Recovery structure of carrier rocket fairing
A technology of launch vehicles and fairings, which is used in projectiles, self-propelled missiles, offensive equipment, etc., can solve the problems of irregular aerodynamic shape, inapplicability, and difficult to break through thermal protection, and achieves outstanding substantive features, damage prevention, The effect of increasing the deceleration area
Pending Publication Date: 2019-06-25
BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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Problems solved by technology
In short, for the fairing, the environmental conditions encountered during the return process are far more complex and harsh than the launch process and operation process, and the fairing re-entry and return technology is quite difficult. Neither is applicable, because the aerodynamic shape is very irregular, thermal protection is more difficult to break through, and it is more challenging for commercial applications, so it is more necessary to break through the technical bottleneck
Method used
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[0037] In order to clearly illustrate the technical characteristics of this solution, the following will describe this solution through specific implementation modes and in conjunction with the accompanying drawings.
[0038] Half-cover fairing, that is, a complete fairing is longitudinally sectioned to form two half-cover fairings.
[0039] A recovery structure for a launch vehicle fairing, as shown in the figure, it includes an inflatable flexible half cover 2 that can be docked with a separated rigid half cover 1, and the rigid half cover 1 includes sequentially along its axial direction Connected end A3, semi-conical section A4 and semi-cylindrical section A5. The material of the flexible half cover 2 is a biaxial nylon cover, the butt joint surface of the flexible half cover 2 and the rigid half cover 1 is fixedly connected by a bolt assembly 9, and the flexible half cover 2 when not inflated is folded and stored in the rigid half cover. Inside the cover 1, other auxilia...
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The invention provides a recovery structure of a carrier rocket fairing. The structure comprises an inflating flexible half fairing which can be docked with a detached rigid half fairing, the flexiblehalf fairing is fixedly connected with a docking face of the rigid half fairing through a bolt assembly, the flexible half fairing is folded and accommodated in the rigid half fairing when the flexible half fairing is not inflated, and the part, docked with the rigid half fairing in the axial direction, of the inflated flexible half fairing and the rigid half fairing are symmetric taking the docking face of the part and the rigid half fairing as the center. The recovery structure has the advantages that detached rigid half fairing can be allowed to obtain an aerodynamic shape which is suitable for a ballistic type return vehicle, more carrying capability of the rocket is not sacrificed, and therefore the soft landing recovery of the rigid half fairing can be achieved.
Description
technical field [0001] The invention relates to a recovery structure of a launch vehicle fairing, and belongs to the technical field of launch vehicle fairing recovery. Background technique [0002] Fairing recovery is a branch of the development and application of reusable launch vehicle technology, and it is also becoming a hot spot pursued by commercial aerospace companies. So far, there has been no successful case. On the one hand, the limitation of the static envelope of the satellite compresses the surplus space inside the fairing, making the space for installing the recovery system and equipment very limited; on the other hand, the recovery technology is complex and expensive. [0003] Fairing recovery technology mainly refers to the use of spacecraft re-entry and return technology to solve the problems of fairing separation, atmospheric re-entry, safe landing, recovery and reuse. Therefore, the recovery technology is quite complicated, and the return process and flig...
Claims
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Inventor 王华光
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD