RU2247926C1 - Method for stabilization of rocket in flight and rocket for its realization - Google Patents

Abstract

FIELD: rocketry, in particular, means for stabilization of small-sized rockets.

SUBSTANCE: the stabilizing moment is produced by continuously braking the incoming air flow by propulsive jets. The broken flow acts on the rocket side surface in the zone shifted relative to its center of mass. The action of the reactive forces on the body in cross section is mutually balanced. The side nozzles are positioned in the aft part of the rocket pairwise opposite each other with an inclination to its side surface towards the rear end face through an angle exceeding the angle of attack of the rocket.

EFFECT: simplified angular stabilization of the rocket in flight in dense atmosphere layers, enhanced its tactical characteristics and reduced cost.

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Description

The invention relates to the field of rocket technology and can be used in small-sized guided and unguided missiles, especially hypersonic.

A known method of stabilizing a rocket in flight with aerodynamic surfaces [1], adopted by the authors as an analogue. For its implementation, the rocket contains stabilizers, which are folding consoles mounted on the axles, with a spring and a power pin, located behind the center of mass of the rocket [1]. The advantages of the known method and the rocket implementing it are the simplicity of the design. The application of the known method and its design is most effective on missiles of relatively large caliber with relatively low supersonic flight speeds, the flight of which takes place in the surface layers of the atmosphere.

The disadvantage of this method and the rocket for its implementation is the presence of protruding beyond the caliber of the rocket surfaces, which increase its aerodynamic drag. When flying in dense layers of the atmosphere with hypersonic speed, they must be protected from kinetic heating by an incoming air stream, which additionally increases the aerodynamic drag of the rocket and its passive weight, which is not always possible in small-sized missiles. The use of heat-resistant materials to protect stabilizers from kinetnagrev sharply increases the cost of the rocket.

A known method of stabilizing a rocket in flight by using the energy of jet jets [2], adopted by the authors as a prototype. In this method, when a disturbing force appears, the control equipment generates a corresponding opposing command, which is worked out by a special drive that turns the jet of the main engine or turns on the auxiliary engine, which creates lateral thrust. The reactive force in this case acts on the rocket body periodically, when a disturbing moment occurs. This method is implemented in relatively large-sized rockets [2] flying in discharged layers of the atmosphere. The rocket contains a housing, a rocket engine and side nozzles mounted on the outer surface of the rocket housing. However, the application of the known method for launches of small-sized missiles, especially uncontrolled missiles, flying mainly in dense atmospheric layers at low altitudes, significantly complicates their design, since it requires control equipment, thrust vector control drives of the main engine or devices for switching on additional engines, which dramatically increases rocket cost. At the same time, the passive weight of the rocket increases and, accordingly, its tactical and technical characteristics deteriorate.

The angle of attack during the implementation of the known method should always be zero, which requires the development of additional commands. It takes a certain amount of time to develop stabilization and control commands, which leads to rocket oscillations around the center of mass and increases its aerodynamic drag, and control equipment can also fail, which can lead to the missile reaching unaccounted angles of attack and its subsequent destruction.

All these are the disadvantages of the known method and design of the rocket for its implementation.

The objective of the invention is to eliminate these drawbacks, namely: simplifying the method by reducing the number of operations and simplifying the design of the rocket for its implementation by eliminating control equipment and drives, increasing due to this reliability and speed, reducing passive weight, which ultimately should ensure the stabilization of missiles during flight in dense layers of the atmosphere (both controlled and uncontrolled) without increasing their aerodynamic drag, which makes it can be used in small missiles without a significant increase in cost.

To solve this problem, in the known method of stabilizing a rocket in flight, which includes creating a stabilizing moment due to the energy of jet jets flowing out of the side nozzles, a stabilizing moment is created by continuously braking the incoming air stream with jet jets, and a blocked flow acts on the side surface of the rocket in an area shifted relative to its center of mass, while the effect on the body of reactive forces in cross section mutually balances.

To implement the proposed method in a rocket containing a body, a rocket engine and side nozzles, unlike the prototype, the side nozzles are located on the aft side of the rocket in pairs opposite to each other, with an angle to the side of the rocket toward the rear end face at an angle greater than the angle of attack of the rocket .

The proposed method and the rocket for its implementation allow to create a zone of increased pressure in the stern of the rocket due to inhibition of the incident flow by jet jets, which ensures its angular stabilization. In this case, due to the inclination of the nozzles, the interaction of jet jets with the incoming air flow occurs after the interaction of the jet with the rocket body ceases, which practically does not increase its (rocket) aerodynamic drag. In addition, inclined nozzles create additional axial thrust.

The essence of the alleged invention is illustrated by graphic materials. Figure 1 shows the proposed rocket in flight without disturbances, figure 2 shows the proposed rocket in flight in the presence of an angle of attack caused by disturbing forces.

The rocket (Fig. 1) contains a head part 1, a jet engine 2, equipped with a central nozzle 3 and side nozzles 4. The lateral nozzles are arranged in pairs opposite to the aft of the rocket 5 and are inclined at an angle α greater than the angle of attack β (Fig. 2).

The device operates as follows. In flight in front of the jets 6 created by the side nozzles 4, a pressure zone 6 is formed on the aft of the rocket 5, which creates a stabilizing moment M _stub. relative to the center of mass of the rocket. In the absence of disturbing forces, the lateral pressure on the stern of the rocket is evenly distributed along the perimeter of the side surface of the stern. When disturbances appear, the rocket rotates relative to the transverse axis at the angle of attack β, while the pressure on the stern automatically increases with the side of the hull blown by the flow, a negative pressure is created on the opposite side, therefore, a stabilizing moment is automatically created, which tends to return the rocket to its original undisturbed state. The inclination of the nozzles prevents the effect of the incident air flow on the jet flowing from the side nozzles, and therefore, the effect of the jet stream on the stern of the rocket remains neutral. The stabilizing moment is created not directly by the action of jet jets (thrust) on the rocket body, but by the interaction of the jet leaving the nozzle with an incoming air stream, which, when interacting with the rocket body, practically does not increase its aerodynamic drag.

The direction of the stabilizing moment depends on the ratio of the static pressure and the braking pressure in the jet stream and the incoming air flow, as well as the geometry of the body (location of nozzles, their number, angle of inclination), therefore, depending on specific conditions, the nozzles can be located behind the center of mass, so in front of him.

After the engine is finished, rocket stabilization can be carried out by increasing the static stability margin while moving the rocket's center of mass forward due to the empty engine casing, which serves as a stabilizer in this case, or the warhead can be detached and stabilized independently.

Thus, the proposed method and device will simplify the angular stabilization of the rocket during flight in dense layers of the atmosphere, which will make it possible to use them on small-sized guided and uncontrolled missiles and will increase their tactical and technical characteristics and reduce cost.

Sources of information

1. Fundamentals of the design and construction of aircraft. V.N. Novikov, B.M. Avkhimovich, V.E. Veitin. - M.: Engineering, 1991, p. 47, 34 - analogues.

2. Fundamentals of the design and construction of aircraft. V.N. Novikov, B.M. Avkhimovich, V.E. Veitin. - M .: Engineering, 1991, p. 47, 48, 49 - prototype.

Claims (2)

1. A method of stabilizing a rocket in flight, including the creation of a stabilizing moment due to the energy of the jet jets flowing from the side nozzles, characterized in that the stabilizing moment is created by continuously braking the incoming air stream with jet jets, and a blocked flow acts on the side surface of the rocket in an area shifted relative to its center of mass, while the effect on the body of reactive forces in cross section mutually balances. 2. A rocket containing a housing, a rocket engine and side nozzles, characterized in that the side nozzles are located on the aft side of the rocket in pairs opposite to each other with an angle to the side of the rocket toward the rear end face at an angle greater than the angle of attack of the rocket.

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