141results about How to "Reduce trial risk" patented technology

The invention relates to a real vehicle test system and method for the traffic coordination of an automatic driving vehicle. A corresponding interactive test scene is set at a closed test road or a flexible test square based on a test need. The automatic driving vehicle serving as a tested body cooperates with a manned or program-controlled background vehicle to carry out multi-vehicle interactivescene simulation and multi-scene auto-driving vehicle traffic coordination testing. During the process, corresponding equipment is used for collecting and recording moving tracks of all tested vehicles and traffic participants and subjective judgment, physiological indicators related to the interaction comfort and riding comfort indicators of tested vehicle passengers and other vehicle participants are recorded, so that the traffic coordination testing of the automatic driving vehicle is realized and thus whether the automatic driving vehicle has the good interaction capability with other vehicle participants during the driving process is verified. According to the invention, the coordination control is powerful; the data are connected in a unified manner; and the good data support is provided.

The invention relates to an integrated type testing device for flying control of a flying machine. The integrated type testing device for the flying control comprises a mother board and a daughter board. The mother board of the flying control computer comprises a central processing unit, a flying controller parameter configuration memorizer, a flying data memorizer (secure digital) SD card, an input port, a pulse-width modulation (PWM) output port and a terminal, wherein the central processing unit is used for calculating algorithms, the input port is used for external PWM signals, the PWM output port for controlling a steering gear, and the terminal capable of carrying out alternating-direct (AD) conversion and direct-alternating (DA) conversion. The flying controller parameter configuration memorizer electrically erasable programmable read-only memory (EEPROM) and the flying data memorizer SD card are connected with the central processing unit through a serial peripheral interface (SPI) and an I2C bus. The daughter board comprises an integrated type triaxial accelerometer, a triaxial magnetometer, a triaxial angular velocity gyroscope, a barometric altimeter, an airspeedometer and a global locating system (GPS), wherein the integrated type triaxial accelerometer, the triaxial magnetometer, the triaxial angular velocity gyroscope, the barometric altimeter, the airspeedometer and the GPS are connected with the mother board respectively through a universal asynchronous receiver / transmitter (UART) interface and an AD conversion interface. The integrated type testing device for the flying control supplies a platform base for the algorithm research of a flying machine navigation system, and has high practical value in the field of meteorological observation, forest fire prevention, traffic monitoring and the like.

The invention relates to a large transformer, in particular to a test method for large transformers. A large transformer differential protection system test method comprises a different protection relay of a transformer, a phase meter and an ammeter and comprises the steps of: 1, selecting the ranges of the phase meter according to the test current for the check of a phase angle; switching the display picture of the differential synthetic protection relay to a differential current display unit; 2, connecting a power supply, utilizing the ammeter and the differential synthetic protection relay to check the current passing the transformer; 3, utilizing the phase meter at the current input of the differential protection relay to check and record the phase difference of the cophase currents at two sides; 4, simulating the fault state of the transformer, measuring the phase angle and the detection differential current on the relay, confirming the reliable operation of the differential protection relay under the default state; 4, ending the test, turning off the power supply and recovering former wires.

The invention relates to the technical field of bridge deflection tests, in particular to a bridge loading test deflection testing instrument. The technical scheme is that the bridge loading test deflection testing instrument comprises an instrument tank box and a leveling instrument which is arranged on the top face of the instrument tank body and used for measuring the levelness of the top face of the instrument tank body, and side face opening holes are formed in the side faces of the tank body. Three springs are fixedly hung on the upper portion of the tank body, a testing platform is connected at the lower ends of the springs, a testing instrument support is fixedly arranged above the testing platform, and the deflection testing instrument is fixedly arranged on the testing instrument support. A turn buckle which is used for adjusting the lengths of the springs before a deflection test is hung below the testing platform. The upper end of a deflection testing rope is fixedly arranged at the lower end of the turn buckle, and the lower end of the deflection testing rope is connected with a counterweight block placed on the ground. A large hang ring is arranged on the top face of the outer portion of the tank body. The bridge loading test deflection testing instrument is reasonable in structural design, convenient to manufacture, mount and arrange, high in deflection test precision, capable of effectively solving the problems that labor and materials are consumed, working at heights is needed, mounting and dismounting are troublesome, the test precision is hard to guarantee and the like of an existing deflection test system in load tests.

The invention discloses a testing stand for the dynamic airflow response in the single / double duct mode switching process. The testing stand mainly comprises a large-power centrifugal blower fan, an expansion segment, a stabilization segment, a contraction segment and a test segment, the centrifugal blower fan serves as an air source and provides continuous and stable airflow for the test segment, the airflow flown out of the centrifugal blower fan is expanded by the expansion segment, flows into the stabilization segment, is contracted by the contraction segment, flows into the test segment and is discharged finally. According to the method, the dynamic airflow response rule in the mode switching process can be researched in the design phase of a variable cycle engine, and the dynamic change rule of the airflow parameters can be obtained in the engine mode switching process.

The invention relates to a real-time fixed wing aircraft simulation system and a simulation method. The real-time fixed wing aircraft simulation system comprises a lower computer, a host computer, a ground station unit, an instrument unit, a vision unit and a parameter interface unit, wherein the lower computer is used for operating an aircraft model in a real-time embedded system, the host computer is used for compiling an aircraft model application program into the real-time embedded operation system and sending the compiled real-time embedded operation system to the lower computer, PID control parameters of the aircraft model are modified in real time, an operation state of the aircraft model is monitored, and the parameter interface unit is used for sending designated aircraft model parameters to the lower computer to realize real-time simulation of a designated fixed wing aircraft. Through the system and the method, a flight scene is simulated in real time, versatility of the aircraft simulation system is improved, complex programming and debugging are avoided, and simulation cost is reduced.

The invention provides a refrigeration heating system semi-physical simulation experimental method, belonging to the large-scale civil aircraft environment control field design technology. An experimental system comprises a refrigeration heating controller, a set of real refrigeration assembly and an excitation simulation bench. The method comprises the following steps: firstly, connecting the above parts together through a lead; secondly, setting up a refrigeration assembly physical simulation model in the excitation simulation bench, and transmitting a temperature value and a flow value of a real refrigeration assembly outlet to the refrigeration assembly physical simulation model; thirdly, setting up a cabin physical simulation model in the excitation simulation bench, and calculating a cabin temperature; fourthly, transmitting the cabin temperature to the refrigeration heating controller by the excitation simulation bench, and calculating a control rate of a temperature control valve by the refrigeration heating controller. The method in the invention has the following advantages: a defect in a system design can be discovered early, risk of an experiment is decreased, a processing period of system accessories is shortened, a quantity of the system accessories is reduced, a performance index and reliability of the whole system can be verified, and a systematic parameter and a control rule can be adjusted.

The invention discloses a rock temperature-permeation-stress-chemical coupling multifunctional test system and operation method thereof. The multifunctional test system comprises a vertical loading device (1), a chemical solution isolating device, a pressure control device, a pressure chamber (4), a volume change determinator (5), a temperature control device (6) and a computer (7); multiple geo-technical test operations are completed by controlling the vertical loading device (1), the chemical solution isolating device, the pressure control device, the pressure chamber (4), the volume change determinator (5) and the temperature control device (6) through the computer (7). The multifunctional test system disclosed by the invention is reasonable in structure design, simple in operation, wide in application range, high in automation degree, capable of realizing overall process automatic control of multiple geo-technical tests, high in stability, and long in service life.

The invention provides a turbine aerodynamics performance virtual testing system for a small turbine engine, which comprises a three-dimensional modeling module, a fluid dynamics modeling module, an assembling module, a three-dimensional computing module, a postprocessing module, a testing report and evaluation report generating module, a database managing module and a user management module. The turbine aerodynamics performance virtual testing system for the small turbine engine, provided by the embodiment of the invention, can be used for partially replacing a turbine actual test, thereby shortening turbine test period and reducing test risk and actual test cost. In addition, the turbine aerodynamics performance virtual testing system for the small turbine engine, provided by the embodiment, can be used for analyzing and evaluating pneumatic performances of a turbine and guiding the design of the turbine. The embodiment of the invention has an important promotion function for realizing the transition of an engine from a traditional design to a prediction design.

The invention discloses a method for two-stage fairing-mounted rocket body free boundary implementation and fairing fixed-end boundary implementation in a vibration tower. The method for two-stage fairing-mounted rocket body free boundary implementation comprises the steps that a free suspension tool is arranged, a rocket body and a fairing are hoisted to a tower body in sequence, the fairing is connected with the rocket body in a butt joint mode, the installing position of a basket is determined, the fairing is separated, and half baskets of the basket are fixed. The method for fairing fixed-end boundary implementation in the vibration tower comprises the two steps of fixed-end tool implementation and fixed-end boundary implementation. Compared with the prior art, the method for two-stage fairing-mounted rocket body free boundary implementation and fairing fixed-end boundary implementation in the vibration tower has the advantages that the test preparation period is short, available resources are effectively utilized, the test cost is reduced, and the test risks are reduced through the matched risk handling scheme.

The invention provides an overall-unit forced surge method for an engine, which successively comprises the following steps: 1. providing a gas compressor, and obtaining a surge margin of the gas compressor; 2. starting the engine, introducing high-pressure gas into the engine so that the engine approaches to the surge margin, and meanwhile, collecting the parameters of the engine by a surge monitor in real time; and 3. according to the parameters obtained by the surge monitor, determining the surge allowance of the engine. With the overall-unit forced surge method for the engine, the surge allowance and the pneumatic stability of the engine can be accurately determined. The method comprises simple operation steps, and the test risk is greatly lowered.

The invention provides an automatic micro-injection device which comprises a supporting plate which is vertically arranged; a supporting frame which is vertically arranged on the supporting plate andcan move in the axial direction of the supporting plate; a horizontal guide rail which is horizontally and vertically arranged on the supporting frame in a sliding manner; a connecting frame which isarranged on the horizontal guide rail in a sliding manner; an injection frame which is rotatably arranged on the connecting frame; an injection arm which is rotatably arranged on the injection frame;a puncture power mechanism which is fixedly arranged on the injection arm; a puncture frame which is fixedly arranged at the output end of the puncture power mechanism; an injection needle clamping device which is fixedly arranged at one axial end, far away from the puncture power mechanism, of the puncture frame; an injection power mechanism which is fixedly arranged at the other axial end of thepuncture frame; and a pushing plate which is fixedly arranged at the output end of the injection power mechanism and is used for being matched with a pushing rod of an injection needle and driving the pushing rod to push for administration. The invention further provides a control method of the automatic micro-injection device.

The invention discloses a loading device of a wing hanging connector. The loading device is used for guaranteeing that engine load is precisely transmitted to a hanging connector of a wing, wherein the hanging connector comprises an upper connector body, an inner side lower connector body, an outer side lower connector body, a lateral connector body and a rear connector body, the loading device comprises a hanging dummy member, a heading connector body, a matching lateral connector body and a vertical connector body, and the hanging dummy member is connected with the hanging connector body; the heading connector body is arranged on the hanging dummy member and is used for transmitting heading load to the inner side lower connector body, the outer side lower connector body and the rear connector body; the matching lateral connector body is arranged on the hanging dummy member and is used for transmitting lateral load to the lateral connector body; and the vertical connector body is arranged on the hanging dummy member and is used for transmitting vertical load to the inner side lower connector body, the outer side lower connector body, the rear connector body and the lateral connector body. The loading device can ensure that the engine load is precisely transmitted to the hanging connector of the wing, and can change the load direction in real time in a fatigue damage tolerancetest.

The invention belongs to the technical field of function test, and relates to a test method for verifying the opening and closing functions of a cargo door designed specific to the opening and closing function test of the cargo door. According to the method, the state of the cargo door during opening and closing function test can be accurately simulated; problems can be found and solved in time in a testing process, and smooth proceeding of the test is ensured; the test risk is lowered, and the safety of the test and test articles is ensured. A test method for verifying the opening and closing functions of the cargo door is realized, the accuracy of test verification is improved, the safety of test is ensured, the problem that the test state cannot be accurately simulated and problems cannot be found in the test process existing in the conventional method are solved, and smooth proceeding of the test is ensured by making adjustment in time.

The invention discloses a high-power offshore platform bollard testing device and belongs to the technical field of offshore platform working equipment. The device is characterized in that a first pull shackle and a second pull shackle are positioned at two ends of a socket rope respectively, a triangular eye plate is connected with the first pull shackle, the second pull shackle and a first buffering shackle respectively, a first connecting shackle is connected with the first buffering shackle and a first pull ring respectively, one end of a pull sensor is connected with the first pull ring, the other end of the pull sensor is connected with a second pull ring, and a second connecting shackle is connected with the second pull ring and a second buffering shackle respectively. By using the eye plate in a double-triangle structure for connection, firmer and more reliable mechanical bearing capacity is obtained, safety coefficients are lowered, and experiment risks are lowered; and especially, due to the pull sensor, connector damages caused by violent rotating or hard contact during experiments are prevented, and connection with other equipment is facilitated.

The invention relates to a 1.25-time brake experiment zero-load testing device and a testing method of a towing lift, and can solve the technical problems that the damage of 1.25-time rated experimentto the lifts is large, and risk of experiment on old lifts is high. The 1.25-time brake experiment zero-load testing device comprises a lift static testing mechanism, a lift dynamic testing mechanism, an intelligent portable terminal and special APP analysis software, wherein the intelligent portable terminal is in communication with a speed testing mechanism and a force testing device in a wireless bluetooth manner; the combination testing of the lift speed testing mechanism and the intelligent portable terminal is dynamic testing; and the combination testing of the lift static testing mechanism and the intelligent portable terminal is static testing. The 1.25-time brake experiment zero-load testing device disclosed by the invention adopts a non-loaded detection method, and has the advantages that a link of repeatedly loading and unloading weights and regulating a weighting switch is omitted, labor cost and time cost are saved, and rental charge and cartage of the weights are saved;and under the premise that the inspection quality is guaranteed, the inspection efficiency is improved, and the damage of the 1.25-time rated load experiment to the old lifts is also avoided, and therisk of the experiment is reduced.

The invention discloses a single conducting wire tension change simulation calculation method and a simulation test device of a transmission line. The simulation test device comprises a curve-shaped track, a fixed pulley at an upper end of the track, a movable pulley arranged on the track and rolling along the track, and a conducting wire towing the movable pulley to roll through the fixed pulley,the conducting wire is connected with a tension meter and a displacement meter, a conducting wire tension simulation weight is hanged on the movable pulley, the simulation test device disclosed by the invention can simulate and shorten a transmission line with a span greater than hectometer to several meter according to the change of factors such as the model number of the conducting wire, the span of the conducting wire and the like, in order to effectively and accurately reflect the tension change of the corresponding transmission line while guaranteeing the consistency of the stress features of a suspension string and the original transmission line, ensure the accuracy and reliability of designing the transmission line and greatly reduce the test difficulty, the test risks and the testcost.

The invention provides a large converter transformer oil tank for a fire extinguishing test. The large converter transformer oil tank comprises an oil tank body; the top cover covers the top of the oil tank body, and a flange connector of the ascending flanged base and the first oil conservator are reserved on the top cover; the second oil conservator is communicated with the oil tank body; and the first bracket is connected with the oil tank body, so that the height of the oil tank body is the same as that of the true transformer oil tank. The first support supports the oil tank body at the same height position as a real transformer oil tank. The size of the top cover is completely consistent with that of the top cover of the true transformer; according to the invention, the lifting baseis removed, and the lifting base flange interface and the first oil conservator are reserved, so that the structure of the test oil tank is simplified, the oil consumption and the test risk are reduced to the maximum extent while the physical fire of the real converter transformer is completely simulated, and the condition that flame burns at the top of the converter transformer during a fire extinguishing test is effectively simulated.

The invention discloses a rotary type slow-baking safety test device. The main components of the device include a heat-insulation heating box, a temperature parameter control element, a power output control element and a frequency adjustment rotary table; the heat-insulation heating box is connected with the temperature parameter control element through a cable, and the device can achieve programmed temperature control in a wide range. The safety test device has the following advantages that temperature control precision is high, the maximum temperature difference in a temperature field is smaller than 1 DEG C, and the minimum heating rate can reach 2 DEG C / h; under the condition of high loading ratio (78%), a sample can be evenly heated, and the maximum temperature deviation is less than 2%; remote control is achieved and safety is good; operation is simple and cost is low. The rotary type slow-baking safety test device is suitable for safety assessment of energetic materials under the condition of programmed temperature control, and especially for slow-baking safety assessment of large-size energetic materials.

The invention provides a device and method for testing the expanding characteristic of an empennage based on an air cannon device. According to the scheme, an air cannon, an experimental simulation bomb, a recycling box and a high-speed camera are included. The experimental simulation bomb is arranged in the air cannon. A shooting camera of the high-speed camera is arranged on the flight track of the experimental simulation bomb. The recycling device is arranged at the bomb point of the experimental simulation bomb. An empennage device is arranged outside the experimental simulation bomb. According to the scheme, the air cannon is adopted for launching the experimental simulation bomb, the empennage expanding condition of the experimental simulation bomb in the flight process is recorded through the high-speed camera, and the expanding performance of the empennage of a rocket can be tested under the completely dynamic condition; and the expanding process of a missile in a flying state can be truly simulated, the expanding characteristic of the empennage can be effectively evaluated, and the risk of a missile flying experiment can be reduced.

The invention provides motor substitution equipment for the static force test of an airplane wing. The motor substitution equipment comprises a motor simulation shell formed by a drum body, a front cover plate and a rear cover plate, horizontal bearing joints arranged on two ends of the drum body along the radial direction of the drum body, an axial bearing joint fixedly arranged on the front cover plate along the axial direction of the drum body, an upward loading platform fixedly arranged below the drum body, and a suspension device fixedly arranged above the drum body for suspending the substitution equipment below the airplane wing; a structure in hinge connection with a load applying device is arranged at each of the horizontal bearing joints and the axial bearing joint; each of the horizontal bearing joints fixedly arranged on the two ends of the drum body along the radial direction of the drum body comprises two first bearing joints symmetrically arranged at two sides of the vertical bisecting surface of the drum body for bearing a vertical downward load, two second bearing joints for bearing a horizontal outward load and two third bearing joints for bearing a vertical upward load. Substitution equipment is adopted for performing the static force test of the airplane wing, and the test risk and cost can be reduced.

The invention discloses a site testing system and method for an excitation device. The site testing system comprises the excitation device which comprises an AI interface, a DI interface, an AO interface and an AI debugging interface. The site testing system is characterized by further comprising an interface box which is connected with the AI interface of the excitation device; the interface box comprises an interface terminal and a signal conditioning module, wherein the interface terminal and the signal conditioning module are connected with external signals needing conditioning, the signal conditioning module processes the external signals needing conditioning and converts the external signals needing conditioning into signals which can be directly received by the AI interface, and the AO interface is connected with the AI debugging interface through a soft switch. Existing capacity of the excitation device is fully utilized, wiring and test operation is simplified, analog quantity signals and switching value signals can be compatible at the same time, an input channel can be flexibly configured, the requirements for site overhaul staff and testing risks are lowered, possible hidden dangers of loops relevant to excitation can be conveniently found out as soon as possible, and therefore whole reliability of the excitation device is improved.

The invention provides an anti-rollover device of an automobile rollover test bench. The anti-rollover device comprises a hydraulic system, an electric control system, a supporting base assembly and asupporting frame assembly, and is characterized in that the hydraulic system provides power for the whole supporting device, and an inclination angle of the supporting frame assembly can be changed by means of a power device in the hydraulic system; the electric control system forms a closed-loop control system and controls the hydraulic system according to parameters acquired by means of a signal acquisition device, so as to ensure that the supporting frame assembly is kept at a preset angle; the supporting base assembly is used for guaranteeing movement of the supporting frame assembly; andthe supporting frame assembly is used for supporting an overturned sample vehicle to ensure the safety of the sample vehicle in the test process. The anti-rollover device is adopted, so that the testrisk is reduced, the test safety is ensured, and the precision of the test result can be ensured.

The invention provides a reusable small-free-volume attitude-control ignition simulating device and method. The reusable small-free-volume attitude-control ignition simulating device and method comprises a reusable valve, a fuel gas generator simulating cavity shell, a pressure testing unit, an ignition unit, a free volume simulator with charges, a jet igniter and a spray pipe simulator; the reusable valve is used for simulating valve control during attitude-control work and used for controlling stopping and starting of a fuel gas simulating generator; the fuel gas generator simulating cavityshell is used for repeatedly bearing high-temperature and high-pressure hot fuel gas impact; the pressure testing unit is used for testing pressure data in the simulator; the ignition unit is used forigniting ignition powder of the jet igniter; the spray pipe simulator is used for simulating spray pipe conditions under the real working conditions; the jet igniter is used for rapidly igniting themain charge surface to ensure the consistency of capability releasing of the igniter; and the free volume simulator with the charges are used for simulating the ignition conditions of an attitude-control fuel gas generator under the real free volume conditions.

The invention relates to a water-base manikin which comprises a head water bag, a trunk water bag, a thigh water bag and a shank water bag, wherein all the water bags are provided with split structures and are made of soft transparent materials; multiple sets of combined valves are respectively arranged between the water bags; a mass center adjusting clamp is arranged on each of the water bag. An adjusting method for mass and gravity center of the water-base manikin comprises the steps of: confirming sizes of the water bags; manufacturing the water bags; adjusting the weight of the water bags; adjusting the mass center; and dewatering. A true person is replaced by the water-base manikin, so that the number of test personnel is reduced, the test risk is reduced, and the test cost is saved. After the mass and the mass center position are adjusted, signs are marked on the water bags and the mass center adjusting clamps, so that a water injection rate and a distance between loops of the mass center adjusting clamps are confirmed according to the signs during the test process and the consistency of the test data is excellent. The water bags are split, thereby being convenient and labor-saving in carrying.

The invention discloses an electric power engineering start-up debugging car which comprises an apparatus and equipment operating area and an apparatus and equipment installing area for debugging located in a cabin; the apparatus and equipment operating area comprises a tool cabinet, an operating board and a distribution box; the apparatus and equipment installing area for debugging comprises apparatus and equipment for debugging, signal wires for debugging, an apparatus rack and a signal wire rack; the signal wire rack is arranged by layers and provided with a wire coil and a sliding plate with a fixed pulley; the end parts of the signal wires for debugging are each provided with a pluggable terminal; the apparatus and equipment are installed on the apparatus rack through a sliding rail and an end lock catch device, and the apparatus and equipment for debugging comprise a voltage and current signal voltage divider, an electro-optical signal convertor, a signal-acquiring device and a data service platform for debugging. The electric power engineering start-up debugging car has the advantages of being compact in structure, convenient in detachment and installation, safe and reliable, flexible in use and great in practicability, the car is suitable for start-up debugging testing systems on electric power engineering sites with different voltage classes, the testing risk can be lowered, the damage to the apparatus can be reduced, the electric power engineering start-up progress can be promoted, time and labor can be saved and integration management can be carried out easily.

The invention discloses a rotor model test stand dynamic balance adjusting method. The rotor model test stand dynamic balance adjusting method comprises steps that step 1, a blade-less rotor test is carried out to acquire effective rotor test data; step 2, counterweights are added at a support arm of any rotor for multiple times; step 3, counterweights are added at a support arm of another rotor besides the support arm of the any rotor added with the counterweights in the step 2, and a rotor test is carried out to acquire rotor test data of the present rotor test; step 4, whether phase difference of the support arm of the rotor in the step 2 and the support arm of the rotor in the step 3 and an absolute value of difference of average data values of the step 2 and the rotor test data of the step 3 are in a threshold scope is determined; and step 6, a rotor balance fundamental frequency restriction value AmxL of the step 5 is taken as a largest threshold to carry out a blade rotor test; whether fundamental frequency of a rotor balance surpasses the rotor balance fundamental frequency restriction value in the blade rotor test process is monitored.

The present invention discloses a knob type shifter high and low-temperature durability test device with a gear information monitoring function. With the test device adopted, the knob component of a tested knob type shifter is driven to rotate between the first gear position, namely a P gear position and the last gear position cyclically under a set temperature test condition; the knob component is controlled to stop when rotating to each gear position, so that gear information real-time values used for judging the accuracy of gear information can be acquired; a feedback mechanism is adopted, when each rotation test is started, whether the telescopic shaft of a solenoid valve extends out from the tested knob type shifter is detected; and if the telescopic shaft of the solenoid valve extends out from the tested knob type shifter, the solenoid valve is energized under control so as to drive the knob component to perform cyclic rotation for once. With the test device of the invention adopted, when the tested knob type shifter is subjected to a high and low-temperature durability test, the accuracy of the gear information of the tested knob type shifter can be tested. The knob type shifter high and low-temperature durability test device with the gear information monitoring function has the advantages of high reliability of test results and capability of protecting the security of test equipment and the tested knob type shifter.

The invention provides a spectrum form librating constructing method of a pendulum impact tester. The method comprises the following steps that influential factors of an impact spectrum form of the pendulum impact tester are determined; major influential factors are combined and arranged via a multi-factor complete factorial experiment, and for minor influential factors, a control variable method is used to implement impact test; curve fitting is carried out to obtain an optimal fitting curve, and a corresponding standard spectrum form is obtained by fitting; and standard spectrum forms are concluded and gathered to obtain a standard spectrum form debugging database. The methods have the advantages that the standard spectrum form debugging database which is convenient to retrieve and easy to analyze is established on the basis of a curve fitting algorithm, the validity and convenience of the database are verified by test of different engineering models, influence of change of different influential factors on the impact response spectrum form is analyzed to obtain a debugging rule of the pendulum impact response tester, a control spectrum form of the impact response spectrum test of a spaceflight product can be guided to establish rapidly, debugging time is shortened, and the test risk is reduced.

The invention discloses an unmanned aerial vehicle ejection test risk assessment method, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle catapulting test flight test risk is analyzed and evaluated from six dimensions of commanding, flying and catapulting devices, a ground station, a measurement and control link and aircraft maintenance and 10 elements ineach dimension, so that the effective control of the unmanned aerial vehicle catapulting test flight test risk is realized.