A multi-star series launch system

Abstract

The present invention provides a multi-satellite series launch system, which includes a satellite fairing, a point separation device, a first support cabin, a first transition cabin, a second support cabin, a satellite adapter, a second transition cabin, a third transition cabin and a third support cabin; the satellite fairing is used to protect the payload inside the satellite fairing before and during the takeoff of the launch vehicle; the first transition cabin, the second transition cabin and the third transition cabin serve as the structural supports for the satellite fairing and the satellite, and protect the payload inside the rocket before and during the takeoff of the launch vehicle; the docking surface between the first transition cabin and the second support cabin is the separation surface between the first transition cabin and the rocket, and the first transition cabin and the rocket are connected by pyrotechnics and separated by a separation spring; compared with the prior art, the present invention makes use of the inverted layout of the second support cabin, thereby making full use of the available space inside the second support cabin. This layout scheme is simple and reliable, and has high economic value and engineering application value.

Description

Technical Field

[0001] The present invention relates to the field of space technology, and particularly to a multi-satellite series launch system. Background Art

[0002] Entering space, utilizing space, and controlling space are the main tasks of space forces. Quick and efficient access to space is the basis for utilizing space and controlling space. The multi-satellite launch technology refers to the technology of launching multiple satellites into predetermined orbits at one time using a single launch vehicle. On the premise that the launch vehicle's carrying capacity and the available envelope inside the fairing permit, the use of multi-satellite launch technology can enable multiple satellites to quickly form a network after entering orbit, meeting the requirements for rapid deployment of constellation missions. At the same time, launching multiple satellites within one rocket launch cycle can shorten the launch cycle of a single satellite and significantly reduce the satellite launch cost, which is an important way to improve the cost performance of launch vehicles. Based on the above advantages, major space powers around the world attach great importance to multi-satellite launch technology and have invested a lot of energy in research and development.

[0003] Currently, the main forms of multi-satellite launches of domestic launch vehicles are in series or parallel configurations. However, the satellite layout generally adopts a central arrangement. When encountering satellites with special configurations, it is difficult to fully utilize the available envelope inside the satellite fairing. In addition, with the booming development of multi-satellite launch technology, certain research and development progress has been made in the multi-satellite launch technology for micro-nano satellites. However, the multi-satellite launch technology for medium and small satellites, especially satellites over 100 kg, remains one of the key technologies that need to be developed urgently in domestic space technology. Summary of the Invention

[0004] The purpose of the present invention is to provide a multi-satellite series launch system that can achieve rapid launch of multiple satellites with one arrow and has high reliability and safety.

[0005] The technical solution of the present invention is: to provide a multi-satellite series launch system, including a satellite fairing, a point separation device, a first support cabin, a first transition cabin, a second support cabin, a satellite adapter, a second transition cabin, a third transition cabin, and a third support cabin;

[0006] The satellite fairing is used to protect the payload inside the satellite fairing before and during the takeoff of the launch vehicle; the first transition cabin, the second transition cabin, and the third transition cabin serve as the structural supports for the satellite fairing and the satellite, protecting the payload inside the rocket before and during the takeoff of the launch vehicle; the docking surface between the first transition cabin and the second support cabin is the separation surface between the first transition cabin and the rocket. The first transition cabin and the rocket are connected through pyrotechnics and separated using separation springs;

[0007] Except for the space occupied by the first support cabin and the point separation device within the satellite fairing, the remaining space can be used to place the satellite. The minimum gap between the satellite fairing and the satellite is not less than 150 mm; the available space within the satellite fairing can meet the envelope space requirements for satellites weighing more than 100 kg;

[0008] The internal space formed by the first support cabin, the first transition cabin, and the second support cabin can meet the external envelope requirements for satellites weighing more than 100 kg; the minimum gap between the satellite and the combination of the first support cabin and the first transition cabin is not less than 150 mm;

[0009] The internal space formed by the second transition cabin, the third transition cabin, the second support cabin, and the third support cabin can meet the external envelope requirements for satellites weighing more than 100 kg; the minimum gap between the satellite and the second support cabin, the second transition cabin, and the third transition cabin is not less than 150 mm.

[0010] Furthermore, within the satellite fairing, one satellite is arranged on the first support cabin, and the satellite-rocket connection is achieved through the point separation device; the second support cabin and the satellite adapter are arranged within the first transition cabin, one satellite is arranged on the second support cabin and the satellite adapter, and the satellite-rocket connection is achieved through the strap; the third support cabin is arranged within the second transition cabin and the third transition cabin, one satellite is arranged on the third support cabin, and the satellite-rocket connection is achieved through the point separation device.

[0011] Furthermore, the satellite on the third support cabin can be laterally offset by 200 mm.

[0012] Furthermore, the large-diameter end of the second support cabin faces upward and the small-diameter end faces downward.

[0013] Furthermore, the satellite separation speed direction within the satellite fairing is parallel to the rocket body axis.

[0014] Furthermore, the satellite separation speed direction within the first transition cabin is parallel to the rocket body axis.

[0015] Furthermore, the satellite separation speed direction within the second transition cabin and the third transition cabin is parallel to the rocket body axis.

[0016] The beneficial effects achieved by the multi-satellite series launch system provided by the present invention are:

[0017] Compared with the prior art, the present invention utilizes the inverted layout of the second support cabin (the large-diameter end faces upward and the small-diameter end faces downward), thereby making full use of the available space inside the second support cabin. This layout scheme is simple and reliable, and has high economic value and engineering application value.

[0018] Compared with the prior art, in the present invention, the docking surface between the first transition module and the second support module is also designed as the separation surface of the first transition module, reducing one transition module. This solution can effectively reduce the weight of the rocket body structure and improve the rocket's carrying capacity.

[0019] In addition, through the improvement of the interface form on the upper end surface of the third support module, the present invention can meet the requirements of satellite offset layout of more than 100 kg and can be used for the envelope layout requirements of satellites with special configurations. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention will be further described below in conjunction with the drawings:

[0021] Figure 1 is a schematic diagram of a multi-satellite series launch system of the present invention;

[0022] Figure 2 is a side view of the third support module and the point separation device of the present invention;

[0023] Figure 3 is a top view of the third support module and the point separation device of the present invention;

[0024] Figure 4 is a side view of the second support module and the satellite adapter of the present invention;

[0025] Figure 5 is a top view of the second support module and the satellite adapter of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] The multi-satellite series launch system proposed by the present invention will be further described in detail below in conjunction with the drawings and specific embodiments. According to the following description and the claims, the advantages and features of the present invention will be clearer. It should be noted that the drawings are all in a very simplified form and use non-precise ratios, only for the purpose of conveniently and clearly assisting in explaining the embodiments of the present invention.

[0027] Embodiment 1

[0028] This embodiment provides a multi-satellite series launch system, as Figure 1 shown, including: satellite fairing 1, point separation device 2, first support module 3, first transition module 4, second support module 5, satellite adapter 6, second transition module 7, third transition module 8, third support module 9.

[0029] One satellite is installed in the satellite fairing of this system, and the star-rocket connection is realized through the point separation device. To ensure the safety of the satellite fairing separation process, it is necessary to ensure that the minimum gap between the satellite and the satellite fairing is not less than 150 mm.

[0030] This system installs a satellite within the internal space formed by the first support module 3, the first transition module 4, and the second support module 5. Flexible connection between the satellite and the rocket is achieved through strap. To ensure that the satellite and the rocket do not collide during the separation process, it is necessary to ensure that the minimum clearance between the satellite and the first support module 3 and the first transition module 4 is not less than 150 mm.

[0031] This system installs a satellite within the internal space formed by the second support module 5, the second transition module 7, the third transition module 8, and the third support module 9. Connection between the satellite and the rocket is achieved through a point separation device. To ensure that the satellite and the rocket do not collide during the separation process, it is necessary to ensure that the minimum clearance between the satellite and the second transition module 7 and the third transition module 8 is not less than 150 mm.

[0032] Embodiment 2

[0033] In this embodiment, a satellite fairing with a diameter of 3.35 m is used. A satellite is arranged within the satellite fairing and on the first support module. See Figure 1 , and the mass of the satellite can reach more than 500 kg. Connection, unlocking, and spring separation between the satellite and the rocket are achieved through a point separation device.

[0034] In the present invention, a 600 kg-class satellite is arranged within the first transition module. See Figure 1 , connection between the satellite and the rocket is achieved through strap, and unlocking is performed. By setting a separation spring on the satellite adapter, separation between the satellite and the rocket is achieved. Among them, the satellite is placed within the internal space formed by the first support module, the first transition module, and the second support module.

[0035] In the present invention, a 500 kg-class satellite is arranged within the third transition module and the second transition module. See Figure 1 , connection, unlocking, and spring separation between the satellite and the rocket are achieved through a point separation device. Among them, the satellite on the third support module is placed with a 200 mm offset. See Figure 3 .

[0036] In the present invention, the docking surface between the first transition module and the second support module is also designed as the separation surface between the first transition module and the rocket. Connection between the first transition module and the rocket is achieved through pyrotechnics, and separation is implemented using a separation spring.

[0037] The content not described in detail in this specification belongs to the prior art well-known to those skilled in the art. For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be encompassed within the present invention.

Claims

1. A multi-star series launch system, characterized in that, It includes a satellite fairing, a point separation device, a first support cabin, a first transition cabin, a second support cabin, a satellite adapter, a second transition cabin, a third transition cabin and a third support cabin; The satellite fairing is used to protect the payload inside the satellite fairing before and during the takeoff of the launch vehicle; the first transition cabin, the second transition cabin and the third transition cabin serve as the structural supports of the satellite fairing and the satellite, and protect the payload inside the rocket before and during the takeoff of the launch vehicle; the docking surface between the first transition cabin and the second support cabin is the separation surface between the first transition cabin and the rocket. The first transition cabin and the rocket are connected by pyrotechnics and separated by separation springs; Except for the space occupied by the first support cabin and the point separation device inside the satellite fairing, the remaining space can be used to place the satellite. The minimum gap between the satellite fairing and the satellite is not less than 150 mm; the available space inside the satellite fairing can meet the envelope space requirements of satellites over 100 kg; The internal space formed by the first support cabin, the first transition cabin and the second support cabin can meet the external envelope requirements of satellites over 100 kg; the minimum gap between the satellite and the combination of the first support cabin and the first transition cabin is not less than 150 mm; The internal space formed by the second transition cabin, the third transition cabin, the second support cabin and the third support cabin can meet the external envelope requirements of satellites over 100 kg; the minimum gap between the satellite and the second support cabin, the second transition cabin and the third transition cabin is not less than 150 mm; Inside the satellite fairing, one satellite is arranged on the first support cabin, and the satellite-rocket connection is realized through the point separation device; the second support cabin and the satellite adapter are arranged inside the first transition cabin, one satellite is arranged on the second support cabin and the satellite adapter, and the satellite-rocket connection is realized through a strap; the third support cabin is arranged inside the second transition cabin and the third transition cabin, one satellite is arranged on the third support cabin, and the satellite-rocket connection is realized through the point separation device; The large diameter end of the second support cabin faces upward and the small diameter end faces downward.

2. The multi-star series launch system according to claim 1, characterized in that, The satellite on the third support cabin can be laterally offset by 200 mm.

3. The multi-star series launch system according to claim 1, characterized in that, The satellite separation speed direction inside the satellite fairing is parallel to the rocket axis.

4. The multi-star series launch system according to claim 1, characterized in that, The satellite separation speed direction inside the first transition cabin is parallel to the rocket axis.

5. The multi-star series launch system according to claim 1, characterized in that, The satellite separation speed direction inside the second transition cabin and the third transition cabin is parallel to the rocket axis.

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