RU2544446C1 - Rolling cruise missile - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: two-stage rolling cruise missile (CM) with five degrees of freedom of spatial movement includes a housing stabilised as to the sixth degree of freedom by rotation in the form of a rotation figure with wings, rudders and an active aerodynamic nozzle, a single-duct control system, a steering gear, a detachable launching accelerator with an axial turbo-jet engine with a gas-dynamic nozzle, a cruise stage with an n duct system of formation of lift capacity in a rotation mode and a small-size disposable turbo-jet engine with a folded air intake, and a self-guidance head.

EFFECT: simpler control and stabilisation of a cruise missile, lower weight and dimensions of the cruise missile.

2 dwg

Description

The present invention relates to the field of precision weapons (TO) and applies simultaneously to cruise missiles (CR) and rotating missiles (BP).

The concept of conducting modern and future wars is based on the widespread use of maintenance. THAT is called such types of weapons that do not hit the squares, but strike directly at the target’s body or at its most vulnerable places. First of all, it is supposed to inflict irreparable damage to the enemy with unmanned delivery vehicles launched from medium and long distances even before the direct contact of ground forces, manned aircraft and the Navy.

By the mid-80s in the USSR, two very important and effective types of maintenance were developed and adopted among a number of others. The first concerned the destruction of all types of air targets, the functioning of which takes place at altitudes of up to 4 km, and this type of TO was a portable rotating anti-aircraft guided missile (ASGM) with a passive optical homing head (OGS), effective at all angles of the target, on any cloud backgrounds and with organized optical counteraction (OOP) by air targets. This complex, known as the Igla, passed a comprehensive test in many military conflicts and surpassed all foreign similar complexes in combat effectiveness. However, the Igla OGS technology was given without a license, cheaply abroad by the administration of LOMO. Moreover, the complex was first sold, and then hastily declassified.

Thus, the United States and NATO received information about our capabilities to defeat their aircraft. The conclusion was made by the United States and found expression in the development of the Kyrgyz Republic such as the Tomahawk and others, the radiation of which is small and does not allow the use of the Igloo to destroy missiles and aircraft of this type.

The second type of maintenance concerned systems using a laser beam reflected from targets for operation. These systems are designed to destroy low-emitting land, sea and other targets where the use of passive OGS is inefficient. A rotating guided artillery shell (VUAS) was developed, fired from a 150-mm howitzer and providing for the destruction of low-emitting targets, provided they were illuminated by the operator of a manual backlight station, which weakened the efficiency of use due to the vulnerability of the backlight operator. This WUAS was also declassified and its production license was sold to China. Through the efforts of the United States, the dependence on the highlighter was eliminated by organizing the illumination of necessary targets from space. Against such a system of using MOT in the form of Raman radiation and laser illumination from space, we have no opposition and we are practically defenseless, as the events in Iraq (2 times) and Yugoslavia showed. In Yugoslavia, with the connivance of Russia, NATO fired 22,000 bombs and missiles, of which more than 70% were TOs, including more than 500 Tomahawk missiles, about 450 stationary targets and more than 900 moving targets were hit.

In view of the foregoing, that is, the high efficiency of VZUR, VUAS and KR, it is proposed to consider a technical solution (TR) of a new type of CR as a hybrid of conventional KR and VR in the form of a rotating cruise missile (SRS).

There are two ways to ensure the stability of both uncontrolled ballistic and controlled movement of missiles and shells: stabilization by plumage and stabilization by rotation. The controllability and stability of non-rotating missiles and shells with 6 degrees of freedom of movement according to the first method is achieved by more complex principles of construction and operation of control and stabilization systems, external aerodynamic and internal layout schemes, and on-board autopilot and manual piloting equipment must generate a large number of commands, and executive bodies - a large number of control forces and moments, since it is necessary to ensure stabilization of the angular positions of the rocket around three axes, roll, course and pitch, and its management of 6 degrees of freedom. In the second method, there is no need to have an on-board stabilization system, since the rocket acquires a sufficient margin of stability in a natural way due to the gyrostabilizing moment of the rotating body. In this case, the control of the components of the control force vector (CSS) is also significantly simplified and implemented through a single channel, therefore, the BPs are called single-channel. In addition, imparting rotation increases aerodynamic and gasdynamic symmetry, since the influence of inaccuracies in the symmetry of the body and the aerodynamic elements mounted on it is eliminated and the eccentricity of the engine thrust arising due to uneven combustion of the fuel is compensated (1, 2, 3, 4).

At present, only 6-degree degrees of freedom of the Kyrgyz Republic are known, stabilized by the first method (5), but they are analogues only for their intended purpose. Close to the destination КР (5) contain an elongated cylindrical or other form of the hull, on which folding wings, plumage and other aerodynamic elements are installed, a small disposable turbojet engine (OTDR) is installed inside the hull or outside on the consoles, the КР is also equipped with on-board automatic pilot systems and navigation, for example, an autonomous inertial system and / or satellite, terrain navigation, etc. Close-to-destination missiles are the most important type of medium and long-range missile defense, and with massive use they can easily be classified as strategic weapons, and missiles can be of various bases, land, air, sea, including submarines. They are characterized by a high probability of hitting a wide range of targets, and the launch of the Kyrgyz Republic is practically not fixed by modern means of warning about a missile attack. The massive use of missile defense even with a conventional non-nuclear warhead (warhead) according to the results of the destructive action is comparable to the use of nuclear weapons with the difference that only specified military and other targets are hit with a minimum of civilian casualties. The disadvantages of close to the purpose of the Kyrgyz Republic are the increased complexity of the stabilization and control systems, since they have 6 degrees of freedom, and accordingly the high cost of technical means, which, in turn, increases the cost, own weights and dimensions of both the missile itself and the launchers ( PU).

The VZUR (1, 6) and VUAS (6), which are close in technical essence, are known, which contain an elongated cylindrical body with 5 degrees of freedom, stabilized along the 6th rotation around the roll axis and equipped with small-sized folding beveled tail stabilizers, a solid fuel jet engine, equipped with the main traction nozzle and concentrically located micro nozzles, beveled at an angle of 5-20 relative to the longitudinal axis of the rocket, OGS, which determines the coordinates of the target, direction and angular velocity of rotation of the line of sight anija "missile-target" and generates a control signal informative features and parameters which contain information about this output connected to the control system in a rotational mode, the output of which is connected to the steering actuator aerodynamic control surfaces.

Vzur have significant advantages over rockets stabilized by plumage, including those close to the destination of the Kyrgyz Republic. For example, the stability of the movement of the ASGM is achieved in a natural way without the expense of technical means due to the gyroscopic effect, the control of the components of the control force vector (US) is simpler and is implemented through one channel. Due to the twisting of the HSSM case, in addition to the natural stability of the angular positions and movement, they acquire higher aerodynamic and gas-dynamic symmetry, simpler aerodynamic and internal layout schemes. These distinctive features allow you to design and manufacture more compact, including wearable systems, dramatically reduce their own weight and dimensions of both the rocket and the launcher (launcher).

VUAS, which are close in essence, have almost the same functional composition as the VZUR. The only difference is that if the VZUR contains a jet engine, then for VUAS an external mover is used - a gun.

However, VZUR and VUAS have a narrow purpose and scope only as anti-aircraft missiles to hit low-flying air targets (VZUR) and as a homing missile to destroy closely located low-emitting ground targets (VUAS).

The technical solution closest in technical essence (TR) to the claimed one is TR of an aircraft of vertical take-off and landing (LAVVP) (7 RF patent No. 2378156). The specified LAVVP contains a body made in the form of a flat figure of rotation, equipped with wings and rudders and stabilized by rotation around the axis of the course, a single-channel control system in rotation mode, connected to the steering gear by the output, one axial turbojet engine (TRD), on the nozzle of which a multi-pass spiral gas-dynamic nozzle (GDN), and an active spiral aerodynamic nozzle (ADN) is installed on the upper half-plane of the apparatus and a device for starting twist is installed on the lower half-plane. The described apparatus uses the aerodynamic lifting force of the rotating wings for takeoff, landing and flight, due to which, unlike the VR, you can use a much more economical turbojet engine with a thrust coefficient (CT) of less than one, and at the same time vertically take off and land, hang for a long time and fly over long distances . At the same time, imparting rotation provides the apparatus with a large margin of stability in the regime of takeoff, landing and flight at low speeds, which are unfavorable for conventional aircraft of GDP at adverse speeds in the presence of adverse weather conditions and other external disturbances. However, the device has large dimensions and its own weight, which is much lower compared to the CR and, moreover, the VZUR marching flight speed and long prelaunch time, since at the start the device must spin up and gain the required rotation speed, which provides lifting force of more than take-off weight.

The aim of the invention is the change of purpose (compared with the prototype in technical essence) and the expansion of applications. When compared with the prototype for its intended purpose, simplification of control and stabilization, reduction of its own weight and dimensions are achieved.

, где n - число пар крыльев, причем направление закручивания дискретной спирали совпадает с направлением вращения ракеты, а в головной части установлена одна пара переключаемых рулей, также ракета снабжается n-канальной системой формирования подъемной силы в режиме вращения, выходы которой подключены на приводы крыльев.This goal is achieved by the fact that the proposed SRS, like the closest LAVVP in terms of technical essence, contains a body with 5 degrees of freedom made in the form of a rotation figure, stabilized by 6 degrees of freedom by rotation, on which wing aerodynamic elements are mounted to form a lift forces, rudders for forming the control force and active helical ADN, also contains a single-channel control system, the output is connected to the steering gear, the turbojet engine on the nozzle of which is installed GDN, and differs in that the housing is made in the form of an elongated cylinder with a pointed warhead stabilized by rotation not around the axis of the course, but around the axis of the heel, in the tail of which a small OTDR is installed, and the rocket body is equipped with a folding air intake and a detachable starting accelerator is mounted on the pyrozam’s tail on the nozzle which is also installed GDN, and in the head part of the 1st marching stage of the rocket installed passive, or semi-active, or active homing head, along the longitudinal axis of the rocket installed on a spiral spiral of n pairs of small folding wings switched synchronously in frequency and phase of rotation of the rocket according to the sign of the angle of attack at a certain angle up to 20 relative to the longitudinal axis of the rocket in increments of the angle of heel $$\frac{2\pi }{n}$$

, where n is the number of pairs of wings, and the direction of twisting of the discrete spiral coincides with the direction of rotation of the rocket, and one pair of switched rudders is installed in the head part, the rocket is also equipped with an n-channel system for generating lift in rotation mode, the outputs of which are connected to the wing drives.

Thus, the novelty and the main distinguishing feature of the claimed TP consists in introducing previously unknown neither in the field of TP analogues for purpose, nor in the field of TP analogues and prototype in technical essence of the n-channel system for the formation of aerodynamic lifting force in rotation around the roll axis (in TR the prototype wings do not switch according to the sign of the angle of attack, since the device is stabilized by rotation around the axis of the course). Wings are completely absent in the close TDGM, since the rocket moves along its trajectory by the thrust of a solid-fuel engine, the CP of which is much larger than unity, and the aerodynamic lift component is insignificant and has a second order of smallness (1). The introduction of the indicated feature allows us to combine the advantages of rotating missiles and vehicles with the advantages of conventional non-rotating missiles, as well as the advantage of reducing drag due to the excited vorticity of the incoming air flow. The traction force of known RS is spent on overcoming inertial forces, on the formation of aerodynamic lifting force, and some of it is irrevocably spent on overcoming the "frontal" drag of the air. In the claimed TR, the energy costs of the OTDR to overcome the resistance of the medium are reduced. The coordinated relative position of the wings, the rudders and the active ADN excites the flow vortex, the energy of the excited soliton vortex accumulates in it and forms a “cavity” of reduced pressure around the rocket and the air resistance decreases. Thus, the proposed combination of gas and aerodynamic elements installed on the rocket and their coordinated relative position allows one to obtain an additional positive effect and increase the efficiency of the OTDR thrust. The expected reduction in self-weight and dimensions of the SRS in comparison with the known KR will allow to obtain an additional beneficial effect of the possibility of creating compact launchers or multiple launch rocket systems of individual Raman guidance, since we are also lagging behind in this area.

Figure 1 presents a drawing of the claimed WRC, figure 2 is an enlarged functional diagram of the WRC, explaining the principle of functioning of the rocket and in more detail the principle of formation of lifting force in rotation mode. In Fig. 1 are indicated: a starting accelerator 1 with GDN 2, housing 3, a small OTRD 4, GDN 5, a folding air intake 6, three pairs of folding wings 7, 8, 9, rudders 10, ADN 11. In Fig. 2, a block is indicated: 1 navigation, autopilot (AP) 2, switch 3, homing head 4, gyroscope 5 roll, combined with sensors of quadrature reference signals and three-phase reference signals, multiplexer 6, wings 7, 8, 9, rudders 10 (for ease of perception, the numbering of wings and 1 and 2 coincides), power amplifiers 11, 12, 13, wing drives 14, 15, 16 and steering gear 17.

$$sign\left(\sin \omega t+\frac{4\pi }{3}\right),$$

которые поступают на входы усилителей 11, 12, 13 мощности, а с выхода усилителей на релейные приводы 14; 15; 16 крыльев 7; 8; 9. Эти приводы переключают крылья по знаку угла атаки синхронно по частоте и фазе вращения ракеты, начальный отсчет которой задан гироскопом 5 по вертикали, в результате чего все результирующие интегрально демодулированные за каждый оборот векторы подъемной силы последовательно через угол 120° направлены вверх по вертикали противоположно вектору силы гравитации. В ближней зоне при подлете к цели сигнал активации поступает на ГС 4, включает ее в режим поиска цели путем сканирования подстилающей поверхности; и после захвата цели ГС 4 автоматически переходит в режим автосопровождения и сигнал захвата поступает на переключатель 3, который подает СУ в АП 2. С этого момента ракета управляется не сигналом блока 1 навигации, а сигналом ГС. При подходе к цели и начале пикирования третий сигнал с выхода АП 2 переключает мультиплексор 6, который отключает опорный сигнал и вместо него теперь на вход УМ 13 подает СУ, при этом пара крыльев 7 переходит в режим формирования УС совместно с парой крыльев 10. При этом увеличивается суммарная УС и повышается маневренность, что важно при работе по подвижным целям.WRC operates as follows. In the initial state, the missile is equipped, installed in a transport and launch container or in a multiple launch rocket launcher, and has undergone prelaunch training. At the “start” command, a blow-out charge is triggered, the rocket leaves the launch tube, then the launch accelerator 1 is launched, accelerates the rocket to marching speed and simultaneously spins it around the roll axis due to the action on the jet of the gas-turbine engine 2. After the fuel is exhausted in the accelerator, the pyro locks are triggered (on they are not shown in the figure) and the accelerator 1 is separated from the rocket. At the same time, commands are issued to launch the OTDR 4 and to unlock the folding air intake 6, wings 7, 8, 9 and rudders 10, which exit the grooves and are fixed in the working position. In accordance with the flight mission recorded in the rocket’s memory, the navigation unit 1 generates a control signal for working out the trajectory of the given approach route to the target, which is fed to the AP 2. The AP 2 generates a standard single-channel control signal that is fed to the steering gear 17, on the axis of which the steering wheels are mounted 10, which begin to switch according to the sign of the angle of attack. When deviating the trajectory of the rocket, the rudders 10 form a control force that returns the rocket to the given trajectory. The reference signal sensors combined with a roll 5 gyroscope synchronously in the frequency and phase of the rocket rotation generate the quadrature reference signals sinωt, cosωt, where ω is the angular velocity of the rocket, t is time. These signals enter AP 2; they are needed to form a single-channel control system. Methods and devices for the formation of a single-channel control system are known from the theory and practice of designing a VZUR and therefore are not considered in the application. The second roll gyroscope sensor 5 converts the roll angle into three-phase “meanders” sign (sinωt), $$sign\left(sin\omega t+\frac{2\pi }{3}\right),$$

$$sign\left(\sin \omega t+\frac{\mathrm{four}\pi }{3}\right),$$

which go to the inputs of power amplifiers 11, 12, 13, and from the output of amplifiers to relay drives 14; fifteen; 16 wings 7; 8; 9. These actuators switch wings by the sign of the angle of attack synchronously in the frequency and phase of rotation of the rocket, the initial count of which is set by the gyroscope 5 vertically, as a result of which all the lifting force vectors integrally demodulated for each revolution are directed upward through the angle 120 ° in the opposite direction gravity force vector. In the near zone, when approaching the target, the activation signal is supplied to the GS 4, turns it on in the target search mode by scanning the underlying surface; and after the target is captured, the GS 4 automatically switches to auto-tracking mode and the capture signal enters the switch 3, which supplies the control system to the AP 2. From this moment, the rocket is controlled not by the signal of the navigation unit 1, but by the GS signal. When approaching the target and the beginning of the dive, the third signal from the output of the AP 2 switches the multiplexer 6, which disconnects the reference signal and instead of it now supplies the SU to the input of the UM 13, while a pair of wings 7 goes into the mode of formation of the CSS together with a pair of wings 10. In this case the total CSS increases and maneuverability increases, which is important when working on moving targets.

The claimed SRS along with the well-known RCs can be used for strikes of the 1st and 2nd waves against clusters of land, sea, both stationary and moving targets at medium and long distances. The essence of the declared TR in the further development of such promising areas of maintenance as KR and IZUR through the creation of a hybrid of BP and KR, combining the useful properties and advantages of the 1st and 2nd type of maintenance. The prospect of the further development of such carriers consists in the creation of small-caliber Raman and Raman scattering, weight and dimensions for multiple launch rocket systems with individual guided missiles.

It is shown above that a previously unknown feature of the system for generating lift in rotation mode is introduced in the declared TR and is characterized by an unknown new set of features that provides far from obvious and original creation of a hybrid of devices having heterogeneous stabilization and control methods, which does not follow explicitly from the current level rocket technology. The claimed solution can be implemented using well-known materials, fuel, OTDD, and as the wing drives can be used worked out by the practice of the development of the VZUR and VUAS steering drives. Thus, the claimed TR meets all the criteria of an inventive step.

LIST OF USED LITERATURE

1. Krasovsky A.A. et al., "Fundamentals of Theory and Design of Rotating Single-Channel Controlled Missiles," VVIA im. Zhukovsky, 1963.

2. Arkhangelsk A.A. and others, "Design of anti-aircraft guided missiles", M., MAI, 1999.

3. Kazakov I.E. et al., "Control systems and dynamics of missile guidance", VVIA im. Zhukovsky, 1973.

4. Technical description of the product 9E46 and complex 9K32M, Oborongiz, 1970.

5. "Missile technology", "Operational system" Air BASE NEW-factoria, Big Aviation Encyclopedia "Corner of the Sky", Air.war.ru "Science" - "American sea-based KR"; R. Radomirov - Description of the Kyrgyz Republic "SCALP-EG (France); AGM-84; SLAM-EM; AGM-129ASM; BGM-109ACM; BGM-109" Tomahawk "; JASSM-BZ (USA); KEPD-150TAURUS (Germany- Sweden) - analogues for their intended purpose.

6. US patent No. 4309393; Patents of the Russian Federation No. 2101742, 2093850; Analogs by technical nature.

7. RF patent No. 2378156 "Aircraft of vertical take-off and landing" - prototype.

LIST OF ABBREVIATIONS USED

TO - Precise weapons; KR - cruise missile; BP - a rotating rocket; WRC - rotating cruise missile; PU - launcher; US - control force; SU - control signal; CT - thrust coefficient; VZUR - rotating anti-aircraft guided missile; VUAS - rotating guided artillery shell; ADN - aerodynamic nozzle; GDN - gas-dynamic nozzle; GS - homing head; TR - technical solution; CA - activation signal; OOP - organized optical opposition; LA - aircraft; LAVVP - aircraft of vertical take-off and landing; TR - technical solution.

Claims (1)

A rotating cruise missile with five degrees of freedom of spatial movement, comprising a body made in the form of a rotation figure, equipped with wings, rudders and an active aerodynamic nozzle, stabilized by sixth degree of freedom of rotation, a single-channel control system, an output connected to the steering gear, an axial turbojet engine, to the nozzle which has a gas-dynamic nozzle, characterized in that in order to change the purpose and expand the scope of applications it is made of two of a separate detachable starting accelerator, on whose nozzle a gas-dynamic nozzle is installed, and a marching stage stabilized by rotation around the axis of the roll and made in the form of an elongated cylinder with a pointed homing equipped with a homing head, a small-sized disposable turbojet engine equipped with a folding an air intake, and the march stage is equipped with an n-channel system for generating lift in rotation mode, the outputs of which are connected terms to the drives of n pairs of small-sized wings folding and switched by the sign of the angle of attack of the wings, which are installed along the longitudinal axis of the rocket symmetrically relative to the center of mass in a discrete spiral with a pitch along the roll angle $$\frac{2\pi }{n}$$

moreover, the direction of twisting of the discrete spiral coincides with the direction of rotation of the rocket and the direction of twisting of the aerodynamic nozzle.

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