The invention discloses a thrust measuring device applicable to a small thrust engine. The thrust measuring device comprises a static frame, a movable frame, an in situ calibration device, a force measuring component and a suspension part, wherein the movable frame, the in situ calibration device and the force measuring component are arranged on the static frame, and the suspension part is used for mounting an engine and can adjust the height of the engine. In the thrust measuring device, the suspension part is composed of a suspension block, a lifting bolt, a lifting thread bushing, an elastic element, a tension part and a rigidity tension and compression part or elastic tension and compression part, the engine is mounted by adopting a suspension way, the quantity of test accessories can be reduced, and mass can be reduced, so that inertia force and frictional force of a test device are reduced, and thrust measurement accuracy is improved; a mechanical loading mode is adopted for implementing static calibration, composition of the in situ calibration device is simplified, time of a test preparatory stage is shortened, and economy of the measuring device is improved; and for a specific engine, appropriate parts are selected for being assembled into the suspension part, and universality of a thrust device can be enhanced.

Small thrust measuring device

The invention relates to a simulation test device for a thrust force of a large-thrust-force double-pendulum engine, and particularly to a test device which can truly simulate the thrust force of the double-pendulum engine in flight of a rocket, wherein the large thrust force is not less than 70T. The simulation test device comprises the components of two force bearing ears, an engine frame, a base, a swinging cross shaft, a gimbal mount, two wire ropes, a connecting block, a first pin, a first joint bolt, an adjusting pull rod, a second joint bolt, a second pin, a third pin, a lever and a loading hydraulic cylinder. Two ends of each wire rope is threaded. According to the simulation test device, connection between the engine body and the loading connecting block is realized through the wire ropes which are provided with threads; and deformation of the wire rope is used for resisting an effect caused by threaded connection at two ends of each wire rope in the bidirectional swinging process of the engine. According to the simulation test device, a lever mechanism is used for realizing thrust force loading, and loading of a 70T thrust force is realized by means of a relatively small hydraulic force. A simple and reliable structure is realized.

Simulation test device for thrust force of large-thrust-force double-pendulum engine

The invention discloses a whole helicopter flexible suspension test device of a helicopter and belongs to the technical field of whole helicopter transfer function testing. The whole helicopter flexible suspension test device comprises a test bed, winches, flexible components, a test piece, lifting installation components, a navigation direction adjustment hanging beam, lateral adjustment hangingbeams, vibration exciter suspension ropes, an electromagnetic vibration exciter and a loading component. One end of each winch is fixedly connected with the test bed, and the other end of each winch is connected with the corresponding lifting installation component through the corresponding flexible component. The lifting installation components are provided with anti-torsion devices and can prevent the test piece from rolling and be twisted in the lifting process. One end of the test piece is fixed to the lifting installation components, and the other end of the test piece is connected with the electromagnetic vibration exciter. The electromagnetic vibration exciter is suspended on the test bed, and a vibration excitation test is conducted on the test piece through the loading component.By the adoption of the device, the free state of the helicopter can be simulated, different loading modes of a vibration excitation source can be achieved, and through a whole helicopter transfer function testing experiment of the helicopter, a transfer function between the center of a propeller hub of the helicopter and each related position can be actually measured.

Whole helicopter flexible suspension test device of helicopter

The utility model provides and a novel seal printer, it contains the shell, shell upper portion both sides be provided with master switch and fingerprint identification button respectively, shell one side below be provided with china ink volume pilot lamp, quantity indicating lamp and status indicator lamp, the inside lower extreme of shell be provided with ink -jet printhead, laser positioning system is installed to the ink -jet printhead lower extreme, shell lower extreme one side be provided with the USB interface, shell internally mounted have a the main control circuit board, the main control circuit board respectively with master switch, fingerprint identification button, china ink volume pilot lamp, quantity indicating lamp, status indicator lamp, ink -jet printhead, laser positioning system and USB interface connection. The utility model discloses seal function except realizing signature etc. Still can realize matcing with cell -phone etc. Is quick, and the remote control printer is more portable, can avoid big or small, the regional restriction of print media, the seal location is more accurate, and it is better to print the effect.

Novel seal printer

The invention discloses a self-centering vector force loading device, and belongs to the field of mechanics. The device comprises a loading rod, a sealing ring, a substrate, a loading apparatus, and a self-centering apparatus. Through the changing of the positions of a rotating flange and an unbalance loading flange in the loading apparatus, the device achieves the adjustment of a three-dimensional vector force in different loading directions. The device achieves the self-centering force loading through a spherical positioning block and a conical positioning block in the self-centering apparatus, and effectively reduces loss caused by axis bending when the three-dimensional force is loaded. The substrate guarantees the flatness of the front and rear surfaces, prevents a force unbalance loading angle from being generated, and avoids the impact on the direction of the vector. The device achieves the loading of the vector force for the loading rod through hydraulic pressure, and a loading process is stable and high in precision. The device is simple in structure, is high in rigidity, is convenient for the flexible adjustment of the direction of the loading force, and achieves the loading of a big high-precision three-dimensional vector force.

Self-centering vector force loading device

The utility model provides a hanging test device employing a flexible fixed connection method, comprising a gantry, a force measuring assembly, a transition rack and a lateral adjusting mechanism. A force bearing plate is fixed on the lower end face at the top end of the gantry, the force measuring assembly comprises a loose flange, a spherical joint, a locking nut, a bidirectional screw rod and a thrust sensor, is arranged coaxially and is in coaxial connections with a to-be-tested engine via the transition rack, and the lateral adjusting mechanism is connected with a gantry upright column and a rear flange of the to-be-tested engine to adjust the central axis of the to-be-tested engine. The hanging test device of the utility model employs an axial and lateral flexible fixed connection method, can bear the thrust and side force generated during the process of simulating the heat run of the engine, and when a ground simulation test is carried out, utilizes a simulation shrinkage ratio engine to carry out an upright ignition test, at the same time, measures the parameters, such as thrust, pressure, gas jet temperature field, etc.

Hanging test device employing flexible fixed connection method

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Hanging test device employing flexible fixed connection method