CN212667707U

CN212667707U - Novel single-layer detachable multi-load satellite-rocket adapter

Info

Publication number: CN212667707U
Application number: CN201922441899.1U
Authority: CN
Inventors: 钟音亮; 余朝静; 周超英
Original assignee: Moutai University
Current assignee: Moutai University
Priority date: 2019-12-30
Filing date: 2019-12-30
Publication date: 2021-03-09
Anticipated expiration: 2029-12-30

Abstract

The utility model discloses a novel many loads star arrow adapter can be dismantled to individual layer, including a center section of thick bamboo, the main satellite is settled to a center section of thick bamboo, and the side symmetry sets up 4 switching adapters all around at a center section of thick bamboo, and the switching adapter settles the microsatellite that carries on, carries on the vertical parallelly connected placing of star, and the switching adapter has detachability, the utility model discloses do not adopt carrying cabin or inside and outside bearing structure form, the adapter in this configuration both will bear the main satellite and also carry on the star, because horizontal space is less and the radome fairing space is limited, and the object of carrying on in this individual layer configuration is four microtlatform satellites, possess the modularization, carry on characteristics such as flexibility height.

Description

Novel single-layer detachable multi-load satellite-rocket adapter

Technical Field

The utility model relates to a space flight technical field specifically is a novel many loads star arrow adapter can be dismantled to individual layer.

Background

When a large carrier rocket launches a payload, the large carrier rocket generally has residual carrying capacity, some of the large carrier rockets have the residual carrying capacity of thousands of kilograms, carrying and launching the small satellites is a good mode for utilizing the residual carrying capacity, and small satellite development units very hope to launch the satellites in the mode due to low carrying cost. But the presence of the secondary payload ride makes the launch task more complex and risky, which is undesirable on the part of the primary payload and the rocket launcher. While the need is present, the risk is present, and the contradiction between the two needs to be solved by an excessively hard mounting technology. Once the multi-load carrying technology is mature, the small satellite market is more prosperous, and the method plays a considerable role in promoting the technical development of the small satellite.

At present, due to the lack of a suitable universal carrying adapter, the carrier rocket can not meet the launching requirements of domestic and foreign minisatellites on flexible carrying, the rocket task benefit is lower, the launching cost is higher, the launching task adaptability is poor, and the international competitiveness is weak. Therefore, the structural design of the novel single-layer detachable multi-load satellite and rocket adapter has important significance for promoting the technical development of small satellites and striving for launching markets at home and abroad. Based on the background, a novel single-layer detachable multi-load satellite-rocket adapter structure is designed.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a novel many loads star arrow adapter structure can be dismantled to individual layer to solve and utilize current large-scale carrier rocket transmission surplus carrying capacity to carry on the little satellite scheduling problem of transmission.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a novel many loads star arrow adapter can be dismantled to individual layer, includes a center section of thick bamboo, and main satellite is settled to a center section of thick bamboo, and side symmetry sets up 4 switching adapters all around a center section of thick bamboo, and the switching adapter is settled the microsatellite that carries on, carries on the vertical parallelly connected placing of star, and the switching adapter has detachability.

Preferably, flanges are respectively arranged on the upper end surface and the lower end surface of the central cylinder, and the upper end and the lower end of the central cylinder are respectively connected with the main satellite and the rocket through the flanges; and the side surfaces of the periphery of the central cylinder are symmetrically provided with a second square flange mechanical interface, and the second square flange mechanical interface is matched with the first square flange mechanical interface on the adapter.

Preferably, an electrical through hole is formed between the second square flange mechanical interface of the central cylinder.

Preferably, two mechanical interfaces with different diameters are arranged at the working end of the switching adapter, the two mechanical interfaces are fixedly connected through a plate, an arc-shaped support plate is arranged in the switching adapter right below the mechanical interface with the small diameter, and reinforcing ribs are arranged on the left side and the right side of the switching adapter and used for increasing the rigidity of the mechanical interface with the large diameter.

Preferably, through holes are arranged on the front side and the rear side of the adapter, and the through holes are electric through holes or lightening holes.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses do not adopt and carry on cabin or inside and outside bearing structure form, the adapter in this configuration has both born the main satellite and has born and carry on the star, because horizontal space is less limited with the radome fairing space, and the object of carrying on in this individual layer configuration is four micro platform satellites, possess characteristics such as modularization, carry on the flexibility height.

Drawings

FIG. 1 is a schematic view of a single layer removable modular adapter;

FIG. 2 is a schematic view of a center cartridge configuration;

FIG. 3 is a side view of the adaptor adapter shaft I;

FIG. 4 is a side view of the adaptor adapter shaft;

fig. 5 is a schematic diagram of the application of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-5, the present invention provides a technical solution: the utility model provides a novel many loads star arrow adapter can be dismantled to individual layer, includes a center section of thick bamboo 2, and main satellite is settled to a center section of thick bamboo 2, and 2 side symmetries all around at a center section of thick bamboo set up 4 switching adapters 1, and switching adapter 1 settles the microsatellite that carries on, carries on the star and vertically connects in parallel and place, and switching adapter 1 has detachability.

Wherein, the upper end surface and the lower end surface of the central cylinder 2 are respectively provided with a flange, and the upper end and the lower end of the central cylinder 2 are respectively connected with the main satellite and the rocket through the flanges; the side symmetry sets up square flange mechanical interface two 8 around a section of thick bamboo 2, this square flange mechanical interface two 8 and the cooperation of the square flange mechanical interface one 9 on the adapter 1, (set up electric through-hole 10 between the square flange mechanical interface two 8 of a section of thick bamboo 2 in the center, set up two kinds of mechanical interfaces 11 of different diameters size at adapter 1 work end, pass through board 12 fixed connection between two mechanical interfaces 11, set up arc backup pad 13 in adapter 1 under the mechanical interface 11 of minor diameter, set up strengthening rib 14 in adapter 1 left and right sides and be used for increasing the rigidity of the mechanical interface 11 of major diameter, set up through-hole 15 in adapter 1's front and back both sides, this through-hole 15 is electric through-hole or lightening hole.

Specifically, this embodiment includes a center section of thick bamboo and 4 switching adapters, and main satellite is settled to a center section of thick bamboo, and the switching adapter is settled the microsatellite of carrying on, carries on the vertical parallelly connected placing of star, and the switching adapter has detachability, can dismantle the switching adapter that need not carry on the satellite, reaches the purpose of saving the quality. Each adapter has two mechanical interfaces with different diameters, so that the carrying of different types of microsatellites is met.

The central cylinder structure is provided with four electrical through holes and four square flange mechanical interfaces, 12 through holes and 12 reinforcing ribs are arranged around the flanges, the upper end flange is connected with a main satellite, the lower end flange is connected with a rocket, 32 through holes are distributed around the flanges, and the connecting modes are all connected by bolts and nuts.

Adapter structure square flange and the square flange phase-match of a center section of thick bamboo, flange department strengthening rib has 12, have the mechanical interface of two kinds of different diameters sizes, link firmly by 12 boards between two interface flanges, be used for increasing the rigidity of the connection of less interface, inside has two arc supports, be used for increasing the rigidity of less interface, outside both sides have three strengthening rib respectively, be used for increasing the rigidity of great interface, all there is a through-hole on kneck and the swash plate, for electric through-hole or alleviate empty, the connected mode all adopts the bolt and nut to connect.

Compared with the prior art, the utility model discloses do not adopt and carry on cabin or inside and outside bearing structure form, the adapter in this configuration both will bear the main satellite and also bear and carry on the star, because horizontal space is less limited with the radome fairing space, carry on the object in this individual layer configuration for four micro platform satellites, possess the modularization, carry on characteristics such as flexibility height.

As shown in fig. 5, the present embodiment is installed in the rocket fairing 5, the lower flange of the rocket fairing is connected to the instrument pod 3, the upper flange is connected to the main satellite 6, and 2 × cast200 platform satellites 4 and 2 × cast100 platform satellites 7 are symmetrically installed on the 4 adapter adapters.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a novel many loads star arrow adapter can be dismantled to individual layer, includes a central section of thick bamboo (2), and main satellite, its characterized in that are settled to a central section of thick bamboo (2): 4 switching adapters (1) are symmetrically arranged on the side surfaces of the periphery of the central cylinder (2), the switching adapters (1) are used for arranging carried microsatellites, the carried microsatellites are longitudinally arranged in parallel, and the switching adapters (1) are detachable.

2. The novel single-layer detachable multi-load satellite-rocket adapter according to claim 1, is characterized in that: flanges are respectively arranged on the upper end surface and the lower end surface of the central cylinder (2), and the upper end and the lower end of the central cylinder (2) are respectively connected with the main satellite and the rocket through the flanges; and a second square flange mechanical interface (8) is symmetrically arranged on the peripheral side surface of the central cylinder (2), and the second square flange mechanical interface (8) is matched with a first square flange mechanical interface (9) on the adapter (1).

3. The novel single-layer detachable multi-load satellite-rocket adapter according to claim 1, is characterized in that: an electric through hole (10) is arranged between the second square flange mechanical interface (8) of the central cylinder (2).

4. The novel single-layer detachable multi-load satellite-rocket adapter according to claim 1, is characterized in that: the mechanical interfaces (11) with different diameters are arranged at the working end of the adapter (1), the two mechanical interfaces (11) are fixedly connected through a plate (12), an arc-shaped support plate (13) is arranged in the adapter (1) right below the mechanical interface (11) with the small diameter, and reinforcing ribs (14) are arranged on the left side and the right side of the adapter (1) and used for increasing the rigidity of the mechanical interface (11) with the large diameter.

5. The novel single-layer detachable multi-load satellite-rocket adapter according to claim 1, is characterized in that: through holes (15) are arranged on the front side and the rear side of the adapter (1), and the through holes (15) are electric through holes or lightening holes.