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Launching device with multiple satellites arranged in parallel

A launching device and parallel technology, applied in the field of satellite launch, can solve the problems of multiple payload weights of rockets, reduce the carrying capacity of rockets, reduce the utilization rate of effective space of fairings, etc. Effect

Active Publication Date: 2020-03-17
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The existing method occupies more payload weight of the rocket, thus reducing the carrying capacity of the rocket, and the series layout also requires a higher satellite fairing, thereby reducing the effective space utilization of the fairing

Method used

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  • Launching device with multiple satellites arranged in parallel
  • Launching device with multiple satellites arranged in parallel
  • Launching device with multiple satellites arranged in parallel

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Embodiment Construction

[0035] A launching device with a multi-satellite parallel arrangement proposed by the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become apparent from the following description and claims. It should be noted that, the accompanying drawings are all in a very simplified form and use imprecise ratios, and are only used to facilitate and clearly assist the purpose of explaining the embodiments of the present invention.

[0036] see Figures 1 to 4 , a launching device with a multi-satellite parallel layout, including a lower cone cabin 1, an inner cone cabin 2, an outer cone cabin 3, a beam system installation platform, and a transition ring 6. The opening of the first end of the lower cone cabin 1 is larger than the opening of the second end of the lower cone cabin 1, that is to say, the lower cone cabin 1 is a hollow conical cavity with...

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Abstract

The invention discloses a launching device with multiple satellites arranged in parallel. The launching device comprises a lower cone cabin, an inner cone cabin, an outer cone cabin, multiple beam system installation platforms and multiple transition rings. A first end opening of the lower cone cabin is larger than a second end opening of the lower cone cabin. A first end opening of the inner conecabin is larger than a second end opening of the inner cone cabin. The first end of the inner cone cabin is connected to the second end of the lower cone cabin. A first end opening of the outer conecabin is larger than a second end opening of the outer cone cabin. The second end of the outer cone cabin is arranged on the outer side cone face of the lower cone cabin or the inner cone cabin in a sleeving manner. The multiple beam system installation platforms are circumferentially arranged between the first end of the outer cone cabin and the second end of the inner cone cabin. A transition ring is arranged on each beam system installation platform. The transition rings are used for installing satellite adapters. The device is compact in structure and small in occupied space.

Description

technical field [0001] The invention belongs to the field of satellite launching, and in particular relates to a launching device with a multi-satellite parallel arrangement. Background technique [0002] One rocket multi-satellite launch technology refers to the technology of using a multi-satellite launch device to launch multiple satellites into a predetermined orbit at one time. This technology can shorten the launch cycle of a single satellite and reduce the launch cost. It is a method to reduce the launch cost of launch vehicles. important way. [0003] At present, the multi-satellite launch with one arrow often adopts a multi-satellite series layout, that is, adding a transition cabin and a support cabin to realize its layout, and then install satellites through satellite adapters. [0004] The existing method occupies more payload weight of the rocket, thereby reducing the carrying capacity of the rocket, and the tandem layout also requires a higher satellite fairin...

Claims

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Application Information

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IPC IPC(8): F41F3/04
CPCF41F3/04
Inventor 赵学成秦震王瑞凤朱亮聪杨颜志郑权
Owner SHANGHAI AEROSPACE SYST ENG INST
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