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161results about How to "Reliable arrangement" patented technology

Independent suspension system for super-heavy chassis

ActiveCN105856996AGood driving maneuverabilityMeet high mobility needsInterconnection systemsResilient suspensionsVehicle frameEngineering
The invention discloses an independent suspension system for a super-heavy chassis. The independent suspension system for the super-heavy chassis comprises upper cross arm assemblies, lower cross arm assemblies and hydro-pneumatic springs, wherein the upper cross arm assemblies, the lower cross arm assemblies and the hydro-pneumatic springs are symmetrically arranged at the two ends of an axle. One end of each upper cross arm assembly is connected with a swing arm support of a vehicle frame through a first bearing structure. One end of each lower cross arm assembly is connected with the swing arm support of the vehicle frame through a second bearing structure. The other end of each upper cross arm assembly is connected with the upper end of a steering knuckle through a first spherical hinge device. The other end of each lower cross arm assembly is connected with the lower end of the steering knuckle through a second spherical hinge device. A supporting lug at the upper end of each hydro-pneumatic spring is connected with a hydro-pneumatic spring support on the vehicle frame through a first knuckle bearing structure. A supporting lug at the lower end of each hydro-pneumatic spring is connected with the corresponding lower cross arm assembly through a second knuckle bearing structure. The independent suspension system for the super-heavy chassis has the characteristics of being compact in structure, reasonable in arrangement, high in reliability and easy to maintain; and a super-heavy vehicle adopting the independent suspension system has good motor driving performance and rapid passing capacity.
Owner:BEIJING INST OF SPACE LAUNCH TECH +1

Preparation device of aircraft composite material fuselage wall panels and preparation method thereof

ActiveCN104029397AFacilitates lay-up operationsReliable arrangementAirplaneEngineering
The invention belongs to the aerospace manufacturing technology, and relates to a preparation device of an aircraft composite material fuselage wall panels and a preparation method thereof. Cap-shaped stringers are formed through solid male molds; large opening frame type female molds are adopted to lay skins to form the wall panels; and cap-shaped stringer positioning tools are adopted to control gaps of the stringers so as to realize precise positioning of the cap-shaped stringers and to finish the production of the fuselage wall panels. In the preparation method of the aircraft composite material fuselage wall panels, the phenomenon of internal corner ester enrichment and external corner attenuation of the cap-shaped stringers can be effectively reduced by adopting an atmosphere feeding manner and a rubber soft mold process, so that the part thickness uniformity is improved; and one-way prepreg is required to be filled in cementing R areas in cementing assembly, and +- 45-degree laying layers are added, so that the stress concentration caused by the R areas, formed between the cap-shaped stringers and the skins, structurally bearing external loads can be relieved. Air bags in the cementing formation process are used as pressure transfer mediums in the cap-shaped stringers and cavities of the skins, and are capable of effectively guaranteeing the formation quality of the skins and cementing surfaces of the R areas.
Owner:AVIC COMPOSITES
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