72results about How to "Increase structural weight" patented technology

A front body structure is provided to disperse an impact load to a floor framework member through a rear end of a subframe effectively. The subframe 11 includes a left side frame 12L, a right side frame 12R and a rear frame 13. Each of the side frames 12L, 12R includes a forked part 14 having an inside branch part 14a pointing to a vehicle's inside in a width direction of the vehicle along a first route A and an outside branch part 14b pointing to a vehicle's outside in the width direction along a second route B. In operation, if an impact load F due to an offset front collision is applied on the side frame 12 in concentration, then the load F is divided into a load component Fa to be transmitted to the other side frame 12L through the inside branch part 14a and the rear frame 13 along the first route A and another load component Fb to be transmitted to the floor framework member 8 through the outside branch part 14b along the second route B.

A composite rigid foam structure that has a skin or coating on at least one of its surfaces. The skin is formed in situ by thermal spray techniques. The skin is bonded substantially throughout the surface of the porous substrate to the peripheries of the pores. The skin on the average does not penetrate the surface of the substrate by more than the depth of about 2 to 5 pores. Thus, thermal spraying the skin onto the rigid foam produces a composite that is tightly and uniformly bonded together without unduly increasing the weight of the composite structure. Both thermal conductivity and bonding are excellent.

The invention relates to a method for determining temperature field distribution of a cabin of a carrier rocket in a flight phase in an atmospheric layer. The method comprises a first step of determining an aerodynamic heating thermal flow qh changing along with the flight height and acting on the outer wall of the cabin; a second step of determining an average natural convection heat transfer coefficient alpha n of the shell surface of an instrument in a closed cavity of the cabin changing along with the flight height; a third step of determining a forced convection heat transfer coefficient alpha f of interior of the cabin caused by flight accelerated speed and constant leakage of gas in the cabin; and a fourth step of building a cabin node thermal network model, finishing thermal coupling analysis, and obtaining the cabin temperature field distribution. The method comprehensively considers the impact of aerodynamic heating outside the cabin, air natural convection in the cabin and forced convection on the cabin thermal environment, thereby effectively solving the problem of determination of temperature field distribution of the cabin of the carrier rocket in the flight phase in the atmospheric layer.

Provided herein methods and structures for construction of light weight sandwich panels or load-bearing panels having improved ballistic protection. The methods disclosed can facilitate construction of a hybrid core comprising ballistic fabrics and deformable pins that exhibit superior resistance to ballistic penetration. The methods and structures of the present disclosures can be advantageously used in many applications, such as armored vehicles.

A submersible raft device that is primarily used for aquaculture farming. The raft device has a raft surface, a buoyance support structure, and a submersion control system. The buoyance support structure and the submersion control system allow the raft to be submerged to a desired depth beneath the ocean surface. When used for certain kinds of aquaculture farming, such as mussel farming, submerging the raft below the surface protects the raft, as well as the mussels growing on ropes suspended from the raft, from damage in times of hazardous sea conditions.

The invention provides a space external heat flux calculation method for a carrier rocket. The method comprises the following steps that: (1) initial moment coordinate system conversion is carried out to obtain an initial conversion matrix; (2) instantaneous coordinate system conversion is carried out to obtain an instantaneous conversion matrix; (3) the included angle cosine of a sunlight vector, an earth infrared radiation vector, an earth light sun radiation vector and an instantaneous rocket body coordinate system is determined; and (4) an environment virtual mapping surface is built, and the rocket body surface space external heat flux is determined. The method has the advantages that the orbital dynamics and the thermodynamics are combined; the Monte Carlo method radiation heat flux calculation is used as the basis; the space external heat flux on the complicated surface of a rocket body can be finely determined; the problems of shielding and multiple times of reflection among the surfaces are effectively solved; and the coordinate conversion and mathematical calculation flow processes are simplified.

The invention relates to a memory-alloy driving front ducted ejector of a variable-cycle engine adjustable mechanism. The memory-alloy driving front ducted ejector comprises a core driving fan case, memory alloy wire bases, pulleys, memory alloy wires, wire locking devices, gaskets, crankshafts, spherical hinge covers, spherical hinge balls, connecting rods, studs, stud supports, a valve body anda bias spring. The memory alloy wires are used as mechanism driving pieces, when the temperature is raised by external electric heating, the length is reduced due to the shape memory effect, displacement generated by the memory alloy wires is amplified by the lever effect of the crankshafts and then is transmitted to the valve body through the connecting rods to enable the valve body to be turneddown, and thus the temperature is adjusted and the flow from a core driving fan to an outer duct is controlled; when electric heating is stopped, the memory alloy is at a low-temperature phase, the bias spring pulls open the valve body, and simultaneously, the memory alloy wires are stretched to be in a loading state. The memory-alloy driving front ducted ejector can be matched with other adjustable mechanisms to convert the working state of a variable-cycle engine, and has the advantages of being small in structure weight, reliable in movement, small in influence on flow channels and the like.

The invention discloses a high-rigidity light launching box and relates to a launching box used for supporting, fixing, transporting and storing missiles. The high-rigidity light launching box is high in both circumferential rigidity and longitudinal rigidity and light and can provide large storage space for the missiles, and the stress on the corners of the launching box can be effectively diffused. The high-rigidity light launching box comprises an outer skin, an inner skin, longitudinal ribs and ring ribs evenly distributed between the outer skin and the inner skin. The ring ribs are connected with the outer skin and the inner skin through glue respectively, the ring ribs are installed on the inner skin in a sleeved mode, small rounded corners are adopted for the corners of the inner skin, the outer skin and the ring ribs, the space between the inner skin and the ring ribs is filled with a heat preserving layer, reinforcing blocks are arranged on the corners of the heat preserving layer, filling interfaces are arranged on the longitudinal ribs, a 35-degree laying layer is adopted for the inner skin, the longitudinal rib laying layers and the ring rib laying layers respectively comprise 0-degree laying layers and 90-degree laying layers, the proportion of the laying layers of the longitudinal ribs is as follows: n 0 degree: n 90 degrees= 2:1- 3:1, and the proportion of the laying layers of the ring ribs is as follows: n 90 degrees: n 0 degree= 2:1- 3:1.

A device for wrapping a substantially flat piece of sheet material with a plurality of creases that define fold lines that when folded, forms an elongate structure that includes a hollow outer portion and a hollow inner portion disposed within the hollow outer portion. The device includes a mandrel, a gripper blade that releasably secures the sheet material to the mandrel, a motor that rotates the mandrel when the sheet material is secured to the mandrel, and a compressive member that releasably presses the first outer side surface of the hollow outer portion of the elongate structure against the inner portion of the elongate structure after the sheet material has been wrapped about the mandrel. The device can also include a controller that is operably associated with the motor and the compressive member.

The invention belongs to the technical field of tunnel construction, and discloses a novel tunnel engineering air-land amphibious climbing detection robot which comprises a rack body, aircraft wheels and rotor wing assemblies, and the aircraft wheels and the rotor wing assemblies are arranged on the rack body. The rack body comprises an upper rack plate, a lower rack plate and a plurality of connecting plates used for connecting the upper rack plate and the lower rack plate. The aircraft wheels are arranged at four corners of the rack body and are connected with the rack body through driving connecting pieces, four rotor wing cavities used for arranging the rotor wing assemblies are uniformly arranged in the rack body, the rotor wing cavities and the aircraft wheels are arranged on the rack body in a staggered manner, a control box is arranged in the center of the rack body, and a detection radar is arranged at the bottom of the control box; and the detection radar comprises a sequential control module and a wireless data transmission module, the sequential control module is used for controlling a transmitting antenna, a receiving antenna and a signal acquisition module, and the wireless data transmission module is used for wirelessly transmitting signals acquired by the signal acquisition module to a ground computer. The structure weight is low, the operation energy consumption of the detection robot can be reduced, and the detection quality and efficiency are improved.

An operation efficiency increasing method based on a position change of an aileron connector is provided. In the method, a connector of an aileron is adopted to fix an aileron surface rotated by a servo, and the hinge position of another connector is adjusted according to the speed of incoming flow or an angle of attack, thus increasing connection rigidity of an aileron surface to allow loads on the aileron surface to be redistributed, and reducing elastic deformation of the aileron surface so as to increase the operation efficiency of the aileron. Abovementioned situations can be avoided under the premise of not increasing an operating mechanism, and the cost is reduced. The two connectors are adopted in a wing-aileron connection, the position of one of the connectors changes, and contactof the connectors is controlled by a relay. According to different flight conditions, the position of the wing-aileron connector changes to change wing-aileron connection (support) rigidity so as toredistribute (optimize) loads on the aileron surface, and aileron deformation is reduced to increase the aileron operation efficiency.

A method is presented for making a composite material from strips comprising longitudinal fibres and a binder or resin, which material comprises a number of layer assemblies one on top of the other. Each layer assembly comprises m sets (with m at least 2) of parallel strips each extending in a different direction, Each layer assembly is manufactured by successive steps of depositing groups of parallel strips according to a well defined pattern (without longitudinally interweaving strips with previously deposited strips). Before completing a layer assembly, with the exception of the last layer assembly, by depositing its last group of parallel strips, the first group of parallel strips of the following layer assembly is already deposited. A composite material manufactured with such a method is presented too.

The invention discloses an arresting hook for an unmanned aerial vehicle in gliding landing. The arresting hook comprises a connecting seat, a V-shaped hook body and a tail hook, the V-shaped hook body is divided into two parts with left and right symmetry, the front end of the V-shaped hook body is provided with the connecting seat, the rear end sides of the left and right parts of the V-shaped hook body are fitted together, the rear end of the V-shaped hook body is connected with the tail hook, and a mounting hole for mounting and fixing the unmanned aerial vehicle is arranged in the connecting seat. By using the V-shaped arresting hook with an angle of 20 degrees, the force transmission path of the arresting hook is changed after a rope is hooked, under the condition of increasing the weight of the arresting hook structure as little as possible, the internal stress distribution and the maximum level under the same external force are greatly reduced, and the safety of landing is ensured.

A mount structure for mounting an ancillary engine unit to a gas turbine engine is provided. The mount structure has plural elongate struts which each extend from a connector portion at one end of the strut to a fastening portion at the other end of the strut. The housing of the ancillary engine unit is formed of a first material having a first coefficient of thermal expansion, and the elongate struts are formed of a second material having a second coefficient of thermal expansion. Each elongate strut extends away from its connector portion in a direction which is crosswise to the direction of the hypothetical differential thermal strain at that connector portion. The mount structure further has a containment bracket which is configured to contain each connector portion.

The invention discloses a third-generation heavy fighter novel gas inlet channel lip. The novel gas inlet channel lip comprises a gas inlet channel lip and a boundary layer separation plate, the fixed gas inlet channel lip of a present heavy fighter is changed to a retractable movable lip, the retractable movable lip is arranged on two sides of the front portion of the boundary layer separation plate through a hinge shaft, a movable lip folding and unfolding hydraulic actuation cylinder on a mounting joint on the inside wall of the air inlet channel is connected with a folding and unfolding pull rod on the rear portion of the inner end of the movable lip through a connection bolt to realize the folding and the unfolding of the movable lip, a fixed lip having a radius larger than the radius of the movable lip is arranged on the rear portion of the movable lip, and a rectification box having a leading edge radius same with the radius of the movable lip is arranged outside the hinge shaft, and enables the third-generation heavy fighter to have relatively large engine push force on a relatively short running track such as when the third-generation heavy fighter launches on an aircraft carrier or flights in a low-altitude and low-speed manner, and to correspondingly increase the launching weight, the fighting capability and the use flexibility of the fighter.

The invention discloses a low noise rudder blade surface structure for a warship. The low noise rudder blade surface structure for the warship comprises common elastic wing panels, an elastic bow wing panel and an elastic stern wing panel, wherein the common elastic wing panels are fixedly connected with a rudder blade shell plate by virtue of mounting screws, the elastic bow wing panel is fixedly connected with the rudder blade shell plate by virtue of mounting screws, and the elastic stern wing panel is fixedly connected with the rudder blade shell plate by virtue of mounting screws; and the common elastic wing panels are connected with the elastic stern wing panel in an overlapping and leaning manner, the common elastic wing panels are mutually connected in an overlapping and leaning manner, and the elastic bow wing panel and the common elastic wing panels are connected in an overlapping and leaning manner. The low noise rudder blade surface structure for the warship has the advantages that one group of detachable elastic wing panels which are mutually matched are mounted on a rudder blade, so that the rudder blade surface structure has certain elasticity, the drastic change of water pressure, caused by turbulent flow or eddy, of a rudder blade surface is relieved, and the water flow field of the rudder blade surface is improved by virtue of surface grooves of the elastic wing panels, so that anti-cavitation and eddy reducing properties of the whole rudder blade are improved, and the fluid noise of the rudder blade is reduced.

Aiming at some practical defects of overlong tail, long power transmission distance, slower speed, poorer maneuverability and the like of a traditional helicopter which balances the rotating torque ofthe helicopter body by utilizing reverse torque tail paddles and mutual reverse rotation of double coaxial rotors, the invention provides a power system of a single-rotor helicopter without the reactive torque tail rotor and a power system of a helicopter with a thrust propeller or a tilting thrust propeller, the reactive torque tail rotor of the traditional helicopter is replaced, one rotor in the double coaxial rotors is used for balancing the rotating torque of the helicopter body, and the flying speed and maneuverability of the helicopter are improved.