RU2741672C1 - Head compartment of supersonic aircraft - Google Patents

Abstract

FIELD: aerospace engineering.

SUBSTANCE: invention relates to aerospace engineering, particularly to head compartments (HC) of AC. HC of supersonic AC includes frontal surface with aerodynamic needle (AN) and side shell. Front surface of HC is coaxial stepped. Peripheral stage is made in form of radiotransparent ring. Central concave bottom or central convex step top are made in the form of ring with 1-8 optically transparent illuminators. In addition, HC may have cylinder with gas of blowing and system of gas reduction. Gas supply holes on the front surface of HC are made in the root part of the AN or inner part of the central stage.

EFFECT: wider range of flight speed of AC.

19 cl, 3 dwg

Description

The invention relates to the design of the head compartments (HE) of supersonic, mainly unmanned aerial vehicles (LA) when they move in the atmosphere.

Known design schemes for supersonic GO aircraft, allowing you to implement the target task while minimizing the drag of the vehicle - see, for example, V.I. Feodosiev, G.B. Sinyarev "Introduction to rocketry", M, Oborongiz, 1960, pp. 38-43 (fig. 2.1-2.7, 2.9), pp. 46-49 (fig. 2.12, 2.14, 2.15), pp. 59-74 ( fig. 2.25-2.29, 2.31-2.33, 2.37-2.39, 2.41, 2.44, 2.45).

There are also known technologies for providing specified thermal regimes of HE of various types of supersonic aircraft, including the use of heat-resistant and heat-resistant structural materials, radiators and heat accumulators (including the implementation of phase transitions of the cooler), liquid (including evaporative effusion), gas and / or ablative cooling - see, for example, V.V. Berezikov, M.A. Burov, V.K. Ziberov et al. "The design of guided ballistic missiles", M., Voenizdat, 1969, pp. 133-136, fig. 6.8, 6.10-6.13.

As the closest analogue, the GO configuration of a supersonic aircraft was chosen with the most characteristic speed parameters of movement and a nose aerodynamic needle (AI) - see, for example, N.F. Krasnov, V.N. Koshevoy "Control and stabilization in aerodynamics", M., "Higher school", 1978, p. 106, fig. 1.12.4. (b).

The disadvantages of the closest analogue include the impossibility of using at high supersonic speeds (for example, Mach numbers more than 5 at low flight altitudes) optically transparent, and in some cases - radio-transparent frontal walls of the aircraft's HE for the operation of the onboard aircraft final guidance systems, which is due to the high level temperatures exceeding the operating range of thermal strength of structural optical and radio-transparent materials.

The technical objective of the present invention is to expand the range of flight speeds of aircraft with radio-transparent and optically transparent frontal surface elements.

The solution to this technical problem is achieved by the fact that the frontal surface of the HE is made coaxially stepped, while its peripheral step is made in the form of a radio-transparent ring, and the bottom of the central concave or the top of the central convex step is made in the form of a ring with 1-8 optically transparent windows. It is also allowed to make a single window in the form of an optically transparent ring, either flat in shape, or in the form of a spherical segment (convex or concave), coaxial AI. In some cases, an annular ridge, for example, cylindrical or conical, can be additionally placed along the peripheral (outer) contour of the nose of the central step. In turn, the peripheral step can be made in the form of a flat washer, or a spheroidal or conical convex ring, or a spheroidal or conical concave ring. Additionally, a cylinder with a boost gas and a gas reduction system can be placed in the HE, while the holes for supplying the boost gas to the front surface of the HE can be made in the root part of the AI or in the inner part of the central stage. In addition, a tank with a liquid coolant and a system for forced supply of a coolant can be additionally placed in the HE, while the holes for supplying a liquid coolant can be made in the root part of the AI and are evenly located in 1-4 planes of the AI cross-section or made in the inner part of the central stage ... In this case, the inclination of the coolant supply holes is performed at an angle from 0 ° to 80 ° against the direction of flight relative to the normal to the longitudinal axis of the aircraft (in the associated coordinate system). It should also be noted that the bottom of the central concave or the top of the central convex step can be recessed relative to the nose of the side shell of the central step to a depth of two diameters. It should also be noted that the side surface of the AI from its bow to the optical porthole can be smooth (without optically visible steps). In this case, the AI of the aircraft can be made folding, including with the possibility of telescopic adjustment of its length directly in flight in the range of lengths from 0.5 to 8.0 diameters of the circle described around the HE. In addition, at least two rotary flaps can be installed in the root part of the AI or on the ridge of the central step. In turn, the side shell of the central step can be cylindrical, or conical, or ogival, or with a longitudinal section in the form of a spline function, as well as in the form of a combination of surfaces of single and double curvature or only double curvature. In some cases, a disposable heat-shielding fairing can be additionally installed on the HE.

FIG. 1-3 show the longitudinal sections of the aircraft head compartment according to the proposed technical solution for various configurations of the peripheral and central stages. Notation accepted:

1 - GO aerodynamic needle;

2 - side shell of HE;

3 - peripheral stage (radio-transparent ring);

4 - central step;

5 - optical porthole;

6 - annular ridge;

7 - receiving (receiving-emitting) device of the optical range;

8 - radio range antenna device;

9 - onboard balloon with inflation gas;

10 - a system for reducing the blowing gas;

11 - pipeline;

12 - onboard tank with liquid cooler;

13 - system of forced coolant supply;

14 - holes in the AI for supplying the boost gas and / or liquid coolant;

15 - rotary flap.

The functioning of the airborne vehicle within the proposed technical solution is carried out as follows (Fig. 1-3). When the aircraft moves in the atmosphere at supersonic speed on the aerodynamic needle pos. 1, an oblique shock is formed, followed by the so-called separation zone up to the frontal surface of the GO. The air temperature in this zone is significantly less than the stagnation temperature of the flow at the bow end of the AI pos. 1. In this technical solution, it is proposed to additionally reduce the temperature on the optical window pos. 5 (in combination with the radio-transparent ring pos. 3) by:

- organization of appropriate gas circulation in the separation zone due to the coaxial stepped configuration of the frontal surface of the HE;

- organization of an additional system of shock waves inside the separation zone by blowing against the incoming flow of blowing gas;

- additional injection of liquid coolant and its phase transition into steam near the optical window pos. five.

The proposed technical solution presupposes that the frontal surface of the aircraft's GO is fully or partially (in the zones of the annular sectors of the step, pos. 3 and the zones of the windows, pos. 5, of the step, pos. 4), radio-transparent and optically transparent. For example, the frontal surface of the GO can be made with a radio-transparent peripheral stage pos. 3 in the form of a flat (Fig. 1), or convex (Fig. 2), or concave (Fig. 3) spheroidal or conical ring and with a coaxial central stage of pos. 4 convex (Fig. 1) or concave (Fig. 2, 3) configuration with a top (bottom) or in the form of a flat (Fig. 1, 3) ring with 1-8 optical windows pos. 5 (with AI pos. 1 in the center), or in the form of a convex or concave segment of a spherical shape (Fig. 2, pos. 5). Such a stepped configuration of the frontal surface of the GO allows, due to the calculated gas circulation in the separation zone, to organize a given temperature decrease in the zone of the optical window pos. 5, the structural material of which (for example, quartz glass), as a rule, is inferior in thermal strength to the structural radio-transparent materials of the stage pos. 3 (for example, specialized ceramics). Flat or segmental-spherical for optics (windows, pos. 5, including for different transmission ranges), flat, spheroidal or conical for the radio range (peripheral ring, pos. 3), the configuration of the frontal surface of the GO allows minimizing distortions of radiation entering the receiving (receiving - emitting) device, respectively, the optical range of pos. 7 and radio range antenna pos. 8.

It should be noted that within the framework of the presented technical solution, for example, the following can be used as on-board systems for the final guidance of aircraft:

- optical passive (including thermal imaging) receiving and / or active (laser) receiving-emitting devices of the visible, infrared and ultraviolet wavelength ranges (item 7);

- passive radio engineering (radio direction-finding) and / or active radar stations with fixed or scanning slot, horn, horn-parabolic, lens and other antenna devices (item 8);

- combinations of the above devices.

The intensity of vortex formation, as well as the ejection of coolant vapors in the separation zone, can be adjusted, for example, by introducing pos. 4 annular ridge pos. 6, which screens the area of the optical window pos. 5. This restricts the throw into the window area pos. 5 "hot" air streams from a shock wave. Taking into account the diagram of reception (reception - radiation) of the radiant flux by the onboard optical device of the final guidance pos. 7 - annular ridge pos. 6, it is advisable to make a cylindrical (minimization of the midsection of the step position 4 - see Fig. 1) or conical (in accordance with the angular field of view of the optical device position 7 - see Fig. 3) shape.

In order to exclude gas pulsations in the semi-closed cavities of the central stage, pos. 4 and, at the same time, the generation of additional oblique shock waves in the separation zone (which reduces the total frontal resistance of the aircraft) - blowing can be carried out, for example, with compressed nitrogen or air of a semi-closed cavity in front of the optical window pos. 5. For this purpose, a cylinder with blowing gas pos. 9, gas reduction system pos. 10 and pipelines pos. 11. In this case, the blowing gas from the onboard cylinder pos. 9 through the reduction system pos. 10 through the pipeline pos. 11 is fed to the outlets pos. 14 in the root of the AI pos. 1 or the inner part of the central stage pos. 4. The boost gas pressure can be adjusted depending on the parameters of the air in the separation zone.

Further decrease in the temperature of the optical window pos. 5 can be produced in portions of a liquid coolant, for which a tank with a liquid coolant pos. 12, the system of forced supply of the coolant pos. 13, pipelines pos. 11. In this case, the supply of liquid coolant to the frontal surface of the HE near the optical window pos. 5 is carried out, for example, through the holes pos. 14 in the root of the AI pos. 1 (with a uniform distribution of holes along the annular surface in 1-4 planes of the AI cross-section) or holes in the inner part of the central stage pos. 4. It should be noted that the liquid cooler from the tank pos. 12 is fed by means of its forced feed system, pos. 13 through a specialized pipeline pos. 11 at a given pressure. A kind of "baffle plate" for the coolant jets and at the same time the main "steam generator" during the phase transition is the "hot" nose of the central stage pos. 4 or an annular ridge pos. 6 (near the window, pos. 5) - see Fig. 2, 3. In this case, the slope of the liquid coolant jets supplied from the holes pos. 14 AI (and also, in some cases, from the holes in the side wall of the central stage, pos. 4), it is advisable to perform at an angle from 0 ° to 80 ° against the direction of flight relative to the normal to the longitudinal axis of the aircraft, which makes it possible to cool the window zone pos. 5 for all rational constructions of the stepped frontal surface of a GO with AI (see Fig. 2).

To ensure a given circulation of gas in the separation zone, the bottom of the central concave (Fig. 2, 3) or the top of the central convex (Fig. 1) step pos. 4 can be made recessed relative to the nose of the side shell of the central stage to a depth of two of its diameters.

To reduce parasitic illumination during operation of the receiving device of the optical range, pos. 7 side surface of AI pos. 1 from its bow to the optical window pos. 5 it is advisable to perform smooth (without optically contrasting steps and details).

Aerodynamic needle pos. 1 GO can be folded in order to minimize the starting dimensions of the aircraft. In some cases - for example, for maneuverable unmanned aircraft operating in a wide range of speeds - AI pos. 1 can be made controllable, for example, with telescopic adjustment directly in flight of its length. Taking into account the efficiency of lowering the temperature on the frontal surface of the HE in the framework of the proposed technical solution, as well as the available characteristics of modern and promising structural materials of the stages, pos. 3 and pos. 4 with their aerodynamic heating, - the range of lengths of the AI pos. 1 selected from 0.5 to 8.0 diameters circumscribed around the GO circle. In this case, it is allowed to use non-axisymmetric side shells pos. 2 GO, for example, for "semi-flat" configurations of an aircraft of the wave-type type (in this regard, the value of the diameter of the circle circumscribed around the GO is used in the claims).

In some cases, in the root part of the AI pos. 1 or on the crest of pos. 6 in front of the porthole pos. 5 can be installed at least two protective rotary shields pos. 15 (Fig. 2). On the cruise leg of the aircraft, without the targeted involvement of the onboard final guidance system, the flaps pos. 15 close (insulate) the optical window pos. 5. In the area of the final guidance of the aircraft, with the standard target operation of the on-board device of the optical range, pos. 7, shields pos. 15 unfold (for example, due to the "relay" supply of excess pressure of the blowing gas from the side of the window) and open the window pos. five.

Side shells of the central stage pos. 4 can be constructively executed, for example, cylindrical, conical, ogival, with a longitudinal section in the form of a spline function ("flexible rail"), as well as in the form of their combinations of single and double curvature or only double curvature (cylindrical-conical, cylindrical-ogival , conical with a transition to come to life, etc.).

Similar configurations of the central stage pos. 4 HEs allow you to optimize the gas circulation in the separation zone for a particular range of estimated flight speeds of the aircraft.

It should be noted that before the final guidance stage, the aircraft head compartment can be closed with a heat-shielding fairing, which is dropped before the start of the regular target operation of on-board radio engineering and optoelectronic complexes. Thus, the onboard volumes and masses of the charged boost gas, coolant, cylinders, tanks, as well as onboard support systems, including power supply and thermal control systems of the HE proper, are saved.

The application of the claimed technical solution, which allows the normal operation of on-board systems for the final guidance of radio and optical wavelength ranges in the extended high-speed range of supersonic flight, is advisable for aircraft for various purposes and aerodynamic configurations with an axisymmetric and non-axisymmetric cross-section of the fuselage HE and an aerodynamic needle.

Claims (19)

1. The head compartment (HE) of a supersonic aircraft (AC), including a frontal surface with an aerodynamic needle (AI) and a side shell, characterized in that the frontal surface of the HE is made coaxial stepped, while its peripheral stage is made in the form of a radio transparent ring, and the bottom of the central concave or the top of the central convex step is made in the form of a ring with 1-8 optically transparent windows. 2. The head compartment of a supersonic aircraft according to claim 1, characterized in that the only optically transparent window is made in the form of a flat ring or a spherical segment coaxial with the AI. 3. The head compartment of a supersonic aircraft according to claim 1, characterized in that an annular ridge is additionally placed along the peripheral contour of the nose of the central stage. 4. The head compartment of a supersonic aircraft according to claim 3, characterized in that the ridge is cylindrical or conical in shape. 5. The head compartment of a supersonic aircraft according to claim 1, characterized in that the peripheral stage is made in the form of a flat washer. 6. The head compartment of a supersonic aircraft according to claim 1, characterized in that the peripheral stage is made in the form of a spheroidal or conical convex ring. 7. The head compartment of a supersonic aircraft according to claim 1, characterized in that the peripheral stage is made in the form of a spheroidal or conical concave ring. 8. The head compartment of a supersonic aircraft according to claim 1, characterized in that the HE is additionally accommodated with an inflation gas cylinder and a gas reduction system, while the gas supply holes to the HE frontal surface are made in the root part of the AI or in the inner part of the central stage. 9. The head compartment of a supersonic aircraft according to claim 1, characterized in that a tank with a liquid coolant and a forced coolant supply system are additionally located in the HE, while the holes for supplying a liquid coolant to the front surface of the HE are made in the root part of the AI and are evenly located in 1- 4 planes of the cross-section of the AI are either made in the inner part of the central step. 10. The head compartment of a supersonic aircraft according to claim 9, characterized in that the slope of the coolant supply holes is made at an angle from 0 ° to 80 ° against the direction of flight relative to the normal to the longitudinal axis of the aircraft. 11. The head compartment of a supersonic aircraft according to claim 1, characterized in that the bottom of the central concave or the top of the central convex step is recessed relative to the nose of the side shell of the central step to a depth of two diameters. 12. The head compartment of a supersonic aircraft according to claim 1, characterized in that the side surface of the AI from its nose to the optical window is smooth. 13. The head compartment of a supersonic aircraft according to claim 1, characterized in that the AI is foldable. 14. The head compartment of a supersonic aircraft according to claim 1, characterized in that the AI is made with the possibility of telescopic adjustment of its length directly in flight in the range of lengths from 0.5 to 8.0 diameters of the circle described around the HE. 15. The head compartment of a supersonic aircraft according to claim 1, characterized in that at least two rotary flaps are installed in the root of the AI or on the crest of the central stage. 16. The head compartment of a supersonic aircraft according to claim 1, characterized in that the side shell of the central stage is cylindrical or conical. 17. The head compartment of a supersonic aircraft according to claim 1, characterized in that the side shell of the central stage is made ogival or with a longitudinal section in the form of a spline function. 18. The head compartment of a supersonic aircraft according to claim 1, characterized in that the side shell of the central stage is made in the form of a combination of surfaces of single and double curvature, or only double curvature. 19. The head compartment of a supersonic aircraft according to claim 1, characterized in that the HE is additionally equipped with a resettable heat-shielding fairing.

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