technical solution are a narrow amidship cabin, which does not allow placing two seats in a “duet” and transforming the right (passenger) seat into a cargo area to accommodate the injured or oversized cargo; doorway insufficient to accommodate oversized cargo, including that located on a stretcher; fixed pilot seat, without the possibility of displacement; flight instability during take-off, climb, descent and landing, as well as when flying at low speeds.

The problem to which the invention is directed is to change the design of the cockpit and wings to eliminate the aforementioned disadvantages.

This problem is solved due to the fact that in the well-known ultra-light multi-purpose aircraft outside the aerodrome base, consisting of four units: a two-seater air module of a classic layout equipped with a pushing propeller, a direct-acting duplex control system from both seats, two wing halves with flaperons designed to strut -the brace scheme, and the tail, with the provided mutual mounting of these units, the cabin is expanded to accommodate two seats in width, allowing them to trans ormirovanie and moving, and is equipped with a full-size single-wing doors.

The existing doorway in the starboard side is expanded, and the right door is enlarged relative to the left one with folding back and forth and fixing in the open position by a gas elevator attached to the lower point of the door frame, as well as with double curvature glazing. The placement of two seats in width is made with the possibility of moving the pilot's seat 7 in the longitudinal direction of the aircraft by (300) mm, in the transverse - by (100) mm to ensure alignment of the aircraft during cargo transportation, and the right seat (passenger seat) 6 can be transformed into a stretcher in a reclining and sitting position to accommodate a passenger or cargo. The two halves of the wing are made with the separation of the flaperon into a flap and aileron for regulating the bearing capacity of the wing.

The technical results achieved by the implementation of the claimed utility model include transportation of a person (“injured”) in a lying or sitting position, cargo delivery and flight stability at low speeds in relation to the closest technical solution - the Chick-2 aircraft.

The invention is illustrated by drawings, which depict.

In FIG. 1 shows a general view of an aircraft with a cockpit layout for air ambulance evacuation;

In FIG. 2 - view of the front of the cab and its starboard side;

In FIG. 3 - diagram of the installation of a stretcher in the cockpit;

In FIG. 4 - options for transforming the right seat;

In FIG. 5 - wing of the plane.

In the drawings, the positions indicated

1 - propeller,

2 - wing

3 - tail

4 - cab

5 - right door

6 - right seat (passenger seat, stretcher chair),

7 - pilot seat,

8 - flap,

9 - aileron.

An ultralight multipurpose non-aerodrome-based aircraft consists of four units: a classic two-seat aeromodule equipped with a pushing propeller 1, direct-acting duplex control system from both seats, two wing halves 2 with flaperons designed according to the strut-brace pattern, and tail 3, with the provided mutual fastening of all units.

The specified technical result is achieved by the fact that to accommodate the support site of the injured party (stretcher) or oversized cargo, an extended cabin 4 with an enlarged view is made. The expansion of the aircraft cockpit using double curvature glazing allows the placement of two seats in width, allowing them to be transformed and moved to transport the “injured” in a lying position or to transport oversized cargo. In FIG. 2 shows the cockpit of the aircraft and its starboard side. The opening of the right door 5 is increased in width and height, which allows you to make and install the overall load or stretcher chair 6 in the unfolded state. For the convenience of placing the support of the victim’s platform (stretcher) or oversized cargo, the right door 5 is made with folding back and forth and fixing in the open position by a gas elevator attached to the lower point of the door frame. The layout of the stretcher in the cockpit is shown in FIG. 3. For transportation of oversized cargo or transportation of the “injured” in a lying position, the placement of two seats in width is made with the possibility of moving the pilot's seat 7 in the longitudinal direction of the aircraft by (300) mm, in the transverse direction by (100) mm to ensure alignment of the aircraft during transportation cargo, and the right seat (passenger seat) 6 can be transformed into a stretcher, in a reclining and sitting position to accommodate a passenger or cargo. For the effectiveness of wing mechanization, the flaperon was separately controlled for flap 8 and aileron 9 (Fig. 5). This gave an increase in deviation angles: ailerons (up to 25 degrees, minus 25 degrees) and flaps with fixation in three positions (0 degrees, minus 15 degrees and minus 23 degrees), which led to an increase in the lift coefficient and an improvement wing carrying capacity during take-off, climb, descent and landing, as well as when flying at low speeds.

The presented air module has the possibility of autonomous use as an air car, snowmobile or airboat with appropriate supports.

Design documentation was developed for this design of an ultralight multipurpose non-aerodrome-based aircraft, a serial model was manufactured and tested.

Claims (4)

1. An ultralight multipurpose non-aerodrome-based aircraft, consisting of four units: a two-seater classic-style aeromodule equipped with a pushing propeller (1), direct-acting duplex control system from both seats, two wing halves (2) with flaperons designed along the strut-brace the scheme, and the tail (3) with the provided mutual fastening of these units, characterized in that the cabin (4) is expanded to accommodate two seats in width, allowing their transformation and movement of. 2. Aircraft according to claim 1, characterized in that the existing doorway in the starboard side is widened, and the right door (5) is made with folding back and forth and fixing in the open position by a gas lift attached to the lower point of the door frame, as well as double curvature glazing. 3. Aircraft according to claim 1, characterized in that the placement of two seats in width is made with the possibility of moving the seat (7) of the pilot in the longitudinal direction of the aircraft by 300 mm, in the transverse - by 100 mm to ensure alignment of the aircraft during cargo transportation, and the right the passenger seat (6) can be transformed into a stretcher, in a reclining and sitting position to accommodate a passenger or cargo. 4. Aircraft according to claim 1, characterized in that the two halves of the wing (2) are made with the separation of the flaperon into a flap (8) and an aileron (9) to regulate the wing's carrying capacity.

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