A force arm adjustment control device for aircraft structure strength test
A strength test and aircraft structure technology, applied in computer control, general control system, program control, etc., can solve problems such as failure to proceed smoothly, lack of control equipment, and inability to coordinate the use of loading systems to achieve the effect of improving loading efficiency
Active Publication Date: 2022-05-17
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology
[0003] Since the current testing machine only has the communication mechanism of the arm adjuster and no corresponding control equipment, similar tests cannot be carried out smoothly, and other current arm adjustment control devices cannot be used in conjunction with the coordinated loading system of the aircraft structural strength test
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specific Embodiment approach
[0019] A specific embodiment of the present invention is: an arm adjustment control device for aircraft structural strength test, the device includes a signal input module 1, a signal conversion module 2, a comparison voltage V1 module 3, a comparison voltage V2 module 4, Comparing circuit 5, display module 6 and control circuit 8. Terminal 1 of the signal input module is connected to the control device, and terminal 8 of the control loop is connected to the control motor of the arm. The servo control current signal in the control device is connected to the signal input module 1, and the input current signal is converted into a variable voltage signal V by the resistor Ri in the signal conversion module 2. Comparator circuit 5 includes a comparator LM339 and six inverters (4069), and a valve voltage is set at pin 7 and pin 4 of the comparator LM339 respectively, and as figure 1 Connect the comparison voltage V1 module 3 and the comparison voltage V2 module 4, adjust the Rc of...
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The present invention proposes a force arm adjustment control device for aircraft structure strength test, which belongs to the technical field of force arm control for strength test; the device of the present invention includes a signal input module, a signal conversion module, a comparison voltage V1 module, a comparison voltage V2 module, The comparison circuit, the display module and the control circuit for controlling the arm motor, one end of the signal conversion module is connected to the signal input module, the other end of the signal conversion module is connected to the input end of the comparison circuit, the comparison voltage V1 module and the comparison voltage V2 module are connected to the comparison circuit The input terminal of the comparison circuit is connected to the display module and the control circuit; the present invention solves the problem that the current arm adjustment control device cannot be used in conjunction with the coordinated loading system of the aircraft structural strength test, and the arm adjustment control device can make the aircraft The arm adjustment control process in the structural strength test is more intuitive and clear, and the function of automatically adjusting the arm is realized.
Description
technical field [0001] The invention belongs to a force arm adjustment control device, in particular to a force arm adjustment control device used for an aircraft structure strength test. Background technique [0002] In the aircraft structural strength test, some tests require the state of the aircraft arm adjustment device to be controlled. The specific requirement is to control the arm adjustment device in different states according to different test load spectra. For example, in some working conditions, it is required The control arms are respectively the states of large force arm (100mm), medium force arm (80mm), medium force arm (70mm), and small force arm (60mm). [0003] Since the current testing machine only has the communication mechanism of the arm adjuster and no corresponding control equipment, similar tests cannot be carried out smoothly, and other current arm adjustment control devices cannot be used in conjunction with the coordinated loading system of the ai...
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IPC IPC(8): G05B19/042
CPCG05B19/0423G05B2219/24215
Inventor 李宏亮张革命张宁冯璐雯吝继锋
Owner CHINA AIRPLANT STRENGTH RES INST