247 results about "Inertial moment" patented technology

The invention belongs to the technical field of aircraft control, relates to an aircraft gravity center real-time balancing method and system based on dynamic parameter fusion, and aims to solve the problems of insufficient real-time performance, accuracy and self-adaptability of a gravity center balancing method under complex flight conditions in the prior art. The method comprises the steps that real-time parameters are obtained, and the real-time gravity center position is calculated; if the real-time gravity center position is not within the preset range, calculating a first inertia moment and a first additional moment caused by fuel density change and a second inertia moment and a second additional moment caused by aeroelastic deformation; performing inertia moment correction based on the first inertia moment and the second inertia moment; additional moment correction is carried out based on the first additional moment, the second additional moment and the real-time pitching inertia moment; when the real-time gravity center position is within the preset range, gravity center balancing is completed. The fuel oil density and aeroelastic parameters are estimated in real time through a self-adaptive control algorithm, rudder deflection and fuel oil distribution are cooperatively adjusted, and the problem of center-of-gravity shift under complex disturbance can be effectively solved.

The invention relates to the technical field of construction and the technical field of software, and discloses a fabricated structure evaluation method and device based on a toughness value and carbon emission, and the method comprises the steps: adding the damage volumes of all interfaces, and obtaining the damage amount of a fabricated structure; when the damage amount of the fabricated structure is within the damage range, a repair scheme of the fabricated structure is obtained, and the carbon emission amount of the repair scheme is generated; according to the length of each interface, the inertia moment of the complete part of each interface, the moving distance of the neutral axis of each interface and the contact surface rigidity model, the contact surface rigidity of the fabricated structure is generated, and according to the contact surface rigidity of the fabricated structure, the material elasticity modulus of the fabricated structure and the toughness model, the toughness value of the fabricated structure is generated. And performing specific value calculation on the carbon emission of the repair scheme and the toughness value of the fabricated structure to generate an evaluation value of the repair scheme. According to the invention, the evaluation efficiency of the repair scheme of the fabricated structure can be improved.

The invention belongs to the field of space manipulators, and relates to a vibration suppression control method and system for a flexible base space manipulator, and the method is based on a Lagrangian method and considers multiple coupling effects to completely establish a dynamic model of the flexible base space manipulator system. An inertia matrix estimation item is constructed based on a parameter identification method to realize motion decoupling of the space manipulator, and a control law is designed based on a fast and slow subsystem theory to realize high-precision control of an assembly task of a space manipulator module and vibration suppression of a flexible base. And mechanical arm fine assembly operation control and base vibration suppression control for the flexible base space mechanical arm are achieved. The problem of how to complete a high-precision assembly task on the basis of restraining vibration of the base of the double-space mechanical arm is solved.

The invention relates to a self-adaptive impedance control method for a robot to track an unknown curved surface, and aims to solve the problems that traditional impedance control parameters are fixed and cannot adapt to sudden change of the curved surface, a solution integrating bimodal curved surface sensing and asymmetric impedance adjustment is provided, and the normal vector and curvature of the curved surface are identified online through an improved recursion method. The normal stiffness is dynamically adjusted based on curvature feedback, the tangential stiffness keeps flexible tracking, and a contact depth constraint mechanism is introduced to prevent overload. The parameter adaptive law is combined with geometric features, the inertia matrix is accelerated and updated in a high-curvature area, and a gravity item is preferentially corrected in the normal direction. Compared with a traditional method, the method has the advantages that the normal force overshoot can be reduced, the curvature sudden change response time is shortened, and the tangential tracking precision is improved.

A method for implementing a closed loop of an advanced driving aid device for the lateral control of a motor vehicle includes synthesizing a controller of the closed loop by solving an optimization problem based on a bicycle model of the vehicle. A family of at least two bicycle models of the vehicle is established, these models having, with respect to one another, at least one dispersion chosen from among a dispersion of mass of the vehicle, a dispersion of drift rigidity on a drivetrain of the vehicle, a dispersion of the center of gravity of the vehicle, and a dispersion of the position of the matrix of inertia of the vehicle, the optimization problem being solved on the basis of all models of the family.

The invention provides a pipeline route design method based on a single-pipe mathematical model. The method comprises the following steps that a three-dimensional vertical section and a UCS coordinate system are determined according to a live-action three-dimensional model of a pipeline laying target area; establishing a single-tube mathematical model according to the three-dimensional longitudinal section and a UCS coordinate system; according to the single-pipe mathematical model, micro-piping laying is carried out on the pipeline; in the process of laying the micro-piping on the pipeline, calculating a direction similarity index according to the similarity between the pipeline shape and the pipe ditch shape; calculating a stress accumulation index according to the elastic modulus and the inertia moment; and constructing a total cost calculation model based on pipeline laying, and performing cost optimization based on the direction similarity index and the stress accumulation index so as to optimize the pipeline laying micro-piping. The method has the technical effects that the laying design precision and efficiency are remarkably improved, the cost is reduced, and the safety of the system can be enhanced.

The invention discloses a steel structure beam unit section intelligent optimization method and device and a medium. Obtaining a target beam unit of which the cross-sectional area is to be calculated, and obtaining a current axial force, a current allowable stress and a plurality of working conditions corresponding to the target beam unit; obtaining an initial beam unit cross-sectional inertia moment, and respectively calculating an initial beam unit cross-sectional area, an initial X-direction cross-sectional modulus and an initial Y-direction cross-sectional modulus through a preset initial beam unit cross-sectional inertia moment function; for each working condition, calculating a beam unit cross-sectional area corresponding to each working condition through a beam unit cross-sectional area intelligent optimization calculation method; and in each beam unit cross-sectional area, selecting the maximum beam unit cross-sectional area as a target beam unit cross-sectional area corresponding to the target beam unit, and feeding back the target beam unit cross-sectional area to a user. The problems that calculation is complex, the calculated amount is large and accuracy is poor due to the fact that the cross section area of the beam unit is determined through artificial experience are solved, and the accuracy of calculating the cross section area of the beam unit is improved.

Gas turbine engine for aircraft includes: an engine core including a turbine, compressor, and core shaft connecting the turbine to the compressor; a fan located upstream of the core; a gearbox; and a gearbox support arranged to at least partially support the gearbox. The fan has a mass in a range of 150 kg to 1200 kg. A moment of inertia of the fan is greater than or equal to 7.40×107 kgmm2. A radial bending stiffness to moment of inertia ratio of:the⁢ radial⁢ bending⁢ stiffness⁢ of⁢ at⁢ least⁢ one⁢ of⁢ the⁢ fan⁢ shaft⁢ at⁢ the⁢ output⁢ of⁢ the⁢ gearbox⁢ and⁢ the⁢ gearbox⁢ supportthe⁢ moment⁢ of⁢ inertia⁢ of⁢ the⁢ fanmay be greater than or equal to 2.5×10−2 Nkg−1m−1mm−2. A tilt stiffness to moment of inertia ratio of:the⁢ tilt⁢ stiffness⁢ of⁢ at⁢ least⁢ one⁢ of⁢ the⁢ fan⁢ shaft⁢ at⁢ the⁢ output⁢ of⁢ the⁢ gearbox⁢ and⁢ the⁢ gearbox⁢ supportthe⁢ moment⁢ of⁢ inertia⁢ of⁢ the⁢ fanmay be greater than or equal to 4.0×10−4 Nmrad−1kg−1mm−2.

The invention discloses a method and system for determining the optimal stress orientation of a concrete special-shaped sheet column, and relates to the technical field of constructional engineering. According to the method, a correlation model of special-shaped contour parameters and load conditions is constructed, a mechanical property key direction set is extracted, the screening range is narrowed, the optimal orientation determination efficiency is greatly improved, the design period is shortened, and the optimal orientation determination efficiency is improved based on multi-dimensional screening of all-circumferential inertia moment distribution, a rigidity curve and a bending moment contribution ratio. Core indexes such as section ultimate bearing capacity and ductility are comprehensively evaluated by combining stress simulation of a concrete nonlinear constitutive relation; through overall structure collaborative checking calculation and node stress analysis, it is ensured that the orientation meets the mechanical requirements of components and adapts to lateral force resistance and stress continuity of the overall structure, in combination with building construction requirements and node compressive strength redundancy optimization, the scheme of optimal mechanics but construction conflicts is eliminated, safety redundancy is reserved, the structure anti-disaster stability is guaranteed, and the construction safety is improved. And meanwhile, the method adapts to complex working conditions and specification requirements and ensures that the scheme can be directly applied.

The invention discloses a robot adaptive neural optimal tracking control method and device considering dynamic constraints, and the method comprises the steps: building a kinetic model of a robot in a joint space, and considering the input torque, inertia matrix, centripetal force and Coriolis force matrix and gravity torque of a robot system; the dynamics of the robot system is mapped to a Cartesian space, a position vector and a speed vector are defined, and a state space model of the robot system is established; and under the condition that dynamic constraints exist, a self-adaptive optimal nerve tracking controller is designed based on an optimal backstepping method and an actor-commentator Sheng network method so as to process the dynamic constraints and realize optimal tracking performance. Under the dynamic constraint environment, the robot can track the expected trajectory more accurately, and meanwhile movement safety is ensured.

Disclosed are systems, apparatuses, and methods for and related to dynamic control of torque and or lateral thrust applied to a load suspended load on a suspension cable to thereby achieve a target orientation or position or to otherwise move through use of a hyperparameter, wherein the hyperparameter comprises a normalized moment of inertia, wherein the hyperparameter comprises a ratio of a force command to a thruster and an angular acceleration.

The invention relates to a self-adaptive fault-tolerant generalization control method for an autonomous underwater vehicle, which comprises the following steps of: considering primary and quadratic term damping effects of water, unknown constant matrixes of a mass matrix and an inertia matrix of the autonomous underwater vehicle and external interference factors; an actuator effectiveness index matrix is introduced to model the autonomous underwater vehicle into an under-actuated model, and meanwhile it is ensured that the resultant force of gravity and buoyancy is zero, and kinematics and dynamics equations of the autonomous underwater vehicle are obtained; a controller is designed based on a backstepping method, a position error and a saturation function are defined, a Lyapunov function is selected, the position error is driven to be within a preset fixed constant range, an estimation rule and a projection function are introduced for solving the problem of unknown parameters to calculate thrust and control input, and high-precision trajectory tracking control over the autonomous underwater vehicle is achieved. Compared with the prior art, the method does not need linearization or conversion dynamics, can solve the problems of fault tolerance and time-varying interference, is better in performance, and effectively improves the control precision and stability of the autonomous underwater vehicle.

The invention discloses a variable cross-section continuous composite beam bending moment and displacement calculation method. The method comprises the following steps: S1, segmenting a variable cross-section continuous composite beam structure; s2, calculating anti-bending inertia moments of combined sections of different beam sections, and segmenting the variable-section continuous combined beam according to the anti-bending inertia moments of the sections to obtain a segmented uniform-section model; s3, geometric morphology equivalence is conducted on the variable-cross-section continuous composite beam according to a segmented uniform-cross-section model, half span is selected through symmetry to conduct theoretical analysis calculation, and the bending moment Mr at the segment point of the equivalent model section is obtained; s4, determining an actual inflection point position, and according to the actual inflection point position, performing further equivalent segmentation on the variable cross-section continuous composite beam; and S5, dividing the half-span variable cross-section continuous composite beam into three sections according to the positions of the cross-section segmentation points and the actual inflection points, establishing an equation based on the stress balance and deformation coordination relationship of the cross-section segmentation points and the actual inflection points, and providing a typical cross-section displacement, corner and bending moment calculation method.

The invention relates to the technical field of dynamic force measurement, and particularly provides an inertia force compensation method and system for a dynamic force measurement platform, and the method comprises the steps: arranging a plurality of acceleration sensors on the measurement platform, so as to collect the acceleration information of the platform in the dynamic motion in real time; by combining the mass of the dynamic force measurement platform and the inertia moment data of the dynamic force measurement platform, the error of the platform caused by inertia is calculated and compensated, so that the precision of dynamic force measurement is improved. The method provided by the invention is particularly suitable for small-amplitude disturbance force and micro-vibration measurement scenes, and the interference of the inertia force of the platform on the measurement result can be remarkably reduced.

The invention discloses a damage quantitative evaluation method based on an intelligent agent model and knocking scanning, and aims to realize accurate recognition and quantitative evaluation of beam structure damage through the agent model. The evaluation method comprises the following steps: firstly, according to a theoretical relational expression of a beam structure, selecting a cross-sectional inertia moment, a structure length, a damage position and a detection vehicle equivalent acceleration as input random variables, and taking a bending stiffness ratio of a damage position as a damage quantitative index, constructing and optimizing an agent model; establishing a nonlinear mapping relation between input and output; secondly, applying excitation by utilizing an intelligent knocking scanning detection vehicle, acquiring an acceleration signal, processing the signal by adopting a time-frequency analysis technology, and extracting feature information related to structural damage; and finally, predicting a damage quantitative index according to the agent model in combination with the identified damage position and feature data, and verifying and outputting a result.

The invention discloses a rapid modeling method of a carrier rocket rigid-elastic-shake coupling model, which comprises the following steps of: establishing a motion equation of a carrier rocket: establishing a mass center motion equation of the carrier rocket according to a Newton's second law, establishing a motion equation around the mass center of the carrier rocket according to a moment of momentum theorem relative to the mass center, and simplifying the carrier rocket into a one-dimensional beam model; establishing an elastic vibration equation; solving force, torque and generalized force thereof; solving expressions of gravity, thrust, control force, engine swing inertia force, aerodynamic force, aerodynamic damping force, wind disturbance force, force, torque and generalized force thereof; propellant shaking is analyzed by adopting a spring-mass-damper equivalent model; propellant shaking equations in the pitching direction and the yawing direction of the carrier rocket are established, and inertia force, inertia moment and generalized force generated by propellant shaking are established; the obtained various forces, moments and generalized forces and inertia forces, inertia moments and generalized forces generated by shaking of a propellant are substituted into a motion equation of the carrier rocket to obtain a mass center motion equation, the motion equation of the rocket is around the mass center, and a six-degree-of-freedom nonlinear total dynamical model of the carrier rocket is established when the rocket tilts and tilts; elastic vibration equations in three directions of yawing and rolling are established; and solving the carrier rocket rigid-missile-shake coupling model. According to the method, rapid numerical simulation can be carried out on the carrier rocket rigid-missile-shake coupling model, the influence of a solving result on carrier rocket attitude change is analyzed, and a foundation is laid for navigation and attitude control design of the carrier rocket.

The invention discloses a reduced scale model pile body test structure which comprises a test box, a model pile and a laser scanner, a test soil body is laid in the test box, the model pile is vertically inserted into the test soil body, a reaction wall is installed on one side of the test box, a jack is installed on the reaction wall, and a thrust plate is installed at the front end of the jack; a target is installed on the model pile, and the laser scanner is located above one side of the target. According to the hollow nylon pipe model pile, it is guaranteed that lateral mechanical behaviors are similar, and the material cost and the machining difficulty are greatly reduced; the nylon pipe can also be used as an inclinometer pipe, so that the sensor is convenient to arrange; meanwhile, a grooving pipe inertia moment correction formula is introduced to accurately calculate the actual inertia moment of the grooved pipe, and similar errors are reduced; meanwhile, a strain gauge and a target are matched to comprehensively monitor the model pile from internal deformation, surface strain to top displacement; the surface of the model pile is roughened, so that the surface roughness of the model pile is equivalent to that of a concrete pile, slurry is injected into a pile-soil gap, and the simulation authenticity of the interface friction characteristic is improved.

The invention discloses a load estimation method and an applicable mechanical arm system and electronic device thereof, which are used for calculating a plurality of inertial parameters of a load. The estimation method includes calculating a load mass; only the fourth joint at the tail end is rotated to calculate the load mass and the equivalent inertia moment; only rotating the second joint to measure the power data of the fourth joint, and repeating the step at least twice to obtain at least two groups of power data so as to calculate the mass center position of the load; and substituting the mass, the equivalent inertia moment and the mass center position into a parallel axis theorem calculation formula to obtain the mass center inertia moment of the load. According to the estimation method, the position of the center of mass is solved for the dynamic equation of the fourth joint, so that the calculation complexity of inertial parameters is simplified.

The invention provides an intelligent calibration method based on steel structure assembly precision, and relates to the technical field of intelligent calibration, and the method comprises the steps: collecting spatial position data of a joint of an I-shaped steel beam flange and an H-shaped steel column flange, converting the spatial position data into a verticality deviation value, and obtaining stress distribution data of a beam column connection node; calculating the deformation compensation amount of the I-shaped steel beam flange based on the perpendicularity deviation value and the stress distribution data, and calculating a calibration force distribution curve according to the change rule of the inertia moment of the section of the I-shaped steel beam flange; and the welding sequence and the welding bead spacing are optimized based on the calibration force distribution curve, and welding parameters are controlled through the thermal field distribution gradient, so that the perpendicularity deviation between the flange of the I-shaped steel beam and the flange of the H-shaped steel column is controlled. In this way, the problem that the assembly precision is insufficient due to the fact that perpendicularity deviation is difficult to calculate accurately and welding heat input distribution is uneven can be solved, the steel structure assembly precision and efficiency are improved, and the structural stability is enhanced.

The invention provides a self-adaptive carrying and dense parking planning method, system and device and a medium, and belongs to the technical field of intelligent logistics control. The method comprises the steps of detecting a vehicle contour in real time, and obtaining a vehicle width value and an attitude angle; based on the clamping jaw material section inertia moment and the moment safety threshold value, the safety distance is calculated; a quaternion PID controller is used for synchronously adjusting the rotating speed of a steering motor and the stroke of a hydraulic cylinder, and the minimum safety distance is calculated; a parking path is generated by adopting an improved path planning algorithm, and multipath interference is eliminated through waveform matching; and storing the parking space state based on the block chain technology, verifying whether the vehicle is parked in the preset parking space after parking is completed, and updating the global map through the smart contract after verification is passed. Through the modes of dynamic perception, adaptive control, multi-target optimization and credible interaction, the operation precision and stability of the AGV in a carrying scene are realized.

A method of operating a work vehicle (10) is provided. The work vehicle (10) comprises a swing device (11) rotatable about a swing axis (33). The swing device (11) includes: an arm structure (14) including a boom (16) and an arm (17); a boom actuator (18) for controlling the boom (16); and at least one boom head pressure sensor (77) for generating boom head pressure data indicative of a boom head pressure of the boom actuator (18). The method includes determining, by a control system (50), a maximum permissible swing speed at which the swing device (11) rotates about the swing axis (33) to account for a moment of inertia of the swing device (11) based on boom head pressure data and a mapping relating the boom head pressure data to the maximum permissible swing speed. The method further comprises limiting a maximum operating swing speed of the swing device (11) to a maximum permissible swing speed.

Provided is a control device and program capable of easily outputting the state of mechanical loss in an induction motor. A control device that controls an industrial machine having an induction motor includes: a power cutoff section that cuts off power supply to the induction motor; a speed acquisition section that acquires the rotational speed of the induction motor; an acceleration calculation section that calculates acceleration based on the acquired rotational speed; a moment of inertia acquisition section that acquires the moment of inertia of the main shaft of the induction motor; a mechanical loss calculation section that calculates the mechanical loss of the induction motor based on the acquired rotational speed, the calculated acceleration, and the acquired moment of inertia; and an output section that outputs the calculated mechanical loss.

The present invention relates to the technical field of aircraft mass characteristic measurement, and discloses a simple aircraft mass characteristic measurement device and measurement method. The measurement device includes a horizontally arranged measurement platform, on which two support mechanisms are installed. The support mechanisms include a base and two hydraulic telescopic rods vertically fixed to the base. A horizontally arranged crossbeam is installed on the top of the two hydraulic telescopic rods. The outer wall of the crossbeam is provided with a plurality of sleeves. A universal joint is fixed to the bottom of the outer wall of the sleeve, and a suspension rope is provided on the universal joint. The present invention suspends the aircraft above the measurement platform, and uses the equilibrium equation of the moment taken at the suspension point to calculate the position of the center of mass relative to the suspension point, thereby determining the position of the center of mass of the aircraft; then, the moment of inertia of the aircraft is measured using the double cycloid method. The operation is simple, the method is reliable, and it can be widely used to measure the mass characteristics of aircraft.

The invention relates to the technical field of steel structure construction, and provides a longitudinal and transverse sliding treatment method and device for a large-span steel structure in a limited space. The method comprises the following steps: obtaining structural rigidity distribution of the large-span steel structure according to elastic modulus, section inertia moment and span of each section of the large-span steel structure so as to obtain a sliding unit block optimization model of the large-span steel structure; according to the sliding unit block optimization model of the large-span steel structure, initial division of the large-span steel structure is carried out, and initial blocks are obtained; the node rigidity difference between the initial blocks is smaller than or equal to a set difference value, and the sliding path of each initial block avoids a space obstacle; according to the ratio of the local rigidity to the overall rigidity of the large-span steel structure, the initial blocks are optimized, and a plurality of sliding units are obtained; and according to the multiple sliding units, a longitudinal and transverse sliding scheme of the large-span steel structure in the limited space is obtained. By adopting the method, the local stress overrun risk of the large-span steel structure can be reduced.

The application discloses a kind of acceleration load calculation formula correction method for pipeline stress analysis, comprising the following steps: 1) based on potential flow theory, diffraction theory, establish ship motion equation;2) in AQWA software, the ship length, type width, type depth, design draft, displacement, inertia moment of general FPSO are input, time domain analysis is carried out, and its hydrodynamic coefficient is obtained, then acceleration load extreme value is predicted using SESAM software;3) according to the ship length, type width, type depth of general FPSO, design draft, structural draft, displacement under different working conditions, the acceleration of each degree of freedom is calculated according to ship motion acceleration load calculation formula;4) error analysis is carried out to the acceleration value calculated in steps 2), 3), and the acceleration formula calculation value needs to be corrected if the error is greater than d;5) introduce correction coefficient f, and the acceleration calculation value with error greater than d is corrected until the error is less than d;6) the corrected acceleration can be applied on the pipeline as acceleration load.

A terminal device 16: acquires, by a set parameter acquisition unit 1611 and as the value of a set parameter, a set value of a rotation speed of a propeller shaft 12 of a ship which is sailing a real sea area; and acquires, by a realized parameter acquisition unit 1612 and as the values of realized parameters, the values of a wave direction, a wave period, a wave height, a tidal direction, a tidal speed, a wind direction, a wind speed, draft, and a travelling direction of the ship which is sailing the real sea area. The terminal device 16 identifies, by a moment-of-inertia identification unit 1616 and through using a machine learning model L, the value of an inertia parameter of a flywheel according to the combination of the acquired values of the parameters. The value of the inertia parameter is for reducing the energy consumption rate of the ship. The terminal device 16 outputs, to a flywheel system comprising a function for changing the moment of inertia of the flywheel, moment-of-inertia data indicating the value of the moment-of-inertia identified by the moment of inertia identification unit 1616.

The invention belongs to the technical field of structural strength design, and particularly relates to an airtight cabin angle section external load determination method and device.The method comprises the steps that S1, the length L1, the elasticity modulus E1 and the sectional inertia moment I1 of a cross beam connected with an angle section horizontal plate are determined, and the cross beam bears evenly-distributed aerodynamic loads q; s2, the length L2, the elastic modulus E2 and the section inertia moment I2 of the angle section vertical plate from the end, connected with the longitudinal beam, of the angle section vertical plate to the root section are determined; and S3, solving the external load borne by the angle section. The calculation time is shortened, the calculation is simple, and the scheme design efficiency of the structure is improved.

The invention relates to hanging basket equipment for a continuous beam and a hanging mechanism and a construction method of the hanging basket equipment. The suspender adopts I-shaped section steel composed of two opposite wing plates and a middle web plate, the web plate transmits axial tension, the wing plates increase the inertia moment of a transverse stress section, the wing plates and the web plate form a collaborative stress system, and lateral bending deformation in the thickness direction is effectively restrained. The cross section of a locking hole of the locking mounting base is of a big-end-up conical structure, the two locking inclined blocks are attached to the inner wall of the locking hole and the two sides of a suspender web correspondingly, and the self-locking effect that the larger the load is, the higher the extrusion force is is is formed. Meanwhile, the limiting protrusion abuts against the locking inclined block, the contact area is increased to share part of vertical loads, and meanwhile the locking inclined block and the hanging rod are limited to move in the locking state. The limiting protrusions are arranged at intervals in the length direction of the hanging rod, a plurality of adjusting gears are formed, the vertical height of the bottom basket mechanism can be adjusted, and the pouring height requirements of different cantilever beam sections are met.

An electronic device casing includes a first plate and two second plates. The first plate includes at least one embossing structure. Times of an average moment of inertia of cross sections of the first plate in a first direction are not smaller than 1.14. The two second plates are connected to the first plate and form an accommodation space with the first plate.

A transducer system having a transducer structure having a plurality of surfaces to be measured and at least one coupling member for removably coupling an object to the transducer structure. A transducer is coupled to the transducer structure and has at least one strain sensor coupled to the plurality of surfaces to be measured for measuring deformations of the transducer structure in a plurality of directions. The system has a dynamic measurement unit for measuring at least one acceleration of the object and at least one controller. The controller is configured to receive deformation measurements in the plurality of directions; receiving an acceleration measurement; and determining at least one of a mass, a moment of inertia, and a center of gravity of the object based on the deformation and acceleration measurements when the object is removably coupled to the coupling member.