RU203407U1 - POWER STRUCTURE OF THE SPACE VEHICLE CASE - Google Patents

Abstract

The utility model refers to mesh structures made of composite materials and can be used in products of aviation and rocket and space technology. The power structure of the hull (SCC) of the spacecraft (SC) is designed to mount SC modules with onboard and target equipment, solar battery wings, storage tanks the working fluid, as well as the elements of the separation system. The tasks to be solved by the claimed technical solution are to improve the design of the SCS spacecraft, increase the reliability, manufacturability and degree of unification. of a composite material of a hollow cylindrical shape, having a mesh structure formed by intersecting spiral and annular ribs, while the ends of the mesh shell are made with integrated reinforcing elements - frames. The mesh shell is made with longitudinal ribs, and the spiral ribs are arranged in pairs, while the frames are made with the lower and upper interfaces. The technical results when using the SCV of the SC with the given set of features are the achievement of a balance of optimal values of the main parameters of the SCV of the SC in accordance with the requirements for technical and operational characteristics ; achievement of increased bearing capacity, axial and lateral rigidity of the mesh shell.

Description

The utility model refers to mesh structures made of composite materials and can be used in products for aviation and rocket and space technology.

The spacecraft (SC) hull load-bearing structure (SC) is intended for fastening SC modules with onboard and target equipment, solar battery wings, working fluid storage tanks, as well as elements of the separation system.

The SCV of the spacecraft must have a given bearing capacity that ensures its integrity under external influences, i.e. have high rigidity and strength. Other requirements for the SCV of the spacecraft are the requirements for ensuring the optimal values of the main parameters:

- high degree of reliability;

- a high degree of unification;

- a high degree of manufacturability;

- dimensional stability;

- low cost;

- low weight.

In the production of a spacecraft, a significant role is played by the production time of its components. The use of technical unification in the manufacture of spacecraft SCCs allows to reduce the time for adaptation to a specific SC, contributes to the realization of the possibility of a wider application of SCCs when creating SCs for various purposes.

At the moment, both in domestic and foreign production of non-pressurized spacecraft, a modular construction principle is used, in which the spacecraft consists of several structurally and functionally separate modules, for example, a service systems module and a payload module, which are attached to one SCC frame. The main variants of the SCK spacecraft can be presented in the form:

- structures made of honeycomb sandwich panels (skins with honeycomb filler between them);

- monolithic construction, without honeycomb filler;

- shells of revolution with a mesh structure.

It is known that of the above embodiments, the optimal parameters, taking into account the requirements indicated above, are possessed by shells of revolution having a mesh structure, the supporting elements of which are ribs that simultaneously provide membrane and bending rigidity of the structure. The geometric shape of the SCV spacecraft in the form of a cylinder contributes to the uniform distribution of the load on the structure as a whole.

It is also known that the use of polymer composite materials as a material for the manufacture of SCC spacecraft makes it possible to reduce the mass of structures by an average of 15-30% compared to metal structures; in addition, modern composite materials (for example, carbon fiber reinforced plastics) surpass aluminum alloys in specific stiffness by 2- 3 times, and in terms of specific strength 5-6 times. The low coefficient of thermal expansion of polymer composite materials ensures dimensional stability of the structure when exposed to a wide range of temperatures in the space environment. The SCC of the spacecraft is integral - the connection of the ribs to each other, as well as to other structural elements, is realized during the manufacture and polymerization of the binder composite material. At present, the ribs of the SCC spacecraft, manufactured under industrial conditions from high-modulus carbon-fiber reinforced plastics, have an elastic modulus of 185 GPa, i.e. close to the modulus of steel with a density of 5.2 times less.

The SCV of the spacecraft must combine the optimal values of the main parameters, the achievement of the balance of which is a technical problem.

It should be noted that the choice of configuration and type of mesh structure during design depends on the effect of a combination of static and dynamic loads. Also, the action of loads can lead to the occurrence of local stresses in the ribs of the mesh shell of the SCC spacecraft. Based on these conditions, select the optimal number and size of longitudinal ribs that increase the axial rigidity of the mesh shell; determine the angle of inclination and the number of spiral ribs, the number and pitch of the annular ribs, which set the lateral rigidity, and also impart the property of self-stabilization to the mesh shell of the SCC of the spacecraft. The parameters of the ribs are selected to ensure the minimum mass, as well as the required strength and rigidity of the mesh shell structure. The configuration of the mesh shell is determined by a special calculation, while the mesh shell of the SCC spacecraft can be made of a composite material based on high-modulus carbon fiber, using the "wet" winding method.

Thus, the SCC of the spacecraft is a shell of revolution made of a composite material of a hollow cylindrical shape, having an anisogrid mesh structure formed by the intersection of spiral, annular and longitudinal ribs, with the formation of cells of several standard sizes. In this case, the spiral ribs are arranged in pairs, and the ends of the mesh shell are made with integrated reinforcing elements - frames, which have lower and upper interfaces.

From the prior art, various designs of SCCs of a mesh structure are known:

- RF patent No. 2475412 "The shell of the compartment of a sealed fuselage of a main plane from a polymer composite material and a method for its manufacture" is made in the form of a laminated skin with a mesh of reinforcing ribs. The grid of reinforcing ribs contains helical ribs with lateral surfaces in the form of surfaces of a straight helicoid of the right course with a turn of these ribs in the area of the compartment end and their transition into helical ribs of the left stroke and vice versa, as well as longitudinal ribs with their U-shaped turn in the zones of the ends of the compartment. The ribs are evenly distributed over the surface of the compartment, formed in layers and made continuous. The ribs are composed of layers of unidirectional strands of polymer composite fibers held together by a polymer binder. On the mesh of the reinforcing ribs, an outer layered skin made of a polymer composite material is formed. The disadvantage of this analogue is the absence of reinforcing elements at the ends of the mesh structures, for example, frames integrated into the structure of the mesh shell.

The need to strengthen the ends is caused by ensuring the integrity of the ribs of the mesh shell, as well as the implementation of the possibility of fastening structural elements or launching means, which implies the presence of interfaces with surfaces and mounting holes.

- RF Patent No. 176806 "Isogrid (mesh) tail boom of a helicopter made of composite materials", which is formed from layers of systems of intersecting spiral and longitudinal strips of unidirectional threads fastened with a polymer binder, repeating along the thickness of the shell wall. Reinforcing frames consist of layers of composite material and layers of metal foil. A shell made of composite materials is installed on the end reinforcing frame located in the tail area. The disadvantage of this analogue is the presence of additional intermediate reinforcing frames, as well as the tail shell, which significantly increase the mass of the structure.

The prior art also knows various designs of the SCC of the mesh structure, which are intended for fastening the structural elements of the spacecraft and are presented in a number of descriptions of the inventions below.

RF patent No. 2622304 "Power structure of the spacecraft platform", which contains a shell of revolution made of a composite material of a hollow cylindrical shape, having a mesh structure formed by intersecting spiral ribs, while reinforcing elements are fixed at the ends of the mesh shell (in the form of frames shown in the prototype drawings). The mesh structure in this case has an isogrid type, characterized by cells of the same standard size with their uniform distribution throughout the entire volume of the shell. The disadvantage of the analogue is the low bearing capacity of the isogrid mesh, due to the absence of annular and longitudinal ribs, which can lead to the destruction of the ribs of the mesh.

To ensure the strength and rigidity of the SCC of the spacecraft, in addition to spiral ribs, it is advisable to have annular and longitudinal ribs located in accordance with the variable nature of the acting combined loads. In addition, the prevailing forces in the structures under consideration, designed to secure the spacecraft structural elements, are oriented along the longitudinal axis of the spacecraft SCV and are most effectively perceived by the longitudinal rather than spiral ribs. In this case, the local stresses of the ribs can be compensated for by the longitudinal ribs, which will prevent deformation and destruction of the mesh structure of the SCC of the spacecraft. It should also be noted that the paired arrangement of the spiral ribs will provide a higher bearing capacity of the mesh structure.

The presence of annular and longitudinal ribs in the SCC is indicated in the description of the inventions:

- RF Patent No. 2392122 "Mesh shell of rotation made of composite materials", formed from layers of systems of intersecting spiral, longitudinal and annular ribbons repeating along the thickness of the shell wall from unidirectional threads fastened with a polymer binder, forming spiral, annular, longitudinal and additional ribs. Additional ribs are oriented longitudinally. Additional ribs are shorter than the generatrix length and are unevenly distributed along the length and perimeter. The disadvantages of the known design are:

- low degree of manufacturability;

- the need for additional reinforcement of the structure in the area of the lower frame;

- the need to organize additional interfaces for docking with mating elements.

- US Patent No. 20100065717 "METHOD AND SYSTEM FOR FORMING COMPOSITE GEOMETRIC SUPPORT STRUCTURES". The support structure is a three-dimensional mesh shell of a hollow cylindrical shape made of a composite material, which is formed by the intersection of spiral, longitudinal, annular and / or lateral transverse ribs (supports) to form a plurality of nodes. The ends of the support structure can be equipped with frames with an aerodynamic profile. The disadvantage of this analogue is the lack of integration of the frame into the structure as a whole, which leads to a loss of strength, rigidity of the structure, as well as a decrease in the reliability of the connection of the ribs of the mesh shell with the frame.

Based on the purpose and the closest set of essential features as the closest analogue (prototype), the "Power structure of the spacecraft body", known from the description of the utility model to the patent of the Russian Federation No. 196913, was chosen, which contains a shell of revolution made of a composite material of a hollow cylindrical shape, having anisogrid mesh structure formed by the intersection of spiral and annular ribs with the formation of cells of two standard sizes. At the same time, reinforcing elements - frames are fixed at the ends of the mesh shell, which are formed by closed circumferentially rectangular profiles and have profiling grooves for the ribs of the mesh structure.

The disadvantages of the prototype are the low bearing capacity and insufficient rigidity of the mesh shell, due to the absence of longitudinal and paired spiral ribs, which is necessary to meet the requirements when designing the configuration of the structure of the claimed SCC.

The tasks to be solved by the claimed technical solution are: improving the design of the SCV spacecraft, increasing the reliability, manufacturability and degree of unification.

The tasks are solved by the fact that the power structure of the spacecraft body contains a shell of revolution made of a composite material of a hollow cylindrical shape, having a mesh structure formed by the intersection of spiral and annular ribs, while the ends of the mesh shell are made with integrated reinforcing elements - frames ... The mesh shell is made with longitudinal ribs, and the spiral ribs are arranged in pairs, while the frames are made with lower and upper interfaces.

The spiral ribs are formed by rectangular profiles, one half of which is oriented at an angle to the plane of the frames, and the second half is oriented mirrored to the first half, while the spiral ribs are located with an equal angular pitch around the circumference of the frames and connect them to each other.

The annular ribs are formed by circumferentially closed rectangular profiles, oriented parallel to the plane of the frames and located between the frames with an equal pitch from each other.

Longitudinal ribs can be made of different lengths, but shorter than the length of the generating line of the mesh shell, formed by rectangular cross-section profiles, oriented perpendicular to the plane of the frames and distributed along the cylindrical surface of the mesh shell in pairs, with an equal pitch from each other, while some ends of these ribs are conjugated with the frame, on which the lower interface is installed, and the other ends are mated with annular and / or spiral ribs.

Frames are formed by closed circumferentially rectangular profiles and can protrude beyond the plane of the cylindrical surface of the mesh shell. Also frames can be made of composite material.

The lower interface consists of overlays located on the frame with an equal pitch from each other, having a U-shaped profile, made with the possibility of mating with the frame, and counterpads, providing fixation of the lower interface with glue and fastening connection, while the lower interface overlays are made with holes, seats and bosses.

The upper interface consists of clamps located on the frame with an equal pitch from each other, made with the possibility of mating with the frame, having holes, seats and bosses, while fixing the clamps on the frame is carried out using glue and a fastening connection. Also, the lower and upper interfaces can be made of metal alloys.

The mesh shell can be made of a composite material based on high-modulus carbon fiber, using the "wet" winding method.

The technical results when using the SCC of the spacecraft with the given set of features are:

- achieving a balance of optimal values of the main parameters of the SCV spacecraft in accordance with the requirements for technical and operational characteristics;

- the achievement of increased bearing capacity, axial and lateral rigidity of the mesh shell.

The essence of the utility model is illustrated by the drawings shown in FIG. 1 - 11:

- fig. 1 - general view of the SCS spacecraft;

- fig. 2 - the main view of the SCS spacecraft;

- fig. 3 is a view A shown in FIG. 2 (general view of the installation of the upper interface of the SCK SC);

- fig. 4 is a view B shown in FIG. 2 (general view of the installation of the lower interface of the SCK spacecraft);

- fig. 5 is a view B shown in FIG. four;

- fig. 6 is a view D shown in FIG. four;

- fig. 7 - remote element D shown in FIG. four;

- fig. 8 is a view K shown in FIG. 3;

- fig. 9 - sec. G-G shown in FIG. 7;

- fig. 10 - sec. AND shown in FIG. 7;

- fig. 11 - sec. EE shown in FIG. 7.

The power structure of the spacecraft body contains a shell of rotation made of a composite material of a hollow cylindrical shape, having a mesh structure formed by the intersection of spiral and annular ribs 1, 2, while the ends of the mesh shell are made with integrated reinforcing elements - frames 4, 5 The mesh shell is made with longitudinal ribs 3, and the spiral ribs 1 are arranged in pairs, while the frames 4, 5 are made with the lower and upper interfaces 6, 7.

Spiral ribs 1 are formed by rectangular profiles, one half of which is oriented at an angle to the plane of frames 4, 5, and the second half is oriented mirrored to the first half, while spiral ribs 1 are located with an equal angular pitch around the circumference of frames 4, 5 and connect them together ...

The annular ribs 2 are formed by circumferentially closed rectangular profiles, oriented parallel to the plane of the frames 4, 5 and located between the frames 4, 5 with an equal pitch from each other.

Longitudinal ribs 3 can be made of different lengths, but shorter than the length of the generating line of the mesh shell, formed by rectangular cross-section profiles, oriented perpendicular to the plane of frames 4, 5 and distributed over the cylindrical surface of the mesh shell in pairs, with an equal pitch from each other, with some ends of these ribs coupled with the frame 4, on which the lower interface 6 is installed, and the other ends are coupled with the annular and / or spiral ribs 2, 1.

Frames 4, 5 are formed by closed circumferentially rectangular profiles and can protrude beyond the plane of the cylindrical surface of the mesh shell. Also frames 4, 5 can be made of composite material.

The lower interface 6 consists of overlays located on the frame 4 with an equal pitch from each other, having a U-shaped profile, made with the possibility of mating with the frame 4, and counterpads providing fixation of the lower interface 6 using glue and fasteners, while the lower interface pads 6 are made with holes, seats and bosses 8.

The upper interface 7 consists of clamps located on the frame 5 with an equal pitch from each other, made with the possibility of mating with the frame 5, having holes, seats and bosses 9, while fixing the clamps on the frame 5 is carried out using glue and fasteners.

Also, the lower and upper interfaces can be made of metal alloys.

SCK KA is manufactured taking into account the design requirements using the manufacturing technology by the method of "wet" winding of carbon fiber impregnated with an epoxy binder.

Winding is a process of manufacturing high-strength reinforced products, the shape of which is determined by the rotation of arbitrary generatrices. In this method, the reinforcing material (carbon filament) is laid along a predetermined path on a rotating mandrel, which determines the internal geometry of the product.

The winding method is used to form products that operate under specific loading conditions, such as internal or external pressure, compressive or torsional loads. Products are designed and manufactured with a high degree of precision.

The carbon fiber structures obtained by winding have a number of advantages over similar products made from traditional materials. First of all, this is increased strength with a low dead weight, which allows you to achieve an optimal ratio of the structure weight to the payload. Other advantages of the winding method are:

- a fast and therefore cost-effective method of laying the reinforcing material;

- inexpensive materials.

"Wet" winding provides increased formability of products, therefore, it is mainly used in the manufacture of large-sized casings of complex configuration.

The ribs of the SCK KA mesh shell are made of carbon fiber based on M46J or M55J carbon fiber impregnated with an epoxy binder.

SCK spacecraft is characterized by the following parameters:

- rib height from 14 to 18 mm;

- the thickness of the spiral ribs is from 3.5 to 5.5 mm;

- the thickness of the annular ribs is from 2 to 4 mm;

- the thickness of the longitudinal ribs is from 5 to 7 mm;

- the angle of inclination of the spiral ribs is 21 °.

The use of unification in the manufacture of this SCC of the spacecraft also provides technical and economic advantages, expressed in reducing the costs and production time by using standard technological processes when creating a number of modifications of the spacecraft for heavy-class spacecraft for various purposes.

Claims (10)

1. The power structure of the spacecraft body, containing a shell of revolution made of a composite material of a hollow cylindrical shape, having a mesh structure formed by the intersection of spiral and annular ribs, while the ends of the mesh shell are made with integrated reinforcing elements - frames, characterized by the fact that that the mesh shell is made with longitudinal ribs, and the spiral ribs are arranged in pairs, while the frames are made with lower and upper interfaces. 2. The body structure according to claim 1, characterized in that the spiral ribs are formed by rectangular cross-section profiles, one half of which is oriented at an angle to the plane of the frames, and the second half is oriented mirrored to the first half, while the spiral ribs are located with an equal angular pitch along the circumference frames and connect them together. 3. The body structure according to claim 1, characterized in that the annular ribs are formed by circumferentially closed rectangular profiles, are oriented parallel to the plane of the frames and are located between the frames with an equal pitch from each other. 4. The power structure of the body according to claim 1, characterized in that the longitudinal ribs can be made of different lengths, but shorter than the length of the generating line of the mesh shell, formed by rectangular cross-section profiles, oriented perpendicular to the plane of the frames and distributed over the cylindrical surface of the mesh shell in pairs, with equal pitch from each other, while some ends of these ribs are mated with the frame on which the lower interface is installed, and the other ends are mated with annular and / or spiral ribs. 5. The structural structure of the body according to claim 1, characterized in that the frames are formed by circumferentially closed profiles of rectangular cross-section and can protrude beyond the plane of the cylindrical surface of the mesh shell. 6. The body structure according to claim 1, characterized in that the frames are made of a composite material. 7. The power structure of the body according to claim 1, characterized in that the lower interface consists of overlays located on the frame with an equal pitch from each other, having a U-shaped profile, made with the possibility of mating with the frame, and counterpads, ensuring fixation of the lower interface with glue and fasteners, while the bottom interface covers are made with holes, seats and bosses. 8. The body structure according to claim 1, characterized in that the upper interface consists of clamps located on the frame with an equal pitch from each other, made with the possibility of mating with the frame, having holes, seats and bosses, while fixing the clamps on the frame is carried out with glue and fasteners. 9. The power structure of the housing according to claim 1, characterized in that the lower and upper interfaces are made of metal alloys. 10. The power structure of the body according to claim 1, characterized in that the mesh shell is made of a composite material based on high-modulus carbon fiber by the "wet" winding method.

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