RU2138765C1 - Jet projectile with detachable nose cone - Google Patents

Abstract

FIELD: rocket armament. SUBSTANCE: the projectile has a jet engine, detachable nose cone, separation and breakaway device. The breakaway device is made in the form of two masses opposite-arranged relative to the longitudinal axis. One of them is positioned in the engine, and the other - in the nose section. The masses are unilaterally shifted in the longitudinal direction relative to the center of mass of the engine and nose section respectively. EFFECT: enhanced reliability of combat use of projectile due to prevention of collision of the engine and nose section after their separation. 3 dwg

Description

 The invention relates to the field of rocket technology, namely to rockets (missiles).

 The object of the invention is a missile with a detachable warhead and may find application in the field of rocketry.

 Recently, one of the main ways to increase combat effectiveness has been the use of rockets divided into trajectories (see, for example, Gogin V., Fedoseyev A. Prospects for the development of multiple launch rocket systems. - "Foreign Military Review>, N1, 1995 or Anisimov B. Ammunition with high-precision military elements. - "Foreign Military Review", N11, 1994.), providing effective destruction of manpower, unarmored and armored vehicles. In these missiles, due to vertical trajectory when approaching e warhead to the target, achieved a multiple increase combat effectiveness compared to conventional missiles with a ballistic trajectory.

 Thus, ammunition designs are known that are protected by US patents N 3946672, N 3491689, N 3636877, adopted by the authors as analogues. These designs are rockets, which include a jet engine, detachable warhead and separation device.

 The objective of this technical solution was to increase combat effectiveness by increasing the approach angle to the target of the detached warhead, without exception, the possibility of its collision with the engine.

 Common features with the design of the missile proposed by the authors is the presence of a jet engine in the analogues, a detachable head (warhead) and separation device.

 A significant drawback of these structures is the possibility of collision of the separated jet engine and the head part. As a result of such an impact, the predetermined trajectory of the separated head part changes, or its elements (system of braking and stabilization, instrumentation) are out of order.

 The closest in technical essence and the technical result achieved is a missile (rocket) according to US patent N 3384016 (see abstract magazine "Armament", 1969, N 14, 14.74.37 P.), adopted by the authors for the prototype. It includes a jet engine, a detachable head (warhead) and a device for separation and removal of the engine from the trajectory of the separated head part.

 In this rocket at one point on the surface of the jet engine housing (asymmetrically about the axis), a cumulative charge is placed. When it is detonated, a hole is formed in the jet engine casing and a lateral force is created, the vector of which intersects with the axial line of the hull at the center of gravity, due to which the jet engine is displaced from the flight path of the warhead.

 The disadvantage of this design is that it cannot provide reliable prevention of the collision of the shared compartments throughout the flight of the rocket, in particular on the passive section of the trajectory.

 The objective of this technical solution (prototype) was to prevent the collision of the detached warhead and the jet engine.

 Common signs with the proposed missile with detachable warhead is the presence in the rocket - a prototype of a jet engine, detachable head (warhead), separation and withdrawal devices.

 In contrast to the prototype, in the proposed missile, the withdrawal device is made in the form of two opposed masses that are opposite to the longitudinal axis of the projectile (i.e., on opposite sides of the axis, with their centers of mass being in the same plane passing through the longitudinal axis), one of which placed in the head part, and the other in the engine, and displaced relative to the centers of mass of the head part and engine, respectively, in the longitudinal direction in the same direction.

 This allows us to conclude that there is a causal relationship between the totality of existing features of the claimed technical solution and the achieved technical result.

 The indicated features, distinctive from the prototype, and to which the requested amount of legal protection applies, are sufficient in all cases.

 The objective of the invention is the creation of a missile with a detachable warhead, providing increased reliability by eliminating the possibility of a collision of the jet engine and the head (warhead) after separation.

 The specified technical result is achieved by the fact that in a rocket containing a jet engine, a detachable head, separation and withdrawal devices, according to the invention, the withdrawal device is made in the form of two unbalanced masses opposite to the longitudinal axis of the projectile, one of which is located in the head part, and the other in the engine, and one-sidedly displaced relative to the centers of mass, respectively, of the head and engine in the longitudinal direction.

 The new set of structural elements, as well as the presence of connections between the nodes of the rocket allow, in particular, due to the opposite location relative to the longitudinal axis of the projectile of two unbalanced masses - to ensure that the center of mass of the assembled projectile coincides with its longitudinal axis and, as a result, the movement of the projectile before separation with low angles of attack; unilateral displacement of both unbalanced masses relative to the center of mass of the head and engine in the longitudinal direction - to ensure the imbalance of the head and engine after separation, their rotation at the angles of attack, which have opposite signs and, as a consequence, the divergence of the trajectories and the prevention of collision.

 The invention is illustrated by drawings.

 In FIG. 1 shows a General view of the proposed design of a missile. It consists of a detachable head 1 and a jet engine 2, a separation device 11 and a withdrawal device. The withdrawal device consists of two unbalanced masses 3 and 4 mounted on both shared parts 1 and 2. The places of their installation are located on one side (on the right in Fig. 1) from the center of mass of the head part 5 and the center of mass of the jet engine 6 after separation. At the same time, they are radially offset in opposite directions from the longitudinal axis 7.

The construction work is as follows. In the process of preparing the projectile for launch, unbalanced masses 3 and 4 are placed on it on different sides from the longitudinal axis 7 and, varying their size, balance the projectile, that is, they achieve the coincidence of the center of gravity 8 of the assembled projectile with the longitudinal axis 7. Thanks to this, after launching such a projectile moves along the trajectory stably, with small angles of attack and minimal deviations from the given trajectory, since the vectors of the aerodynamic drag force X and the reactive force of the engine R do not create overturning moments with respect to center of gravity 8. After separation of the head from the engine, each of them due to the presence of unbalanced masses 3 and 4 is unbalanced (Fig. 2). This is manifested in the displacement of the center of gravity of the separated head part 9 upward relative to the original axis 7, and the center of gravity of the engine 10 — downward relative to the axis 7, as well as positive on the engine and negative on the head part angular mismatch between the longitudinal geometric axis and the central axis of inertia. As a result of this, the aerodynamic forces X of the _taxiway and X of the _warhead , directed along the geometric axis 7, create oppositely directed moments M of the _taxiway and M of the _warhead , which, in turn, lead to the rotation of the separated compartments at the angles α of the _taxiway and α of the _warhead (Fig. 3) having opposite signs. Under the influence of aerodynamic lifting forces
(In _MS = qS _MS C $\genfrac{}{}{0ex}{}{\text{α}}{\text{UHF}}$ α _warhead , at _taxiway = qS _taxiway C $\genfrac{}{}{0ex}{}{\text{α}}{\text{URD}}$ α _RD
where q is the pressure head, S is the Midel area, C $\genfrac{}{}{0ex}{}{\text{α}}{\text{at}}$ is the derivative of the lift coefficient with respect to the angle of attack, α is the angle of attack), the engine and the warhead receive oppositely directed additional lateral speeds, which ensure the divergence of trajectories and collision avoidance.

The values of the unbalanced masses 3 and 4 and the coordinates of the points of their installation depend on the geometric, inertial-mass parameters of the parts to be separated and their bearing properties. As shown by the calculated and experimental studies, they should be selected from the condition of ensuring angles of attack of the warhead α _warhead and the engine α _taxiway after separation close to 10-15 ^o .

 In this case, at the moment when the engine overtakes the head part, the distance between them in the direction perpendicular to the direction of movement is 4 ... 6 times greater than the overall dimensions of the divided parts, which prevents the possibility of their collision.

 The invention can be used in the development of various rockets with detachable warhead.

 The specified positive effect is confirmed by testing prototypes of rockets with detachable warhead made in accordance with the invention.

 Currently, design documentation has been developed, flight tests have been conducted, and mass production is scheduled.

Claims (1)

 A missile containing a jet engine, a detachable warhead, separation and withdrawal devices, characterized in that the withdrawal device is made in the form of two unbalanced masses opposed to the longitudinal axis, one of which is located in the head and the other in the engine, and one-sided displaced in the longitudinal direction relative to the center of mass, respectively, of the head and engine.

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