CN218777703U - Non-firer separating mechanism suitable for stacked satellites - Google Patents

Abstract

The utility model provides a non-explosive separation mechanism suitable for stacked satellites, wherein three or four clamp rings are arranged on each satellite, the clamp rings on adjacent satellites are longitudinally stacked, the clamp rings on the same direction form a group of clamp ring units, and the satellite group completes stacking through four groups of clamp ring units; the compression ring unit is compressed by a locking rod, the lower end of the locking rod is connected with a separation nut, and the upper end of the locking rod is connected with a compression seat through a compression screw; the lower end of the separation nut is connected with a locking seat, and the locking seat is fixed on the carrying platform; after stacking is completed, pretightening force is applied through the compression screws to compress each compression ring unit, so that the satellite group is locked. When the locking rods are separated, all the separating nuts are controlled to be unlocked and the locking rods are released simultaneously; the separation spring pushes the locking rod to fly upwards and pushes the satellites to be separated in sequence. The utility model discloses the equipment is simple and convenient, compact structure, the quality is light, space utilization is high, and the disengaging process does not have the impact, does not have gas outgoing, can carry out the ground separation experiment, and the security is high, the reliability is high.

Description

Non-firer separating mechanism suitable for stacked satellites

Technical Field

The utility model relates to a space flight technical field, in particular to technical field that heap satellite connection and separation.

Background

"one rocket multi-star" refers to launching two or more satellites to a predetermined orbit using one launch vehicle. Compared with the traditional one-rocket one-satellite launching mode, the one-rocket multi-satellite launching mode can fully utilize the carrying capacity of the rocket, greatly shorten the time of constellation networking and improve the launching efficiency, thereby fully playing the functions of the constellation.

In one-arrow-multi-satellite launching, the compression and separation technology of multiple satellites is the key technology to be solved firstly. At present, there are two kinds of layouts for one-arrow multi-satellite launching, one is a force bearing cylinder wall hanging type and the other is a stacking type. The stacked layout is that the satellite is directly connected with the satellite, and the satellite is stacked together in the axial direction, so that compared with the hanging type of the bearing cylinder wall, the weight and the volume of the central bearing cylinder are saved, the carrying efficiency is higher, and the stacked type satellite carrier is more suitable for rapid networking of a large number of satellites.

At present, a multi-satellite pressing and separating device is mainly based on an explosive separation technology, satellites are sequentially stacked in a fairing, and two layers of satellites are directly fixed through explosive bolts. When the separation is carried out, the explosion bolt needs to be detonated for many times, the impact is large, and the impact damage to the satellite can be possibly caused; moreover, the polluted gas and the redundant substances generated by the explosion of the bolts pollute the space environment and even possibly pollute sensitive devices of the satellite; in addition, such separation devices are of large mass and have a high risk of single point failure.

Disclosure of Invention

The utility model discloses mainly to the not enough of the technique that present pile up the satellite and compress tightly and separate, provide a non-firer separating mechanism suitable for pile up the satellite.

The utility model discloses the technical scheme who adopts: the utility model provides a non-firer separating mechanism suitable for pile up satellite, includes compressing tightly seat, clamp ring, check lock lever, locking seat, locking screw, separation nut, housing screw and separation spring. Three or four compression rings are arranged on each satellite, the compression rings on adjacent satellites are sequentially stacked along the longitudinal direction, the compression rings of a plurality of layers of satellites in the same direction form a group of compression ring units, and the whole satellite group is stacked through four groups of compression ring units; each group of compression ring units is compressed by two locking rods, the lower ends of the locking rods are connected with a separation nut through locking screws, and the upper ends of the locking rods are connected with the compression seat through compression screws; the lower end of the separation nut is connected with a locking seat, and the locking seat is fixed on the carrying platform; after the satellite groups are stacked, pretightening force is applied through the compression screws, so that each compression ring unit is compressed, and the satellite groups are locked;

a pre-compressed separation spring is arranged in each compression ring; when the separation is carried out, all the separation nuts are controlled to be unlocked simultaneously, and the locking rod is released; under the action of the separation spring, the locking rod can rapidly fly upwards, and meanwhile, the satellites are sequentially pushed to realize separation.

Furthermore, the upper end and the lower end of each compression ring are respectively provided with a frustum and a conical socket which are matched with each other, so that positioning can be provided for the stacking process, and transverse displacement is limited to occur between the compression rings after compression, so that the satellite can be prevented from moving in a plane in the launching process.

Furthermore, the upper end and the lower end of the clamp ring are respectively provided with a mounting edge connected with the satellite, and the whole clamp ring is seen from the side surface

And (4) shaping. After stacking, the compression ring unit can provide stable support for the satellite, and the satellite is prevented from moving up and down when encountering vibration.

Further, the bottom in the pressing ring is provided with a platform for placing the separation spring.

Furthermore, the lower end of the separation spring is fixed on the platform in the compression ring, so that the separation spring is prevented from separating from the compression ring and flying out in the separation process.

Furthermore, the separating springs arranged on different layers have different rigidity so as to provide spring forces with different sizes, so that the satellite can be stably pushed away and cannot be impacted due to overlarge spring force; wherein, the rigidity of the separation spring at the bottommost layer is the largest, and the rigidity of the separation spring at the topmost layer is the smallest.

Further, the utility model discloses can be used to single file pile up the satellite or pile up the satellite side by side. When the single-column stacking device is used for single-column stacking, four compression rings with the same structure are respectively arranged on different sides of each satellite. When the device is used for stacking in parallel, two corners (called inner corners for short) of adjacent inner side surfaces of a left satellite and a right satellite are respectively provided with a short pressing ring, the outer side surface (the surface opposite to the inner side surface) of the satellite is provided with a long pressing ring, and the height of the short pressing ring is half of that of the long pressing ring; the N long compression rings form a group of long compression ring units, and the 2N short compression rings form a group of short compression ring units; the satellite group is locked by two groups of long clamp ring units on the outer side surface and two groups of short clamp ring units on the inner side angle.

Furthermore, the separating nut is a memory metal separating nut, the lower end of each locking rod is locked by one separating nut, low-impact unlocking can be achieved, ground testing can be conducted repeatedly, and reliability is high.

Compared with the prior art, the beneficial effects of the utility model are embodied in:

(1) The utility model has no impact during separation, does not need to specially design an ignition circuit, has no gas discharge during separation, can verify the performance in a ground test, and solves the problems of large impact and high single-point failure risk of the existing firer separation technology;

(2) The utility model has compact structure, light weight and high space utilization rate; the plurality of stacked satellites are sequentially stacked and arranged along the extension direction of the compression ring, so that the adjacent satellites are directly connected without an additional adapter, the size and the weight of the additional adapter are saved, the overall device is lighter in weight, and the space utilization rate is higher;

(3) The utility model is used for the satellite is assembled portably when piling up, is required loosely, and the emission process security is high, and the reliability of on-orbit unblock separation is high.

Drawings

Fig. 1 is a schematic view of the locking state of the stacked satellite according to the present invention;

fig. 2 is a schematic diagram of the present invention in a state separated from the stacked satellites;

FIG. 3 is an enlarged view of FIG. 1 at A;

FIG. 4 is an enlarged view of FIG. 1 at B;

FIG. 5 is a cross-sectional view taken at B in FIG. 1;

FIG. 6 is a cross-sectional view taken at C of FIG. 1;

FIG. 7a is a schematic structural view of a long clamp ring;

FIG. 7b is a cross-sectional view of the elongated clamp ring;

FIG. 8a is a schematic structural view of a short clamp ring;

fig. 8b is a cross-sectional view of the shorting ring.

The reference numerals have the meanings given below: 1. a pressing seat; 2. a locking lever; 3. a long compression ring; 4. a short compression ring; 5. a locking seat; 6. separating the nut; 7. locking the screw; 8. a separation spring; 9. a flat satellite; 10. and pressing the screw.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and the specific embodiments, by taking a scheme of locking ten flat satellites as an example.

The utility model provides a non-firer separating mechanism suitable for pile up the satellite, its overall structure and the arrangement of satellite group on it are shown in figure 1, figure 2. The ten flat satellites 9 in this embodiment form a satellite group by stacking the satellites in parallel from left to right.

In the locked state, as shown in fig. 1, each flat satellite 9 is provided with three clamp rings, including a long clamp ring 3 located on the outer side of the satellite and two short clamp rings 4 located at the inner corners of the satellite. The compression rings on adjacent satellites are sequentially stacked along the longitudinal direction; five long clamp rings 3 on the outer side face form a group of long clamp ring units, ten short clamp rings 4 at the inner side corners form a group of short clamp ring units, and the whole satellite group is stacked by four groups of clamp ring units including two groups of long clamp ring units and two groups of short clamp ring units. Each group of the clamp ring units is pressed by two symmetrically arranged locking rods 2, the lower ends of the locking rods 2 are connected with a separation nut 6 through locking screws 7 (the details refer to fig. 3), and the upper ends of the locking rods 2 are connected with the clamp seat 1 through compression screws 10. The upper end and the lower end of the long compression ring 3 and the short compression ring 4 are respectively provided with a frustum and a cone socket (shown in figures 7 a-8 b) which are matched with each other, so that positioning is provided for the stacking of the satellite, and the transverse displacement between the compression rings after compression is limited, thereby avoiding the dislocation of the satellite in a plane in the launching process. The separating nut 6 is a memory metal separating nut, the lower end of the separating nut is connected with the locking seat 5 through a flange, and the locking seat 5 is fixed on the carrying platform. After the satellite groups are stacked, pretightening force is applied through the two compression screws 10, so that each compression ring unit is compressed, and the satellite groups are locked (fig. 4).

As shown in fig. 5 and 6, a separation spring 8 is arranged inside each compression ring, and preferably, the stiffness of the separation springs arranged in different layers is different, so as to provide spring forces with different magnitudes, ensure that the satellite can be pushed away smoothly, and the impact on the satellite due to the excessive spring force is avoided. The bottom separating spring has the highest rigidity and the highest load, and can push all the satellites stacked on the top to move separately; the stiffness of the top most separation spring is minimal, the load is minimal, and it only needs to push the top most satellites apart.

When the satellites need to be separated, as shown in fig. 2, power is supplied to eight separating nuts 6 of the satellite group at the same time, and the separating nuts 6 are unlocked and the locking rod 2 is released. Under the spring force action of the separating springs 8 in the top-most pressing ring, the four groups of locking rods 2 can rapidly fly upwards, and meanwhile, the separating springs in the lower pressing ring sequentially push satellites in different layers and rows to be separated from each other.

As shown in fig. 7a to 8b, the upper and lower ends of the long clamp ring 3 and the short clamp ring 4 are provided with mounting edges for connecting with a satellite, the height of the short clamp ring 4 is half of that of the long clamp ring 3, and the whole clamp ring is seen from the side

And a platform for placing the separation spring 8 is arranged at the bottom of the compression ring. Preferably, the lower end of the separation spring 8 is fixed on a platform at the bottom of the compression ring by a small screw, so that the separation spring is prevented from flying off from the compression ring. After stacking, the compression ring unit can provide stable support for the satellite, and the satellite is prevented from moving up and down when encountering vibration, so that the locking rigidity of the satellite group and the system fundamental frequency are improved.

It should be noted that the above expressions referring to orientations, such as "inner", "outer", "top", "bottom", etc., are based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships usually placed when the product of the present invention is used, and are only for convenience of description, but do not indicate or imply that the components related to have specific orientations, configurations or operations. In addition, for the sake of clarity, some features or characteristics, such as holes, mounting edges, clamp rings, etc., in the drawings are not all labeled, and although reference numerals refer to only one or a few of them, the description refers to the same overall characteristics.

The invention is not described in detail and belongs to the technology known in the art. The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not intended to limit the present invention in any way, and all modifications, equivalents, improvements and the like that are made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.

Claims (8)

1. A non-firer separating mechanism suitable for stacked satellites comprises a pressing seat (1), a pressing ring, a locking rod (2), a locking seat (5), a separating nut (6), a locking screw (7), a separating spring (8) and a pressing screw (10); it is characterized in that the preparation method is characterized in that,

three or four compression rings are arranged on each satellite, the compression rings on adjacent satellites are sequentially stacked along the longitudinal direction, the compression rings of a plurality of layers of satellites in the same direction form a group of compression ring units, and the whole satellite group is stacked through four groups of compression ring units; each group of compression ring units are compressed by two locking rods (2), the lower ends of the locking rods (2) are connected with a separation nut (6) through locking screws (7), and the upper ends of the locking rods (2) are connected with a compression seat (1) through compression screws (10); the lower end of the separation nut (6) is connected with the locking seat (5), and the locking seat (5) is fixed on the carrying platform; after the satellite groups are stacked, pretightening force is applied through a compression screw (10), so that each compression ring unit is compressed, and the satellite groups are locked;

a pre-compressed separation spring (8) is arranged in each compression ring; when the separation is carried out, all the separation nuts (6) are controlled to be unlocked simultaneously, and the locking rod (2) is released; under the action of the separation spring, the locking rod (2) flies upwards, and simultaneously, the satellites are sequentially pushed to realize separation.

2. A non-pyrotechnic separation mechanism suitable for stacked satellites as in claim 1 wherein the clamp rings are provided at their upper and lower ends with respective frustums and sockets that match to provide positioning for the stacking process and to limit lateral displacement between the clamp rings.

3. The non-pyrotechnic separation mechanism suitable for stacked satellites as in claim 1 wherein the clamp ring is provided with mounting edges at both its upper and lower ends for connection to the satellites and is integral with the clamp ringViewed from the side, the body is

And (4) shaping.

4. Non-pyrotechnic separation mechanisms suitable for stacked satellites according to any of claims 1 to 3 wherein the bottom inside the compression ring is provided with a platform for placing a separation spring (8).

5. Non-pyrotechnic separation mechanism suitable for stacked satellites according to claim 4 wherein the lower end of the separation spring (8) is fixed on a platform inside the hold-down ring avoiding the separation spring from flying off the hold-down ring during separation.

6. The non-pyrotechnic separation mechanism suitable for stacked satellites as in claim 1 wherein the separation springs disposed at different levels have different stiffnesses to provide spring forces of different magnitudes, the bottommost separation spring having the greatest stiffness and the topmost separation spring having the least stiffness.

7. The non-pyrotechnic separation mechanism suitable for stacked satellites in accordance with claim 1 wherein the separation mechanism is usable with single or side-by-side stacked satellites;

when the device is used for single-row stacking, four compression rings with the same structure are respectively arranged on different side surfaces of each satellite, and a satellite group is locked by four groups of compression ring units;

when the two short pressing rings are used for being stacked in parallel, one short pressing ring (4) is respectively installed at two inner side corners of each satellite, one long pressing ring (3) is installed on the outer side face of each satellite, the height of each short pressing ring (4) is half of that of each long pressing ring (3), and the satellite group is locked by two groups of long pressing ring units on the outer side face and two groups of short pressing ring units on the inner side corners.

8. Non-pyrotechnic separation mechanism suitable for stacked satellites according to claim 1 characterized in that the separation nut (6) is a memory metal separation nut.

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