Method for test rig development of laser beam-controlled rockets, microrange and test rig for its realization

FIELD: tests.

SUBSTANCE: the rocket is installed on a test rig, the countdown graph is started, the power of the control signal is changed in proportion with the distance of the rocket to the target, and the external actions on the rocket in a real flight are simulated. The operation of the rocket control system and the parameters of the external actions are monitored, the serviceability of the system is determined according to the response of the rocket control system to the checked external actions. The microrange includes a test route, rocket and a test rig for development of the rocket. A guidance instrument is installed on the test route, a device for varying the control signal power in proportion with the distance to the rocket is installed between the guidance instrument and the rocket, and the rocket is positioned on the rig simulating the external actions on the rocket. The device for varying the control signal power is made in the form of optical filters of various penetrability or reflecting surfaces of various curvature that are installed on the shaft of the rotation drive. The rig has a device for installation of the rocket, base and a system for measurements and recording of the rocket parameters. The device for installation of the rocket is made in the form of a gas turbine, whose rotor is fastened on the rocket, and the stator is coupled to the base through a hinge providing for turning of the rotor in the horizontal plane, and an additional rotation assembly installed at a distance from the turbine. The fixed yoke of the additional rotation assembly is coupled through a hinge to the rod of a pendulum, whose axle is installed on the vertical guide of the base. The system for measurement and recording in addition has transducers of rocket attitude, spinning and rocket bank position electrically coupled to the recording system.

EFFECT: provided test rig development of laser beam-controlled rockets in the conditions simulating the real flight, the material for the analysis and repeated use being preserved.

6 cl, 4 dwg

 

The invention relates to the field tests. Preemptive scope - bench testing of guided missiles.

Experimental testing of guided missiles mainly by flight test telemetry transmission of information about their work. This method requires considerable material and time costs, and the quality and amount of information does not always satisfy developers.

This raises the need to develop methods and devices that allow bench to simulate the flight of a rocket with all its nodes.

There is a method of measuring the gyroscopic stability of the rotating apparatus and the device for its realization [see U.S. Patent No. 446739 from 28.08.1984,, IPC G01M 1/16 (1)]. The method includes: securing the projectile to pneumatic ball bearing so that the center of mass of the projectile coincides with the radial axis of the ball joint; the spin of the projectile by the motor via a releasable coupling; uncoupling from the projectile; the message of the rotating projectile transverse momentum forces; monitoring the response of the shell to the applied impulse force depending on the magnitude of the angular velocity of the projectile.

The method is implemented by a device comprising a pneumatic threefold prop rotation, in which the reference spherical element has a radial groove in the system shell, providing the combination of the center of mass of the projectile with the radial axis of the spherical element, the motor and disconnect coupling for the spin of the projectile, detach the engine from the projectile, an electromagnetic device for applying a transverse shock.

The above method and device for determining gyroscopic stability allow the bench to determine the reaction gyrostabilizers of the projectile on the attached side of the pulse.

These method and device for its implementation do not allow testing on bench guided missiles, speed which is insufficient to obtain the gyroscopic effect of the desired value.

A known way of bench testing missiles [see U.S. Patent No. 3314285 from 30.10.1964 year, NCI 73-67 (2)], taken as a prototype of the present invention, in which the missile is mounted on the guide beam (the stand), run onboard equipment (program start) and she is flying in a small distance, and then is captured by the trap, commonly used to measure and record the parameters of the rocket and the data obtained is judged on its performance.

The method is implemented in the test bench to relieve takeoff performance rockets small rods [2].

The stand is made in the form of guide beams for launch, test track small length and traps for the salvation of the product and is micropolygons, to whom that maintains visual observation of rocket flight, measurement of speed, vibration, and acceleration at the initial portion of the trajectory (measurement system).

The rocket is mounted on the guide beam, using a cable system with dampers connected with the base (device setup), and the measuring cable is connected to the recording system.

The trap is made in the form of bulk lattice of the strained perpendicular threads.

At start-up is included on-Board equipment of the rocket (the program start), released lock, fired the engine and it comes with the guide beams (stand) and flies to traps, pulling cables and cable, and then moves to trap up until its movement is not restricted to the working stroke of the damper.

When this happens check the settings of the onboard equipment of the rocket, its speed, acceleration and vibration.

Way, micropolygon and stand, implement, allow to evaluate the performance of the rocket only at the initial portion of the trajectory and does not provide information about the cruise phase, which is the main in the course of the missile, as the flight to cruising the plot is much more starting. Moreover, the absence of rotation does not give the opportunity to work on guided missiles, for which the rotation required.

Solved technical objective of the proposed group of inventions is expanding fu is clonally opportunities by bringing the conditions of bench testing to full-scale by simulating the motion of a rocket in the beam control system on a path.

Technical result:

- getting information about the health of the missile complex in laboratory conditions simulating the actual launch;

- save the missiles for analysis;

- multiple use of the same missiles by replacing waste sites and realignment of management programs.

The problem is solved due to the fact that:

in the way of bench testing managed by a laser beam missiles, including missiles on the stand and start timeline start missiles, the power control signal rocket change is proportional to the distance of the missile to the target and simulate external influences acting on the missile in real flight, thus controlling the operation of the control system of the rocket and the parameters of external influences, and the reaction of the rocket control system for controlled external impact is judged on its performance;

- micropolygon for bench testing managed by a laser beam missiles, including the test track, rocket and stand for testing on the test track has guidance device, between the pointing device and rocket set the device to change the power control signal proportional to the distance of the missile to the target and the missile is placed on the stand, modeling of external influence on the rocket;

- Mick is Polygone device changes the power control signal is made in the form of optical filters of different permeability or reflecting surfaces of different curvature, installed on the axis of the drive rotation;

- stand for testing managed by a laser beam missiles containing the device to install missiles, basis and measurement system and the registration parameters of the rocket, the device for installing missiles made in the form of a gas turbine, the rotor of which is mounted on the rocket, and the stator is connected to the base via a hinge, enabling rotation of the rocket in the horizontal plane, and is installed at a distance from the turbine of the secondary node of rotation, a stationary ring which is connected via a hinge with the rod of a pendulum whose axis is installed on the vertical rail of the base, and the measurement system and registration further comprises a sensor of angular position of the rocket, rotation and position missile roll associated with the recording system;

- stand in the secondary node rotation is made annular manifold connected to a source of air pressure and the power steering rockets.

Changing the power control signal is proportional to the distance to the target allows to determine the operability of the photodetecting devices and missiles in General during the flight.

The control of the onboard equipment of the rocket and the parameters of the simulated external influences allows to determine the response of the missile to external influences and its compliance is a journey to the required values.

The device changes the control signal in the form of optical filters or reflective surfaces of different curvature enables the testing of missiles at a different distance from the pointing device.

Modeling external effects (rotation, oscillations, vibrations) allows you to bring the conditions of bench tests to full-scale launches.

The use of a gas turbine for rotation enables you to test missiles at different speeds by changing the gas flow and pressure, and also to eliminate electrical noise arising from the operation of the drive motor.

Introduction to stand pendulum suspension gives the opportunity to give the rocket an oscillatory motion in a wide range of amplitudes and frequencies by changing the length of the rod of the pendulum and moment of inertia.

The presence of air collector in the secondary node of rotation, is connected to a source of air pressure and the power steering (PDU) missiles, gives the opportunity to test the PDU when the change in the flow rate (pressure) of air, i.e. to simulate different speed missiles.

The invention is explained with graphics, which show:

figure 1 - General view of micropolygon for testing missiles, managed by reflected laser beam (top view);

figure 2 - about the speaker type micropolygon for testing missiles, managed by the laser beam (side view);

figure 3 - General view of the stand for testing of controlled laser beam riding missiles (side view);

figure 4 - additional site rotation with the air manifold (cut).

Micropolygon for the implementation of the method of processing managed by a laser beam missile includes a stand 1 for testing rockets 2, the pointing device 3, the test route 4 and the device changes proportionally to the distance of the missile to the target control signal, made in the form of optical filters 5 different permeability for missiles with guidance by the laser beam or reflective surfaces 6 different curvature for missiles, managed by the reflected beam of the laser, mounted on the axis of the rotation drive 7.

Stand 1 to implement the method of bench testing managed by a laser beam missile consists of a power actuator in the form of a gas turbine 8, the rotor 9 which is rigidly secured to the missile 2 and the stator 10 through the hinge 11 is connected to base 12.

The rotor 9 and the stator 10 is interconnected through the bearings 13. The hinge 11 provides angular movement of the rocket in the horizontal plane.

The stator 10 is made of a nozzle 14 for supplying gas from a source of high pressure turbine 8.

At a distance from the actuator is the rotation unit 15 consisting of clips 16 and sleeve 17, for repleni rocket 2, which interact through the bearings 18. The cage 16, on the one hand, through the hinge 19 is attached to the rod 20 of the pendulum 21, and on the opposite side of the fixed guide 52 with the load 53, designed to change the moment of inertia of the swinging part of the stand. Fixation of cargo 53 on the guide 52 is carried by the screw 54. In the upper part of the rod 20 passes through the bushing 22 and is secured therein by a screw 23. The sleeve 22 through the bearing 24 is mounted on the axis 25, which is fixed by a screw 26 on the guide 27 with a groove 28. The guide 27 is attached to the base 12.

The sleeve 22 is made a groove 29, which includes a belt 30, kinematically connecting sleeve 22 and the pulley 31 mounted on the axis 32 of the sensor 33 angular position of the missile, which can travel in the groove 28 of the guide 27 and is fixed by a screw 34.

For testing missiles with a steering actuator that operates from a velocity head of air, additional site rotation is performed with the manifold 35, in which the air is supplied to the desired pressure through the fitting 36 (figure 4).

The collector is made in the form of grooves 35 in the holder 37, the contacting edges 38 through the seal 39 with the sleeve 40. In the sleeve 40 with holes 41, which connects the manifold 35 with the annular cavity 42, from which the air through the intakes 43 rocket falls into the steering linkage.

The system of measurement and registration of micropoly what it includes radio system parameter definitions missiles and sensors register the parameters of external influences (angular position of the rocket 33, rotation 44 and the position of the missile roll in time 45), electrically connected with the registering property.

The rotation sensor of the missile 44 consists of a tachometer 46, through which the pulley 47 communicates with a rotating missile.

The position sensor of the missile roll in time 45 consists of a light source 48 and the photodetector 49, mounted on the stator 10 of the actuator and cylinder 50, fastened with 2 rocket. In the cylinder 50 with holes 51 through which the light falls on the photodetector 49.

Holes 51 are made of different diameters, which provides a different value of the signal at the photodetector.

Knowing the initial position of the missile relative to the light source - photodetector, the magnitude of the signal it is possible to determine the position of the missile roll in time trials.

The operation of the proposed method (on the example of the method for testing managed by reflected laser beam riding missiles with a steering actuator that operates from a high-speed air pressure) is performed as follows.

Rocket 2 is mounted on the stand by rigid fastening of the rotor 9 and the sleeve 17 on it.

By moving the rod 20 of the pendulum 21 in the sleeve 22 and the axis 25 of the groove 28 of the guide 27 is set to the length of the rod 20, which provides the desired angular frequency of oscillation of the rocket. At the same time moves the sensor 33 angular position p of the chum.

On the track 4 are guidance device 3 and the device in the form of surfaces 6 different curvature installed on the axis of the rotation drive 7.

Then configure radio-telemetric system for measuring and recording the parameters of the rocket control system and tests the functioning of the rocket and the instrument guidance using remotes checks and submit the command to start timeline start (activates on-Board power sources and then onboard equipment and radiotelemetry). After the release of on-Board equipment on operating mode perform the following operations:

applying compressed air to the turbine 8 actuator (imitation of rotation of the missile);

applying compressed air into the manifold 35 additional node of rotation 15 (imitation of the velocity head of air for operation of the steering actuator);

- include guidance device 3;

- install the device changes the power control signal to the minimum reflection (imitation maximum range);

- give the missile angular oscillatory motion of the desired amplitude (simulation of movement on the trajectory).

During the test, the command is given to the rotation drive 7 to rotate the surfaces 6, which allows to increase the power of the reflected control signal (imitation reduce the distance to the target).

When developing missiles, UE is supplied by a laser beam performs the same operation, but installing missiles, device targeting and filters is carried out according to scheme 2.

When testing records parameters of external influences (the number of revolutions of the rocket, its position on the roll in time, the angular position of the missile relative to the pointing device and the settings of the onboard equipment control system of the missile.

Analysis of the tests is to determine the reaction of the rocket control system and on-Board equipment to external influences and compliance timeline start required and according to the results, the conclusion about the health of the rocket.

The present invention can test the missile in the desired range of speed, velocity head of the air, the deviation of the missile from the trajectory and power of the control signal, while retaining the material part for analysis and reuse by replacing blocks of one-time use, which allows high-quality testing of guided missiles on bench.

Sources of information

1. U.S. patent No. 4467639 from 28.08.1984,, IPC G01M 1/16 - equivalent.

2. U.S. patent No. 3314285 from 30.10.1964 year, NCI 73-67 prototype.

1. The way of bench testing managed by a laser beam missiles, including missiles on the stand, start timeline start missiles, characterized in that the ISM is both power and control rocket signal proportional to the distance of the missile to the target, model external influences acting on the missile in a real flight, and record the reaction of the rocket control system for controlled external influences.

2. Micropolygon for bench testing managed by a laser beam missiles, including the test track, the rocket is placed on the stand for testing missiles, characterized in that on the test track has guidance device, between the pointing device and rocket set the device to change the power control signal proportional to the distance of the missile to the target and stand made with the possibility of modeling the external influences on the rocket.

3. Micropolygon according to claim 2, characterized in that it is a device to change power control rocket signal made in the form of optical filters of different permeability installed on the axis of the rotation drive.

4. Micropolygon according to claim 2, characterized in that the device changes the power control rocket signal is made in the form of reflecting surfaces of different curvature, installed on the axis of the rotation drive.

5. Stand for testing managed by a laser beam missiles containing the device to install missiles, base, measurement system and registration options missiles, characterized in that the device for installing missiles made in the form of gas round the ins, a rotor which is fixed on the rocket, and the stator is connected to the base via a hinge, enabling rotation of the rocket in the horizontal plane, and is installed at a distance from the turbine of the secondary node of rotation, a stationary ring which is connected via a hinge with the rod of the pendulum, the axis of which is mounted on vertical guide base can move it, and the system of measurement and registration further comprises a sensor of angular position, rotation and position of the missile roll, electrically connected with the registering property.

6. The stand according to claim 5, characterized in that the secondary node rotation is made annular manifold connected to a source of air pressure and the power steering rockets.



 

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