44results about How to "Increase drag coefficient" 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.

The present invention relates to a device for reducing the pressure and velocity of a flowing fluid. According to the present invention, a cage has discs having through holes which come into close contact with an outer surface of a plug. The discs are stacked in a direction of a central shaft of the cage. Flow passage portions are formed on the stacked discs, wherein the flow passage portions communicate with the outer surfaces of the discs, and the inner surfaces which correspond to the through-holes so as to form flow passages between the stacked discs, and the direction of the flow passages changes to a circumferential direction and a vertical direction on the stacked discs. Additionally, the discs are stacked by applying one or more flow passage portions based on the number of times of the direction of the flow passage changes and the number of flow passage portions to the discs so as to control the increasing velocity of the flow rate of the fluid according to the degree of opening formed upon upward movements of the plug.

The invention relates to a profile modification agent for an epoxy resin emulsion, which is used for solving the problem of poor selectivity of the conventional organic resin plugging agent. The profile modification agent for an acrylic monomer grafted epoxy resin emulsion is obtained by polymerizing epoxy resin with an acrylic monomer, neutralizing with N,N-dimethylethanolamine and emulsifying with deionized water, wherein the concentration of the epoxy resin in an emulsion system is 300-600 mg / L, the concentration of the N,N-dimethylethanolamine is 3,000-5,000 mg / L, and the crosslinking ratio is 10:1 or 20:1 or 40:1. When the profile modification agent is in use, a large quantity of gel particles of the emulsion enter large pore canals while a small quantity of or no gel particle enterssmall pore canals, the resistance coefficients of the large pore canals are increased, and the resistance coefficients of the small pore canals are increased at a lower frequency in comparison to thelarge pore canals, so that selective plugging can be realized; and moreover, the profile modification agent has high temperature resistance and high salt resistance, and the emulsion system is stable.

The invention relates to a passive fluidic resistor suspension with an equivalent mechanical structure, and belongs to the technical field of engine supporting structures. The passive fluidic resistor suspension with the equivalent mechanical structure mainly comprises an external rubber mainspring, an upper connecting bolt connected with the external rubber mainspring, an external supporting spring, an upper fluid chamber, a lower fluid chamber, an inner gas chamber, an inner spring, a mass block and the like, wherein the inner spring and the mass block are arranged in the inner gas chamber. The upper fluid chamber which tightly abuts against the upper end face of a partition board between the upper fluid chamber and the lower fluid chamber, an external gas chamber and the inner gas chamber are arranged in sequence from outside to inside. The lower fluid chamber tightly abuts against the lower end face of the partition board between the upper fluid chamber and the lower fluid chamber. An inertia channel which enables the upper fluid chamber to be communicated with the lower fluid chamber is arranged in the partition board between the upper fluid chamber and the lower fluid chamber. According to the passive fluidic resistor suspension with the equivalent mechanical structure, the notch frequency of the fluidic resistor suspension is constant within a low frequency range, but the dynamic stiffness of the fluidic resistor suspension is reduced as far as possible within a notch frequency range; in addition, the dynamic stiffness of a corresponding peak frequency is reduced as far as possible, the noise lowering effect and the damping effect of the engine fluidic resistor suspension are improved within the low frequency range, and the fatigue performance and the creep property of the fluidic resistor suspension can also be improved.

The invention relates to a self-pressurizing cryoablation system controlled by PID, which comprises cryoablation equipment and a cryoablation catheter, wherein the cryoablation equipment comprises a control unit, a vacuum unit and a delivery unit; the delivery unit comprises an air source manufacturing device, an air path control device, a low-temperature conversion device and an equipment connecting piece which are sequentially connected; an air outlet end of the equipment connecting piece and the vacuum unit are respectively communicated with the cryoablation catheter; the low-temperature conversion device comprises a Dewar bottle and a heat exchanger, the air source manufacturing device is arranged in the Dewar bottle, the air outlet end of the air source manufacturing device is communicated with an air inlet end of the air path control device; the air source manufacturing device comprises a coolant storage tank, a pressure relief valve communicated with the coolant storage tank, acoolant supplement joint communicated with the coolant storage tank and a heating device arranged in the coolant storage tank; the control unit comprises a PID controller, and the heating device is electrically connected with the PID controller; and a large and heavy pressurized gas tank is not required to be externally connected, so that a space of the cryoablation equipment is saved.

The invention discloses a device for driving solid-liquid two-phase flow to form abrasive water jet based on the electromagnetic principle. The device comprises a control box, an electromagnetic driving device and an intermittent on / off device. The electromagnetic driving device comprises a main flow coarse channel, an upper inclined and thin channel and a lower inclined and thin channel. The upper side and the lower side of the main flow coarse channel are both provided with connecting end openings. An input end opening of the upper inclined and thin channel and an input end opening of the lower inclined and thin channel are both provided with flow guide areas. Each flow guide area is composed of an upper transition arc-shaped region and a lower transition arc-shaped region. Each upper transition arc-shaped region is provided with an arc A. Each lower transition arc-shaped region is composed of an extending section, an arc-shaped transition section and an inclined section. According to the device, the function of driving the solid-liquid two-phase flow to form continuous abrasive water jet through intermittent multi-directional combination is adopted, the phenomenon of electrolysis in the device can be effectively avoided, pressure energy losses are effectively reduced, and the effect of driving the solid-liquid two-phase flow to form an abrasive water jet pressure head through the device is effectively improved.

The invention discloses a compounded type cationic polyacrylamide profile control agent which comprises the following components in percentage by mass: 0.2-0.8% of compounded type cationic polyacrylamide, 0.5-0.7% of a phenolic aldehyde cross-linking agent, and the balance of water, wherein the compounded type cationic polyacrylamide comprises the following components in percentage by mass: 3-12% of cationic polyacrylamide with the molecular weight of 5000-15,000,000, and 88-97% of nonionic polyacrylamide with the molecular weight of 8000-12,000,000. According to the profile control agent disclosed by the invention, cationic polyacrylamide is adopted as a polymer, and due to attraction of the positive charges of cationic polyacrylamide and the negative charges of reservoir stratum rock, the viscous force of the profile control agent with rock is improved, the plugging strength is improved, and the effective period of profile control is prolonged.

The invention discloses a solid carrier rocket sub-stage capable of being recycled and reused. The solid carrier rocket sub-stage comprises a sub-stage body, an inflatable heat protection structure and a solid rocket engine; the inflatable heat protection structure comprises a front-end airbag which covers the windward side of a front cabin section under an expanding state and is in a shape of a rotating body, and the front-end airbag comprises a flexible heat-insulating layer and a heat-proof coating which are sequentially arranged from inside to outside; and the solid rocket engine comprisesa combustion chamber shell with a cavity allowing a grain to be placed, and a combustion chamber heat protection structure is arranged on the inner wall of the combustion chamber shell. By adopting the inflatable heat protection structure with heat protection, deceleration and buffering combined, the front-end airbag can maintain the good aerodynamic shape, the sub-stage is not damaged due to pneumatic heating and large landing impact force in the reentry process, and can be recycled, through re-charging, replacing of disposable parts and the like of the rocket engine, the sub-stage and the engine thereof can be reused, and thus the launching cost of a solid carrier rocket is lowered.

The invention provides a composite conical slotted parachute applied to a supersonic low-density parachute opening environment, and a structural design method thereof. The parachute disclosed by the invention comprises two parts, namely a canopy and parachute cords, wherein the fabric surface of the canopy is composed of a composite conical upper part and a cylindrical canopy bottom, which are vertically separated from the middle by virtue of a wide gap; and the composite conical upper part comprises a top cone, a middle cone and a bottom cone. The composite conical slotted parachute has the advantages of high resistance coefficient and high stability, the defects of an existing background technology are overcome, and the composite conical slotted parachute is an excellent supersonic low-density parachute.

The invention relates to double-wing non-parachute terminal sensing ammunition which comprises a projectile body (1), a large wing (2) and a small wing (3), wherein the large wing (2) and the small wing (3) are arranged at the two sides of the projectile body (1) in a staggered manner; a connection position of the large wing (2) and the projectile body (1) is positioned on the top of the projectile body (1); the large wing (2) deviates to left by 1 / 3 and deviates to right by 2 / 3 relative to the axis of the projectile body (1); and a connection position of the small wing (3) and the projectile body (1) is positioned on the top of the projectile body (1), and the small wing (3) deviates to left by 2 / 3 and deviates to right by 1 / 3 relative to the axis of the projectile body (1). According to the double-wing non-parachute terminal sensing ammunition, a resistance coefficient is increased by about 10%, a rotating torque coefficient is doubled, and steady-state scanning time and rotation speed of the non-parachute terminal sensing ammunition are improved.

The invention discloses an aircraft stress simulation method used in a flight stall state, which comprises the following steps: S1, establishing an aircraft body coordinate system and a ground inertial coordinate system, and obtaining an aircraft airspeed, an aircraft acceleration, an attitude rotation matrix and a rotation angular speed; S2, calculating to obtain an attack angle and a sideslip angle of the aircraft and an attack angle change rate of the attack angle along with time according to the aircraft airspeed, the aircraft acceleration, the attitude rotation matrix and the rotation angle speed; S3, according to the attack angle and the attack angle change rate, calculating an airflow separation identifier based on the airflow separation hysteresis characteristic of the wing; S4, calculating a corrected lift coefficient and a corrected resistance coefficient according to the airflow separation identifier so as to correct the aerodynamic parameters of the aircraft; and S5, calculating a corrected aerodynamic moment coefficient according to the airflow separation identifier so as to correct the aerodynamic moment parameter of the aircraft. The method has the technical characteristics that the deep tail spin flight characteristic is simulated and displayed, and the simulation result is vivid.

The invention relates to an ejection seat stabilization parachute which comprises a canopy and parachute cords. The canopy comprises a primary top width, a secondary top width and a skirt width whichare connected sequentially from top to bottom, the skirt width bends outwards, a row of evenly distributed crescent holes are formed by stitching the primary top width and the secondary top width at intervals, another row of evenly distributed crescent holes are formed by stitching the secondary top width and the skirt width at intervals, openings of the crescent holes of the upper row are locatedin the upper outer side of the secondary top width, openings of the crescent holes of the lower row are located in the upper outer side of the skirt width, and the crescent holes on the same row areidentical in size. The ejection seat stabilization parachute is small in parachute opening forces, rapid in stabilization, high in stabilization, lightweight and simple in manufacture.

The invention discloses a tube internal and external expansion type spiral corrugated tube, and relates to the field of heat transfer devices. The invention aims to solve the problem that local resistance of the internal and external flowing of the tube is large and the comprehensive heat exchange performance improvement is not obvious due to the structure of an existing reinforced heat exchange tube. The tube internal and external expansion type spiral corrugated tube comprise a hollow pipe body, a spiral corrugated channel is arranged on the outer circumference side wall of the hollow pipe body, the spiral corrugated channel is spirally and uniformly arranged on the outer circumference side wall of the hollow pipe body in the length direction, the cross section of the spiral corrugated channel is an arc shape with the middle part protruding outwards in the radial direction. The tube internal and external expansion type spiral corrugated tube is used for reinforcing heat exchange technology.

The invention discloses a water source carbon dioxide heat pump system with a buffer tank, which belongs to the carbon dioxide heat pump system. The internal pressure of the existing carbon dioxide unit system is high, and the water source carbon dioxide unit adopting a piston compressor has periodicity due to the exhaust of the compressor The internal high-pressure airflow plus the periodic pulsation state will cause the pipeline to violently vibrate, which will have an irreversible impact on the safety and long-term stable operation of the system. The buffer tank is connected in series with the carbon dioxide inlet for heat exchange between the gas port and the gas cooler, and the gas flow direction inside the buffer tank is changed to buffer the gas ejected from the cylinder, thereby increasing the resistance coefficient of the air flow pulsation, achieving shock absorption and The purpose of enhancing unit reliability.

The present invention relates to uncooled microbolometers which can be integrated in future thermal instruments engaged in land imaging on future observatories. The present invention includes: (1) developing and characterizing a microstructured VOx thin film, and, (2) fabricating an uncooled microbolometer array over the 8-14 micron spectral band.

An electrochemical sensor is provided that includes a housing having an outer wall, an axial bore circumscribed by the outer wall, and a barrier wall that aids in defining a reference cavity. The housing further including a plurality of cross members in spaced relation to one another disposed between the axial bore and the outer wall, each cross member defining an aperture. A junction plug is disposed at the distal end of the housing. The junction plug comprises a porous material that enables ionic flow through the junction plug. The sensor enables ionic communication between the target fluid and the reference electrode within the reference cavity through the apertures of the plurality of cross members. In this manner, the sensor provides generally a long, tortuous flow path, or salt bridge, between the target fluid and the reference electrode, resulting in a high resistance factor for the sensor.

An electrochemical sensor is provided that includes a housing having an outer wall, a plurality of longitudinal walls disposed within the outer wall, and a reference chamber housing a reference electrode. The longitudinal walls define a plurality of longitudinal chambers. Ionic communication between the target fluid and the reference electrode passes sequentially through each of longitudinal chambers from a first longitudinal chamber to the reference chamber. In this manner, the sensor provides generally a long, tortuous flow path, or salt bridge, between the target fluid and the reference electrode, resulting in a high resistance factor for the sensor.

The invention relates to a feed water regulating valve which comprises a valve body, a valve core and a valve seat, wherein the valve core and the valve seat are arranged in the valve body; the valve core is also connected with a valve rod; a labyrinth disc is arranged above the valve seat in the valve body; a flow equalization cover is arranged above the labyrinth disc; the labyrinth disc and the flow equalization cover are annular; and the valve core can pass through the labyrinth disc and the flow equalization cover in a sliding way. In the valve core structure of the invention, a labyrinth type zigzag flow passage structure and a new multi-stage balanced depressurized valve core design are adopted, thereby improving the resistance coefficient of a throttling component, increasing the adjustable amplitude of the resistance coefficient, reducing the flow rate of the flow passage, greatly improving the flow regulating performance of a high differential pressure regulating valve, reducing the vibration and the noise of the regulating valve and prolonging the service life.

A fluid control valve for use in a fluid delivery system for delivering fluid to a patient includes a valve body defining an internal chamber, a first inlet port for receiving a first inlet tube, a second inlet port for receiving a second inlet tube, an outlet port, and a sliding valve member slidably disposed in the internal chamber. The first inlet tube defines a first inlet lumen axially aligned with the internal chamber. The second inlet tube defines a second inlet lumen axially aligned with the internal chamber. The sliding valve member includes a first sealing end and second sealing end. The sliding valve member is positionable in a first operating state, a second operating state, and a third operating state based on a flow differential between the first inlet lumen and the second inlet lumen.

The invention provides a spherical slotted parachute applied to a supersonic low-density parachute opening environment and a structure design method of the spherical slotted parachute. A parachute canopy is shaped like a dense fabric parachute, and is structurally shaped like a 210-degree sphere, the bottom edge of the hemisphere extends by 15 degrees, and the parachute canopy tends to be hemispherical in a complete opening state. In order to improve the stability, a wide slot is formed in the maximum diameter of the parachute canopy to achieve certain structural air permeability. The spherical slotted parachute has the advantages of high resistance coefficient, high stability, uniform parachute canopy stress distribution, low parachute opening dynamic load and high flutter resistance, and is an excellent supersonic low-density parachute, and the defects in the prior art are overcome.

The invention belongs to the technical field of mechanical vibration, and discloses a damping shock absorber which comprises an upper shell, a lower shell, a supporting plate, a first connecting rod and a second connecting rod. A first cavity is formed in the upper shell, and a first permanent magnet is arranged in the first cavity. The lower shell is provided with a second cavity. The supporting plate is arranged between the upper shell and the lower shell, and a universal ball is arranged in the middle of the supporting plate. The first end of the first connecting rod is connected with the universal ball, the second end of the first connecting rod is provided with an energy dissipation panel, and a first magnetic liquid is arranged between the energy dissipation panel and the first cavity. The first end of the second connecting rod is connected with the universal ball, the first connecting rod and the second connecting rod are coaxially arranged, the second end of the second connecting rod is provided with a second permanent magnet, and a second magnetic liquid is arranged between the second permanent magnet and the second cavity. According to the damping shock absorber, the equivalent stiffness coefficient of the shock absorber can be effectively changed, the resistance coefficient is increased, multi-dimensional shock absorption is achieved, the shock absorption effect and efficiency of the shock absorber are greatly improved, and the practicability is higher.

The invention aims at disclosing a throttle element for a direct-current vapor generator. The throttle element comprises a cylindrical body. An inlet runner is arranged in the center of the body. Water flowing holes are symmetrically formed in the two sides of the bottom of the inlet runner. Multiple stages of impellers are arranged on the outer side of the lower portion of the body, and a sealing thread is arranged on the outer side of the upper portion of the body. Compared with the prior art, the throttle element is conveniently mounted at the end of a heat transfer pipe through the sealing thread, the number of the impellers and the size of gaps are selected according to the needed resistance coefficient, the large resistance coefficient can be achieved, no small runner clearance exists, the possibility that blocking happening after long-time operating is reduced, good universality and expansibility are achieved, and the aim of the throttle element is achieved.

The invention provides an oil displacement system for a heterogeneous oil reservoir. The oil displacement system comprises association polymer, molecular weight of the association polymer is 1.036-40.215 million, the association polymer is obtained by polymerizing, by molar percent, acrylamide, 0.11-9.96% of hydrophobic monomer and 0-15.4% of functional monomer, and concentration of the association polymer in the oil displacement system is 400-3500mg / L. compared with the prior art, the oil displacement system has the advantages that the association polymer obtained by introducing a small amount of the hydrophobic monomer and the functional monomer on molecule main chain of polymer is adopted, and hydrophobic groups are mutually associated in a water solution to form a spatial network structure, so that viscosity of the system is improved, high resistivity coefficient and high residual resistance coefficient are established, permeability of relatively-high-permeation areas is lowered effectively, and the oil displacement system has good profile control effect; due to introduction of the functional monomer and the spatial network structure, the system has good temperature-resistant, salt-resistant, shearing-resistant and aging-resistant stability and has better effects on improving oil-water mobility ratio and injection water wave and efficiency of the heterogeneous oil reservoir, thereby better improving recovery ratio of the heterogeneous oil reservoir.

The present invention relates to a method for increasing the field of vision in the mirror of a vehicle outside rearview mirror device (1) fixed on at least one side of a vehicle especially automobile. The method includes the steps of: mounting a convex spherical mirror (2) which has a curvature radius about 120-135 cm to the rearview mirror device (1); fixing the rearview mirror to the vehicle such that a distance between the center of the convex spherical mirror (2) of the mirror and a median of a segment, connecting the eyes of a driver of the motor vehicle, projected on a longitudinal axis of the vehicle is in the order of twenty to forty centimeters. The invention also relates to a vehicle for implementing the method, especially automobile.

The invention discloses a solid carrier rocket sub-stage capable of being recycled and reused. The solid carrier rocket sub-stage comprises a sub-stage body, an inflatable heat protection structure and a solid rocket engine; the inflatable heat protection structure comprises a front-end airbag which covers the windward side of a front cabin section under an expanding state and is in a shape of a rotating body, and the front-end airbag comprises a flexible heat-insulating layer and a heat-proof coating which are sequentially arranged from inside to outside; and the solid rocket engine comprisesa combustion chamber shell with a cavity allowing a grain to be placed, and a combustion chamber heat protection structure is arranged on the inner wall of the combustion chamber shell. By adopting the inflatable heat protection structure with heat protection, deceleration and buffering combined, the front-end airbag can maintain the good aerodynamic shape, the sub-stage is not damaged due to pneumatic heating and large landing impact force in the reentry process, and can be recycled, through re-charging, replacing of disposable parts and the like of the rocket engine, the sub-stage and the engine thereof can be reused, and thus the launching cost of a solid carrier rocket is lowered.

The invention discloses a dual-channel hydraulic suspension of an engine. The is internally provided with a main liquid chamber and a secondary liquid chamber are arranged at the inner part of the hydraulic suspension, wherein an ejection block, a runner plate, a decoupling piece and an iron clapboard are arranged between the main liquid chamber and the secondary liquid chamber; liquid is filled at the inner parts of the main liquid chamber and the secondary liquid chamber, a low-frequency vibration reduction fluid passage and a high-frequency vibration reduction fluid passage are arranged between the main liquid chamber and the secondary liquid chamber; the low-frequency vibration reduction fluid passage is arranged along the ejector block, the runner plate and the iron clapboard, and the high-frequency vibration reduction fluid passage is arranged along the runner plate, the decoupling piece and the iron clapboard. The hydraulic suspension can distinguish between low-frequency vibration and high-frequency vibration of an engine so as to realize isolation, vibration reduction and noise isolation.

The invention relates to a rear ring back-turning type balance drum of a multi-stage pump. The excircle of the balance drum is provided with a back-turning ring surface, the inner circle of a balance sleeve is provided with a back-turning ring surface corresponding to the back-turning ring surface of the excircle of the balance drum, and the two back-turning ring surfaces are mutually matched to form an S-shaped sealing gap, wherein the gap has the effect of increasing resistance on media passing through the gap. The front and the back of the balance drum form a balance force opposite to the sucking direction of the pump, and the balance force is used for balancing unbalanced axial forces such as impeller cover plate force, and the like acting on a rotor. By changing the seal between the balance drum and the balance sleeve into a labyrinth seal, the invention reduces the length of the balance drum, effectively reduces the leakage quantity, enhances the balance effect, improves the efficiency of the pump and optimizes the structure.