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

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.

A device for accelerating separation of the head and the body of an aircraft comprises a device body (3-1), a central spindle (3-2), a compression spring (3-4) and a blanking cap (3-3), wherein two inner holes are symmetrically formed in the device body (3-1), one end of each inner hole serves as a guiding hole, the other end of each inner hole serves as an internal threaded hole, the diameter of each guiding hole is smaller than that of the corresponding internal threaded hole, one end of the central spindle (3-2) is connected with the blanking cap (3-3), an outer stud is arranged at one end of the blanking cap (3-3), a positioning flange is arranged at the other end of the blanking cap (3-3), a through hole is formed in the axial center of the blanking cap (3-3), an outer stud of the central spindle (3-2) extends out of the through hole after the outer stud of the blanking cap (3-3) is screwed into one internal threaded hole of the device body, and the compression spring (3-4) is arranged between the blanking cap (3-3) and the central spindle (3-2). By the adoption of the device (3), the head and the body of the aircraft can be separated quickly and reliably.

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 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 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.

The invention relates to a position speed controllable quasi-optimal explicit guidance method in a power decrease process; the quasi-optimal explicit guidance method respectively use the maximum thrust and minimum thrust as input values, and uses a normal thrust power explicit guidance method to calculate guidance parameters and predict terminal positions corresponding to the thrusts; according to a relation between a target position and predicted terminal positions under two different thrusts, the quasi-optimal explicit guidance method can automatically determine whether to use the maximum thrust or the minimum thrust to guide, thus realizing automatic switching between the maximum trust and minimum thrust. The invention only relates to two PEG guidance rules for calculation, and the computational complexity is smaller when compared with an iteration thrust adjusting mode; the thrust control uses an automatic maximum-minimum switching mode, an engine usage efficiency is higher than continuous variable thrusts, so propellant consumption is theoretically least.

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.