CN216954548U

CN216954548U - Aviation attitude sensor test auxiliary installer

Info

Publication number: CN216954548U
Application number: CN202220656467.1U
Authority: CN
Inventors: 赵焕玲
Original assignee: Guizhou Open University Guizhou Vocational And Technical College
Current assignee: Guizhou Open University Guizhou Vocational And Technical College
Priority date: 2022-03-24
Filing date: 2022-03-24
Publication date: 2022-07-12
Anticipated expiration: 2032-03-24

Abstract

The utility model relates to the field of testing tools and discloses an aviation attitude sensor testing auxiliary installer which comprises a rack and a trapezoidal gear transmission mechanism arranged on the rack, wherein the trapezoidal gear transmission mechanism consists of a gear shaft, sliding blocks and a motor, the two ends of the gear shaft are respectively provided with one sliding block, the middle part of the gear shaft is provided with a coaxial gear which is in meshing transmission with the output end of the motor, and the rack is provided with a sliding chute in sliding fit with the sliding blocks. The test auxiliary installer for the aviation attitude sensor drives the trapezoidal gear transmission mechanism through the motor, so that the left-handed threads and the right-handed threads at two ends of the gear shaft drive the sliding blocks to slide in the sliding grooves of the rack oppositely to grab, and otherwise, the sliding blocks are loosened, so that the functions of automatic grabbing and loosening are realized, the test auxiliary installer is convenient to operate, and the efficiency is improved.

Description

Aviation attitude sensor test auxiliary installer

Technical Field

The utility model belongs to the field of testing tools, and relates to an auxiliary installer for testing an aviation attitude sensor.

Background

In engineering practice, the aviation attitude sensor needs to be installed in an annular testing base, the structure of the aviation attitude sensor 2 and the annular testing base 1 after installation is shown in detail in fig. 1 and fig. 2, the installation accuracy is that the inner cylindrical surface of the annular installation base is in clearance fit with the outer cylindrical surface of the aviation attitude sensor, the fit tolerance is H7/H7, the installation reference requirement of the cylindrical surface is high, the clearance is small, the fit height H (namely the thickness of the aviation attitude sensor) of the installation cylindrical surface exceeds 100mm, and the installation depth is 90 mm. When using artifical direct mount, because aviation attitude sensor is heavier, the product of taking is difficult, when putting into annular test base simultaneously, and clearance between them is less, leads to hand activity space little, and easy bruising installs the difficulty, inefficiency. Still because both cooperation face of cylinder highly apart from longer, at the installation with take out the in-process, easily with aviation attitude sensor card in annular test base, cause aviation attitude sensor damage fitting surface precision and unable normal use. Therefore, an auxiliary mounting device is needed, which is simple and reliable by visually checking the matching condition so as to place (or take out) the aviation attitude sensor into the annular testing base.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model aims to provide an auxiliary installer for testing an aviation attitude sensor, which is reasonable in structure and convenient to operate, and aims to solve the problems that the aviation attitude sensor is difficult to put in or take out of an annular testing base, low in efficiency and easy to damage the precision of a matching surface.

In order to achieve the purpose, the utility model provides the following technical scheme:

the utility model provides an auxiliary installer for testing an aviation attitude sensor, which comprises a rack and a trapezoidal gear transmission mechanism arranged on the rack, wherein the trapezoidal gear transmission mechanism consists of a gear shaft, sliders and a motor, the two ends of the gear shaft are respectively provided with one slider, the middle part of the gear shaft is provided with a coaxial gear which is in meshing transmission with the output end of the motor, and the rack is provided with a sliding chute in sliding fit with the sliders.

Further, two trunnions which are arranged side by side are arranged on the rack.

Further, the lower end of the slide block is provided with a hook part extending inwards

Furthermore, the bottom of the frame and other side surfaces except the side where the sliding block is located are provided with weight-reducing through holes.

Furthermore, the two ends of the gear shaft are respectively provided with a left-handed thread and a right-handed thread.

Further, the motor is a torque motor.

Further, the coaxial gear is a trapezoidal gear.

Furthermore, the trapezoidal gear transmission mechanism also comprises a key switch, a contact switch and a direct current power supply, wherein the direct current power supply is electrically connected with the key switch, the contact switch and the motor, and the contact switch is arranged corresponding to at least one sliding block.

The utility model has the technical effects that:

1. the test auxiliary installer for the aviation attitude sensor drives the trapezoidal gear transmission mechanism through the direct-current torque motor, not only is convenient to operate, but also ensures the required torque, and left-handed and right-handed threads at two ends of the gear shaft drive the sliding block to slide in the sliding chute of the frame in the opposite direction; and the reverse driving switch reversely drives the direct-current torque motor to reversely rotate, the left-handed thread and the right-handed thread at the two ends of the gear shaft drive the two sliding blocks to reversely keep away from sliding, and the grabbed column body is loosened, so that the functions of automatic grabbing and loosening are realized, the operation is convenient, and the efficiency is improved.

2. The auxiliary installer for testing the aviation attitude sensor is extracted through the trunnion of the rack, and can effectively observe the matching condition of the aviation attitude sensor and the annular testing base, avoid the occurrence of clamping stagnation faults in the installation process and improve the installation efficiency; the aviation attitude sensor is grabbed and loosened through the sliding block, so that the aviation attitude sensor can be installed in a small gap which is inaccessible to a hand, and the accident of collision and injury caused by the movement of the hand in a narrow space is avoided; and can conveniently look over the cooperation condition of aviation attitude sensor and annular survey base through visualing, convenient installation. Meanwhile, the design scheme is also suitable for the installation application scene of the annular test base of other products similar to the aviation attitude sensor.

Additional advantages, objects, and features of the utility model will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the utility model. The objectives and other advantages of the utility model may be realized and attained by the means of the instrumentalities and combinations particularly pointed out hereinafter.

Drawings

For the purposes of promoting a better understanding of the objects, aspects and advantages of the utility model, reference will now be made to the following detailed description taken in conjunction with the accompanying drawings in which:

FIG. 1 is a schematic plan view of a prior art aero-attitude sensor mounted with an annular test base;

FIG. 2 is an axial perspective schematic view of FIG. 1;

FIG. 3 is a schematic overall plan view of an auxiliary installer for testing an aviation attitude sensor according to the present invention;

FIG. 4 is a schematic front view of the structure of FIG. 3;

FIG. 5 is a side view of the housing of FIG. 3;

FIG. 6 is a schematic diagram of a trapezoidal gear transmission mechanism of the auxiliary installer for testing the aviation attitude sensor of the present invention;

FIG. 7 is a control circuit diagram of the trapezoidal gear drive of FIG. 6;

FIG. 8 is a schematic top view of an aerospace attitude sensor test accessory mounter of the present invention in grabbing a product;

FIG. 9 is a schematic front perspective view of FIG. 8;

reference numerals: annular test base 1, aviation attitude sensor 2, frame 3, spout 4, slider 5, motor 6, gear shaft 7, coaxial gear 8, key switch 9, contact switch 10, DC power supply 11, through-hole 12, trunnion 13, hook portion 14.

Detailed Description

The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The utility model is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention in a schematic way, and the features in the following embodiments and examples may be combined with each other without conflict.

Wherein the showings are for the purpose of illustration only and are shown by way of illustration only and not in actual form, and are not to be construed as limiting the present patent; to better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted. Furthermore, the present invention may repeat reference numerals and/or letters in the various examples. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed.

As shown in fig. 3-7, the aviation attitude sensor test auxiliary mounter according to the embodiment includes a rack 3, a trapezoidal gear transmission mechanism is detachably mounted on the rack 3, the trapezoidal gear transmission mechanism is composed of a gear shaft 7, a slider 5, a motor 6, a key switch 9, a contact switch 10 and a dc power supply 11, two sliders 5 are respectively disposed at two ends of the gear shaft 7, a coaxial gear 8 meshed with an output end of the motor 6 for transmission is disposed at the middle of the gear shaft 7, a sliding chute 4 in sliding fit with the slider 5 is disposed on the rack 3, the dc power supply 11 is electrically connected with the key switch 9, the contact switch 10 and the motor 6, and at least one contact switch 10 is disposed to correspond to the slider 5.

In this embodiment, the two ends of the gear shaft 7 are respectively provided with left-handed and right-handed threads to drive the sliding blocks 5 at the two ends to move in the sliding slot 4 of the frame 3 in opposite directions, the middle part is a coaxial gear 8 with a trapezoidal structure, and the coaxial gear and a driving gear (not marked) arranged on the output shaft of the motor 6 form a gear transmission pair.

The motor 6 in this embodiment is a dc torque motor, and the motor, the dc power supply, the key switch and the contact switch are all fixed to the frame by screws. The action relationship is as follows: after the direct-current torque motor, the direct-current power supply and the key switch are fixed in a rack mounting hole, the contact switch 10 is mounted by taking the mounting edge of the aviation attitude sensor 2 as a reference, then the electric welding is carried out according to a graph 7, and then the two sliding blocks 5 are mounted at two ends of a gear shaft 7 according to a graph 6.

Frame 3 in this embodiment is formed through aluminum alloy casting processing, and light in weight simultaneously, can all set up at the bottom of frame 3 and remove on other sides of slider 5 place side and subtract heavy through-hole 12, the upper end is two trunnion 13 of arranging side by side as the handle, both ends processing spout 4, spout 4 snatchs the size design spacing according to the product, after installation slider 5, two axial positioning to slider 5 simultaneously, make slider 5 only can slide in a direction, simultaneously, guarantee reliably to snatch fixed product. In order to further guarantee stable grabbing, the lower end of the slidable block 5 is provided with a hook part 14 extending inwards to be matched with the shape of a product.

The installation description of the auxiliary installer for testing the aviation attitude sensor is as follows: firstly, a contact switch 10 is arranged on a frame 3 according to the product grabbing size; then the gear shaft 7 is inserted into the frame 3, the two sliding blocks 5 are respectively installed at the two ends of the gear shaft 7 and slide into the sliding grooves 4 of the frame 3, namely the protruding parts at the two sides of the sliding blocks 5 are aligned with the sliding grooves 4 of the frame 3, then the gear shaft 7 is rotated to enable the protruding parts of the two sliding blocks 5 to simultaneously slide in opposite directions in the corresponding sliding grooves 4 of the frame until the edges of the sliding blocks 5 contact the contacts of the contact switch 10; then a motor 6 with a driving gear is arranged on the frame 3, and the driving gear is meshed with a trapezoidal coaxial gear 8 in the middle of a gear shaft 7 to form a gear pair; then, a direct current torque motor is installed and fixed on the rack by using an installation screw assembly; and then the key switch 9 and the direct current power supply 11 are fixed on the frame 3 by screws, and the direct current power supply 11, the motor 6, the contact switch 10 and the key switch 9 are electrically connected by cables.

As shown in fig. 8-9, when the aviation attitude sensor needs to be grabbed, the rack is placed on the aviation attitude sensor 2 (product), the button "D" button of the key switch is pressed to switch on the power supply of the direct-current torque motor, the direct-current power supply supplies forward current to the motor, the trapezoidal gear transmission mechanism is driven by the direct-current torque motor, the output torque drives the gear shaft to slowly rotate so as to drive the sliders installed on the two ends of the rack to move oppositely, after the installation part on each slider reliably contacts the side face of the aviation attitude sensor, each slider touches the contact switch to switch off the power supply, and the slider is switched on reversely, at the moment, the installation part of each slider is reliably fixed with the aviation attitude sensor, and then the aviation attitude sensor is extracted through the trunnion on the rack and is conveniently and reliably installed in the annular test base 1. After the product is installed and fixed on the annular test base, a key switch R button is pressed down, a reverse power supply is switched on, reverse current is supplied to a motor, a trapezoidal gear transmission mechanism is driven by a direct current torque motor, an output torque drives a gear shaft to slowly rotate so as to drive sliding blocks installed on two ends of a rack to move in the reverse direction, the product is loosened, when an installation part on the sliding block is separated from the product and leaves the side surface of the aviation attitude sensor, a key switch S button is pressed down, a power switch is switched off, and the aviation attitude sensor test auxiliary installer is taken out. Like this, can conveniently put into or take out aviation attitude sensor from annular test base, use the gudgeon in the frame to draw aviation attitude sensor, convenient operation avoids the hand to bump the accident, and motor drive is automatic spacing promptly reliably, simultaneously, observes the installation of aviation attitude sensor in annular base easily, effectively avoids aviation attitude sensor in annular test base jamming, reduces the risk of product damage, improves the installation effectiveness simultaneously.

Finally, the above embodiments are only intended to illustrate the technical solutions of the present invention and not to limit the present invention, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions, and all of them should be covered by the claims of the present invention.

Claims

1. The utility model provides an aviation attitude sensor test auxiliary installer, includes frame (3), its characterized in that, still includes the trapezoidal gear drive mechanism who sets up in the frame, trapezoidal gear drive mechanism comprises gear shaft (7), slider (5), motor (6), respectively set up slider (5) on the both ends of gear shaft, the middle part of gear shaft sets up with motor output end meshing driven coaxial gear (8), set up in the frame with slider sliding fit's spout (4).

2. The aeronautical attitude sensor test auxiliary installer according to claim 1, characterized in that said frame is provided with two trunnions (13) arranged side by side.

3. The aeronautical attitude sensor test auxiliary installer according to claim 1, characterized in that the lower end of the slider is provided with an inwardly extending hook (14).

4. The test auxiliary installer of the aviation attitude sensor according to claim 1, wherein the bottom of the rack and other side surfaces except the side where the sliding block is located are provided with weight-reducing through holes (12).

5. The aided installer of claim 1, wherein the two ends of the gear shaft are left and right threads.

6. The aeronautical attitude sensor test-aided installer of claim 1, wherein the motor is a torque motor.

7. The aeronautical attitude sensor test-assisted installer of claim 1, wherein the coaxial gear is a trapezoidal gear.

8. The aviation attitude sensor test auxiliary installer as claimed in any one of claims 1 to 7, wherein the trapezoidal gear transmission mechanism further comprises a key switch (9), a contact switch (10) and a DC power supply (11), the DC power supply is electrically connected with the key switch, the contact switch and the motor, and the contact switch is arranged corresponding to at least one slider.