RU2222771C1 - Rocket - Google Patents

Abstract

FIELD: armaments, applicable in short-range rocket complexes. SUBSTANCE: the rocket has a separating booster engine telescopically-joined to the aft part of the sustainer stage. The aft part of the main stage is provided with a movable piston enveloping it in the outside diameter, the piston is made with a flare projecting from the end face of the sustainer stage. The location seat in the front part of the engine is provided with a stop, whose inside diameter equals the diameter of the sustainer stage. The piston is joined to the aft part of the sustainer stage by a split member. EFFECT: reduced disturbances of the sustainer-stage at separation of the rocket, and as a result, enhanced reliability. 2 dwg

Description

 The invention relates to the field of armaments and may find application in short-range missile systems.

 The known design of the kinetic anti-tank missiles (US Pat. RU 2108537, MKI F 42 B 12/06, 15/00, publ. 10.04.98, bull. 10), adopted by the authors for an analogue of the invention. It contains a housing, which is also a jet engine housing, a solid fuel charge, an armor-piercing rod and auxiliary actuators located inside the solid fuel charge along its axis and fastened directly or through a connecting element to the rear bottom of the housing, the walls of the housing and the solid fuel charge, and a homing head and governing bodies.

 This design with a minimum length provides an even distribution of the load across the hull and reduces the effectiveness of the elements of the dynamic or active protection of tanks on the combat element.

 However, the execution of a rocket with an inseparable starting engine does not allow to realize long firing ranges (over 3 ÷ 5 km), since a large drag results in a sharp drop in speed after the engine is finished. The use of a marching engine to compensate for drag leads to an increase in the starting mass of the rocket, an increase in the dimensions and mass of the rocket and the starting engine, and complication of the design. All together, this leads to a decrease in transportable ammunition and a decrease in the effectiveness of the complex.

 The closest analogue adopted by the authors for the prototype of the invention is a two-stage rocket (US patent 5005781, CL 244-3.26, 19991), containing a detachable starting engine, which telescopically includes the aft part of the marching stage. The starting engine is rigidly connected to the separation unit with the mid-flight stage at the starting portion of the flight and is separated from it at the end of work.

 The design of the prototype provides a reduction in length due to the partial entry of the marching stage into the starting engine and allows firing at long ranges without the use of an additional marching engine. Thanks to the separation of the starting engine, the side surface of the rocket and the friction drag component are reduced. In addition, the design of the prototype allows for a high degree of filling of the engine chamber when placing part of the sustainer stage in it.

 However, the disadvantage of this design are significant disturbances acting on the march stage of the rocket during separation. This is due to the presence of lateral forces acting on the engine when it is separated, causing it to turn relative to the direction of movement and hit the aft part of the marching stage at the time of separation, which can lead to the destruction of the marching stage, especially at high flight speeds. In the process of separation under the influence of lateral forces acting on the engine and the stabilizing forces opposing them acting on the march stage, friction forces arise in the separation unit to counteract the separation process and increase the separation time. Due to the increase in the separation time, the momentum of the lateral forces acting on the marching step increases, which further increases the perturbations in the separation.

 In the process of separation under the influence of the control moment, the march stage housing is bent and the contact surface of the interaction of the aft part and the engine seat within the gap increases. As a result, the friction force and the travel time along the landing nest increase, and as the marching stage moves out of the landing nest, the amplitude of the marching stage oscillations within the gap between the aft and the landing nest can increase. An increase in the amplitude of oscillations of the march stage relative to the engine also leads to an increase in perturbations at the time of separation.

 At the moment of disengagement of the march stage and the starting engine, the march stage, which has a stability margin less than the rocket as a whole before separation (with an engine with a burned-out charge), makes a sharp angular turn, changing the angle of attack. In this case, the turn is carried out not relative to its center of mass, but relative to the contact surface of the aft part of the march stage with the landing seat, which increases the shoulder of the application of force and can cause an increase in the angle of attack of the stage beyond the permissible limits, which may result in the march stage leaving the control beam and, accordingly, rocket loss.

 Thus, the objective of the invention is to reduce disturbances of the march stage of the rocket during separation, and as a result, to increase reliability.

 The task is achieved in that in a rocket containing a detachable starting engine, telescopically connected to the aft of the march stage, in contrast to the prototype, the aft of the march stage is equipped with a movable piston covering it in outer diameter, made with a skirt protruding beyond the end of the march stage, this landing seat in the front of the engine is equipped with a stop, the inner diameter of which is equal to the diameter of the sustainer stage, and the piston is connected to the aft of the sustainer stage by a discontinuous element ntom.

The combination of structural elements and their relative position allows:
- reduce the power effect on the aft of the march stage from the engine side by reducing the separation time and impulse of disturbing forces;
- to reduce at the time of separation the angle of rotation of the starting engine relative to the direction of motion due to the displacement of the center of mass of the engine forward and due to the impulse of the dynamic impact of the piston against the stop at the time of stopping;
- to ensure that there is no skew of the march stage relative to the landing jack of the starting engine when they are separated due to the stop and the skirt of the movable piston, increasing the length of the landing. In this case, the moment from the control forces is transmitted only along two cylindrical surfaces, which excludes the possibility of contact of the aft part of the march stage when it is bent with the walls of the landing nest and reduces the friction force and, ultimately, allows to reduce the separation time of the stages and thereby reduce the lateral forces momentum at the time of separation;
- reduce the angle of rotation of the march stage relative to the point of contact with the starting engine by the time the stern comes out of the landing nest due to the presence of a skirt on the movable piston protruding beyond the end of the march stage, which reduces disturbance during separation;
- reinforce the starting seat of the starting engine with a movable piston, which allows to increase the length of the landing socket and execute it in the combustion chamber of the engine without increasing the wall thickness, as well as to increase the depth of movement of the marching step into the engine and thereby reduce the length of the rocket.

 The invention is illustrated by the rocket diagram (Fig. 1) and the diagram of forces and moments (Fig. 2) acting on the marching stage and the detachable starting engine at the time of separation.

The proposed rocket (Fig. 1) contains a marching stage 1 and a starting engine 2, rigidly connected by a fixation-unlocking unit 4. The aft part 3 of the marching stage 1 is placed in a movable piston 6, covering its outer diameter D _ms , made with a protruding end the mid-flight stage with a skirt 7, and is connected to it by a discontinuous element 9. In the front part of the landing socket 5 of the detachable starting engine 2, an emphasis 8 is made that prevents the movable piston 6 with the skirt 7 from coming out of the engine landing socket after separation of the steps Aketi.

 The work of the proposed design is as follows.

 At the launch site, the rocket flies with the march stage 1 rigidly connected to each other by the fixation-release unit 4 and the detachable start engine 2. At the moment the launch engine finishes, the release mechanism 4 and the march stage located in the movable piston 6 are activated, and the start engine separated either by the difference in aerodynamic forces acting on the march stage and the engine, or by the pressure that can be created behind the piston by the combustion products from the burned pyro or the composition of the Technical selected from combustion chamber gas engine starting. At the moment of impact of the piston 6 about the stop 8 of the landing seat 5, the breaking element 9 is destroyed and the starting engine is separated from the sustainer stage.

 When separating the stages, the stop 8 ensures that the piston 6 stops at the moment the sustainer stage 1 leaves the landing seat 5 of the detachable starting engine 2. At the same time, the angle of rotation of the engine is reduced due to the displacement of the center of mass of the engine forward and the dynamic action of the piston on the engine (Fig. 2).

 With active separation, stopping the piston eliminates the power and thermal effects on the marching stage of the combustion products of the pyrotechnic composition or the products of fuel combustion, under which the stages are separated after the engine stops working.

 The length of the stop, the piston skirt and the length of the section of the aft part of the marching stage that the piston covers, as well as the gap between the aft of the marching stage and the engine seat, are selected in each case by calculation and are refined during development.

 Thus, in the proposed technical solution, it is possible to reduce the angular perturbations of the sustainer stage at the time of its separation with the starting engine by reducing friction forces along the landing jack and thereby reduce the separation time, reduce the angle of rotation of the sustainer stage relative to its point of contact with the engine mounting socket, and the force effect on the stern of the march stage is also excluded during the active separation of the products of combustion of an additional sample or the products of combustion of the starting fuel wiggler.

Sources of information
1. Patent RU 2108537, MKI F 42 B 12/06, 15/00, published April 10, 1998, bull. 10 - analogue.

 2. US patent 5005781, CL 244 - 3.26, 19991 - prototype.

Claims (1)

A rocket containing a detachable starting engine telescopically connected to the aft part of the march stage, characterized in that the aft part of the march stage is equipped with a movable piston enveloping it in outer diameter, made with a skirt protruding beyond the end of the march stage, while the landing seat in the front of the engine is made with a stop, the inner diameter of which is equal to the diameter of the sustainer stage, and the piston is connected to the aft part of the sustainer stage by a discontinuous element.

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