68results about How to "Improve battlefield survivability" patented technology

The invention relates to a radar digital platform leveling device and method. The leveling method comprises the following steps of sensing the attitude of a vehicle body and a coordinate conversion digital platform by utilizing an attitude angle sensing system to establish a digital platform; calculating the value of an antenna azimuth code salver, the value of an antenna pitch code salver and a transverse rolling angle formed between an antenna array surface X axis and a horizontal plane which are parallel to each other during the working process of a radar; and driving an antenna to the appointed position, the pitch position and the antenna X axis attitude position to realize the radar leveling function. The leveling device comprises an attitude angle sensing system, an antenna drive control system and an antenna leveling mechanism. The attitude angle sensing system is used for sensing a transverse inclination angle and a longitudinal inclination angle of the prior vehicle body as well as an included angle formed between a reference axis of the longitudinal inclination attitude angle and the north direction; the antenna drive control system is used for converting the antenna to the appointed direction through the azimuth code salver and an azimuth driving mechanism; a supporting back frame of the antenna is pushed to rotate by a pitch driving mechanism and the pitch code salver, so that the antenna reaches an appointed pitch angle; the antenna leveling mechanism is used for pushing the antenna to carry out one-dimensional rotation around a ball bearing, so that an X axisin an antenna array surface rectangular coordinate system is parallel to the horizontal plane, thereby the leveling of the radar is finished.

The invention belongs to the technical field of intelligent monitoring of UAVs (Unmanned Aerial Vehicles), and discloses an integrated monitoring system and method oriented for multi-UAV ground station mission flight. Combined with the use requirements of multi-UAV formation cooperative operations, an intelligent human-computer interaction interface is provided and a simple and efficient monitoring method is provided for operators aimed at the characteristics of man-machine separated use scenarios of UAV operation, task/flight integrated control of an operator and single-person single-seat control over multiple UAVs, so as to solve the current problems of bloated configuration of ground station operators of the UAVs, low level of intelligent human-machine interaction, and insufficient multi-UAV cooperative control capability.

The invention discloses a device for simulating radiating capacity of an armored vehicle radiator in sand-dust environment. The device comprises a heating device and a radiator radiating capacity simulating device; a first cooling water inlet and a second cooling water outlet are formed on the heating device; the radiator radiating capacity simulating device comprises a radiator, an air flue, a feeder and a fan; the feeder, the radiator and the fan are orderly arranged in the air flue from top to bottom; a second cooling water inlet and a second cooling water outlet are respectively arranged at two sides of the radiator; the first cooling water outlet is communicated with the second cooling water inlet, and the second water cooling outlet is communicated with the first cooling water inlet.The radiating performance of the armored vehicle radiator in the sand-dust condition is researched by using the device for simulating radiating capacity of the armored vehicle radiator in the sand-dust environment, thereby providing a test condition for the design and optimization of the armored vehicle radiator, and enhancing the environment adaptability and battlefield survival ability of the armored vehicle.

The invention discloses a skin-camouflaged ointment containing a base stock, stuffing, pigments and auxiliary agents; and with respect to each 100 parts of the ointment by weight, the parts of various components by weight are as follows: 58-62 parts of the base stock, 21-23 parts of the stuffing, 15-16 parts of the pigments and 1.5-2.0 parts of the auxiliary agents. A preparation method of the skin-camouflaged ointment comprises the following steps of: carrying out fine grinding on the stuffing to obtain the fineness of more than 800 meshes; mixing the finely ground stuffing with the base stock, the pigments and the auxiliary agents at 60-70 DEG C and sufficiently stirring for 25-35 min; and cooling to the room temperature to obtain the prepared ointment. When the skin-camouflaged ointment is used, according to the relevant requirements of camouflage painting, skin-camouflaged ointments with different colors are coated on the exposed skins such as faces, necks and hands of people so as to inhibit reflection and infrared radiation features of the skins, change original outline shapes of the faces of people, effectively integrate with color patterns and near infrared landscapes of the background, thereby improving the survivability of people in battlefield. The ointment disclosed by the invention has good water resistance, air permeability, weather resistance, and skin-moisturizing performance; and the ointment is easy to wipe off, has no smell and good skin compatibility, and is applicable to camouflage painting of skins of people during training exercises and battles and also applicable to body painting or personalized skin coating decorations.

In order to prevent an electronic system from being threatened by strong electromagnetic pulses, an X-band energy selection surface is provided by the invention. The X-band energy selection surface comprises a dielectric substrate, wherein a surface structure arranged periodically is printed on the upper surface of the dielectric substrate, the surface structure comprises a series of metal square ring units distributed in an array mode, each metal square ring unit comprises a square metal outer ring, and an I-shaped metal strip group is arranged in each square metal outer ring; and each I-shaped metal strip group comprises two T-shaped metal sheets, each T-shaped metal sheet is composed of a transverse metal sheet and a longitudinal metal sheet connected between the transverse metal sheets, the longitudinal metal sheets of the two T-shaped metal sheets are oppositely arranged and are spaced by a certain distance, and a PIN diode is loaded between the longitudinal metal sheets. According to the X-band energy selection surface, X-band energy selection protection characteristics are realized for the first time, and key indexes such as insertion loss, protection effect and processing complexity are equivalent to those of a disclosed low-band energy selection surface.

The invention relates to a photonic crystal composite film with both infrared protection and anti-laser-detection functions, which belongs to the technical field of surface engineering. The photonic crystal film is designed by connecting two photonic crystal film stacks with different central wavelengths in series. For the same composite film structure, the reflectivity to an infrared heat sourceis greater than 95%, and the reflectivity to a laser detection beam is less than 5%. Thus, the requirements of weaponry for both infrared protection and anti-laser-detection functions are satisfied. Moreover, the photonic crystal composite film has a long service life, high reliability and a wide range of application, and greatly improves the survivability of weaponry on the battlefield.

The invention relates to a weapon aiming system layer fusion method applied in an AR scene; the method comprises the following steps: S1, providing a weapon aiming system, wherein the system comprises a glass and a sight, the glass and the sight communicate in a wired or wireless mode, thus realizing mutual data transmission; S2, processing the image collected by the sight of the weapon aiming system, and transmitting the image to the glass for display; S3, fusing the layers of the glass and the sight in the weapon aiming system, allowing a user to use the glass to see a real scene portion and a virtual scene portion, wherein the real scene portion is the view actually seen by human eyes, and the virtual scene portion is an overlaid layer formed by an image processing module. The method can form a virtual 3D target in a real scene, thus allowing the glass user to finish simulation training in the game interaction application field, or realizing man-gun separated real time aiming effect in the military actual combat application field and the shooting capability with the machine visual sense assistances.

The invention discloses a variant tiltrotor aircraft and a working method thereof. When the tiltrotor aircraft is in a helicopter mode, a propeller blade for providing a lifting force can automatically become longer in diameter, and meanwhile, the span of a wing becomes short, so that the flexibility of the propeller blade is improved to generate a larger lift force, the span of the wing is reduced, and the aerodynamic interference of a rotor wing to the wing is reduced; and when the tiltrotor aircraft is in a fixed-wing mode, a propeller for providing forward thrust can automatically become smaller in diameter, and meanwhile, the span of the wing becomes longer, so that the rigidity of the propeller is increased to produce larger thrust, and the span of the wing is increased to produce alarger lift force. According to the variant tiltrotor aircraft and the working method, the propeller and the wing can be optimized and matched in different flight modes according to the tiltrotor aircraft, the flight performance is remarkably improved, meanwhile, an advanced shape memory alloy material is adopted, no complex mechanical structure is required for variant, and the power of an engineis maximally utilized.

The invention provides a pilot real-time decision prediction method based on airplane survivability. The pilot real-time decision prediction method based on airplane survivability includes the following steps: determining effective emission sections and an emission-off-target relation curve of an infrared interference bomb; determining the optimal emission time of the infrared interference bomb; and instantly sending a control command of dropping the infrared interference bomb, to a pilot to enable the pilot to emit the infrared interference bomb at the optimal emission time of the infrared interference bomb. The pilot real-time decision prediction method based on airplane survivability has the advantages of predicting a real-time decision of the pilot in real time by taking the highest survivability as the target, considering the influence of data link performance on the airplane survivability and the decision of the pilot, considering the influence of working pressure of the pilot onthe final decision of the pilot, providing a specific quantification formula so as to accurately calculate the optimal time of making the decision of dropping the infrared interference bomb when theairplane is in the highest survivability state so as to notify the pilot to emit the infrared interference bomb at the optimal emission time of the infrared interference bomb in real time, maximizingthe off-target distance of the missile, and maximizing the battlefield survivability.

The invention provides an independent hydraulic drive system of an automobile. The independent hydraulic drive system of the automobile comprises a power system, an energy storage system, an actuating mechanism, a brake system and a control system. The power system comprises an engine, a clutch connected with the engine, and a motor connected with the clutch. The energy storage system comprises a storage battery pack and an energy accumulator, and the storage battery pack can be used for driving the motor to rotate. The actuating mechanism comprises a variable pump capable of being driven by the motor, and the variable pump drives another motor to rotate so that wheels can be driven to rotate. The brake system comprises a brake valve set and brakes coaxial with the wheels. The control system comprises a controller, a rotation speed sensor, a steering sensor, a pressure sensor, a gear shift switch and a brake pedal. The controller can control the engine to output kinetic energy to the outside, or control the engine to stop and make the storage battery drive the motor to rotate so that kinetic energy can be output to the outside. The independent hydraulic drive system of the automobile can achieve infrared silence of the automobile, automobile speed regulation in an ultra-large range, automatic gear shifting and energy recycling.

Disclosed is an axial-flow type thermoelectric device. A turbo type burner, a heat exchanger and a motor are adopted, a power generator is driven to be started by means of rotation of a turbine of the burner, and hot air of the burner pushes an axial power turbine in the power double-layer heat exchanger to drive the power generator. Water jackets are arranged outside the burner, a flame chute and a volute casing and on the heat exchanger and connected with a radiator to provide a heating source. Auxiliary power is provided for the power turbine besides the action of the hot air of the turbo type burner, and the utilization rate of energy is increased. The axial-flow type thermoelectric device can be used in small or confined space to serve as a heating and power generation device in a tank or armored car and the like and can also serve as a power generation and heating device independently for outdoor camping and on an island or frontier sentry and the like. The axial-flow type thermoelectric device is simple in structure and low in production cost and has promotional value.

The invention provides a biaxial rotation modulation initial fine alignment method. The method comprises the steps: acquiring the latitude and elevation information of the position where the carrier is located, completing the coarse alignment process of the system, and executing the fine alignment process based on the navigation calculation result. The method mainly solves the problems that in thefine alignment process, due to the fact that constant zero offset of an inertial device in an error model is not completely observable, and the convergence speed is low. By introducing the double-shaft rotation modulation mechanism, an error model can be improved to meet completely observable conditions, so the precision and reliability of an alignment result are ensured. By shortening the discretization time and increasing the length of the observation sequence in unit time, richer observation information is obtained, the convergence time of the equivalent sky-oriented gyroscope constant zero offset estimation sequence is greatly shortened, and the rapidity of initial alignment is improved. By optimizing the updating method of the discretization error model, the problem that the calculation complexity is increased due to the fact that the filtering period is shortened is solved. In combination with the three parts, the patent provides a rapid and high-precision biaxial rotation modulation initial fine alignment method with high engineering practicability.

The invention discloses a motorized integrated anchoring chassis. The motorized integrated anchoring chassis comprises locking screws, fixed lug pieces, accessory boxes, front supporting legs, automatic leveling supporting legs, cable boxes, overturning supporting legs, supporting leg fixing rods, a protective cover, a slewing bearing, bearing supporting legs, axle tires and a chassis longitudinal beam. The front supporting legs, the automatic leveling supporting legs, the two overturning supporting legs and the bearing supporting legs can be folded when the motorized integrated anchoring chassis is transported, and the overturning supporting legs are folded in the direction of a tractor. According to the motorized integrated anchoring chassis, the platform functionality, the maintainability and man-machine engineering are integrated, and integrated design, environmental adaptability design, rapid expansion erection design, automatic leveling design and safety design are conducted; the high motorizing performance of the anchoring chassis and reliable integrating of a slewing upper tool and the anchoring chassis are achieved; the erection and deployment time is effectively saved; and the working efficiency is improved.

The invention discloses a mine thrower quick firing and training detecting device. The device comprises a first display control device, a positioning orienting device, an angular transducer, an encoder, a second display control device, a processor and a communication circuit. The positioning orienting device is used for measuring the gun position coordinates and firing direction. The angular transducer is used for measuring the firing angle. The encoder is used for measuring the firing direction adjustment amount. The processor is used for resolving firing data. The display control devices areused for inputting information and displaying aiming circumstances and firing parameters. At the same time, the invention discloses a firing method and a training detecting method. According to the mine thrower quick firing and training detecting device, the firing method and the training detecting method, the quick reaction capability and attack precision of a mine thrower can be improved, the battlefield survivability of a gunner is improved, and the mine thrower quick firing and training detecting device can continue working when satellite signals are interrupted or interfered and is simple in structure, easy and convenient to operate, low in cost and applicable to mine throwers of all calibers; and by changing a firing table and appropriately adjusting the mounting mode, the device can be also widely applied to a large number of other types of artilleries without digital operating systems in service in troops, and the device is of important value to improvement of the combat effectiveness of the troops.

The invention aims to provide an aircraft S bend and embedded type combination air inlet channel. The combination air inlet channel comprises an actuating device, a sealing gasket, an air inlet channel jettison section, a breakable connecting device, an embedded type air inlet channel, an engine and an aircraft body. The air inlet channel jettison section is fixed on the outer portion of the aircraft body through the actuating device and the breakable connecting device and is in sealed butt joint combination with the embedded type air inlet channel through the sealing gasket on an air inlet channel jettison section flange to form an S bend air inlet channel. At a small flow starting period and a cruising period, an aircraft supplies gas to the engine through the S bend air inlet channel formed by combining the air inlet channel jettison section and the embedded type air inlet channel. When the aircraft is at a penetration period, the air inlet channel jettison section is discarded, and gas is supplied to the engine through the embedded type air inlet channel. The aircraft S bend and embedded type combination air inlet channel is simple in structure and convenient to use and has the advantages that the air inlet channel is good in reliability at the small flow starting period, high in total pressure recovery coefficient at the cruising period, good in stealth capability at the penetration period and high in battlefield survivability.

The invention provides a preparation method of a high anti-elastic aluminum alloy plate. The preparation method comprises the following steps that S1 an aluminum alloy ingot is prepared into an aluminum alloy plate through an extrusion method; according to the mass percent, the aluminum alloy ingot comprises the following chemical compositions including 8.2%-8.8% of Zn, 2.0%-2.5% of Cu, 2.0%-2.6%of Mg, 0.15%-0.30% of Zr, 0.1%-0.3% of CeO2 , not larger than 0.10% of Fe, not larger than 0.07% of the sum of Cr and Ti and the balance Al. The preparation method has the beneficial effects that theprepared aluminum alloy plate has ultra-high anti-elastic performance and excellent stress corrosion resistance. The battlefield survivability of armored vehicles can be improved, the weight of a vehicle body is reduced, and the mechanical performance is improved.

A dual-frequency energy selection surface is a dual-frequency space self-adaptive energy selection surface working in a C wave band and an S wave band at the same time and comprises a dielectric substrate, wherein a surface structure arranged periodically is printed on the upper surface of the dielectric substrate, the surface structure comprises a series of metal units distributed in an array mode, each metal unit comprises two rectangular metal rings which are oppositely arranged in parallel, namely a first metal ring and a second metal ring, a certain distance is formed between the two metal rings, the distance is the distance between two adjacent long edges of the first metal ring and the second metal ring, and the first metal ring and the second metal ring are the same in length and different in width; and a notch is formed in each of the first metal rings and the second metal rings, the two metal rings are respectively disconnected, and the notches of the first metal rings and the second metal rings are respectively connected through loading diodes and lumped capacitors. According to the dual-frequency energy selection surface, the frequency selection characteristic of incident electromagnetic waves and the energy selection characteristic of sensing electromagnetic energy are realized.

The invention relates to a deformable aircraft, as well as a use field and the application thereof, and provides a structural design scheme, a structural design method and the application of a novel deformable aircraft. According to the scheme and the method, a telescopic mechanism and a rotatable mechanism are spatially arranged and combined; a radar reflector is applied to a mechanism; a fuel gas power device is applied to the mechanism; and a foldable high-temperature-gas-resistant special textile fabric is applied to the mechanism. After the aircraft is unfolded, the aircraft can generate an infrared characteristic and has an appearance characteristic of an aircraft body; the product produces a flight accompanying product with the same size as an aircraft platform, can be used for protecting the platform, and can also be used for specific performance purposes; the method is used for a specific product which needs to simulate the same characteristics of medium and remote monitoring and display of an original aircraft platform. The structural design scheme and the method of the deformable aircraft are mainly applied to all aircraft platforms (including various water surface ships and boats and ground mobile platforms), including unmanned or manned aviation aircrafts, such as transport aircrafts, helicopters, fighters, bombers, aerospace crafts, manned spacecrafts and the like.