Method of testing spacecraft multi-member mechanical system for functioning and device for realization of this method

FIELD: testing technology; testing of multi-member mechanical systems for functioning during ground optimization of structures.

SUBSTANCE: proposed method includes securing of each member of mechanical system to respective section of beam system supporting the mechanical system by means of adjustable springs for opening of mechanical system in vertical plane. Then, members of mechanical system are unweighed through adjustment of springs and each member of mechanical system is rigidly connected with respective section of beam system. Tests are conducted at simultaneous opening of members of multi-member mechanical system and section of beam system, thus checking the mechanical system for proper functioning. Device proposed for realization of this method is made in form of ring secured in upper part of spacecraft and provided with sectionalized swivel rods. Sections of sectionalized swivel rods are located in plan above respective members of multi-member mechanical system and are connected with them by means of adjustable unweighing springs and adjustable rods consisting of bars and bushes. Adjustable rods are located symmetrically on both sides from respective adjustable unweighing spring.

EFFECT: enhanced accuracy of test results; possibility of keeping multi-member system intact.

4 cl, 6 dwg

 

The invention relates to a method of testing multi-link mechanical systems, primarily spacecraft on the functioning and devices for their implementation and can be used in missile and space technology when conducting ground tests of spacecraft designs.

A known method of testing multi-link mechanical system of the spacecraft on the functioning (see Product F. The instruction on transportation and congestion. Part 2. Transportation and congestion on TFI, part 2, revision 1, 4 KB "Flight", 2001), according to which the space vehicle, comprising a housing with a fixed and fixed it in the folded position multilink solar panels, equipped with actuators of disclosure, is installed vertically on the stand obespechivaniya and produce an exhibition of the axis of rotation of each solar panel in a vertical plane by means of a plumb (plumbing axes of rotation). Then make securing each panel solar battery to regulated springs obespechivaniya and by adjusting efforts tension last (solar panels Rashkovan and are in the open state), restore the length of each adjustable springs obespechivaniya obtained by weighting each panel and solar battery (when determining its actual weight). As a result of these operations, the upper ends of the links, multi-link mechanical system (in this case, solar panels for spacecraft are placed in the horizontal plane. After that make consistent the disclosure of solar panels at a nominal value of efforts to drive their disclosure.

There is also known a method of testing multi-link mechanical system of the spacecraft on the functioning (see UDC-355.242. "Development of the military-industrial complex at the present stage", materials of the scientific-technical conference, Omsk, Omsk state University publishing, 2003, str-140), namely, that on the upper part of the spacecraft containing multi-link mechanical system (e.g., multi-tiered solar panel), equipped with actuators disclosure, fixed beam system made in the form of technological rings, equipped with a sectional rotary rods, each section of which is placed in the plan over the appropriate level of multibody mechanical systems, to the sections of the sectional rotary rods are fixed adjustable spring obespechivaniya links, multi-link mechanical system space apparatus and by adjusting their efforts tension expose the upper ends of the links of the multilink of the mechanical system to the economic unit in a horizontal plane (when unfolded links, multi-link mechanical system), then fold the parts of the multi-link mechanical system to its original position, fix them in this position for a space system, and then tests the functioning of multibody mechanical systems of the spacecraft (sequential exposure of its links) using the efforts generated by the actuators disclosure.

The disadvantage of this method of testing multi-link mechanical system of the spacecraft to the operation is that when the joint disclosure of multibody mechanical systems of the spacecraft and beam system, due to the presence between them of only elastic connection in the form of adjustable springs obespechivaniya disclosed system is not hard. Thus there is an abrupt (non-synchronous) moving the deployable elements. After the submission of the Manager's efforts to drive the disclosure of each link of the multi-link mechanical systems this link moves, adjustable spring obespechivaniya stretched, thus increasing braking effect on the disclosed link multi-link mechanical system from the action of the adjustable spring obespechivaniya, the speed of movement of the deployable element of multibody mechanical system is reduced. Upon reaching a certain efforts adjustable spring obespechivaniya pulls own the th corresponding section beam system, which, moving with increasing speed, catching up and having high inertia, ahead of an expandable link multi-link mechanical system of the spacecraft. Thus, there is an abrupt (rescourse) non-synchronous reciprocal movement of the deployable element of multibody mechanical systems of the spacecraft and the corresponding section of the sectional rotary rods. The dynamics of disclosure of multibody mechanical systems for bench testing (ground tests) does not correspond to the real conditions of disclosure of multibody mechanical systems of a spacecraft in space and may not give a reliable confirmation of the standard disclosures in the conditions of real operation. In addition, in the process of testing the disclosure of possible damage to the elements of the disclosed multi-link mechanical system. Execution sectional rotary rods of rectangular shape in the apparatus of the present method of testing multi-link mechanical system of the spacecraft on the functioning, leads to inefficient allocation and increase in the mass breakout of the rotary rod. This, in turn, leads to increasing load on the actuator opening links in multi-link mechanical system, which shall have a minimum capacity, so how in the weightlessness of outer space.

Objective (purpose) of the proposed method of testing multi-link mechanical system of the spacecraft on the functioning and device for its implementation is the reduction of dynamic inertial loads on the design of multibody mechanical systems and actuators disclosed in the process of testing by providing synchronous movement of the links of the multi-link mechanical system of the spacecraft and the relevant sections of the sectional rotary rods.

The goal in the proposed method of testing multi-link mechanical system of the spacecraft on the functioning of the device for its implementation is achieved by providing (after adjusting the tension of each adjustable springs obespechivaniya) hard links of each link of multibody mechanical systems with corresponding section of the sectional rotary rod and the subsequent joint disclosure of each link of the multi-link mechanical system of the spacecraft and the corresponding section of the sectional rotary rod as a whole, i.e. as a rigid structure. The formation of rigid construction is achieved by assigning each partition sectional rotary rods according to the corresponding link of the multi-link mechanical system by means of adjustable rods, each of which consists of a shaft and sleeve, the rods are placed in the sleeve and contact them via threaded connections and clamps position, and the sleeve is fixed to the sections of the sectional rotatable rods, and the rods are fixed on the respective links of the multi-link mechanical system, with adjustable ties placed symmetrically on both sides of the respective adjustable spring obespechivaniya. Symmetrical placement of two adjustable rods relative to the adjustable spring obespechivaniya allows obtusity each link of the multi-link mechanical system resultant force passing through the center of mass of link multi-link mechanical system.

To create ravnopolochny design sections sectional rotary rod beam system with minimum mass that meets the requirements of strength, each section of the sectional rotary rod is of variable cross-section, namely, a trapezoidal shape in projection on a vertical plane with the vertical location of the bases of the trapezoid. The height of the bases of the trapezoidal sections sectional rotary rods from the section most remote (unfolded) from technological ring section, the least remote from technological rings, is increasing proporzionale ordinal partition sectional rotary rod (links, multi-link mechanical system). When proportional change in height of the bases of the trapezoidal sections of the upper side of the trapezoid of each section of the sectional rotary rods are arranged in the same inclined plane, and the lower side of the trapezoid of each section of the sectional rotary rods are arranged in the same horizontal plane.

To reduce the mass-inertial characteristics of the sections of the sectional rotary rod, and to reduce loads on the actuators disclosure of multibody mechanical systems in the partitions are open (cut).

A device that implements the proposed method of testing multi-link mechanical system of the spacecraft to the function presented in figure 1-6.

Figure 1 presents a General view of the proposed device in the process of opening links in multi-link mechanical system of the spacecraft.

Figure 2 shows a top view of the proposed device in the folded position of the sections of the sectional rotary rods and links, multi-link mechanical system of the spacecraft.

Figure 3 shows a top view of the proposed device when unfolded sections sectional rotary rods and links, multi-link mechanical system of the spacecraft.

Figure 4 presents the extension element I according to figure 1.

Figure 5 shows azres a-a according to Fig 1.

Figure 6 shows the calculated scheme of loading sections sectional rotary rods.

The device for realization of the proposed method of testing multi-link mechanical system of the spacecraft on the operation consists of a beam system 1 (figure 1), made in the form of technological rings 2, mounted in the upper part of the spacecraft 3 and provided with a sectional rotary rod 4. Each section 5 sectional rotary rod 4 is placed in the plan on the relevant link 6 (1, 2) multi-link mechanical system 7 spacecraft 3 and connected with it by means of an adjustable spring obespechivaniya 8 (1) and two adjustable rods 9. Each of the adjustable rod 9 consists of a shaft 10 (figure 4) and bushing 11. The rods 10 are arranged in the sleeves 11 and connected with them by means of threaded connections and clamps provisions 12 (figure 4). Sleeve 11 attached (attachment elements on the drawings conventionally not shown) in sections 5 sectional rotary rod 4, and the rods 10 secured (mounting on the drawings conventionally not shown) on the respective links 6 of multibody mechanical system 7. Adjustable ties 9 are symmetric (figure 1) on both sides of the respective adjustable spring obespechivaniya 8. Section 5 sectional rotary rod 4 in the projection on the vertical plane and out the shape of a trapezoid with a vertical location of their bases 13 and 14 (6), and the upper side 15 of the line are in the same inclined plane. The height of the bases 13 and 14 (trapezoidal) sections 5 sectional rotary rod 4 is determined by the number of units 6 (disclosed) multi-link mechanical system 7 and increases from section 5, the most remote (unfolded) from technological rings 2, section 5, the least remote (unfolded) from the process of ring 2, is proportional to the ordinal number of the section 5 (of 6 links multi-link mechanical system 7). For example, for multi-link mechanical system 7 consisting of n links 6, the ratio of the heights of the corresponding bases 13 or 14 of the trapezoid adjacent sections 5 sectional rotary rod 4 in the direction from section 5, the most remote (unfolded) from technological rings 2, section 5, the least remote (unfolded) from the process of ring 2, is defined as 1:2:3:...:(n-1):n.

It should be noted that the ratio of the heights of the bases 13 or 14 of the trapezoidal sections 5 sectional rotary rod 4 obtained from using them for obespechivaniya of multibody mechanical system 7, in which the mass and length (and hence the length of the sections 5 a sectional rotary rod 4) of each of its links 6 are the same (this condition is satisfied in most of the existing and developed the multi-link mechanical systems).

Considered the condition of the sectional strength of the rotary rod 4 as cantilever beams with bending - the main type of their deformation when obespechivanie of multibody mechanical systems 7. The vertical cross-section of each section 5 sectional rotary rod 4 was seen as a box-shaped (closed) sections, namely: two shelves 16 and 17 (figure 5), United the two (vertical thin) walls 18. This form of cross-section has the greatest relative stiffness in bending and torsion) with minimum weight.

The load on the (i-th) section 5 of the sectional rotary rod 4 in the equilibrium position of multibody mechanical systems 7, mounted on the technological ring 2, is determined by the weight and number of links 6, secured to the sections 5 a sectional rotary rod 4 to the (i-th) of section 5 and level 6 directly fixed to this section 5.

The total bending moment acting in the vertical section of the i-th section 5 (in the section on the base 14), is equal to:

where M1, M2, M3- bending moments from the 1st, 2nd, 3rd, etc. links 6 of multibody mechanical systems 7 (adopted numbering is calculated from the most remote (unfolded) from spacecraft 3 link 6 to the least remote (RA is the indoor position) from spacecraft 3 link 6).

In the expression (1):

After substitution of expressions (2) in equation (1) with respect for the equal mass m and length L of all the links 6 to the total bending moment Mthe i-th section 5 turns ratio:

where K1is the coefficient of proportionality.

In relations (2) and (3) the following notation:

m is the mass of one (each) level 6 of multibody mechanical systems 7 kg;

g=9,81 m/s2- free fall acceleration;

L is the length of each link 6 of multibody mechanical systems 7, m;

i is the number (integer natural number) of section 5 of the sectional rotary rod 4 corresponds to the number of discharging sections 6 of multibody mechanical systems 7 (i=1, 2, ..., n-1, n - adopted numbering from the most remote section 5 from the technological ring 2 to the least remote partition 5 from the tech rings 2);

n is the total number of links 6 in the composition of the whole multi-link mechanical system 7 (respectively the total number of sections 5 sectional rotary rod 4).

From the analysis of expression (3) implies that the magnitude of the maximum bending moment acting in the vertical section of the i-th section 5 (in the section on the base 14), is directly proportional to the number of links 6 of multibody mechanical si themes 7, the loading of the i-th section 5. It should be noted that the number of links 6 of multibody mechanical system 7, the loading of the i-th section 5, coincides with its sequence number i.

So, for example, for a vertical cross-section (cross-section on the basis of 14) of section 5, the least remote from the process of ring 2, when obespechivanie of multibody mechanical system 7 consisting of n links 6, the maximum bending moment is:

At the conclusion of the expressions (3) and (4) were not taken into account its own weight sections 5 sectional rotary rod 4, and the fixing parts 6 of multibody mechanical system 7 to sections 5 sectional rotary rod 4 to simplify taken in the middle of the span L for each link 6.

The moment of resistance W (m3) curve for a beam of a closed box-shaped (rectangular) cross-section is directly proportional to the square of the section height H (m) beam (see, for example, Academy, etc, Handbook of strength of materials", Kiev, "Naukova Dumka", 1988, p.36-37):

where K2is the coefficient of proportionality.

From the condition of ravnopravnosti sections 5 sectional rotary rod 4 when applying them to obespechivaniya of multibody mechanical system 7 with different number of links 6, which is a known value when the bending of the beams are:

where K - coefficient of proportionality,

should the proportional dependence of the height H of the vertical cross-sections of sections 5 sectional rotary rod 4 (heights of the bases 13 or 14 adjacent trapezoidal sections 5) the serial number i (ordinal links 6 of multibody mechanical system 7).

In the expression (6):

σ - the current maximum bending stress in the considered (i-th) of section 5 (in its section on the basis of 14);

σb- tensile strength when the material is bent sections 5 sectional rotary rod 4.

Thus, in accordance with equation (3) to reduce the mass breakout of the rotary rod 4 by distributing the weight between the sections 5 of the last made in the form of box beams (closed) cross-section with variable height. Thus the projection of each section on a vertical plane is a trapezoid with height (vertical) bases 13 or 14 contiguous sections 5 sectional rotary rod 4, increasing in the direction of technological ring is proportional to the ordinal number of the section 5 (numbering of sections 5 adopted from the most remote from technological rings 2 of section 5 to the least remote from the tech rings 2 of section 5).

Normally, the estimated error in the determination of the mass-inertia features the links to 6 multi-link mechanical system 7 (and multi-link mechanical system 7 in General) is ± 10% from the nominal value. Given this variation are selected actuators disclosure (in the drawing conventionally not shown) of 6 links multi-link mechanical system 7 with the corresponding power characteristics (capacity, effort, disclosure and so on). Since the actuators disclosure is simultaneous (synchronous with opening parts 6 of multibody mechanical system 7) disclosure sections 5 sectional rotary rod 4, in order to reduce the required drive power erection when conducting ground tests sectional rotary rod 4 are structurally with a minimum mass-inertial characteristics, in practice, components of 15-20% from the corresponding mass-inertial characteristics of multibody mechanical systems 7.

In order to limit mechanical stress (loads) on drives of disclosure (in the drawing conventionally not shown), reduce inertial effects from the sectional rotary rod 4 on the iterative mechanical system 7 by reducing the weight of the sections 5 in the walls of the last 18 holes of the perforation (window, cut) 19.

Implementation of the proposed method of testing multi-link mechanical system 7 spacecraft 3 proposed device occurs in the following process sequence:

space AP is Arat 3 with fixed and fixed it in the folded position of multibody mechanical system 7 is installed in a vertical position on a technological stand 20 (1);

on the upper part of the spacecraft 3 establish and fix beam system 1 (Fig 1);

- each link 6 of multibody mechanical systems 7 spacecraft 3 is fixed by means of adjustable springs obespechivaniya 8 to the corresponding section 5 sectional rotary rod 4 beam system 1;

- carry out the adjustment of the tension of each adjustable springs obespechivaniya 8 (when unfolded links 6 of multibody mechanical system 7) with software install the upper ends 21 (1, 4) links 6 of multibody mechanical system 7 in a horizontal plane;

- carry out the installation of adjustable rods 9 (Fig 1) with the provision of attachment (figure 4) their sleeves 11 in sections 5 sectional rotary rod 4 and rods 10 on relevant parts 6 of multibody mechanical systems 7;

- by adjusting the rods 10 in the threaded bushing 11 adjustable thrust 9 put on exactly the same length as the length of the pre-exposed adjustable spring obespechivaniya 8 (the distance between the upper end face 21 (Fig 1, 4) level 6 of multibody mechanical system 7 and the bottom end 22 (Fig 1, 4) corresponding section 5 sectional rotary rod 4 is defined (determined) by the setting of adjustable springs obespechivaniya 8 terms and conditions provide the necessary obespechivaniya, posleduyuschego and adjustment of the adjustable rod 9 does not need to change this distance);

- fix the mutual position of the rods 10 in the sleeve 11 (the length of the adjustable rod 9) by means of securing provisions 12 (figure 4);

- close (turn off) the links 6 of multibody mechanical system 7 to its original position and fix (fixation on the drawing conventionally not shown) on the spacecraft 3;

- produce unfixing (fixation on the drawing conventionally not shown) and consistent disclosure (1, 3) links 6 of multibody mechanical system 7 into position using their drives disclosure (in the drawing conventionally not shown);

- close (turn off) the links 6 of multibody mechanical system 7 to its original position and fix (fixation on the drawing conventionally not shown) on the spacecraft 3.

Disassembly of the device is realized in the following process sequence:

- respexit relative position of the rods 10 in the sleeve 11 (the length of the adjustable rod 9) the abstraction of securing provisions 12;

- carry out dismantling adjustable rod 9 with the release of their rods 10 from 6 links multi-link mechanical system 7 and the bushing 11 from the respective sections 5 sectional rotary rod 4;

- carry out dismantling adjustable spring obespechivaniya 8;

- carry out dismantling beam system 1 with spacecraft 3.

With the exception of the sequential opening of 6 links multi-link mechanical system 7 into position using their drives disclosure (in the drawing conventionally not shown) of adjustable rods 9 provides a rigid mount links 6 of multibody mechanical system 7 to the corresponding sections 5 sectional rotary rod 4, resulting in simultaneous reciprocal movement of the deployable elements. This eliminates the effect of "rocking" on adjustable springs obespechivaniya 8 6 links multi-link mechanical system 7 when their disclosure in the testing process.

Implementation of sections 5 sectional rotary rod 4 variable cross-section of a trapezoidal shape in projection on a vertical plane with a certain ratio of the heights of the bases 13 or 14 contiguous sections 5 allows to reduce the load on the actuators disclosure (in the drawing conventionally not shown) experienced multi-link mechanical system 7.

Therefore, when using the proposed method of testing multi-link mechanical system 7 spacecraft 3 operation eliminates abrupt (rescourse) non-synchronous reciprocal movement of the deployable units 6 of multibody mechanical systems 7 spacecraft 3 and the corresponding sections 5 sectional rotary rod 4. The dynamics of this disclosure allows you to more accurately simulate (for ground test bench) real conditions of disclosure of multibody mechanical systems 7 spacecraft 3 in space and give eno is but a reliable confirmation of the regular disclosure of multibody mechanical system 7 in the conditions of real operation. In addition, in the process of testing disclosure eliminates the possibility of damage to structural members test multi-link mechanical system 7 and drives the disclosure (in the drawing conventionally not shown).

Thus, the proposed method of testing multi-link mechanical system of the spacecraft on the functioning and device for its implementation have significant differences from the previously known objects patenting and reduce the inertial loads on the design of multibody mechanical systems and actuators disclosed in the process of testing by providing synchronous movement of the links of the multi-link mechanical system of the spacecraft and the relevant sections of the sectional rotary rods.

1. The method of testing multi-link mechanical system of the spacecraft on the operation, which consists in the fact that the spacecraft with a fixed multi-link mechanical system connected to the actuators disclosure, equipped with beam system, is attached to the upper part of the spacecraft, set with opening links in multi-link mechanical system in the vertical plane, attach each link of the multi-link mechanical system regulated by p the dinner obespechivaniya to beam system, carry out the adjustment of the tension of each adjustable springs obespechivaniya when unfolded links, multi-link mechanical system, the close links of the multilink of the mechanical system, fix the links in multi-link mechanical systems for space apparatus and perform consistent unfolding of the links of the multi-link mechanical system using actuators disclosure, wherein after adjusting the tension of each adjustable springs obespechivaniya with ensuring the installation of the upper ends of the links of the multi-link mechanical system in the horizontal plane to provide a rigid connection of each link of multibody mechanical systems with corresponding section of the sectional rotary rod beam system by attachment of adjustable rods that are placed symmetrically on both sides of the respective adjustable spring obespechivaniya, to the respective links of the multilink of the mechanical system and the sections of the sectional rotary rod beam system with subsequent joint disclosure of each link of the multi-link mechanical system of the spacecraft and the corresponding section of the sectional rotary rod beam system as a whole.

2. The device for implementing the method of testing multi-tier mechanical the system of the spacecraft on the functioning containing beam system made in the form of technological rings fixed in the upper part of the spacecraft and provided with a sectional rotary rods, each section of which is placed in the plan over the appropriate level of multibody mechanical system and connected with it by means of an adjustable spring obespechivaniya, characterized in that the sections of the sectional rotary rods are secured to the respective links of the multilink of the mechanical system by means of adjustable rods, each of which consists of a shaft and sleeve, the rods placed in the sleeve and connected with them by means of threaded connections and clamps position, and the sleeve is fixed to the sections of the sectional rotatable rods, and the rods attached on the relevant parts of multibody mechanical system, with adjustable ties placed symmetrically on both sides of the respective adjustable spring obespechivaniya.

3. The device according to claim 2, characterized in that the sections of the sectional rotary rods in projection on a vertical plane have the form of a trapezoid with a vertical location of their bases, and the upper sides of the trapezoid are in the same inclined plane, with the vertical height of the bases of adjacent sections sectional rotary rods made of uvelichivalas is towards technological ring is proportional to the ordinal number of the sections of the sectional rotary rods.

4. The device according to claim 3, characterized in that the sections of the sectional rotary rods made hole punch.



 

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2 dwg

FIELD: mechanical engineering.

SUBSTANCE: method includes recording vibration parameters on body of subject transmission. By filtering, source signal of body oscillations is selected. Rounding curve of filtered signal and spectrum of curve are determined. From received data, informative components are picked, as which amplitudes of recorded vibration parameters are utilized. Static characteristics are determined and on their basis load level of teeth is determined. Source signal of body oscillations is selected by band filtering of source signal. Processing of rounding curve of filtered signal is made in following order: smoothing out of curve and determining of main frequency of curve from analysis of its spectrum, determining of number of periods of body oscillation pulses during experiment time, calculating curve derivative and minimums of curve, selecting global minimums of curve, determining separation boundaries and duration of periods between oscillations pulses, determining of impacts energy in each period.

EFFECT: selection of informative components from received data.

8 dwg

FIELD: mechanical engineering.

SUBSTANCE: method includes, prior to operation of toothed gear, measuring thickness of cog tooth on polar line and on line, containing input point of working portion of teeth engagement line. After wear of toothed transfer gear, thickness of tooth is measured again at aforementioned lines of tooth and by means of measurement results cyclic error of toothed frequency is determined in toothed gear by mathematical calculations.

EFFECT: possible determining of tooth frequency cyclic error for large-module toothed transfer gears without any additional means and/or operations.

2 dwg

FIELD: test equipment.

SUBSTANCE: torsion and loading moments are applied to shafts of reducer to be tested. Loading moment of electric engine at input of reducer is calculated automatically on the base of values of electric parameters of electric engine, which drives reducer into motion. Loading moment of generator at output of reducer is calculated automatically from values of electric parameters of generator connected with output shaft of reducer to be tested. Efficiency of reducer is calculated automatically as loading moment of generator relatively loading moment of electric engine. Digital values of loading moment of electric engine and efficiency of reducer are displayed onto monitor periodically. Values of loading moment of electric engine and efficiency of reducer are memorized to get access to subsequent reading mentioned values out. Total number of cycles of measurement and number of cycle of corresponding measurement is specified. Values of loading moment of electric engine and efficiency of reducer are pt into memory during 8192 cycles. Technical condition of reducer is estimated by due to comparing read out data with reference data.

EFFECT: improved efficiency of test.

2 dwg

FIELD: the invention refers to testing technique.

SUBSTANCE: the test bench has a drive , input shafts for connecting with tested transmissions, output shafts, a loader and a locking device. The test bench has two tested transmissions and the locking device is fulfilled in the shape of gearings firmly connected between themselves and having equal gearing ratio with tested gearings and installed on the input parallel shafts of tested gearings. A calibrated dynamometer clutch connecting two output shafts of tested gearings. serves as a loader.

EFFECT: the invention simplifies and increases productivity of testing.

3 dwg

FIELD: transport engineering.

SUBSTANCE: invention relates to design of test stands and it can be used for testing coaxial reduction gears in closed circuit. Proposed stand contains drive motor 3 and two coaxially installed reduction gears 1 and 2. Hollow output shafts 7 and 8 are interconnected by flexible coupling 9. Input shafts 4 and 5 arranged inside hollow shafts are connected by coupling 6. Housing of reduction gear 1 is installed stationarily on frame 10of stand, and housing of reduction gear 2 is installed in process support 11 secured on frame 1 for turning through preset angle relative to housing of reduction gear 1. Worm self-braking pair 12 is installed in support 11 to turn housing of reduction gear 2 through preset angle and fixing it in position. Worm wheel of pair can be made in form of sector secured by screws on housing of reduction gear 2. Any mechanical or hydraulic device installed on process support can be used instead of worm pair.

EFFECT: improved testing.

2 dwg

FIELD: testing engineering.

SUBSTANCE: method comprises determining initial rate of impact from preliminary deviation of rotatable traverse from vertical. When the rotatable traverse is in vertical position, the axis of rotation of the rotatable traverse, axis of the gearing wheel secured to the unmovable end of the rotatable traverse, and gearing wheel secured to the housing are vertically aligned. In so doing, the sides of the wheel teeth engage the gearing. The initial rate of impact is determined from the formula proposed.

EFFECT: enhanced reliability of investigating.

1 dwg

FIELD: testing engineering.

SUBSTANCE: bench comprises base, driving shaft mounted on the base for permitting rotation, clutch connected with the driving shaft, mechanism for clutch engagement and disengagement, and control desk. The driving shaft is composed of at least two members. One member can be connected with the driving shaft of the electric drive to be tested and is provided with clutch member rigidly connected with its free end, drum with slots uniformly arranged over periphery along the generatrices and mounted on the intermediate section of the shaft, and inductive contactless switch which is mounted on the base near the drum at the level of slots and whose output is connected with the control desk. The other member of the driving shaft provided with the other clutch member kinematically connected with the mechanism for clutch engagement and disengagement is provided with a single-arm lever whose one end is rigidly connected with the shaft member for permitting rotation together with it and co-operation with the force pickup with its free end.

EFFECT: simplified design and expanded functional capabilities of the bench.

1 dwg

FIELD: testing engineering.

SUBSTANCE: bench comprises asynchronous electric motor and balancing machine interconnected through the shaft to be tested, control unit, and resonance pickup mounted on the shaft and connected with the input of the control unit. The bench is provided with the frequency converter, DAC unit, thyristor controller of voltage, and inverter. The first output of the control unit is connected with the frequency converter connected to the circuit for power supply to the asynchronous motor. The second output of the control unit is connected in series with the DAC unit and thyristor voltage controller connected with the exciting winding of the balancing machine. The circuit of the armature of the balancing machine is connected to the inverter.

EFFECT: enhanced reliability of testing.

1 dwg

FIELD: testing engineering.

SUBSTANCE: bench comprises asynchronous electric motor and balancing machine interconnected through the shaft to be tested, control unit, and resonance pickup mounted on the shaft and connected with the input of the control unit. The bench is provided with the frequency converter, DAC unit, thyristor controller of voltage, and inverter. The first output of the control unit is connected with the frequency converter connected to the circuit for power supply to the asynchronous motor. The second output of the control unit is connected in series with the DAC unit and thyristor voltage controller connected with the exciting winding of the balancing machine. The circuit of the armature of the balancing machine is connected to the inverter.

EFFECT: enhanced reliability of testing.

1 dwg

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