CN113548197B - A multi-star adapter dedicated to the star chain system - Google Patents

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

A multi-star adapter dedicated to the star chain system

technical field

The invention belongs to the field of aerospace, in particular to a multi-star adapter specially used in a star chain system.

Background technique

At this stage of aerospace technology development, the small and medium-sized satellite star chain technology is a cutting-edge technology. In order to support this technology, countries are exploring the corresponding launch method of one arrow and multiple satellites. This technology has realized the launch control of more than 20 small satellites and the control of the launch process The monitoring of the environment and the communication between the upper and lower computers.

At this stage, many countries in the world have one-rocket multi-satellite launch systems. At this stage, small satellite launch systems such as Minotaur in the United States and Vega in Europe are all developed from traditional satellite launch methods. The single-rocket and single-satellite launch method adds multiple satellites, but with the further increase in the number of satellites required by Starlink technology and the development of satellite technology, the traditional satellite launch method can no longer meet the current needs. The main problem is that it is difficult to precisely control The direction of the release of small satellites and the inability to release small satellites at different positions at a time to achieve the purpose of forming a star chain, while the traditional satellite launcher needs to be installed inside the rocket body, which requires separate space and design of supporting systems. Aiming at the current requirements for the Starlink layout and the deficiencies and vacancies of the current implementation methods, a specific study was carried out on the functional requirements of the Starlink layout, and a multi-star adapter specially used for the Starlink system layout was invented, the Star Packet System. The realization of multiple satellites at one time, repeated opening and closing, and multi-position arrangement of small satellites has achieved the purpose of arranging the star chain at one time.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a multi-satellite adapter specially used for the star chain system, so as to realize the simultaneous launch of multiple small satellites and the supporting monitoring and control functions.

The technical solution that realizes the object of the present invention is:

A multi-satellite adapter dedicated to the star chain system, including a star package, and a plurality of satellite adapters arranged in the star package;

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 star bag protective shell and the chassis to control the opening and closing of the star bag protective shell;

The chassis is provided with multiple rows of adapter fixing surfaces along the axial direction, and each row of adapter fixing surfaces is provided with multiple groups of satellite adapters; the number of sets of satellite adapters on the fixed surface of each row of adapters is the same as the number of satellite package protective shells; Satellite adapters are used to accommodate satellites, and each set of satellite adapters is provided with a satellite catapult, which is used to eject the satellites after the protective shell of the satellite bag is opened.

Compared with the prior art, the present invention has the following significant advantages:

(1) The multi-direction, multi-point and multi-satellite launch can be achieved through the repeatable opening and closing of the star package, which is more conducive to the layout of the star chain.

(2) The internal launch system of the satellite package is independent of the rocket launch system. Compared with the traditional satellite adapter, it does not need to provide supporting equipment inside the rocket body, and the adaptability is stronger.

(3) By improving the locking mechanism of the traditional launching device, the overall size of the adapter can be reduced, and it is more convenient for the central controller to control and achieve the effect of sequential launching.

Description of drawings

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

Figure 2 is an overall outline drawing (single petal unfolded).

Figure 3 is an internal structure diagram.

Figure 4 is a side view of the small satellite adapter.

Figure 5 is a front view of the small satellite adapter.

FIG. 6 is a structural diagram of the rotation of the star package shell.

In the picture: 1. Small satellite adapter, 2. First slide rail, 3. Adapter fixing surface, 4. Center column, 5. Sensor, 6. Connecting rod, 7. Star package shell, 8. Bottom cover, 9 , stepper motor, 10, center controller, 11, chassis, 12, spring, 13, push plate, 14, second slide rail, 15, small satellite, 16, chute, 17, locking mechanism, 18, bottom Side shaft, 19, connecting block

Detailed ways

The present invention will be further introduced below with reference to the accompanying drawings and specific embodiments.

A multi-star adapter specially used in the star chain system of the present invention includes the following parts (as shown in Figure 1): a star packet protective shell (ie "petal"), a shell driving device, a multi-star adapter, an environmental detection system (detecting temperature , attitude, atmospheric pressure), integrated controller, satellite charging system, connection and separation device, upper and lower computer communication system.

The overall shape of the star package is shown in Figure 2. The overall shell is composed of four star package shells 7 and a chassis 11. When closed, a closed space is formed, and each piece can be individually opened and closed by a stepping motor 9. The inner side of the upper end of the star package shell 7 is fixed with a first slide rail 2, the lower part of the star package shell 7 is connected with a connecting block 19, the connecting block 19 is connected with the bottom side rotating shaft 18, and the bottom side rotating shaft 18 is fixed on the chassis 11, The four groups of stepper motors 9 are fixed to the edge of the upper surface of the chassis 11 with a difference of 90° in sequence. The rotating shaft of the stepper motor 9 is connected to one end of the connecting rod 6, and the other end of the connecting rod 6 is connected to the slider through the rotating pair, and the slider is connected to the first end of the connecting rod 6. A sliding rail 2 is matched and can slide up and down along the first sliding rail 2 . The central controller 10 controls the forward and reverse rotation of the stepping motor 9 to achieve the purpose of opening and closing.

The bottom cover 8 is fixed in the center of the chassis 11 . The bottom cover 8 encapsulates a central controller 10 , a sensor 5 and a power supply part. The sensor 5 (including one or more of temperature, attitude, and air pressure sensors) is used to monitor the internal environment of the star package to confirm the launch condition and feedback abnormality. The central column 4 is fixed on the upper side of the bottom cover 8, and five sets of adapter fixing surfaces 3 are fixed on the central column 4 at equal distances in the axial direction. The adapters 1 are distributed equidistantly in the circumferential direction. A total of twenty groups of small satellite adapters 1 can be carried inside the satellite package. The locking mechanism 17 of each group of adapters 1 is connected to the central controller 10 by cables through the interior of the central column 4 .

Each group of small satellite adapters 1 is provided with a small satellite catapult. The composition of the small satellite catapult of the present invention is shown in FIGS. 4 and 5 . The small satellite catapult includes a locking mechanism 17 and a push plate 13 arranged in the adapter cabin. And the spring 12 arranged between the push plate 13 and the adapter cabin, the two ends of the adapter cabin are provided with locking mechanisms 17 for locking the push plate 13 . In this embodiment, the locking mechanism 17 can use an electric telescopic rod, and the central controller 10 controls the telescopic extension of the electric telescopic rod, so as to realize the locking and unlocking of the push plate 13 . There are sliding grooves 16 on both sides of the adapter compartment, and the push plate 13 is slidably matched with the sliding grooves 16 to guide the sliding of the push plate 13 . Second sliding rails 14 are provided on the left and right sides of the upper end and the left and right sides of the lower end of the adapter cabin. The small satellites arranged in the adapter cabin cooperate with the second sliding rails 14 to guide the sliding of the small satellites. The small satellite uses the spring 12 as the power to launch through the push plate 13. Before launching, the spring 12 is compressed and the two wings of the push plate 13 are locked through the side locking mechanism 17 through the chute 16, and the central controller is used for launching. 10. Control the locking mechanism 1 to unlock to realize elastic launch. The chute 13 and the second sliding rail 14 ensure that the launch position of the small satellite does not deviate from the predetermined orbit, and the second sliding rail 14 is used to ensure that the solar panel on the side of the small satellite and the inner surface of the adapter cabin maintain a certain distance to avoid friction.

Claims (6)

1. A multi-satellite adapter specially used in a star chain system, is characterized in that, comprises a star package, and is arranged in a plurality of satellite adapters in the star package; 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 star bag protective shell and the chassis to control the opening and closing of the star bag protective shell; The chassis is provided with multiple rows of adapter fixing surfaces along the axial direction, and each row of adapter fixing surfaces is provided with multiple groups of satellite adapters; the number of sets of satellite adapters on the fixed surface of each row of adapters is the same as the number of satellite package protective shells; The satellite adapter is used to accommodate satellites, and each satellite adapter is equipped with a satellite catapult, which is used to eject the satellite after the protective shell of the satellite bag is opened; The satellite catapult includes a locking mechanism, a push plate disposed in the cabin of the satellite adapter, and a spring disposed between the push plate and the cabin of the satellite adapter; the cabin of the satellite adapter is provided with a locking mechanism, It is used to lock the push plate; a guiding mechanism is arranged between the push plate and the cabin of the satellite adapter to guide the sliding of the push plate; In the cabin of the satellite adapter, second sliding rails are provided on the left and right sides of the upper end and the left and right sides of the lower end. The interior surfaces of the adapter's body are kept at a distance. 2 . The multi-star adapter specially used for the star chain system according to claim 1 , wherein the closing mechanism comprises a stepping motor, a first sliding rail, a connecting block, and a rotating shaft; the inner side of the upper end of the star package shell is fixed inside. 3 . There is a first sliding rail, the lower part of the star package shell is connected with the connecting block, and the connecting block is connected with the chassis through the rotating shaft; the rotating shaft of the stepping motor is connected with one end of the connecting rod, the other end of the connecting rod is connected with the slider through the rotating pair, and the slider is connected with The first slide rail is matched and can slide up and down along the first slide rail. 3 . The multi-star adapter specially used for a star chain system according to claim 1 , wherein the locking mechanism adopts an electric telescopic rod. 4 . 4 . The multi-star adapter specially used for the star chain system according to claim 1 , wherein a bottom cover is also fixed in the center of the chassis for protecting the control unit and the power module. 5 . 5. The multi-satellite adapter dedicated to the star chain system according to claim 4, wherein a sensor unit is further provided in the bottom cover for detecting the internal environment of the star package. 6 . The multi-star adapter dedicated to a star chain system according to claim 1 , wherein the adapter fixing surface is fixed on the bottom cover through a central column. 7 .

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