30 results about "Aerospace vehicle" patented technology

The application provides a kind of aerospace vehicle assembly workshop intelligent dynamic scheduling method and system, method includes steps S1: by real-time connection assembly workshop central control system to obtain real-time multi-source data;Step S2: training multi-evaluation network coordination safety near end strategy optimization model, optimal control sequence in limited time domain is solved at each sampling time, only the first control action is adopted, the next sampling time is optimized based on last control action and state, after completing all control action optimization, reward model is based on neural network back update;Repeat the above process until convergence;Step S3: the multi-evaluation network coordination safety near end strategy optimization model trained is deployed to carry out workshop state update and rescheduling decision, generate and issue new scheduling plan.The application realizes the real-time response to the abnormal disturbance such as response emergency order, equipment failure, realizes the safe, efficient, flexible dynamic self-adapting scheduling of aerospace vehicle assembly workshop.

The present application relates to a kind of weld reinforcement structure for stainless steel tank, belong to aerospace vehicle propellant tank structure technical field;First tank bottom, first short shell, barrel section, second short shell and second tank bottom;Wherein, first tank bottom and second tank bottom are hemispherical shell structure;First short shell, second short shell, barrel section are barrel section structure;First short shell, barrel section and second short shell are in turn horizontal coaxial butt joint;First tank bottom is coaxially installed at the axial outer end of first short shell;Second tank bottom is coaxially installed at the axial outer end of second short shell;The open end of first tank bottom is inserted into first short shell, and the outer wall of first tank bottom is butt joint with the inner wall of first short shell;The open end of second tank bottom is inserted into second short shell, and the outer wall of second tank bottom is butt joint with the inner wall of second short shell;The present application solves the problem that the welding performance of reinforcing material cannot be reinforced by partition thickness design, realizes the purposes such as high performance, low cost manufacturing of stainless steel tank.

This invention provides a vertical tail control surface motion mechanism with guide rail limiting and guidance, and an unmanned aerial vehicle (UAV), relating to the field of aerospace vehicle control system technology. The mechanism uses the metal part of the vertical tail connector as the installation reference. A linear servo is hinged and fixed via a servo base. The linear servo push rod is connected to a guide pin. The lower part of the guide pin is embedded in the arc-shaped guide groove of a copper guide rail, and the upper part is hinged to the control surface linkage rocker arm. The control surface linkage rocker arm is rigidly connected to the control surface hinge shaft. This invention uses a copper guide rail to provide full-stroke directional constraint and limiting for the guide pin, significantly compressing the mechanism's motion envelope, adapting to the compact installation space of a thin vertical tail, eliminating transmission backlash, and improving control surface deflection accuracy and motion smoothness. It has the advantages of compact structure, precise operation, resistance to jamming, long service life, and convenient maintenance, and is particularly suitable for the vertical tail rudder control system of small fixed-wing UAVs and light aircraft.

The present invention relates to a nanocellulose-based high-strength carbon fiber-reinforced polymer composite and a method for manufacturing same and, specifically, to a nanocellulose-based high-strength carbon fiber-reinforced polymer composite, infused with a thermosetting resin containing dispersed nanocellulose to simultaneously enhance strength and lightweight characteristics, and to a method for manufacturing same. The present invention provides the effects of significantly improving tensile strength and impact resistance of a composite by effectively inhibiting crack formation and uniformly distributing stress within the composite. Furthermore, by achieving a weight reduction compared to conventional metallic materials, the present invention can improve the fuel economy and energy efficiency of transportation means, such as automobiles and aerospace vehicles.

The application discloses a design method of a reusability aerospace vehicle compression heart rear movement, and a pair of pitching stabilizing plates are symmetrically arranged at both sides of a tail section of a fuselage of the aerospace vehicle; the pitching stabilizing plates are connected with the fuselage through rudder shafts; the pitching stabilizing plates can rotate around the rudder shafts to realize the conversion between an opening mode and a folding mode of the pitching stabilizing plates. The design method of the reusability aerospace vehicle compression heart rear movement can move the compression heart of the aerospace vehicle rearward and realize the adjustment of the pitching stability of the aerospace vehicle under different flight conditions.

The application discloses a kind of processing technology of power two guide inner machine cabinet front section welding assembly, belong to aerospace parts processing technical field.Aiming at the problem that assembly rigidity is poor, processing is easy to deform, and it is difficult to guarantee precision size, the process realizes precision control by optimizing route, improving clamping, configuring special tooling and relaxing unnecessary tolerance.Process route is: 0 is matched→10 vacuum brazing→15 bench grinder→20 numerical control machine processing→30 bench work→40 numerical control machine processing→42 numerical control machine finishing→50 numerical control milling processing→60 bench work→70 electric spark grinding→80 ultrasonic cleaning→85 numerical control machine processing→90 bench work→100 inspection→110 electric arc ion plating→120 inspection→130 cleaning→140 packaging.15, 42, 85 new process, optimize the clamping mode of each core process, configure fixed cover plate and special gauge, reasonably adjust tolerance range, and the qualified rate of part processing can be effectively improved.

This invention discloses a perovskite-type high-entropy ceramic material, its preparation method, and its application. The preparation method of the perovskite-type high-entropy ceramic material of this invention includes the following steps: 1) mixing A-site oxide powder and B-site oxide powder and wet ball milling, followed by drying and grinding to obtain a mixed powder; 2) adding the mixed powder into a graphite crucible and compacting it, then subjecting it to laser radiation heating to obtain the perovskite-type high-entropy ceramic material. The perovskite-type high-entropy ceramic material of this invention exhibits multi-band absorption characteristics, high service temperature, and stable performance at high temperatures, making it suitable for use in stealth coatings for aerospace vehicles. Furthermore, its preparation method is simple, with a short reaction time and low production cost, making it suitable for large-scale industrial production and application.

This invention discloses a knitting machine for a thermal insulation and sealing elastic inner support structure for aerospace vehicles, comprising: a frame, a knitting cylinder, a knitting toothed plate, a needle feed cam, multiple needles, a gantry, an elastic structure support, and a drafting mechanism. The drafting mechanism is disposed on the frame and is used to clamp and pull the knitted elastic structure and the mesh sleeve wrapped around the elastic structure. This invention relates to the field of knitting machine technology. By installing the gantry on the knitting toothed plate and rotating it synchronously, the special metal wire is fed in a follow-up manner, enabling the special metal wire to enter the knitting area evenly and stably, effectively solving the problem of uneven knitting of special metal wire. Through the cooperation of the knitting toothed plate, the needle feed cam, and the needles, the regular up-and-down reciprocating motion of the needles on the fixed needle cylinder is achieved. At the same time, the knitting toothed plate drives the gantry to rotate around the elastic structure support to feed the wire, ensuring that the metal wire is always evenly wrapped around the elastic structure support during the knitting process.

This application discloses an online trajectory planning method, system, and storage medium for the ascent phase of a combined-propulsion aerospace vehicle, belonging to the field of aircraft guidance and control technology. The method includes: offline generation of a large number of trajectory samples under parameter deviation conditions within the framework of the direct method, forming a dataset for network training; dividing the ascent phase of the combined-propulsion aerospace vehicle into a turbine-based combined cycle propulsion (TBCC) phase and a liquid rocket propulsion (RKT) phase based on the differences in the dynamic characteristics of the engine modes, and designing corresponding state-control networks for each, followed by training to obtain a segmented network; using the segmented network, outputting the control variables required at the current moment, providing the corresponding flight strategy, and realizing online trajectory planning. Numerical simulation results of this application verify that the method can maintain high terminal accuracy and strong robustness under different thrust deviation scenarios while ensuring the accuracy and real-time performance of online applications.

A polishing device for aerospace components includes a main support base, a rotary drive motor, a polishing roller, aerospace components, a displacement drive ring, and a first locking block. The main support base has a first support platform on one side and a second support platform on the other side. The first support platform has a first support block in the middle, and a driven block connecting platform on the side of the first support block. Three sets of driven block connecting platforms are evenly arranged around the first support block. The driven block connecting platform has a driven block connecting groove inside, which is adapted to a driven slider. The driven slider is connected to the driven block connecting groove and slides inside the driven block connecting groove. The first support block has a first locking block connecting groove inside, and a first locking block is provided on the side of the first support block facing the middle of the main support base. The side of the first locking block facing the first support block has a first locking block connecting post.

A method for obtaining micro-vibration test conditions for aerospace vehicles involves: searching for micro-vibration disturbance sources during the vehicle's on-orbit operation; classifying the micro-vibration disturbance sources and identifying those that cannot be avoided; conducting micro-vibration environment measurement tests on the unavoidable disturbance sources to obtain the time-domain curve of the maximum vibration environment of the disturbance sources; establishing a finite element model for micro-vibration response analysis; conducting transient response analysis to determine the micro-vibration response of precision instruments; converting the time-domain curve of the micro-vibration response of the precision instruments into a frequency-domain curve and performing envelope design to obtain the micro-vibration test conditions of the precision instruments for subsequent experimental verification.

An aerospace wiring harness inspection system comprises a computer system communicatively coupled to a camera system connected to a robot, a machine learning model running in the computer system, and a controller. The machine learning model is trained to detect anomalies in a set of images of a wiring harness in an aerospace vehicle. The controller is configured to control the camera system to generate a set of images of the wiring harness; send the set of images of the wiring harness to the machine learning model; and receive a result from the machine learning model indicating whether an anomaly is present in the wiring harness.

The application provides a liquid crystal oligomer, a liquid crystal phthalonitrile resin with intrinsic high thermal conductivity and a preparation method and application thereof. The liquid crystal oligomer is obtained by condensation polymerization of the following raw materials: diphenyl ether compounds, biphenyl compounds and nitro phthalonitrile; the raw material of the liquid crystal phthalonitrile resin of the application comprises the liquid crystal oligomer. The liquid crystal phthalonitrile of the application can be used in the fields of aerospace, military and national defense, rail transit, electronic appliances and the like, and is expected to make high-temperature-resistant and high-thermal-conductivity structural parts (such as aerospace vehicles) more lightweight, and can improve the heat dissipation capacity of equipment (such as radars, vehicle-mounted thermal control systems and integrated chips) and maintain the insulation properties, thereby prolonging the service life of the equipment.

This invention relates to the field of aerospace manufacturing technology, specifically to a processing equipment for integrated molding of aerospace shells. The equipment includes a base and a mounting base, with the mounting base fixedly mounted on the base. Multiple piston holes are formed on the upper surface of the mounting base, and a punch is coaxially mounted in each piston hole. The upper end of the punch extends beyond the piston hole. A flexible pad is provided on the upper side of the mounting base, with its lower end face fitting against the upper end face of the punch. The flexible pad has through holes matching the number of punches. A spherical groove is coaxially formed on the upper surface of the punch, and a ball bearing is rolled within the spherical groove. This invention, by using a flexible pad, avoids direct contact between the punch's sharp corner and the sheet metal, preventing localized plastic deformation of the sheet metal. Simultaneously, the flexible pad provides elastic support to the sheet metal, preventing gaps between adjacent punches from easily forming micro-wrinkles in the sheet metal, thus improving the molding quality of the aerospace shell.

An aerospace wiring harness inspection system comprises a mobile personal computing device; a camera system connected to the mobile personal computing device; a machine learning model running in the mobile personal computing device; and a controller. The machine learning model is trained to detect anomalies in a set of images of a wiring harness in an aerospace vehicle and to identify a respective remedial action associated with the detected anomalies, wherein the respective remedial action comprises at least one of replace, repair, use as-is, or defer review. The controller configured to control the camera system to generate a set of images of the wiring harness; send the set of images of the wiring harness to the machine learning model; and receive a result from the machine learning model indicating whether an anomaly is present in the wiring harness and an associated remedial action for the anomaly.

The application relates to the technical field of alloy materials, in particular to a high-strength alloy material and a preparation process thereof. The application overcomes the problem that the mechanical properties and high-temperature resistance of alloy materials in the prior art cannot be considered simultaneously. The alloy component obtained by the application comprises Al-Li-Cu-Zr-Sc-Yb-In-Ag, and a hot-pressed alloy is obtained through high-temperature zirconium melting-low-temperature lithium pressing smelting, hierarchical homogenization, deformation heat processing, deep cooling and pre-strain dislocation network induction technology; then a bimodal structure coexisting with equiaxed fine crystals and elongated fiber crystals is constructed through gradient instantaneous annealing, and a dense carbon atom layer is deposited on the surface by combining chemical vapor deposition technology. The alloy material obtained by the application has good fatigue resistance and corrosion resistance, and is suitable for large thin-walled stressed components of aerospace vehicles and high-temperature protection fields.

The application provides a gas bag type spacecraft storage and transportation container, which comprises a top cover, an upper flange of a box cover, a flexible container cover, a guide assembly, a lower flange of the box cover, a container bottom and a flexible film. The application has the beneficial effects that: the lifting operation of the flexible container cover is completed by using the power of air pressure and the self weight of the flexible cover, the lifting height limit of the factory building crane is avoided; the opening and closing operations of the container cover can be realized only by inflation and deflation, the hoisting and sleeving operation is cancelled, the operation process is simplified, and the operation risk is reduced; the regular and orderly folding storage of the container cover is realized, and the folding and unfolding are easy; the folding and unfolding ratio is greater than 10:1, the storage volume is greatly reduced; the hard metal is changed into the flexible film material, and the self weight of the container is greatly reduced.

This invention discloses a phenolic / zirconium aluminum phosphate-based dual-network high-temperature resistant foam and its preparation method. The foam comprises a zirconium aluminum phosphate matrix, a water-soluble phenolic prepolymer, a high-temperature resistant filler, a foaming agent, a curing agent, and a foam stabilizer. This invention constructs an organic-inorganic dual-network structure through the co-construction of an organic-inorganic network by the water-soluble phenolic prepolymer and zirconium aluminum phosphate resin. The water-soluble phenolic prepolymer acts as the organic network, significantly improving the material's bonding strength, toughness, and compressive strength. The zirconium aluminum phosphate resin forms a rigid inorganic network, endowing the material with excellent ultra-high temperature resistance. By controlling the foaming rate through the synergistic reaction of foaming and curing, a porous foam structure with uniform pore size and stable structure is prepared. This material combines lightweight, ultra-high temperature resistance, and excellent thermal insulation properties, enabling adaptive filling of complex-sized gaps and rapid on-site foaming molding. It is suitable for applications such as thermal protection for aerospace vehicles, thermal insulation layers for rocket engines, and high-temperature sealing.

A molding process for atomic oxygen-resistant composite materials. This invention belongs to the field of aerospace materials technology. This invention solves the problems of composite materials being susceptible to atomic oxygen in aerospace environments, and the tendency for debonding and air bubbles to form during bonding processes. This invention involves first coating an alloy material and a resin-based carbon fiber composite material separately with adhesive, and then bonding the alloy material and the resin-based carbon fiber composite material together to obtain an atomic oxygen-resistant composite material. The use of pressure rollers in this invention effectively ensures uniform adhesive layer thickness. A uniform adhesive layer allows for better adhesion of the metal protective layer to the surface of the resin-based carbon fiber composite material. The molding process of this invention ensures that the atomic oxygen-resistant composite material does not debond in aerospace environments, effectively extending the service life of aerospace equipment.

The present invention relates to the technical field of aerospace vehicles, and specifically discloses a modular multi-purpose aerial delivery and air transportation unmanned aerial vehicle and a usage method thereof. The unmanned aerial vehicle adopts a canard layout with a "gong"-shaped double fuselage, double wings and double vertical tails. The core of it is that the front wing adopts a modular design, and the total wing area and aerodynamic center of the whole aircraft can be flexibly adjusted by replacing different components to adapt to different loads; a hanging area is provided under the front and rear central wings between the double fuselages, and a hoisting point with a winch is configured, so that a variety of loads can be quickly hoisted from the ground and released in the air. Through the modular design and innovative hanging and loading method, the single platform of the present invention can flexibly perform various functions such as cargo transportation, equipment aerial delivery (such as prototypes, rockets), mission payload carrying (such as communication base stations), etc., significantly improving the multi-functional adaptability and mission cost-effectiveness of the platform, and at the same time having the advantages of simple loading process and low deployment requirements.

An aerospace physical component inspection system comprises a mobile personal computing device; a camera system connected to the mobile personal computing device, a machine learning model running in the mobile personal computing device; and a controller. The machine learning model is trained to detect anomalies in a set of images of a physical component in an aerospace vehicle. The controller configured to control the camera system to generate a set of images of the physical component; send the set of images of the physical component to the machine learning model; and receive a result from the machine learning model indicating whether an anomaly is present in the physical component.

The utility model relates to an unmanned aerial vehicle upper energy storage battery pack heat radiation structure belongs to aerospace vehicle thermal management system field. Including energy storage battery pack air duct, airflow import, airflow export, the multiple holes are opened on every baffle in energy storage battery pack inside, form energy storage battery pack air duct, the hole is opened on the nose fairing, serves as airflow import, the hole is opened on the fuselage cabin section, serves as airflow export, the airflow enters the body inside from the nose fairing hole, flows through energy storage battery pack air duct, then flows out from the fuselage cabin section hole, forms complete air flow channel. The utility model can effectively radiate to high heat flux density energy storage battery pack, is applicable to the aerial vehicle under different flight height. Especially suitable for the flight environment of low air pressure high flight speed under near space height.

The application discloses high-entropy dodecaboron ceramic powder and a preparation method and application thereof. The preparation method of the high-entropy dodecaboron ceramic powder comprises the following steps: 1) mixing metal oxide powder and boron powder to carry out wet ball milling, and then carrying out drying and grinding to obtain a mixed powder; and 2) adding the mixed powder into a graphite crucible and compacting, and then placing the mixed powder into a protective atmosphere to carry out laser radiation heating to obtain the high-entropy dodecaboron ceramic powder. The high-entropy dodecaboron ceramic powder has excellent wave absorption performance, has wide-band absorption and strong reflection loss, is suitable for being used on an aerospace vehicle stealth coating, and has the advantages of simple preparation method, short reaction time, low production cost, and suitability for large-scale industrial production and application.

A representative hatch system can include a base portion surrounding an opening, a hatch portion movable relative to the base portion between a closed configuration and an open configuration, and a movement mechanism positioned to move the hatch portion relative to the base portion between the closed and open configurations. The movement mechanism can include four arms pivotably attached to the hatch portion and the base portion via four pivot axes. When the hatch portion is in the closed configuration, the axes can be coplanar. The axes can be spaced apart from a sealing plane between the hatch portion and the base portion. The arms can traverse a periphery of the hatch portion. A representative aerospace system can include a hatch system supported in a wall portion of an aerospace vehicle. The movement mechanism can keep the sealing surface of the hatch facing away from an interior of the vehicle.

The invention belongs to the field of aerospace aircrafts, and particularly relates to a force fighting test stand and application thereof. The invention provides a force fighting test bench, which comprises a test bench panel, more than two actuators, a simulation control surface, a torque sensor and a load simulator, and is characterized in that the actuators, the simulation control surface, the torque sensor and the load simulator are mounted on the surface of the test bench panel; the actuator drives the shaft of the load simulator to rotate through the simulation control surfaces, and the two adjacent simulation control surfaces are connected through the shaft of the load simulator; the torque sensor is provided on a shaft of the load simulator. The invention also provides an application of the force fighting test bench in an aircraft actuation system. According to the invention, the torque sensor is installed on the shaft, and the torque of different actuators on the shaft is measured, so that the measurement of the force fighting during the parallel driving of different actuators is realized, and the technical defect that the force fighting of the parallel driving actuation system cannot be measured in the prior art is solved.

This invention discloses an attitude control method for aerospace vehicles based on fractional-order sliding mode considering actuators, belonging to the field of aircraft control technology. Addressing the performance degradation problem caused by traditional sliding mode attitude controllers neglecting actuator dynamics, this invention first integrates attitude dynamics, aerodynamic torque, and actuator models to construct a second-order linearized attitude control model. Subsequently, an extended state observer is designed to estimate and compensate for convergent disturbances in the system in real time. Furthermore, a fractional-order non-singular terminal sliding surface is designed, and combined with a reaching law using saturation functions, the desired intermediate control quantity is derived, ultimately calculating the rudder deflection command. Through the coordinated design of model construction, disturbance observation, and advanced control laws, this invention achieves rapid finite-time convergence of attitude angle tracking errors while fully considering the dynamic characteristics of the actuators, effectively suppressing control chattering and significantly improving the control accuracy and robustness of the system under parameter uncertainty and external disturbances.

The present application relates to the technical field of thermal management of aerospace vehicles, and particularly relates to a composite thermal control structure and an aerospace vehicle. The composite thermal control structure comprises, from bottom to top, a temperature equalization layer, a transition layer and a cooling layer; wherein the temperature equalization layer is used for absorbing and diffusing heat and equalizing temperature, and dot matrix units for filling phase change medium are arranged in the temperature equalization layer; the transition layer is used for transferring heat of the temperature equalization layer to the cooling layer; and the cooling layer is used for rapid heat dissipation, and has a conformal flow channel with a special cross section, and an inner surface of the conformal flow channel is plated with a high-thermal-conductivity layer. The present application relieves thermal mismatch of aerospace vehicles through micro-nano scale effect, and has the advantages of improving heat dissipation efficiency, adapting to complex geometric shapes and being lightweight and low-cost.

This invention provides a strengthened aerospace aluminum alloy component, obtained through surface nano-sizing treatment; the surface nanocrystals of the aerospace aluminum alloy component contain precipitated phases. This invention also provides a surface nano-sizing strengthening process for aerospace aluminum alloy components, preventing premature precipitate formation due to temperature rise during the surface nano-sizing process, while protecting the precipitates in the substrate from being affected. After aging heat treatment, the nanocrystals promote the precipitation of a nanoscale second phase on the material surface. This invention effectively avoids the breakage problem caused by dislocation cutting of the strengthening phase, achieving the dual effects of fine-grain strengthening and nanoscale second-phase particle strengthening, significantly improving the mechanical properties of the aluminum alloy surface. This invention can flexibly adjust the strengthening process according to the characteristics and application requirements of different aluminum alloys, meeting the requirements of different applications, while also possessing high energy efficiency and high performance.

This invention relates to the field of oil and gas drilling equipment manufacturing, and discloses a pneumatic expansion packer for oil and gas wells. The packer includes an upper connector, one end of which is fixedly connected to an exhaust / unsealing valve. A central tube is fixedly connected to the end of the exhaust / unsealing valve away from the upper connector. An expansion cylinder is slidably connected to the inner wall of the central tube. A sealing cylinder is fixedly connected to the end of the expansion cylinder away from the central tube. An installation mechanism includes a mounting pad, which is fixedly connected to the inner wall of the expansion cylinder. A connecting frame is fixedly connected to the top of the mounting pad. By setting up this installation mechanism, when the expansion cylinder is subjected to impact force from tubing vibration, the impact force is transmitted through a friction wheel to a silicone compression cylinder. The compression cylinder initially buffers the vibration through its own elastic expansion and contraction. Then, a buffer rod transmits the remaining pressure to a rubber bladder inside the buffer box. The rubber bladder completely absorbs the vibration pressure, achieving a two-stage flexible buffering of the vibration impact force, thus completely avoiding plastic deformation of the expansion cylinder caused by vibration.