Compact aircraft with self-stabilising airfoils

FIELD: transport.

SUBSTANCE: invention relates to aircraft structural components and airfoils, particularly, to airfoils design for compact aircraft stabilisation in the plane of trajectory and for control in ballistic flight. Compact aircraft comprises fuselage, airfoils and tail plane. Airfoils are mounted at fuselage at the center of gravity to turn about aircraft lengthwise axis. Said airfoils represent two wings secured to turn assembly and arranged in symmetry about aircraft lengthwise axis in different planes.

EFFECT: higher aircraft efficiency, use of airfoils for flight control.

3 dwg

 

The invention relates to structural and aerodynamic elements of the aircraft (LA), in particular to elements perform the aerodynamic surfaces of the aircraft to the implementation of the stabilization of small aircraft in the plane of the trajectory and control of small aerial vehicle in flight along a ballistic trajectory.

The invention can be used in devices of small aircraft used for personal protection the basic carrier, which is allocated a limited weight on the stabilization device, for example, in devices of small maneuvering decoys, jammer disposable, detachable from the main carrier and make the trip on a ballistic trajectory.

The closest to the technical nature of the claimed device is an aircraft (Lebedev A.A., Chernobrovkin PS flight Dynamics of unmanned aerial vehicles. Barongis, 1962, s)containing the fuselage aerodynamic surface and a tail section attached to the fuselage. Aerodynamic surface in the form of two wings, symmetrical relative to the longitudinal axis of the aircraft and lying in the same plane.

A disadvantage of the known device is indefinitely the th position of the aerodynamic surfaces in space, occurring due to the perturbation of the aerodynamic moment on the roll at the Department of LA from the media. It is not possible to use the area of aerodynamic surfaces for flight control of small aerial vehicles, thereby decreasing the efficiency of application of small-size aircraft.

The task, which directed the inventive device is to eliminate the uncertainty of the position of the aerodynamic surfaces of small aircraft in space arising from the perturbation of the aerodynamic moment on the roll in the separation of small LA from the media and the creation oriented lifting force using the same aerodynamic surfaces in the plane of the flight path for flight control of the aircraft.

The technical result consists in increasing the efficiency of the use of small aircraft by providing semistability position of the aerodynamic surfaces relative to the fuselage and create oriented lifting force using the same aerodynamic surfaces in the plane of the flight path for flight control of the aircraft.

The technical result is achieved by the fact that on small aircraft, containing the eat the fuselage, aerodynamic surfaces and tail, aerodynamic surfaces mounted on the fuselage near the center of mass of the aircraft for rotation about the longitudinal axis of the aircraft and made in the form of two installed on the node rotation of aerodynamic wings, symmetrical relative to the longitudinal axis of the aircraft and not lying in one plane.

Due to the installation of the aerodynamic surfaces at an angle to each other when the roll LA occurs stabilizing moment in the plane of the roll, directed towards the opposite Bank.

Due to the installation of the aerodynamic surfaces on the fuselage of the aircraft using node rotation about the longitudinal axis LA decreases the magnitude of the aerodynamic moment, in which there is semistability block aerodynamic surfaces, as in this case, the stabilization of not only the aircraft, but only the aerodynamic surfaces relative to the fuselage of the aircraft, installed on the node rotation.

Due to the installation of the aerodynamic surfaces at an angle to the longitudinal axis of the aircraft creates an aerodynamic lifting force, correcting the flight path of the aircraft in the plane of fire, thereby polychaets the efficacy of small-sized aircraft.

The essence of the invention consists in the following. It is proposed to stabilize not all small aircraft, but only aerodynamic surfaces mounted on the fuselage for rotation around the longitudinal axis of the small-sized aircraft. At the same time the same aerodynamic surface is proposed to use for creating oriented directional aerodynamic forces to correct the trajectory of small aircraft.

Figure 1 presents the claimed small aircraft with self-stabilizing aerodynamic surfaces.

Figure 2 presents the possibility of using small aircraft with self-stabilizing aerodynamic surfaces.

Figure 3 presents a view of small-sized aircraft with side bow and shows the principle of semistability proposed aerodynamic surfaces.

Presented in figure 1 small-sized aircraft with self-stabilizing aerodynamic surfaces contains a fuselage 1, which set the rotation unit 2 with a fixed aerodynamic surfaces 3, and a tail 4. Site rotation 2 is a rolling bearing or sliding, to ascertain the tion on the fuselage 1 of the aircraft in the area of the center of mass 5 aircraft for rotation about the longitudinal axis 6 of the aircraft. The aerodynamic surface 3 is made in the form of two aerodynamic wings, mounted on the rotation unit 2. While the wings 3 are arranged symmetrically relative to the longitudinal axis of the aircraft 6 do not lie in one plane. Depending on the position relative to the longitudinal axis 6 of the aircraft wings 3 can create positive or negative lift force.

The device operates as follows. In the process of separation of the aircraft from 7 media 8 and its flight near the carrier 8 along a ballistic trajectory 9 due to the bevels of flow of the medium sliding LA or production variances, production elements LA to the aircraft operates the roll moment MPROBcausing rotation of the aircraft about the longitudinal axis 6 (see Fig 1, 3). After separation of the LA 7 moves along a ballistic trajectory 9 (see figa). When driving along a ballistic trajectory 9 speed LA has a horizontal VGand vertical VIncomponents (see figa). Under the action of the vertical component of velocity VInarise aerodynamic force applied to the center of pressure to the left FCLand to the right FCPaerodynamic surface 3 (see figure 3).

The magnitude of the aerodynamic forces applied to the aerodynamic surfaces 3, op is Adelaide by the formulas (S.p.kiselev. Physical fundamentals of aerodynamics of missiles. Military publishing house of the Ministry of defense of the USSR, M., 1976, p.45).

FKP=CxρVg22SKPsinαKP

FKL=CxρVg22SKLsinαKL

where Cx- the drag coefficient aerodynamic surfaces;

ρ - air density;

SCL, SCPsquare left and right aerodynamic surfaces;

VG- the vertical component of the velocity of flying small aircraft;

αCL- the angle between the vertical and the plane left the airfoil;

αCP- the angle between the vertical and the plane of the right aerodynamic surfaces.

When the perturbing moment in the direction shown in figure 3, the magnitude of the aerodynamic forces FCLis always greater than FCP. Due to the presence of the difference between aerodyn the economic forces F CL-FCPoccurs resulting stabilizing aerodynamic moment MCAMERA(see figure 3), the value of which is determined by the formula (Ingebrigsten and K.semendyaev. Handbook of mathematics. Publishing House "Nauka", M., 1965).

MCAMERA=FCL·L-FCP·L=MCP-MCP,

where L is the distance from the center of pressure of the aerodynamic surface 3 to the longitudinal axis 6 of the aircraft.

The resulting stabilizing aerodynamic moment MCAMERAalways acts in the direction opposite to the action of the disturbance torque roll MPROB(see figure 3). Due to the difference of the moments MCL-MCPthe aerodynamic surface 3 will turn in the rotation unit 2 on the angle at which the equality MCL=MCP. Similarly there is a stabilization of the aerodynamic surface 3 in the plane of the trajectory of LA when the perturbing moment the opposite is shown in figure 2.

After the end of the transient aerodynamic surface 3 are oriented symmetrically relative to the vertical component of airspeed. This phenomenon can be used to create oriented lifting force in the plane of the trajectory (positive or negative)required for assests is in the management of aircraft in the plane of the trajectory. Use small aircraft with self-stabilizing aerodynamic surfaces shown in figb, and figa - usage of the prototype. From the comparison shown in figure 2 trajectories of the prototype and of the present invention, it follows that the trajectory of small aircraft with self-stabilizing aerodynamic surfaces (see figb) is closer to the flight path of the carrier 8, than the trajectory of the flight of the prototype (see figa). This is achieved by improving the efficiency of application of small-size aircraft with self-stabilizing aerodynamic surfaces compared to the prototype.

In the search for sources of patent and scientific and technical information, the set of indicators proposed small aircraft with a self-stabilizing aerodynamic surfaces, not detected. Thus, the present invention meets the eligibility criterion of "new".

Based on comparative analysis of the proposed technical solutions with the prior art by sources of scientific-technical and patent literature it can be argued that between the set of features, including distinctive, and their functions and achievable goals, there is not chevigny causality. Based on the above we can conclude that the technical solution is not obvious from the prior art and, therefore, meets the criterion of "inventive step".

The proposed solution is characterized by simple design and can be used to create small maneuvering decoys and transmitters interference detachable from the carrier and flying on ballistic trajectories. Thus, the present invention meets the eligibility criterion "industrial applicability".

Small flying machine that contains the fuselage aerodynamic surface and a tail, wherein the aerodynamic surfaces mounted on the fuselage near the center of mass of the aircraft for rotation about the longitudinal axis of the aircraft and is designed as two mounted on the rotation unit aerodynamic wings, symmetrical relative to the longitudinal axis of the aircraft and not lying in the same plane.



 

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