174 results about "Ground testing" patented technology

The present invention discloses an intelligent onboard protection system for a plasma detector, comprising: an integrated protective cover and a nitrogen blowing port, a pressing device, a deployment device, a power supply subsystem and a control subsystem; the protective cover covers the sensor head and has an appearance consistent with the shape of the sensor head; the nitrogen blowing port blows nitrogen into the interior of the sensor during a ground test phase to prevent contamination; the system is sealed with a blocking cap before satellite launch to prevent dust contamination; the pressing device presses the protective cover against the sensor head when the system is in a protection state, and releases the protective cover by thermal cutting according to the instruction of the control subsystem; the deployment device cooperates with the pressing device to realize the deployment of the protective cover, and locks the protective cover after it is released to a specified position; the power supply subsystem supplies power to the pressing device according to the instruction of the control subsystem; the control subsystem periodically collects status monitoring parameters and transmits them to a payload management unit, controls the power on and off of the pressing device according to the ground remote control instruction, and executes the deployment operation of the system.

The invention discloses an on-board personnel physiological stress early warning method and system, and relates to the field of aviation intelligent health monitoring, and the method comprises the steps: carrying out the ground testing of a tested on-board personnel before on-board, and constructing a personalized physiological baseline threshold library; in the flight process of the aircraft, physiological data of personnel on the aircraft are collected in real time through wearable equipment, and aircraft navigation parameters are synchronously obtained and transmitted to a ground station; the ground station evaluates the stress degree of the personnel on the aircraft by combining a locally deployed physiological large model with a stored personalized physiological baseline threshold library; and when the stress degree exceeds a safety threshold value, a hierarchical regulation and control mechanism is triggered. According to the method, the physiological stability of the low-altitude aircraft personnel in the low-altitude complex airflow environment can be improved, the man-machine work efficiency level of the low-altitude manned aircraft is enhanced, and the stress state of the low-altitude aircraft personnel can be quantitatively evaluated.

The invention discloses a ground testing and evaluating method and system for the swell capacity of a capsule body of a floating airship. The method comprises the steps that the residual buoyancy weight of the airship is obtained; the front auxiliary air bag volume and the rear auxiliary air bag volume of the airship are obtained; acquiring the atmospheric density, the helium airbag density, the front auxiliary airbag density and the rear auxiliary airbag density; acquiring the mass of a front auxiliary airbag and the mass of a rear auxiliary airbag; the volume of the front auxiliary airbag and the volume of the rear auxiliary airbag are added and multiplied by the density of the helium airbag to serve as a minuend, the minuend is subtracted from the mass of the rear auxiliary airbag, the difference value is added with the residual buoyancy weight of the airship and the mass of the front auxiliary airbag, the addition result serves as a numerator, and the difference between the atmospheric density and the density of the helium airbag serves as a denominator; acquiring the actual volume of the airship airbag; according to the ratio of the actual volume of the airship airbag to the designed theoretical volume of the floating airship, the swell capacity of the airship airbag is obtained; the method has the advantage that the swell capacity of the capsule body of the floating airship can be accurately calculated and evaluated.

The invention discloses ground zero-gravity deployment test equipment for a two-dimensional deployable planar antenna, and relates to the technical field of satellite ground tests. The first follow-up assembly and the second follow-up assembly are movably installed on the supporting truss in the horizontal direction and used for passively following unfolding and folding movement of the panel antenna; the at least two unloading assemblies are detachably connected with the first follow-up assembly or the second follow-up assembly and used for hanging and gravity unloading of the panel antenna; the satellite overturning vehicle is used for changing the attitude of the panel antenna; and the switching assembly is mounted on the satellite turnover vehicle and is used for connecting the panel antenna. The device combines the unfolding principle of the two-dimensional deployable planar antenna and the precise unloading requirements of gravity and gravitational torque in the unfolding process, provides powerful technical support and engineering practice guarantee for smooth unfolding and stability keeping of the planar antenna after a satellite is in orbit, and has important significance for guaranteeing normal operation of a satellite system.

The invention belongs to a jet well washing process, and particularly relates to a high-pressure hydraulic jet well washing process for an in-situ leaching uranium mining layer. The in-situ leaching uranium mining layer high-pressure hydraulic jet well washing process comprises the following steps: step 1, drifting a well; step 2, ground testing; thirdly, a cleaning tool string is assembled and cleaned; and 4, pulling out of the hole. The high-pressure hydraulic jet well washing method has the advantages that 40 liquid pumping holes are cleaned in total in high-pressure hydraulic jet well washing, and in follow-up test effect tracking, the water quantity of 16 drilled wells (40%) is increased to 1.5 m < 3 > / h, and the maintaining time is longer than 150 d; when the liquid injection hole is removed, the effect of the hole washing mode is far better than that of a liquid pumping hole, the water amount is increased by 1.3 m < 3 > / h, and the maintaining time is only 32.5 d.

The invention provides a method and a system for improving the precision of an on-orbit SAR antenna pattern of a light and small satellite. The method comprises the following steps: S1, establishing an SAR antenna mechanical flatness field model; s2, establishing a thermal deformation field model of the SAR antenna; s3, establishing an SAR antenna T / R active channel amplitude-phase data field model; s4, SAR antenna machine, thermal and electrical errors are converted into a unified phase coordinate system; s5, establishing a satellite attitude pointing error model, and performing unified physical field conversion; and step S6: respectively carrying out sensitivity analysis on the direction of the antenna pattern aiming at the satellite attitude and the SAR antenna mechanical, thermal and electrical errors. According to the method, ground test and on-orbit data are adopted to compensate for SAR antenna mechanical, electrical and thermal phase errors and satellite platform attitude errors, so that the precision of an SAR antenna pattern model is further improved, and the on-orbit image quality is practically guaranteed.

The invention discloses an on-satellite intelligent protection system for a plasma detector. The on-satellite intelligent protection system comprises a protective cover and a nitrogen blowing port which are integrally designed, a pressing device, an unfolding device, a power supply subsystem and a control subsystem, the protective cover covers the head of the sensor and is consistent with the head of the sensor in shape; the nitrogen blowing port blows nitrogen into the sensor in a ground test stage to prevent pollution; the blocking cap is used for blocking before the satellite is launched to prevent dust pollution; when the system is in a protection state, the pressing device presses the protective cover and the head of the sensor, and the protective cover is released through thermal cutting according to an instruction of the control subsystem; the unfolding device is matched with the pressing device to achieve unfolding of the protective cover, and the protective cover is locked after being released to a designated position. The power supply subsystem supplies power to the pressing device according to an instruction of the control subsystem; the control subsystem periodically collects state monitoring parameters and transmits the state monitoring parameters to the load management unit, controls power-on and power-off of the pressing device according to a ground remote control instruction, and executes unfolding operation of the system.

The invention discloses a lunar dust protection system for a low-energy particle detector. The lunar dust protection system comprises a protective cover, a nitrogen blowing opening, a pressing device, an unfolding device, a power supply subsystem and a control subsystem, wherein the protective cover and the nitrogen blowing opening are integrally designed; the protective cover covers the head of the sensor and is consistent with the head of the sensor in shape; the nitrogen blowing port blows nitrogen into the sensor in a ground test stage to prevent pollution; the blocking cap is used for blocking before the satellite is launched to prevent dust pollution; when the system is in a protection state, the pressing device presses the protective cover and the head of the sensor, and the protective cover is released through thermal cutting according to an instruction of the control subsystem; the unfolding device is matched with the pressing device to achieve unfolding of the protective cover, and the protective cover is locked after being released to a designated position. The power supply subsystem supplies power to the pressing device according to an instruction of the control subsystem; the control subsystem periodically collects state monitoring parameters and transmits the state monitoring parameters to the load management unit, controls power-on and power-off of the pressing device according to a ground remote control instruction, and executes unfolding operation of the system.

The invention discloses an aircraft high-altitude operation data calibration method based on a ground test, and the method comprises the following steps: S1, simulating all altitude environments, and selecting different working conditions; s2, calibrating operation data under different altitude environments and different working conditions; wherein in the step S2, the operation data comprises the fuel injection quantity, when the fuel injection quantity is calibrated, the working condition is selected, the optimal fuel injection quantity is set as an initial value under the 0-altitude environment, then adjustment is conducted on the basis of the initial value, and the fuel injection quantity under the same working condition at all the altitudes is determined according to the change condition of the aircraft power. The calibration process is relatively simple, the adjustment basis is reliable, the adjustment efficiency is high, the result is reliable, and the high-altitude flight reliability of the aircraft can be ensured.

The invention discloses an adaptive detection system and method for a spaceborne computer, relates to the technical field of space flight and aviation, and adopts a nonlinear state space model to establish a state transition equation and an output equation so as to realize accurate modeling and real-time detection of the spaceborne computer. The adaptive detection middleware integrates heartbeat detection, power supply power-on detection, multi-protocol communication, RS422, CAN, TCP and the like, supports remote interaction and intelligent task scheduling, and improves the automation degree of detection; compared with a traditional method, data interaction is optimized through a multi-protocol self-adaptive processing mechanism, the detection efficiency is improved, the system maintenance cost is reduced, the data interaction real-time performance is improved, the problems that detection equipment is complex, data interaction is not flexible, detection precision is low and the like are solved, the integration level, the intelligence and the remote control capability of the detection system are improved, and the detection efficiency is improved. The method is suitable for the fields of spacecraft ground testing, spaceborne computer research and development, testing and maintenance and the like, and has important engineering practical value.

The invention provides a drilling fluid flow monitoring device and method suitable for a mud runway, relates to the field of petroleum drilling ground testing instruments, and solves the problem that an existing monitoring method is low in overflow prediction precision and cannot find overflow in time. The device comprises a flow measuring unit (1), and the left side and the right side of the flow measuring unit (1) are connected with a flow guide unit (2) and a flow blocking unit (4) through flange plates respectively. The upper part of the diversion unit (2) is connected with the video monitoring unit (3); the flow measuring unit (1) is an electromagnetic flowmeter and is used for measuring the outlet displacement; the flow guide unit (2) is used for guiding drilling fluid to flow to the flow meter; and the flow choking unit (4) is used for controlling stable flow of the drilling fluid. According to the drilling fluid flow monitoring device suitable for the mud runway, real-time accurate monitoring of the flow of a drilling fluid outlet can be achieved, then monitoring of overflow and leakage of the drilling fluid is achieved, and well control safety is ensured.

The invention discloses a high-redundancy repeatable unlocking earth screen unfolding mechanism, which relates to the technical field of satellite load unfolding mechanisms and comprises an electromagnetic unlocking assembly, a hinge spring driving assembly, a ball pin assembly, an earth screen assembly and a mounting base. The hinge spring driving assembly provides unfolding driving force and in-place pre-tightening force for the earth screen mechanism. The electromagnetic unlocking assembly locks the ball pin assembly installed on the earth screen, and therefore locking of the earth screen is achieved. When the satellite is launched, the electromagnetic box is locked to fold the earth screen, and load envelope is reduced; the electromagnetic box is unlocked after on orbit, and the earth screen is unfolded and pre-tightened in place through the hinge spring driving assembly. The earth screen mechanism is simple in structure, an electromagnetic box unlocking scheme is adopted, the earth screen mechanism can be repeatedly locked and unlocked in a ground test, the unlocking assembly and the driving assembly are in redundant design, and the reliability of the unfolding mechanism is greatly improved.

The invention discloses a ground testing device and method for a high-thrust electric servo steering engine based on torsion bar spring composite loading, and belongs to the field of aviation aircraft design. According to the invention, the elastic deformation of the torsion bar spring is utilized to resist the torque transmitted by the motor actuator cylinder, and the actual flight load of the control surface is simulated. A plurality of groups of high-rigidity spiral springs (the rigidity coefficient is 10-100N / mm) are connected in parallel, so that 0-600Nm multi-stage torque output is realized; a mechanism driven by a servo motor is integrated, and according to different spring sets and the working length of the torsion bar, a servo steering engine is driven to stretch out and draw back through a target torque real-time conversion algorithm, so that the torsion bar is rotated to achieve the target torque.

The application discloses a hydrogen fuel cell power supply adaptability ground test method, system, equipment, medium and product of a UAV, relates to the UAV test technical field, obtains the ground test data of the to-be-tested UAV, carries out power demand analysis by using the ground test data, obtains a plurality of motor input total power, a plurality of motor output shaft power and weighted average propeller force efficiency, carries out power supply test on the preset hydrogen fuel cell by using each motor input total power, obtains a safety detection result and a plurality of variable load power response times, when the safety detection result is qualified, then carries out power supply adaptability detection according to each variable load power response time, each motor input total power, each motor output shaft power and weighted average propeller force efficiency, and obtains a power supply adaptability detection result. The application solves the problem that the existing hydrogen fuel cell lacks the safety buffer and power regulation capability of lithium batteries, which easily leads to the risk of stack overheating and reduces the reliability of the hydrogen fuel cell in the application of the UAV.

The application provides a kind of aircraft servo elastic dynamics model correction method considering operating surface gap, first aircraft structure is divided into substructure, and the aircraft dynamics model containing aileron gap nonlinearity is established according to substructure branch modal;And additional inertia force caused by aircraft operating aileron deflection is introduced in dynamics model, and the aircraft open-loop servo elastic motion equation containing aileron gap nonlinearity under independent generalized coordinate is obtained;According to sensor output equation, rudder transfer function and flight control system equation, the aircraft nonlinear servo elastic closed-loop system model containing aileron gap nonlinearity is established, and the model is corrected based on ground vibration test, rudder frequency response test and gap measurement test result, and the stability of the model is judged based on simulation analysis result and open-loop frequency response test result and is further corrected, which improves the accuracy of gap nonlinearity aircraft aerodynamic servo elastic characteristic evaluation, and is helpful to guide aircraft servo elastic ground test engineering practice.

This invention provides a satellite-launch separation signal system and a satellite-launch separation system, comprising: a first user unit that outputs two satellite-launch separation signal sources, each leading to two different contacts of a first analog separation relay; these signals then return to the first user unit via a first separation connector and a second separation connector; the input and output terminals of the first analog separation relay are each connected to a satellite display socket via cables; and a second user unit that outputs two satellite-launch separation signal sources, each leading to two different contacts of a second analog separation relay; these signals then return to the second user unit via a first separation connector and a second separation connector; the input and output terminals of the second analog separation relay are each connected to a satellite display socket via cables. This invention ensures that the signal is provided by the analog satellite-launch separation relay during ground testing, and avoids fatal malfunctions such as accidental separation commands issued before launch or mis-separation due to severe vibrations during the active phase, thus improving the reliability of the satellite-launch separation signal link.

The invention relates to the technical field of space robot ground testing, in particular to a space crawling robot surface and microgravity simulation system. Comprising a surface simulation assembly, an inclined plane adjusting assembly and a gravity balancing assembly, the surface simulation assembly is arranged on the inclined plane adjusting assembly, and the inclined plane adjusting assembly is used for adjusting the inclination angle of the surface simulation assembly; the gravity balancing assembly is arranged above the surface layer simulation assembly and used for being connected with the space crawling robot to be tested, and when the space crawling robot moves on the surface layer simulation assembly according to a set trajectory plan, the gravity balancing assembly can passively adapt to the motion trajectory of the space crawling robot; and the climbing motion of the simulated satellite surface in the space microgravity environment is completed. The space crawling robot simulates crawling on the surfaces of satellites and spacecrafts in the microgravity state, verification of the motion performance of the crawling robot under the space microgravity in a ground test is completed, and the problem that the ground test of the space crawling robot is difficult is solved.

The utility model relates to VPX switching equipment applied to satellite ground test, which relates to the technical field of satellite single-machine ground test and comprises a VPX female adapter plate, a VPX male adapter plate 6U, a VPX male adapter plate 3U, a VPX male adapter plate 6U structural frame, a switching cable and a VPX male adapter plate 3U structural frame. The VPX male adapter plate 6U is mounted in a structural frame of the VPX male adapter plate 6U, and the VPX male adapter plate 3U is mounted in a structural frame of the VPX male adapter plate 3U; a 6U bonding pad and a 3U bonding pad are respectively arranged on the VPX male adapter plate 6U and the VPX male adapter plate 3U, a plurality of cables are connected to the 6U bonding pad and the 3U bonding pad, and the other end of each cable is connected with a first connector; one end of the adapter cable is connected with the first connector, the other end of the adapter cable is connected with a second connector, and the adapter cable is connected with the VPX female adapter plate through the second connector; and a 3U clamping groove and a 6U clamping groove are arranged on the VPX female adapter plate.

The invention discloses a device for ground testing of a satellite two-dimensional radar mechanism. The device comprises a housing frame; a first driving motor and a second driving motor; a first speed reducer and a second speed reducer; the spherical parallel mechanism comprises a first transmission assembly, a second transmission assembly and a movable platform, the first transmission assembly is connected with the first speed reducer and the movable platform, and the second transmission assembly is connected with the second speed reducer and the movable platform; the two ends of the first pressure sensor and the second pressure sensor are connected with the movable platform and the output support respectively, and the first pressure sensor and the second pressure sensor are perpendicular to each other in the normal direction on the mounting surface of the movable platform; the information processor is connected with the first pressure sensor, the second pressure sensor, the first driving motor and the second driving motor; the radar mechanism driver is connected with the information processor and the radar mechanism; and the upper computer is connected with the radar mechanism driver and the information processor. The synchronous force increasing device has the advantage that synchronous force increasing of the radar mechanism can be achieved.

A multifunctional integrated ground testing system for spaceborne equipment is disclosed, covering the multifunctional testing field of spaceborne equipment. It provides reliable support for the functional performance testing of spaceborne equipment. The system includes an integrated management module, a telemetry and data processing unit, an interface forwarding simulator, a Ka-band converter, an RF link network, an interface forwarding network, and power supply equipment. Adopting a modular design, it features data interaction between the various components of the integrated ground testing system, human-machine interaction, remote control command parsing and distribution, telemetry information parsing, display and storage, health information monitoring, and dynamic signal simulation parameter calculation and distribution. This system solves major problems such as the limited number of connected spaceborne equipment and the single nature of functional performance test items, providing reliable and stable technical support for the ground testing of spaceborne equipment.

The present invention relates to a shallow water landing string, comprising a ground test tree, a blowout preventer nipple, a quick connector, a gate valve, a plurality of oil pipes, a shear blowout preventer valve, and an oil pipe hanging and running tool; the bottom of the ground test tree is detachably connected to the blowout preventer nipple, the bottom end of the blowout preventer nipple is detachably plug-connected to the quick connector, the bottom end of the quick connector is detachably connected to the gate valve, the bottom end of the gate valve is detachably connected to one of the oil pipes, a plurality of the oil pipes are detachably connected to each other, the bottom end of the oil pipe is detachably connected to the top end of the shear blowout preventer valve, and the bottom end of the shear blowout preventer valve is detachably connected to the oil pipe hanging and running tool. The shallow water landing string uses a deepwater string for shallow waters, so that direct production can be achieved at the bottom of the well during shallow water operations without the need for platforms and other facilities, ensuring the normal development of marine oil operations while ensuring a clear waterway.

The application provides a novel satellite-rocket electrical interface system, which comprises an interface assembly arranged on the outer surface of a satellite cabin plate, the interface assembly comprising X1F connectors, X2F connectors and X10B connectors arranged side by side; a ground test cable assembly, one end of which is provided with a first connector for connecting a satellite ground test device, and the other end of which is provided with a second connector for being connected with the X1F connectors and the X2F connectors; wherein a working port is arranged on the rocket fairing at a position corresponding to the interface assembly, and the working port is configured to allow the ground test cable assembly to be connected with the satellite connectors of the interface assembly before launch or to be manually disconnected and withdrawn. Thus, the application simplifies the satellite-rocket interface relationship, improves the reliability of satellite-rocket separation, improves the launch capacity, and reduces the system development cost.

The invention discloses a control system test method suitable for engine frame compensation, and the method comprises the steps: carrying out the zero debugging of a first-stage servo mechanism after the final assembly of the first-stage servo mechanism is completed; a rack compensation value delta, namely an offset signal, is sent to the first-stage servo mechanism through ground test equipment, and after the first-stage servo mechanism responds to the offset signal, a protection hoop is installed on the first-stage servo mechanism; the length of the first-stage servo mechanism is adjusted, so that the length of the first-stage servo mechanism is consistent with the length of the installed upper arrow; and carrying out a whole-rocket integration test. According to the invention, the pre-launch test work of deformation compensation of racks of different carrier rockets is solved, understanding and interpretation are facilitated, and the engine bellows is protected from long-term offset.

This invention relates to the field of spacecraft attitude control technology, and more particularly to an ultra-precise and ultra-stable on-orbit adaptive control method and system for pointing under additional stiffness disturbances. This on-orbit adaptive control method, by applying specific excitations to actuators and measuring their responses, combined with a recursive filtering algorithm, can accurately identify the total actuator stiffness, including the additional stiffness of the cable, in real-time on-orbit, overcoming problems caused by differences in ground testing environments and time-varying stiffness. Based on the real-time identified stiffness values, the parameters of the axial compensation controller and the actuator compensation controller are dynamically adjusted, enabling the control system to adapt to changes in the additional stiffness of the cable and maintain excellent control performance at all times. By employing dual compensation control at the axial load level and the actuator level, additional stiffness disturbances are synergistically suppressed at both the overall system and local actuator levels, improving the comprehensiveness and accuracy of control, and achieving ultra-precise and ultra-stable on-orbit adaptive control for pointing under cable additional stiffness disturbances.

The invention discloses a ground test bench position control method and system in a vacuum low-temperature environment, belongs to the technical field of ground calibration in the vacuum low-temperature environment, particularly relates to a precise position control method and system in a lunar soil injection simulation process, and is particularly suitable for the technical field of ground test and research and development of deep space exploration loads. The invention provides a ground test bench position control method and system in a vacuum low-temperature environment, which can overcome stress accumulation caused by temperature reduction in vacuum, can fully automatically complete a penetration simulation process, and provides a final physical boundary environment for data measurement of a detection load. The method for controlling the position of the ground test bed in the vacuum low-temperature environment is characterized by comprising the following steps of: 1, putting an occupying bomb into a cold barrel, filling simulated lunar soil between a bomb body of the occupying bomb and the cold barrel, and jolt-ramming the simulated lunar soil; 2, another test bomb is prepared, and the test bomb is kept at the room temperature;

The present application relates to the technical field of ground test of space liquid engine, and particularly relates to a large-thrust inclined test bench based on flexible leaf spring support and an in-situ calibration method. The test bench comprises a fixed frame platform arranged obliquely and a movable frame supported in the fixed frame gantry through multiple sets of leaf spring assemblies; the leaf spring assemblies constrain the movable frame to move only along the thrust axis direction; the front end of the movable frame is connected to a force measuring assembly through a transition frame, and the rear end is installed with a liquid engine through a adapter frame; the fixed frame is provided with an in-situ calibration assembly and a pre-tightening force assembly acting on the movable frame, and a safety limiting assembly. The in-situ calibration method applies a standard force to the movable frame through the calibration assembly, and simultaneously records the output of the force measuring assembly to establish a calibration relationship. The present application optimizes the super-large thrust bearing path through the oblique leaf spring support structure, has single-degree-of-freedom guiding and high lateral stiffness, and realizes high-precision, high-dynamic and high-reliability measurement of the thrust of the hundred-ton liquid rocket engine under real inclined working conditions in combination with in-situ hydraulic calibration.

The invention discloses an automatic test system and an automatic test sequence framework for a spacecraft. The system is characterized in that an automatic test sequence framework used for describing the automatic test of the spacecraft is defined, and the automatic test sequence framework is used for realizing the automatic test of the spacecraft through the following modules, the module comprises a sequence configuration sub-module, an automatic sequence execution sub-module, a result monitoring sub-module and a device-ground interface sub-module; and the sequence configuration sub-module is used for configuring and describing test steps of a test item by adopting the automatic test sequence framework to form an automatically executed test sequence. According to the invention, the ground test system for the automatic test of the spacecraft is realized by designing the automatic test sequence framework of the spacecraft, so that the test sequence is automatically executed, the data is automatically interpreted, the probability of errors introduced by human factors is reduced, and the overall test efficiency is greatly improved.

The invention discloses a high-precision gravity unloading device capable of achieving three-dimensional motion, and belongs to the field of gravity unloading. The device comprises an unloading truss assembly, a first longitudinal guide rail assembly, a second longitudinal guide rail assembly and two independent moving units, wherein the first longitudinal guide rail assembly and the second longitudinal guide rail assembly are different in installation height. Each set of motion unit comprises a longitudinal tackle assembly slidably connected to the longitudinal guide rail assembly, a transverse guide rail assembly bridged between the longitudinal guide rail assemblies, a transverse tackle assembly slidably mounted on the transverse guide rail assembly, a fixed pulley assembly fixedly connected to the transverse tackle assembly, and a lifting rope crossing the fixed pulley assembly to connect the tested rotating mechanism and the counterweight. Two sets of independent movement units are arranged, and the structural interference of a plurality of unloading points in the longitudinal opposite staggered movement process is avoided through the arrangement of longitudinal guide rails which are arranged in a high-low staggered mode. By optimizing the layout of the fixed pulley and the counterweight, three-dimensional high-precision dynamic follow-up unloading of a complex double-shaft rotating mechanism in a large rotating angle range is realized, and reliable microgravity environment simulation is provided for ground testing of aerospace equipment.

1. Name of the Design Product: Signal Processing Computer. 2. Use of the Design Product: For aerospace, aviation ground testing, shipborne, vehicle-mounted, etc., where there are complex signal transmissions, signal acquisitions, and signal processing. 3. Design Key Points of the Design Product: Lies in the shape. 4. Picture or Photo Most Illustrating the Design Key Points: Perspective View 1.

This utility model relates to a mobile testing system for ground testing of a turboshaft engine, belonging to the field of turboshaft engine technology, and solves the problem of the lack of mobility in existing whole-engine testing technologies. This utility model includes an experimental platform unit, a measurement and control unit, and a water circulation unit; the experimental platform unit, measurement and control unit, and water circulation unit are mounted on a mobile device; the experimental platform unit includes an engine testing platform and a dynamometer; the measurement and control unit includes a measurement and control device and a data acquisition device; the water circulation unit includes a circulating water cooling device, a cold water tank, and a hot water tank. This utility model enables ground testing and rapid transfer of a turboshaft engine.