CN113548197B

CN113548197B - Special multi-satellite adapter for star chain system

Info

Publication number: CN113548197B
Application number: CN202110756901.3A
Authority: CN
Inventors: 沈娜; 李文涛; 张祥金; 周鹏; 余延浩; 邓雪薇; 华抟; 郭竞杰
Original assignee: Nanjing University of Science and Technology
Current assignee: Nanjing University of Science and Technology
Priority date: 2021-07-05
Filing date: 2021-07-05
Publication date: 2022-07-22
Anticipated expiration: 2041-07-05
Also published as: CN113548197A

Abstract

A special multi-satellite adapter for a star chain system comprises a satellite packet and a plurality of satellite adapters arranged in the satellite packet; the star bag comprises a chassis and a plurality of star bag protective shells arranged on the chassis; a closing mechanism is arranged between the satellite bag protective shell and the chassis and is used for controlling the opening and closing of the satellite bag protective shell; a plurality of rows of adapter fixing surfaces are arranged in the chassis along the axial direction, and a plurality of groups of satellite adapters are arranged on each row of adapter fixing surfaces; the number of the groups of the satellite adapters on the fixed surface of each row of the adapters is the same as that of the satellite bag protective shells; the satellite adapter is used for accommodating satellites, and a satellite ejector is arranged in each group of satellite adapters and used for ejecting the satellites out after the satellite bag protective shell is opened. The invention can realize the simultaneous emission of a plurality of minisatellites and the matched monitoring and control functions.

Description

Special multi-satellite adapter for star chain system

Technical Field

The invention belongs to the field of aerospace, and particularly relates to a multi-satellite adapter special for a star chain system.

Background

The technology of the small satellite chain group in the development content of aerospace technology at the present stage is a leading-edge technology, and in order to match with the technology, all countries are exploring corresponding one-rocket multi-satellite launching modes, the technology realizes launching control of more than 20 small satellites, monitoring of the environment in the launching process and communication between an upper computer and a lower computer.

At present, a plurality of countries in the world all have one rocket multi-satellite launching systems, launching modes of the small satellite launching systems at present, such as minodo in the united states, European weaving girl and the like, are developed by traditional satellite launching modes, and only a single rocket single-satellite launching mode is added with a plurality of satellites, but with further improvement of satellite quantity requirements of a satellite chain technology and development of the satellite technology, the traditional satellite launching modes cannot meet requirements at present, the main problems are that the direction of small satellite release cannot be accurately controlled, and the small satellites cannot be released at different positions once to achieve the purpose of forming the satellite chain, and meanwhile, the traditional satellite launching device needs to be installed inside a rocket body to be separately reserved in space and design a matching system. Aiming at the requirements on the arrangement of the star chains at the present stage and the defects and the vacancy of the implementation mode at the present stage, the functional requirements on the arrangement of the star chains are specifically researched, the invention is specially used for a multi-star adapter, namely a star packet system, of the arrangement of a star chain system, and the purpose of arranging the star chains at one time by using a multi-star adapter, namely a multi-star packet system, which can be repeatedly opened and closed at one time and arranging small satellites at multiple positions is achieved.

Disclosure of Invention

The invention aims to provide a multi-satellite adapter special for a star chain system so as to realize simultaneous emission of a plurality of small satellites and matched monitoring and control functions.

The technical solution for realizing the purpose of the invention is as follows:

a multi-satellite adapter special for a star chain system comprises a satellite bag and a plurality of satellite adapters arranged in the satellite bag;

the star bag comprises a chassis and a plurality of star bag protective shells arranged on the chassis; a closing mechanism is arranged between the satellite bag protective shell and the chassis and is used for controlling the opening and closing of the satellite bag protective shell;

a plurality of rows of adapter fixing surfaces are axially arranged in the chassis, and a plurality of groups of satellite adapters are arranged on each row of adapter fixing surfaces; the number of the groups of the satellite adapters on the fixed surface of each row of the adapters is the same as that of the satellite bag protective shells; the satellite adapter is used for containing satellites, and a satellite ejector is arranged in each group of satellite adapters and used for ejecting the satellites out after the satellite bag protective shell is opened.

Compared with the prior art, the invention has the following remarkable advantages:

(1) the multi-directional multi-point multi-satellite launching is achieved through the characteristic that the satellite bag can be opened and closed repeatedly, and the arrangement of a star chain is facilitated.

(2) The internal launching system of satellite bag is independent of rocket launching system, compares in traditional satellite adapter, does not need the inside corollary equipment that provides of rocket body, and the adaptability is stronger.

(3) Through improving the locking mechanism of the traditional transmitting device of transmission, the whole size that reaches the adapter reduces, and the central controller control of being more convenient for reaches the effect of transmission in proper order.

Drawings

Fig. 1 is a block diagram of the overall design structure.

Figure 2 is an overall profile (single petal deployment).

Fig. 3 is an internal structural view.

Figure 4 is a side view of a moonlet adapter.

Figure 5 is a front view of a moonlet adapter.

Fig. 6 is a view showing a rotation structure of the satellite case.

In the figure: 1. the small satellite adapter comprises a small satellite adapter body 2, a first sliding rail 3, an adapter fixing surface 4, a central column 5, a sensor 6, a connecting rod 7, a satellite bag shell body 8, a bottom edge cover 9, a stepping motor 10, a central controller 11, a chassis 12, a spring 13, a pushing plate 14, a second sliding rail 15, a small satellite 16, a sliding groove 17, a locking mechanism 18, a bottom edge rotating shaft 19 and a connecting block

Detailed Description

The invention is further described with reference to the following figures and embodiments.

The invention relates to a special multi-star adapter for a star chain system, which comprises the following parts (as shown in figure 1): the device comprises a star bag protective shell (namely 'petals'), a shell driving device, a multi-star adapter, an environment detection system (for detecting temperature, attitude and atmospheric pressure), a comprehensive controller, a satellite charging system, a connection and separation device and an upper computer and a lower computer communication system.

The overall shape of the star bag is shown in figure 2, the overall shell consists of four star bag shells 7 and a chassis 11, a closed space is formed when the star bag is closed, and each star bag can be controlled to be opened and closed independently by a stepping motor 9. The inner side of the upper end of the satellite bag shell 7 is fixedly provided with a first sliding rail 2, the lower portion of the satellite bag shell 7 is connected with a connecting block 19, the connecting block 19 is connected with a bottom edge rotating shaft 18, the bottom edge rotating shaft 18 is fixed on a chassis 11, four groups of stepping motors 9 are sequentially fixed on the edge of the upper surface of the chassis 11 in a 90-degree difference mode, the rotating shaft of each stepping motor 9 is connected with one end of a connecting rod 6, the other end of each connecting rod 6 is connected with a sliding block through a rotating pair, and the sliding blocks are matched with the first sliding rail 2 and can slide up and down along the first sliding rail 2. The central controller 10 controls the stepping motor 9 to rotate forward and backward to achieve the purpose of opening and closing, and an angle of 100 degrees is formed between the stepping motor and the central column 4 when the stepping motor is opened in the maximum range.

A bottom edge cover 8 is fixed at the center of the chassis 11, a central controller 10, a sensor 5 and a power supply part are packaged in the bottom edge cover 8, and the central controller 10, the sensor 5 and the power supply part are fixed at the center of the chassis 11. The sensors 5 (including one or more of temperature, attitude, barometric pressure sensors) are used to monitor the internal environment of the satellite bag to confirm launch conditions and feedback anomalies. Center post 4 is fixed in 8 upsides in the end cover, and five groups of adapter fixed surfaces 3 are fixed in on center post 4 along axial equidistance, are fixed with four groups of little satellite adapters 1 on every group adapter fixed surface 3, and four groups of little satellite adapters 1 are circumference equidistance and distribute, and this star package is inside wholly can carry on twenty groups of little satellite adapters 1 altogether, and the locking mechanism 17 of each group of adapter 1 is connected with central controller 10 through the inside of center post 4 by the cable.

Each group of the small satellite adapters 1 is internally provided with a small satellite ejector, the composition structure of the small satellite ejector is shown in figure 4 and figure 5, the small satellite ejector comprises a locking mechanism 17, a push plate 13 arranged in the adapter cabin and a spring 12 arranged between the push plate 13 and the adapter cabin, and the two ends of the adapter cabin are respectively provided with the locking mechanism 17 for locking the push plate 13. In this embodiment, the locking mechanism 17 can be an electric telescopic rod, and the central controller 10 controls the electric telescopic rod to extend and retract, so as to lock and unlock the push plate 13. Sliding grooves 16 are formed in two sides in the adapter cabin, and the push plate 13 is in sliding fit with the sliding grooves 16 so as to guide sliding of the push plate 13. The left and right sides of the upper end and the left and right sides of the lower end in the adapter cabin are provided with second slide rails 14, and the moonlet arranged in the adapter cabin is matched with the second slide rails 14 so as to guide the sliding of the moonlet. The small satellite is launched through the push plate 13 by taking the spring 12 as power, the spring 12 is compressed before launching, the two wings of the push plate 13 are locked through the sliding grooves 16 by the locking mechanisms 17 on the side faces, and the central controller 10 controls the unlocking of the locking mechanisms 1 during launching to realize elastic launching. The sliding grooves 13 and the second sliding rails 14 ensure that the launching position of the moonlet does not deviate from the predetermined orbit, and the second sliding rails 14 are used for ensuring that the solar panel on the side of the moonlet keeps a certain distance from the inner surface of the adapter cabin so as not to generate friction.

Claims

1. A multi-satellite adapter special for a star chain system is characterized by comprising a satellite packet and a plurality of satellite adapters arranged in the satellite packet;

a plurality of rows of adapter fixing surfaces are arranged in the chassis along the axial direction, and a plurality of groups of satellite adapters are arranged on each row of adapter fixing surfaces; the number of the groups of the satellite adapters on the fixed surface of each row of the adapters is the same as that of the satellite bag protective shells; the satellite adapters are used for accommodating satellites, and each group of satellite adapters is internally provided with a satellite ejector which is used for ejecting the satellites out after the satellite bag protective shell is opened;

the satellite ejector comprises a locking mechanism, a push plate arranged in a cabin body of the satellite adapter and a spring arranged between the push plate and the cabin body of the satellite adapter; a locking mechanism is arranged on the cabin body of the satellite adapter and used for locking the push plate; a guide mechanism is arranged between the push plate and the cabin body of the satellite adapter so as to guide the sliding of the push plate;

the left and right sides of the upper end and the left and right sides of the lower end in the cabin body of the satellite adapter are provided with second slide rails, and a small satellite arranged in the cabin body of the satellite adapter is matched with the second slide rails, so that the distance between a solar cell panel on the side face of the satellite and the inner surface of the cabin body of the satellite adapter is kept.

2. The multi-star adapter special for the star chain system as claimed in claim 1, wherein the closing mechanism comprises a stepping motor, a first slide rail, a connecting block, a rotating shaft; a first sliding rail is fixed on the inner side of the upper end of the satellite bag shell, the lower part of the satellite bag shell is connected with a connecting block, and the connecting block is connected with a chassis through a rotating shaft; the rotating shaft of the stepping motor is connected with one end of a connecting rod, the other end of the connecting rod is connected with a sliding block through a revolute pair, and the sliding block is matched with the first sliding rail and can slide up and down along the first sliding rail.

3. The special multi-star adapter for the star chain system as claimed in claim 1, wherein the locking mechanism is an electric telescopic rod.

4. The multi-star adapter for a star-chain system as claimed in claim 1, wherein a bottom cover is further fixed to the chassis center for protecting the control unit and the power module.

5. The adapter of claim 4, wherein a sensor unit is further disposed in the bottom edge cover for detecting the internal environment of the satellite bag.

6. The adapter of claim 1, wherein the adapter fixing surface is fixed on the bottom cover by a center post.