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

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 provides an optical system for a miniaturization high-precision star sensor. According to the invention, a quasi-gauss lens structure is adopted and formed by 6 lenses; all the lenses are spherical lenses; and the glass of the first lens is made of fused quartz materials so that the first lens can be immediately used for correcting image difference and can be used as protection glass of the optical system. According to the optical system is characterized by wide spectrum, large view side and large relative aperture and has quite small distortion quantity in a quite wide spectrum range and view field; the concentration degree of confusion disc energy of each view field is uniformly distributed; the imaging quality is good; the system can work at a temperature from -50 DEG C to +70 DEG C and has good image quality and defocusing amount; and posture measurement of high-precision star sensor working in severe space and temperature can be met.

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.

The invention discloses a space 3D printing system based on amorphous alloy superplastic welding. The space 3D printing system comprises a shell (1), a control unit (2), a workbench (8) arranged inside the shell (1), an amorphous alloy material (3), a heating device, a mechanical loading device (11) and a conveying device, wherein the mechanical loading device (11) controls the speed of the conveying device and the pressure load of a spray head (6) according to the material use requirements of 3D printing molding parts, and the heating device performs local heating and welding on the amorphousalloy material (3) to realize part molding. According to the space 3D printing system based on the amorphous alloy superplastic welding, the heating device only heats an area near the spray head, thecrystallization risk of amorphous alloy under a long-time high-temperature condition is avoided, and the amorphous alloy is heated to a superplastic state of a supercooled liquid phase area to realize molding, a laser or electron beam heating device is cancelled, the equipment working stability is increased, and the space 3D printing system based on the amorphous alloy superplastic welding is especially suitable for in-orbit fabrication in the space environment.

The invention provides a method for reducing transmission control protocol (TCP) message loss in a space information network. According to the method, data packet loss can be effectively reduced, link throughput can be improved, and unnecessary retransmission of a transmitting end in case of link disconnection is prevented. The method is implemented as follows: a transmitting storage module is added at a transmitting end of the TCP; according to a known motion track of a man-made satellite and a predictable characteristic of link disruption due to celestial body blocking, a communication time sequence PAB (t) between any nodes A and B is pre-arranged in the space information network with a node motion rule that can be followed, wherein when PAB (t) is equal to 1, nodes A and B are in a link communication state at the time t, when PAB (t) is equal to 0, nodes A and B are in a link disconnection state at time t; while the network operates, for any time t0, a sending node A firstly verifies the value of PAB(t0), if PAB (t0) is equal to 1, a data packet is sent to a target node B; and if PAB (t0) is equal to 0, the data packet is cached in the storage module of the TCP, and the cached data packet is extracted from the cache and is recovered and sent at next time when PAB (t) is equal to 1 and t is equal to t1.

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 relates to an ultraviolet wide angle objective lens which is used for moon exploration, comprising a front-end negative power lens (1), a rear-end negative power lens (7) and an intermediate-group lens with positive power, wherein, the front-end negative power lens (1), the intermediate-group lens and the rear-end negative power lens (7) are arranged on a same optical axis (8) in turn. The invention provides the ultraviolet wide angle objective lens which is capable of correcting aberration and distortion.

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 provides an optical system for a miniaturization high-precision star sensor. According to the invention, a quasi-gauss lens structure is adopted and formed by 6 lenses; all the lenses are spherical lenses; and the glass of the first lens is made of fused quartz materials so that the first lens can be immediately used for correcting image difference and can be used as protection glass of the optical system. According to the optical system is characterized by wide spectrum, large view side and large relative aperture and has quite small distortion quantity in a quite wide spectrum range and view field; the concentration degree of confusion disc energy of each view field is uniformly distributed; the imaging quality is good; the system can work at a temperature from -50 DEG C to +70 DEG C and has good image quality and defocusing amount; and posture measurement of high-precision star sensor working in severe space and temperature can be met.

The invention relates to a porous mask plate capable of being recognized by an APS solar sensor, which comprises a glass substrate and a film coating layer, wherein a film is coated on the lower surface of the glass substrate; at least 3 imaging pinholes are optically etched on the film coating surface of the glass substrate; the difference of the distance in at least one of the x direction and the y direction between any two imaging pinholes is not less than 20 pixels; and the side length of the square zone boundary of the imaging pinholes does not exceed d=L-2htan alpha (unit: mm), wherein L is the side length of the effective image plane of an image sensor in the APS solar sensor, h is the distance between the mask plate and the image plane of the image sensor, and alpha is the angle of field of the APS solar sensor. By adopting independent characteristics between holes in the porous array, the invention can quickly recognize contaminated pinholes, ensures high data updating rate of products, and is suitable for engineering application.

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 discloses a braided structure thin cable applied to a space solar battery array, and relates to the technical field of space solar array power transmission. The cable is characterized in that the thin cable is formed by braiding M wiring harnesses through a single layer braiding technology; each wiring harness is composed of N copper wires; the diameter range of each copper wire is between 0.02mm and 0.3mm; and M and N are natural numbers greater than two. According to the invention, the thin cable is formed by braiding M wiring harnesses through the single layer braiding technology; each wiring harness is composed of N copper wires; compared with a traditional single copper wire, the thin cable has better structural elongation; the thin cable has great adaptability for a complex thermal stress environment caused by space high and low temperature alternation; specific stress reduction measures are no longer designed; an installation process is easy; and the reliability and the safety of a product are improved.

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 relates to a polysiloxane long-acting lubricating protective paint with space environment resistance. The paint is prepared by uniformly stirring and dispersing the following componentsin parts by weight: 20 parts of epoxy polysiloxane resin, 9-20 parts of disulfide compound slurry and 1.4-6 parts of amino curing agent at the rotating speed of 2800r / min and 3500r / min, so that the solid component content is 35 + / -10%. With the lubricating protective paint adopted, the space environment resistance and wear resistance of an existing space lubricating coating can be greatly improved. The protective paint has the characteristics of favorable adhesive force to the metal substrate, favorable flexibility, favorable impact resistance, long wear resistance, excellent space environmentresistance and the like, and can effectively prolong the service life of the related equipment in the space environment.

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 an automatically adjustable field high-precision bearing platform and a leveling method. The carrying platform includes: a cabin for carrying equipment; an optical platform located in the cabin for installing an optical system, the optical platform is provided with a detection unit for detecting the orientation of the optical platform; used to support the cabin an electric cylinder for leveling the cabin body; and an electric control device for controlling the electric cylinder to level the cabin body according to the orientation information of the optical platform detected by the detection unit. The invention realizes the automatic leveling of the high-precision bearing platform in the field, solves the problem of the cleanliness of the transmission optical path and the problem of poor environmental adaptability, and provides the platform conditions for the field test of the optoelectronic equipment; The structure reference has the characteristics of high precision and convenient use.

The invention provides a method for reducing TCP (Transmission Control Protocol) message loss in a space information network, and aims at providing a method capable of reducing data packet loss efficiently, increasing link throughput and avoiding meaningless retransmission of a transmitting terminal when a link is disconnected. The method for reducing the TCP message loss in the space information network is realized through the following technical scheme comprising the steps of adding transmission and storage modules at a transmission end of a TCP; presetting a connection time sequence PAB(t) between any node A and a node B based on a known movement track of an artificial satellite and characteristics of link disconnection caused by shielding of a predictable celestial body in the space information network with a node movement rule to follow, wherein PAB(t)=1 indicates that the node A and the node B are in a link connection state at the moment t; and PAB(t)=0 indicates that the node A and the node B are in a link disconnection state at the moment t; firstly verifying the value of the PAB(t0) by the transmitting node A at any moment t0 in a network running process; if PAB(t0)=1, sending a data packet to the target node B; and if PAB(t0)=0, caching the data packet in a storage module of the TCP, wherein the cached data packet is extracted from the cache for transmission in the next moment t=t1 when the PAB (t) is enabled to be equal to 1.

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.