Large-batch satellite launching device and separation method

Abstract

The invention relates to the technical field of satellite generation, in particular to a large-batch satellite launching device and a separation method.The large-batch satellite launching device comprises a rocket launching tower which is of a cylindrical structure, multiple layers of satellite separation mechanisms are installed on the side face of the rocket launching tower in the axial direction of the rocket launching tower, and the multiple satellite separation mechanisms on each layer are evenly arranged in the circumferential direction of the rocket launching tower; the satellite separation mechanisms are connected with corresponding satellites, the satellites are separated and released through the satellite separation mechanisms, and meanwhile when the large-batch satellite separation method is operated, the rocket launching tower alternately controls the two satellite separation mechanisms symmetrically arranged at the two ends of the rocket launching tower, and the controller separates the correspondingly connected satellites. The problems that when an existing aviation launcher adopts a disordered separation mode to launch a large number of satellites, the overall attitude and mass gravity center changes of the satellites and rockets which are not separated are large, and attitude control and separation safety cannot be guaranteed are solved.

Description

Technical Field

[0001] The present invention relates to the field of satellite launching technology, in particular to a mass satellite launching device and a separation method. Background Art

[0002] When existing aviation launchers launch large quantities of satellites, the separation of satellites mainly adopts a disordered separation mode, that is, when separated, the satellite as a whole has a certain separation angle and rotation angular velocity. After the separation mechanism is unlocked, the overall posture and mass center of gravity of the unseparated satellite and rocket change greatly, and attitude control and separation safety cannot be guaranteed. Summary of the invention

[0003] The purpose of the present invention is to provide a mass satellite launch device and separation method, which is used to solve the problem that when existing aviation launchers use a disordered separation mode to launch large quantities of satellites, the overall attitude and mass center of gravity of the unseparated satellites and rockets change greatly, and the attitude control and separation safety cannot be guaranteed. To achieve the above-mentioned purpose, the present invention provides a large-scale satellite launch device, including a rocket launch tower, which is a cylindrical structure. A plurality of layers of satellite separation mechanisms are installed on the side of the rocket launch tower along its axial direction. The multiple groups of satellite separation mechanisms in each layer are evenly arranged along the circumference of the rocket launch tower. The satellite separation mechanisms are connected to corresponding satellites, and the satellite separation mechanisms are used to separate and release the satellites.

[0004] At the same time, the present invention also provides a method for separating large quantities of satellites, which is applied to the above-mentioned large quantity satellite launching device, and comprises the following steps: The rocket launching tower alternately controls two groups of satellite separation mechanisms symmetrically arranged at two ends thereof, and the controller separates the corresponding connected satellites.

[0005] As a further solution of the present invention, the rocket launch tower first controls the satellite separation mechanisms near the two ends in sequence to launch satellites. When the satellites at both ends are completely launched, the satellite separation mechanisms in the adjacent inner layers are controlled to carry out subsequent launches in sequence.

[0006] Compared with the prior art, the present invention installs multiple layers of satellite separation mechanisms along the axial direction of the side of the rocket launch tower, and the multiple groups of satellite separation mechanisms in each layer are evenly arranged along the circumference of the rocket launch tower. When the rocket launch tower is launched, the rocket launch tower alternately controls the two groups of satellite separation mechanisms symmetrically arranged at its two ends, and the controller separates the corresponding connected satellites, which solves the problem that when the existing aviation launcher adopts an unordered separation mode to launch a large number of satellites, the overall posture and mass center of gravity of the unseparated satellites and rockets change greatly, and the attitude control and separation safety cannot be guaranteed. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1The figure is a schematic structural diagram of a mass satellite launching device and a separation method in the present invention.

[0008] In the attached figure: 1. Rocket launch tower; 2. Satellite. DETAILED DESCRIPTION

[0009] The technical solution of the present invention is further described in detail below in conjunction with specific implementation methods.

[0010] like Figure 1 As shown, in an embodiment of the present invention, a large-volume satellite launch device includes a rocket launch tower 1, which is a cylindrical structure. A plurality of layers of satellite separation mechanisms are installed on the side of the rocket launch tower 1 along its axial direction. The plurality of groups of satellite separation mechanisms in each layer are evenly arranged along the circumference of the rocket launch tower 1. The satellite separation mechanisms are connected to corresponding satellites 2, and the satellite separation mechanisms separate and release the satellites 2.

[0011] At the same time, the present invention also provides a method for separating large quantities of satellites 2, which is applied to the above-mentioned large quantity satellite 2 launch device, comprising the following steps: the rocket launch tower 1 alternately controls two sets of satellite separation mechanisms symmetrically arranged at both ends thereof, and the controller separates the corresponding connected satellites 2; Specifically, the present invention designs a symmetrical satellite launch method, which greatly reduces the change in the center of mass of the satellite 2 and the rocket launch tower 1 after the satellite 2 is separated, thereby reducing the impact on attitude control during the process.

[0012] Furthermore, the rocket launch tower 1 first controls the satellite separation mechanisms near the two ends in sequence to launch satellites. When the satellites 2 at both ends are completely launched, the satellite separation mechanisms of the adjacent inner layers are controlled to perform subsequent launches in sequence. Specifically, the present invention is provided with N layers of satellites 2 along its axial direction on the rocket launch tower 1, with M satellites 2 on each layer. Multiple satellites 2 (M*N satellites) are released in sequence by controlling the separation and unlocking method. For the convenience of subsequent description, the first satellite 2 of the first layer at the bottom is identified as A-1-1, and the first satellite 2 at the top is represented as AN-1. The release order is: A-1-1, AN-1, AN-2, A-1-2... and so on. After the separation mechanisms are unlocked in sequence, satellite 2 separates in sequence. After the separation mechanism of each satellite is unlocked, the angular velocity is less than 10° / s. The separation speed of satellite 2 is 0.5m / s. The angle of this separation is relatively large. Symmetrical unlocking greatly reduces the impact of the change in the center of mass after the separation of satellite 2 on attitude control. This separation method can be released symmetrically in time, and can tolerate the speed and angle deviations caused by the separation mechanism, which greatly improves safety and reduces the risk of collision when meeting the separation of large quantities of satellites 2.

[0013] The preferred embodiments of the present invention are described in detail above, but the present invention is not limited to the above embodiments. Various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention.

Claims

1. A mass satellite launching device, characterized in that: It includes a rocket launch tower, which is a cylindrical structure. A plurality of layers of satellite separation mechanisms are installed on the side of the rocket launch tower along its axial direction. The plurality of groups of satellite separation mechanisms on each layer are evenly arranged along the circumference of the rocket launch tower. The satellite separation mechanisms are connected to corresponding satellites, and the satellite separation mechanisms are used to separate and release the satellites.

2. A method for separating large quantities of satellites, characterized in that: A mass satellite launch device as claimed in claim 1, comprising the following steps: The rocket launching tower alternately controls two groups of satellite separation mechanisms symmetrically arranged at two ends thereof, and the controller separates the corresponding connected satellites.

3. A method for separating satellites in large quantities according to claim 2, characterized in that: The rocket launch tower first controls the satellite separation mechanisms near the two ends in sequence to launch satellites. When the satellites at both ends are completely launched, the satellite separation mechanisms in the adjacent inner layers are controlled to carry out subsequent launches in sequence.

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