RU2812209C9 - Harmonic vibration stand - Google Patents

Abstract

FIELD: testing equipment.

SUBSTANCE: invention can be used to test guidance and control systems for short-range air-to-air missiles not only in stationary industrial conditions, but also in airfield-based conditions of aircraft during pre-flight functional control of engineering technical staff of the Russian Aerospace Forces. Essence: in a harmonic vibration stand containing base 1 with side supports 2 of one-component movable platform 3 with the ability to swing relative to the axis of hinge unit 4 with a locking mechanism, blocks of springs 5 of a given stiffness are introduced equidistant from the swing axis, an angular position sensor of platform 6, supports 7 for missile mounts 8 with additional elements of equipment for monitoring control systems and guidance head 9. Target simulator 10 is installed in the front part of the stand at a certain distance from the guidance head.

EFFECT: increasing the operational manufacturability of a harmonic vibration test bench with minimal weight, size and energy consumption, but sufficiently accurate and adapted for complex functional monitoring of navigation and control systems of air-to-air missiles immediately before their installation on an aircraft.

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Description

The proposed invention relates to testing equipment, and can be used for testing the mechanical control part of the means for testing guidance and control systems for short-range air-to-air missiles, and can also be used not only in stationary industrial conditions, but also in airfield-based conditions aircraft during pre-flight functional control by engineering and technical staff.

A known harmonic oscillation stand (HV) (RF patent for invention No. 1210103, IPC G01P 21/00, G01D 21/00) for testing gravitational equipment, containing a platform for installing the device under test, hingedly connected to a translator made in the form of two parallelograms and a drive mechanism.

The disadvantage of this analogue is the possibility of operation only in stationary laboratory conditions with special requirements. Since the maximum possible load weight on the platform of these stands is no more than 100 kg, this requires the removal of sensors of guidance, control systems, etc. for their separate testing, which entails the effect of multiple division of technological operations due to the removal of sensors and installing them back, reducing the resource and decreased reliability. Also, to attach such stands there must be a rigid, fixed support - a concrete cube or a solid foundation.

There are also known experimental single-stage stands: developments of MSTU named after. N.E. Bauman, a single-stage stand developed by the Corpus software (Saratov), a single-stage stand from Gargo and many others [Precision controlled stands for dynamic testing of gyroscopic devices / D.M. Kalikhman / Under general. ed. acad. V.G. Peshekhonov. - St. Petersburg: State Scientific Center of the Russian Federation Central Research Institute "Electropribor", 2008, 296 pp.] based on single-stage rotating platforms.

The disadvantage of the above analogues is the possibility of their operation only in stationary laboratory conditions with special requirements, the presence of trained, highly qualified personnel. And since the maximum possible weight of the load on the platform of these stands is no more than 100 kg, this requires the removal of sensors of guidance, control systems, etc. for their separate testing, which entails the effect of multiple fragmentation of technological operations due to the removal of sensors and installing them back, reducing the resource and decreased reliability. Also, to attach such stands there must be a rigid, fixed support - a concrete cube or a solid foundation.

The closest prototype to the claimed invention is the “Installation of pitching and long-term tilts UK-900-1K” from the VibroSer-visTest company (RF) (website: https://vstest.ru), intended for testing products for stability when exposed to pitching and long-term inclinations, in terms of checking the product’s compliance with the technical requirements specified in the standards and technical specifications. The installation consists of a one-component platform with the ability to swing about one axis with an inclination angle of ±45°, a manual platform position lock, and an electromechanical drive with a supply voltage of 380 volts with a specified swing period from 7 to 16 s. The disadvantage of the prototype is the possibility of operation only in stationary laboratory conditions with special requirements for fastening, as well as the presence of an electromechanical drive for rotating the platform.

The technical result of this invention is achieved due to the fact that in a harmonic vibration stand consisting of a base with side supports, a one-component platform with the ability to swing relative to a hinge unit in the side supports, a platform position lock at a certain angle of inclination, spring blocks of a given stiffness are introduced equidistant from the swing axis , platform angular position sensor, cradle for mounting the missile with additional hardware elements, control system monitoring functions and a guidance head, allowing to obtain a balanced mass relative to the hinge unit; a target simulator is installed in the front part of the stand at a certain distance from the guidance head.

Thus, the SGC implements the primary stimulating effect on the missile guidance system in the form of periodic mechanical rotational movement of the missile body according to the law of damped harmonic oscillations without any external electromechanical drives. The guidance head tracks the target simulator, and the hardware elements of the control systems control function in just one cycle carry out comprehensive functional control of the navigation and control systems of air-to-air missiles immediately before their installation on the aircraft by the engineering and technical staff in airfield-based conditions.

Figures 1, 2 and 3 show the main design elements of the harmonic vibration stand:

1 - base;

2 - side supports;

3 - movable platform;

4 - hinged unit with a locking mechanism;

5 - spring block;

6 - platform angular position sensor;

7 - rocket cradle;

8 - rocket;

9 - homing head;

10 - target simulator.

The harmonic oscillation stand works as follows.

The side supports 2 are rigidly attached to the base 1, in which a movable platform 3 is installed by means of two hinge units with a locking mechanism 4. The platform 3 is intended for laying and rigid fixation on it using the cradle 7 of the rocket 8 with additional control devices and homing head 9. Block spring 5 is designed to initiate damped harmonic oscillations of the movable SGK system, which occur after the platform is displaced to a certain angle, locked in this position, and then quickly released.

Platform 3 has a U-shaped cross-section with transverse dimensions that allow the rocket garrot to be placed in it, as well as ensuring free rotation of the aerodynamic rudders and ailerons of the rocket. Four supports 7 prevent the rocket from moving in the longitudinal and transverse planes when the platform performs harmonic oscillations.

Using the locking mechanism, you can set two positions of the platform: zero (horizontal) and deflection of the head part down to a given angle.

Locking the frame in the zero (horizontal) position is used to lay the rocket on the platform, to prevent the rocket from moving and falling from the stand before it is secured to the cradle.

After securing the missile to the cradle, auxiliary devices for monitoring the missile control systems and a homing head 9 are installed on it, and a target simulator 10 is installed in the front part of the SGC at a certain distance (Figure 2).

After preparatory operations, the missile is put into working condition and the “Capture” command is issued. The horizontal locking of the platform is removed and, overcoming the resistance of the springs, the platform is smoothly rotated to a certain angular position, and again placed on the lock (Figure 3).

After placing the platform with the missile on the stopper in a given angular position, a technological pause is maintained, during which operations in the guidance system control circuit are performed. After issuing response commands from the missile guidance system and in the presence of zero signals in the circuit of the guidance systems of the “hardware and software complex of functional control” (PAK FC) equipment, the locking is abruptly released. The moving platform 3 with the rocket 8 is released, and under the action of the spring block 5 they begin to perform free damped harmonic oscillations in the vertical plane.

When the platform 3 with the missile performs 8 harmonic damped oscillations, the homing head 9 tracks the target simulator 10, and the PAK FC equipment, through a number of parallel channels, processes information from the signals from the sensors of the head missile guidance system, as well as from the signal from the SGK measuring system.

Thus, the proposed invention makes it possible to: increase operational manufacturability, ensure minimum weight, size and energy consumption indicators, allow for fairly accurate functional monitoring of navigation and control systems of air-to-air missiles immediately before their installation on an aircraft by engineering and technical staff in airfield conditions.

Claims (1)

A stand for harmonic vibrations containing a base with side supports, a one-component platform with the ability to swing relative to a hinge unit in the side supports and a platform position lock at a certain angle of inclination, characterized in that spring blocks of a given stiffness are introduced into it, equidistant from the swing axis, an angular position sensor of the platform , cradle for mounting the rocket with additional elements of equipment for monitoring control systems and a guidance head, allowing for the implementation of a primary stimulating effect on the missile guidance system in the form of periodic mechanical rotational movement of the missile body according to the law of damped harmonic oscillations, in the front part of the stand at a certain distance from the guidance head The missile has a target simulator installed.