31results about How to "Improve drop point accuracy" patented technology

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.

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.

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.

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.

The invention discloses a cargo air-dropping and receiving system, which includes an aircraft and a cargo compartment arranged on the belly of the fuselage, a lifting device connecting the cargo compartment and the cargo, and ground receiving equipment. The cargo compartment is provided with a pushing mechanism, The lifting device includes a sling, a rope reel, a rope fixer, a release mechanism, a deceleration mechanism, a cargo bag and an altimeter, and one end of the sling is connected to the rope reel, and the rope reel is fixedly installed On the inner top of the cargo compartment, the rope fixing device is sleeved on the sling, the rope fixing device is fixed at the hatch of the cargo cabin, the lower end of the sling is connected to a release mechanism, and the release mechanism is connected to the cargo bag bag, and the cargo bag is provided with goods. The invention combines the technology of direct delivery of goods by aircraft at ultra-low altitude and the technology of delivery by sling, improves the accuracy of airdrop, realizes low-cost and fast transportation, and promotes the development of air cargo equipment.

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.

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.

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.

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.

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.