13results about "Parachutes testing apparatus" patented technology

The invention provides an air-drop dummy neck sensor mounting device, and relates to the technical field of air-drop testing. A mounting groove is formed in the neck counterweight connecting piece, a support is mounted in the mounting groove through a bolt, a rotatable rotating rod is mounted on the support through a bearing, a take-up barrel is fixedly mounted on the rotating rod, three grooves are formed in the take-up barrel, movable plates are mounted in the three grooves through pin shafts, a hole groove is formed in the take-up barrel, and the movable plates are arranged in the hole groove. A spring is installed in the hole groove and abuts against the movable plate. According to the cable take-up device, the take-up barrel adopts the movable plate which is tightly jacked by the spring, so that cables are stored in order and are prevented from loosening; meanwhile, the fluted disc is meshed with the gear shaft, and a buckling plate, a pressing plate and a tension spring locking structure are matched, so that the flexible adjustment requirements of the cable length and the component posture in the test are met; the sensor connecting seat is movably connected with the fixing seat through the connecting pin, and the connecting pin is tightly pressed by the jacking screw, so that the displacement risk under air-drop impact is thoroughly eliminated.

The invention discloses a marine parachuting simulation test device and a test method thereof.The device comprises a simulation pool, a wave making room and a lifting throwing platform, an auxiliary tower is arranged on the lifting throwing platform, a main tower is arranged on the pool side of the simulation pool, and a steel cable system is erected between the main tower and the auxiliary tower; the steel cable system is provided with a guide rail steel cable and a driving steel cable, the guide rail steel cable and the driving steel cable are connected with a floating driving vehicle running between the main tower and the auxiliary tower, and an umbrella stand system is arranged below the floating driving vehicle. According to the seaborne parachuting simulation test device, a test environment meeting seaborne parachuting simulation test requirements is constructed by transforming or newly building existing pool resources; according to the marine parachuting simulation device, the horizontal and vertical movement speeds in the marine parachuting process can be accurately simulated, the accuracy of a test result is ensured, a real scene training environment is provided, and the lifesaving skills and the coping ability of passengers in a sea condition environment are enhanced through the simulated training.

The invention discloses a parafoil glide ratio test method. The method comprises the following steps: (1) preparation before test; a three-cup anemograph is used for testing the wind speed in the horizontal direction and the wind speed in the descending direction to replace the air-drop height and the horizontal distance to calculate the glide ratio, different wind speeds are used in a wind tunnel to calibrate the precision of the three-cup anemograph, and a calibration certificate is obtained; before testing, drawing a corresponding relation curve of a test value and a standard value according to indication calibration value data on a calibration certificate of the three-cup anemograph; a linear fitting method based on the least square method theory is adopted, a functional equation between a test value and a standard value is constructed, and the fitting precision R2 is larger than 0.99; (2) measuring data; measuring a vertical descending speed and a horizontal speed; (3) data processing; and carrying out test section relative density conversion, standard atmospheric sea level, standard weight vertical descent speed and horizontal speed conversion and glide ratio calculation. The glide ratio testing method can reduce errors and fully consider interference of external factors.

A method for testing the strength of a large-size high-strength parachute comprises the following steps: carrying out size scaling treatment of equal mechanical strength on a full-size parachute, and designing a parachute for an impact-drop test; and determining the weight M and the lifting stroke L of the counterweight, and carrying out a punching and falling test. According to the invention, the strength verification of the large-size parachute can be completed under the condition of a size-limited test field, and the effect of accurately evaluating the impact-falling load of the parachute can be achieved.

The invention belongs to the technical field of parachutes, and particularly relates to an air-drop parachute verification method. The technical scheme comprises the following specific steps: 1, configuring a pod, arranging an empennage at the rear part of the outer end of the pod, integrating a sensor and a communication module at the top, accommodating a parachute to be verified and a parachute stripper at the rear part, and placing a balancing weight in the pod; 2, the unmanned aerial vehicle is put after mounting the pod to a preset height; 3, stabilizing the attitude of the empennage during falling, and acquiring data such as time, height and velocity pressure in real time by a sensor; 4, when the data reaches a preset threshold value, parachute opening is triggered, and parachute opening and stable descending stage parameters are recorded; 5, when the pod falls to the ground, the parachute remover executes parachute removal and records mechanical parameters; and 6, verifying the multiple performances of the parachute and the real working condition performance of the parachute remover in combination with data after recovery. According to the invention, accurate verification is realized through process innovation, and the test reliability and comprehensiveness are improved.

This invention relates to a high-speed impact simulation test device for spacecraft landing tests, belonging to the technical field of extraterrestrial landing and takeoff tests. A rotating speed-up mechanism is horizontally positioned axially on top of a support frame. A lifting motor is coaxially connected to the rotating speed-up mechanism via a clutch. A counterweight is placed on the top platform of the support frame. One end of a first rope is connected to the counterweight, and the other end is wound around the small-diameter end of the rotating speed-up mechanism. One end of a second rope is wound around the large-diameter end of the rotating speed-up mechanism, and the other end hangs down naturally. A release device is installed on the second rope. The bottom end of the release device hooks the top end of a third rope. The third rope is connected to a parachute system. The parachute system and a buffer pad are placed on the bottom surface of the support frame, with the buffer pad located directly below the counterweight. This invention can pull out the parachute pack at a maximum speed of 40 m / s, enabling parachute pull-out performance tests of different specifications of parachute systems. Simultaneously, it can meet other high-speed impact test requirements.

The application discloses a simulation dummy for parachute air-drop test and an adjusting seat, and the dummy comprises a head assembly, a neck assembly, a shoulder assembly, a chest assembly, an arm assembly, a waist assembly and a leg assembly; the neck assembly comprises a cervical vertebra main body, the cervical vertebra main body comprises neck support pieces, neck elastic pieces and neck ligaments, the neck support pieces are arranged at intervals in the up-down direction, the neck elastic pieces are arranged between every two adjacent neck support pieces, the neck ligaments are made of collagen fibers, the neck ligaments are arranged at intervals in the circumferential direction at the middle and rear part of the cervical vertebra main body, each neck ligament is sequentially connected with the neck support pieces from top to bottom, and each neck ligament is located outside the neck elastic piece; the front part, the rear part, the left side part and the right side part of each neck support piece are outwardly convex to form convex parts, and the neck ligaments are connected at the convex part positions of each neck support piece. The dummy is closer to the real structure of a human body, and can truly reflect the neck condition of the human body in the parachute air-drop test.

Systems, methods and apparatus configured for optimizing a JMPI process introducing an easily visible worn device with an interactive authentication mechanism, illustratively, a keypad for entering a jumpmaster code or a fingerprint authentication device for obtaining a jumpmaster fingerprint. Following the completion of a JMPI, the jumpmaster signs their inspection with the code or fingerprint on a student's device for record keeping. Once recorded, in some embodiments a green LED, one of two, is illuminated. The process repeats for a second JMPI and a second green LED is illuminated. The two illuminated LEDs on a parachutist's wearable indicate to the jumpmaster that the parachutist has been inspected twice and may continue to jump. Each wearable is connected via wired or wireless means to a computing device in the manifest office, where records of each JMPI are kept, and where the JMPI status of each lift may be visualized.

A ground-effect drag parachute performance evaluation test method comprises the steps that load measurement three-component data is obtained, and the drag coefficient and the comprehensive swing angle of a drag parachute are obtained by combining atmospheric density and wind speed calculation; calculating a resistance coefficient and a comprehensive swing angle mean value; carrying out statistics on comprehensive swing angle frequency distribution; calculating a horizontal swing angle and a vertical swing angle; calculating a vertical direction swing angle mean value / a horizontal swing angle mean value; the rotation performance of the drag parachute is obtained through images. The method can be used for evaluating the ground effect influence of the near-ground horizontal drag parachute, and can quantitatively evaluate the influence of the ground effect on the resistance performance and the swing angle of the drag parachute.

The invention discloses a low-cost parachute verification pod, which belongs to the related technical field of parachutes, and comprises a buffer device, a pod body, a parachute mounting structure and an empennage, the interior of the pod body is provided with a counterweight mounting bracket and a counterweight, and the top of the pod body is provided with a hanging structure; the front end of the cabin body is connected with the buffer device; the parachute mounting structure is arranged at the end, away from the buffer device, in the cabin body in a triggering manner; the empennage is arranged around the circumferential position of the cabin body; the parachute mounting structure is arranged on the low-cost pod, the parachute opening process and aerodynamic characteristics of the parachute can be verified under different parachute opening speeds, different weights and different heights, and the defects of a parachute test method are effectively overcome.

This invention discloses a parachute opening friction test platform, comprising a test platform frame, a drive loading mechanism, a parachute line traction mechanism, and a steel cable; the drive loading mechanism includes an asynchronous motor and a traction roller; the parachute line traction mechanism includes a friction force fixture fixing mechanism, a sensor trolley mechanism, a limit switch, and a buffer unloading mechanism; the friction force fixture fixing mechanism limits the parachute lines; the tension sensor and safety release mechanism of the sensor trolley mechanism are respectively fixed on a slider plate, the slider plate is slidably connected to a ball bearing rail, the end of the parachute lines is connected to the tension sensor, the safety release mechanism is connected to one end of the steel cable, and the other end of the steel cable is wound around the traction roller; the buffer unloading mechanism is used to decelerate the sensor trolley mechanism and allow the steel cable to continue moving when it collides with the safety release mechanism; the limit switch is located on one side of the sensor trolley mechanism to control the asynchronous motor of the drive loading mechanism to stop.

The utility model discloses a parachute opening test device which comprises a tractor, a bearing carriage is installed on the tractor, a supporting base is fixedly installed on the bearing carriage, a parachute dragging mechanism is installed on the supporting base, and the front end of the parachute dragging mechanism is connected with a cross angle adjusting assembly. The cross angle adjusting assembly is connected with three groups of traction cables through three groups of tension detection assemblies, the other ends of the traction cables are all connected with the parachute opening assembly, and a data acquisition device is installed at the head of the tractor. And angle adjustment in four directions can be carried out, so that the traction cable and the tension detection assembly are kept on the same straight line, and the accuracy of data testing is improved.