CN208699072U - Unmanned plane during flying angle balancing device - Google Patents
Unmanned plane during flying angle balancing device Download PDFInfo
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- CN208699072U CN208699072U CN201820763189.3U CN201820763189U CN208699072U CN 208699072 U CN208699072 U CN 208699072U CN 201820763189 U CN201820763189 U CN 201820763189U CN 208699072 U CN208699072 U CN 208699072U
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Abstract
The utility model relates to air vehicle technique field more particularly to a kind of unmanned plane during flying angle balancing devices.Unmanned plane during flying angle balancing device provided by the utility model, including device noumenon, device noumenon include top support, pedestal and the connection bar assembly for connecting top support and pedestal and adjustable in length；Top support is used to withstand unmanned plane when unmanned plane trimmed flight angle；Pedestal includes base body and the weighing component in base body.With usually, multiple balancing devices need to be only respectively placed in the wing two sides, body head and body tail portion of unmanned plane, it is used with flight control system joint debugging, by adjusting the length of connection bar assembly come the flight angle of trim unmanned plane, and only need to flight angle to unmanned plane and bottom weighing carry out 2 zeroings respectively, trim step is easy and trim precision is high.
Description
Technical field
The utility model relates to air vehicle technique field more particularly to a kind of unmanned plane during flying angle balancing devices.
Background technique
Unmanned plane (unmanned aerial vehicle or drone) is one kind by radio robot or itself journey
The unmanned vehicle of sequence control device manipulation.In flight test of unmanned aerial vehicle, airborne ins element can only measure attitude angle,
The flight parameters such as angular speed, air speed and height, and the flights such as wind speed, wind direction and flight angle in-flight ginseng can not be obtained
Number.
In the analysis of existing flight test of unmanned aerial vehicle flying quality, simple approximate processing is generally only done to flight angle,
Such as lift resistance ratio is only assessed with attitude angle substitution flight angle, the performance parameters such as lift coefficient, or according to weather when flight
State measures wind speed and direction at that time as reference, when estimating flight angle, is deducted from pitch angle to replace flying
Row angle, the angle of attack estimation obtained in this way are more coarse and inaccurate.
Apart from the above, also there are the method using flight and wind tunnel test data estimation unmanned plane trim angle of attack, unmanned plane
In flight test, the flight parameters such as aerial wind information and the angle of attack are unable to measure, can be used afterwards test flight data and
Wind tunnel data estimates unmanned plane during flying angle, realizes the requirement of flying quality analysis.First according to flight test of unmanned aerial vehicle spy
Flat winged characteristic in flight test is intercepted out, and uses data processing method by point, intercepts stable flat winged parameter.
Kinematic relation when with post analysis unmanned plane airflight, and consider wind tunnel data, pass through Gasuss_Newton optimization method
Do the flat winged equation optimization processing of unmanned plane, when between test parameters and estimation parameter there are when error, needing to wind tunnel data and
Kinetics relation carries out offset correction and iterates, and terminates until error is less than certain threshold value.Using aforesaid way, need
Wind tunnel test data are acquired, fund cost and the time cost for obtaining data are all very high；In addition, current trim scheme is to be based on
It has carried out the data obtained after multiple flight test analysis to carry out, and accurate trim adjustment can not be carried out before flying.
Utility model content
(1) technical problems to be solved
The purpose of this utility model is: it is high and effectively save can match to provide a kind of simple structure and reasonable design, trim precision
Flat step and the unmanned plane during flying angle balancing device for improving control efficiency, the angle of attack estimation existing for solve in a manner of existing trim
Fund cost and the higher problem of time cost more coarse and inaccurate and that obtain data.
(2) technical solution
In order to solve the above-mentioned technical problem, the utility model provides a kind of unmanned plane during flying angle balancing device, including
Device noumenon, described device ontology include top support, pedestal and for connecting the top support and pedestal and length
Adjustable connection bar assembly；The top support is used to withstand the unmanned plane when unmanned plane trimmed flight angle；
The pedestal includes base body and the weighing component in the base body.
According to the above technical scheme preferred, the top support includes thimble, and the thimble is used for the unmanned plane
The unmanned plane is withstood when trimmed flight angle.
According to the above technical scheme preferred, the top support include support ontology and be set to the support ontology and
The pressure sensor between bar assembly is connected, the support ontology is used to withstand the nothing when unmanned plane trimmed flight angle
It is man-machine.
Preferred, machine of the pressure sensor set on the support ontology and the unmanned plane according to the above technical scheme
The underface at the center of body contact surface.
According to the above technical scheme preferred, the connection bar assembly include push rod and sleeve, mandril and adjusting knob, described
Push rod and sleeve is connect with the base body, and the mandril is connect with the top support；The top stem casing is set to the top
It can move in rod sleeve and along the axis direction of the push rod and sleeve, the push rod and sleeve is equipped with mounting hole, the adjusting
Knob pushes against after passing through the mounting hole in the mandril.
According to the above technical scheme preferred, the push rod and sleeve are equipped with internal screw thread, and the mandril is equipped with and the interior spiral shell
The external screw thread of line cooperation, the mandril is by the external screw thread and internal screw thread along its axis direction precession in the push rod and sleeve
Or it screws out.
According to the above technical scheme preferred, the mounting hole are screw hole, the adjusting knob include knob and with institute
The abutting portion of knob connection is stated, the abutting portion is equipped with the screw thread cooperated with the screw hole, and the abutting portion passes through the spiral shell
Kong Hou rotates the knob until the abutting portion is pushed against in the mandril.
According to the above technical scheme preferred, the weighing component includes the electronic scale equipped with weight sensor, described heavy
Quantity sensor is set to the underface of the center of the top support.
According to the above technical scheme preferred, the electronic scale includes scale body and the display screen on the scale body, institute
Weight sensor is stated on the scale body.
According to the above technical scheme preferred, the electronic scale further includes the serial communication connecting with the weight sensor
Device.
(3) beneficial effect
The above-mentioned technical proposal of the utility model has the advantages that
The utility model provides a kind of unmanned plane during flying angle balancing device, including device noumenon, device noumenon include
Top support, pedestal and the connection bar assembly for connecting top support and pedestal and adjustable in length；Top support
For withstanding unmanned plane when unmanned plane trimmed flight angle；Pedestal includes base body and the weighing sections in base body
Part.Balancing device provided by the present application, top use top support, and bottom is used integrated to be set with what weighing component connected
Multiple balancing devices need to be only respectively placed in the wing two sides, body head and body tail portion of unmanned plane with usually by meter, with
Flight control system joint debugging uses, position of centre of gravity when according to unmanned plane whole design, and the length by adjusting connection bar assembly come
The flight angle of quick trim unmanned plane, structure is simple, and design is reasonable, and easy to operate；In addition, in trim, it only need to be to nothing
Man-machine pitch angle, roll angle carry out 2 zeroings respectively, also only need 2 zeroings to bottom weighing stage, trim step it is easy and
Trim precision is high, practical, conducive to production and popularization is standardized.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of unmanned plane during flying angle balancing device in the utility model embodiment one；
Fig. 2 is that the arrangement axis of unmanned plane during flying angle balancing device and unmanned plane is surveyed in the utility model embodiment one
Figure；
Fig. 3 is the arrangement schematic diagram of clump weight on unmanned plane in the utility model embodiment one；
Fig. 4 is that the arrangement of unmanned plane during flying angle balancing device and unmanned plane is faced in the utility model embodiment one
Figure；
Fig. 5 is in the utility model embodiment one using unmanned plane during flying angle balancing device trim unmanned plane during flying angle
Method and step block diagram.
In figure: 1: thimble；2: connection bar assembly；2-1: mandril；2-2: adjusting knob；2- 3: push rod and sleeve；3: pedestal；
10: unmanned plane during flying angle balancing device；100: unmanned plane；100-1: starboard wing；100-2: port wing；100-3: body head
Portion；100-4: body tail portion；100-5: the first clump weight；100-6: the second clump weight；100-7: third clump weight；100-8: the
Four clump weights.
Specific embodiment
It is practical new below in conjunction with this to keep the objectives, technical solutions, and advantages of the embodiments of the present invention clearer
Attached drawing in type embodiment, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that is retouched
The embodiment stated is a part of the embodiment of the utility model, instead of all the embodiments.Based on the reality in the utility model
Apply example, those of ordinary skill in the art's every other embodiment obtained without making creative work, all
Belong to the range of the utility model protection.
Embodiment one
As shown in Figures 1 to 4, on the one hand, the utility model embodiment provides a kind of unmanned plane during flying angle with paperback
It sets, including device noumenon, device noumenon includes top support, pedestal 3 and for connecting top support and pedestal 3 and long
Spend adjustable connection bar assembly 2；Top support is used to withstand unmanned plane 100 when 100 trimmed flight angle of unmanned plane；Pedestal
3 include 3 main body of pedestal and the weighing component in 3 main body of pedestal.Wherein, the flight angle of unmanned plane 100 includes pitch angle
And roll angle.
Unmanned plane during flying angle balancing device 10 provided by the present application, including the top braces set gradually from top to bottom
Part, connection bar assembly 2 and pedestal 3, wherein the adjustable in length of connection bar assembly 2, pedestal 3 are equipped with weighing component；Specifically
Ground, balancing device provided by the present application, top use top support form, and bottom is integrated using connecting with weighing component
4 balancing devices need to be only respectively placed in port wing 100-2, the starboard wing 100-1, machine of unmanned plane 100 with usually by design
Body head 100-3 and body tail portion 100-4 is used with flight control system joint debugging, center of gravity position when according to 100 whole design of unmanned plane
It sets, and by adjusting the length for connecting bar assembly 2 come the flight angle of quick trim unmanned plane 100, and in the machine of unmanned plane 100
The clump weight of corresponding counterweight is pasted in body position, e.g., the first clump weight 100- 5 is pasted on starboard wing 100-1, in port wing
The second clump weight 100-6 is pasted on 100-2, third clump weight 100-7 is pasted on the 100-3 of body head, in body tail portion
The 4th clump weight 100-8 is pasted on 100-4, to meet basic required state of flying, avoids the multiple iteration meter of the prior art
It calculates, and device provided by the present application, structure is simple, and design is reasonable, and easy to operate；In addition, in trim, it only need to be to unmanned plane
100 pitch angle, roll angle carry out 2 zeroings respectively, also only need 2 zeroings to bottom weighing stage, trim step it is easy and
Trim precision is high, practical, conducive to production and popularization is standardized.
According to the above technical scheme preferred, top support include thimble 1, and thimble 1 is used for unmanned plane trimmed flight angle
Unmanned plane is withstood when spending.
In the present embodiment, top support preferably uses thimble 1, wherein the upper end stress surface of thimble 1 can according to
The shape of the specific contact portion of unmanned aerial vehicle body is accordingly designed, in general, to mitigate the pressure to thimble, protection thimble end
The end in portion, thimble is mostly plane by face and area is as big as possible, capable of effectively being supported, positioning and being surveyed to fuselage
Weight.
According to the above technical scheme preferred, connection bar assembly 2 include push rod and sleeve 2-3, mandril 2-1 and adjusting knob
2-2, push rod and sleeve 2-3 are connect with 3 main body of pedestal, and mandril 2-1 is connect with top support；Mandril 2-1 is sheathed on push rod and sleeve
It can move in 2-3 and along the axis direction of push rod and sleeve 2-3, push rod and sleeve 2-3 is equipped with mounting hole, and adjusting knob 2-2 is worn
It pushes against after crossing mounting hole in mandril 2-1.
Specifically, in the present embodiment, connection bar assembly 2 includes push rod and sleeve 2-3, mandril 2- 1 and adjusting knob 2-2,
Mandril 2-1 is set in push rod and sleeve 2-3 and can reciprocatingly move along the axis direction of push rod and sleeve 2- 3, to match for basis
It is flat to need to be turned up or turn down the whole height of balancing device 10.Adjusting knob 2-2 is for fastening mandril 2-1 and push rod and sleeve
2-3 after one end of adjusting knob 2-2 passes through mounting hole, rotates knob when the position of mandril 2-1 and push rod and sleeve 2-3 is fixed
Until the end of adjusting knob 2-2 is pushed against in mandril 2-1, locking is realized.Structure is simple, and processing technology is easy, is conducive to reduce life
Cost is produced, easy to operate and locking effect is good.
According to the above technical scheme preferred, push rod and sleeve 2-3 are equipped with internal screw thread, and mandril 2-1 is equipped with and screw-internal thread fit
External screw thread, mandril 2-1 is by external screw thread and internal screw thread along its axis direction precession or back-out in push rod and sleeve 2-3.
It is further preferred that improve the connection effect of mandril 2-1 and push rod and sleeve 2-3, in the inner wall of push rod and sleeve 2-3
Equipped with internal screw thread, correspondingly, the outer wall in mandril 2-1 is equipped with the external screw thread matched with internal screw thread.If entire connection need to be adjusted
When the length of bar assembly 2, only need to precession or back-out in push rod and sleeve 2-3 by mandril 2-1, it is easy to operate；In addition, using screw thread
The mode of mating connection carries out accurate adjusting conducive to the height to connection bar assembly 2, is conducive to improve trim precision and trim effect
Rate.
It should be noted that mandril 2-1 and push rod and sleeve 2-3 in addition in such a way that internal screw thread is matched with external screw thread it
Outside, it can also be equipped with slideway along its axis direction in push rod and sleeve 2-3, mandril 2-1 can do reciprocal fortune along the trend of slideway
It is dynamic.Further, it can be positioned apart from multiple salient points on slideway, to prevent mandril 2-1 single mobile range excessive, be unfavorable for
It is rapidly achieved trim precision.
According to the above technical scheme preferred, mounting hole are screw hole, and adjusting knob 2-2 includes knob and connects with knob
The abutting portion connect, abutting portion is equipped with the screw thread cooperated with screw hole, and after abutting portion passes through screw hole, rotation knob is until abutting portion supports
Tightly in mandril 2-1.
The portion adjusting knob 2-2 includes that knob and one end are connect with knob, and the other end is used to push against the abutting of mandril 2-1
Portion, it is preferred that abutting portion is equipped with screw thread, correspondingly, mounting hole is screw hole, when that need to lock connection bar assembly 2, will push against portion
When across screw hole, when rotating knob, abutting portion advances towards mandril 2-1, until the end in abutting portion is pushed against in mandril 2-
1, structure is simple, and production technology is easy, is conducive to reduce production cost, and fastening effect is good.
According to the above technical scheme preferred, weighing component include the electronic scale equipped with weight sensor, weight sensor
Set on the underface of the center of top support.
In the present embodiment, weighing component includes the electronic scale equipped with weight sensor, it is preferred that sets weight sensor
In the underface of the center of top support, accurately to measure the weight of unmanned plane 100, conducive to the accurate of subsequent clump weight
Debugging, to further improve trim precision.Certainly, weight sensor can also be set to the position for deviateing top support center
Place, specifically can be reasonably arranged according to actual implementation condition.
According to the above technical scheme preferred, electronic scale includes scale body and the display screen on scale body, weight sensor
On scale body.
Further, by being provided with the electronic scale of display screen, display screen shows the weight transmitted by weight sensor
Data are measured, in order to read the weight that each thimble 1 measures during trim, to provide data reference for subsequent trim.
According to the above technical scheme preferred, electronic scale further includes the serial communication device connecting with weight sensor.
Further, electronic scale may also include serial communication device, and the display data of bottom of device are led to by serial ports
T unit is connected on computer, realizes key zero and data observation on position machine software on computers, avoids reading on data time
Waste and error in reading generation.
Wherein, it should be noted that, serial communication device can be both arranged simultaneously with display screen, can also select a setting, tool
Body can reasonably be set according to actual implementation condition.
On the other hand, as shown in figure 5, the utility model additionally provide it is a kind of by adopting the above technical scheme in unmanned plane fly
The method of row angle balancing device trim unmanned plane during flying angle first passes through the connection for adjusting unmanned plane during flying angle balancing device
Unmanned plane during flying angle so that the flight angle of unmanned plane is stablized within a preset range, and is matched paperback by the length of bar assembly
The weighing component display set is reset, to prepare for the trim of next step adjustment；Unmanned plane is placed in matching after length adjustment again
On leveling device, at this point, the display of the weighing component of each balancing device is not zero, pitch channel and rolling are successively carried out to unmanned plane
The trim for turning channel pastes clump weight on the fuselage of unmanned plane according to trim result, so that each unmanned plane during flying angle
The weighing component registration of balancing device bottom connection is shown to zero again, and the pitch angle of unmanned plane and roll angle are in predetermined angle
In range, so far trim is completed.
According to the above technical scheme preferred, specifically comprises the following steps:
Step S1, the unmanned plane that has been respectively arranged below in the wing two sides of unmanned plane, body head and body tail portion flies
Row angle balancing device, and it is better by being done at the fuselage plane contact point of each unmanned plane during flying angle balancing device and unmanned plane
Bit identification；
In the present embodiment, it needs 4 balancing devices to match with the flight control system of unmanned plane and carrys out quick trim unmanned plane
Flight angle.Specifically, 4 balancing devices are placed in the port wing, starboard wing, body of unmanned plane respectively according to default principle
Head and body tail portion, wherein the thimble of balancing device then marks the fuselage of thimble and unmanned plane flat for contacting with unmanned plane
The contact point in face, and it is denoted as a bit identification.
Step S2, the length for adjusting the connection bar assembly of each unmanned plane during flying angle balancing device, so that unmanned plane
Pitch angle and roll angle within the scope of predetermined angle；After the pitch angle and roll angle of unmanned plane are stablized, connecting rod group is locked
Part；
The fuselage of unmanned plane is separately mounted to fuselage after finishing assembly, by the flight control system of unmanned plane and power module
Corresponding position；Wherein, flight control system includes data transmission module, BEC module (Battey Elimination Circuit), flies
Control module and GPS module.Preferably, fly control module to be mounted on body nodal point position and lie in a horizontal plane in fuselage interior, GPS module
It is mounted on the top position of wing central axis and is horizontally mounted towards heading, other modules are fitted without that position is special to want
It asks, can specifically be put according to the space in fuselage.
In the present embodiment, when adjustment, first power on to the flight control system for being placed in fuselage interior, and be according to winged control
Earth station's software interface of system reads the angle of pitch channel and roll channel, specifically includes pitch angle and the roll of unmanned plane
Angle；The length that bar assembly is connected in 4 balancing devices is adjusted separately, so that the fuselage that the ground station software of flight control system is read
Posture pitch angle and roll angle are within the scope of predetermined angle, wherein predetermined angle range is between -0.5 °~0.5 °.When nobody
After the pitch angle and roll angle of machine reach stationary value within the scope of predetermined angle, the connecting rod group in each balancing device is locked
Part.
Step S3, the horizontal fuselage for lifting unmanned plane so that the thimble of each unmanned plane during flying angle balancing device with
The fuselage of unmanned plane completely disengages, and the weighing component registration that each unmanned plane during flying angle balancing device bottom connects is returned
Zero；
Specifically, in the present embodiment, after locking the connection bar assembly in each balancing device, a people is used double at this time
Hand firmly grasps wing two sides, after standard of fuselage is lifted, so that the thimble of 4 balancing devices is completely disengaged with fuselage；Another
The registration of the weighing component of 4 balancing devices is zeroed by people respectively, wherein the effect of zero is in order to which the trim of next step adjusts
It prepares.
Step S4, unmanned plane is placed on the unmanned plane during flying angle balancing device of each weighing component registration zero,
Wherein, the thimble alignment corresponding points bit identification of each unmanned plane during flying angle balancing device is placed；
In the present embodiment, unmanned plane is integrally placed to balancing device that 4 weighing component registrations have been zeroed again
On thimble, wherein 4 bit identifications respectively correspond on the thimble for 4 balancing devices for being placed in lower part.
Step S5, when the total weight of unmanned plane is pressed on unmanned plane during flying angle balancing device, each unmanned plane at this time
The weighing component registration of flight angle balancing device bottom connection is not zero, and pitch channel is successively carried out to unmanned plane and rolling is logical
The trim in road pastes clump weight on the fuselage of unmanned plane according to trim result, so that each unmanned plane during flying angle trim
The weighing component registration of bottom of device connection is shown to zero again, and the pitch angle of unmanned plane and roll angle are in predetermined angle range
Interior, so far trim is completed.
Specifically, in the present embodiment, 4 trims of lower part are placed in when 4 bit identifications of unmanned plane respectively correspond
On the thimble of device, after letting go, the total weight of unmanned plane is pressed on 4 balancing devices, at this time the title of 4 balancing device bottoms
The registration of heavy parts, which will be shown, to be not zero, and needs the trim that pitch channel and roll channel are successively carried out to unmanned plane later, and
According to specific trim as a result, pasting the clump weight of corresponding counterweight on the fuselage of unmanned plane, until 4 balancing device bottoms
Weighing component registration is shown as zero again, and the pitch angle of unmanned plane and roll angle are also within the scope of predetermined angle at this time, then
The trim work for representing fuselage has been completed.
According to the above technical scheme preferred, in step s 5, successively carries out pitch channel and roll channel to unmanned plane
Trim, clump weight is pasted on the fuselage of unmanned plane according to trim result, is specifically included:
The trim that pitch channel is first carried out to unmanned plane, i.e., carry out counterweight front and back along the fuselage axis direction of unmanned plane
To put adjustment so that the pitch angle of unmanned plane is within a preset range, and clump weight is glued in fuselage current location；It is right again
Unmanned plane carry out roll channel trim, i.e., along it is vertical on the fuselage axis direction with unmanned plane and pass through body nodal point position
Line carry out counterweight left and right directions and put adjustment so that the roll angle of unmanned plane is within a preset range, and clump weight is glued
Fortunately fuselage current location.
When matching flat to unmanned plane progress pitch channel, i.e., tune is put in the front-back direction along progress counterweight on fuselage axis
It is whole, when the clump weight after putting is located at the pitch angle of unmanned plane in preset range, clump weight is glued into working as in fuselage
Front position, at this point, the trim of body pitching channel is completed；Wherein, the predetermined angle range of pitch angle is between -0.5 °~0.5 °；
After completing pitch channel trim, then carry out roll channel trim adjustment, i.e., along on fuselage axis direction
Vertical and line by body nodal point position carries out, and clump weight is carried out left and right adjustment along line direction, observes earth station circle
Clump weight is glued working as in fuselage when the clump weight after putting is located at the roll angle of unmanned plane in preset range by face
Front position, at this point, fuselage roll channel trim is completed；Wherein, the predetermined angle range of roll angle is between -0.5 °~0.5 °.
According to the above technical scheme preferred, in step sl, is placed in the unmanned plane during flying angle trim of wing two sides
Line between the thimble of device, the line should be by body nodal points and vertical with fuselage axis institute；Be placed in body head and
The unmanned plane during flying angle balancing device of body tail portion, is placed according to the position of the partial operation plane of fuselage.
Preferably, in this embodiment, for the trim precision for improving unmanned plane, the default principle that 4 balancing devices are put, tool
Body includes: 2 unmanned plane during flying angle balancing devices for being placed in wing two sides, and the connection between the thimble of both device needs
By body nodal point and vertical with fuselage axis institute, in this way, this 2 balancing devices are symmetrically disposed at fuselage two sides, and with machine
A bit identification is carried out at underwing contact point；2 unmanned plane during flying angles of body head and body tail portion are placed in paperback
Set, then placed according to the position of partial operation plane of fuselage, and will with carry out a bit identification at fuselage plane contact point.
It should be noted that in the present embodiment, it is preferred to use 4 balancing devices complete unmanned plane during flying angle trim,
But it is not limited to be also possible to 4 or more, particular number can be according to practical reality using above-mentioned 4 balancing devices in trim step
Condition is applied to be reasonably arranged.
Embodiment two
Difference with embodiment one is only that:
In the present embodiment, unmanned plane during flying angle balancing device provided by the utility model, top support include branch
Ontology and the pressure sensor between support ontology and connection bar assembly are supportted, support ontology is used for unmanned plane trimmed flight angle
Unmanned plane is withstood when spending.Wherein, support the shape of the top support surface of ontology specifically can specifically contact according to unmanned aerial vehicle body
Partial shape is accordingly designed, can play effective, reliable support and positioning action.
Preferably, pressure sensor is set to the underface at the center of the fuselage contact surface of support ontology and unmanned plane, with energy
The weight for accurately measuring unmanned plane, conducive to the accurate debugging of subsequent clump weight, to further improve trim precision.Certainly, it presses
Force snesor can also be set at the position at the center of fuselage contact surface for deviateing support ontology and unmanned plane, specifically can be according to reality
Border implementation condition is reasonably arranged.
Other technologies scheme is identical as embodiment one, to avoid repeating, is not repeated.
In conclusion the utility model provides a kind of unmanned plane during flying angle balancing device, including device noumenon, device
Ontology includes top support, pedestal and the connection bar assembly for connecting top support and pedestal and adjustable in length；Top
Portion's supporting element is used to withstand unmanned plane when unmanned plane trimmed flight angle；Pedestal includes base body and in base body
Weighing component.Balancing device provided by the present application, top use top support, and bottom uses the one connecting with weighing component
Change design, with usually, multiple balancing devices need to be only respectively placed in the wing two sides, body head and body tail of unmanned plane
Portion is used with flight control system joint debugging, position of centre of gravity when according to unmanned plane whole design, and the length by adjusting connection bar assembly
The flight angle for carrying out quick trim unmanned plane is spent, structure is simple, and design is reasonable, and easy to operate；In addition, only being needed in trim
2 zeroings are carried out to pitch angle, the roll angle of unmanned plane respectively, 2 zeroings, trim step are also only needed to bottom weighing stage
Easy and trim precision is high, practical, conducive to production and popularization is standardized.
Finally, it should be noted that above embodiments are only to illustrate the technical solution of the utility model, rather than its limitations；
Although the utility model is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that:
It is still possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is carried out etc.
With replacement；And these are modified or replaceed, various embodiments of the utility model technology that it does not separate the essence of the corresponding technical solution
The spirit and scope of scheme.
Claims (11)
1. a kind of unmanned plane during flying angle balancing device, it is characterised in that: including device noumenon, described device ontology includes top
Supporting element, the pedestal with weighing component and the connecting rod group for connecting the top support and pedestal and adjustable in length
Part.
2. unmanned plane during flying angle balancing device according to claim 1, it is characterised in that: the top support includes
Thimble.
3. unmanned plane during flying angle balancing device according to claim 1, it is characterised in that: the top support includes
Support ontology and the pressure sensor between the support ontology and connection bar assembly.
4. unmanned plane during flying angle balancing device according to claim 3, it is characterised in that: the pressure sensor is set to
The underface at the center of the fuselage contact surface of the support ontology and the unmanned plane.
5. unmanned plane during flying angle balancing device according to claim 1-4, it is characterised in that: the connecting rod
Component includes push rod and sleeve, mandril and adjusting knob, and the push rod and sleeve is connect with the base body, the mandril with it is described
Top support connection.
6. unmanned plane during flying angle balancing device according to claim 5, it is characterised in that: the top stem casing is set to described
It can move in push rod and sleeve and along the axis direction of the push rod and sleeve, the push rod and sleeve is equipped with mounting hole, the tune
It saves after knob passes through the mounting hole and pushes against in the mandril.
7. unmanned plane during flying angle balancing device according to claim 5, it is characterised in that: the push rod and sleeve is equipped with interior
Screw thread, the mandril are equipped with the external screw thread with the screw-internal thread fit.
8. unmanned plane during flying angle balancing device according to claim 6, it is characterised in that: the mounting hole is screw hole,
The adjusting knob includes knob and the abutting portion connecting with the knob, and the abutting portion is equipped with to be cooperated with the screw hole
Screw thread, the abutting portion pass through the screw hole after, rotate the knob until the abutting portion push against in the mandril.
9. unmanned plane during flying angle balancing device according to claim 1, it is characterised in that: the weighing component includes setting
There is the electronic scale of weight sensor, the weight sensor is set to the underface of the center of the top support.
10. unmanned plane during flying angle balancing device according to claim 9, it is characterised in that: the electronic scale includes scale
Body and the display screen on the scale body, the weight sensor are set on the scale body.
11. unmanned plane during flying angle balancing device according to claim 9 or 10, it is characterised in that: the electronic scale is also
Including the serial communication device being connect with the weight sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820763189.3U CN208699072U (en) | 2018-05-22 | 2018-05-22 | Unmanned plane during flying angle balancing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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