9results about How to "High specific stiffness" patented technology

The invention discloses a high-light-weight remote sensing camera focal plane supporting structure. The structure comprises a focal plane main bearing; the focal plane main bearing comprises a composite rod, a focal plane side support and an interface module; the three composite rods are parallel, the two ends of each composite rod are fixedly connected with the two focal plane side supports respectively, and three connecting points of the three composite rods and the same focal plane side support are distributed in a triangular shape. And the interface module is arranged on the composite rod and is used for connecting the functional module. The invention further provides a high-light-weight remote sensing camera focal plane which comprises the supporting structure, a splicing reflector, a detector, a back circuit and a thermal control module, wherein the splicing reflector, the detector, the back circuit and the thermal control module are fixed to the supporting structure. The supporting structure is high in specific stiffness, high in temperature stability and high in interface adaptability, the mechanical burden of the camera body is greatly relieved, and resources of the whole machine are saved.

The invention discloses a composite tire and a manufacturing method thereof. The method comprises surface pretreatment of a tire carcass, configuration of a tread treatment agent, and casting and molding the composite tire tread using a unique process. The method has the characteristics of simple manufacturing process and low cost. The manufactured composite tire has a series of outstanding advantages such as good elasticity, low rolling resistance, low fuel consumption, good tread wear resistance, etc., has high cost performance, and is easy to industrialize.

This invention relates to the field of polymer materials technology, specifically to a method for preparing and applying a rigid polyimide foam reinforced with aluminum honeycomb. The method for preparing the rigid polyimide foam reinforced with aluminum honeycomb provided by this invention includes steps such as surface pretreatment of the aluminum honeycomb core material and fixing the pretreated aluminum honeycomb core material into a molding die. The rigid polyimide foam material reinforced with aluminum honeycomb obtained by this invention not only possesses high specific strength and high specific stiffness, but also inherits the excellent properties of polyimide foam such as high temperature resistance, flame retardancy, low smoke, and thermal insulation. The introduction of the aluminum honeycomb skeleton also improves the material's impact resistance and dimensional stability, making it an ideal multifunctional integrated lightweight structural material with promising application prospects.

The invention relates to a preparation method of a composite wire, in particular to a preparation method of a high-specific-stiffness composite wire. The invention aims to solve the problems of high density, low specific stiffness and low strength of the existing lead. The beryllium / aluminum composite material bar subjected to hot extrusion is subjected to sheathing treatment, a multi-pass drawing method is adopted at the high temperature, the copper element is diffused into the beryllium / aluminum composite material at the core part, metallurgical bonding is formed, high interface bonding strength is achieved, and the low-density copper-sheathed beryllium / aluminum composite material composite wire is obtained; and meanwhile, the rigidity of the wire is improved through the bearing of the beryllium / aluminum composite material inner core. According to the invention, the beryllium / aluminum composite material is used as the inner core skeleton of the composite wire, so that the reinforcing effect is achieved, and the density of the wire can be greatly reduced. The specific stiffness of the prepared high-specific-stiffness composite wire exceeds 27 GPa / (g / cm < 3 >), and the conductivity exceeds 4 * 10 < 7 > S / m.

The invention provides a compact quick unfolding and locking mechanism for an air rudder, which comprises a control surface, a rudder fork and an unfolding and locking mechanism, a control surface rotating shaft hole and a rudder fork rotating shaft hole are correspondingly formed in the control surface and the rudder fork, and the unfolding and locking mechanism comprises a torsion spring and a locking device; the two ends of the torsion spring are connected with the control surface and the rudder fork in a fastening mode respectively, and when the control surface is in a folded state, the torsion spring is provided with a pre-torsion angle for providing unfolding torque; the locking device comprises a compression spring and a locking block, a clamping groove is formed in the hole wall of the control surface rotating shaft hole, and when the control surface is in an unfolded state, the locking block is inserted into the control surface rotating shaft hole and abuts against the clamping groove of the control surface rotating shaft hole. The air rudder unfolding torque is provided through the torsion spring, and the positioning and locking effects of the rudder surface and the rudder fork after the air rudder is unfolded are achieved through the locking spring and the compression spring; and by adopting an unfolding and locking integrated structure, the space volume can be reduced, the structural mass can be reduced, and the problem of uneven stress can be effectively solved.

The invention provides a modular satellite structure based on an open type grid framework and a final assembly method thereof, and belongs to the technical field of satellite structures. The problems that according to an existing method, the defects of blind operation and adhesive fixation are not fundamentally eliminated, the cable laying efficiency is low, and the weight of an outer plate is too large are solved. The thermal control protection structure comprises an open type main bearing grid framework and a plurality of thermal control protection outer plates, the open type main force bearing grid framework is a hexahedral cage-shaped framework formed by connecting six plate-shaped grid frameworks in a butt joint mode. The thermal control protection outer plates are arranged on at least one outer side face of the open type main force bearing grid framework. The plate-shaped grid frame is used for installing one side plane of the thermal control protection outer plate, and a force bearing structure of the plate-shaped grid frame is recessed inwards. The method is mainly used in the aerospace field.

The application discloses a light and small lens anti-large impact design method, which comprises the following steps: a lens group in a main bearing lens barrel is divided into multiple sections, and a pressing ring is used to press and fix the lens group; the main bearing lens barrel is provided with glue injection holes in the area of each section of the lens group, optical glue is injected to the non-working surface of the optical lens part through the glue injection holes; and glue flow grooves are arranged around the inner wall of the cylinder of the main bearing lens barrel which is matched with each section of the lens group, the glue flow grooves are communicated with the glue injection holes, and the optical lens part is stable and firm in the main bearing lens barrel. In the centering processing of the optical lens part, stress-free assembly is realized. Through the system engineering idea of "strengthening, buffering and protecting", the application overcomes the problems that the lens is broken and the optical axis is deviated due to the lens delamination, displacement or loosening of the lens under the extreme physical environment, and guarantees the reliability and imaging quality of the core optical system under the extreme physical environment.

The invention relates to a wing based on a bistable composite material. The wing comprises a main body, a wingtip and a bistable deformation connecting section for connecting the main body and the wingtip, the bistable deformation connecting section comprises a bistable composite material plate and a driving assembly, and the bistable deformation connecting section can perform bistable jumping so as to change an included angle between the main body and the wingtip; the driving assembly is an SMA spring, the SMA spring drives steady-state jumping of the bistable-state composite material plate to achieve overall bending of the bistable-state deformation connecting section, and then the angle of the wingtip is changed. Compared with the prior art, the invention has the advantages of high deformation speed, stable configuration, high specific stiffness, strong bearing capacity and the like.