4272 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 fast acting active protection system for military vehicles defeats RPG (rocket propelled grenade) threats fired from close ranges. The system minimizes the hazard to troops and civilians nearby. The system uses a plurality of passive sensors to locate the threat and initialize the system. A low cost radar or laser tracker is used as the means to determine range, velocity, and (if required) angular position of the threat. The countermunition used may be one of several choices, with the requisites being that the countermunition provides fast response with low inertia, and is able to damage or destroy the detected threat. A multi-barrel recoilless gun is the weapon of choice. A launching device is used to deploy and aim the countermunition and the tracking means. On board software and electronics are used to control the system.

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.

Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.

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 improved system is provided for aiming a shotgun-based or other countermeasure system so as to be able to countermeasure incoming rockets or projectiles. In one embodiment a shotgun aimed and controlled by the subject system projects a pattern of pellets to intercept a rocket-propelled grenade or incoming projectile. The fire control system uses a CW two-tone monopulse radar to derive range and angle of arrival within 150 milliseconds, with range and angle of arrival measurements having approximately twice the accuracy of prior CW two-tone monopulse radars. The improvement derives from using all of the information in the returned radar beams and is the result of the recognition that one can use the Sum and Difference signals to assemble a two-by-two Rank One matrix that permits using singular value decomposition techniques to generate range and angle of arrival matrices in which all available information is used and in which noise is eliminated.

A child's toothbrush includes a handle in the form of a toy, such as a rocket ship or a vehicle, and wherein a toothbrush head and neck easily connects and disconnects from the handle. The handle may also contain a hollow compartment for holding stationary a removable vehicle, figurine, other toy or sundry product therein.

The invention provides a posture adjustment assembly system used for butt joint of components of a rocket. The posture adjustment assembly system comprises a posture adjustment system, a test system and a controller, wherein the posture adjustment system comprises first guide rails, beams and guide rail wheels, the guide rail wheels can move along the first guide rails through a horizontal moving mechanism, the posture adjustment system further comprises two posture adjustment devices arranged in parallel, each posture adjustment device is transversely arranged on the upper sides of the two first guide rails and is connected with the top faces of the beams, and each posture adjustment device comprises a supporting beam, a lifting table, a bracket support and an arc-shaped bracket. A posture adjustment method of the posture adjustment assembly system used for butt joint of the components of the rocket includes six steps. The posture adjustment system comprises the two posture adjustment devices, and the test system comprises an optical measurement device, measurement points located at the end of a rocket body and a processor. When only one single posture adjustment device is combined with the first guide rails, the guide rail wheels and the horizontal moving mechanism, four-freedom-degree posture adjustment can be achieved; when the two posture adjustment devices are used in cooperation with each other, six-freedom-degree posture adjustment can be achieved, and the two posture adjustment devices are independent, do not interfere with each other during six-freedom-degree adjustment and are matched with each other during adjustment.

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.

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.

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 2pi 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.

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.

A modular reconnaissance capsule or reconnaissance pod is provided that is suitable for deployment by means of an artillery launching platform, such as a conventional 40 mm grenade launcher or 155 mm cannon wherein a parachute is deployed at a pre-calculated observation altitude, the parachute being designed to yield a sufficiently slow rate of descent to permit live video capture and transmission of images as forward observation information. Alternatively, pods according to the invention may also be air dropped from an aircraft, either piloted or pilotless, thus allowing the aircraft to operate at a safe distance and yet provide close reconnaissance even under a cloud cover. Accurate information about targeting dynamics is made available to the user through commercially available products. The invention complements other reconnaissance methods and provides easy-to-use real-time visual information for a desired area of interest.

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.