RU2494340C1 - Missile with caseless nozzleless eng-ignition engine (versions) - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: proposed missile comprises head and solid propellant charge. In compliance with one version, proposed missile comprises sliding finned bush arranged at solid propellant. Said bush is equipped with impellers for threads connected with missile head to be wound thereon. In compliance with another version, missile head accommodates impeller with skewed or crosswise vanes and is connected with spools. The latter are connected by thread with sliding bush and fin. In compliance with one more version, missile head accommodates motor, reduction gear and two or more spools for thread winding. The latter are connected by thread with sliding bush and fin. In compliance with the other version, missile fin is composed of several fins glued to engine charge and jointed in one plane "heat-to-tail" or "ledge-to-slot". In compliance with one more version, missile head accommodates motor, reduction gear and two or more spools for thread winding connected with sliding bush with gas rudders or interceptors.

EFFECT: better controllability.

10 cl, 3 dwg

Description

The invention relates to missiles, mainly military.

Known open-frame, particleless combustion engine without a housing or nozzle and consisting of 99% of a cylindrical solid rocket checkers of a special structure. However, the problem is the installation on a rocket with such an engine stabilizers. When burning a checker, it is shortened, and if stabilizers were installed on it, they would soon fall off or warp.

When using such missiles from tubular guides with or without a groove to spin the rocket, there is no difficulty. There are no difficulties with missiles that have a gyroscopic control system, however, only the "Regressive weathervane duck" according to US Pat. No. 2410286, or gas-dynamic control using an auxiliary engine in the head of the rocket. However, when using such missiles as maneuverable anti-aircraft missiles, some difficulties are possible - it is desirable for the missile to have plumage, and, quite developed, that maneuver with a certain overload. For this, the following rocket options are possible.

OPTION 1. The missile has a sliding sleeve with stabilizers located on the solid fuel checker, and on the sleeve there are impellers with shafts on which threads are wound, connected to the head of the rocket. Under the influence of an incoming air flow, the impeller rotates, and a thread is wound on the shaft, pulling the sleeve forward (all directions are given relative to the direction of flight). It is desirable that the impeller has oblique blades, that is, it has the appearance of a propeller, more precisely, a turbine (see figure 1).

To reduce the aerodynamic drag of the wound yarn, the impeller shafts can be positioned in the cutouts of the stabilizers.

However, the speed of winding the thread varies depending on the speed of the rocket, which is especially noticeable when starting from the ground. While the burning speed of the checkers is approximately constant. To avoid this drawback, the impeller shaft can be positioned at an angle to the incoming flow so that the external (i.e., far from the longitudinal axis of the rocket) impeller blade is parallel to the flow or even has a negative angle of attack with respect to the planned direction of rotation. In this case, the impeller almost does not rotate under the action of the oncoming flow, and will rotate only when the inner impeller blade enters the cone of the gases flowing from the engine. In this case, the impeller rotation speed will self-regulate as the cage moves toward the head of the rocket: with intensive winding, the inner impeller blade leaves the cone of outflowing gases and the rewind slows down, and vice versa, if the rewind is slowed down, the impeller fully enters the cone of outflowing gases and the speed of the rewind increases .

It is desirable to have at least 6 blades on the impeller.

The impeller can also be with transversely arranged blades and is mounted at the same time in a recessed position at the ends of the stabilizer arms, like roller rollers.

Figure 1 shows this embodiment of the invention, where: 1 - the motor block, 2 - the sleeve on it, 3 - stabilizers on the sleeve, 4 - the shaft installed in the plain bearings in the cutouts of the stabilizer, 5 - the impeller (note on the lower the shaft image shows that the shaft is located at an angle to the incoming flow, and the outer blade is parallel to the flow, that is, it does not create torque, the torque is created by the inner impeller blade not visible in the picture). A thread 6 is wound onto the shaft 4 and passed through the eye 7. Dashed lines 8 show the cone of the gases flowing out of the engine.

The rocket works like this: the impeller 5 rotates under the action of the outgoing gases 8, the thread 6 is wound on the shaft 4, and the sleeve 2 is automatically pulled to the head of the rocket as the end of the engine burns.

OPTION 2. An impeller with oblique or with transverse blades can also be mounted on the head of the rocket - this will slightly reduce the aerodynamic drag of the rocket due to the fact that the filament spools are hidden in the body of the head of the rocket. In this case, the thread pulling system may include a gearbox (for example, a worm gear) and a centrifugal speed stabilizer. In this case, the pull-up speed should be calculated a little more than the linear burning speed of the engine checkers.

OPTION 3. The power required to tighten the bushings with stabilizers is relatively small. Therefore, it can be pulled by an electric motor. Such a rocket contains in the head part an electric motor, a gearbox and two or more spools for winding the thread.

For constant winding speed, the electric motor can be powered by an electronic circuit for stabilizing the speed of rotation (such circuits are well known and are not considered here). The pull-up speed should also be calculated slightly more than the linear burning speed of the engine checkers.

Options 2, 3 are not graphically illustrated and work similarly to option 1.

Options 1, 2, 3 can work well with tubular launch guides, for example, on a grenade launcher or on a MANPADS - a sleeve with stabilizers is fed to the neck of the guide, and the thread is collected in a snake nearby. When launched due to inertia, the sleeve jumps to the rear of the rocket.

OPTION 4. The problem of falling off stabilizers can be solved in a different way: each stabilizer is made of several stabilizers glued to the engine block, and connected in one plane “nose to tail” by a “protrusion-groove” connection.

Glued stabilizers gradually fall off as the engine end burns, and such stabilizers are gradually shortened during the flight.

Figure 2, 3 shows the fourth variant of the rocket, where: 1 - engine block, 3 - small stabilizers glued to it "nose to tail". The front stabilizer is attached to the head of the rocket. When controlling a rocket not in two planes, but in one plane and along a roll, two of the four stabilizers can be much smaller (the top one in the drawing).

The rocket works like this: as the end of the engine burns out, unnecessary parts of the stabilizers fall off.

OPTION 5. This option is intended primarily for missiles that go beyond the atmosphere, but can also be used in the atmosphere.

This rocket contains in the head part an electric motor, a gearbox and two or more spools for winding threads connected to a sliding sleeve with gas rudders or spoilers. Moreover, the threads are made electrically conductive of metal or carbon fiber, and are connected to a power supply and control system.

To position the sleeve, it may have a fire sensor on it.

The rocket works like this: commands and power are supplied to the gas rudders or spoilers along the threads. And the fire sensor controls the winding of the threads so that the sleeve is always at a predetermined distance from the end of the engine.

Claims (10)

1. A rocket with a frameless engineless end-face combustion engine containing a head part and a solid rocket fuel checker, characterized in that it has a sliding sleeve with stabilizers located on the solid fuel checker, and on the sleeve there are impellers with shafts on which threads are wound connected to the head part rockets. 2. The rocket according to claim 1, characterized in that the impeller shafts are located in the notches of the stabilizers. 3. The rocket according to claim 1, characterized in that the impeller shaft is located at an angle to the incoming flow so that the external (that is, far from the longitudinal axis of the rocket) impeller blade is parallel to the flow or even has a negative angle of attack with respect to the planned direction rotation. 4. The rocket according to claim 1, characterized in that the impeller with transverse blades is installed in a recessed position at the ends of the stabilizer arms. 5. A rocket with a particleless, faceless combustion engine, comprising a head and a solid rocket rocket, characterized in that the impeller with oblique or with transverse blades is mounted on the head of the rocket and connected to the spools, which are connected by a thread to the sliding sleeve with stabilizers. 6. A rocket with a frameless engineless end-face combustion engine, comprising a warhead and a rocket of solid rocket fuel, characterized in that the rocket comprises an electric motor, a gearbox and two or more spools for winding threads connected to a sliding sleeve with stabilizers in the head. 7. The rocket according to claim 6, characterized in that the electric motor is powered by an electronic circuit for stabilizing the speed of rotation for constant winding speed. 8. A rocket with a frameless engineless end-face combustion engine containing a head part and a rocket of solid rocket fuel, characterized in that each stabilizer is made of several stabilizers glued to the engine block, and connected in one plane "nose to tail" connection protrusion-groove ". 9. A rocket with a frameless engineless end-face combustion engine containing a head part and a solid rocket rocket, characterized in that the rocket contains in the head part an electric motor, gearbox and two or more spools for winding threads connected to a sliding sleeve with gas rudders or spoilers. 10. The rocket according to claim 9, characterized in that the threads are electrically conductive of metal or carbon fiber and are connected to a power supply and control system, and there is a fire sensor on the sleeve.

Images