Stabilizing device of aircraft winged missile

FIELD: rocketry, in particular, device for stabilization of aircraft winged missiles at the initial stage of independent flight.

SUBSTANCE: the body of the stabilizing device is made in the form of a convex cover sealing the nozzle of the missile solid-propellant acceleration engine, and the controls-in the form of four pairs of kinematically linked with one another aerodynamic control surfaces and jet vanes of the solid-propellant acceleration engine, each of them is positioned in the plane of installation of the aerodynamic control surface of the missile sustainer stage and linked with the drive of the mentioned control surface by means of control rods. The control mechanism of the stabilizing device control surfaces is made for separation of the links controlling the position of the device aerodynamic control surface, as well as for separation with the control rods from the sustainer stage control surface drive.

EFFECT: simplified structure and reduced overall dimensions of the stabilizing device, enhanced aerodynamic characteristics of the winged missile.

7 dwg

 

The invention relates to the field of rocketry, and more specifically to cruise missiles (CR) aviation industry. The invention describes a device that provides stabilization and management of CR in the initial part of the flight, immediately after separation from the aircraft, and may find application mainly on missiles, originally designed for other media types, such as marine or terrestrial, and adaptable to the conditions of the aviation industry.

One of the main requirements for aviation KR is the most compact of their placement on aircraft carriers. To this end, apply different technical solutions, such as: folding wing missiles when placed on the media, for example - CU M ("Mosquito") and X-35 (Avicenna, Simkanin "Domestic aviation tactical missiles, military-technical collection "Bastion" No. 1, 2000, S.-Petersburg, p.56-59 and 73-74); placement of missiles on the aircraft in position, a deployed around the longitudinal axis, providing a rational configuration of CU on the suspension, in combination with poliestrovym reversal in the source (flight) position, as described in the application for the invention "Method of application of aviation CU with air-breathing propulsion system", filed concurrently with the present application.

However, the folding of the wing, usually deprives R is Ketu controllability until it is full disclosure, and to complete reversal of CU in the flight position may require measures to increase the efficiency of governing bodies, for example, in case of unfavourable initial alignment characteristic of missiles with tandem or built-in solid-fuel upper stage engine. In such cases, which typically arise when adaptation to the conditions of the air-based missiles, previously developed for other media types, use special devices that provide stabilization of CU at the time of passage of the transient.

The closest set of features with the claimed invention is the stabilization device, used at the aviation version of the KR "Meteorite" (FSUE "NPO Mashinostroyenia. 60 years of selfless work for peace, ed. home "Weapons and technology of Russia, M., 2004, p.81, 82, 229). The known device stabilization (see photo from the specified source in the Appendix) made in the form of detachable from the rocket tail fairing, equipped with three aerodynamic control surfaces. Its functioning provide actuators and control mechanisms rudders placed in the cavity of the fairing, and separation from the rocket - special quick coupling. As such, generally used mechanical pyrotechnics (peerbolte or Pirot is lately) and detachable electrical connectors.

However, for small-CU, co-location of required equipment within a limited diameter leads to an increase in length and unsustainable external forms of structure stabilization. The implementation of such layout solutions, applied to CR with combined propulsion units on the basis of the RAMJET, for example, performed by a layout scheme that is described in the patents of the Russian Federation No. 2117907 and No. 2215981 (IPC F42 15/00), is fraught with additional difficulties.

First, the design features of the combined propulsion system of this CR, which is a ramjet sustainer engine (RAMJET) with bearing (i.e. which element of the fuselage) housing and built-in booster rocket motor solid fuel (solid rocket motor), make it almost impossible posting service to the stabilization device within the diameter of the fuselage of the rocket. Also significantly complicated the layout of the quick coupling at the interface of such a CR device stabilization. This leads to the necessity of the organization of gargorov and blisters, substantially protruding beyond the contours of the rocket, and therefore increase its aerodynamic resistance in General.

Secondly, most fuel built upper stage solid rocket motor is concentrated in the tail of the KYRGYZ Republic, in the ocher is , allows to judge about the adverse initial alignment of the rocket. In combination with a relatively small shoulder installation of aerodynamic control surfaces (see figure 1 description of the invention according to patent No. 2215981), it is fraught with possible static instability of CU in the configuration without additional stabilisasi surfaces. This circumstance arising after the separation device stabilization and valid up to the start of the upper stage solid rocket motor (i.e. enable its efficient gas-dynamic controls), is the basis for the "stringency" synchronization perform the above operations.

The problem solved by the invention is:

the reduction in the total number of airborne units, necessary to ensure the stabilization and control of the missile during the initial stage of its Autonomous flight, including equipment to be placed in the device stabilization

- ensuring continuous control of the KR on the specified flight stage by minimizing the travel time of transition processes

- limit the negative impact on the aerodynamic characteristics of CU from the implementation of the stabilization device in the composition of a rocket at the last adaptation to the conditions of the aviation industry.

This problem is solved due to the fact that in the known device stabil the sale of aircraft cruise missiles, comprising a housing mounted with the possibility of separation at the tail of the rocket, the aerodynamic control surfaces mounted on the housing, the actuator and the control mechanisms rudders, according to the claimed invention, the housing stabilization device made in the form of a convex cap, sealing the nozzle of the solid-fuel booster rocket engine, and controls of part of this device is in the form of four pairs of kinematically interconnected aerodynamic rudders and gas rudders solid-fuel upper stage engine, and each pair of rudders stabilization device placed in the planes of the installation of the aerodynamic control surfaces of the missile and associated with the respective actuator steering rockets through control rods and the control mechanism driving device stabilization, which made with the possibility of separation of the links that control the position of the aerodynamic steering device, and separation control rods from the steering actuator missiles.

The technical result of the use of the invention is that it allows you to create the design of the stabilization device, which, compared to traditional, characterized by a simplified structure and significantly less weight and size. This is achieved by the application of solutions to the aviation units CU to combine n is how many functions including placing on the stabilization device, for example:

- execution to allow the stub upper stage solid rocket motor in the form of a convex cover allows it, along with the main purpose, namely the sealing of the internal cavity and to provide a specified start mode of the engine, to perform the functions of the device stabilization. This eliminates the need to use any additional nodes to separate the device from the rocket and manages CR without gaps on the "transfer of control" from one (aerodynamic) the management bodies of the stabilization device to the other (dynamic);

- kinematic relationship management bodies, the stabilization device between themselves and drive on Board the rocket, allows this drive to control not only the relevant aerodynamic wheel sustainer stage of the KYRGYZ Republic, but also a pair of rudders stabilization device that is installed in the same plane. When this thrust from the actuator, laid on the outer surface of the caudal compartment of the rocket can be made in the form of ropes or metal strips, almost not protruding beyond the contours of its fuselage, and the desired gear ratio between the controls of the rocket and the stabilization device can be achieved by selecting an appropriate ratio plait the pumping mechanism control rudders.

Thanks to a specified set of technical solutions, from traditional composition of the stabilization device can be excluded special ProCredit mounting and separation of the device from the rocket and highly specialized actuators. Accordingly, there is no need for the electrical equipment of the stabilization device, and wiring communications and the use of connectors, which would link it with the onboard control system of the missile.

The essence of the proposed device is illustrated in Fig.1-7.

Figure 1 presents a General view of the KR gathering with the stabilization device when placing missiles on the aircraft carrier (in the specific example CU placed on the aircraft in accordance with the technical decision on the application for "Method of application of air CU...", that is, in position, a deployed around the longitudinal axis at an angle of 45°). Figure 2 - rear view of CU in the specified position. Figure 3 and 4 shows the tail part of the KR and the stabilization device in partial section. Figure 5-7 shows the functional diagram of the KR with the stabilization device after separation of the missile from the aircraft.

Cruise missile (1) performed on a normal aerodynamic scheme and contains axisymmetric fuselage, wing and tail Assembly, which is made in the form of four tselnopovorotnogo aerodynamic rudders (2). Rudders (2) p is okoth I, II, III and IV rocket and managed by means of the actuator (3)is placed inside the fuselage.

CU (1) is equipped with a combined propulsion system, which is a RAMJET (4) with a carrying case and a built-in booster solid rocket motor (5), which has a gas-dynamic controls, designed with four gas rudders (6).

On the tail of CU (1) set the device stabilization (7), which consists of a body and controls.

The device stabilization (7) made in the form of a cover (8), the sealing nozzle (9) upper stage solid rocket motor (5). Cover (8) has a cylindrical lateral surface, favouring the nozzle (9), and bonded with the latest torque bolts (10), designed for the destruction from the action of tensile forces a certain value.

The management bodies of the stabilization device (7) is designed as four pairs of kinematically interconnected tselnopovorotnogo aerodynamic control surfaces (11) and the above-mentioned gas rudders (6) solid rocket motor (5), which are part of the stabilization device functionally.

Aerodynamic control surfaces (11) are mounted on the side surface of the cover (8) through bracket (12), which is pressed to the axis of rotation of these wheels. Each aerodynamic wheel (11) is installed coaxially with the respective gas handlebar (6) and interacting the with the rocker (13) of the latter. Why in the plane of the steering wheel (11) is pressed the guide pin (14)in the bracket (12) a radial groove to move the pin (14)and the rocker (13) of the gas the steering wheel (6) is danced in a slot under the specified pin.

Paired thus handlebars (11) and (6) stabilization device (7) is placed in the planes I, II, III and IV rockets, i.e. in planes setup aerodynamic rudders (2) CU (1). Each rocking chair (13) gas booster (6), which on the shoulder, the opposite cage has a toothed sector, through an intermediate gear (15) communicates with the rocking-gear (16)mounted on the rear end of the fuselage CU (1). In turn, the rocker-gear (16) through the tape rods (17), laid on the outer surface of the tail module KR (1), associated with the respective actuator (3) steering (2) rockets. Thus, the kinematic system formed by the rocking-gear (16), an intermediate gear (15), rocking chair (13) of the gas the steering wheel (6) and the associated guide pin (14) aerodynamic steering (11), is a control mechanism (18) pair of wheels (6) and (11) of the device stabilization (7).

The specified device operates as follows.

On command from the control arms of the airplane revealed grips aircraft launching device, resulting in CU (1) is separated from the La and begins its Autonomous movement. CU (1) in gliding flight is removed from the aircraft, while its position is stabilized according to the onboard control system (BOP) with the Executive bodies of the rocket (the actuator (3) and aerodynamic rudders (2)) and the stabilizing device (7) (tie rods (17), mechanisms (18) and the aerodynamic control surfaces (11)). It should be noted that the control surfaces (11) of the stabilization device (7) on this flight CU (1) are the main contributors to the overall effectiveness of the controls as they are, compared with rudders (2) rockets, have significantly greater the force arm about the center of mass of the rocket.

For a given time delay, BSU CU (1) issues a command for executing program reversal roll angle 45°, which is held through a joint deviation of the aerodynamic control surfaces (2) and (11). While the efforts of the actuators (3) create the axes of the wheels (2) rockets (1) control points that thrust through (17) and links mechanisms (18), namely - rocking-gear (16), idler (15), rocking (13) and interact with the guides (14)are transferred to the aerodynamic control surfaces (11) of the stabilization device (7).

In a reversal of the CU (1) takes flight position, corresponding to vertical and horizontal orientation of its planes.

On the removal of CU (1) distance is topanga for the carrier aircraft launch, upper stage solid rocket motor (5) (of the order of several tens of meters) BSU missile issue the command to run it. The result triggered the solid fuel igniter charge solid rocket motor (5) and the pressure in the combustion chamber begins to rapidly increase. Upon reaching a given value of the pressure in the combustion chamber of the solid rocket motor (5) dissolved calibrated bolts (10), which cover (8) on the nozzle (9)and cover (8) together with fixed thereto aerodynamic control surfaces (11) is separated from the CU (1). While the guides (14) rudder (11) disengage from the measured including carriers of units (13), thereby breaking the chain of mechanisms (18), previously governed by the position of the steering wheel (11). Further, the control torques generated by the actuators (3), applied only to aerodynamic rudders (2) CU (1) and gas surface (6) solid rocket motor (5).

Under the action of thrust upper stage solid rocket motor (5) CU (1) dramatically accelerates, while gas handlebars (6), the decline in the flow of the jet stream, flowing from the nozzle (9) of the engine, make the main contribution to the stabilization of the rocket and the possible software implementation of the maneuvers. As the growth rate KR (1) (and, hence, the velocity head acting on the bearing and control surfaces of the missile) and the combustion of fuel upper stage solid rocket motor (5) (and, hence, the offset forward of the center of mass of the rocket) increasing the efficiency of the aerodynamic control surfaces (2)that by the end of the upper section of the rocket flight acquire the ability to "self" to control its motion is m

When the recession thrust upper stage solid rocket motor (5) to a certain value, the pressure of air flowing in the air path of the propulsion system rocket, the exhaust housing of the engine ejected from the cavity RAMJET (4). The intermediate gear (15) disengage from the rocking chairs-gear (16) which functioned earlier parts of the control gas rudders (6) mechanisms (18) are separated at the rear edge of the fuselage CU (1).

In the "released" air tract RAMJET (4) and after operations to run the CU (1) starts a flight in cruise mode, in which control motion of a rocket is the aerodynamic control surfaces (2).

Thus, we can conclude that the proposed solution allows to simplify the structure, reduce the total number of the equipment, reduce the dimensions and weight of the device stabilization, which in turn provides lower costs for its development and manufacture. The positive effect of the introduction of such devices in the aviation version of small CU is not accompanied by a reduction of its aerodynamic characteristics.

The device stabilization aircraft cruise missiles, comprising a housing mounted with the possibility of separation at the tail of the rocket, the controls in the form of rudders, with antiromance on the housing, drive and control mechanisms rudders, characterized in that the device stabilization made in the form of a convex cap, sealing the nozzle of the solid-fuel booster rocket motor and controls - in the form of four pairs of kinematically interconnected aerodynamic rudders and gas rudders solid-fuel upper stage engine, and each pair of rudders stabilization device placed in the planes of the installation of the aerodynamic control surfaces of the missile and associated with the respective actuator steering rockets through control rods and the control mechanism driving device stabilization, which is made with the possibility of separation of the links that control the position of the aerodynamic steering device, and separation control rods from the steering actuator the rocket.



 

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