34 results about "Hypervelocity" patented technology

Launching payloads at high velocity uses high-pressure gas or combustion products for propulsion, with injection of high pressure gas at intervals along the path behind the payload projectile as it accelerates along the barrel of the launcher. An inner barrel has an interior diameter equal to the projectile diameter or sabot containing the projectile. An outer casing surrounds the inner barrel. Structures at intervals attach the outer casing and the inner barrel. An axial gas containment chamber (AGC) stores high pressure gas between the inner barrel wall, the outer casing wall, and enclosure bulkheads. Pressure-activated valves along the barrel sequentially release the high pressure gas contained in the AGC in to the barrel to create a continuously refreshed high energy pressure heads behind the projectile as it moves down the barrel. A frangible cover at the exit end of the barrel allows the barrel to be evacuated prior to launch. The launcher is rapidly recyclable. The valves close automatically after the projectile has exited the barrel, allowing a new projectile to be introduced into the breech and the AGC to be recharged with high-pressure gas.

The invention discloses a common-channel OCT (optical coherence tomography) ultra-large range space measurement system and method. A gain compensation type polarization-maintaining fiber optical circulation cavity is arranged in a sweep frequency OCT imaging system, and the optical circulation of the P-channel light and the S-channel light with different optical paths in the same polarization-maintaining fiber is realized based on the birefringence effect of the polarization-maintaining fiber. The low-coherence interference between the sample lights of different depth areas and the reference light with the ultra-large range is realized based on the hypervelocity stepping change of the optical path difference between the P-channel light and S-channel light. The coding of the interference signals of different depth areas within the ultra-large range is realized based on different carrier frequencies of an electrooptical modulator on the P-channel light and S-channel light in the optical circulation cavity of the polarization-maintaining fiber. A wave plate is arranged in front of the sample surface so as to realize the common channel of the reference light and the sample light; and the common-mode rejection of DC (direct current) term in the interference signal is realized by use of the dual-channel balance detection of the polarization light split. The system disclosed by the invention has a compact structure and high stability, and effectively improves the quantization precision and dynamic range of the interference signal.

The invention provides a navigation device for vehicle over-speed alarming and prompting. The invention comprises a position signal receiving unit for receiving and processing GPS and / or GPSOne wireless communication signals, a storage unit for storing various electronic map data and vehicle running geographic position information, an audio unit for transmitting or outputting over-speed alarming audio signals, a power unit for providing a power supply for the navigation device, and a controlling unit, wherein, the controlling unit is respectively connected with the units, and through comparing the vehicle running speed with the speed limit standard of the geographic position information, the positioning and the over-speed alarming and prompting of the navigation device are controlled and realized. The invention also provides a method for the vehicle over-speed alarming and prompting. The invention not only realizes the usual functions of the navigation device, but also can inform users of over quick the vehicle running speed in a way of voice prompting, or character displaying, etc. when the vehicle drives over speed, thereby the driving security is enhanced.

Apparatus for inductive braking of a projectile are disclosed. Embodiments include a receiver that has a unidirectional conductor having a closed conductive pathway that encircles a passageway for a moving projectile. The unidirectional conductor permits current to flow through it in substantially only one direction around the passageway. As the projectile and its associated magnetic field move past the unidirectional conductor, the moving magnetic field induces a current flow through the closed conductive pathway, which in turn generates a magnetic field behind the projectile having the same polarity as the projectile's field. The two fields attract one another, which both exerts a braking force on the projectile and tends to align the two fields. Alignment of these fields centers the projectile away from the passageway wall. Because the unidirectional conductor permits current to flow in substantially only the direction that produces a field having the same polarity as the moving field, the opposite-polarity repulsive magnetic field that would otherwise be generated ahead of the projectile, which would otherwise deflect the projectile from its path, is suppressed. Methods of inductive braking are also disclosed.

A shear-thickening fluid is used in conjunction with fabrics utilized in an expandable spacecraft. The combination of the fluid and the fabric allows the fabric to resist penetration by hypervelocity particles in space.

A hypervelocity impact detection method and system for determining the precise impact location in a detection surface, of impacts such as ballistic missile intercepts, micrometeoroids and orbital debris (MMOD) or other shock events, utilizes a gridless detection surface capable of propagating radio frequency (RF) impact detection signals responsive to receiving hypervelocity impacts from objects, and multiple sensors on the detection surface that directly measure radio frequency RF emissions generated by the hypervelocity impacts on the surface, and a time of arrival (TOA) position measurement technique for determining the precise impact location in the detection surface.

The invention discloses a wind generating set variable rate feathering halt method based on accelerated velocity of an engine room. On the basis of a conventional control strategy, a variable rate feathering module based on the former accelerated velocity and the current accelerated velocity of the engine room is added. The method comprises the steps that when the set enters the halt logic, firstly, whether the fault type triggered by the set is software hypervelocity halt alarm or not is judged; If no, the corresponding halt logic action is taken, and if yes, the variable rate feathering haltlogic based on the accelerated velocity of the engine room is adopted; the former accelerated velocity and the current accelerated velocity of the engine room are measured in real time through a sensor; after filtering is conducted through a filter, a feathering rate value is output to be superposed with an original feathering rate value output by a controller; and then, amplitude limiting is conducted, and a final feathering rate value is multiplied by the cycling time of the controller, so that a final pitch angle given value is obtained and transmitted to a variable pitch system till all vane pitch angles reach the maximum pitch angle and the feathering halt action is completed. By means of the method, the load optimization control, under the special working condition, over the wind generating set can be achieved.

The invention relates to a light beam generator and a digital holography device for hypervelocity holography. The light beam generator comprises a pulsed laser and a multi-mode fiber coupler, wherein the multi-mode fiber coupler comprises an odd number of output ends on the same plane, and the number of the output ends is the same as that of beam splitting laser pulses; the optical fiber length differences among all the output ends are determined on the basis of a preset relative time delay, and the positions of all the output ends on the plane are determined on the basis of a preset spatial orientation angular difference; and the arrangement of the output ends ensures that any two output ends do not form central symmetry. The digital holography device comprises the light beam generator and a subsequent optical system, wherein the subsequent optical system comprises a second lens and a photosensitive device. By implementing the invention, laser pulses having different spatial orientation angle codes and strictly controlled relative time delays can be conveniently obtained so as to form a plurality of hypervelocity holographic images, and the invention has simple and compact structure and high system stability and reliability.

A hybrid gun device composed of two barrels (1,10) that accept energy from combustion of standard propellant (6), one barrel (10) being operative to produce a high intensity electric current to add accelerating energy to a projectile (7) in the second barrel (1) and at least one coil (8) stage to convert energy between electrical and kinetic to cause the projectile (7) to be launched at hypervelocity.

A method and system for detecting hypervelocity impacts on a detection surface utilizes multiple sensors that directly measure electrical pulse radio frequency (RF) emissions generated by hypervelocity impacts on a detection surface and time of arrival (TOA) position measurements for determining the precise impact location on the detection surface. The detection surface material is compressed differentially in such a way that the inherent equalization of the compressed electron density in one area of the impact is directed to the uncompressed area of the material causing an electrical current that flows until the redistribution of the electrical charge has been completed and the rapid redistribution of charge and inherent current that results emits the radio frequency pulse that is induced into the detection surface.

The invention discloses a Mars dust collecting device in the hypervelocity flight state. The Mars dust collecting device comprises a dust particle collecting port, a gas inlet pipe, a filtering and collecting device, an exhaust pipe and a returner, wherein the filtering and collecting device is installed in the returner; the returner is installed inside a detector; the gas inlet pipe and exhaust pipe respectively penetrate through the returner and are connected with the filtering and collecting device; the dust particle collecting port and exhaust pipe are connected with the outer side of the detector; the dust particle collecting port is connected with the front end of the gas inlet pipe; the gas inlet pipe is connected with a filtering inlet of the filtering and collecting device; and a filtering outlet of the filtering and collecting device is connected with the exhaust pipe. The Mars dust collecting device can implement filter-type fine dust sampling in the Mars atmosphere in the hypervelocity flight state, avoids the links of landing-descending and Mars surface rising in the traditional sampling return process, reduces the detector weight and task complexity, and thus, has engineering application value. The Mars dust collecting device has favorable expandability, and lays the foundation for other subsequent planet sampling detection and development in China.

A method, device, and projectile having a device for guiding or piloting projectiles or missiles (self-propelled or non-self-propelled), to deflect, in a direction Y, a hypervelocity projectile operating in a gas, such as a shell, a bullet, or a missile, having a nose, generally in the shape of a cone, with a more or less pointed tip, by generating a first high-voltage discharge able to produce a plasma over a first limited sector of the projectile surface and in direction Y, maintaining the plasma, and generating another low-voltage discharge able to supply the plasma with energy over a second limited sector of the projectile surface and in direction Y, the first and the second sectors being different and may overlap.

The invention discloses a pneumatic ball valve for a hypervelocity wind tunnel throat and a processing method of the pneumatic ball valve. When the pneumatic ball valve is opened, axisymmetric profilechannels are formed among central through holes of a left end cover, a ball core and a right end cover, and the axisymmetric profile channels are in smooth transition with the throat profile and arepart of the throat profile. The processing method of the pneumatic ball valve comprises the steps: a. processing a solid first pneumatic ball valve according to the size of the hypervelocity wind tunnel throat; b. opening and fixing the solid first pneumatic ball valve to obtain a solid second solid pneumatic ball valve; c. mounting the solid second pneumatic ball valve on the hypervelocity wind tunnel throat; and d. integrally processing the solid second pneumatic ball valve with the hypervelocity wind tunnel throat to obtain the pneumatic ball valve with the axisymmetric profile channels. The pneumatic ball valve can quickly stop the throat and prevent driving gas from scouring a sensor; and the driving gas and test gas can be effectively separated, and the reuse of the driving gas is convenient. The processing method of the pneumatic ball valve has the advantages of integrity, high machining precision and good consistency with the profile of the hypervelocity wind tunnel throat.

When the existing vehicles are in running, the functions of braking and emergency braking which are used all the time are extremely important. When in the brake, certain vehicles brake the wheels by a brake and other vehicles close the throttle and break the energy supply for running at the same time. The invention provides a vehicle over-speed anti-collision emergency brake which aims at solving the problem of collision and rear collision caused by that due to the inertia, the existing vehicle can not be braked under emergency situation.

The invention relates to the technical field of hypervelocity impact loading tests, in particular to a sabot separation device. The electromagnetic sabot separation device for a light-gas gun comprises an annular casing, annular electromagnets, a sensing device, a controller and an electric storage device, wherein a projectile and the sabot are accelerated by the light-gas gun to enter an electromagnetic separation device connected with a gun muzzle, and when the projectile and the sabot pass through the sensing device located on the inner wall of the electromagnetic separation device, the sensing device triggers the controller to control the electric storage device to produce strong current to power on the annular electromagnets and the annular electromagnets produce strong attraction force on the sabot made of a ferromagnetic high-polymer material. The sabot with a split structure is separated towards the lateral direction under the action of uneven electromagnetic attraction force,and meanwhile, after the sabot flies over the positions of the electromagnets, the annular electromagnets produce backward electromagnetic force on the sabot to slow down the sabot, so that the sabotand the projectile are separated. The sabot is separated from the projectile stably and smoothly without impact.