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2022 results about "Rocket" patented technology

A rocket (from Italian rocchetto "bobbin") is a missile, spacecraft, aircraft or other vehicle that obtains thrust from a rocket engine. Rocket engine exhaust is formed entirely from propellant carried within the rocket before use. Rocket engines work by action and reaction and push rockets forward simply by expelling their exhaust in the opposite direction at high speed, and can therefore work in the vacuum of space.

Multi-point forming method for whole aluminum alloy wall plate of aircraft

InactiveCN104646475ASolve efficiency problemsSolve the problem that cracks are prone to occur and cause the overall wall panel to be scrappedShaping toolsMetal working apparatusRocketDouble curvature
The invention discloses a multi-point forming method for a whole aluminum alloy wall plate of an aircraft. The multi-point forming method comprises the following steps of arranging the whole aluminum alloy wall plate with ribs between an upper multi-point die and a lower multi-point die of a quick reconstructing die surface, filling a filling material between the ribs, arranging an elastic cushion between the wall plate and the multi-point die, and gradually forming a whole aluminum alloy wall plate part with ribs by a die pressing method along a controllable deformation path. The multi-point forming method has the advantages that by utilizing the quick and adjustable characteristic of the reconstructing multi-point die surface, the wall plate parts with different geometric shapes and double curvatures can be processed by one set of equipment; compared with the traditional rolling and bending forming method and the pressing and bending forming method, the stress of the wall plate is uniform, and the forming quality can be guaranteed; compared with the shot peen forming method and the aging forming method, the deformation amount is large, and the forming efficiency is high; the method can be used for forming the whole aircraft wall plate with different rib structures and the double curvatures, the problems of large size and high rib in the whole wall plate forming process are solved, and the method can be applied to the manufacturing of other large ribbed curvature parts of aircrafts, rockets and the like.

Image-text firework production method with users dyeing partial preset part

ActiveCN103234396AGuaranteed eleganceGuaranteed consistent specificationsFireworksGraphicsText display
The invention discloses an image-text firework production method with users dyeing a partial preset part. The image-text firework production method is characterized in that an image-text firework carrier, dyeing articles and a dyeing image-text production method are adopted. The image-text firework carrier is provided with a lift-off rocket, a lattice structural body, preset image-text display flames, flame primary color powder, simultaneous propellant powder and a simultaneous ignition device, wherein the lift-off rocket is connected with the lattice structural body, and the simultaneous propellant powder, the preset image-text display flames and the flame primary color powder are filled in the lattice structural body. The dyeing articles include a dyeing saline solution and a dyeing device. The dyeing image-text production method includes image-text sample manuscript design, dyeing saline solution application, flame primary color powder penetrating staining, liquid component removing for sufficient drying and the like. According to the image-text firework production method, the displayed picture part of set off fireworks is preset and can be randomly combined according to free expressing of users, and accordingly the users can experience pleasure brought by personal participation and can directly express affection. In addition, the image-text firework production method is simple to implement, low in cost and suitable for volume production.

Production method of partitioned independent powder-charged post-dyed graphic fireworks

The invention discloses a production method of partitioned independent powder-charged post-dyed graphic fireworks. A graphic firework structure and a post-dyed graphic firework production method are included. The graphic firework structure comprises lattice structural bodies, the lattice structural bodies are filled with firework base color powder and connected with simultaneous launchers, the simultaneous launchers are connected with a simultaneous ignition bin, and the simultaneous ignition bin is filled with simultaneous ignition powder and connected with a lift-off rocket. The post-dyed graphic firework production method comprises a dyeing salt solution, a dyeing device and a dyeing method, wherein the dyeing method comprises designing graphic sample manuscripts, contacting the dyeing salt solution with the firework base color powder through the dyeing device, enabling the dyeing salt solution to permeate into the firework base color powder according to rule limitation, mixing, removing liquid components, performing full drying, and displaying desired colors after the original firework base color powder is lighted. The production method is simple in implementation and convenient to produce, inventory is not needed, and the graphic fireworks can be dyed before leaving factories and be dyed by users through free combination after being purchased.

Semi-physical simulation system for developing laser terminal guidance ammunition round

ActiveCN102589350AReduce the difficulty of mathematical modelingImprove simulation accuracyAiming meansMathematical modelRocket
A semi-physical simulation system for developing a laser terminal guidance ammunition round comprises a rocket sled test platform, a target simulation device, an attitude simulation device and a simulation platform. The rocket sled test platform launches a rocket sled loaded with a target and measures speed and position information of the rocket sled in real time. The target simulation device utilizes laser to irradiate the target to enable a seeker of the laser terminal guidance ammunition round to be capable of receiving laser from the target to perform target tracking. The attitude simulation device comprises a three-axle rotary table capable of loading the seeker and is used for simulating attitude movement of a missile body. The simulation platform analyzes and processes the speed and position information of the rocket sled and a seeker generating signal according to a preset simulation mathematical model to obtain information related with attitude change of the missile body and relative movement of a missile and correspondingly controls the rotation of the three-axle rotary table. The rocket sled test platform is located outside the outdoor, and the rocket sled test platform and the simulation platform perform data transmission through a radio station and achieve time synchronization.

Multilayer armor system for defending against missile-borne and stationary shaped charges

An armor system for defeating rocket propelled grenade-type missiles and/or high velocity jets created by shaped charges directed at a vehicle includes a grid layer such as a net and/or an array of slats or bars (“RPG”) spaced from an outer surface of the vehicle by support members. The grid layer has a characteristic mesh size or bar/slat spacing to disrupt the missile firing mechanism. The system also has a shaped layer having a plurality of tapered members formed from a fiber-reinforced material, the tapered members positioned between the grid layer and the vehicle outer surface and having respective apex ends proximate the distant the grid layer and base ends, the tapered members defining with adjacent tapered members a plurality of depressions opening in a direction to receive an incoming conical portion of an unexploded RPG-type missile, or a jet emanating from an exploded RPG or other anti-armor device, and a layer of fiber-reinforced material abutting the base ends of the tapered members. The system may further include reactive elements disposed on surfaces of the tapered members defining the depressions to deflect impinging jets. The system may still further include one or more metal armor layers and one or more additional fiber-reinforced material layers disposed between the shaped fiber-reinforced material layer and the vehicle surface.

Method for optimizing orbital transfer strategy of geostationary orbit satellite

The invention relates to a method for optimizing an orbital transfer strategy of a geostationary orbit satellite, which comprises the following steps of: 1, determining orbital transfer times, orbital transfer circle times and the controlled variable of each-time orbital transfer; and 2, determining time and a thrust direction in each-time orbital transfer. The process of launching the geostationary orbit satellite at present generally comprises the following steps of: launching the satellite into a highly elliptic transfer orbit with an inclination angle by using a carrier rocket; performing apogee/perigee orbital transfer for several times by using a self-contained liquid engine of the satellite, and transferring to a geosynchronous orbit; and correcting and rounding the inclination angle of the orbit to realize a geostationary orbit. For the satellite, operation for changing the transfer orbit into the geostationary orbit by performing apogee/perigee orbital transfer for several times is complex, so too many orbital transfer times is not suitable, and orbital transfer complexity and risk are prevented from being increased; in addition, factors such as the capacity of the liquid engine of the satellite, arc segment loss in an orbital transfer period, and the like are considered, so too few orbital transfer times is not suitable.

Autonomous and cooperated type aircraft cluster system and running method

The invention discloses an autonomous and cooperated type aircraft cluster system and a running method. The aircraft cluster system mainly comprises at least one node aircraft cluster, wherein the node aircraft cluster has an autonomous running capability and a network information connection function, the node aircraft cluster is provided with a resource sharing interface, node aircrafts in the node aircraft cluster are connected with each other by a space self-organizing network, the node aircrafts in the aircraft cluster fly in shared navigation and cluster flight modes, the commutation is realized by the space self-organizing network, and the fleet configuration is automatically adjusted according to the task existing condition. When the aircraft cluster receives a task instruction, the resource scheduling, the task planning, the task reconfiguration and the failure regrouping are autonomously carried out according to the task types, so as to further complete the tasks. The autonomous and cooperated type aircraft cluster system is suitable for quick or maneuvering launching of small carrier rockets, the quick response of the space system is greatly improved, and the risk of the in-orbit failure of the aircrafts is reduced.

Low-impact non-pyrotechnic separation device

The invention discloses a low-impact non-pyrotechnic separation device, which is used for the locking and release between stages of a rocket, between a satellite and a launch vehicle, and of a satellite solar panel substrate, an antenna and the like. The low-impact non-pyrotechnic separation device is formed by using a shape memory alloy as a triggering switch and being provided with components and parts of springs, a locking sleeve, a split nut and the like in a matching manner. Based on the shape memory effect of the shape memory alloy, stretching and pre-deformation are firstly carried out on the shape memory alloy during assembly; when separation and unlocking are needed, an alloy material is electrified and heated to be at a phase-transition temperature of the alloy material; the alloy material is recovered to be in a shape before the pre-deformation; thus, a triggering block is driven to act; the locking sleeve is disengaged from the split nut; the release of loads of the satellite and the like is realized. After the one-time separation is completed, a trigger part inside a shell can be conventionally taken out; a shape memory alloy wire is loaded in the low-impact non-pyrotechnic separation device after the pre-deformation is carried out on the shape memory alloy wire once again by adopting a special tool; thus, the low-impact non-pyrotechnic separation device can be repeatedly used. The separation device provided by the invention is low in impact, can be repeatedly used, has no pollution, is low in cost, is safe to use, and is especially applicable to an occasion which is high in the requirement on a separation impact.

FPGA (Field Programmable Gate Array) based ground launching control device of small and medium-sized rocket

ActiveCN104296605AReduce volumeRealize fully intelligent controlSelf-propelled projectilesIgnition controlRocket
The invention provides an FPGA (Field Programmable Gate Array) based ground launching control device of a small and medium-sized rocket. The device comprises a main control computer, a ground control box, a signal conditioning case which uses FPGA as the core, and a missile device; the main control computer receives and feeds back a signal through an RS422 communication interface; the ground control box is used for performing hardware control for the system; the signal conditioning control case comprises the combination of a PCB and a power supply; the PCB comprises a level isolation conversion circuit which uses the FPGA as the core, a power-on sequence control circuit, a voltage AD acquiring circuit, an RS422 isolation conversion circuit, an RS422 relay circuit, a level conversion circuit in a head power supply circuit, and a corresponding filter circuit; the missile device comprises a missile distributor, a missile battery combination and a missile electrical device. With the adoption of the device, the functions of supplying power to the missile device from the ground, activating the missile battery, converting power, cutting off power supply, controlling a pressure release valve, and controlling ignition can be realized; the device has the characteristics of being safe, reliable, small in cost, short in development cycle, fast in speed, high in efficiency, and high in real-time performance.
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