RU2759326C1 - Method for quality control of production of rocket fairings - Google Patents

Abstract

FIELD: rocketry.SUBSTANCE: invention is intended for quality control of the production of missile fairings. The substance of the invention lies in the fact that the quality parameters of individual operations of the manufacturing process and ground testing are monitored, the condition of the technological and test equipment is monitored, the quality parameters of each technological operation are recorded in its own coordinate system, the reference point of which is rigidly connected with the features of this technological equipment, and the quality parameters of the finished rocket fairing in the process of ground development (testing) are recorded in the coordinate system, the reference point of which is associated with the characteristic design features of the structure, then when anomalous zones are detected in the fairing structure during ground tests that differ from the specifications of the task, the current coordinates of the anomalous zones are revealed in coordinate systems associated with the features of the technological equipment at each operation of the technological process, and the connection between the coordinates in the systems related to the features of the technological equipment and the coordinates in the system related to the design features of the fairings is carried out through mathematical communication operators.EFFECT: improving the reliability of quality control of the production of missile fairings.2 cl, 3 dwg

Description

The invention relates to a technique for quality control of the development and production of elements of aircraft of bodies of revolution, and in particular to quality control of the production of rocket fairings.

An analysis of the known methods of end-to-end control of the production of missile fairings shows that they have the same significant drawback. They have a weak connection in time, in space between the operations of the technological process and the stages of ground tests, control of the design of the element of the aircraft (AC) as a whole. This leads to the fact that when detecting defective areas in a structure during control and testing at various stages of the life cycle, it is rather difficult to determine the time of occurrence. and the coordinates of the cause that led to the occurrence of the defective area.

At present, methods and means of quality control of technological processes in various industries have been developed and are known, for example, technical solutions for patents for inventions of the Russian Federation: No. 2602393 (IPC G06F 11/30, G08B 23/00, H04W 4/12, publ. 20.11 .2016), 2536351 (IPC G06F 17/00, G08B 23/00, G01W 1/00, publ. 20.12.2014), 2304798 (IPC G05B 19/418, publ. 20.08.2007), 2700464 (IPC G05B 19 / 04, F17D 1/08, publ. 09/18/2019), 2615247 (IPC G05B 15/00, publ. 04/04/2017), 2687842 (IPC G01T 1/167, G21C 17/00, publ. 16/05/2019), 2657085 (IPC G05B 19/04, publ. 08.06.2018) and for patents for a useful model of the Russian Federation: No. 48910 (IPC B61K 9/08, publ. 10.11.2005), 108162 (IPC G05B 19/00, publ. 10.09. 2011), 98261 (IPC G05B 19/418, publ. 10.10.2010), 113031 (IPC G05B 19/418, publ. 27.01.2012).

Known modern quality control systems consist of hardware and software. Hardware (primary converters, data transmission lines, controllers, data storage devices, etc.), as a rule, are rigidly tied to the structure of the technological process, and the software part unites them into a single whole (into a system).

In the known technical solutions with a rigid connection of the primary transducers to the technological operations or to the site control object, it is quite easy to identify the reasons, and in the technological processes of the development and production of aircraft elements, for example, ceramic fairings, it is rather difficult.

Many defects can be detected only in the process of ground testing in the coordinate system tied to the aircraft element structure, and the primary transducers for control are tied to technological operations and to the means of production, that is, there is no connection in the fairing positioning systems during manufacturing and ground testing. This is the main drawback of existing systems, complexes for the development and production of rocket fairings, especially ceramic ones, since ceramics is a brittle material.

In the known control methods, the process of finding the cause of the defective zone is laborious and costly, since it requires additional tests and research with the involvement of highly qualified specialists for expert assessment, as well as holding meetings, seminars, etc., which increases the time to find the cause of the defective zone.

In addition, the existing quality control systems "scare" managers of different levels with a cumbersome interface. The intervention of information technology specialists is constantly required. This is one of the reasons why such systems are poorly implemented.

It should be noted that the most intensively integrated automated systems are being introduced in the oil and gas industry (technical solutions for RF patents No. 2602393 (IPC G06F 11/30, G08B 23/00, H04W 4/12, publ. 20.11.2016), 2304798 ( IPC G05B 19/418, publ. 20.08.2007), 2700464 (IPC G05B 19/04, F17D 1/08, publ. 18.09.2019), as well as at facilities with increased danger (technical solutions according to RF patent No. 2536351 (IPC G06F 17/00, G08B 23/00, G01W 1/00, publ. 20.12.2014) and according to the USSR AS No. 1615247 (IPC D01G 23/00).

The closest in technical essence are the system for positioning and monitoring the technical condition of spacecraft, alarm and warning systems for fire safety and the technical condition of complex objects. While the facility is working properly, the control system is silent, when a danger arises, the system warns the relevant authorities or managers. In the technological process of manufacturing, for example, fairings, the situation is the same. If the production yields high-quality products, then there is no need to bother the management, but in case of exceeding the quality tolerances, the system must warn.

As a prototype, the "Hardware and software management complex integrated into the production of ceramic products" was chosen (RF patent No. 2699330 IPC G05B 19/00, G06F 9/00, G06F 13/00, publ. 04.09.2019). The authors of this complex tried to streamline the flow of information in the production of ceramic fairings. It should be emphasized that this was partially succeeded, however, it was not possible to combine the process of making fairings into a single whole with the results of ground testing.

The problem to be solved by the proposed invention is to combine the process of manufacturing fairings into a single whole with the results of ground testing due to complex of diagnostic methods and end-to-end coordinate system.

The technical result consists in increasing the efficiency of quality control of the production of rocket fairings.

The technical result is achieved by the fact that it is proposed:

1. A method for quality control of production of rocket fairings, containing quality control of individual operations of the manufacturing process and ground testing, monitoring the state of technological and test equipment, characterized in that registration of quality parameters of each technological operation is carried out in its own coordinate system, the origin of which is rigidly connected with the features of this technological equipment, and the quality parameters of the finished rocket fairing during ground testing (testing) are recorded in a coordinate system, the origin of which is associated with the characteristic design features of the structure , then, when anomalous zones are detected in the fairing structure during ground tests that differ from the technical requirements of the assignment, the current coordinates of the anomalous zones are revealed in coordinate systems associated with the features of the technological equipment at each operation of the technological process, and the relationship between the coordinates in systems related to the features technological equipment and coordinates in the system associated with the design features of the fairings is carried out through mathematical communication operators.

2. A method for quality control of the production of missile fairings, according to claim 1, characterized in that the mathematical operator in technological operations, where the fairing does not rotate around its own axis of symmetry, can be specified by the formulas:

;

;

;

;

Z ⁿ = H ₀ + H ,

– угол между плоскостью Z ^H O ^H X ^H и плоскостью, проходящей через ось Z ^H O ^H и ось ZO; where

- the angle between the planeZ ^H O ^H X ^H and a plane passing through the axisZ ^H O ^H and axisZO;

R ₀ - the distance between the axes Z ^H O ^H and ZO ;

r _{( z )} is the radius of the section with the Z coordinate;

H ₀ - distance from the plane of the end of the product to the plane Y ^H O ^H X ^H ;

H is the distance from the section with the radius r _{( z )} to the plane of the end face of the product.

The essence of the proposed technical solution lies in the fact that the registration of quality parameters of each technological operation is carried out in its own coordinate system, the origin, in which it is rigidly connected with the features of this technological equipment, and the quality parameters of the finished fairing in the process of ground testing (testing) are recorded in the coordinate system , the reference point, which is associated with the characteristic design features of the structure, for example, with a reference point on the nose of the fairing, and the reference point on the fairing is rigidly tied to the zero reference point in each coordinate systemi-th technological operation, then, upon detection of defective zones in the structure during ground tests, differing from the technical requirements of the assignment, the current coordinates of defective zones are revealed in coordinate systems associated with the features of technological equipment at each operation of the technological process, and the relationship between coordinates in systems related to the features of technological equipment and coordinates in a system associated with the design features of fairings such as bodies of revolution , carried out through mathematical communication operators.

To control the production of fairings for rockets such as bodies of revolution, the mathematical operator in technological operations where the fairing does not rotate around its own axis of symmetry can be specified by the formulas:

;

;

;

;

Z ⁿ = H ₀ + H ,

,

– угловые координаты системы координат технологического оборудования;where

,

- angular coordinates of the technological equipment coordinate system;

– угол между плоскостью Z ^H O ^H X ^H и плоскостью, проходящей через ось Z ^H O ^H и ось ZO;

- the angle between the planeZ ^H O ^H X ^H and a plane passing through the axisZ ^H O ^H and axisZO;

R ₀ - the distance between the axes Z ^H O ^H and ZO ;

r _{( z )} is the radius of the section with the Z coordinate;
H ₀ - distance from the plane of the end of the product to the plane Y ^H O ^H X ^H ;

H is the distance from the section with the radius r _{( z )} to the plane of the end face of the product.

The coordinate system must contain:

- uniform means of registering the coordinates of the investigated area at all stages of the fairing creation;

- reference points of the component parts of the fairing (shell, frame, rings, etc.);

- reference point of the fairing;

- reference points of technological and test equipment.

The figure 1 schematically shows an end-to-end coordinate system for tracking the state of the fairing during its production.

In the end-to-end system, the coordinates ( x, y, z ) of any point A of the fairing in the mobile system (attached to the structure) can be expressed in terms of coordinates ( Xi, Yi, Zi ) attached to the process and test equipment.

Such a system makes it possible to tie the model of the technological process of manufacturing the fairing to the features of the technological equipment.

координаты любой точки А поверхности обтекателя могут быть заданы через координату Z и угол α (между плоскостью ZOX и плоскостью, проходящей через точку А и осью Z подвижной системы координат, привязанной к изделию). При тех же условиях координаты точки А в системе координат, привязанной к технологическому и испытательному оборудованию могут быть заданы через координату Z и двумя углами α^н и β^н (см фигуру 3). α^н – угол между плоскостью Z ^H O ^H X ^H и плоскостью, проходящей через ось Z ^H O ^H и точку А. β^н – угол между плоскостью Y^HO^HX^H и радиусом-вектором O ^H А.With the known equation of the fairing contour

coordinates of any pointA the fairing surfaces can be specified via the coordinateZ and angle α (between the planeZOX and a plane passing through point A and the Z-axis of the movable coordinate system attached to the product). Under the same conditions, the coordinates of the pointA in the coordinate system associated with the technological and test equipment can be specified through the coordinateZ and two angles αⁿ and βⁿ (see figure 3). αⁿ - the angle between the planeZ ^H O ^H X ^H and a plane passing through the axisZ ^H O ^H and pointA... βⁿ - angle between plane Y^HO^HX^H and radius vectorO ^H A...

It should be noted that the coordinate systems associated with technological and test equipment are implemented by software.

Suppose that a defect is detected at point A ( x, y, z ) (in the moving coordinate system) of the fairing during ground mining, then calculating the coordinates of point A (alternately) for each operation relative to the i- th coordinate system in time, it is possible to reveal the relationship between the parameters technological process and parameters of the fairing design in the space-time coordinate system.

On the basis of a complex of diagnostic methods and an end-to-end coordinate system, at the modern level of computer technology, it is possible to implement an automated search system for analyzing cause-and-effect relationships in the development and production of fairings.

The main elements of such a system are:

- a subsystem for automatic scanning and input of the coordinates of points of the investigated zones into the computer;

- a subsystem of coordinate grids of all links of the technological process, taking into account the characteristics of the equipment, for example, the temperature field in the firing furnace T = f _{( X} ^H _{, Y} ^H _{, Z} ^H ₎ ;

- a subsystem for analyzing the results of non-destructive testing during ground testing in conjunction with the current quality of the technological process, including the human factor.

Obviously, for the practical implementation of the end-to-end coordinate system, it is necessary:

- a comprehensive study of all technological and test equipment (search for features and setting reference points on technological and test equipment);

- to develop a universal (for all links of the technological process) coordinate table with an electric generator of coordinates, which starts when an anomalous zone is detected on the fairing.

Figure 2 shows a movable coordinate system attached to the fairing.

Figure 3 shows the coordinate system associated with the i- th technological equipment.

From Figures 2 and 3 it can be seen that the operators of the transition from the coordinate system tied to the reference point of the fairing in the i-th coordinate system of the technological operation (in the absence of rotation) can be specified by the formulas:

;

;

;

;

Z ⁿ = H ₀ + H.

,

– угловые координаты системы координат технологического оборудования;where

,

- angular coordinates of the technological equipment coordinate system;

– угол между плоскостью Z ^H O ^H X ^H и плоскостью, проходящей через ось Z ^H O ^H и ось ZO;

- the angle between the planeZ ^H O ^H X ^H and a plane passing through the axisZ ^H O ^H and axisZO;

R ₀ - the distance between the axes Z ^H O ^H and ZO ;

r _{( z )} is the radius of the section with the Z coordinate;

H ₀ - distance from the plane of the end of the product to the plane Y ^H O ^H X ^H ;

H is the distance from the section with the radius r _{( z )} to the plane of the end face of the product.

Claims (10)

1. A method for quality control of production of rocket fairings, containing quality control of individual operations of the manufacturing process and ground testing, monitoring the state of technological and test equipment, characterized in that registration of quality parameters of each technological operation is carried out in its own coordinate system, the origin of which is rigidly connected with the features of this technological equipment, and the quality parameters of the finished rocket fairing during ground testing (testing) are recorded in a coordinate system, the origin of which is associated with the characteristic design features of the structure , then, when anomalous zones are detected in the fairing structure during ground tests that differ from the technical requirements of the assignment, the current coordinates of the anomalous zones are revealed in coordinate systems associated with the features of the technological equipment at each operation of the technological process, and the relationship between the coordinates in systems related to the features technological equipment and coordinates in the system associated with the design features of the fairings, is carried out through mathematical communication operators. 2. A method for quality control of the production of missile fairings according to claim 1, characterized in that the mathematical operator in technological operations, where the fairing does not rotate around its own axis of symmetry, can be specified by the formulas:

;

; Z ⁿ = H ₀ + H , where

- the angle between the planeZ ^H O ^H X ^H and a plane passing through the axisZ ^H O ^H and axisZO; R ₀ - the distance between the axes Z ^H O ^H and ZO ; r _{( z )} is the radius of the section with the Z coordinate; H ₀ - distance from the plane of the end of the product to the plane Y ^H O ^H X ^H ; H is the distance from the section with the radius r _{( z )} to the plane of the end face of the product.

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