Aircraft direct-current generator calibrator

Abstract

The utility model relates to the technical field of generator calibrators, and discloses an airplane direct current generator calibrator, which comprises a detector, a voltmeter group, direct current output positive and negative terminals and a detection self-holding switch, and is characterized in that the voltmeter group, the direct current output positive and negative terminals and the detection self-holding switch are respectively assembled on the front surface of the detector; a winding mechanism is assembled on the back face of the detector and comprises a transverse shaft, a torsional spring is connected between the transverse shaft and the detector, and a rotating disc is assembled on the back face of the transverse shaft. According to the airplane direct-current generator calibrator, the risk of airplane associated damage is avoided; the utility model provides an aircraft power supply system fault detection means, avoids the problem that the detection of a generator which is not easy to move is influenced because the existing detection device is large in size and is not convenient to carry, and avoids the problem that the aviation direct current cable is easy to be pulled by external personnel to cause unstable connection and poor reliability. And the problem that the aviation direct-current cable is easy to heat when being wound and stacked together is solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of generator calibrator, concretely is a kind of airplane direct-current generator calibrator. BACKGROUND

[0002] The working principle of airplane direct-current generator is based on Faraday's law of electromagnetic induction. When the rotor rotates, the magnetic field interacts with the stator coil, generating alternating current. The rectifier converts alternating current into direct current, which is then transmitted to the rotor coil through the brush, thereby outputting direct current;

[0003] After processing and producing, the airplane direct-current generator needs to be detected by a verification device. The existing airplane direct-current generator calibrator is large in size, which makes it difficult to detect the generator when it is not convenient to move. This causes delays in the detection of the generator. In addition, the external lines of the airplane direct-current generator calibrator are usually scattered outside the device, which causes the lines to accumulate and heat up when the calibrator is used, reducing its service life and making the connection unstable when the staff walks. UTILITY MODEL CONTENT

[0004] (I) Technical problem solved

[0005] To solve the technical problems of the existing calibrator, the utility model provides an airplane direct-current generator calibrator to solve the above technical problems. The calibrator is large in size, which makes it difficult to detect the generator when it is not convenient to move. This causes delays in the detection of the generator. In addition, the external lines of the airplane direct-current generator calibrator are usually scattered outside the device, which causes the lines to accumulate and heat up when the calibrator is used, reducing its service life and making the connection unstable when the staff walks.

[0006] (II) Technical solution

[0007] To achieve the above purpose, the utility model provides the following technical solution: an airplane direct-current generator calibrator, comprising: a detector, a voltmeter group, a direct-current output positive and negative terminal, and a detection self-protection switch, the voltmeter group, the direct-current output positive and negative terminal, and the detection self-protection switch are respectively assembled on the front of the detector, the back of the detector is equipped with a winding mechanism, the winding mechanism comprises a horizontal shaft, the horizontal shaft is connected with the detector through a torsion spring, the back of the horizontal shaft is equipped with a turntable, the outside of the turntable is connected with a winding roller, and a square groove is formed on the back of the turntable.

[0008] Preferably, the back of the detector is provided with an assembly groove, the assembly groove is connected with the horizontal shaft through a bearing with a seat, and the assembly groove is connected with a torsional spring, so that the horizontal shaft is conveniently assembled.

[0009] Preferably, the back of the detector is provided with an input port, the input port comprises an input opening, and notches are formed on both sides of the input opening, so that the external cable is conveniently connected with the detector, and the position of the turntable is conveniently locked through the T-shaped arm.

[0010] Preferably, the top of the winding roller is provided with a baffle disc, and the baffle disc comprises a disc, and a handle is arranged on the top of the disc, so that the staff can conveniently drive the turntable to rotate.

[0011] Preferably, T-shaped arms are arranged on both sides of the turntable, and the T-shaped arms are connected with the turntable through springs, so that the external cable can be conveniently inserted into the input port through the T-shaped arms and the springs, and the position of the turntable is fixed by extruding the T-shaped arms.

[0012] Preferably, the winding roller comprises a circular shaft, and a spiral groove is formed on the outer side of the circular shaft, so that the cable can be uniformly wound through the external spiral groove, and the cables are prevented from being wound together.

[0013] (Three) beneficial effects

[0014] Compared with the prior art, the aircraft DC generator calibrator has the following beneficial effects:

[0015] 1. The aircraft DC generator calibrator fills the blank of the aircraft DC generator without ground detection equipment, changes the mechanical transmission driving of the generator into DC power driving, realizes ground off-site detection, changes the previous generator test mode after assembly into a ground off-site test mode, avoids the risk of aircraft damage, and provides a fault detection means for the aircraft power supply system.

[0016] 2. The aircraft DC generator calibrator has the characteristics of compact structure and small size, facilitates the staff to take the device out for detection of the generator, avoids the problem that the existing detection device is too large to be conveniently carried, and thus affects the detection of the generator which is not easy to move.

[0017] 3. The aircraft DC generator calibrator is provided with a winding mechanism, which can quickly wind the aviation DC cable, adjust the position of the aviation DC cable, and automatically fix the position, so as to avoid unstable connection caused by external personnel pulling the aviation DC cable during use, and avoid the problem that the aviation DC cable is wound and stacked together, which causes easy heating during use. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 is a front view of the utility model;

[0019] Figure 2 is a back view of the utility model;

[0020] Figure 3 is a back view of the detector of the utility model;

[0021] Figure 4 is an external view of the winding mechanism of the utility model;

[0022] Figure 5 is an enlarged view of A of the utility model Figure 4 ;

[0023] Figure 6 is a circuit diagram of the utility model.

[0024] In the figure: 1, detector; 11, assembly groove; 12, input port; 2, voltmeter set; 3, DC output positive and negative terminals; 4, detection self-protection switch; 5, winding mechanism; 51, horizontal shaft; 52, torsional spring; 53, turntable; 54, winding roller; 55, square groove; 56, baffle disc; 57, T-shaped arm; 58, spring. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0026] The utility model provides a technical scheme, please refer to Figure 1 and Figure 2 , a kind of aircraft DC generator calibrator, comprising: detector 1, voltmeter set 2, DC output positive and negative terminals 3 and detection self-protection switch 4, voltmeter set 2, DC output positive and negative terminals 3 and detection self-protection switch 4 are respectively assembled in the front of detector 1, the back of detector 1 is equipped with winding mechanism 5, winding mechanism 5 includes horizontal shaft 51, torsional spring 52 is connected between horizontal shaft 51 and detector 1, the back of horizontal shaft 51 is equipped with turntable 53, and turntable 53 is externally connected with winding roller 54, and square groove 55 is set in the back of turntable 53.

[0027] The detector 1 can detect the generator of the airplane, the voltmeter set 2 can display the voltage data of the airplane generator, the DC output positive and negative terminals 3 can be connected with the detector 1 to output the current, the detection self-protection switch 4 can control the operation of the detector 1, the detector 1 is internally equipped with a fuse, and the detector 1 is internally equipped with a shunt, the voltmeter set 2 comprises a voltmeter and a current-voltage meter, and the voltmeter and the current-voltage meter are respectively arranged on both sides of the front face of the detector 1.

[0028] Please refer to Figure 3 and Figure 4 , the horizontal shaft 51 can drive the rotating disc 53 to rotate, the torsional spring 52 facilitates the rotating disc 53 to return after rotation, the winding roller 54 can wind the cable, the square groove 55 facilitates the plug of the cable to be connected with the input port 12, and simultaneously can fix the position of the rotating disc 53.

[0029] Please refer to Figure 5 and Figure 6 , wherein Figure 6 the in-circle label 1 is a power input end, the in-circle label 2 is a fuse, the in-circle label 3 is a power switch, the in-circle label 4 is a voltmeter, the in-circle label 5 is a detection switch, the in-circle label 6 is a current-voltage meter, the in-circle label 7 is a shunt, and the in-circle label 8 is a power output end, the back face of the detector 1 is provided with an assembly groove 11, the assembly groove 11 is connected with the horizontal shaft 51 through a bearing with a seat, and the assembly groove 11 is connected with the torsional spring 52, the assembly groove 11 facilitates the assembly of the horizontal shaft 51, the back face of the detector 1 is provided with an input port 12, the input port 12 comprises an input opening, slot openings are formed on both sides of the input opening, the input port 12 facilitates the external cable to be connected with the detector 1, and simultaneously facilitates the position of the rotating disc 53 to be locked by cooperating with the T-shaped arm 57.

[0030] The top of the winding roller 54 is equipped with a flapper 56, and the flapper 56 comprises a disc, the top of the disc is equipped with a crank handle, the flapper 56 facilitates the rotating disc 53 to be driven to rotate, the external two sides of the rotating disc 53 are respectively inserted with a T-shaped arm 57, and the T-shaped arm 57 is connected with the rotating disc 53 through a spring 58, the T-shaped arm 57 can facilitate the external cable to be inserted into the inside of the input port 12 by cooperating with the spring 58, the T-shaped arm 57 is pressed to fix the position of the rotating disc 53, the winding roller 54 comprises a circular shaft, a helical groove is formed on the outside of the circular shaft, the winding roller 54 can uniformly wind the cable through the external helical groove, and the cable is prevented from being wound together.

[0031] The aviation direct current cable wire of the scheme is assembled outside the winding roller 54, and the winding roller 54 is driven to rotate by the baffle disc 56, the length of the aviation direct current cable wire is adjusted to the length required for use, the plug at one end of the aviation direct current cable wire is inserted into the inside of the input port 12 through the square groove 55, the position of the rotating disc 53 is fixed by driving the T-shaped arm 57, the other end is connected with the generator, the inertia safety inside the detector 1 is realized by the input port 12 in series, the power supply protection of the equipment circuit and the generator is realized, the input voltage value whether conforming to the specified value is displayed by the self-protection door 4 and the voltmeter group 2 on the front of the detector 1, the input power supply is controlled by the self-protection door 4, the voltmeter group 2 and the direct current output positive and negative terminals 3 on the panel are connected through the current divider inside the equipment shell, the direct current output positive and negative terminals 3 are connected with the generator through the switching wire, the generator is driven to operate, the voltage value and the current value under the generator working state are displayed by the voltmeter group 2, whether the indication conforms to the specified standard is observed, whether the generator working and function are normal are judged, and the inspection work of the generator is completed in this way.

[0032] It should be noted that the relative terms, such as first and second, and the like, are used herein solely to distinguish one entity or action from another, without necessarily requiring or implying any such actual relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0033] Although the embodiments of the present application have been shown and described, it is to be understood that various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. An aircraft DC generator checker comprising: The utility model relates to a detector (1), voltmeter group (2), DC output positive and negative terminal (3) and detect self -preservation electric door (4), voltmeter group (2), DC output positive and negative terminal (3) and detect self -preservation electric door (4) are equipped respectively in the front of detector (1), it is characterized by: the back of detector (1) is equipped with winding mechanism (5), winding mechanism (5) includes horizontal shaft (51), and torsional spring (52) is connected between horizontal shaft (51) and detector (1), the back of horizontal shaft (51) is equipped with carousel (53), the outside of carousel (53) is connected with winding roller (54), and the back of carousel (53) is equipped with square groove (55).

2. An aircraft DC generator checker according to claim 1, characterised in that: The back of the detector (1) is provided with an assembly groove (11), the assembly groove (11) is connected with the horizontal shaft (51) through a bearing with a seat, and the assembly groove (11) is connected with the torsional spring (52).

3. An aircraft DC generator checker according to claim 1, wherein: The back of the detector (1) is provided with an input port (12), the input port (12) includes an input port, and the input port is provided with a slot on both sides.

4. An aircraft DC generator checker according to claim 1, wherein: The top of the winding roller (54) is provided with a flapper (56), and the flapper (56) includes a disc, and the top of the disc is provided with a crank.

5. An aircraft DC generator checker according to claim 1, wherein: The outside of the carousel (53) is provided with a T-shaped arm (57) on both sides, and the T-shaped arm (57) is connected with the carousel (53) through a spring (58).

6. An aircraft DC generator checker according to claim 1, wherein: The winding roller (54) includes a circular shaft, and the outer part of the circular shaft is provided with a spiral groove.

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