阅读说明：本技术 堆叠卫星发射结构 (Stacked satellite launching structure ) 是由 尹健 杜冬 秦美泽 赵川 肖宁斌 张晓彤 周圣鹏 于 2021-09-14 设计创作，主要内容包括：本发明提供了一种堆叠卫星发射结构,包括上层组件、橡胶垫以及下层组件；所述橡胶垫位于所述上层组件与所述下层组件之间；所述堆叠卫星发射结构包括压紧状态与弹离状态；当处于压紧状态时,所述上层组件、橡胶垫、下层组件紧密贴合,橡胶垫由于被上层组件与下层组件挤压产生压缩变形,具有回弹力；当处于弹离状态时,橡胶垫由于回弹力将上层组件与下层组件相互弹开,使上层组件与下层组件分离。本发明设置有橡胶垫结构,橡胶垫可以减轻上层组件以及下层组件碰撞导致的危害,并且能够确保在压紧状态下,上层组件的太阳阵结构能够被紧密的压紧在上层组件的卫星底部结构板的底面,在弹离状态中所述橡胶垫有足够的回弹力使上层组件与下层组件分离。(The invention provides a stacked satellite launching structure, which comprises an upper layer assembly, a rubber pad and a lower layer assembly; the rubber pad is positioned between the upper layer assembly and the lower layer assembly; the stacked satellite launching structure comprises a pressing state and a bouncing-off state; when the rubber pad is in a compressed state, the upper layer assembly, the rubber pad and the lower layer assembly are tightly attached, and the rubber pad is compressed and deformed by the upper layer assembly and the lower layer assembly and has resilience force; when being in the bullet state of leaving, the rubber pad is owing to resilience force bounces upper assembly and lower floor's subassembly each other and is opened, makes upper assembly and lower floor's subassembly separation. The invention is provided with the rubber pad structure, the rubber pad can reduce the harm caused by the collision of the upper layer assembly and the lower layer assembly, and can ensure that the solar array structure of the upper layer assembly can be tightly pressed on the bottom surface of the satellite bottom structural plate of the upper layer assembly in a pressing state, and the rubber pad has enough resilience to separate the upper layer assembly from the lower layer assembly in a bouncing-off state.)

1. A stacked satellite launching structure is characterized by comprising an upper layer assembly, a rubber pad (3) and a lower layer assembly; the upper layer assembly is detachably connected with the lower layer assembly; the rubber pad (3) is positioned between the upper layer assembly and the lower layer assembly and is arranged at the top of the lower layer assembly;

the stacked satellite launching structure comprises a pressing state and a bouncing-off state;

when the upper layer assembly, the rubber pad (3) and the lower layer assembly are tightly attached to each other in a compressed state, and the rubber pad (3) is compressed and deformed by being squeezed by the upper layer assembly and the lower layer assembly and has resilience force;

when the elastic separation type rubber mat is in an elastic separation state, the rubber mat (3) enables the upper-layer assembly and the lower-layer assembly to be mutually bounced apart due to the resilience force, so that the upper-layer assembly and the lower-layer assembly are separated.

2. The stacked satellite launching structure according to claim 1, characterised in that the upper and lower assemblies each comprise a satellite bottom structure plate (1), a satellite solar array structure (2) and a spacer assembly (4), and the upper and lower assemblies are structurally identical;

the bottom of satellite bottom structural slab (1) is provided with deployment mechanism, deployment mechanism with the bottom surface of satellite bottom structural slab (1) is parallel, satellite solar array structure (2) are installed the bottom of satellite bottom structural slab (1), and can under deployment mechanism's effect, expand in the external portion of celestial body.

The clapboard component (4) is arranged on the satellite bottom structural plate (1), and the rubber pad (3) is arranged on the clapboard component (4); the partition plate assembly (4) is perpendicular to the satellite bottom structural plate (1).

3. Stacked satellite launch structure according to claim 2, characterized in that said baffle assembly (4) comprises a plurality of baffles of equal height, equal thickness and unequal length; the plurality of spacers form an array structure.

4. Stacked satellite launch structure according to claim 2, characterized in that it further comprises a pre-buried mounting bracket (5),

the rubber pad (3) is installed on the partition plate assembly (4) through the embedded installation support (5).

5. Stacked satellite launch structure according to claim 1, characterized in that said rubber mat (3) satisfies the following requirements:

the stress relaxation rate of the compression ratio of 40% is less than 25%, and the resilience force is more than 15 kPa.

6. Stacked satellite launch structure according to claim 1, characterized in that the number of said upper assembly, said lower assembly and rubber pads (3) is multiple.

The upper-layer assembly and the lower-layer assembly are alternately arranged along the height direction of the upper-layer assembly, and the rubber pad (3) is positioned between the upper-layer assembly and the lower-layer assembly.

7. Stacked satellite launch structure according to claim 1, characterized in that the satellite bottom structural plate (1) is an aluminium alloy honeycomb plate.

8. Stacked satellite launch structure according to claim 2, characterized in that the rubber mat (3) is glued or connected by means of a connection with the bulkhead assembly (4).

9. The stacked satellite launch structure of claim 1 wherein the upper assembly and lower assembly are compressed together by the compression structure when the stacked satellite launch structure is in the compressed state.

10. Stacked satellite launch structure according to claim 1, characterised in that said rubber pad (3) is made of silicone rubber material.

Technical Field

The invention relates to a stacked satellite structure, in particular to a stacked satellite launching structure, and particularly relates to a pressing, vibration isolating and buffering design for stacked satellite launching.

Background

The low-orbit communication satellite has the advantages of low time delay and high dynamic property due to the characteristic of low orbit, and countries strive to put forward an internet constellation plan to seize the development opportunity of a space network. However, the launching cost of the satellite is high, and the maximum utilization of the payload of the launch vehicle is one of the effective methods for reducing the launching cost, so that the design method of a stacked satellite group structure for launching multiple satellites at a time is increasingly important.

Compared with the traditional single satellite structure, the stacked satellite group structure has the advantages of large weight, low rigidity and poor structural integrity, so how to improve the integral rigidity of the stacked satellite group structure, reduce the vibration response of the stacked satellite group structure and realize the smooth separation of the stacked satellite group structure into key technologies which need to be solved urgently at present.

Patent document CN205533992U discloses a spring cushion rubber pad for an automobile shock absorber, which is installed between a shock absorber spring and a spring tray, and comprises a rubber pad body, wherein the upper surface of the rubber pad body is a spring assembling surface matched with the shock absorber spring, the lower surface of the rubber pad body is a spring tray attaching surface matched with the spring tray, and the edge of the rubber pad body is provided with a first spring limit stop; one side of the first spring limit stop block, which is close to the lower surface of the rubber pad body, is provided with a sound insulation groove. The utility model discloses a small produces when avoiding using and pat the noise, avoids sliding.

Patent document CN201827280U discloses a cushion rubber pad, which comprises a top plate and a base, wherein the top plate and the base are made of cast steel; a molded rubber body is filled between the top disc and the base, the rubber body is provided with a vertical semi-cylinder which is vertical to the direction of the base and is concave inwards, a horizontal semi-cylinder which is parallel to the direction of the base and is concave inwards and intersected with the vertical cylinder, the vertical semi-cylinder and the horizontal semi-cylinder which are intersected in a cross shape are distributed at two symmetrical sides of the rubber body, and the other two sides of the rubber body are smooth rubber surfaces; the top disc is provided with a counter bore, a hexagon nut is arranged in the counter bore and used for fixing the cushion rubber pad under heavy equipment, and the base is provided with a pair of through holes which are symmetrically distributed relative to the cushion rubber pad. The rubber body is filled between the top disc and the base, so that the vibration and collision of heavy equipment are well buffered, the structure is simple, the production and maintenance cost is low, and the implementation is easy.

Patent document CN203188110U discloses a vibration isolation rubber pad for a bridge, which is used for solving the problem of poor vibration isolation effect of the existing vibration isolation rubber pad. It comprises a rubber block with a plurality of hollow chambers inside but not on the surface. A plurality of hollow chambers are distributed in an array mode inside the rubber block, a peripheral stop block contact surface and a bridge girder contact surface are arranged on the rubber block, the peripheral stop block contact surface is a plane, and the bridge girder contact surface is a convex arc-shaped surface. The utility model discloses a rubber cushion's middle part align to grid a plurality of independence, the same or different hollow chamber of size, these a plurality of independent cavitys help reducing the transmission and the impact of vibrations at the during operation, and the distributed distribution of a plurality of cavitys, can disperse external impact force like this, can not take place stress concentration phenomenon.

However, due to the special use environment of the satellite, the prior art is not suitable for the stacked satellite structure, and cannot meet the requirements of the stacked satellite in various aspects such as compression, bouncing and the like.

Among other things, patent document CN107889482B discloses a stackable satellite comprising a satellite frame and at least one vertical pillar attached to said frame. The vertical strut has an upper end and a lower end. The upper end is coupled to the lower end of the vertical column of the satellite above and the lower end is coupled to the upper end of the vertical column of the satellite below. The scheme reduces the mass of the satellite, but still does not solve the problems of reducing the vibration response of the stacked satellite structure and helping to realize the smooth separation of the stacked satellite constellation structure.

Disclosure of Invention

In view of the deficiencies in the prior art, it is an object of the present invention to provide a stacked satellite launch architecture.

The invention provides a stacked satellite launching structure, which comprises an upper layer assembly, a rubber pad and a lower layer assembly; the upper layer assembly is detachably connected with the lower layer assembly; the rubber pad is positioned between the upper layer assembly and the lower layer assembly and is arranged at the top of the lower layer assembly;

the stacked satellite launching structure comprises a pressing state and a bouncing-off state;

when the rubber cushion is in a compressed state, the upper layer assembly, the rubber cushion and the lower layer assembly are tightly attached, and the rubber cushion is compressed and deformed due to the extrusion of the upper layer assembly and the lower layer assembly and has resilience force;

when the elastic separation type rubber mat is in an elastic separation state, the upper layer assembly and the lower layer assembly are mutually bounced apart by the elastic force of the rubber mat, so that the upper layer assembly is separated from the lower layer assembly.

Preferably, the upper layer assembly and the lower layer assembly both comprise a satellite bottom structural plate, a satellite solar array structure and a partition plate assembly, and the upper layer assembly and the lower layer assembly are identical in structure;

the bottom of satellite bottom structural slab is provided with deployment mechanism, deployment mechanism with the bottom surface of satellite bottom structural slab is parallel, satellite solar array structure installs the bottom of satellite bottom structural slab, and can be in under deployment mechanism's the effect, expand in the external portion of star.

The partition plate assembly is arranged on the satellite bottom structural plate, and the rubber pad is arranged on the partition plate assembly; the baffle plate assembly is perpendicular to the satellite bottom structural plate.

Preferably, the baffle plate assembly comprises a plurality of baffle plates with equal height, equal thickness and unequal length; the plurality of spacers form an array structure.

Preferably, the stacked satellite launching structure further comprises a pre-buried mounting bracket,

the rubber pad is installed on the partition plate assembly through the embedded installation support.

Preferably, the rubber mat meets the following requirements:

the stress relaxation rate of the compression ratio of 40% is less than 25%, and the resilience force is more than 15 kPa.

Preferably, the number of the upper layer assembly, the lower layer assembly and the rubber pad is multiple.

The upper layer assembly and the lower layer assembly are alternately arranged along the height direction of the upper layer assembly, and the rubber pad is positioned between the upper layer assembly and the lower layer assembly.

Preferably, the satellite bottom structural plate is an aluminum alloy honeycomb plate.

Preferably, the rubber pad is bonded to the diaphragm assembly or connected thereto by a connector.

Preferably, when the stacked satellite launching structure is in a compressed state, the upper layer assembly and the lower layer assembly are compressed together through the compression structure.

Preferably, the rubber pad is made of a silicone rubber material.

Compared with the prior art, the invention has the following beneficial effects:

1. the invention is provided with a rubber pad structure, and the adopted rubber pad has the characteristics of softness and high elasticity, so that the rubber pad can reduce the damage caused by collision of an upper-layer assembly and a lower-layer assembly in the process of launching and separating a satellite.

2. The solar array structure is provided with the rubber pad structure, the rubber pad is made of rubber materials with larger resilience force and smaller stress relaxation rate, so that the stress loss of the rubber pad is smaller in the compression state, the solar array structure of the upper-layer assembly can be tightly compressed on the bottom surface of the satellite bottom structural plate of the upper-layer assembly in the compression state, and the rubber pad has enough resilience force to separate the upper-layer assembly from the lower-layer assembly in the bouncing-off state.

3. The stacked satellite structure is provided with the rubber pad structure, and the rubber pad with high damping characteristic is adopted, so that the rubber pad can achieve the effect of vibration reduction through deformation energy consumption, the effect of reducing the vibration amplitude of the upper layer assembly and the lower layer assembly can be achieved, and the overall rigidity of the stacked satellite structure can be improved.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic structural diagram of an upper assembly of the present invention;

FIG. 3 is a bottom view of the upper assembly of the present invention;

FIG. 4 is a schematic view of the rubber pad of the present invention;

fig. 5 is a schematic structural view of a preferred example of the present invention, in which the number of the upper layer assembly, the lower layer assembly and the rubber pads are 2.

The figures show that:

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The invention provides a stacked satellite launching structure, which comprises an upper layer assembly, a rubber pad 3 and a lower layer assembly; the upper layer assembly is detachably connected with the lower layer assembly; the rubber pad 3 is positioned between the upper layer assembly and the lower layer assembly and is arranged at the top of the lower layer assembly; the stacked satellite launching structure comprises a pressing state and a bouncing-off state;

when being in the state of compressing tightly, upper assembly, rubber pad 3, lower floor's subassembly are closely laminated, rubber pad 3 is owing to be extruded by upper assembly and lower floor's subassembly, produces compression deformation, consequently has the resilience force. When the stacked satellite launching structure is in a compressed state, the upper layer assembly and the lower layer assembly are compressed together through the compression structure. The compressing structure is used for applying pretightening force to the upper layer assembly and the lower layer assembly to enable the upper layer assembly and the lower layer assembly to be tightly pressed together.

When in the state of bouncing off, the rubber pad 3 bounces the upper assembly and the lower assembly away from each other due to the resilience force, so that the upper assembly and the lower assembly are separated.

The upper layer assembly and the lower layer assembly respectively comprise a satellite bottom structural plate 1, a satellite solar array structure 2 and a partition plate assembly 4, and the upper layer assembly and the lower layer assembly are identical in structure; as shown in fig. 1, in a preferred embodiment, the satellite bottom structural plate 1 is an aluminum alloy honeycomb plate, the outer contour of the satellite bottom structural plate 1 is in a convex shape, the size of the circumscribed rectangle is 3200mm × 1600mm, the thickness is 15mm, and the outer contour of the solar array structure 2 is 2800mm × 800mm, and the thickness is 30 mm.

As shown in fig. 3, a spreading mechanism (not shown) is disposed at the bottom of the satellite bottom structural plate 1, the spreading mechanism is parallel to the bottom of the satellite bottom structural plate 1, and the satellite solar array structure 2 is mounted at the bottom of the satellite bottom structural plate 1 and can be spread outside the satellite body under the action of the spreading mechanism. In a preferred example, the unfolding mechanism is a rotating shaft along which the satellite solar array structure 2 can rotate so as to unfold outside the star.

As shown in fig. 2, the partition plate assembly 4 is mounted on the satellite bottom structural plate 1, and the rubber pad 3 is mounted on the partition plate assembly 4; the partition plate assembly 4 is perpendicular to the satellite bottom structural plate 1; in a preferred embodiment, the rubber gasket 3 and the partition plate assembly 4 can be connected by means of matching of holes and embedded parts, as shown in fig. 1 and 2, the stacked satellite launching structure further includes an embedded mounting bracket 5, and the rubber gasket 3 is mounted on the partition plate assembly 4 through the embedded mounting bracket 5 to prevent the rubber gasket 3 from falling off or slipping. In another preferred embodiment, the rubber pad 3 is adhered to the partition plate assembly 4 or connected thereto by a connecting member, which is a bolt.

When the stacked satellite launching structure is in a compressed state, the satellite solar array structure 2 in the upper assembly is compressed on the bottom surface of the satellite bottom structural plate 1 in the upper assembly under the resilience force from the rubber pad 3, and at the moment, the satellite solar array structure 2 in the upper assembly cannot rotate or translate along the unfolding mechanism.

When the stacked satellite launching structure is in a bouncing-off state, the upper-layer assembly and the lower-layer assembly are mutually bounced apart by the resilience force of the rubber pad 3, so that the upper-layer assembly is separated from the lower-layer assembly, and the satellite solar array structure 2 in the upper-layer assembly can be unfolded outside a satellite under the action of the unfolding mechanism.

The rubber pad 3 has high damping characteristic, and can achieve the effect of vibration reduction through deformation energy consumption, so that the amplitude of vibration of the upper layer assembly and the lower layer assembly can be reduced in the compressed state, and the overall rigidity of the stacked satellite launching structure can be improved. Rubber pad 3 adopts the great and less rubber materials of stress relaxation rate of resilience force, guarantees that under the compression state, 3 stress losses of rubber pad are less to this solar array structure 2 of guaranteeing upper assembly under the compression state can be inseparable compress tightly on the satellite bottom structural slab 1 of upper assembly, and in the state of bounceing rubber pad 3 has sufficient resilience force to make upper assembly and lower floor's subassembly separate. Rubber pad 3 has soft, the big characteristics of elasticity, and in satellite transmission and separation process, rubber pad 3 can alleviate the harm that upper assembly and lower floor's subassembly collision caused.

The partition plate assembly 4 comprises a plurality of partition plates with equal height, equal thickness and unequal length, as shown in fig. 2, in a preferred embodiment, the partition plate assembly 4 comprises 40 aluminum alloy honeycomb plates which are perpendicular to a bottom plate, have the height of 273mm, the length of 126 mm-1525 mm, and the thickness of 10mm, and the plurality of partition plates form an array structure. As shown in fig. 4, the outer contour of the rubber pad 3 is designed according to the arrangement mode of the partition plate assembly 4, so that the rubber pad 3 can be fixed on the partition plate of the lower-layer satellite. In a preferred embodiment, the rubber pad 3 is made of a silicone rubber material, the thickness of the rubber pad 3 is 20mm, the width of each strip is 60mm, the designed compression thickness is 8mm, namely the use thickness after compression is 12mm, and the rubber material meets the index that the stress relaxation rate is less than 25% and the resilience is greater than 15kPa when the compression rate is 40% so as to meet the requirement of the pressing force of the upper satellite solar array structure 2.

In a preferred example, the number of the upper layer assembly, the lower layer assembly and the rubber pads 3 is multiple, the lower layer assembly and the upper layer assembly are alternately arranged along the height direction of the upper layer assembly, and the rubber pads 3 are positioned between the upper layer assembly and the lower layer assembly.

In another preferred example, as shown in fig. 5, the number of the upper layer assembly, the lower layer assembly and the rubber pads 3 is 2, and the number is respectively the first upper layer assembly, the second upper layer assembly, the first lower layer assembly, the second lower layer assembly, the first rubber pad and the second rubber pad; the first upper layer assembly is detachably connected with the first lower layer assembly; the first rubber pad is positioned between the first upper layer assembly and the first lower layer assembly; the second upper layer assembly is detachably connected with the second lower layer assembly; the second rubber pad is positioned between the second upper layer assembly and the second lower layer assembly; the first upper-layer assembly is connected with the second upper-layer assembly in a matched mode, and the first lower-layer assembly is connected with the second lower-layer assembly in a matched mode.

According to the invention, the integrity of the stacked satellite structure is improved in a mode of the satellite bottom structural plate 1, the satellite solar array structure 2, the rubber pad 3 and the partition plate assembly 4, and a proper force transmission path is established. The rubber pad 3 and the related structure thereof are used for improving the overall rigidity of the stacked satellite group, the requirements of compaction, vibration isolation and buffering of the stacked satellite group in the launching stage are met, the requirement of interlayer separation in the separation stage of the stacked satellite group is met, and a reliable structural design scheme is provided for successful launching and separation of the stacked satellite.

According to the preferred embodiment of the invention, not only can the energy consumption and vibration reduction effects be realized in the vibration process of the satellite group by means of the high damping characteristic of the rubber pad, but also the compression effect can be realized on the satellite solar array structure 2 in the upper layer assembly when the stacked satellite launching structure is in the compression state, and the resilience force can be provided in the bouncing-off process of the stacked satellite launching structure, so that the relative displacement is generated between the upper layer assembly and the lower layer assembly, and the separation is realized. And the satellite can collide in the launching and separating process, and the rubber pad structure can reduce the damage caused by collision.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.