RU2553519C2 - Motor-glider - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircrafts of light-motor aviation. The motor-glider includes fuselage, engine, lifting wing and auxiliary wing, drive arms in wing rudder, wheel, elevator control. The lifting wing is fitted with articulated units two of which are located symmetrically relative transversal axis of symmetry on longeron. One articulated unit is located on auxiliary longeron and fixed on column which is hinged on sliding member movably installed in frame guides. The unit is linked with control wheel column by spring-loaded tie-rod. Auxiliary wing consists of two independent consoles movably fitted on transversal axis immovably fixed in frame nose part. The consoles are equipped with arms linked by tie-rods with double-armed lever of steering wheel. Front wheel pillar movably fixed in frame bushing is equipped with wheel spat made in the form of turning keel and provided with double-armed lever provided with compensators.

EFFECT: higher flight safety.

2 cl, 9 dwg

Description

The motor glider belongs to aircraft of light-engine aviation and is intended for training beginners to comprehend the alphabet of safe piloting of an airplane.

In this regard, the task arose: to create the design of a motor glider that is easy to operate and safe in flight.

From the review of technical information, it can be seen that a similar problem was solved in such improvised aircraft designs as: KhAI-19, KhAI-34, KhAI-40, Argo-02, Malysh, Leningrades, PMK-3, Don Quixote, Polonaise, A- 12, Cree-Cree, Phoenix 4-5, Aeroprakt, Wirdman T1-1 Screw-Ding 11, ...

Analogues are known from the patent information in which the flight safety problem is solved by a nodal and detailed method, for example, RU (21) 2009 107490/11 (13) A - the task of increasing the wing lift was solved in the Euromarkap; RU (11) 2399553 (13) C2 - Device and method for regulating the lifting force; RU (21) 2009 110283/11 (13) A - Chassis assembly; RU (11) 2400407 (13) C1 - Block storage and supply of liquid fuel for the engine; RU 2384577 (13) C1 - Steering gear equipped with compensators; ...

Patent RU (11) 2387578 (13) C1 - Automatic flight control system for highly maneuverable aircraft was selected as a prototype

This solution of the flight safety problem in the prototype is allowed at a higher level of automation, which is not required for the first time comprehending the science of control of a “low-speed” aircraft because in the training of pilots they adhere to the concept of training “from simple to complex”. In addition, in the prototype, sensors are a command system that has a execution system — drives in the control system, and this complicates the control system. It is well known: the more nodes and parts in the car, the more failures in operation.

In the proposed design of the motor glider, the goal of flight safety was pursued by simplifying the design of components and parts in the aircraft control system, which dictated the shape of the motor glider, and the restrictions that prevent the motor glider from going beyond critical flight parameters are achieved by a simple way of selecting the ratio of leverage lengths in the control system; an increase in the lifting force of the carrier and auxiliary wing is achieved by their rotation by an angle α and β, respectively, while the auxiliary wing still performs the functions of both the wing, the aileron, and the flap; the rotation of the motor glider on the ground and in the air is performed by the front landing gear, equipped with a fairing made in the form of a rotary keel; fuel is supplied to the engine forcibly and without energy costs of the engine using the mass of the pilot; the length and area of the carrier wing provide the planning of the motor glider over sufficient distances for a safe landing in case of engine failure.

The problem is solved using the design of the device motor-glider and control system.

Brief description of the drawings.

The drawings depict a motor glider, where:

in FIG. 1 shows a side view of the layout diagram of a motor glider, and the control system rods are shown in dash-dotted lines;

in FIG. 2 shows a general diagram of a motor glider control system;

in FIG. 3 shows the connection of the lever of the front landing gear - compensator - traction;

in FIG. 4 shows the connection node thrust - console arm - thrust;

in FIG. 5 is a plan view of FIG. four;

in FIG. 6 shows the compensator of the slider of the movable strut of the supporting wing (rotated);

in FIG. 7 shows a layout diagram of the hinged attachment points of the carrier wing;

in FIG. 8 shows section AA in FIG. 7;

in FIG. 9 shows a fuel tank and its attachment to the frame of a motor glider.

Motor glider device.

The motor glider consists of a frame 1, an engine 2, a chassis, the main wheels 3, 3, the front wheel 4, the supporting wing 5, the auxiliary wing, consisting of two independent consoles 6, 7, and the helm 8.

The frame 1 contains a sleeve "a", two stationary racks 9, 9, mounted on the frame by welding, which are attached to the supporting wing 5 by hinge assemblies 13, 14, a rack 10, mounted on the wing using the hinge assembly 15 and pivotally mounted on the slider 11, placed in the guides 12 of the frame 1;

the carrying wing 5, equipped with hinged nodes 13, 14, 15 located on the side members;

consoles 6, 7, equipped with levers 16, 17, movably fixed on the axis 18, fixed on the frame motionless;

a front wheel 4 pivotally mounted on a strut 19 equipped with a two-arm lever 20 and a cowl 21;

the slider 11 is equipped with a compensator 22, consisting of a spring "k" and a washer l with a thread;

two-arm lever 20, mounted on a stand 19, equipped with two compensators - 23, 23, which are similar to a turnbuckle containing a coupling d, springs - e and f separated by a washer q, with thread, bushings - h with thread;

a helm 8 comprising a strut 24, a tube 25 provided with a two-arm lever 26;

rods 27, 27 equipped with a thread, rods - 28, 28, rods - 29 with a thread.

The linkage of the rods with levers is carried out using a ball connection (the holes of the ends of the rods are countersunk under the scope of the screw GOST 17474-72) and are fastened with the same screw. This connection eliminates the bending of rods attached to levers operating in mutually perpendicular planes. Rods made from PVC tube must meet the conditions:

, где $$P_{кр}=\frac{{\pi }^{2}EJ}{\mu l^2}$$

,traction stability: $$\delta =\frac{R_{\mathrm{to}R}}{E_{bR\mathrm{at}tt\mathrm{about}}}\le \varphi [\delta ]$$

where $$P_{\mathrm{to}R}=\frac{{\pi }^{2}EJ}{\mu l^2}$$

,

where φ is the bending coefficient, E is the modulus of elasticity, J is the moment of inertia, l is the length of the thrust, μ is the coefficient of the reduced length for articulation is equal to one.

traction strength: $$\delta =\frac{R_{\mathrm{to}R}}{F_{nett\mathrm{about}}}\le [\delta ]$$

Adjustment of the control system is carried out by the rods of the compensators 22, 23, 23, while the control system must be fixed in the neutral position, while the condition must be met:

Q ₁ + Q ₁ = Q ₂ ,

where Q ₁ = Q ₁ and O ₂ = O ₂ ; Q ₁ , Q ₁ - spring force of the compensators 23, 23, Q ₂ - spring force of the compensator 22.

The frame 1 of the motor glider is equipped with a soft fuel tank 30, which is the pilot seat tank, so that the mass of the pilot can be used as energy for the forced supply of fuel from the tank to the engine, i.e. use as a fuel boost pump.

Tank 30 consists of a soft gas-resistant, rubberized material, inside of which are two frames 31, between which springs 32 are located at the corners. The tank has a tide - reserve capacity - “a”, separated from the tank by a check valve 33 and connected to a pipe 34 equipped with a valve 35. The tank is equipped with an atmospheric valve 36.

The work of management mechanisms.

All executive controls of the motor glider: steering wheel 8, wheel 4 with fairing 21, wing wing 5, consoles 6, 7 are installed in a neutral position under the influence of compensator springs 22, 23, 23.

When take-off, the helm 8 moves towards itself: the lever 26 with its shoulders pushes the rods 28, 28, which with equal effort turn the levers 16, 17 of the consoles 6, 7 down, while the end of the strut 24 pulls the rod 29, which moves the slider 11 forward, and together with him and the stand 10, connected by a hinge assembly 15 with the wing 5, and rotates the wing 5 by an angle α.

In this case, the motor glider gains maximum lifting force.

Smooth climb is due to the difference in the rotation angles of the consoles 6, 7 and wing 5.

After gaining a safe height for maneuvering the helm 8 is set to the neutral position of horizontal flight.

To make a turn to the right (left), the steering wheel turns to the right, while the right rod 28 will pull the lever 16, and the left rod 28 will push the lever 17, the console 6 will go up, and the console 7 will turn down - the motor glider will roll to the right, rod 28, 28 will transmit movement through the levers 16, 17 to the rods 27, 27, and through the compensators 23, 23 - to the lever 20, which will turn the fairing wheel to the right - the motor glider will make a right turn with a roll. In this case, the carrier wing 5 remains in a neutral position.

When turning to the right (left) with a climb, the angle of rise is first set, and then the turn follows, as described above

When landing, the angle of the landing glide path is set: the helm is fed forward, while the rod 29 is shifted back and compresses the spring “k”, holds the slider 11 in the neutral position, and the rods 28, 28 pull the levers 16, 17, which turn the console 6, 7 up - reduced motor glider. Before exiting the landing glide path, the engine is idled (or turned off). The steering wheel 8 is fed back as when taking off, while the carrier wing 5 and the consoles 6, 7 rotate: the console is at an angle β, and the carrier wing at an angle α - the motor glider regains its maximum lift and is aerodynamically braked before landing. On the ground, the brakes of the main wheels 3, 3 are activated.

The engine is provided with fuel in this way: when the pilot is landing on the seat, the springs of the tank 30 are compressed, the atmospheric check valve 36 closes the tank volume - overpressure is created. In this case, the fuel check valve 33 unlocks the passage for fuel from the tank to the reserve tank "a". When opening the valve 35, the fuel through the pipe 34 enters the engine.

With the evolution of the motor glider in the air, when the pilot is "upside down" to the horizon, the load on the springs 32 is removed, they stretch the tank, creating a vacuum inside the tank. In this case, the atmospheric check valve 36 allows air to enter the tank, and the fuel check valve 33 locks the container "a", excluding the access of air to the pipeline. At this time, the engine is powered from the reserve tank "a", where the pressure was locked.

When returning the motor glider to a horizontal position, the fuel system of the motor glider begins to work as usual.

Similar devices are described in patent information B65B 31/04. - "Devices and method for filling containers."

Claims (2)

1. A motor glider, consisting of: a fuselage, an engine, a wing, a stabilizer, a keel, a three-post chassis and a control system of rods and rockers kinematically connected to the control handle, characterized in that the carrier wing is equipped with hinged assemblies, two of which are symmetrically located the transverse axis of symmetry of the bearing wing on the spar passing through the center of the lifting force of the bearing wing, attached to the racks mounted on the frame by welding; one hinge unit is located on the auxiliary spar, at the intersection with the transverse axis of symmetry of the wing, and is mounted on a rack that is pivotally mounted on a slide movably mounted in the frame guides, and is connected to the helm post by a spring-loaded rod, and the auxiliary wing consists of two independent consoles, seated movably on a transverse axis, fixedly mounted in the bow of the frame, equipped with levers connected by rods with a two-arm lever of the helm, while the front wheel strut, movably fixed in the hub of the frame, equipped with a wheel fairing made in the form of a rotary keel, equipped with a two-arm lever, equipped with compensators, which are a clutch in which springs are located, separated by a washer, into which the ends of the rods are screwed to be attached to the arms of the consoles with a ball joint. 2. The motor glider according to claim 1, characterized in that the fuel tank is made of an elastic gas-resistant material located under the pilot's seat, the inner cavity of which is divided by a diaphragm into two unequal cavities, the upper cavity is equipped with two frames, between which springs are fixed at the corners, and is communicated with the atmosphere and the lower cavity through the check valves, and the lower cavity through the valve and the pipeline communicates with the carburetor of the engine.

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