RU2569165C1 - Aircraft - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: claimed aircraft comprises fuselage, wing, tail unit and propeller assembly including engine, transmission and aligned counterrotation propellers. Propeller blades are composed of flexible bands with 4…200 extension, their roots being secured at time-rotation drums and ends being composed of centrifugal streamlined weights with rigidly fixed or controlled aerodynamic rudders. Propeller mid sections as-folded do not exceed that of aircraft fuselage. Elastic coating composed of aerodynamic profile can be applied on said band from its end section and to over at least 25% of the blade length.

EFFECT: increased midflight path of high-altitude aircraft.

5 cl, 4 dwg

Description

The invention relates to aircraft, and more specifically to aircraft (including unmanned) with screw propellers.

Airplanes with various structural and layout schemes of propeller-driven installations (VMUs) are known - see, for example, V.B. Shavrov. The history of aircraft designs in the USSR, (t. 1, 2), M .: "Engineering", 1978; P. Bowers. Aircraft of unconventional schemes. M .: "World", 1991.

As the closest analogue, an airplane according to RF patent No. 201563 (priority from 01/16/1992), equipped with coaxial large-diameter coaxial propellers (BB), deployable and normally functioning due to centrifugal forces during rotation of the VMU shaft, was adopted.

However, this technical solution is proposed for implementation only on aircraft with a push-type explosive and does not allow an increase in the length of the explosive blades beyond the length of the tail boom in the presence of a tail.

The aim of the invention is the creation of an aircraft with a VMU of both pushing and pulling type, equipped with explosives with ultra-large elongation blades (not limited due to the design features of the aircraft along its longitudinal axis).

This goal is achieved by the fact that in an aircraft containing the fuselage, wing, tail, VMU (including engine, transmission and coaxial counter-rotation propellers), the blades of the explosive are made in the form of flexible tapes with an elongation of 4 ... 200, the root parts of which are mounted on synchronously rotary drums, end parts are made in the form of streamlined centrifugal loads with rigidly fixed or controlled aerodynamic rudders, while the mid-section of the explosive in the folded configuration does not exceed the mid-section of the aircraft fuselage. An elastic coating made in the form of an aerodynamic profile can be applied to the tape from its end part and not less than 25% of the total length of the blade. The width of the flexible tape along the span of the blade can be constant or variable. In the case of using rotary blades of explosives on centrifugal loads, control units and aerodynamic rudder drives can be additionally installed. Moreover, synchronously rotary drums can be made with the possibility of their simultaneous rotation (up to an angle of 90 ° inclusive) perpendicular to the plane of rotation of the explosive.

In FIG. 1 shows the structural layout of the aircraft according to the proposed technical solution, FIG. 2, 3 - BB blade in plan, in FIG. 4 is a cross-section of an explosive blade with an applied elastic forming coating.

Designations accepted:

1 - aircraft fuselage;

2 - wing;

3 - tail unit;

4 - propeller installation;

5 - explosive blade;

6 - drum;

7 - centrifugal load;

8 - aerodynamic steering wheel of a centrifugal load;

9 - shape-forming elastic coating.

The functioning of the device according to the proposed technical solution is as follows.

A plane takes off from the Earth, for example, either with the help of a rocket launch-booster stage (SRS), or behind a towing plane in a glider. In this case, the blades pos. 5 explosives are rolled onto the drums pos. 6 and do not advocate for the midsection of the fuselage pos. 1. It should be noted that the acceleration of the aircraft by means of the CDS can be carried out both in the march configuration from the ejection device, and from a specialized transport and launch container with the wing folded pos. 2 (as well as, in some cases, with the tail unit, pos. 3).

Upon reaching the maximum lift height with the use of CPC or towing, the aircraft, according to the proposed technical solution, switches to the march configuration if necessary (separates the CPC, unfolds the wing pos. 2 and the tail unit pos. 3), includes the BMP pos. 4 and deploys by means of centrifugal forces the blades pos. 5 explosives, which are simultaneously pulled from the reels pos. 6, transfers the target equipment to the standard operation mode and starts the programmed flight (including with additional climb) or directly controlled (adjusted) from the control point (ground, surface or air based) flight - see fig. one.

VMU pos. 4 within the framework of this technical solution includes an engine (piston, gas turbine, electric, etc.) located in the fuselage pos. 1 aircraft and kinematically connected with counter-explosive explosives. In this case, the distance between the planes of rotation of the front and rear explosives is taken, as a rule, in the range of 0.05 ... 0.25 of the diameter of the explosive with its greatest deployment: here the minimum value is selected from the condition for excluding overlap of the blades pos. 5 explosives, and the maximum - from the condition that the difference in torque between the front and rear explosives is less than 20% (see, for example, BC Vozhdaev. Method and results of parametric studies of the aerodynamic characteristics of the coaxial system of screws in hovering and vertical lifting modes. M: TsAGI proceedings , issue 1953, 1976, p. 48-50). Since it is known that in coaxial explosives the circumferential induced velocity is close to zero, there are practically no circumferential losses, unlike a single screw. The balancing and piloting of the aircraft is also simplified, since coaxial explosives provide symmetry around the airflow of structural members behind the screws (i.e., there is no reactive moment), and the total gyroscopic moment is zero (i.e., the left and right maneuvers of the aircraft are the same). Rational in terms of the effectiveness of the VMU and the conditions for folding the explosives, the range of blade elongation is 4 ... 200. Here the minimum value corresponds to the so-called. fan mode, maximum - to the maximum operating mode of explosives according to the conditions of balancing the blades.

It should be noted that the use of coaxial explosives of extra-large diameter is most advisable on high-altitude aircraft with an extended marching section, cruising in the stratosphere at altitudes of more than 12 ... 15 km. At the same time, for effective (from the point of view of the efficiency of the screw propulsion) conversion of the rarefied air stream into the discarded working fluid, the blades of the explosive are advantageously performed profiled along the span. In this case, on the power part of the blade - the tape - apply the elastic coating forming poses to the specified aerodynamic profile. 9 - see FIG. 4. Since the main thrust of the explosive is created by the end sections of the blades pos. 5 - there, no less than 0.25 times the total length of the blade, it is advisable to apply an elastic coating pos. 9 (the total length of the coating is determined by the ability to collapse the blades pos. 5 with the coating pos. 9 on the drum pos. 6 so that the folded explosives do not protrude beyond the midsection of pos. 1 of the aircraft - see Figs. 2, 3).

Preset blade profile pos. 5 along its span in addition to aerodynamic coating pos. 9 is formed by geometric twist due to the corresponding rotation of the root part, mounted on the drum pos. 6 (carried out by turning the drum pos. 6 at an angle of up to 90 ° inclusive perpendicular to the plane of rotation of the explosives), as well as the corresponding rotation of the end part of the blade pos. 5 due to the interaction of the air flow with the aerodynamic wheel pos. 8 centrifugal load pos. 7. At the same time, the steering wheel pos. 8 can either be hard-wedged (analogy with a fixed-pitch explosive), or it must allow the possibility of operational control of it during the flight (analogy with a variable-pitch explosive). In the latter case, centrifugal load pos. 7, an additional control unit (receiver of control signals) and an actuator (for example, electromechanical) for steering the steering wheel pos. 8. In order to minimize the aerodynamic drag of explosives, centrifugal loads, including the placed mechanisms and equipment, should have a streamlined shape optimized for the cruising speed of rotation of the screws. In this case, the angle of attack of the blades of the rear explosive, taking into account the bevel of the flow from the front explosive, is usually 1 ° ... 1.5 ° greater than the angle of attack of the blades of the front screw.

It should also be noted that the width of the blade (power tape) pos. 5 along the span — otherwise, the aerodynamic chord of the blade — may be constant or variable — see FIG. 2, 3. In this case, the “widened” end part of the blade, as a rule, is advisable to use for coaxial explosives of relatively small diameter with a large number of blades (the so-called fan mode), and the “narrowed” end part is for single-mode explosives of extra large diameter with stringent requirements for dimensions when folded.

The landing of the aircraft according to the proposed technical solution is usually carried out according to the glider: before landing, the VMU is throttled, while the blades of the explosive pos. 5 synchronously wound on the reels pos. 6.

The application of the proposed technical solution is most advisable on unmanned high-altitude aircraft for remote monitoring of the Earth’s surface, regional relay of radio and optical signals (including areas with complex terrain, polar, etc.), studies of the upper atmosphere, ionosphere and magnetosphere, etc. n., including quickly brought to the marching altitude by means of the cruise control system, performing a long cruising flight in rarefied layers of the atmosphere (the so-called “aerodynamic satellite” concept).

Claims (5)

1. Aircraft containing the fuselage, wing, tail, propeller installation, including an engine, transmission and folding coaxial counter-rotation propellers (BB), characterized in that the blades of the BB are made in the form of flexible tapes with an extension of 4 ... 200, the root parts of which are fixed on synchronously rotary drums, and the end parts are made in the form of streamlined centrifugal loads with rigidly fixed or controlled aerodynamic rudders, while the midsection of explosives with blades wound on drums does not exceed dividing the fuselage. 2. The aircraft under item 1, characterized in that on the tape from its end part and not less than 25% of the total length of the blade fixed elastic coating made in the form of an aerodynamic profile. 3. The aircraft under item 1, characterized in that the width of the flexible tape along the span of the blade is made constant or variable. 4. Aircraft according to claim 1, characterized in that the control units and aerodynamic rudder drives are additionally installed on centrifugal loads. 5. The aircraft under item 1, characterized in that the synchronously rotary drums are made with the possibility of their simultaneous rotation through an angle of up to 90 ° inclusive perpendicular to the plane of rotation of the explosive.

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