35results about How to "Good space environment adaptability" patented technology

The invention relates to a spaceborne Kovar / silver metal laminated composite material and a preparation method thereof. The composite material comprises a Kovar alloy foil piece and two pure silver foils, and is characterized in that the pure silver foils acting as surface layers and the Kovar alloy foil piece acting as an interlayer form a laminated sandwich structure, and the top, middle and bottom layers form chemical bonds through rolling and bonding so as to be connected into an integral whole. The preparation method comprises the steps of laminating the pure silver foils and the Kovar alloy foil piece into a combined blank with a sandwich structure according to a sequence of the pure silver foil, the Kovar alloy foil piece and the pure silver foil; performing hot rolling and composite bonding on the combined blank; performing further annealing processing at the atmosphere of an inert gas after rolling and bonding, and acquiring a spaceborne Kovar / silver metal laminated composite material after annealing processing. The composite material has good space environment adaptability, thermal conductivity, electrical conductivity and weldability, and meets requirements of space electronic packaging applications; and the spaceborne Kovar / silver laminated composite material is simple in production process, sable and controllable in quality, convenient to operate and capable of realizing large-area automatic roll-to-roll batch production.

A symmetrical piezoelectric-driven two-dimensional directional adjusting mechanism and a rotating platform angle adjusting method are provided. The invention relates to a piezoelectric driving deviceand an adjusting method. The symmetrical piezoelectric-driven two-dimensional directional adjusting mechanism comprises a rotating platform, a base, universal flexure hinges and four displacement amplifying units. Each displacement amplifying unit is mainly composed of a triangular amplifying structure and a piezoelectric ceramic actuator. The universal flexure hinges and the triangular amplifyingstructures are arranged between the rotating platform and the base. The rotating platform angle adjusting method comprises the following steps: gasless connection is carried out on the symmetrical piezoelectric-driven two-dimensional directional adjusting mechanism, and after installation, the initial height displacement deviation of the two symmetrical universal flexure hinges of the rotating platform is measured by using a laser displacement sensor; and then, the angle of the rotating platform is adjusted, and when the work is finished, the piezoelectric ceramic actuators are powered off and restored to the initial state. The symmetrical piezoelectric-driven two-dimensional directional adjusting mechanism and the rotating platform angle adjusting method are applied to the field of precision directional positioning and laser communication in a space environment.

The invention relates to a method for manufacturing a micromechanical shutter, which comprises the following steps of: 1) selecting a stainless steel substrate, preparing a layer of positive photoresist on the upper and lower surfaces of the substrate respectively, and pre-curing the photoresist; 2) exposing a rectangular hole array serving as a mask, wherein the pre-cured photoresist on the lower surface is not exposed; 3) developing the substrate, finishing full curing of the photoresist, then performing corrosion, removing the photoresist and cleaning the substrate; 4) spraying the positive photoresist on the upper and lower surfaces of the substrate, and pre-curing the photoresist; 5) on the photoresist on the lower surface of the substrate, exposing a twist beam type shutter corroding pattern array serving as a mask, wherein the upper surface of the substrate is not exposed; 6) developing the substrate, finishing full curing of the photoresist, then performing corrosion, removingthe photoresist and cleaning the substrate; 7) manufacturing a shutter substrate; and 8) assembling and fixing the shutter blade structure and the substrate, and finishing upper and lower electrode leads. According to the method, the stainless steel is used as a structural material, so the micromechanical shutter has longer service life and higher reliability.

The invention discloses an intelligent detection circuit suitable for redundant magnetic latching supply and distribution lines. Test design is performed by a supply and distribution control line formed by magnetic latching relays KZ1 to KZ4, and a parallel control line is independently led out in a single machine. A bridging mode is achieved in a system so that a supply and distribution system can have more independent control nodes in unit testing. Without the addition of a special test wire, different combined logic control is performed on four signal control ports in the testing including a switching-on control port 1, a switching-on control port 2, a switching-off control port 1, and a switching-off control port 2. Simultaneously, voltage detection is performed on the power supply end of an instrument so as to achieve status confirmation of each relay contact of the KZ1 to KZ4 and achieve 100% measurement of the on-off states all contacts of the control paths.

The invention relates to an optical system for a star sensor. The optical system is applied to high-precision star sensors. The optical system is of an improved peaceful structure and consists of six lenses, wherein the six lenses are all spherical lenses; an aperture diaphragm is arranged on first glass; the first glass is made of fused quartz, can be used for correcting aberration and can be used as protective glass of the optical system. The optical system has the characteristics of wide spectrum, large visual field, relative large aperture and the like; the distortion is very low in relatively large spectral range and visual fields, concentration ratios of discs of confusion of each visual field are uniformly distributed, and the imaging quality is good. The optical system can work in a temperature range from -40 DEG C to 50 DEG C, has good image quality and defocusing amount at each temperature point and can meet attitude measurement requirements of the high-precision star sensors working at severe space temperature environments.

The invention provides a label for pasting a satellite surface. The label is mainly composed of a thin film base, a paint film layer, a transparent emissivity adjusting layer and a transparent anti-static layer, wherein the paint film layer is stuck on the thin film base; the transparent emissivity adjusting layer and the transparent anti-static layer are plated on the paint film layer; and the transparent emissivity adjusting layer is arranged between the transparent anti-static layer and the paint film layer. According to the label for pasting the satellite surface, a high-emissivity transparent thin film material and a conductive transparent thin film material are prepared on the surface of a paint film by a magnetron sputtering method, so that the paint film has high emissivity and anti-static performance.

The invention relates to molybdenum / titanium / silver metal layered composite material used for space and a preparation method thereof. The composite material comprises a layer of pure molybdenum foil; two layers of pure titanium foils; and two layers of pure silver foils, wherein the foils are laminated into a similar "sandwich" structure according to the order of the pure silver foil, the pure titanium foil, the pure molybdenum foil, the pure titanium foil and the pure silver foil and connected as a whole, and the molybdenum-titanium interface and the silver-titanium interface are chemically and metallurgically bonded. The preparation method comprises the steps that a combined blank material of the similar "sandwich" structure is formed by orderly lamination; hot rolling composite connection is performed on the combined blank material, and annealing processing is further performed under the atmosphere of inert gas after hot rolling; and the molybdenum / titanium / silver metal layered composite material used for the space is obtained after annealing. The composite material has great space environment adaptability, thermal conductivity, electrical conductivity and weldability so as to meet the requirements of the space electronic packaging application; and the preparation method of the composite material realizes formation through hot rolling composite connection so that the manufacturing technology is simple, the quality is stable and controllable, operation is convenient and large-area automatic roll-to-roll batch production can be realized.

The invention provides a dual-channel optical fiber rotary connector with long space life and solves the problems of low service life, large loss, easy failure and complex structure of the existing dual-channel optical fiber rotary connector. The optical fiber rotary connector includes a stator housing, a rotor sleeve, a central one-channel unit, a central two-channel unit, a front end cover and a rear end cover; the stator housing is a sleeve structure, and the rotor sleeve is installed in the cavity of the stator housing through a bearing assembly The front side of the body, the front end cover is arranged on the front end of the rotor sleeve, and the rear end cover is arranged on the rear side of the cavity of the stator housing; the central channel unit includes the first rotor pigtail arranged coaxially in sequence, and a channel incident light collimator component, optical system beam expander component, optical system coupling component, one-channel receiver and the first stator pigtail; the center two-channel unit includes the first rotor pigtail, two-channel incident light collimation component, two-channel receiver and the first Two stator pigtails.

The invention relates to a high-damping heat deformation release device which comprises a base (1), an elastic element (2), a shell (3), a damping element (4) and a connection base (5). The lower end of the elastic element (2) is fixedly connected with the base (1), the elastic element (2) is perpendicular to the base (1), the upper end of the elastic element (2) is fixedly connected with the connection base (5), the rigidity of the elastic element (2) in the direction perpendicular to the base (1) is larger than the rigidity of the elastic element (2) in the direction parallel to the base (1), the shell (3) is connected with the base (1) and used for wrapping the elastic element (2), the space between the elastic element (2) and the shell (3) is filled with the damping element (4), a gap exists in the contact face between the damping element (4) and the elastic element (2), the gap is used for adjusting the contact area of the damping element (4) and the elastic element (2), and the volume ratio of the gap in the damping element (4) is inversely proportional to the damping coefficient of the damping element (4) and the rigidity of the elastic element (2).

The invention discloses a packaging method for a weaving-structured thin cable for a space solar battery array. The packaging method is characterized by comprising the steps of 1, performing installation position positioning; 2, performing surface treatment on a packaging position; 3, performing blade coating of a packaging material; 4, performing cable cleaning and forming; 5, performing primary packaging of the cable; and 6, performing secondary packaging of the cable. By adoption of the technical scheme, the packaging dimensions and positions of the weaving-structured thin cable can be effectively controlled, so as to satisfy use requirements on cable packaging thickness by special space models; the thickness is not greater than 0.3mm after a cable with the thickness of 0.2mm is packaged; the packaging material adopted by the packaging method is high in high-temperature characteristic and low-temperature characteristic; and the packaged weaving-structured thin cable can keep high structural growth rate in a track working condition, and is high in adaptivity to a complex thermal stress environment caused by space high temperature and low temperature alternation, so that the reliability and safety of the product are improved.