RU2287771C2 - Winged-missile airframe - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the winged-missile airframe has an axisymmetric fuselage consisting of successively fastened nose, central and tail compartment, the latter of which is made in the form of a ramjet engine, as well as - a wing and a fin assembly. Assemblies for suspension of the missile under the aircraft are made on the fuselage outer surface, the assemblies represent profiled wells, which in pairs are located in the attachment frame of the nose compartment and on the front frame of the ramjet engine, they provide for suspension of the missile in a position turned on the longitudinal axis by an angle of 45 deg.

EFFECT: produced a unitized missile for bases of various kinds - air, ground and naval.

6 dwg

Description

The invention relates to the field of rocket technology, and more particularly to cruise missiles (CD), sea and aviation based.

The invention describes a device for a glider of the Kyrgyz Republic, which allows placing it on both marine and aircraft carriers, and can be used to create standardized missiles, including adapting previously developed missiles to new types of carriers.

The main requirements that ensure high performance requirements for modern KR include:

- supersonic flight speed, providing a high probability of overcoming missile defense;

- reach, allowing the carrier to use weapons without entering the zone of possible destruction by means of air defense;

- overall mass characteristics, allowing to place the CR on the most common marine (light ships of the class missile boat, corvette) and aviation (tactical aircraft) carriers.

The totality of these requirements is met by the marine-based anti-shipborne missile defense systems ZM80 (Moskit) and Yakhont (see the Russian Arms and Technologies Encyclopedia, Volume 3, Navy Armament, Arms and Technologies Publishing House, Moscow, 2001, pp. 103 and 126). At supersonic flight speeds (M≥2.5 ÷ 3), they have firing ranges of 120 km (KR "Mosquito") and 300 km (KR "Yakhont"). At the same time, in the course of the analysis of the characteristics of existing anti-ship missile launchers, no aircraft missiles of the required reach were detected: the supersonic anti-ship missile launcher X-31A has a firing range of 50-70 km (A.V. Karpenko, S.M. Ganin, "Domestic Aviation tactical missiles, "Bastion military-technical collection No. 1, 2000, St. Petersburg, p. 62), while modern ship anti-aircraft guided missiles (SAM) are capable of hitting carrier aircraft anti-ship missiles at distances of up to 100 km (SAM "Standard-2" mod.2) and - up to 140 km (SAM Standard-2 "mod.4). Therefore, the search for technical solutions aimed at adapting existing marine anti-ship missiles to aircraft carriers seems to be very relevant, however, proposals that provide a minimum amount of refinement of the basic model and a maximum degree of unification of missiles of various types of basing can be of practical importance.

A device is known for supersonic KR, described in the patent of the Russian Federation No. 2117907 from 08.20.98, MKI F 42 B 15/00, F 02 K 7/18. This KR is made according to the normal aerodynamic scheme and is equipped with an integrated power plant with a ramjet engine with ramjet starting and accelerating stage integrated in its air duct. The glider of the rocket includes an axisymmetric fuselage, wing and plumage, located according to the "plus" scheme (US Pat. No. 2117907). The fuselage is divided into compartments, including: the nose, which is the frontal air intake of the rocket, the middle, which is a fuel tank of a torocylindrical shape, and the tail, made in the form of a ramjet "supporting structure", that is, the ramjet combustion chamber directly forms the outer surface of the tail of the rocket.

In the patent of the Russian Federation No. 2215981 dated 12/10/03, a solution is described that allows compactly accommodating RCs of a similar scheme in a transport-launch container (TPK), as applied to the variant of its sea or land based.

However, aviation KR is characterized by different placement methods and a mechanical interface with carriers. As a rule, CRs are attached to the carrier aircraft by means of two pairs (front and rear) of standard or special suspension units located symmetrically with respect to the vertical plane of symmetry of the rocket, for example, two pairs of suspension units protruding beyond the contours of the upper part of the fuselage under the X-31 cruise missile aircraft and X-35 (A.V. Karpenko, S.M. Ganin, “Domestic Aviation Tactical Missiles”, military-technical collection “Bastion”. 2000, No. 1, S. Petersburg, pp. 64, 73). These nodes interact with locks and guiding elements of an aircraft launcher (APU).

Another feature of aircraft-based missiles is the predominant use of the "X" -shaped installation of aerodynamic surfaces, which allows you to place them on the AAP in the configuration with the wing open and plumage (figure 1 and 2).

With regard to the Kyrgyz Republic, performed according to the scheme described in patents No. 2117907 and No. 2215981, the implementation of aircraft suspension solutions typical for aircraft missiles is fraught with the following difficulties.

Firstly, the installation of the wing and feathering according to the “plus” scheme provided for in this circuit design prevents the compact placement of the RC on the carrier aircraft, since the placement of such missiles with open aerodynamic surfaces increases the overall dimensions of the “suspension” both in vertical and in horizontal planes (see, for example, figure 2 and 3). The first may impose restrictions on the airplane take-off and landing modes in order to avoid “touching” the runway (size “h”, Fig. 3) and cause the folding of the wing and aerodynamic steering wheel adjacent to the APU, and the second substantially complicates the layout conditions within a limited space (for example, between engine nacelles or in close proximity to other aircraft weapons (size "M", Fig. 3)). While the folding of the wing and the plumage on the "suspension" deprives the rocket of controllability in the initial phase of autonomous flight and, obviously, will require the use of special measures to stabilize its movement until the aerodynamic surfaces are fully disclosed.

Secondly, the central part of the RC of the considered circuit is a torocylindrical fuel compartment, which has a rather complicated structure consisting of two shells (internal and external), bottoms and partitions of a ring shape. Such designs of supersonic aircraft are made of welded aluminum alloys using special equipment for automatic welding. The introduction into the already developed design of the compartment of the new suspension units for the aircraft or the implementation for this purpose of finalizing the existing frames with the corresponding strengthening of the shells adjacent to them will require not only a large amount of calculation and design work, but also almost complete experimental testing of the static and dynamic strength of this most responsible and expensive glider assembly. And in the case when the base sample is at the production stage, redesigning, manufacturing and commissioning of welding equipment with all the associated costs is additionally required.

Thirdly, restrictions on the diameter of the circumscribed circle of the KR imposed by the dimensions of the transport and launch container in the basic marine version may not allow the suspension units under the aircraft to protrude beyond the fuselage (similar to the KR-X-31 and X-35 nodes). To the maximum degree of unification of the main components of the Kyrgyz Republic, the units “recessed” into the fuselage body to a greater extent meet the requirements, which implies the organization of special niches in the power frames of rockets for captures and guiding elements of an aircraft launcher. However, taking into account the real strength characteristics of the structural material of the frames (in this case, an aluminum fuel tank), for the perception of the forces and moments associated with the operation of the rocket on an airplane, sufficiently large construction heights of the power elements are required. This leads not only to an increase in the mass of the frames in which these nodes are made, but also to a limitation of the internal useful volumes of the rocket.

The choice of the place of installation of the suspension units for the aircraft along the fuselage length (outside the central compartment) not only allows you to completely borrow the design of the fuel tank of the basic sample for the aviation version of the rocket, but also expands the possibilities for choosing the structural material of the frames in which these nodes are supposed to be located. And if heat-resistant steels are traditionally used for the manufacture of hull ramjet assemblies, the choice of a high-strength alloy for the manufacture of a frame with front suspension units is predetermined by the consideration of reducing the building heights of its power elements and, consequently, the dimensions of the niches in the frame. At the same time, it is obvious that the design of this frame, as well as the front ramjet ramp, needs to be finalized and experimentally tested for strength, but their volume is incomparably less than the required work in the case of introducing nodes into the design of the fuel tank of the Kyrgyz Republic.

The choice of the position of the nodes in the cross section of the fuselage is due, on the one hand, to considerations of the rational configuration of the missile on the suspension under the plane and, on the other hand, to maintain its orientation in flight. This is realized by means of the provided post-launch “turn-over” of the CR along the roll by 45 ° to the marching flight position (with the spatial orientation of the rocket according to the “plus” pattern), which although it requires refinement of the rocket motion control algorithms, they will only apply to the initial stage of flight and The algorithms of the main sections of the trajectory, including guidance to the target, will not be affected. But the main effect of the implementation of this proposal, as a means of adapting a previously developed missile to a new type of carrier, is the preservation of the layout of its equipment and, therefore, the hull structures of the fuselage, since the placement of a number of anti-ship Raman assemblies, such as radio altimeter antennas, homing sight, fuel intake device, etc., is directly related to its orientation in flight.

The problem solved by the invention is the creation of the most unified design of the glider of the Kyrgyz Republic, corresponding to the conditions of placement on various types of media with a minimum degree of refinement of the base sample.

In the glider of the Kyrgyz Republic, containing an axisymmetric fuselage, consisting of sequentially fastened nose, center and tail compartments, the last of which is made in the form of a ramjet engine, as well as a wing and tail, located according to the "plus" scheme, the nodes for mounting the rocket are made under the aircraft, located in the butt frame of the nose compartment and in the front frame of the ram engine and representing niches on their outer surface, and the position of these nodes in the cross section of the fuselage provides The missile suspension is in a position rotated around a longitudinal axis by an angle of 45 °.

The essence of the proposed device is illustrated in Fig.1-6.

Figure 1-3 shows the options for placing the rocket on the plane in an "X" -shaped configuration and the "plus" scheme with the display of the layout features inherent in each of the options.

Figure 4 presents a General view of the CR in a marching flight configuration, Figure 5 - placement of the RC in the transport and launch container in relation to the sea version of its basing, Figure 6 - placement of the RC on the aircraft launcher of the carrier aircraft.

The cruise missile 1 with an axisymmetric fuselage is made according to the normal aerodynamic scheme with “plus-shaped” wings and plumage. The nose compartment 2 is a sidewall of the frontal air intake, the middle 3 is a fuel tank of a torocylindrical shape, the tail 4 is made in the form of a ramjet "supporting structure". In the air channel of the middle compartment 3 and in the ramjet 4 cavity, a starting-accelerating stage is located. On the connecting frames 7 of the nose compartment 2 and the tail compartment 4, fastened to the middle compartment 3, for example, by a threaded connection, niches of suspension units 6 are arranged at an angle of 45 ° to the planes of the rocket I-III and II-IV (see D-D 6), and forming, respectively, the front and rear belt of the suspension. Suspension nodes provide KR suspension on the aircraft launcher of carrier aircraft 5 with spread wings according to the “X”, i.e. in the most rational way with regard to aircraft carriers. At the same time, the nodes under consideration, recessed into the body of the rocket glider, do not interfere with its placement in the transport-launch cup 8 (Figure 5) when sea and ground based (see RF patent No. 2215981 dated 12/10/03 g).

The specified device operates as follows.

When hanging on a plane, rocket 1 (see FIG. 6) is fed by means of a loading device to the aircraft launcher 5 with a preliminary relative exhibition of the niches of the rocket suspension units 6 and APU capturing devices. Exciting devices are synchronously introduced by a manual drive or by means of a special device into the niches of the rocket suspension units 6 (DD, FIG. 6). There is a mechanical coupling and fixation of the rocket on the APU of the carrier aircraft. In this state, the rocket is at all stages of joint operation with the carrier aircraft until the launch of the KR.

At the “Start” command, the APU capturing devices, using a special drive mechanism, are synchronously unlocked and out of engagement with the rocket 6's suspension units. From this moment, the KR starts its autonomous movement while stabilizing the position with the help of aerodynamic rudders on commands from the onboard autonomous control system and with a programmatic rotation of the rocket relative to the longitudinal axis by 45 ° to the marching flight position according to the plus scheme. Next, the engine starts the start-up stage and accelerates the rocket. The final section of the flight path of the Kyrgyz Republic corresponds to the flight path of the rocket if it is based on marine carriers (when starting from the TPS).

Thus, we can conclude that the use of the proposed solution makes it possible to unify for the different type of basing of the Kyrgyz Republic its most responsible and labor-intensive unit in the manufacture - the glider. At the same time, due to the unity of production processes of the basic and unified products, the time and costs for developing the production of the latter are reduced, and subsequently due to mass production, the cost of manufacturing missiles as a whole is reduced.

Claims (1)

Glider of a cruise missile containing an axisymmetric fuselage, consisting of sequentially fastened nose, center and tail compartments, the last of which is made in the form of a ramjet engine, as well as a wing and plumage, located according to the plus pattern, characterized in that on the outside the fuselage surface is made nodes for hanging the rocket under the plane, which are shaped niches that are pairwise located in the butt frame of the nose compartment and on the front frame of the direct-flow air active engine to ensure the suspension of the rocket in a position deployed around a longitudinal axis at an angle of 45 °.

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