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31results about How to "Improve drop point accuracy" patented technology
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Differential game anti-interception maneuver penetration/accurate strike guiding method with falling angle constraint
ActiveCN105759612AThe drop angle constraint satisfiesPenetration misses a large amountAdaptive controlCountermeasureDynamic models
A differential game anti-interception maneuver penetration / accurate strike guiding method with falling angle constraint comprises the following three steps: 1, building a three-body differential game model, wherein a dynamic model of three belligerent parties, a linear belligerent model of three belligerent parties, and a three-body differential game model are included; 2, performing reduction of dimensionality for the original three-body differential game model to obtain a new three-body differential game model; and 3, solving the new three-body differential game model based on the optimal control theory to obtain the optimal control law of a missile. Through adoption of the above steps, the differential game anti-interception maneuver penetration / accurate strike guiding method with falling angle constraint is achieved. According to the differential game anti-interception maneuver penetration / accurate strike guiding method, expressions are very simple, and physical significance of each term is clear; in addition, the differential game anti-interception maneuver penetration / accurate strike guiding method is large in penetration miss distance, high in falling point accuracy, and can simultaneously meet the falling angle constraint.
Owner:BEIHANG UNIV
Differential game anti-interception maneuver penetration/precise striking guide method
ActiveCN105716470APenetration misses a large amountImprove drop point accuracyAiming meansLink modelCountermeasure
A differential game anti-interception maneuver penetration / precise striking guide method includes the following three steps of firstly, carrying out modeling of a three-body differential game model, wherein a warring three-party dynamics link model, a warring three-party linearized warring model and a three-body differential game model are included; secondly, carrying out dimension reduction processing on an original three-body differential game model and obtaining the new three-body differential game model; and thirdly, solving the new three-body differential game model based on the optimal control theory and obtaining the optimal control law of a guided missile, wherein solving of the Hamiltonian function of the new three-body differential game model and the optimal control problem corresponding to the new three-body differential game model is included. By means of the three steps, the establishing process of the three-body differential game model, the conversion process of the new model and the old model and the solving process of the differential game model are described, and finally, the differential game anti-interception maneuver penetration / precise striking guide method is obtained.
Owner:BEIHANG UNIV
Non-singular terminal sliding mode finite time convergence angle constraint guidance method
InactiveCN110471275ABounded Time Convergence GuaranteeAvoiding Singular Chattering ProblemsAdaptive controlFinite timeComputer science
The invention discloses a non-singular terminal sliding mode finite time convergence angle constraint guidance method and belongs to the technical field of guidance and control. According to the technical schemes of the invention, the non-singular terminal sliding mode finite time convergence angle constraint guidance method comprises the following steps that: step 1, a target-aircraft relative movement equation is established; step 2, a non-singular terminal sliding mode finite time convergence angle constraint guidance law is designed; and step 3, stability analysis is performed on the guidance law. The on-singular terminal sliding mode finite time convergence angle constraint guidance method of the invention is based on a non-singular terminal sliding mode surface and a terminal slidingmode reaching law. With the method adopted, a singular buffeting problem on a sliding mode surface can be avoided; finite time convergence is guaranteed; and landing precision is improved. The methodhas a bright application prospect.
Owner:HARBIN INST OF TECH
Stability augmentation inflation type reentry vehicle
InactiveCN104986358ARealize active controlThe overall structure is light in weightSystems for re-entry to earthCosmonautic landing devicesFlight vehicleControl system
The invention provides a stability augmentation inflation type reentry vehicle. An umbrella-shaped inflation body is formed by an inflation type speed reduction cover and an instrument cabin. Four inflation type control surfaces are evenly distributed on the outer edge of the speed reduction cover. An air compressor and a control system are placed in an effective load cabin from bottom to top. A main valve of the air compressor is communicated with inflation openings of the control surfaces and inflation openings of the speed reduction cover through inflation pipelines respectively. In the stability augmentation inflation type reentry vehicle, the control surfaces and the speed reduction cover can be opened through an inflation device when used, and are put away after being used. The stability augmentation inflation type reentry vehicle is light in structural weight and convenient to design, machine, maintain, control and the like. Under the condition that the structure of the speed reduction cover does not need to be changed and no complex propelling systems need to be added, the aerodynamics characteristics required for control are obtained, the active control over the atmospheric reentry aircraft is achieved, and unsteady influences of complex eddy of the leeward area of the speed reduction cover on the posture of the reentry vehicle are avoided.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Control system used for fixed wing canard rudder
InactiveCN106871741AChange the direction of the control force vectorChange the electromagnetic torqueProjectilesElectronic loadAngular velocity
The invention discloses a control system used for a fixed wing canard rudder, and the control system replaces the head of a mortar projectile to fuze, and is mounted on the head of the mortar projectile. The control system comprises a control mechanism system, an attitude measurement system, a wireless communication system and a processor, wherein the control mechanism system comprises electronic load, a rectifying bridge and a permanent magnet motor; the attitude measurement system is used for transmitting acquired rolling angular velocity to the processor through the wireless communication system; the processor is used for controlling the electronic load according to rotation speed difference between the wing canard rudder and a projectile body; and electromagnetic torque of the permanent magnet motor is regulated through the rectifying bridge, so that rolling angular velocity of the fixed wing canard rudder is changed. According to the control system disclosed by the invention, the electromagnetic torque of the permanent magnet motor and the rolling angular velocity of the fixed wing canard rudder are changed, so that the control force vector direction of the canard rudder is changed; mass centre motion is corrected by motion around a mass center, so that fall point precision of the mortar projectile is improved; and moreover, a conventional servo mechanism is cancelled, so that the size and the cost of the control system can be greatly reduced, and therefore, the control system has the characteristic of a high cost-benefit ratio.
Owner:BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
Method for accurately guiding sublevel return stage of carrier rocket based on ballistic forming
ActiveCN109115035AImproved repeat use return guidance accuracyImprove drop point accuracyAiming meansAngular velocityRocket
The invention provides a method for accurately guiding a sublevel return stage of a carrier rocket based on ballistic forming, and belongs to the technical field of guidance and control. The method ischaracterized in that a virtual inertial sight angular velocity model which uses a grid rudder as an actuator and is composed of the rocket-loaded navigation output sublevel state and before-shootingbinding target information is designed, the optimal guidance expression of ballistic forming under a ballistic system is derived, and then real-time flight overload commands of the sublevel return stage are obtained. The method can effectively improve the sublevel dropping area and sublevel reusing return guidance precision, and effectively ensures high-precision landing of a sublevel at a target landing point with the desired dropping angle by fully utilizing the high control efficiency of the grid rudder in the large dynamic pressure area.
Owner:黑龙江省工研院资产经营管理有限公司
Online planning method for reentry trajectory of aircraft based on particle swarm optimization algorithm
InactiveCN107590297AAvoid Converging to Local OptimaAvoid problems such as large amount of calculationForecastingBiological modelsTechnical standardInversion Time
The invention provides an online planning method for reentry trajectory of an aircraft based on a particle swarm optimization algorithm. The method comprises the following steps of 1, determining an envelop range of an initial condition of reentry according to an reentry task requirement of the aircraft; 2, determining the sizes of piecewise constants of a heeling angle and the maximum number of inversion times of a heeling angle symbol according to the envelop range of the initial condition of reentry; 3, dividing the envelop range of the initial condition of reentry into grids, and ensuringthat an original envelop peak is a sub-envelop peak; 4, using each sub-envelop peak as the initial condition of reentry, and using the particle swarm optimization algorithm to design an reentry standard trajectory of the aircraft offline; 5, verifying validity of envelopment range division and the reentry standard trajectory via offline digital simulation; and 6, statistically analyzing a simulation result, and if the result does not meet an expected design requirement, returning to the step 3 to redivide sub-envelops; and if the result meets the expected design requirement, ending design. Themethod provided by the invention has the advantages of being small in online computing amount and high in placement accuracy of standard trajectory generated online.
Owner:BEIJING SPACE TECH RES & TEST CENT
Parachute cord contraction and release device
InactiveCN108298093AAvoid failureSolve the problem of automatic controlFilament handlingParachutesMotor driveRemote control
The invention discloses a parachute cord contraction and release device, comprising a box body. The box body is internally provided with at least two winding wheels and cord guiding wheels for windingparachute cords. Each winding wheel is provided with two guide grooves for winding, two parachute cords are wound on the two guide grooves, and the two parachute cords symmetric relative to the parachute are reversely wound on the two guide grooves for winding; each winding wheel is provided with a motor for driving the winding wheel to rotate, each motor is provided with a motor drive, and the motor drives are connected with a flight control board and a power source. According to the parachute cord contraction and release device, the box body is connected with the parachute cords through thecord guiding wheels, during the descending flight process of the parachute, the flight control board forms a control command through receiving a remote control signal or automatically detecting the error between the position of the parachute and the target landing point, to drive the corresponding motors to contract / release the parachute cords, so that the parachute always flies toward the targetlanding point.
Owner:DALIAN UNIV OF TECH
Cargo dropping and receiving system
PendingCN107390720AReduced horizontal pull speedReduce traction speedParachutesPosition/course control in three dimensionsMeasuring instrumentMarine engineering
The invention discloses a cargo dropping and receiving system. The system comprises a plane, a cargo cabin arranged on the abdomen of the plane body, a lifting device connected with the cargo cabin and cargo and ground receiving equipment; a pushing mechanism is arranged in the cargo cabin; the lifting device comprises a lifting rope, a rope roller, a rope fixer, a releasing mechanism, a decelerating mechanism, a cargo bag and a height measuring instrument, wherein one end of the lifting rope is connected with the rope roller, the rope roller is fixedly installed on the inner top of the cargo cabin, the rope fixer is arranged on the lifting rope in a sleeving mode, the rope fixer is fixed to the hatch of the cargo cabin, the lower end of the lifting rope is connected with the releasing mechanism, the releasing mechanism is connected with the cargo bag, and the cargo is arranged in the cargo bag. According to the cargo dropping and receiving system, the plane minimum-altitude direct cargo dropping technology is combined with the lifting rope dropping technology, the precision of air drop is improved, low-cost rapid transportation is achieved, and the development of air cargo equipment is promoted.
Owner:陶文英
Air-drop forest fire extinguishing bomb
PendingCN113926106AQuick responsePrecision strikeClimate change adaptationFire rescueAviationNacelle
The invention discloses an air-drop forest fire extinguishing bomb. The air-drop forest fire extinguishing bomb is aviation fire fighting equipment which is mainly loaded on air platforms such as helicopters and unmanned aerial vehicles, adopts an air-drop launching mode, flies in an unpowered gliding mode and realizes high-precision forest fire extinguishing through guidance control. According to the air-drop forest fire extinguishing bomb, a three-section split type structure is adopted, a seeker cabin, a medium cabin and a steering engine cabin are sequentially arranged from front to back, the seeker cabin is used for providing a mounting space for a head aerodynamic configuration and an infrared seeker, the medium cabin is used for loading a fire extinguishing medium, fins are fixed on the outer surface of the medium cabin, and the steering engine cabin is used for providing an installation space for the steering engine and an avionics system and providing a control moment when a bomb body flies. The air-drop forest fire extinguishing bomb adopts a throwing mode of a central detonation tube structure, and the fire extinguishing medium preloaded in the explosive cabin is driven to be thrown to the periphery through explosion, so that a certain area of coverage is formed, and the fire extinguishing effect is achieved.
Owner:SICHUAN AEROSPACE LIAOYUAN SCI & TECH CO LTD
Pose correction method for powered phase of aircraft
ActiveCN105182987AImprove drop point accuracyImprove position velocity accuracyAttitude controlPosition/course control in three dimensionsCorrection methodMarine navigation
Provided is a pose correction method for a powered phase of an aircraft. The method is designed according to flight characteristics of a powered phase, and through comprehensive determination of overload and other information, effective use of pure inertial navigation, integrated navigation, and GNSS information is determined, so that effective information of GNSS is fully used, navigation precision of the powered phase of an aircraft is improved, GNSS mistaken correction caused by complex interference is prevented, and a problem of high-precision navigation of low-cost aircraft is solved. Control cost is reduced, and the method provides conditions for popularized use of the aircraft pose correction method.
Owner:BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
Unmanned aerial vehicle traction device for erecting wires
ActiveCN111682452AEasy to fixImprove drop point accuracyApparatus for overhead lines/cablesUncrewed vehicleRelative motion
The invention provides an unmanned aerial vehicle traction device for erecting wires. The device comprises a composite wing unmanned aerial vehicle; a reciprocating lifting mechanism is arranged at the lower end of the composite wing unmanned aerial vehicle; a clamping and releasing mechanism is arranged at the lower end of the reciprocating lifting mechanism; and a linkage transmission mechanismis arranged on one side of the clamping and releasing mechanism. The unmanned aerial vehicle traction device has the beneficial effects that a wire can be stably fixed to the unmanned aerial vehicle through the action of the clamping and releasing mechanism; relative movement between a clamp and the wire can be effectively avoided through the fixing mode; the falling point precision of the wire isimproved, and the traction device works more efficiently; and through the effect of the reciprocating lifting mechanism, the clamp can be retracted into the unmanned aerial vehicle when not used, andthe effect of reducing wind resistance is achieved.
Owner:河北柒壹壹玖工业自动化技术有限公司
Triplet geocontainer and method for calculating dumping drift amount thereof
The invention discloses a triplet geocontainer and a method for calculating dumping drift amount thereof. The triplet geocontainer is characterized by comprising three independent geocontainers, wherein reinforcing belts are arranged at surrounding edge lines and diagonal lines of each geocontainer to reinforce. The method for calculating the dumping drift amount comprises the following steps of (1) calculating transverse and longitudinal accelerations; (2) according to an initial coordinate and speed in a time interval, obtaining a final speed and coordinate of each geocontainer in the time interval; (3) performing iterative calculation; when a longitudinal coordinate is the same as a longitudinal coordinate at a water bottom, the distance from the horizontal coordinate to the lower edge of a turning plate is the dumping drift amount. The triplet geocontainer and the method have the beneficial effects that the larger the size of the triplet geocontainer is, the larger the inertia is, and the corresponding drift amount is smaller in comparison with the drift amount of a single geocontainer; during dumping, a falling point of the triplet geocontainer is more centralized, and the falling point accuracy calculated by a falling point formula is higher, so the difficulty in construction is effectively decreased, the construction efficiency is higher, and the cost is reduced.
Owner:HOHAI UNIV
Car loader
PendingCN111377260AAvoid inertial effectsArrange neatlyConveyorsLoading/unloadingLeather beltAutomotive engineering
The invention relates to a car loader. The loader comprises an upper bag receiving device which is used for movable assembled on a corresponding guide rail, wherein the upper bag receiving device is provided with a downward sliding belt conveying device, the downward sliding belt conveying device is provided with an outlet and an inlet for receiving downward released by the upper bag receiving device, an outlet of the downward sliding belt conveying device is provided with a bag placing device, the bag placing device comprises a bag placing bucket used for receiving a bag sent from the downward sliding belt conveying device, the bag placing bucket comprises a bucket body which can be relatively closed to form a bag placing cavity and can be opened relatively to achieve bag packing operation, and the bag placing bucket is provided with a bag receiving opening which is arranged towards the downward sliding belt conveying device and communicates with the bag placing cavity. Compared withthe prior art, the car loader is used for receiving the bag and buffering the bag through the bag placing bucket, so that the inertia influence of the bag is avoided, the falling point accuracy is improved, bag placing is more orderly, and the loading efficiency is remarkably improved.
Owner:ZHENGZHOU JINGU GRAIN MECHANICAL ENG EQUIP
Gyroscope combination high-order error coefficient separation and compensation method and system
ActiveCN113865585AIdentify the exact valueConfidenceSustainable transportationNavigation by speed/acceleration measurementsGyroscopeControl engineering
The invention discloses a gyroscope combination high-order error coefficient separation and compensation method and system. The method comprises the following steps: establishing a gyroscope combination high-order error coefficient separation test system; based on the established gyroscope combination high-order error coefficient separation test system, carrying out gyroscope combination high-order error coefficient separation test to obtain a test result; according to a test result, separating various error coefficients of the gyroscope combination in combination with a gyroscope combination error model; and according to the separated error coefficients of the gyroscope combination, correcting the error of the gyroscope combination participating in navigation solution so as to realize compensation of the inertial navigation gyroscope measurement error. According to the method, various error coefficients of the gyroscope combination can be separated, and the measurement precision of the gyroscope combination is improved through error compensation.
Owner:BEIJING INST OF AEROSPACE CONTROL DEVICES
GNSS and INS combined navigation accurate guidance fire extinguishing bomb device
ActiveCN109341442ALow costImprove drop point accuracyAmmunition projectilesFire rescueInertial measurement unitControl function
The invention provides a GNSS and an INS combined navigation accurate guidance fire extinguishing bomb device. The fire extinguishing bomb device comprises a fire extinguishing bomb loading cabin anda guidance control cabin; the guidance control cabin comprises a guidance combined body, wherein the guidance combined body comprises a structural component and an information processing unit; the information processing unit comprises a navigation, guidance and control processing unit, wherein the navigation, guidance and control processing unit comprises a micro-inertia measurement module, a satellite navigation module, an embedded combined navigation information processing module, a guidance information processing module and a communication controller module; and the satellite navigation module is used for receiving a global navigation satellite system (GNSS) information, and the embedded combined navigation information processing module is used for receiving inertial measurement unit information and satellite navigation information. The fire extinguishing bomb device adopts the GNSS / the INS combined navigation for accurate guidance, a flight path and a throwing point can be accurately controlled, complete information feedback and control functions are provided, and the comprehensive performance is excellent.
Owner:湖南科华军融民科技研究院有限公司
A stabilized inflatable reentry vehicle
InactiveCN104986358BRealize active controlThe overall structure is light in weightSystems for re-entry to earthCosmonautic landing devicesControl systemFlight vehicle
Owner:NORTHWESTERN POLYTECHNICAL UNIV
A device for accelerating the separation of aircraft head and body
InactiveCN104457447BEasy to separateSeparate without interferenceSelf-propelled projectilesEngineeringFlange
Owner:BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
A Differential Countermeasure Anti-Interception Maneuver Penetration/Precision Strike Guidance Method
ActiveCN105716470BPenetration misses a large amountImprove drop point accuracyAiming meansLink modelCountermeasure
Owner:BEIHANG UNIV
Precise parafoil recovery system and method for safety control of landing area of booster
PendingCN114476142ATroubleshoot structural adaptationsDeceleration attitudeSystems for re-entry to earthCosmonautic landing devicesAutomatic controlSafety control
The invention provides an accurate parafoil recovery system and method for safety control of a booster falling area, a sectional connection and separation and centralized layout design is adopted, an original integrated booster nose cone is divided into an end cap, a nose cone middle section and a nose cone bottom section, a stabilizing parachute is mounted in the end cap, and the stabilizing parachute is mounted in the nose cap. Other products of the recovery system are intensively mounted on the nose cone bottom section through a bearing structure, so that the problem of structural adaptability change of an existing booster is solved; the recovery system adopts a segmented homing control strategy of multiple target points and multiple obstacle avoidance areas, the drop point precision under the obstacle avoidance condition is improved, obstacle avoidance and accurate landing of the booster are achieved, meanwhile, the recovery system has two control modes, namely an automatic control mode and a ground manual control mode, redundant backup is achieved, and the system reliability is improved.
Owner:BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
Aerodynamic configuration of air-drop forest fire extinguishing bullet
ActiveCN112999544AEasy loadingReduce round trip timeClimate change adaptationFire rescueStructural engineeringMechanical engineering
The invention discloses an aerodynamic configuration of an air-drop forest fire extinguishing bullet. The aerodynamic configuration adopts a stable empennage type layout and comprises a bullet head, a bullet body, a bullet tail and eight empennages, wherein the bullet head is located at the front end, the bullet body is located in the middle portion, the bullet tail is located at the tail portion, the eight empennages are arranged at the tail portion of the bullet body in the circumferential direction, the bullet head is spherical or ellipsoidal, a length of the bullet head accounts for 12% to 14% of a length of the whole bullet, the bullet body is a standard cylinder, a length of the bullet body accounts for 43% to 50% of the length of the whole bullet, the bullet tail is a cone-cylinder assembly, a length of the bullet tail accounts for 36% to 44% of the length of the whole bullet, a ratio of a conical section to a column section of the bullet tail is 1:(2.5 to 3.5), a diameter of the column section of the bullet tail is 0.43 to 0.57 of a diameter of the bullet body, and a slenderness ratio of the bullet is 3.7 to 4.3. According to the aerodynamic configuration, the filling space is large, the stability is high, the structure is rational, and the space is saved during storage.
Owner:湖北航天飞行器研究所
Air drop method and device
PendingCN111976986AImprove drop point accuracyLow costAircraft componentsLaunching weaponsStructural engineeringMechanical engineering
The invention discloses an air drop method and device, and relates to the technical field of computers. One specific embodiment of the method comprises the following steps that a target position of air drop is received to carry out cargo air drop; the air-drop cargo is provided with a buffer device, meanwhile, two ducts are symmetrically installed on the air-drop cargo, and the spray pipe direction of the ducts is parallel to the edges of the air-drop cargo; a real-time position of the air-drop cargo is acquired; and according to the real-time position and the target position of the air-drop cargo, a descending track of the air-drop cargo is adjusted through the two ducts until the air-drop cargo descends to the target position. Therefore, the air drop method and device can solve the problem of low precision of the landing position of the air-drop cargo.
Owner:XIAN JINGDONG TIANHONG TECH CO LTD
A gnss and ins combined navigation precision guidance fire extinguishing bomb device
ActiveCN109341442BEfficient fire fightingLow costAmmunition projectilesNavigation by speed/acceleration measurementsInformation processingGuidance control
The invention provides a GNSS and an INS combined navigation accurate guidance fire extinguishing bomb device. The fire extinguishing bomb device comprises a fire extinguishing bomb loading cabin anda guidance control cabin; the guidance control cabin comprises a guidance combined body, wherein the guidance combined body comprises a structural component and an information processing unit; the information processing unit comprises a navigation, guidance and control processing unit, wherein the navigation, guidance and control processing unit comprises a micro-inertia measurement module, a satellite navigation module, an embedded combined navigation information processing module, a guidance information processing module and a communication controller module; and the satellite navigation module is used for receiving a global navigation satellite system (GNSS) information, and the embedded combined navigation information processing module is used for receiving inertial measurement unit information and satellite navigation information. The fire extinguishing bomb device adopts the GNSS / the INS combined navigation for accurate guidance, a flight path and a throwing point can be accurately controlled, complete information feedback and control functions are provided, and the comprehensive performance is excellent.
Owner:湖南科华军融民科技研究院有限公司
Differential Countermeasures Anti-Interception Maneuver Penetration/Precision Strike Guidance Method with Fall Angle Constraint
ActiveCN105759612BThe drop angle constraint satisfiesPenetration misses a large amountAdaptive controlCountermeasureDynamic models
A differential countermeasure anti-interception maneuver penetration / precise strike guidance method with fall angle constraints, which includes the following three steps: 1. Three-body differential countermeasure model modeling; including the dynamics model of the three parties at war, and the linearization of the three parties at war Engagement model, three-body differential game model; second, the original three-body differential game model is reduced in dimensionality to obtain a new three-body differential game model; third, based on optimal control theory, the new three-body differential game model is obtained to obtain the missile’s optimal Control law; through the above steps, the differential countermeasure anti-interception maneuver penetration / precise attack guidance method with the drop angle constraint can be obtained; the present invention has very concise expressions, and the physical meanings of its items are clear and definite; its penetration misses the target The quantity is large, the drop point accuracy is high, and the drop angle constraint can be satisfied at the same time.
Owner:BEIHANG UNIV
A Triple Geotechnical Package and Its Casting Drift Calculation Method
ActiveCN106777447BIncrease in sizeHigh inertiaGeometric CADBreakwatersStructural engineeringMechanics
The invention discloses a triplet geocontainer and a method for calculating dumping drift amount thereof. The triplet geocontainer is characterized by comprising three independent geocontainers, wherein reinforcing belts are arranged at surrounding edge lines and diagonal lines of each geocontainer to reinforce. The method for calculating the dumping drift amount comprises the following steps of (1) calculating transverse and longitudinal accelerations; (2) according to an initial coordinate and speed in a time interval, obtaining a final speed and coordinate of each geocontainer in the time interval; (3) performing iterative calculation; when a longitudinal coordinate is the same as a longitudinal coordinate at a water bottom, the distance from the horizontal coordinate to the lower edge of a turning plate is the dumping drift amount. The triplet geocontainer and the method have the beneficial effects that the larger the size of the triplet geocontainer is, the larger the inertia is, and the corresponding drift amount is smaller in comparison with the drift amount of a single geocontainer; during dumping, a falling point of the triplet geocontainer is more centralized, and the falling point accuracy calculated by a falling point formula is higher, so the difficulty in construction is effectively decreased, the construction efficiency is higher, and the cost is reduced.
Owner:HOHAI UNIV
Solar unmanned aerial vehicle for infrastructure construction
ActiveCN111688923AEasy to fixImprove drop point accuracyAircraft componentsApparatus for overhead lines/cablesUncrewed vehicleRelative motion
The invention discloses a solar unmanned aerial vehicle for infrastructure construction. The solar unmanned aerial vehicle comprises a composite wing unmanned aerial vehicle body, a reciprocating lifting mechanism is arranged at the lower end of the composite wing unmanned aerial vehicle body, a clamping and releasing mechanism is arranged at the lower end of the reciprocating lifting mechanism, and a linkage transmission mechanism is arranged on one side of the clamping and releasing mechanism. The solar unmanned aerial vehicle has the following beneficial effects: a wire can be stably fixedto the unmanned aerial vehicle through the action of the clamping and releasing mechanism, relative movement between a clamp and the wire can be effectively avoided through a fixing mode, the fallingpoint precision of the wire is improved, and the wire clamping and releasing device works more efficiently; and through the effect of the reciprocating lifting mechanism, the clamp can be retracted into the unmanned aerial vehicle when not used, and the effect of reducing wind resistance is achieved.
Owner:河北柒壹壹玖工业自动化技术有限公司
A Pose Correction Method for Active Section of Aircraft
ActiveCN105182987BImprove drop point accuracyImprove position velocity accuracyAttitude controlPosition/course control in three dimensionsActive phaseCorrection method
A pose correction method for the active segment of an aircraft is designed according to the flight characteristics of the active segment, and the effective use of pure inertial navigation, integrated navigation and GNSS information is determined through comprehensive judgment of information such as overload, which not only makes full use of the effective information of GNSS, It improves the navigation accuracy of the active segment of the aircraft, avoids GNSS miscorrection caused by complex interference, solves the problem of high-precision navigation of low-cost aircraft, reduces control costs, and provides conditions for the popularization and use of aircraft pose correction methods.
Owner:BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
An Approximate Optimal Explicit Guidance Method with Fully Controllable Position and Velocity During Dynamic Descent
ActiveCN105253328BConvenience guaranteedLower requirementSpacecraft guiding apparatusComputer terminalContinuous variable
Owner:BEIJING INST OF CONTROL ENG
A Precise Guidance Method for Launch Vehicle Sub-stage Return Stage Based on Trajectory Shaping
ActiveCN109115035BImproved repeat use return guidance accuracyImprove drop point accuracyAiming meansAngular velocityRocket
The invention provides a method for accurately guiding a sublevel return stage of a carrier rocket based on ballistic forming, and belongs to the technical field of guidance and control. The method ischaracterized in that a virtual inertial sight angular velocity model which uses a grid rudder as an actuator and is composed of the rocket-loaded navigation output sublevel state and before-shootingbinding target information is designed, the optimal guidance expression of ballistic forming under a ballistic system is derived, and then real-time flight overload commands of the sublevel return stage are obtained. The method can effectively improve the sublevel dropping area and sublevel reusing return guidance precision, and effectively ensures high-precision landing of a sublevel at a target landing point with the desired dropping angle by fully utilizing the high control efficiency of the grid rudder in the large dynamic pressure area.
Owner:黑龙江省工研院资产经营管理有限公司
A solar-powered drone for infrastructure
ActiveCN111688923BEasy to fixImprove drop point accuracyAircraft componentsApparatus for overhead lines/cablesUncrewed vehicleStructural engineering
The invention discloses a solar-powered unmanned aerial vehicle for infrastructure construction, including a compound-wing unmanned aerial vehicle. The lower end of the composite-wing unmanned aerial vehicle is provided with a reciprocating lifting mechanism, and the lower end of the reciprocating lifting mechanism is provided with a clamping and releasing mechanism. One side of the clamping release mechanism is provided with a linkage transmission mechanism. The beneficial effect of the present invention is that the electric wire can be stably fixed on the drone through the action of the clamping and releasing mechanism, and the relative movement between the clamp and the electric wire can be effectively avoided through its fixing method, and the accuracy of the landing point of the electric wire is improved, so that Its work is more efficient; through the function of the reciprocating lifting mechanism, the clamp can be shrunk into the inside of the drone when not in use, so as to reduce the effect of wind resistance.
Owner:河北柒壹壹玖工业自动化技术有限公司
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