阅读说明：本技术 一种宽温域高刚度静定式压紧系统 (Wide-temperature-range high-rigidity statically determinate type pressing system ) 是由 刘卫 鄢青青 刘学 满剑锋 齐跃 姜生元 马超 于 2021-09-13 设计创作，主要内容包括：本发明涉及航天器技术领域,公开了一种宽温域高刚度静定式压紧系统,用于对航天器本体上的被压紧机构进行压紧,包括固定压紧装置、至少两个并位于固定压紧装置两侧的浮动压紧装置,所述浮动压紧装置用于限制被压紧机构的两个平动自由度和三个转动自由度,并调整被压紧机构热变形方向的伸缩；所述固定压紧装置用于限制全部六个自由度；所述浮动压紧装置包括滑槽支架、设置在所述滑槽支架上的固连法兰和第一压紧组件,所述固定压紧装置包括固连支架、设置在固连支架上的第二压紧组件,所述固连法兰和固连支架分别安装在被压紧机构上,第一压紧组件和第二压紧组件两者安装在航天器本体上。本发明具有高刚度、高基频的特点,对高低温环境适应能力强。(The invention relates to the technical field of spacecrafts, and discloses a statically determinate pressing system with wide temperature range and high rigidity, which is used for pressing a pressed mechanism on a spacecraft body and comprises a fixed pressing device and at least two floating pressing devices which are positioned at two sides of the fixed pressing device, wherein the floating pressing devices are used for limiting two translational degrees of freedom and three rotational degrees of freedom of the pressed mechanism and adjusting the stretching of the heat deformation direction of the pressed mechanism; the fixed pressing device is used for limiting all six degrees of freedom; the floating pressing device comprises a chute support, a fixedly connected flange and a first pressing assembly, the fixedly connected flange and the first pressing assembly are arranged on the chute support, the fixed pressing device comprises a fixedly connected support and a second pressing assembly, the second pressing assembly is arranged on the fixedly connected support, the fixedly connected flange and the fixedly connected support are respectively arranged on a pressed mechanism, and the first pressing assembly and the second pressing assembly are both arranged on the spacecraft body. The invention has the characteristics of high rigidity and high fundamental frequency, and has strong adaptability to high and low temperature environments.)

1. The utility model provides a wide temperature domain high rigidity statically determinate formula system that compresses tightly for being compressed tightly its characterized in that by hold-down mechanism on to the spacecraft body: the device comprises a fixed pressing device and at least two floating pressing devices which are positioned at two sides of the fixed pressing device, wherein the floating pressing devices are used for limiting two translational degrees of freedom and three rotational degrees of freedom of a pressed mechanism and adjusting the expansion of the pressed mechanism in the thermal deformation direction; the fixed pressing device is used for limiting all six degrees of freedom of the pressed mechanism;

the floating pressing device comprises a chute support, a fixedly connected flange and a first pressing assembly, the fixedly connected flange and the first pressing assembly are arranged on the chute support, the fixedly connected device comprises a fixedly connected support and a second pressing assembly, the second pressing assembly is arranged on the fixedly connected support, the fixedly connected flange and the fixedly connected support are respectively arranged on a pressed mechanism, and the first pressing assembly and the second pressing assembly are both arranged on the spacecraft body.

2. The wide temperature range, high stiffness statically determinate compaction system of claim 1, wherein: the first pressing assembly and the second pressing assembly both comprise pressing supports, pressing rods, cutters, cover plates and cover plate supports, the pressing supports are mounted on the spacecraft body, and the middle parts of the pressing rods are arranged on the corresponding chute supports and the corresponding fixed connection supports; one end of the pressing rod is provided with a cutter and is arranged on the pressing support, and the other end of the pressing rod is provided with a cover plate; the cover plate is further arranged on the cover plate support, and the cover plate support are in running fit.

3. The wide temperature range, high stiffness statically determinate compaction system of claim 2, wherein: the fixedly connected flange comprises a connecting plate and double lug plates arranged on the connecting plate; the sliding groove support comprises a first support and a second support which are vertically arranged, and an installation convex portion located on the side face of the first support, a sliding groove in sliding fit with the double lug pieces is arranged at the end portion of the second support, and an installation through hole for installing the pressing rod is formed in the installation convex portion.

4. The wide temperature range, high stiffness statically determinate compaction system of claim 2, wherein: the first compressing assembly and the second compressing assembly further comprise pre-tightening nuts, and the two end parts of the compressing rod are respectively provided with the pre-tightening nuts.

5. The wide temperature range, high stiffness statically determinate compaction system of claim 4, wherein: the first compressing assembly and the second compressing assembly further comprise escape-proof caps which are arranged on the cover plate and located on the outer surface of the pre-tightening nut.

6. The wide temperature range, high stiffness statically determinate compaction system of claim 2, wherein: the first pressing assembly and the second pressing assembly further comprise torsion springs connected with the cover plate and the cover plate support.

7. The wide temperature range, high stiffness statically determinate compaction system of claim 2, wherein: the cover plate comprises a connecting part and a bent part which are connected with each other, the connecting part is arranged on the corresponding sliding groove support and the fixed connection support, and the end part of the bent part is hinged on the cover plate support.

8. The wide temperature range, high stiffness statically determinate compaction system of claim 3, wherein: and a sliding surface between the sliding groove support and the fixed connection flange is coated with a lubricating coating.

Technical Field

The invention relates to the technical field of spacecrafts, in particular to a statically determinate type pressing system with wide temperature range and high rigidity.

Background

In the process from launching to orbit, the spacecraft mechanism is limited by the carrying envelope size of the rocket, and the modes of folding and compressing firstly, and unfolding and releasing after orbit entering are generally adopted. In order to ensure that the mechanism is reliably compressed to bear the severe vibration condition of the rocket launching section, the mechanism product needs to be installed on a spacecraft structural plate, and the mechanism is connected with the structural plate through a compressing device. In addition, the mechanism compression state needs to have enough compression rigidity so as to avoid the coupling of the fundamental frequency of the mechanism compression state with the whole device, and further cause the damage of the mechanism due to overlarge vibration response. Therefore, for a large-size mechanism, the pressing is often required to be performed at a plurality of positions, namely, the number of pressing devices is increased, a statically indeterminate pressing system is formed, and the whole pressing system becomes a geometric invariant structure system with redundant constraint, so that the pressing rigidity is improved as much as possible.

Because the thermal expansion coefficient of the mechanism product generally has a significant difference with that of the spacecraft body structure, the spacecraft can generate thermal stress at the position of the pressing device under the influence of the temperature environment of space high-low temperature alternation in the in-orbit flying process, the more the number of the pressing devices is, the more the redundant constraint is, the more difficult the release of the thermal stress of the hyperstatic pressing system is, and the more difficult the harm of the thermal stress is to be eliminated.

With the increase of the size of the mechanism and the increase of the amplitude of the deep low temperature or high temperature alternation, the compression thermal stress is further increased. The low temperature of the first Mars detection task in China is-130 ℃, the environment of the moon south-pole detection task can be as low as-200 ℃, the high temperature can still reach 80 ℃, and the severe conditions of high temperature and low temperature in the wide temperature range form serious threats to the reliable compaction of large-size mechanisms and even cause thermal stress damage, thereby causing the mechanism functions to be incapable of being realized smoothly and causing irrecoverable loss to the whole system detection task.

Disclosure of Invention

The invention aims to solve the technical problems in the prior art, and provides a statically determinate compression system with wide temperature range and high rigidity, which has simple integral structure and reliable function, realizes high-rigidity compression, can release thermal stress and has strong adaptability to high and low temperature alternating environments.

In order to solve the problems proposed above, the technical scheme adopted by the invention is as follows:

the invention provides a statically determinate pressing system with wide temperature range and high rigidity, which is used for pressing a pressed mechanism on a spacecraft body and comprises a fixed pressing device and at least two floating pressing devices which are positioned at two sides of the fixed pressing device, wherein the floating pressing devices are used for limiting two translational degrees of freedom and three rotational degrees of freedom of the pressed mechanism and adjusting the expansion of the thermal deformation direction of the pressed mechanism; the fixed pressing device is used for limiting all six degrees of freedom of the pressed mechanism;

the floating pressing device comprises a chute support, a fixedly connected flange and a first pressing assembly, the fixedly connected flange and the first pressing assembly are arranged on the chute support, the fixedly connected device comprises a fixedly connected support and a second pressing assembly, the second pressing assembly is arranged on the fixedly connected support, the fixedly connected flange and the fixedly connected support are respectively arranged on a pressed mechanism, and the first pressing assembly and the second pressing assembly are both arranged on the spacecraft body.

Furthermore, the first pressing assembly and the second pressing assembly both comprise pressing supports, pressing rods, cutters, cover plates and cover plate supports, the pressing supports are mounted on the spacecraft body, and the middle parts of the pressing rods are arranged on the corresponding chute supports and the corresponding fixed connection supports; one end of the pressing rod is provided with a cutter and is arranged on the pressing support, and the other end of the pressing rod is provided with a cover plate; the cover plate is further arranged on the cover plate support, and the cover plate support are in running fit.

Further, the fixedly connected flange comprises a connecting plate and double lug plates arranged on the connecting plate; the sliding groove support comprises a first support and a second support which are vertically arranged, and an installation convex portion located on the side face of the first support, a sliding groove in sliding fit with the double lug pieces is arranged at the end portion of the second support, and an installation through hole for installing the pressing rod is formed in the installation convex portion.

Furthermore, the first compressing assembly and the second compressing assembly further comprise pre-tightening nuts, and the two end parts of the compressing rod are respectively provided with the pre-tightening nuts.

Furthermore, the first compression assembly and the second compression assembly further comprise escape-proof caps which are arranged on the cover plate and located on the outer surface of the pre-tightening nut.

Furthermore, the first pressing assembly and the second pressing assembly further comprise torsion springs which are connected with the cover plate and the cover plate bracket.

Further, the apron includes interconnect's connecting portion and flexion, connecting portion set up at the spout support that corresponds and link firmly on the support, the tip of flexion articulates on the apron support.

Furthermore, a sliding surface between the sliding groove support and the fixedly connecting flange is coated with a lubricating coating.

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

the static fixed structure is formed by the floating pressing devices and the fixed pressing devices, namely the unidirectional floating pressing devices are adopted to release thermal stress, the high-rigidity pressing effect is achieved through the coupling action of the floating pressing devices and the fixed pressing devices, no redundant constraint exists in the thermal deformation direction, the thermal stress is completely eliminated, the problem of thermal stress damage of a large-size mechanism in a pressing state caused by a high-temperature environment and a low-temperature environment is solved, the overall structure is simple, the function is reliable, the high-rigidity pressing is realized, the thermal stress can be released, and the adaptability to high-temperature and low-temperature alternating environments is strong.

Drawings

In order to illustrate the solution of the invention more clearly, the drawings that are needed in the description of the embodiments will be briefly described below, it being obvious that the drawings in the following description are some embodiments of the invention, and that other drawings may be derived from these drawings by a person skilled in the art without inventive effort. Wherein:

fig. 1 is a schematic structural diagram of a wide-temperature-range high-rigidity statically determinate compaction system.

Fig. 2 is a schematic structural diagram of the floating pressing device of the present invention.

Fig. 3 is a schematic structural view of the fixing and compressing device of the present invention.

Fig. 4 is a front view of the floating press device of the present invention.

Fig. 5 is a front view of the stationary compaction apparatus of the invention.

Fig. 6 is a schematic structural view of the chute holder of the present invention.

Fig. 7 is a schematic structural view of the fastening flange of the present invention.

Fig. 8 is a diagram of an embodiment of a wide temperature range high stiffness statically determinate compression system of the present invention.

Fig. 9 is a diagram of another embodiment of a wide temperature range, high stiffness statically determinate compression system of the present invention.

The reference numerals are explained below: 1-pressing support, 2-pressing rod, 3-pre-tightening nut, 4-cutter, 5-escape-proof cap, 6-cover plate, 7-cover plate bracket, 8-torsion spring, 10-pressed mechanism, 20-spacecraft body, 100-floating pressing device, 200-fixed pressing device, 101-fixed flange, 102-chute bracket, 201-fixed bracket, 11-first bracket, 12-second bracket, 13-installation convex part, 121-chute, 131-installation through hole, 21-installation plate, 22-bracket, 30-connecting rod, 61-connecting part and 62-bending part.

Detailed Description

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs; the terminology used in the description presented herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention, e.g., the terms "length," "width," "upper," "lower," "left," "right," "front," "rear," "vertical," "horizontal," "top," "bottom," "inner," "outer," etc., refer to an orientation or position based on that shown in the drawings, are for convenience of description only and are not to be construed as limiting of the present disclosure.

The terms "including" and "having," and any variations thereof, in the description and claims of this invention and the description of the above figures are intended to cover non-exclusive inclusions; the terms "first," "second," and the like in the description and in the claims, or in the drawings, are used for distinguishing between different objects and not necessarily for describing a particular sequential order. In the description and claims of the present invention and in the description of the above figures, when an element is referred to as being "fixed" or "mounted" or "disposed" or "connected" to another element, it may be directly or indirectly located on the other element. For example, when an element is referred to as being "connected to" another element, it can be directly or indirectly connected to the other element.

Furthermore, reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the invention. The appearances of the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is explicitly and implicitly understood by one skilled in the art that the embodiments described herein can be combined with other embodiments.

Referring to fig. 1, the invention provides a statically determinate pressing system with wide temperature range and high rigidity, which is used for pressing a pressed mechanism 10 on a spacecraft body 20, and comprises at least two floating pressing devices 100 and a fixed pressing device 200, wherein the two floating pressing devices 100 are located at two sides of the fixed pressing device 200.

The floating pressing devices 100 and the fixed pressing device 200 form a static pressing system, two translational freedom degrees and three rotational freedom degrees of the pressed mechanism 10 can be limited through the floating pressing devices 100, the stretching of the pressed mechanism 10 in the thermal deformation direction is not limited, and the stretching of the pressed mechanism 10 in the thermal deformation direction is adjusted; the fixed pressing device 200 is limited by the 6 degrees of freedom of the pressing mechanism 10, so that the pressed mechanism 10 can be reliably pressed and the thermal stress can be released.

As shown in fig. 2 to 5, the floating pressing device 100 includes a chute support 102, a fastening flange 101 disposed on the chute support 102, and a first pressing assembly; the fixed pressing device 200 comprises a fixed connecting support 201 and a second pressing assembly arranged on the fixed connecting support 201. The fixed connection flange 101 and the fixed connection bracket 201 are respectively installed on the pressed mechanism 10, and the first pressing assembly and the second pressing assembly are installed on the spacecraft body 20.

The first pressing assembly and the second pressing assembly are identical in structure and comprise pressing supports 1, pressing rods 2, cutters 4, cover plates 6 and cover plate supports 7, the pressing supports 1 are mounted on the spacecraft body 20, and the middle portions of the pressing rods 2 are arranged on the corresponding chute supports 102 and the corresponding fixedly connecting supports 201. One end of the compressing rod 2 is provided with a cutter 4 and is arranged on the compressing support 1, and the other end is provided with a cover plate 6. The cover plate 6 is also arranged on the cover plate bracket 7, and the cover plate bracket are in running fit. Specifically, since the floating pressing device 100 and the fixed pressing device 200 are respectively provided with a first pressing component and a second pressing component which have the same structure, the pressing rods 2 corresponding to the two groups of pressing components are respectively arranged on the corresponding chute support 102 and the fixed connection support 201.

As shown in fig. 6, the fastening flange 101 includes a connecting plate 111, and a double tab 112 disposed on the connecting plate 111, and is mounted on the pressed mechanism 10 through the connecting plate 111 for providing an external pressing interface, and is slidably engaged with the chute holder 102 through the double tab 112.

As shown in fig. 7, the chute holder 102 includes a first holder 11 and a second holder 12 that are vertically disposed, and an installation protrusion 13 located on a side surface of the first holder 11, wherein a chute 121 slidably engaged with the double tab 112 is disposed at an end of the second holder 12, and an installation through hole 131 for installing the pressing rod 2 is disposed on the installation protrusion 13. Specifically, the chute 121 is a C-shaped opening chute, which is convenient to install and connect, and the shape of the chute can be adjusted according to actual needs.

The sliding groove bracket 102 is inserted into the two lug pieces 112 of the fastening flange 101 through the sliding groove 121, and is in clearance fit with the fastening flange 101, and the fastening flange 101 and the sliding groove bracket 102 can slide relatively, but are limited by the remaining 2 translational degrees and 3 rotational degrees of freedom of the pressing mechanism 10, which are all limited by the sliding groove bracket 102. A first pressing assembly is arranged on the mounting convex part 13 of the chute support 102 and is used for pressing the pressed mechanism 10 on the spacecraft body 20.

Further, the sliding surface between the chute holder 102 and the fastening flange 101 is coated with a lubricating coating for reducing frictional resistance and preventing a vacuum cold welding phenomenon. In particular, the lubricating coating adopts a dry film lubricating coating, and other coatings capable of realizing lubrication can also be adopted.

Further, as shown in fig. 5, the fixing bracket 201 is an L-shaped structure, and includes a mounting plate 21 and a bracket 22 that are vertically disposed, the mounting plate 21 is fixedly connected to the pressed mechanism 10, and the end of the bracket 22 is provided with the second pressing assembly. Specifically, the end of the bracket 22 is also provided with a mounting portion, and the mounting portion is also provided with a mounting hole for mounting the compression rod 2.

Further, as shown in fig. 4 and fig. 5, both the first compressing assembly and the second compressing assembly further include a pre-tightening nut 3 and an anti-escape cap 5, and the two end portions of the compressing rod 2 are respectively provided with the pre-tightening nuts 3 for locking and fixing the compressing rod 2 on the compressing support 1. The outer surface of the pre-tightening nut 3 is provided with an escape-proof cap 5, and the escape-proof cap 5 is positioned on the cover plate 6 and used for preventing the compression rod 2 from generating uncontrolled escape movement after being cut off.

Specifically, the cover plate 6 is pressed and fixed on the corresponding chute support 102 and the fixed connection support 201 by the pre-tightening nut 3 at one end of the pressing rod 2, and the pressing rod 2 is fixed on the pressing support 1 by the pre-tightening nut 3 at the other end. The cutter 4 is located between the corresponding chute support 102 and the pressing support 1 or the fastening support 201 and the pressing support 1.

Further, the first pressing assembly and the second pressing assembly both further comprise a torsion spring 8 for connecting the cover plate 6 and the cover plate bracket 7, and when the pressing rod 2 is cut off, the cover plate 6 is driven to rotate by the torsion spring 8.

Further, the cover plate 6 comprises a connecting portion 61 and a bending portion 62 which are connected with each other, the connecting portion 61 is arranged on the corresponding chute support 102 and the corresponding fixed connection support 201 and is compressed and fixed through the pretightening nut 3, and the end portion of the bending portion 62 is hinged on the cover plate support 7 to realize rotating fit. Specifically, the bending angle of the bending portion 62 can be adjusted according to actual needs, so that the installation and connection are convenient, and the whole structure is compact.

In the floating pressing device 100 of the present embodiment, the pressing rod 2 sequentially passes through the cover plate 6, the mounting protrusion 13 of the chute bracket 102, the central hole of the cutter 4, and the pressing support 1 from top to bottom. Pretension load is applied to two end parts of the pressing rod 2 through the pretension nut 3, so that the chute support 102 is tightly pressed on the pressing support 1, the fixedly connected flange 101 is unidirectionally floated and pressed through the chute support 102, the fixedly connected flange 101 can only produce unidirectional displacement along the chute 121, and other degrees of freedom are all pressed and limited. When the unlocking is needed, the cutter 4 cuts off the compression rod 2, the cover plate 6 is driven to rotate through the torsion spring 8, the cut compression rod 2 is taken away through the rotation of the cover plate 6, and meanwhile, the connection between the chute bracket 102 and the compression support 1 is released.

In the fixing and compressing device 200 of the embodiment, the compressing rod 2 penetrates through the cover plate 6, the mounting part of the fixed connecting bracket 201, the central hole of the cutter 4 and the compressing support 1 from top to bottom respectively. And a pre-tightening load is applied to the pressing rod 2 through the pre-tightening nut 3, so that the fixedly-connected bracket 201 is tightly pressed on the pressing support 1, and the degrees of freedom of the pressed mechanism 10 are tightly limited. When the unlocking is needed, the pressing rod 2 is cut off through the cutter 4, the torsion spring 8 drives the cover plate 6 to rotate, the cut-off pressing rod 2 is taken away through the rotation of the cover plate 6, and meanwhile, the connection between the fixedly-connected support 201 and the pressing support 1 is released.

With continued reference to fig. 1, in the present embodiment, a fixed pressing device 200 is disposed at the middle position of the pressed mechanism 10, and two floating pressing devices 100 are symmetrically disposed at the two ends of the pressed mechanism 10.

In the above, one fixed pressing device 200 and the symmetrically arranged floating pressing devices 100 constitute a statically fixed pressing system which allows thermal deformation. The pre-tightening force in the thermal deformation direction of the pressed mechanism 10 is completely provided by the fixed pressing device 200, i.e. no extra constraint exists in the thermal deformation direction. In the case of temperature variation, since the fixed pressing device 200 constrains all degrees of freedom of the pressed mechanism 10, the thermal deformation of the pressed mechanism 10 will increase linearly towards both ends and be symmetrically distributed on the fixed pressing device 200, and the thermal stress at the position of the fixed pressing device 200 is zero. Thermal deformation of the clamped mechanism 10 is allowed by the relative sliding of the attachment flange 101 of the floating clamping device 100 and the chute support 102, so that thermal stresses are completely eliminated.

In this embodiment, the fitting length of the fastening flange 101 and the chute holder 102 can be changed according to the thermal deformation value, so that the temperature range that can be adapted to is increased, and the method can be applied to both high-temperature environments and low-temperature environments. Therefore, the statically determinate compaction system has the remarkable characteristic of strong adaptability to wide-temperature-range high-low temperature alternating environments.

Referring to fig. 8, which is a schematic view of an application example of the statically determinate pressing system of the multi-floating pressing device 100, when the pressed mechanism 10 is too long, the floating pressing device 100 can be symmetrically added between the fixed pressing device 200 and the end floating pressing device 100. The compression stiffness is further improved by increasing the number of floating compression devices 100 without causing additional thermal stress problems, thereby achieving a high stiffness compression effect under wide temperature range conditions as a whole.

As shown in fig. 9, 2 pieces of the workpiece are connected by the pressing mechanism 10 through the connecting rod 30, and are combined and applied by 2 statically determinate pressing systems, so that the pressing is reliably realized.

In this embodiment, the floating pressing device 100 is dual, i.e., even, and forms a statically determinate structure with the fixed pressing device 200, the floating pressing device 100 may be symmetrically arranged or asymmetrically arranged with respect to the fixed pressing device 200, and if symmetrical arrangement is adopted, the modal fundamental frequencies (i.e., the heights of the pressing stiffness) of the pressed mechanisms 10 at the two sides of the fixed pressing device 200 are the same and can be simultaneously increased; if an asymmetric arrangement is adopted, the modal fundamental frequencies of both sides of the mechanism 10 to be pressed can be increased, but one side is high and the other side is low, so that the fundamental frequency of the whole mechanism 10 to be pressed is represented as the fundamental frequency of the lower side. Therefore, in the present embodiment, the paired floating pressing devices 100 are symmetrically arranged with respect to the fixed pressing device 200, so as to improve the pressing rigidity of the pressed mechanism 10.

The statically determinate pressing system with wide temperature range and high rigidity provided by the invention has the characteristics of high rigidity and high fundamental frequency, has strong adaptability to high and low temperature environments, and is particularly suitable for pressing large-size spacecraft mechanism products.

The above embodiments are preferred embodiments of the present invention, but the present invention is not limited to the above embodiments, and any other changes, modifications, substitutions, combinations, and simplifications which do not depart from the spirit and principle of the present invention should be construed as equivalents thereof, and all such changes, modifications, substitutions, combinations, and simplifications are intended to be included in the scope of the present invention.