67results about How to "Increase fuel capacity" patented technology

The present invention relates generally a method and apparatus for adjusting the buoyancy of towed seismic arrays comprising a plurality of streamers and specifically to the dynamic buoyancy control of the buoyancy of a towed array of streamers by means of applying current to electroactive polymers (EAP) incorporated within the towed array of seismic streamers. The bulk density of the streamer array is electrically altered to accomplish neutral buoyancy for a towed array of streamers within the full range of water-densities from fresh to extremely dense seawater.

A novel containment system for encapsulating nuclear fuel particles is disclosed. The containment system has a gas-impervious ceramic composite hollow shell having a spheroidal or ovoidal shape. The shell has a pair of longitudinally aligned round openings that are sealed with a gas-impervious ceramic composite tube to define a cavity between the shell inner surface and the tube outer surface. A ceramic composite matrix containing the nuclear fuel particles is enclosed within the cavity. The ceramic composite matrix has a controlled porosity, and can contain moderators or neutron absorbing material. The tube and shell are composed of a ceramic matrix composite material composed of ceramic reinforcement material that is bound together by a polymer-derived ceramic material.

A fuel delivery system for a gas turbine engine includes a catalytic device for treating fuel to increase the usable cooling capability of an endothermic fuel. The catalytic device operates to treat and decompose components within in the fuel to render the fuel non-coking beyond 250° F. The catalytic device includes material that initiates reactions, and decomposition of coke forming components within the fuel to non-coke forming components within the fuel.

The invention relates to functional medium and long chain fatty acid glyceride microcapsules. The functional medium and long chain fatty acid glyceride microcapsules consist of plant blend oil, a wallmaterial, an emulsifying agent, an oil phase antioxidant, an aqueous phase antioxidant, a metal chelator, a heat stabilizer and an anticaking agent. Based on 100 parts of the microcapsules, 30-60 parts of the plant blend oil is added, the plant blend oil comprises the following raw material components in parts by weight: 10-20 parts of linseed oil, 1-3 parts of plukenetia volubilis Linneo oil, 20-30 parts of fructus perillae oil, 1-3 parts of peony seed oil, 1-3 parts of sea buckthorn seed oil, 5-10 parts of cannabis sativa seed oil, 5-20 parts of Chinese wolfberry fruit seed oil, 1-2 parts of acer truncatum seed oil, 10-22 parts of pumpkin seed oil, 3-7 parts of evening primrose oil, 1-5 parts of shea butter, and 16-21 parts of coconut oil. The functional medium and long chain fatty acidglyceride microcapsules have the advantages of having positive effects on reducing blood lipid, improving insulin resistance, protecting endothelial cell functions of cardiovascular disorders, preventing coronary heart diseases, improving protective screen of the immune function of intestines, controlling body weight, and preventing breast cancer, prostatic cancer and carcinoma of colon and rectum.

The invention provides a carotenoid preparation which relates to oil suspension, a feed which contains the carotenoid preparation, a method used for preparing the feed, and the use as additives of animal feed, food, cosmetics and / or medicines used for the carotenoid preparation. Effective compositions in the feed grains are uniformly distributed; furthermore, most of the effective compositions are distributed in the grains, thus reducing the surface oxidation loss; the carotenoid exists in a dissolved state, thus being beneficial for the absorption and utilization of animals; the animal testsalso show that the coloring effect of the fish is extremely good after the feed grains are used for feeding the fish.

The invention provides a multifunctional unmanned plane launch and recovery vehicle which consists of a carrier, a lifting bracket, a gaseous catapult, recovery devices and an unmanned plane transfer box. The bottom of the lifting bracket is connected with the carrier, the gaseous catapult is arranged at the top part of the middle of the lifting bracket through a hinge, the recovery devices are arranged at the two sides of the lifting bracket, and the unmanned plane transfer box is arranged in the middle part of an upper bracket of the carrier. The recovery vehicle successfully solves launch and recovery difficulties which cannot be solved by an unmanned plane. The multifunctional unmanned plane launch and recovery vehicle has the following advantages that: (1) launch, recovery, storage and carrying in vehicle are integrated together, continuous launch and recovery of multiple planes can be achieved, no damage of planes is caused during transport in marching, planes can be launched and recovered at any time, the multifunctional unmanned plane launch and recovery vehicle can be suitable for bad field environment and can be free of ground environment influence; and (2) the flying resistance is low as the unmanned plane has no undercarriage, the unmanned plane does not need to carry a parachute and an anti-drop air sac, the characteristics of large fuel capacity, long cruising time, wide application scope and the like are realized, and good popularization and application values are achieved.

A cooling system for a gas turbine engine includes a fuel deoxygenator for increasing the cooling capacity of the fuel. The fuel deoxygenator removes dissolved gases from the fuel to prevent the formation of insoluble deposits. The prevention of insoluble deposits increases the usable cooling capacity of the fuel. The increased cooling capacity of the deoxygenated fuel provides a greater heat sink for cooling air used to protect engine components. The improved cooling capacity of the cooling air provides for increased engine operating temperatures that improves overall engine efficiency.

The invention provides a maneuvering type unmanned aerial vehicle recovery device, and belongs to the technical field of unmanned aerial vehicle recovery. The maneuvering type unmanned aerial vehicle recovery device comprises a blocking assembly, a U-shaped part, a lifting hydraulic cylinder, a support, a rotation base, an upper supporting hydraulic cylinder, a lower supporting hydraulic cylinder and a carrier. After an unmanned aerial vehicle rapidly rushes at the vertically unfolded blocking assembly at a certain recovery speed, the unmanned aerial vehicle pushes a blocking pulley to move forwards together, a pulling rope which is connected to the lower end of the blocking pulley surrounds a pulley block and pulls a damper piston rod in a damper cylinder body, the kinetic energy of the unmanned aerial vehicle and the blocking pulley is quickly absorbed, and therefore the purposes that the unmanned aerial vehicle and the blocking pulley are decelerated and stopped within a quite short period, and finally the unmanned aerial vehicle lands, is buffered by a belly buffering part, and is supported and recovered in a frame of the blocking assembly are achieved. By the adoption of the maneuvering type unmanned aerial vehicle recovery device, an undercarriage or a recovery parachute or a hooking rope device does not need to be additionally installed on the unmanned aerial vehicle, the quantity of loaded oil of the unmanned aerial vehicle can be increased, the flight resistance of the unmanned aerial vehicle can be reduced, and therefore the cruising time of the unmanned aerial vehicle is prolonged, and the flight speed of the unmanned aerial vehicle is increased.

The invention relates to an internal combustion steam boosting take-off unit of an airplane, and belongs to the technical field of boosting take-off technology of airplanes. The internal combustion steam boosting take-off unit of the airplane comprises a combustion chamber, a balancing chamber, an air cylinder, an electromagnetic piston, an electromagnetic lantern ring, a breather pipe, a blow-off pipe and five valves. The outlet of the combustion chamber is connected with the balancing chamber through a pipeline. The electromagnetic piston is arranged inside the air cylinder and can slide and move. The electromagnetic lantern ring is sleeved outside the air cylinder. The electromagnetic lantern ring follows up under the effect of an electromagnetic force of the electromagnetic piston. A valve is arranged at the left end of the balancing chamber. Four of five valves are arranged on the side wall of the air cylinder. The combustion chamber is provided with a catalyst net, an oil spray hole, a gas injection hole and a water injection hole. High-pressure oil and high-pressure oxygen combust in the combustion chamber to generate gas. High-pressure water enters the combustion chamber through the water injection hole and steam turns into vapor. Then the vapor and the gas enter the balancing chamber to push the electromagnetic piston to move and the electromagnetic lantern ring follows up. The internal combustion steam boosting take-off unit of the airplane provided by the invention is small in electromagnetic energy consumption and light and simple in device. The internal combustion steam boosting take-off unit of the airplane provided by the invention is high in energy conversion ratio, energy-saving, economic and environment-friendly.

A fuel filter includes: a filtration chamber consisting of an inner cylinder and an outer cylinder disposed concentrically with a predetermined space, a bottom part that closes an opening end on one end side of the inner cylinder and the outer cylinder, and a lid part disposed with a fuel suction pipe and a fuel sending pipe, that closes an opening end on the other end side of the inner cylinder and the outer cylinder; and a filtering member that is accommodated in a filtration chamber and filtrates fuel that flows into the filtration chamber. In this filter, a centrifugal force applying member for centrifuging the fuel that flows into is disposed at the end of the filtering member on the lid part side. A groove portion extending along an inner wall face of the outer cylinder is formed on the bottom part.

The invention relates to an oil-water composite cabin for a ship, comprising a liquid cabin and perfusion pipelines. A separation unit is arranged in the middle of the liquid cabin, is in watertight match with the cabin wall of the liquid cabin and separates the liquid cabin into two parts; and the perfusion pipelines are respectively arranged in and communicated with the liquid cabins at both sides of the separation unit which moves towards both sides or stretches or withdraws along with the volume variance of liquid at both sides. The oil-water composite cabin for a ship realizes the composite use of any functional liquid cabin on the ship, integrates economic benefits and environment-friendly benefits, has simple structure, compact arrangement and convenient production, processing and daily maintenance and can be widely applied to various ships and ocean structural objects with liquid cabins.

The invention relates to a V-tail unmanned aerial vehicle with an oil tank embedded into a blended wing body. The unmanned aerial vehicle can be used to execute flight missions such as scientific experiments, remote sensing, aerial photographing and the like. The unmanned aerial vehicle is characterized in that: 1) the duration of flight is long and flight missions with high requirements can be conducted conveniently; 2) the use is simple and the operation is convenient; 3) the stability is good and devices such as autopilots, aerial photographing cameras, video cameras and the like can be carried; and 4) the requirement on taking-off and landing conditions is low. According to one aspect of the invention, the small unmanned aerial vehicle comprises a body (1), wings (3), an empennage (7), a left front oil tank (16), a left rear oil tank (15), a right front oil tank (13) and a right rear oil tank (14), wherein the wings (3) are connected on the body (1); and the left front oil tank (16) is arranged at the left front of the internal part of the body (1), the left rear oil tank (15) is arranged at the left rear of the internal part of the body (1), the right front oil tank (13) is arranged at the right front of the internal part of the body (1) and the right rear oil tank (14) is arranged at the right rear of the internal part of the body (1). According to the further aspect of the invention, the left front oil tank, the right front oil tank, the left rear oil tank and the right rear oil tank are respectively provided with shapes adaptive to the wing profile of the body and balanced oil consumption sequences.

A fuel system for a propulsion system includes a fuel deoxygenating device and a catalytic module containing catalytic materials. The fuel deoxygenating device removes dissolved oxygen from the fuel to prevent formation of insoluble materials that can potentially foul the catalyst and block desirable catalytic reactions that increase the usable cooling capacity of an endothermic fuel.

The invention provides a V-shaped tail layout unmanned plane with an oil tank embedded into a blended wing body, which can be used for executing flight missions on scientific research experiment, remote sensing, aerial photography and the like. The unmanned plane has the following characteristics that 1, the flight duration is longer and the implementation of the flight commission with higher requirement on flight time is facilitated; 2, the use is simple and the control is facilitated; 3, the stability is better and the unmanned plane is applicable for carrying equipment such as an autopilot, an aerial camera and a vidicon; and 4, the take-off and landing conditions are lowly required. The small unmanned plane according to one aspect of the invention comprises a plane body (1), wings (3), a tail wing (7), a left front oil tank (16), a left rear oil tank (15), a right front oil tank (13) and a right rear oil tank (14), wherein the wings (3) are connected onto the plane body (1); and the left front oil tank (16), the left rear oil tank (15), the right front oil tank (13) and the right rear oil tank (14) are arranged ahead of the left, behind the left, ahead of the right and behind the right in the plane body (1) respectively. According to a further aspect, the left front oil tank, the right front oil tank, the left rear oil tank and the right rear oil tank are in a shape matched with the wing type of the plane body, and have a balanced oil consumption sequence.

The invention relates to a small multi-purpose unmanned aerial vehicle, which can be used for performing scientific experiments, remote sensing, aerial photography and other flight tasks. The small multi-purpose unmanned aerial vehicle has the following advantages: 1) the cruising duration is long, thereby facilitating the performance of flight tasks with high requirement for the flight duration; 2) the utilization is simple, thereby facilitating the operation; 3) the stability is good and is suitable for carrying autopilots, aerial cameras, video cameras and the like; and 4) the requirements for takeoff and landing conditions are low. According to one aspect of the invention, the small unmanned aerial vehicle comprises a body, wings connected with the body, an empennage, a boom used for realizing connection of the empennage and the body, an engine (10) arranged on the front end of the body (1), and an engine driven propeller (11) used for providing thrust for the aerial vehicle to fly. According to the other aspect of the invention, the unmanned aerial vehicle further comprises a modular loading design with a bottom board supporting plate (32) arranged in the middle of the body (1) used for installation of airborne equipment.

A stove using biomass pellets as fuels is disclosed herein, comprising a stove body that comprises a firebox, at least one hopper, and a feed tube, wherein the at least one hopper is connected to the firebox via the feed tube, and fuels contained inside the at least one hopper can enter the firebox along the feed tube under gravity. The stove has a simple structure and removes any mechanically or electrically controlled feeding system by feeding the firebox using gravity of the fuels, therefore lowers the cost.

The invention relates to a vitamin D powder and a preparation method thereof, wherein the preparation method comprises the step of embedding vitamin E oil into microcapsules by micro-encapsulation technology; and wall materials used for embedding the vitamin E oil are maltodextrin and gelatin. A spray drying method is used in micro-encapsulation. Emulsifier used in spray drying method is compoundof glyceryl monostearate and sucrose ester. The mass ratio of maltodextrin to gelatin is (12 to 20):1. The mass ratio of vitamin E oil and emulsifier is 1:(0.05 to 0.06). The mass ratio of glyceryl monostearate to sucrose ester is 1:(0.4 to 0.5). The Vitamin E powder prepared by the method has high micro-encapsulation efficiency being higher than 96 percent and high oil carrying capacity, and is extremely easy to be dissolved in water.

A motorcycle has a large accommodating space and an enlarged capacity of a fuel filter. The motorcycle includes: a fuel tank disposed on the upper side of the rear wheel and on the rear side of the luggage box; a rear fender provided between the rear frames and, disposed between the luggage box and the rear wheel, and covering the rear wheel on the front and upper sides of the rear wheel; a fuel supply path; and a fuel secondary filter. The rear fender is so disposed that its front portion faces a rear wall of the luggage box, the front portion is inclined rearwardly upward so that the distance thereto from the rear wall increases along an upward direction, and the fuel secondary filter is disposed between the rear wall of the luggage box and the front portion of the rear fender.

The invention discloses a preparation method for a coix seed oil microemulsion. The coix seed oil microemulsion is a coix seed oil microemulsion system which consists of coix seed oil, composite emulsifiers, emulsifier aids, distilled water and the like. Each 100 milliliters of coix seed oil microemulsion contains 5 to 13 grams of coix seed oil, 20 to 30 grams of composite emulsifiers, 1 to 2 grams of emulsifier aids, 0 to 10 grams of dispersants and the balance of water. The microemulsion is prepared by uniform magnetic stirring at 40 DEG C. The preparation method for the coix seed oil microemulsion has the advantages of small addition amount of the emulsifiers, simple process, high oil load, high bioavailability and the like.

A cooling system for a gas turbine engine includes a fuel deoxygenator for increasing the cooling capacity of the fuel. The fuel deoxygenator removes dissolved gases from the fuel to prevent the formation of insoluble deposits. The prevention of insoluble deposits increases the usable cooling capacity of the fuel. The increased cooling capacity of the deoxygenated fuel provides a greater heat sink for cooling air used to protect engine components. The improved cooling capacity of the cooling air provides for increased engine operating temperatures that improves overall engine efficiency.

A small multipurpose unmanned plane can be used to execute flight tasks in scientific experiment, remote sensing and aerial photography and the like. The unmanned plane has the following characteristics that 1) endurance time is long and it is convenient to carry out flight tasks which have a high requirement on endurance time; 2) the unmanned plane is simple to use and convenient to control; 3) the unmanned plane has good stability and is applicable to be used to carry equipment such as an automatic pilot, an aerial photography camera, a camera and the like; and 4) the unmanned plane has low requirements on the rising and landing condition. In dependence on one aspect, the small unmanned plane contains a fuselage, wings connected on the fuselage, empennages, tail booms for connecting the empennages with the fuselage, an engine (10) installed at the front end of the fuselage (1), and propellers (11) which are driven by the engine (10) and used for providing the airplane with pulling force required by flight. In dependence on the other aspect, the unmanned plane further contains a modularization loading design. It contains a baseboard support plate (32) positioned at the central portion of the fuselage (1). The baseboard support plate is used to install airborne equipment.

A miniature multipurpose unmanned plane can be used for flight tasks of scientific research experiment, remote sensing detection and air aerial photography, etc. The unmanned plane ha the following characteristics: 1) long endurance time to facilitate flight task having high requirements on flight time; 2) simple usage to facilitate control; 3) good stability to suit carrying equipment of automatic pilot, aerial photography camera and camera, etc.; and 4) low requirements on rising and landing conditions. One the one side, a miniature multipurpose unmanned plane provided by the invention comprises a fuselage, wings connected to the fuselage, empennages, a tail boom for connecting the empennages and the fuselage, an engine (10) arranged on the front of the fuselage (1), a propeller (11) driven by the engine (10) and for providing pulling force required by flight of an airplane. On the other hand, an unmanned plane of the invention further comprises a modularization loading design, which comprises a base plate support plate (32), arranged on a middle part of the fuselage (1), for arranging airborne equipment.

A control unit included in a first fuel cell unit stores a target range set. The target range set includes an SOC control target range, a control target range of temperature of a secondary battery, a control target range for FC temperature, a control target range for temperature of a BDC, a control target range for temperature of a hydrogen pump, and a control target range for temperature of an air compressor. The control unit controls the respective parameters to fall within these target ranges. A control unit included in a second fuel cell unit also stores the target range set. The control unit included in the second fuel cell unit thus similarly controls the respective parameters to fall within the same target ranges, like the control unit included in the first fuel cell unit.

The invention discloses a zein composite particle, a delivery system, a preparation method and application, which belong to the technical field of functional composite materials. The protein composite particles are formed by zein and a second component in a solution through electrostatic interaction and covalent bond interaction, and the particle size of the protein composite particles is 100-1000 nm. The prepared particles can be used for preparing Pickering emulsion, drug carriers and microcapsules, and have excellent pH stability and emulsion stability. The method can be further applied to the fields of food, cosmetics, pharmacy and the like.