RU2724000C1 - Device for group launching of satellites - Google Patents

Abstract

FIELD: aerospace engineering.SUBSTANCE: invention relates to aerospace engineering, particularly, to satellite launch devices. Device for group launching of satellites is made in the form of a column of identical sections connected to each other and made in the form of tetrahedral trusses. Farm of each section comprises four lengthwise posts, top and bottom belts with support assemblies connected with lengthwise posts, transverse power elements and diagonal braces. Braces are made in cross section with profile in form of double tee and are attached to each other near their centers. Section of device are equipped with frames, beams of which are made in cross section in form of U-profile. Outer belt of the frames are made so that to enable attachment of launched satellites, and inner belts are fixed on diagonal braces. Jointing points of frame beams with each other are equipped with support platforms, which are connected to inner beams of beams and are made with possibility of arrangement of frame attachment elements to said diagonal braces on said sites.EFFECT: device weight reduction is achieved.5 cl, 5 dwg

Description

The technical solution relates to space technology, namely to means of group launch of satellites.

From the patent of the Russian Federation for utility model No. 148483 (IPC B64G 1/10, publ. 07/07/2014), a device for launching satellites is known, including a farm and means for fastening satellites mounted on it.

In accordance with this decision, the device contains an octagonal truss, including eight longitudinal racks located parallel to the longitudinal axis of the device, upper and lower belts with support nodes and transverse force elements, and diagonal braces located between the longitudinal racks in the openings of the truss except one opening. In this case, the ends of the longitudinal struts, transverse force elements of the truss belts and diagonal braces are connected to the supporting nodes of the truss. In addition, a pair of diagonal braces placed in the aperture of the truss between adjacent posts is connected to each other near their midpoints at the intersection.

In accordance with this utility model, the diagonal braces are made of an I-profile, while the geometric dimensions of their profiles in the solution are chosen constant along the length of the braces. In the most preferred embodiment of the use of this utility model, the transverse force elements are made in cross section with a profile in the form of a corner.

The satellites, separated in the lateral directions, in this solution are mounted on adapters made in the form of rectangular frames mounted on the diagonal braces of the power truss. The adapter frames are made with the length of the side - the side perpendicular to the diagonal braces, 2 ... 2.5 times smaller than the length of the side of the base of the frame. This ensures placement of their fastening and separation means in the adapters of the launched satellites.

In addition, in accordance with the utility model, the satellite launching device also includes means for launching a satellite detachable laterally, placed on a rectangular platform fixed to the longitudinal posts of the truss in the span of the truss without diagonal braces, and means for fastening the satellite located inside the truss and detachable in the axial direction.

The satellite deduction device considered is oriented for satellite deduction along with the main payload of a large mass installed on the supporting nodes of the upper belt of the farm. The supporting nodes of the lower truss belt are connected to the last block of the carrier rocket.

The considered satellite removal device makes it possible to install on the farm up to 8 ... 16 passing loads of small mass, which may differ in the geometry of the seats for mounting with the farm and the direction of their separation from the farm. However, this solution to the satellite deduction device becomes ineffective in the case of solving the problem of deducing satellites identical or similar in geometrical characteristics over a significant calendar period for several launches of launch vehicles. This is relevant, for example, in solving the problem of forming satellite communication systems, consisting of 100 or more satellites and requiring their removal within 2 ... 5 years using several launches of carrier rockets.

The prior art (see, for example, US patents No. 5884866, 6138951, 6276639, 6416018, RF patent No. 2156212), devices are known that provide group launch of 12 ... 20 satellites with similar or identical geometric characteristics. This is ensured by the use of a column in the device of group launch of satellites as the main bearing element, an elongated column along the longitudinal axis of the device, on the side surface of which there are several tiers of fastening devices for launching satellites with the possibility of their separation in the lateral direction.

The closest analogue of the proposed solution is a device for group satellite output, known from US patent No. 6138951 (IPC B64G 1/00, publ. 31.10.2000).

In accordance with US Pat. No. 6,138,951, a device for group launching of satellites includes a longitudinally elongated column made up of sections of the same construction, equipped with fastening devices for launching satellites and separating satellites.

Column sections include longitudinal struts, longitudinal and transverse panels.

In this invention, the longitudinal struts are made in cross section in the form of small sizes of squares and are oriented along the longitudinal axis of the device. The ends of the longitudinal struts of the sections are aligned with the vertices of a regular quadrangle and are equipped with lower and upper supporting nodes, while the upper supporting nodes of the longitudinal struts of each section are connected to the lower supporting nodes of the subsequent section. The lower support nodes of the first section of the column are connected to an adjacent booster block. In addition, the longitudinal racks are equipped with means for fastening and separating launched satellites and are located near their ends.

The transverse panels, providing increased stability of the device during the separation of satellites, are made in the form of circles, placed at the ends of the sections of the device and connected to the longitudinal racks of the sections.

Between the transverse panels of the sections, longitudinal panels are placed: the panels of the first group are placed along the longitudinal axis of the device with the formation of a central power element with a cross section in the form of a small square, and the panels of the second group are oriented in the radial direction and are connected to the longitudinal struts and to the central power element.

Launched satellites are located in the internal volume of the device sections, limited in height by the transverse panels and on the sides by longitudinal panels and a head fairing. To maintain them in a position assembled with the device section in the transverse panels and in the central power element of the sections, small-sized operational cutouts are made.

The placement of launched satellites in the internal volume of the device sections in combination with the small size of the cutouts in the panels complicates the installation of satellites on the device and their maintenance, which determines the long installation time of launched satellites and verification of their operability assembled with the sections of the device. Placing at a short distance from the ends of the longitudinal struts both fastening means and separation means for launched satellites also increases the assembly time of the entire device.

Another disadvantage of the considered device for group launch of satellites is the large mass of the device, which is determined by the selected structural - power scheme of the sections of the device, including longitudinal racks and transverse and longitudinal panels. At the same time, the four-point fastening of satellites to longitudinal power elements under the conditions of an “open” external contour leads to loading of the satellite structure with significant internal forces.

The technical problem solved by the claimed solution is to reduce the mass of the structure of the device for group launch of satellites in combination with a reduction in the assembly time of the device.

The claimed solution to a technical problem is solved as follows.

Like the closest analogue, the device of group launch of satellites is made in the form of a column of identical sections connected to each other.

In accordance with the claimed decision, the sections are made in the form of tetrahedral trusses. The trusses contain four longitudinal struts, upper and lower belts with support nodes connected to the longitudinal struts, transverse force elements and diagonal braces. The diagonal braces are made in cross section with a profile in the form of an I-beam and are placed in each of the openings of the farm between the longitudinal struts and fastened to each other near their midpoints.

In addition, the sections are equipped with frames, the beams of which are made in cross section in the form of a channel with belts oriented outward of the frame. In this case, the outer frame belts are made to ensure fastening of the launched satellites, and the inner belts are mounted on diagonal braces.

The joints of the beams of the supporting frame with each other are equipped with supporting platforms that are connected to the inner belts of the joined beams, reinforced by the walls of the beams extended beyond the junction of the beams, and are made possible to place the frame fastening elements to the diagonal braces on these sites.

Implementation of the structural - power scheme of the sections of the proposed solution in the form of a tetrahedral truss with spans overlapped by diagonal braces, and placement on the last frames connected to the launched satellites, ensuring the transmission of lateral loads between the sections and from the launched satellites through the frames and diagonal braces to the reference sections and eliminating the structural elements of the closest analogue - transverse and longitudinal panels placed inside the sections of the device, allows you to reduce the weight of the structure of the device.

The implementation of diagonal braces with a cross section in the form of an I-beam having a maximum value of the moment of resistance to bending and the moment of inertia, compared with other forms, also reduces the mass of the device of equal strength and stiffness.

The presence at the junction of the beams of the frames of the supporting platforms connected to the inner belts of the beams and reinforced by the walls of the beams extended beyond the junction of the beams, and the implementation of these supporting platforms with the possibility of placing on them the fastening elements of the frame to the diagonal braces can reduce bending moments in the braces and increase stiffness and natural frequencies of satellites on braces without increasing the mass of braces.

The implementation of the frames with the possibility of mounting launched satellites on them, including their adapters with means of fastening and separating the satellites, eliminating operations from the general assembly of the device for the laborious installation of satellite separation means on their adapters, reduces the overall assembly time of the device. Reducing the assembly time of the device is also ensured by providing access to launched satellites and their systems both outside the trusses and inside truss sections.

The technical result of using the proposed solution is to reduce the mass of the device group launch of satellites by 4 ... 7 percent in combination with a reduction in the time of its assembly.

The implementation of the transverse force elements in the form of round rods of tubular section provides their higher strength and rigidity, especially torsion, in comparison, for example, with profiles of the angular section, which in particular prevents their loss of stability, which is especially important for asymmetric loading of the structure.

The longitudinal struts of the sections are most preferably made of carbon fiber, which also reduces the weight of the device.

In addition, the belts of the diagonal braces can be made with decreasing width when moving from the junction of the diagonal braces to each other to the support nodes, which ensures a stress distribution in the belts that is close to uniform and simplifies the fastening of the braces to the vertical struts of the device. This further reduces the mass of the device, both by reducing the mass of the diagonal braces, and by reducing the mass of the support nodes.

Among other things, transverse ribs can be placed in a niche limited by belts and walls of frame beams, which makes it possible to increase the rigidity of frames and further reduce the weight of the device.

The claimed solution is illustrated by the following materials:

FIG. 1 is a General view of the device group launch of satellites in a perspective view,

FIG. 2 is a General view of a section of the device in a perspective view,

FIG. 3 is a side face of a section of a device (view A of FIG. 2),

FIG. 4 is a General view of the support frame in a perspective view,

FIG. 5 is a cross-sectional view of the support frame (view BB from FIG. 4),

FIG. 6 - connection node of adjacent beams of the support frame assembly with a diagonal brace of the truss (callout B from Fig. 2).

Without loss of generality, in the following presentation, we agree to denote by the terms “external” and “internal” elements located respectively farther or closer to the longitudinal axis of the device in the transverse plane.

A device for group launch of satellites (see Fig. 1) is made in the form of a column 10 made of sections 20 connected to each other.

Each section 20 (see Fig. 2) of the device is made in the form of a tetrahedral truss containing four longitudinal racks 21 parallel to the longitudinal axis 1 of the device (see Fig. 3), upper and lower belts and diagonal braces 22 located in each of the openings trusses between the longitudinal struts 21 and fastened to each other near their midpoints. The ends of the longitudinal struts of the sections are aligned with the vertices of a regular quadrangle. The ends of the longitudinal struts 21, the transverse force elements 23 of the upper and lower truss belts and the diagonal braces 22 are connected, as shown in FIG. 1-3, with each other in the support nodes 24 of the lower farm belt and in the support nodes 25 of the upper farm belt.

Longitudinal racks 21 it is advisable to perform in the form of pipes made of carbon fiber, for example, carbon fiber based on high-modulus carbon tape Coulomb-500 / 0,07 (STO 75969440-007-2009). At the same time, the connection of the truss rod elements made of carbon fiber with elements made of metal materials can be performed using overlays (see, for example, RF patent 2292490).

The transverse power elements 23 of the upper and lower zones are expediently made of round rods.

In accordance with the claimed solution, the diagonal braces 22 are most preferably made of blanks with a profile in the form of an I-beam, the belts of which are made with a variable width - with a decrease in the width of its belts when moving from the junction of the diagonal braces to each other to the support nodes (see Fig. 1 -3). In the most preferred embodiment of the proposed solution, the width of the diagonal brace belts near their joints with the frames can be selected in the range from 85 to 105 mm, and when moving to the support nodes it is reduced to 35 ... 50 mm.

In accordance with the claimed solution, the device of group launch of satellites is equipped with frames 30 composed of beams 31 connected to each other at right angles (see Figs. 4, 5). The beams 31 of the supporting frames are made in cross section in the form of a channel with belts oriented outward of the frames. Transverse ribs 34 can be placed in a niche limited by belts 32, 33 and walls 38 of beams. Most preferably, the channel wall height is selected from the range from 65 to 75 mm and the belt width is from 30 to 45 mm.

The outer belts 33 of the beams — the profile belts oriented outward to the truss, are made capable of mounting launched satellites on them, and, as shown in FIG. 5, 6, provided with holes 35 for detachable connections.

The corners of the frames 30 are fixed on the diagonal braces 22 of the farm (see Fig. 1, 2, 3, 6). Moreover, near the corners of the frame are equipped with supporting platforms 37 connected to the inner belts of 32 beams. In addition, the supporting pads 37 are supported by the walls of 38 adjacent beams, extended beyond the junction of the beams. The supporting platforms 37 are made with the possibility of placement on the sites of the elements 36 for attaching frames to diagonal braces. Most preferably, the frame attachment elements 36 to the diagonal braces are oriented along the braces, as shown in FIG. 6, which reduces bending moments in the braces.

The supporting nodes 24 of the lower belt of one of the sections of the column of the device through the transitional farm 40 (see Fig. 1) are connected to an adjacent block of the head of the launch vehicle (conventionally not shown).

In the most preferred embodiment of the technical solution, the column 10 of the device, oriented to use as part of the Soyuz-2 launch vehicle, can be composed of two sections 20 (see Fig. 1) with a height of each section from 1500 to 1750 mm and the length of the transverse power elements from 900 to 1100 mm, which facilitates access to launched satellites from the internal volume of the farm and provides the ability to install an onboard cable network inside the farm. The supporting frames can be made of beams with a length of 450 to 550 mm and a profile wall height of 65 mm ... 75 mm, that is, with a beam wall height of 6 ... 7.5 times less than the length of the beam. The length of the diagonal struts can be selected from a range from 1700 to 1850 mm, and the fastening elements 36 of the supporting frames to the diagonal braces are fixed at a distance from the supporting nodes of the truss at a distance of 400 to 500 mm.

Farm sections can be made of aluminum-based alloys using known methods of machining and assembly. As indicated above, the longitudinal struts are most preferably made of carbon fiber. The support frames are most preferably made integrally in one piece on numerically controlled milling machines. Assembling sections into a column can be carried out using detachable joints.

At the first stage of assembly, sections of the device with launched satellites are assembled, which is most preferably carried out in parallel for sections. In this case, the launched satellites assembled with adapters equipped with satellite separation systems are mounted on the outer belt frames of each of the sections of the device. After this, a general assembly of the column from sections with pre-installed launched satellites on them is carried out. The first of the sections is connected to the transitional farm for mounting the column of the device on the booster block of the carrier rocket.

The resulting inertial loads act on the frames at the satellite-leading site: the normal force perpendicular to the plane of attachment of the satellites, two components of the lateral forces acting in the plane of attachment of the satellites, and two components of the bending moment (we neglect the torque).

All these components of the inertial forces from adapters with launched satellites through the support frames are perceived at the points of attachment of the support frames to the diagonal braces in the form of normal forces acting normally to the braces of the braces and tangential forces acting in the plane of the braces.

As a result, axial and cutting forces and bending moments arise in the braces.

The forces acting on the braces are balanced by the reactions at the points of their attachment to the longitudinal struts by the reactions of the forces along the longitudinal struts and along the transverse elements.

These efforts are summed up along the longitudinal struts and in horizontal planes along the transverse elements and in the plane of attachment of the column to the truss 40 are balanced by the reactions that occur in the truss 40.

After putting the device into the reference orbit, the booster rocket - carrier transfers the device to the working orbits and satellites, upon reaching which the launched satellites are separated from the device.

Claims (9)

1. A device for group launch of satellites, made in the form of a column of identical sections connected to each other, made with the possibility of fastening launched satellites, characterized in that the sections are made in the form of tetrahedral trusses, each of which contains four longitudinal struts, upper and lower belts with support nodes connected to longitudinal struts, transverse force elements and diagonal braces, the last of which are made in cross section with a profile in the form I-beams, placed in each of the openings of the farm between the longitudinal struts and fastened to each other near their midpoints, in addition, sections of the device are equipped with frames, the beams of which are made in cross section in the form of a channel, the frame belts are oriented outward of the frames, and their outer belts are made to ensure fastening of the launched satellites, and the inner belts are mounted on diagonal braces, at the same time, the joints of the beams of the frames with each other are equipped with supporting platforms that are connected to the inner belts of the beams, reinforced by the walls of the beams extended beyond the junction of the beams, and are made possible to accommodate the elements for attaching the frame to the diagonal braces. 2. The device according to p. 1, characterized in that the transverse power elements are made of round rods. 3. The device according to p. 1, characterized in that the longitudinal racks are made of carbon fiber. 4. The device according to claim 1, characterized in that the diagonal brace belts are made with decreasing width when moving from the junction of the diagonal braces to each other to the support nodes. 5. The device according to p. 1, characterized in that in the niche of the beams, limited by their belts and walls, transverse ribs are placed.

Images