186 results about "Military standards" patented technology

Systems and methods to provide multi-layer visibility of nested containers at a mobile checkpoint are disclosed. Thee systems include a portable deployment kit in communication with a nested container. The portable deployment kit can be contained in a durable carrying case having a total weight that is within military standards for carrying by one person and includes a handle. Inside, the carrying case can include foam or other material to protect internal components during transport and deployment. In use within the system, the portable deployment kit can serve as a self-contained checkpoint or site server for gathering necessary information from the nested container and uplinking for centralized data collection. In one embodiment, the portable deployment kit includes a label printer for updating an identification device on the nested container to reflect, for example, aggregation and deaggregation.

The wireless video game controller is a 1:1 scale realistic replica Air soft gun, of a weapon, such as a US military standard issue assault rifle or machine gun. An M16, M4, or other such realistic replica having realistically operational moving mechanical parts may function as a wireless video game controller when equipped with a wireless video game controller having switch placement that facilitates electrical and mechanical interaction between the switches and the operational moving mechanical parts of the gun replica. Moreover, joystick and pushbutton wireless game controls are disposed on portions of the gun that are ergonomically consistent with a gun user's stance and hand positioning when handling and firing the weapon. Programmable buttons are optionally provided and placement of the programmable buttons is consistent with the inventive game controller's ergonomic design.

The invention discloses a HoloLens-based battlefield situation construction and interaction implementation method. The method sequentially comprises the following steps of 1, firstly, sequentially constructing a terrain model, a three-dimensional object model and a three-dimensional military standard, and then adopting the mode of combining geometric characteristic optimization and grain optimization for performing model optimization; 2, sequentially achieving the purposes of battlefield situation dynamic showing fluency and authenticity and the purpose of three-dimensional virtual-real fusion; 3, performing user interaction. The method can achieve construction and interaction according to user identity roles, operation habits, interaction action tendencies and other natural human-machine interaction holographic battlefield situation electronic sand table information, the situation awareness fidelity and immersion can be enhanced, the method can intelligently and efficiently provide the imaginable and visual battlefield situation and visualized information interaction interface for commanders and the staff, and the method is used for supporting construction of intelligent information service systems of future advanced command posts with different fight persons and different operation patterns.

The invention relates to a porous membrane having a particle filtration value of at least 10 under U.S. Military Standard MIL-STD-282 (1956), where the porous membrane is a polyethylene membrane. The membranes according to the invention are particularly useful for filters such as ASHRAE filters, HEPA filters and ULPA filters for example in heating, ventilating, respirators and air conditioning applications.

The invention discloses a film system of an infrared double-waveband antireflection film system and a plating method thereof, belonging to a manufacture technology of optical films. The film system comprises six layers of films or eight layers of films, preferably six layers of films which are a Ge film, a ZnS film, a Ge film, a ZnS fillm, a YbF3 film and a ZnS film in sequence from inside to outside, wherein the optical thickness of each layer of films is 895 nm, 306 nm, 422 nm, 1626 nm, 770 nm and 200 nm in sequence from inside to outside. The plating method comprises the following steps: firstly, cleaning a plated part; then roasting a substrate; and plating the Ge film, the ZnS film, and the like in sequence. The transmittivity of the optical part obtained by the film system and the plating method in two waveband ranges of 3.7 microns-4.8 microns and 7.7 microns-10.5 microns is larger than 98 percent, and the adhesion force and the environmental adaptation of the film layers meet the requirements specified by a Chinese military standard GJB2485-95.

The invention discloses a semi-hard high-flame-retardant oil-proof thermal shrinkage tube. The material for preparing the thermal shrinkage tube comprises the following components in parts by weight: 100 parts of polyethylene and ethylene vinyl acetate copolymer, 0 to 30 parts of ethylene terpolymer, 30 to 150 parts of a fire retardant, 0.2 to 3 parts of a lubricant, 0.1 to 3 parts of a sensitized crosslinking agent, 0.3 to 3 parts of an antioxidant and 0 to 10 parts of a color master batch. The semi-hard high-flame-retardant oil-proof thermal shrinkage tube has a good flame-retardant effect, meets an ROHS environmental protection requirement, has a better oil-proof effect and can meet a standard requirement of an American military standard (SAE-AMS-DTL-23053/6), and the flame retardant rating of the thermal shrinkage tube can reach an American UL224 VW-1 standard.

The invention relates to a cooling liquid composition which is mainly applied to the field of aircrafts. The cooling liquid composition comprises base oil, antioxidant, preservative, and anti-foaming agent. The cooling liquid composition provided by the invention completely meets the index requirements of US Military standard MIL-PRF-87252, is high in dielectric strength, and has the capacity of cooling a component in a refrigerated plate way instead of an immersion way.

An electrical connector for testing of a missile launch rail is provided. A stationary housing is combined with a coupling ring to form an outer housing. An internal plunger is housed in the outer housing and spans the length of the outer housing. The stationary housing anchors to the missile launch rail, while the coupling ring is free to rotate about the internal plunger. The coupling ring is rotated via a hand grasp. The coupling ring rotation translates into forward and aft movement of the pin assembly. The connector provides forward and backward stops for limiting pin insertion and extraction moves to desired distances. Rotation via triple-start threads readily overcomes insertion and extraction resistance of a bulky multi-pin assembly and provides a smooth and controlled electrical connection. The size of the connector approaches that of a small conventional military standard 38999 series III connector.

The invention discloses a vacuum electron beam welding method for refractory alloy. The vacuum electron beam welding method for refractory alloy specifically comprises the steps of treatment of a weld face, preparation before welding, assembling, electron beam welding, and quality checking after welding. The vacuum electron beam welding method for refractory alloy has the characteristics that a vacuum electron beam welding environment is utilized, the penetrability is high, energy is centralized, and heat input is small; Nb521 niobium alloy with the thickness being 12 mm can be welded, and the welding performance is stable. Formation of a weld joint after welding is good, defects including cracks, air holes, pits, undercuts, weld lumps and the like of the surface of the weld joint are avoided, the internal welding quality is good, all normal-temperature mechanical properties can meet the national military standard requirements, and the high-temperature performance is good.

The invention relates to a preparation technique for spacecraft-solar-cell-array-interconnection-sheet-used molybdenum/platinum/silver/ layered metal matrix composite materials. The technique comprises the steps of pretreatment of Molybdenum metal foils, platinum plating of molybdenum metal surfaces, molybdenum/platinum electroplating sample annealing, silver electroplating of molybdenum/platinum layered annealing sample surfaces, annealing of molybdenum/platinum/silver electroplating samples, scanning electron microscope observation of molybdenum/platinum/silver layered metal matrix composite material surface morphologies, Auger spectroscopy analysis along the depth and resistor spot welding tensile strength testing. According to the invention, diffusion infiltrating happens in a molybdenum/platinum interface and a platinum/silver interface, so that metallurgical bonding is realized in the molybdenum/platinum interface and the platinum/silver interface, and relatively high interface bonding intensity is realized. The molybdenum/platinum/silver/ layered metal matrix composite materials with the high interface bonding intensity and high welding tensile strength are obtained. The welding tensile strength of the molybdenum/platinum/silver/ layered metal matrix composite materials when in spot welding with a solar cell single spot resistor is 324gf, and a welding strength index prescribed by China military standard GJB2602-1996 is exceeded.

The invention discloses an optimization method for electromagnetic compatibility fault repair by adopting electromagnetic compatibility test over-standard strategies. In the method, a conducted emission curve, a conducted susceptibility curve, a radiated emission curve and a radiated susceptibility curve are used and are respectively compared with requirements of national military standards to obtain over-standard areas; according to electromagnetic vulnerability weights of different frequency ranges, an area weighted integration method is adopted to quantify the over-standard areas to obtain respective weights; and finally the respective weights are introduced to obtain electromagnetic compatibility weight expected values of helicopter-borne equipment. By virtue of index quantification and weight allocation, the electromagnetic compatibility interference faults of the helicopter-borne equipment are associated with the electromagnetic compatibility of the entire helicopter, factors such as electromagnetic compatibility conducted emission, conducted susceptibility, radiated emission, radiated susceptibility and electromagnetic compatibility classification of all helicopter-borne equipment are comprehensively considered, the index quantification and the corresponding weight allocation are conducted to obtain degrees of influence of the electromagnetic compatibility interference faults of the helicopter-borne equipment on the electromagnetic compatibility of the entire helicopter are obtained, the priorities of the repair sequences of the electromagnetic compatibility interference faults of the helicopter-borne equipment are determined and a basis is provided for determining sequences for electromagnetic compatibility rectification.

The invention relates to a mutual non-solid-solution system metal infiltration process and device based ion implantation radiation damage. The process comprises the following steps of polishing and ultrasonic cleaning of pure tungsten metal, vacuum drying, silver metal plasma implantation, tungsten metal surface vacuum evaporation silver coating, vacuum drying, argon protection silver infiltration, hot-pressing infiltration supplementation, section scanning electron microscope (SEM) observation of a tungsten/silver composite metal material, section line scanning component analysis, Auger energy spectrum analysis of components along the material depth, welding strength test when the tungsten/silver composite metal material is used for spot-welding electrodes, and SEM observation of welding head tensile fractures. In the invention, a metal plasma implantation technology is utilized to combine with the vacuum evaporation technology, the high-temperature silver infiltration technology and the hot-pressing infiltration supplementation technology, thus silver metal is successfully infiltrated to the surface of a metal tungsten workpiece to prepare the tungsten/silver composite metal material. Test results show that when a tungsten/silver composite metal material electrode is utilized to carry out resistance spot welding on a silver metal interconnection sheet and an aerospace craft solar cell sheet, the single-spot welding strength is up to 450gf which excesses Chinese military standard and current enterprise standard, and the welding head tensile fractures is determined to be ductile fractures through SEM analysis.

The invention discloses a method for testing accurate multifrequency and synchronous synergetic conduction sensitivity at high speed, which comprises the steps: firstly, a testing frequency from 10 kHz to 18 GHz is dispersed according to a frequency step length which conforms to a GJB sensitivity testing requirement to ensure a testing frequency point; the whole testing frequency is grouped from low to high beginning from a starting frequency, and each group has N frequency points; then, an arbitrary waveform generator is controlled to output N frequencies once and switch the frequencies according to group steps; the frequency groups are scanned, if a tested device is sensitive, the frequency group is scanned point to point to determine the sensitive frequency point, and the sensitivity threshold level of the frequency point is determined according to a military standard single-point testing method; the frequencies are switched according to a group stepping mode, each group of frequencies integrally step according to the N delta f step length equivalently, and the next group of multifrequency signals is output until a whole frequency band is scanned completely. The method can synchronously test a plurality of frequently points by scanning once, automatically realize the step scan according to the groups, greatly increase the testing efficiency of the sensitivity test and can quickly diagnose the failures of the sensitive points.

The invention provides a fault diagnosing and tolerance control method for aircraft longitudinal movement. The method comprises the following steps of according to a model and a state combination index discriminant when an aircraft has no fault, carrying out the fault diagnosing; and when the aircraft has a fault, firstly, classifying the fault, analyzing the influence of the whole-aircraft parameters and the flight dynamic properties according to the determined fault type, and remodeling an abrupt-change system after the fault occurs, so as to obtain a new model description when the aircraft has the fault. The design method of a tolerance controller is characterized in that the output of a fault-free model can meet the requirements of military standards by the designed control amount; and when the aircraft has the fault, the new model output is stable by the control input which is formed by the control amount and the non-artificial additional control amount caused by the aircraft fault.

Disclosed a blood tank for counter strike and wild war comprises a thermocomplex and a heat-insulated container as main body. It ultimately solves the problems of heat dissipation, thermal difference, and heat insulation which prevent the refrigeration function of semi-conduct by promoting the effect of refrigeration to 40 % that has been over the military standard, therefore can transmit and store blood in long time. It realizes heat preservation with changing battery in little power, while freeing from external power and mechanical carrier. The invention provides conventional, portable, and blood sampling blood tank, which can apply the various kinds of actual combat in modern war.

The invention discloses an optimization method for conducted interference fault correcting by using a conduction test standard-exceeding strategy. A conducted emission curve and a conducted susceptibility curve are used for being compared with national military standard requirements, and a standard-exceeding area is obtained; area integral is adopted for quantizing the standard-exceeding area to obtain conducted emission index weight and conducted susceptibility index weight; and finally airborne device electromagnetic compatibility classification weight, the conducted emission index weight and the conducted susceptibility index weight are combined to obtain airborne device electromagnetic compatibility classification weight expectation. The optimization method combines airborne device electromagnetic compatibility conducted interference fault and electromagnetic compatibility of a whole plane by means of index quantization and weight distribution, gives overall consideration to factors such as all airborne device electromagnetic compatibility conducted emission, conducted susceptibility and electromagnetic compatibility classification, conducts index quantization and corresponding weight distribution, obtains affecting degree of airborne device conducted interference fault on the electromagnetic compatibility of the whole plane, determines priority of an airborne device electromagnetic compatibility conducted interference fault correcting sequence, and provides proof for determining a sequence of electromagnetic compatibility rectification.

The invention discloses an artificial plate with an electromagnetic shielding function and a manufacturing method thereof. The artificial plate is prepared from a wooden/bamboo single plate and an aniline prepolymer, wherein the aniline prepolymer is subjected to in-situ polymerization in a wooden/bamboo single plate substrate to form conductive polyaniline macromolecules and adopts a double-layer structure; a surface layer is a polyaniline-containing wooden/bamboo single plate, and a bottom layer adopts a wooden plywood, a medium (high)-density fiber plate or a chipboard. The artificial plate has the advantages that characteristics of wood and polyaniline are fully used; the wooden artificial plate is used as a base material, and a wooden/bamboo material with the polyaniline is laminated on the surface layer of the base material, so that the novel wooden artificial plate with a conductive function is prepared. The artificial plate has the self performance feature of the wooden material, and the electromagnetic shielding efficiency of the artificial plate is up to 32.78-49.35dB under a shielding efficiency test within a frequency range of 5-1,500KHz according to a military standard (GB-SJ20524-1995) of the electronic industry in China.

The invention provides a fault diagnosing and tolerance control method for an aircraft large-angle-of-attack movement quaternion model. The method comprises the following steps of according to a model and a state combination index discriminant when an aircraft has no fault, carrying out the fault diagnosing; and when the aircraft has a fault, firstly, classifying the fault, analyzing the influence of the whole-aircraft parameters and the flight dynamic properties according to the determined fault type, and remodeling an abrupt-change system after the fault occurs, so as to obtain a new model description when the aircraft has the fault. The design method of a tolerance controller is characterized in that the output of a fault-free model can meet the requirements of military standards by the designed control amount; when the aircraft has the fault, the new model output is stable by the control input which is formed by the control amount and the non-artificial additional control amount caused by the aircraft fault; and the fault diagnosing and the tolerance control can be directly carried out on the aircraft large-angle-of-attack flight.

The invention discloses a super-huge type multi-layer full-automatic sliding swing rainfall test device, which comprises a PLC (programmable logic controller) full-automatic control system, a base, a main column, a plurality of lateral branch pipes distributed along the main column at vertical intervals and a sliding swing mechanism. The main column is a main water supply pipe, each branch pipe is connected with the main column through a rocker arm in a swinging mode is and provided with a plurality of catapulting drop type spray nozzles which can spray discontinuous water drops with diameter of 0.5 to 4.5 mm; a driving device of the sliding swing mechanism drives a upper push-pull rod and a lower push-pull rod to ascend and descend, the upper push-pull rod and the lower push-pull rod drives each branch pipe to make horizontal arc swing in a range of 30 degrees upwards to 45 degrees downwards under the traction of the rocker arms through push-pull connecting rods, so that a vertical component and a horizontal component of the rainfall reach the technical requirements of the military standard and the national standard. The super-huge type multi-layer full-automatic sliding swing rainfall test device is particularly suitable for rainfall tests of large-scale devices, high-voltage devices, military devices, sky weapons and the like.

The invention discloses a method for confirming anti-high RF interferece threshold of electronic information equipment, which acquires the response rule of the electronic information equipment under asmall signal and low field density environment through an experiment method to extrapolate the response condition under the high RF environment and confirms the anti- interferece threshold accordingto the performance parameter of the equipment. The invention can accurately confirm the anti-high RF interferece threshold under the condtion that the prior laboratory condition can not simulate the high RF environment, provides a method for the electromagnetic compatibility evaluation and the military standard of the corresponding country of the equipment, and has simple method and easy operation.

The invention relates to a movable pump pressure type atomized fuel water distribution device and a water distribution method. The movable pump pressure type atomized fuel water distribution device comprises four subsystems including a saturated fuel water distribution subsystem, an oil and water separation subsystem, a super-saturated water distribution subsystem and a control subsystem accordingto functions. The saturated fuel water distribution subsystem comprises a quick-release connector a (1), a quick-release connector b (11), a moisture tester a (2), a water tank a (3), a water injection pump a (4), an atomization spray nozzle a (5), a control valve a (6), a flow sensor a (7), a pressure sensor a (8), a temperature sensor a (9) and a static mixer a (10). The water distribution method for distributing water by the aid of the movable pump pressure type atomized fuel water distribution device mainly includes two steps of preparing saturated fuel; preparing super-saturated fuel. The movable pump pressure type atomized fuel water distribution device and the water distribution method have the advantages that the movable pump pressure type atomized fuel water distribution device can be quickly connected with test heat preservation fueling trucks and test storage fueling trucks by the quick-release connectors, can be automatically controlled and is easy to operate; the movablepump pressure type atomized fuel water distribution device and the water distribution method are accurate in water distribution proportion owing to the water injection micro-pump and a water flow control system, and accordingly index requirements of national and military standards can be met.

An anchored 522 male electrical connector is provided. A stationary housing 520 is combined with a coupling ring 540 to form an outer housing. An internal plunger 560 is housed in and spans the length of the outer housing. The stationary housing 520 mounts onto an anchoring surface via an anchor mount 522, while the coupling ring 540 is free to rotate about the internal plunger 560. The coupling ring is rotated via a hand grasp 441. The coupling ring rotation 442, 443 translates into forward and aft movement of the pin assembly 515. The connector provides forward 520-1 and backward stops 520-4 for limiting pin insertion and extraction moves to desired distances. Rotation via triple start threads 548, 525 readily overcomes insertion and extraction resistance of a bulky multi-pin assembly 515 and provides a smooth and controlled electrical connection. The connector may be sized to meet multi-pin connector needs or military standards.

The invention provides a fault diagnosing and tolerance control method for an aircraft large-angle-of-attack movement ternary number model. The method comprises the following steps of according to a model and a state combination index discriminant when an aircraft has no fault, carrying out the fault diagnosing; and when the aircraft has a fault, firstly, classifying the fault, analyzing the influence of the whole-aircraft parameters and the flight dynamic properties according to the determined fault type, and remodeling an abrupt-change system after the fault occurs, so as to obtain a new model description when the aircraft has the fault. The design method of a tolerance controller is characterized in that the output of a fault-free model can meet the requirements of military standards by the designed control amount; when the aircraft has the fault, the new model output is stable by the control input which is formed by the control amount and the non-artificial additional control amount caused by the aircraft fault; and the fault diagnosing and the tolerance control can be directly carried out on the aircraft large-angle-of-attack flight.