2022 results about "Rocket" patented technology

Processes for conversion of lignin to liquid products such as bio-fuels and fuel additives are disclosed and described. A process for conversion of a lignin material to bio-fuels can include subjecting the lignin material to a base catalyzed depolymerization reaction to produce a partially depolymerized lignin. The partially depolymerized lignin can then be subjected to a stabilization/partial hydrodeoxygenation reaction to form a partially hydrodeoxygenated product. Following partial hydrodeoxygenation, the partially hydrodeoxygenated product can be reacted in a hydroprocessing step to form a bio-fuel. Each of these reaction steps can be performed in single or multiple steps, depending on the design of the process. The production of an intermediate partially hydrodeoxygenation product and subsequent reaction thereof can significantly reduce or eliminate reactor plugging and catalyst coking. A variety of useful bio-fuels such as fuels, fuel additives, and the like, including gasoline and jet or rocket fuels are describe which can be readily produced from renewable lignin materials in an improved conversion process.

A method for intercepting and a defeating rocket propelled grenade (RPG) which includes the steps of detecting a thermal signature from a launch of the RPG; and cueing a narrow beam radar which locates the RPG and develops a ballistic solution and target intercept point for intercepting the PPG with an intercept vehicle.

A countermeasure system which is capable of defusing rocket propelled grenades (RPG) is provided by spacing an array of explosive charges or primacord from the protected structure to allow and sense an ogive of the fused RPG to enter into a functional plane of the array initiating one or more of the charges to collapse to ogive. The array is supported flexibly or rigidly and further ballistic protection is incorporated behind the array in fixed or inflatable forms to provide protection of the structure from the explosive products from the array and the ballistic impact of the defused RPG.

A rocket-powered vehicle used for entertainment, namely races, exhibitions, competitions, and revenue-generating events.

System and methods are disclosed for fluid measurements which may be utilized to determine mass flow rates such as instantaneous mass flow of a fluid stream. In a preferred embodiment, the present invention may be utilized to compare an input mass flow to an output mass flow of a drilling fluid circulation stream. In one embodiment, a fluid flow rate is determined by utilizing a microwave detector in combination with an acoustic sensor. The acoustic signal is utilized to eliminate 2 pi phase ambiguities in a reflected microwave signal. In another embodiment, a fluid flow rate may be determined by detecting a phase shift of an acoustic signal across two different predetermined transmission paths. A fluid density may be determined by detecting a calibrated phase shift of an acoustic signal through the fluid. In another embodiment, a second acoustic signal may be transmitted through the fluid to define a particular 2pi phase range which defines the phase shift. The present invention may comprise multiple transmitters/receivers operating at different frequencies to measure instantaneous fuel levels of cryogenic fuels within containers positioned in zero or near zero gravity environments. In one embodiment, a moveable flexible collar of transmitter/receivers may be utilized to determine inhomogenuities within solid rocket fuel tubes.

An interceptor projectile includes a deployable net that deploys during flight and wraps around an incoming projectile, such as a rocket propelled grenade (RPG). The net is initially in a tubular body of the interceptor projectile. A propellant is used to deploy the net from the body. Even after deployment the net remains attached to the body by an elastic tether. The engagement of the net with the incoming projectile disables the incoming projectile, with the momentum imparted by the interceptor projectile sending the incoming projectile off course. This successfully defends a target against the incoming projectile. Through the tether, substantially all of the parts of the interceptor projectile may be mechanically linked together even after deployment of the net. This mechanical linking provides more momentum for impacting the interceptor projectile, which may facilitate diverting the incoming projectile.

A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

An apparatus for launching and dispensing multiple satellites into orbit includes a central structure and a plurality of satellites releasably bundled around the central structure to form a cohesive, single payload mounted on an upper stage of a launcher rocket. The central structure includes a central tube and an adapter shell that fits onto the upper stage of the rocket. Each satellite has the shape of a partial cylinder segment of which an outer wall is a cylindrical segment shell. The satellites are bundled and secured together around the central structure by tension bands, whereby the cylindrical segment shells form a load-bearing complete outer cylindrical shell that surrounds the central tube. This structure provides sufficient stiffness and strength to withstand the loads that arise during launch, while having a reduced mass. The satellites themselves, rather than the central structure, bear the loads during launch. This allows the central structure to be of relatively lightweight construction.

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.

A system that includes a synchronized network of three search and track radars and associated processing means and communication channels. The radars are configured to detect and track the target. In response to detected target, an interceptor is launched towards the target. The radars are configured to measure and track the target and the interceptor. The target and interceptor ranges are accurately measured by the radars in the synchronized network, giving rise to synchronized accurate range measurements that are combined by range triangulation to provide accurate target and interceptor position measurements irrespective of the angular measurement accuracy of each radar. The processing means are configured to utilize the measurements to calculate interceptor maneuvers required to overcome errors and bring the interceptor close to a target. The maneuver commands are transmitted to the interceptor using the communication channel. The interceptor is equipped with kill mechanism designed to destroy a target warhead when the interceptor approaches the target.

Thrust vectoring enhances aircraft and spacecraft maneuverability. The propulsion systems of aircraft, using gas turbine engines, and spacecraft, using solid or liquid rockets, generate compressed gases that are directed through a nozzle to generate forward thrust. This patent describes opening ports to release gases from aircraft and spacecraft in a direction other than the direction of forward propulsion. By altering the direction of gas flows leaving the craft pitch, roll, yaw and attitude control is obtained. To control gas flow from ports a variable throat thrust vectoring nozzle is described. Independent operation of ports, rotational nozzles, laterally moving flaps and rotational vanes assists the thrust vectoring of gases leaving aircraft or spacecraft ports. The ability to direct gases enhances maneuverability during vertical takeoff and landing, forward flight and space flight.

The invention provides an integrated large-angle rolling and posture adjusting rack car. The rack car comprises two parallel guide rails and two movable frames transversely erected on the guide rails. The movable frames can move along the guide rails through the rack car. Each movable frame comprises a rolling bracket and a butt joint bracket, the butt joint bracket is located on the side where the two movable frames are close to each other, and the rolling bracket is located on the side where the two movable frames are far from each other. The rack car further comprises a detachable rolling ring capable of rolling on the rolling bracket, the detachable rolling ring can be formed by connecting a plurality of equally-divided rings with the ends provided with connecting end faces and threaded holes, and the side faces of the equally-divided rings are provided with connecting holes. The integrated large-angle rolling and posture adjusting rack car integrates rocket part section large-angle rolling and part section posture adjusting, rocket part section assembling and part section posture adjusting are carried out on the same station, and the defects that due to repeated hoisting, total assembling efficiency is low and the safety performance is poor are overcome.

Light-weight, heat-managing structures feature open-cell lattice, honeycomb, and/or corrugated (prismatic) arrangements in their substructures, combined with heat pipe/heat plate arrangements for managing heat to which the structures are subjected. The structures are well suited to aerospace applications and may be employed in the leading edge of wings or other airfoil-shaped components; gas turbine engine components; rocket nozzles; and other high-heat, high-stress environments.

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.

An interceptor projectile includes a deployable net that deploys during flight and wraps around an incoming projectile, such as a rocket propelled grenade (RPG). The net is initially in a tubular body of the interceptor projectile. Weights are attached to ends of the net with metal cables. A propellant is used to deploy the net from the tubular body and to deploy the weights at acute angles to the longitudinal axis of the interceptor projectile. The weights move radially out from the interceptor projectile, expanding the net outward, and wrapping the net around an incoming projectile. The engagement of the net with the incoming projectile disables the incoming projectile, sending the incoming projectile off course.

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.

The invention discloses a hard polyimide foaming structural material and a preparation method thereof. The method comprises the following steps of: mixing aromatic dianhydride and/or aromatic acid ester, high molecular alcohol, low molecular alcohol, a catalyst and a surfactant according to a ratio into a polar solvent and reacting to form polyimide foam precursor solution; reacting the precursor solution with isocyanate in a die; pressurizing and foaming to form a polyimide foam intermediate; and performing microwave radiation or/and performing heat curing by using an oven to obtain the hard polyimide foaming structural material. The preparation process route is short and the process is simple; the storage stability of the foam precursor solution is high; and the prepared hard polyimide foaming structural material has uniform aperture, hard quality, high strength, low density and high temperature resistance, is non-toxic and environmentally-friendly in the foaming process and easy to industrialize, and can be applied in the fields of electron, carrier rockets, aviation, ships, railway locomotives and the like.

A cargo carrier is disclosed for the efficient delivery of cargo to space, such as to support the International Space Station (ISS). Both pressurized and unpressurized cargo may be delivered into space on an expendable launch vehicle, such as the Delta-IV rocket. The cargo carrier may utilize a slightly modified Delta-IV second stage to provide on-orbit station keeping of the payload until it is transferred to the ISS. The cargo carrier can include an unpressurized section having a rigid central structure supporting a frame to which unpressurized cargo modules are coupled. In addition, a pressurized cargo section may be coupled to the unpressurized section. The cargo carrier may utilize existing on-orbit assets such as the European Automated Transfer Vehicle (ATV) to transfer the ISS cargo from a rendezvous orbit to the ISS.

The present invention provides fully renewable engine fuels derived completely from biomass sources. The fully renewable engine fuel is comprised of one or more low carbon number esters, one or more pentosan-derivable furans, one or more aromatic hydrocarbon, one or more C₄-C₁₀ straight chain alkanes derivable from polysaccharides, and one or more bio-oils. In addition, the fuel may contain triethanolamine. Such a lower octane renewable fuel may be utilized, for example, in automobile fuel, 100 LL aviation fuel applications, and turbine engine applications. These ethanol-based, fully renewable fuels may be formulated to have a wide range of octane values and energy, and may effectively be used to replace 100LL aviation fuel (known as AvGas), as well as high octane, rocket, diesel, and turbine engine fuels.

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.

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.

The invention discloses an electric conical valve type gas flow regulator for solid rocket ramjets. A drive motor is fixed to a connecting box. One end of a coupling is fixedly connected with a shaft of a motor, and a slider is disposed in a slide hole in the other end of the coupling. The slider is fixedly connected with a valve stem through a tension and pressure sensor. A drive nut is fixedly connected to a solid gas generator. The valve stem passes the drive nut and in threaded fit with the drive nut. A conical valve head is fixedly connected with the valve stem in a threaded manner and extends into a spray pipe of the gas generator. The gas generator is in an inner shell structure which is hollow. The valve stem is fitted in the inner shell, and a bushing is fitted between the valve stem and the gas generator. One end of the valve stem, close to the conical valve head, is provided with a peripheral circular groove, and a moving seal is disposed in the circular groove. A pressure sensor is mounted on the rear head of the gas generator. The electric conical valve type gas flow regulator for solid rocket ramjets is simple in structure, small in size, reliable in operation, low in ablation effect, low in cost, and accurately controllable.

An ordinance, such as a rocket propelled grenade, shield includes a net with hard points at select nodes of the net and cable guides on the side of the net. Cables under tension extend through the cable guides supporting the net typically in conjunction with a top cross bar, spaced top struts, and spaced bottom struts. This framis design facilitates entering and exiting the vehicle or structure.

A directed vapor deposition (DVD) method and system for applying at least one bond coating on at least one substrate for thermal barrier coating systems. The method and system provides for alloy strengthening in high temperature metallic alloys that can be melt or solid state processed to materials that one applies by vapor deposition. The creep strengthened coating contains nanoscopic particles of oxides, nitrides, borides, carbides, and other materials which are formed by reactive codeposition. An approach for reactive codeposition is plasma assisted directed vapor deposition. Accordingly, the resultant structure may be utilized for, but not limited thereto, high temperature coatings, e.g. for protecting rocket or power turbines, or diesel engine components. The resultant structure is has a greatly extended lifetime attributed in part to the elimination of coating spallation by the “rumpling” mechanism.

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.

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.

The present invention provides fully renewable engine fuels derived completely from biomass sources. In one embodiment the fully renewable engine fuel is comprised of one or more low carbon number esters, one or more pentosan-derivable furans, one or more aromatic hydrocarbon, one or more C₄-C₁₀ straight chain alkanes derivable from polysaccharides, and one or more bio-oils. In addition, the fuel may contain triethanolamine. Such a lower octane renewable fuel may be utilized, for example, in automobile fuel, 100 LL aviation fuel applications, and turbine engine applications. These ethanol-based, fully renewable fuels may be formulated to have a wide range of octane values and energy, and may effectively be used to replace 100 LL aviation fuel (known as AvGas), as well as high octane, rocket, diesel, and turbine engine fuels. In another embodiment, there is provided a synthetic high octane aviation fuel comprising isopentane and mesitylene, and process of producing same from a biomass.

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.

An active satellite dispenser is preferably attachable to a reusable launch vehicle for deployment of one or more satellites into one or more desired orbits. The active satellite dispenser includes a center mast that releasably receives the satellite(s), a liquid propellant rocket, and an orbital control system on an avionics pallet. In the preferred embodiment, a pressurized gas selectively pressurizes the propellant tanks (which may include fuel and oxidizer tanks), to provide propellant to the rocket. In operation, the launch vehicle releases the satellite dispenser in a first deployment orbit. The active dispenser rocket and orbital control system then transport the active dispenser and satellite(s) into the final deployment orbit. In the preferred embodiment the active dispenser can operate multiple times to place individual satellites in different orbits.

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.