CN2326935Y

CN2326935Y - Fully-automatic measuring locater

Info

Publication number: CN2326935Y
Application number: CN 98205425
Authority: CN
Inventors: 胡凡
Original assignee: Individual
Current assignee: Individual
Priority date: 1998-05-27
Filing date: 1998-05-27
Publication date: 1999-06-30
Anticipated expiration: 2008-05-27

Abstract

The utility model discloses a fully-automatic measuring locater, particularly the fully-automatic engineering measuring instrument used for the fully-automatic measurement of distances, angles and positioning, which can be controlled by a computer. The utility model comprises the vertical angles automatically regulating device which takes stepping motor as dynamic force, the automatic regulating device of horizontal angles, and a laser illuminating apparatus with adjustable optical axes. The utility model is suitable for high accuracy measurement in the ranges of hundreds meters for projections such as tunnels, subways, large water supply and sewerage, etc.

Description

The all automatic measurement orientator

The utility model relates to engineering surveying instrument, especially the instrument of measuring distance, angle and location.

At present in tunnel, subway, large-scale water supply and sewage work etc. are built, measurement and location for construction surface distance, angle are to be related to whole engineering to run smooth, improving construction quality, accelerate the basic work of duration progress, generally all is to finish with total powerstation.But total powerstation can not be realized automatic operation, only possesses manual measurement and artificial target localization, and each step in the operation all must be with manually carrying out, and one of its reason is the rotation system of total powerstation, and the adjustment of horizontal direction and vertical direction angle can only be used manually-operated; Former two is not each automatic necessary irradiation system in location of tool of total powerstation therefore, so can't realize by computer-controlled all automatic measurement and location.

The purpose of this utility model provides a kind of all automatic measurement orientator of available computers control.

The technical scheme of the utility model all automatic measurement orientator is as follows: all automatic measurement orientator has frame, fuselage is housed on frame, be connected with Electronic Distance Meters at back, at the underbelly two ends LCD is housed, on the described fuselage left side vertical angle automatic regulating apparatus is housed also, on described fuselage the right the level angle automatic regulating apparatus is housed also, adjustable optical axis laser irradiation device is housed at the top of described Electronic Distance Meters.Described vertical angle automatic regulating apparatus and level angle automatic regulating apparatus, they have step motor, the motor slide bar is equipped with in the end of step motor axle, the motor slide bar inserts in the chute of chute connector and rotational limitation indicator, the other end of chute connector is inserted with transmission shaft, the outside of transmission shaft is with propeller shaft tube, between transmission shaft and the propeller shaft tube for being threaded, at the propeller shaft tube overcoat fuselage twist-lock axle is arranged, at fuselage twist-lock outer shaft sleeve bearing support is arranged, the other end at transmission shaft is equipped with universal bar, outside and whole universal bar outside in transmission shaft and universal bar coupling part are with a spring, the other end of universal bar withstands on the end face of fuselage rotation axis, between fuselage rotation lock dead axle and fuselage rotation axis, the chute connector is housed, the chute connector links to each other with fuselage rotation lock dead axle with fixed screw, in the radial position of fuselage rotation axis end fuselage is housed and rotates slide bar, fuselage rotates slide bar and inserts in the chute of chute connector, it is to be slidingly connected in chute that fuselage rotates slide bar, axial location at the other end of fuselage rotation lock dead axle is equipped with fuselage rotation lock dead axle driving lever, with the radial position of the corresponding bearing support of driving lever the slotted hole of spending greater than 90 is arranged, driving lever can be made 90 degree and rotate in the slotted hole of bearing support, the rotational limitation indicator is discoid, it is arranged in the radial position of outside surface of the chute connector that is enclosed within step motor axle and transmission shaft end, with the top of the corresponding bearing support of rotational limitation indicator the windowpane of observing the rotational limitation indicator is installed, with the corresponding bottom of windowpane the bearing support bottom is being installed, fuselage rotational limitation switch I and fuselage rotational limitation switch II are being housed on the bottom inside surface of chute connector, described adjustable optical axis laser irradiation device has the base that is connected with described Electronic Distance Meters top, the laser instrument shell is equipped with at the top of base, be divided into laser instrument shell right part and laser instrument shell left part, laser instrument is equipped with in centre at the laser instrument shell, left end at laser instrument is with laser optical axial adjustment seat, the left end portion of laser optical axial adjustment seat is a rectangular parallelepiped, on the two adjacent surfaces of rectangular parallelepiped, have mutually perpendicular two half grooves that do not connect, laser optical axial adjustment spring is housed in each half groove, laser optical axial adjustment spring one end contacts with the bottom surface of half groove, the other end contacts with the inside surface of laser instrument shell, the other two sides of rectangular parallelepiped contacts with two laser optical axial adjustment knobs respectively, laser optical axial adjustment knob vertically reaches the outside of shell by the hole on the shell left part, laser optical axial adjustment knob is to be threaded with hole on the shell left part.

The utility model all automatic measurement orientator has the following advantages: (1) is owing to adopted vertical angle automatic regulating apparatus and level angle automatic regulating apparatus, replaced vertical angle adjusting means and the level angle adjusting gear on the total powerstation, can be connected with computing machine by communication interface, computing machine is measured the driver that passes to step motor with the horizontal direction of customer requirements and the rotation angle of vertical direction, step motor rotates under the driving of driver, thereby finish the user automatically and in computing machine, give various measurements and the positioning action of setting earlier, realized the robotization of measurement and positioning action.(2) because adopted adjustable optical axis laser irradiation device, be easy to laser beam axis parallel with the optical axis furnishing in the eyepiece, make instrument possess the laser positioning function, changed, can in hundreds of rice scope, carry out high-acruracy survey and location by manually passing through the scopodromic operation of eyepiece; (3) simple in structure, highly versatile can be common to all kinds of total powerstations.

Below by drawings and Examples the utility model all automatic measurement orientator is described further.

Fig. 1 is the utility model all automatic measurement orientator structural representation;

Fig. 2 is an angle automatic regulating apparatus structural representation;

Fig. 3 is adjustable optical axis laser irradiation device structural representation;

The sectional view of Fig. 4 for being done along Fig. 3 A-A line;

Fig. 5 is that the A of Fig. 3 is to view.

The all automatic measurement locating device has left and right two frame horizontal adjustment devices 2 on frame 1 as shown in Figure 1, at upper rack fuselage 8 is installed, Electronic Distance Meters 4 is installed on fuselage, on fuselage the right level angle automatic regulating apparatus 3 is installed, on the fuselage left side vertical angle automatic regulating apparatus 6 is installed, adjustable optical axis laser irradiation device 5 is installed at the top of Electronic Distance Meters 4, LCD 7 is installed at the left and right two ends of upper rack.The concrete structure of vertical angle automatic regulating apparatus 6 and level angle automatic regulating apparatus 3 as shown in Figure 2, the motive power of angle automatic regulating apparatus is step motor 9, step motor axle 10 is connected with fuselage rotation axis 20 with universal bar 19 by transmission shaft 17, the rotation of step motor is passed to fuselage rotation axis 20, the left end of transmission shaft 17 inserts the right-hand member of chute connector 12, with fixed screw 27 transmission shaft and chute connector are fixed, the radial position of the right-hand member of step motor axle 10 is equipped with step motor slide bar 11, in the chute of the left end of step motor slide bar insertion chute connector 12, the right part of transmission shaft 17 is with propeller shaft tube 14, transmission shaft is to be threaded with propeller shaft tube, because the rotation of transmission shaft 17, transmission shaft and transmission shafts inner room produce relative displacement, transmission shaft is moved to the left or to the right, at the propeller shaft tube overcoat fuselage twist-lock axle 15 is arranged, at step motor axle 10, the outermost layer of chute connector 12 and transmission shaft 17 is bearing supports 16, play shell, in the radial position of chute connector 12, be connected with a discoid rotational limitation indicator, top at corresponding bearing support has windowpane 13, be used to observe the position of rotational limitation indicator, bottom at corresponding bearing support is a bottom 29, the appropriate location is separately installed with fuselage rotational limitation switch I 26 and fuselage rotational limitation switch II 28 on the bottom inside surface, when transmission shaft is moved beyond specialized range to the left or to the right, the rotational limitation indicator will touch fuselage rotational limitation switch I or II, and step motor is stopped operating.Fixing between propeller shaft tube 14 and the bearing support 10 by propeller shaft tube fixed screw 25.Right-hand member at transmission shaft 17 is equipped with universal bar 19, outside and universal bar outside in transmission shaft and universal bar coupling part are with a spring 22, the other end of universal bar 19 withstands on the end face of fuselage rotation axis 20, right-hand member at fuselage rotation lock dead axle 15 connects a chute connector 18 by fixed screw 23, in the radial position of fuselage rotation axis 20 ends fuselage is housed and rotates slide bar 21, fuselage rotates slide bar 21 and inserts in the chute of chute connector 18.In the left end radial position of fuselage rotation lock dead axle 15 fuselage rotation lock dead axle driving lever 24 is housed, corresponding radial position at bearing support with driving lever has the slotted hole greater than 90 degree, and then drive chute connector 18 and fuselage rotation axis 20 corresponding revolving turn 90 degrees, reach the purpose of locking fuselage.Rotate when computing machine and computing machine after the step motor communication interface is connected pass to user's the rotation angle tolerance that requires horizontal direction or vertical direction the driver of step motor and then drive step motor, reach various measurements and the positioning action of finishing customer requirements automatically.The concrete structure of adjustable optical axis laser irradiation device 5 is shown in Fig. 3～Fig. 5, the base 38 of adjustable optical axis laser irradiation device 5 is fixed on the top of described Electronic Distance Meters 4 by screw 40 usefulness screws, adjustable optical axis laser irradiation device shell right part 31 is installed on the base 38 by screw 39, shell left part 35 is connected with the shell right part by shell connecting screw 34, and laser instrument 30 is installed in enclosure by screw 41.The left part of laser instrument inserts in the laser optical axial adjustment seat 33, and it is fixing by screw 32, the left end portion of laser optical axial adjustment seat is a rectangular parallelepiped, on the adjacent two sides of rectangular parallelepiped, have two half grooves orthogonal and that do not connect, laser optical axial adjustment spring 37 is housed in each half groove, one end of spring contacts with the bottom surface of half groove, the other end contacts with the inside surface of the left part 35 of laser instrument shell, other two sides at rectangular parallelepiped contacts with two laser optical axial adjustment knobs 36 respectively, laser optical axial adjustment knob is vertically by the screw on the shell left part, reach enclosure, the vertical direction of laser optical axis and horizontal direction can be adjusted knob by the rotary laser optical axis and adjust, thereby make all automatic measurement orientator possess the function of laser positioning.

Claims

1, a kind of all automatic measurement orientator, has frame (1), fuselage (8) is housed on frame (1), be connected with Electronic Distance Meters (4) on fuselage (8) top, LCD (7) is housed at the underbelly two ends, it is characterized by on the described fuselage left side vertical angle automatic regulating apparatus (6) also is housed, on described fuselage the right level angle automatic regulating apparatus (3) is housed also, at the top of Electronic Distance Meters (4) adjustable optical axis laser irradiation device (5) is housed, described vertical angle automatic regulating apparatus and level angle automatic regulating apparatus, they have step motor (9), motor slide bar (11) is equipped with in the end of step motor axle (10), motor slide bar (11) inserts in the chute of chute connector and rotational limitation indicator (12), the other end of chute connector is inserted with transmission shaft (17), the outside of transmission shaft (17) is with propeller shaft tube (14), between transmission shaft (17) and the propeller shaft tube (14) for being threaded, at propeller shaft tube (14) overcoat fuselage twist-lock axle (15) is arranged, outside fuselage rotation lock dead axle (15), be with bearing support (16), the other end at transmission shaft (17) is equipped with universal bar (19), outside and whole universal bar (19) outside in transmission shaft (17) and universal bar (19) coupling part are with a spring (22), the other end of universal bar (19) withstands on the end face of fuselage rotation axis (20), between fuselage rotation lock dead axle (15) and fuselage rotation axis (20), chute connector (18) is housed, chute connector (18) links to each other with fuselage rotation lock dead axle (15) with fixed screw (23), in the radial position of fuselage rotation axis (20) end fuselage is housed and rotates slide bar (21), fuselage rotates slide bar (21) and inserts in the chute of chute connector (18), it is to be slidingly connected in chute that fuselage rotates slide bar (21), axial location at the other end of fuselage rotation lock dead axle (15) is equipped with fuselage rotation lock dead axle driving lever (24), with the radial position of the corresponding bearing support of driving lever the slotted hole of spending greater than 90 is arranged, driving lever can be made 90 degree and rotate in the slotted hole of bearing support, rotational limitation indicator (12) is discoid, it is arranged in the radial position of outside surface of the chute connector that is enclosed within step motor axle (10) and transmission shaft (17) end, with the top of the corresponding bearing support of rotational limitation indicator the windowpane (13) of observing the rotational limitation indicator is installed, with the corresponding bottom of windowpane (13) bearing support bottom (29) is being installed, fuselage rotational limitation switch I (26) and fuselage rotational limitation switch II (28) are being housed on the bottom inside surface of chute connector, described adjustable optical axis laser irradiation device (5) has the base (38) that is connected with described Electronic Distance Meters (4) top, the laser instrument shell is equipped with at the top of base (38), be divided into laser instrument shell right part (31) and laser instrument shell left part (35), laser instrument (30) is housed in the centre of laser instrument shell, left end at laser instrument (30) is with laser optical axial adjustment seat (33), the left end portion of laser optical axial adjustment seat (33) is a rectangular parallelepiped, on the two adjacent surfaces of rectangular parallelepiped, have mutually perpendicular two half grooves that do not connect, laser optical axial adjustment spring (37) is housed in each half groove, laser optical axial adjustment spring one end contacts with the bottom surface of half groove, the other end contacts with the inside surface of laser instrument shell, the other two sides of rectangular parallelepiped contacts with two laser optical axial adjustment knobs (36) respectively, laser optical axial adjustment knob vertically reaches the outside of shell by the hole on the shell left part, laser optical axial adjustment knob is to be threaded with hole on the shell left part.