RU2288420C2 - Method of conducting stand tests of rocket catapult unit - Google Patents

Abstract

FIELD: methods of testing catapult units for launching rockets.

SUBSTANCE: proposed method consists in placing the weight and overall dimension mock-up of rocket on horizontal guides of jig secured on test stand platform and piston-type catapult unit with solid propellant gas generator placed between and under jig guides. Acceleration of said mock-up is performed by means of catch brought in contact with its rear bottom and rigidly connected with moving piston of catapult unit. Jettisoning of rocket mock-up is carried out directly from horizontal guides of jig. Provision is made for barrier (made from sand, for example) beyond boundaries of jig for catching the rocket mock-up of length "l" which is out of gauge; barrier is made at distance ≤l from point of mock-up takeoff from horizontal guides of jig. Barrier length L= (3-4)l at height of H≥2h, where h is height of mounting of mock-up by its axis on jig horizontal guides. Wooden shield or timber bulkheads are mounted in barrier at distance of (0.5-0.9)L in way of motion of mock-up; barrier is bounded transversely by rigid side walls. Jig, rocket mock-up and piston-type catapult unit are provided with sensors for recording takeoff speed of mock-up, axial load factor of mock-up and pressure of combustion products of solid propellant gas generator in under-piston space of catapult unit.

EFFECT: enhanced informative capacity of stand tests of catapult units; reduction of testing time.

3 cl, 1 dwg

Description

The present invention relates to the field of rocket technology and can be used in the design, development and manufacture of ejection devices for launching missiles.

When developing medium-range missiles (starting weight up to 1.5 tons) with container launch from a launch tube using a piston ejection device, experimental verification of technical solutions is necessary, in terms of the characteristics of missile launch, on weight and size models of the latter, both at the development stage and ( in some cases) in mass production (assessment of the initial speed of the rocket leaving the launch tube, magnitude of overloads, level of ballistic characteristics (VBH) in the process of bailout).

Existing methods for testing ejection devices (KU) of missiles when launched from the launch tube provide for their experimental evaluation in polygon conditions, with vertical launches. At the same time, the fired rocket mockups are usually damaged when dropped onto the ground and are not subject to further use. An example of the design of this type of missiles and KU is given in the source - g. "MILITARY PARADE" ("Military Parade" magazine of the military-industrial complex), April 1994, p. 65, and accepted by the authors as a prototype.

Polygon testing methods for catapult missile devices are characterized by complexity, low information content and high cost during their implementation.

The technical task of the patented invention is to develop an economical and more advanced method for testing rocket ejection devices (KU).

The specified technical problem is solved within the framework of the patented invention by developing a benchmark method for testing rocket launchers without using a launch tube and maintaining technical capabilities for multiple targeted use of the rocket model in subsequent tests, as with testing on horizontal stands at the manufacturer of the rocket launcher and / or components to them, and at landfills.

The invention is illustrated in the drawing, which shows a diagram of the testing of the patented method.

1 - test bench (horizontal slipway);

2 - guides of the horizontal slipway (stand);

3 - solid fuel gas generator (GT);

4 - missile layout;

5 - bulk barrier;

6 - side walls;

7 - a wooden partition;

8 - cylinder;

9 - the piston of the ejection device;

10 - hook;

11 - stock;

12 - bleed holes.

The technical result of the patented method consists in placing a piston ejection device with a solid fuel gas generator and a weight-scale model (4) of a rocket on a test (slipway) stand (1). In this case, the layout is installed on horizontal guides (2) of the slipway, an ejection device including: a solid propellant gas cylinder (3), a cylinder (8) equipped with bleed holes (12), a piston (9), a rod (11) and gas connection fittings with KU cylinder is placed between or under the guides of the slipway. To transfer the force (acceleration) developed during the movement of the piston to the rocket model, a hook (10) in contact with the bottom of the breadboard is rigidly fixed to the piston rod (11). When shooting a missile model, due to the expansion of the products of combustion (PS) of the GG in the piston volume, the catch of the latter is carried out in a bulk barrier (5). Upon completion of the layout bailout GG from the cylinder is carried out through the bleed holes (12). To ensure the efficiency of the catch, the obstacle is carried out at a distance of not less than the length (l) of the layout (rocket), height H≥2h (h is the height of the layout along its axis on the horizontal guides of the slipway) and length (3 ... 4) l. When testing KU of heavy rocket mockups (m> 0.5 t) in a bulk barrier at a distance of (0.5 ... 0.9) · L, a wooden shield and / or log partition (7) is installed along the layout. To reduce the costs during testing (reduce the mass of the bulk barrier) and increase the braking efficiency of the layout, the transverse dimension of the bulk barrier is limited by rigid side walls (6). It was experimentally established that sand can be used as a material of a bulk barrier.

The implementation of the bulk barrier with a height H of at least 2h is due to the need to "hold" the ejection model inside the embankment. If the embankment height is less than 2h, it is possible to “jump out” the model from the embankment and “land” it on the concrete platform (fence) of the test bench, which is accompanied by damage.

The length of the embankment 3 ... 4 of the length of the rocket model, experiments have shown, effectively allows you to catch mock-ups weighing up to 0.5 t. When launching tests of mock-ups of rockets weighing more than 0.5 t, additional ones are needed to exclude the exit (departure) from the bulk barrier damping devices. In the framework of the patented method, the effectiveness of wooden partitions (board and log) was checked. It is most expedient, having extinguished the speed of heavy-weight (more than 0.5 t) layouts in a bulk barrier, limit their further progress along the length of 0.5 ... 0.9 of the length of the bulk barrier with wooden and / or log walls.

At the same time, the slipway, the weight-sized missile prototype, and the piston ejection device are equipped with sensors that record the speed of the descent of the layout from the horizontal slipway guides, the axial overload and the pressure of the combustion products of a solid fuel GT in the under-piston volume of the ejection device.

The essence of the invention lies in the implementation and registration in the bench conditions of the parameters of the launch of the rocket (exit speed from the launch tube, the magnitude of the overloads, the level of the VBH) and the capture of the weight-and-size model of the rocket (when testing the KU) while maintaining the possibility of its use in subsequent tests.

An example implementation of the method.

The method is practically implemented when testing KU missiles with the following characteristics:

- layout dimensions - мак 150 mm, length - 2.5 m;

- layout weight - 0.6 t;

- bulk barrier - sand, the distance from the vanishing point of the breadboard model from the guides of the slipway (“launch pipe cut”) to the embankment is 3.6 m, the length of the embankment is 8.5 m, the horizontal installation height along the layout axis is 0.5 m, height embankments - 1.0 ... 1.2 m; intermediate shield (thickness 50 mm) and log (diameter of logs 150 ... 200 mm) obstacles installed side by side, sequentially one after another, at a distance of 0.6 length of the bulk barrier in the direction of the layout;

- when implementing the method were fixed VBH GG and cylinder-piston group, axial overload and the speed of the layout along the guides of the slipway.

A solid fuel gas generator equipped with charges of smoky and ballistic solid fuel with a total mass of ~ 1.0 kg was used to shoot the prototype. Inhibition of the layout was provided within the bulk barrier. The layout condition for subsequent tests is satisfactory.

A positive effect of the invention is an increase in information content, a reduction in economic and time costs when developing KU rockets.

Claims (3)

1. A method for bench testing a piston ejection device of a rocket, including placing a piston ejection device with a solid fuel gas generator and a weighted model of a rocket on a test bench, launching a solid fuel gas generator, accelerating and shooting a weighted model of a rocket by expanding the combustion products of the said gas generator into a sub-piston device having a different piston catapult volume the fact that the weight-based missile model is installed on the horizontal guides of the slipway, warmed up on the test bench platform, and a piston ejection device with a solid fuel gas generator is placed between and under the guides of the slipway, and the acceleration of the rocket's mock-up is provided by a hook that is rigidly connected to the moving piston of the ejection device, and it is shot directly from horizontal while guiding the slipway, while for catching a weighty-sized missile model of length l outside the slipway at a distance of ≥l from the vanishing point of the removed layout from the horizontal guides of the slipway, a bulk barrier is made of length L = (3 ... 4) l and height H≥2h, where h is the installation height of the breadboard model along its axis on the horizontal guides of the slipway, and in the bulk barrier at a distance of (0.5 ... 0.9) L in the direction of the layout, wooden shield and / or log partitions are installed, and the transverse dimension of the bulk barrier is limited by rigid side walls. 2. The method according to claim 1, characterized in that sand is used as a bulk barrier. 3. The method according to any one of claims 1 and 2, characterized in that the slipway, weight and breadboard model of the rocket and the piston ejection device are equipped with sensors that record the speed of the said layout from the horizontal guides of the slipway, the axial overload of the layout and the pressure of the combustion products of the solid fuel gas generator in the sub-piston the volume of the ejection device.