CN206494143U - Fly control test device - Google Patents
Fly control test device Download PDFInfo
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- CN206494143U CN206494143U CN201720111476.1U CN201720111476U CN206494143U CN 206494143 U CN206494143 U CN 206494143U CN 201720111476 U CN201720111476 U CN 201720111476U CN 206494143 U CN206494143 U CN 206494143U
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Abstract
The utility model discloses a kind of winged control test device, including：First rotating mechanism, including the first noumenon and the first rotating shaft on the first noumenon；First arrestment mechanism, is connected with first rotating shaft, and prevents the rotation of first rotating shaft；Second rotating mechanism, including the second body and the second rotating shaft on the second body, the second body are fixedly connected with first rotating shaft；Second arrestment mechanism, is connected with the second rotating shaft, and prevents the rotation of the second rotating shaft；3rd rotating mechanism, including the 3rd body and the 3rd rotating shaft on the 3rd body, the 3rd body are fixedly connected with the second rotating shaft, and the connector of connection unmanned plane is provided with the 3rd rotating shaft；3rd arrestment mechanism, is connected with the 3rd rotating shaft, and prevents the rotation of the 3rd rotating shaft；Wherein, first rotating shaft, the second rotating shaft and the 3rd rotating shaft are arranged and are mutually perpendicular to two-by-two from bottom to up.Technical solutions of the utility model can improve the rotational freedom for flying control test device, to meet the testing requirement of Three Degree Of Freedom.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, more particularly to a kind of to fly control test device.
Background technology
With the development of science and technology, unmanned plane is more and more universal in our real-life uses, unmanned plane extensively should
For in all trades and professions.When studying the flight attitude of unmanned plane and controlling it design, researcher is mostly by flying
Control test device is acquired and studied to data such as the course angular dimensions under unmanned plane during flying state, pitching angular dimensions, but existing
The winged control test device function having is fairly simple, the general free degree that only there is one or two to rotate, and to the survey of unmanned plane
Examination be usually need to be rotated, front and rear rollover and the test of left-right rollover, it is free that existing winged control test device can not meet three
The testing requirement of degree.
Utility model content
Main purpose of the present utility model is to provide a kind of winged control test device, it is intended to improve the rotation for flying control test device
The free degree, to meet the testing requirement of Three Degree Of Freedom.
To achieve the above object, the winged control test device that the utility model is provided, for the test of unmanned plane, including：
One kind flies control test device, the test for unmanned plane, it is characterised in that including：
First rotating mechanism, including the first noumenon and the first rotating shaft on the first noumenon；
First arrestment mechanism, is connected with the first rotating shaft, and prevents the rotation of the first rotating shaft；
Second rotating mechanism, including the second body and the second rotating shaft on second body, second body
It is fixedly connected with the first rotating shaft；
Second arrestment mechanism, is connected with second rotating shaft, and prevents the rotation of second rotating shaft；
3rd rotating mechanism, including the 3rd body and the 3rd rotating shaft on the 3rd body, the 3rd body
It is fixedly connected with second rotating shaft, the connector for connecting the unmanned plane is provided with the 3rd rotating shaft；
3rd arrestment mechanism, is connected with the 3rd rotating shaft, and prevents the rotation of the 3rd rotating shaft；
Wherein, the first rotating shaft, the second rotating shaft and the 3rd rotating shaft are arranged and are mutually perpendicular to two-by-two from bottom to up.
Preferably, the first noumenon includes being set in the axle sleeve of the first rotating shaft outer surface, the first rotating shaft and
Clutch shaft bearing, the clutch shaft bearing and the first rotating shaft tight fit are provided between the axle sleeve and the axle sleeve is connected to
It is interior.
Preferably, the clutch shaft bearing includes at least one ball bearing and at least one thrust ball bearing.
Preferably, first arrestment mechanism includes the first holder, the second holder, the first locking member and the second locking
Part, the edge of first holder is formed with the first enlarging, and the edge of second holder is formed with the second enlarging, described
First holder and the second holder are oppositely arranged so that first enlarging and second enlarging enclose a holding chamber, institute
State first rotating shaft to be placed in the holding chamber, first holder and the second holder are fixed by the first locking member to be connected
Connect, first holder and/or the second holder are fixedly connected by second locking member with the first noumenon.
Preferably, second body includes the second substrate being connected with the first rotating shaft and located at the second substrate
On the second mounting seat, second rotating shaft and second mounting seat pass through second bearing and rotate connection.
Preferably, second mounting seat is provided with two, the two ends of second rotating shaft respectively with second mounting seat
Connection is rotated by two second bearings, the second mounting seat described in two is internally formed along the axial direction side of second rotating shaft
To the second groove of extension, the second bearing is in second groove；
Second bearing described in two is ball bearing, and the ball bearing includes inner ring and outer rings, and second groove is away from described
It is provided with what is be connected to the second tabletting of the inner ring collar extension edge and be tightly connected with the notch at the notch of second rotating shaft
Second enclosing cover, second enclosing cover abuts second tabletting.
Preferably, second arrestment mechanism includes the 3rd locking member, and second body is provided with the second mounting hole, institute
The 3rd body is stated provided with the 3rd mounting hole, the 3rd locking member passes through second mounting hole and the 3rd mounting hole, will
Second body and the 3rd body are fixedly connected.
Preferably, the 3rd body includes the 3rd substrate being connected with second rotating shaft and located at the 3rd substrate
On the 3rd mounting seat, the 3rd rotating shaft and the 3rd mounting seat pass through 3rd bearing and rotate connection.
Preferably, the 3rd mounting seat is provided with two, the two ends of the 3rd rotating shaft respectively with the 3rd mounting seat
Rotated and connected by 3rd bearing, the 3rd mounting seat described in two is internally formed along the axial direction extension of the 3rd rotating shaft
3rd groove, the 3rd bearing is in the 3rd groove；
3rd bearing described in two is ball bearing, and the ball bearing includes inner ring and outer rings, and the 3rd groove is away from described
Provided with being connected to the 3rd tabletting of the inner ring collar extension edge and close with the 3rd notch at 3rd notch of the 3rd rotating shaft
The 3rd enclosing cover of connection is sealed, the 3rd enclosing cover abuts the 3rd tabletting.
Preferably, the 3rd arrestment mechanism includes the 4th locking member, and the 3rd body is provided with the 4th mounting hole, institute
Connector is stated provided with the 5th mounting hole, the 4th locking member passes through the 4th mounting hole and the 5th mounting hole, by institute
The 3rd body is stated to be fixedly connected with connector.
Preferably, the first rotating shaft is vertically set.
Technical solutions of the utility model are by setting the first rotating mechanism to include the first noumenon and located at the first noumenon
On first rotating shaft, the first rotating shaft can rotation, in this way, rotary test of the unmanned plane with respect to the first noumenon can be realized；The
Two rotating mechanisms include the second body and the second rotating shaft on second body, second body with described first turn
Axle is fixedly connected, second rotating shaft can rotation, in this way, rotary test of the unmanned plane with respect to the second body can be realized；3rd
Rotating mechanism, including the 3rd body and the 3rd rotating shaft on the 3rd body, the 3rd body with described second turn
Axle is fixedly connected, the 3rd rotating shaft can rotation, so, it is possible to realize rotary test of the unmanned plane with respect to the 3rd body；And
The first rotating shaft, the second rotating shaft and the 3rd rotating shaft is set to arrange and be mutually perpendicular to two-by-two from bottom to up, the 3rd rotating shaft is used
It is connected in the unmanned plane, so, it is possible to realize the rotary test of the free degree of the unmanned plane in three mutually perpendicular directions；
Meanwhile, this flies the first arrestment mechanism that control test device also includes being used to prevent first rotating shaft rotation, for preventing the second rotating shaft
The second arrestment mechanism rotated, the 3rd arrestment mechanism for preventing the 3rd axis of rotation, in this way, can according to the demand of test,
Wherein one or more frees degree are prevented, to realize the test for wherein one or two free degree.
Brief description of the drawings
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the accompanying drawing used required in description of the prior art is briefly described, it should be apparent that, drawings in the following description are only
It is some embodiments of the present utility model, for those of ordinary skill in the art, is not paying the premise of creative work
Under, other accompanying drawings can also be obtained according to the structure shown in these accompanying drawings.
Fig. 1 is the structural representation that the utility model flies control test device preferred embodiment；
Fig. 2 is to fly the structural representation that the first rotating mechanism and the first arrestment mechanism coordinate in control test device shown in Fig. 1；
Fig. 3 is sectional view of the structure along AA directions shown in Fig. 2；
Fig. 4 is the broken away view of structure shown in Fig. 2；
Fig. 5 is the broken away view for flying control test device part-structure shown in Fig. 1；
Fig. 6 is the structural representation that the utility model flies ball bearing in control test device.
Drawing reference numeral explanation：
| Label | Title | Label | Title |
| 10 | First rotating mechanism | 11 | The first noumenon |
| 111 | Axle sleeve | 112 | Thrust ball bearing |
| 113 | Ball bearing | 1131 | Inner ring |
| 1132 | Outer shroud | 12 | First rotating shaft |
| 121 | Central axle portion | 1211 | Annular boss |
| 122 | Clamping part | 1221 | Annular groove |
| 20 | Second rotating mechanism | 21 | Second body |
| 211 | Second substrate | 212 | Second mounting seat |
| 22 | Second rotating shaft | 23 | Second bearing |
| 24 | Second tabletting | 25 | Second enclosing cover |
| 26 | Second mounting hole | 30 | 3rd rotating mechanism |
| 31 | 3rd body | 311 | 3rd substrate |
| 312 | 3rd mounting seat | 32 | 3rd rotating shaft |
| 33 | 3rd bearing | 34 | 3rd tabletting |
| 35 | 3rd enclosing cover | 36 | 3rd mounting hole |
| 40 | First arrestment mechanism | 41 | First holder |
| 411 | First enlarging | 42 | Second holder |
| 421 | Second enlarging | 43 | Second locking member |
| 44 | Holding chamber | 50 | Second arrestment mechanism |
| 51 | 3rd locking member | 60 | 3rd arrestment mechanism |
| 61 | 4th locking member | 70 | Connector |
Realization, functional characteristics and the advantage of the utility model purpose will be described further referring to the drawings in conjunction with the embodiments.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the present utility model, rather than all
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not making creative work premise
Lower obtained every other embodiment, belongs to the scope of the utility model protection.
If it is to be appreciated that in the utility model embodiment it is directional indicate (such as up, down, left, right, before and after ...),
Then it is only used for explaining relative position relation, motion conditions under a certain particular pose between each part etc., if this is specific
When posture changes, then directionality indicates also correspondingly therewith to change.
If in addition, being related to the description of " first ", " second " etc. in the utility model, it is only used for describing purpose, and
It is not intended that indicating or implying its relative importance or the implicit quantity for indicating indicated technical characteristic.Thus, limit
At least one this feature can be expressed or be implicitly included to the feature for having " first ", " second ".In addition, between each embodiment
Technical scheme can be combined with each other, but must can be implemented as basis with those of ordinary skill in the art, work as technical side
It will be understood that the combination of this technical scheme is not present, also not in this practicality when the combination appearance of case is conflicting or can not realize
Within the protection domain of new requirement.
Fly control test device, the test for unmanned plane the utility model proposes one kind.
As shown in Fig. 1,2 and 5, the winged control test device in the utility model includes：
First rotating mechanism 10, including the first noumenon 11 and the first rotating shaft 12 on the first noumenon 11, first rotating shaft
12 being capable of rotation；
First arrestment mechanism 40, is connected with first rotating shaft 12 and can prevent the rotation of first rotating shaft 12；
Second rotating mechanism 20, including the second body 21 and the second rotating shaft 22 on the second body 21, the second body
21 are fixedly connected with first rotating shaft 12, and the second rotating shaft 22 being capable of rotation；
Second arrestment mechanism 50, is connected with the second rotating shaft 22 and can prevent the rotation of the second rotating shaft 22；
3rd rotating mechanism 30, including the 3rd body 31 and the 3rd rotating shaft 32 on the 3rd body 31, the 3rd body
31 are fixedly connected with the second rotating shaft 22, and the 3rd rotating shaft 32 being capable of rotation；
3rd arrestment mechanism 60, is connected with the 3rd rotating shaft 32 and can prevent the rotation of the 3rd rotating shaft 32；
Wherein, first rotating shaft 12, the second rotating shaft 22 and the 3rd rotating shaft 32 are arranged and are mutually perpendicular to two-by-two from bottom to up；3rd
Rotating shaft 32 is used to be connected with unmanned plane.
The utility model by set the first rotating mechanism 10 include the first noumenon 11 and on the first noumenon 11 the
One rotating shaft 12, first rotating shaft 12 can rotation, in this way, rotary test of the unmanned plane with respect to the first noumenon 11 can be realized；Second rotation
Rotation mechanism 20 includes the second body 21 and the second rotating shaft 22 on the second body 21, and the second body 21 is consolidated with first rotating shaft 12
Fixed connection, the second rotating shaft 22 can rotation, in this way, rotary test of the unmanned plane with respect to the second body 21 can be realized；3rd rotation
Mechanism 30, including the 3rd body 31 and the 3rd rotating shaft 32 on the 3rd body 31, the 3rd body 31 and the second rotating shaft 22 are consolidated
Fixed connection, the 3rd rotating shaft 32 can rotation, so, it is possible to realize rotary test of the unmanned plane with respect to the 3rd body 31；And set
First rotating shaft 12, the second rotating shaft 22 and the 3rd rotating shaft 32 are arranged and are mutually perpendicular to two-by-two from bottom to up, the 3rd rotating shaft 32 be used for
Unmanned plane is connected, and so, it is possible to realize the rotary test of the free degree of the unmanned plane in three mutually perpendicular directions.
Meanwhile, this flies the first arrestment mechanism 40 that control test device also includes being used to prevent the rotation of first rotating shaft 12, is used for
The second arrestment mechanism 50 of the second rotating shaft 22 rotation is prevented, for preventing the 3rd arrestment mechanism 60 that the 3rd rotating shaft 32 is rotated, such as
This, can prevent wherein one or more frees degree, to realize for wherein one or two free degree according to the demand of test
Test.
Preferably, as shown in figure 1, setting first rotating shaft 12 vertically to set, in this way, the second rotating mechanism 20 and the
Three rotating mechanisms 30 are horizontally disposed respectively, and are mutually perpendicular, and through experiment, the structure can facilitate to enter unmanned plane
Row flies control test；And now, first rotating shaft 12 can realize the rotation test of unmanned plane, and the second rotating shaft 22 and the 3rd rotating shaft 32 can be real
The rollover test of existing unmanned plane.
As shown in Figures 1 to 4, the first noumenon 11 is set to include the axle sleeve for being set in the outside of first rotating shaft 12 in the utility model
111, first rotating shaft 12 and axle sleeve 111 are rotated by clutch shaft bearing and connected, and it is outer and with that clutch shaft bearing is set in first rotating shaft 12
The tight fit of one rotating shaft 12, and clutch shaft bearing is connected in axle sleeve 111, in this way, the rotation of first rotating shaft 12 can be realized, to realize nothing
The test of a man-machine rotary freedom.Specifically, when being rotated to reduce first rotating shaft 12, first rotating shaft 12 is along own axes
With the stress of radial direction, clutch shaft bearing is set to include at least one ball bearing 113 and at least one thrust ball bearing 112, such as
This, can extend the life-span of first rotating shaft 12.
As shown in Figures 3 and 4, the utility model sets the first arrestment mechanism 40 to include the first holder 41, the second holder
42nd, the first locking member (not shown) and some second locking members 43, the edge of the first holder 41 are formed with the first enlarging 411,
The edge of second holder 42 is formed with the second enlarging 421, and the first holder 41 and the second holder 42 are oppositely arranged, and first expands
Mouthfuls 411 and second enlarging 421 enclose a holding chamber 44, first rotating shaft 12 is located in holding chamber 44, the first holder 41 and the
Two holders 42 are fixedly connected by the first locking member, and the first holder 41 and/or the second holder 42 pass through the second locking member
43 are fixedly connected with the first noumenon 11.The first holder 41 and the second holder 42 are fixed by the first locking member in this way, working as
Connection, when the first holder 41 and/or the second holder 42 are fixedly connected by the second locking member 43 with the first noumenon 11, you can
Prevent the rotation of first rotating shaft 12, rotary test of the limitation unmanned plane with respect to the first noumenon 11.
Specifically, as shown in Figures 3 and 4, set first rotating shaft 12 include central axle portion 121 and be connected with central axle portion 121,
And the clamping part 122 in the outside of central axle portion 121 is located at, clutch shaft bearing is set in the outside of central axle portion 121, and clamping part 122 is used
The purpose that first rotating shaft 12 is rotated is prevented to realize in coordinating with the first holder 41 and the clamping of the second holder 42, is separately provided
The structure of clamping part 122, can conveniently prevent first rotating shaft 12 rotation, such as can clamping part 122 periphery set annular groove
1221, to facilitate the cooperation with the first holder 41 and the second holder 42；Wherein, clutch shaft bearing includes two thrust ball bearings
112 and a ball bearing 113, the periphery at the middle part of central axle portion 121 is to being externally provided with annular boss 1211, two thrust ball bearings
112 are located at the both sides of annular boss 1211 respectively, along the stress in own axes direction when being rotated with reasonable distribution first rotating shaft 12.
As shown in Figures 3 and 4, in order to simplify the structure of the first holder 41 and the second holder 42, both are set in symmetrical
Structure, now, the first enlarging 411 are identical with the shape of the second enlarging 421, can set screw hole respectively at both two ends, lead to
Both mode connects for screw are crossed, to clamp clamping part 122；Meanwhile, it can expand in the first holder 41 and the second holder 42 away from first
The position of the enlarging 421 of mouth 411 and second sets the screw hole coordinated with the first noumenon 11, can fix the first folder respectively by screw
The connection of the holder 42 of gripping member 41 and second, to clamp clamping part 122, and fixes the first holder 41 and the second holder simultaneously
42 respectively connection with the first noumenon 11 when, you can realize and prevent the purpose that first rotating shaft 12 is rotated.
As shown in figure 5, the second body 21 includes the second substrate 211 being connected with the upper end of first rotating shaft 12 and located at the second base
The second mounting seat 212 on plate 211, the second rotating shaft 22 and the second mounting seat 212 are rotated by second bearing 23 and connected, in this way,
The rotation of the second rotating shaft 22 can be achieved, you can realize the test of another free degree of unmanned plane.
Specifically, as shown in figure 5, setting the second mounting seat 212 to be provided with two, the two ends of the second rotating shaft 22 are respectively with second
Mounting seat 212 is rotated by two second bearings 23 and connected, and two second mounting seats 212 are internally formed the axle along the second rotating shaft 22
The second groove (not shown) extended to direction, second bearing 23 is in the second groove；Two second bearings 23 are ball bearing
113, ball bearing 113 includes inner ring 1131 and outer shroud 1132, and the second groove is provided with the notch of the second rotating shaft 22 and is connected to
Second tabletting 24 of the collar extension edge of inner ring 1131 and the second enclosing cover 25 being tightly connected with notch, the second enclosing cover 25 abut second
Tabletting 24.In this way, can not only realize the rotation of the second rotating shaft 22, and stability and the sealing of the structure of second bearing 23 can be ensured
Property.
As described in figures 1 and 5, the purpose that the second rotating shaft 22 is rotated is prevented in order to realize, sets the second arrestment mechanism 50 to include
3rd locking member 51, the second body 21 is provided with the second mounting hole 26, and the 3rd body 31 is provided with the 3rd mounting hole 36, the 3rd lock
Tight part 51 connects the second mounting hole 26 and the 3rd mounting hole 36, to fix the connection of the second body 21 and the 3rd body 31.Due to,
3rd body 31 is connected with the second rotating shaft 22, in this way, can be achieved to prevent second by the locking effect of the 3rd locking member 51
The purpose that rotating shaft 22 is rotated.As shown in figure 5, the 3rd locking member 51 is provided with two, and respectively screw.
As described in figures 1 and 5, the 3rd body 31 includes the 3rd substrate 311 being connected with the second rotating shaft 22 and located at the 3rd base
The 3rd mounting seat 312 on plate 311, the 3rd rotating shaft 32 and the 3rd mounting seat 312 are rotated by 3rd bearing 33 and connected, in this way,
The rotation of the 3rd rotating shaft 32 can be achieved, you can realize the test of unmanned plane three degree of freedom.
Specifically, as it can be seen in figures 5 and 6, setting the 3rd mounting seat 312 to be provided with two, the two ends of the 3rd rotating shaft 32 respectively with
3rd mounting seat 312 is rotated by 3rd bearing 33 and connected, and two the 3rd mounting seats 312 are internally formed the axle along the 3rd rotating shaft 32
The 3rd groove (not shown) extended to direction, 3rd bearing 33 is in the 3rd groove；Two 3rd bearings 33 are ball bearing
113, ball bearing 113 includes inner ring 1131 and outer shroud 1132, and the 3rd groove is provided with the 3rd notch of the 3rd rotating shaft 32 and supported
The 3rd enclosing cover 35 for being connected on the 3rd tabletting 34 of the collar extension edge of inner ring 1131 and being tightly connected with the 3rd notch, the 3rd enclosing cover 35
Abut the 3rd tabletting 34.In this way, can not only realize the rotation of the 3rd rotating shaft 32, and the stabilization of the structure of 3rd bearing 33 can be ensured
Property and sealing.
As described in figures 1 and 5, the purpose that the 3rd rotating shaft 32 is rotated is prevented in order to realize, sets and be installed with the 3rd rotating shaft 32
For the connector 70 being connected with unmanned plane, the 3rd arrestment mechanism 60 includes the 4th locking member 61, and the 3rd body 31 is provided with the
Four mounting holes (are not indicated), and connector 70 is provided with the 5th mounting hole (not indicating), and the 4th locking member 61 connects the 4th mounting hole
With the 5th mounting hole, to fix the connection of the 3rd body 31 and connector 70.In this way, being acted on by the locking of the 4th locking member 61
It can be achieved to prevent the purpose that the 3rd rotating shaft 32 is rotated.As shown in figure 5, the 4th locking member 61 is provided with two, and respectively screw.
It is noted that the first arrestment mechanism 40, the second arrestment mechanism 50 and the 3rd arrestment mechanism 60 can also be bags
Include the mechanism of the Detachable connection structures such as latch, buckle.
Preferred embodiment of the present utility model is these are only, the scope of the claims of the present utility model is not thereby limited, it is every
Under inventive concept of the present utility model, the equivalent structure transformation made using the utility model specification and accompanying drawing content, or
Directly/be used in other related technical fields indirectly and be included in scope of patent protection of the present utility model.
Claims (11)
1. one kind flies control test device, the test for unmanned plane, it is characterised in that including：
First rotating mechanism, including the first noumenon and the first rotating shaft on the first noumenon；
First arrestment mechanism, is connected with the first rotating shaft, and prevents the rotation of the first rotating shaft；
Second rotating mechanism, including the second body and the second rotating shaft on second body, second body and institute
First rotating shaft is stated to be fixedly connected；
Second arrestment mechanism, is connected with second rotating shaft, and prevents the rotation of second rotating shaft；
3rd rotating mechanism, including the 3rd body and the 3rd rotating shaft on the 3rd body, the 3rd body and institute
State the second rotating shaft to be fixedly connected, the connector for connecting the unmanned plane is provided with the 3rd rotating shaft；
3rd arrestment mechanism, is connected with the 3rd rotating shaft, and prevents the rotation of the 3rd rotating shaft；
Wherein, the first rotating shaft, the second rotating shaft and the 3rd rotating shaft are arranged and are mutually perpendicular to two-by-two from bottom to up.
2. as claimed in claim 1 fly control test device, it is characterised in that the first noumenon includes being set in described first
The axle sleeve of rotating shaft outer surface, is provided with clutch shaft bearing between the first rotating shaft and the axle sleeve, the clutch shaft bearing with it is described
First rotating shaft tight fit and it is connected in the axle sleeve.
3. as claimed in claim 2 fly control test device, it is characterised in that the clutch shaft bearing includes at least one ball bearing
With at least one thrust ball bearing.
4. as claimed in claim 1 fly control test device, it is characterised in that first arrestment mechanism includes the first clamping
Part, the second holder, the first locking member and the second locking member, the edge of first holder are formed with the first enlarging, described
The edge of second holder is formed with the second enlarging, and first holder and the second holder are oppositely arranged so that described first
Enlarging and second enlarging enclose a holding chamber, and the first rotating shaft is placed in the holding chamber, first clamping
Part and the second holder are fixedly connected by the first locking member, and first holder and/or the second holder pass through described
Two locking members are fixedly connected with the first noumenon.
5. as claimed in claim 1 fly control test device, it is characterised in that second body includes and the first rotating shaft
The second substrate of connection and the second mounting seat on the second substrate, second rotating shaft and second mounting seat are led to
Cross second bearing and rotate connection.
6. as claimed in claim 5 fly control test device, it is characterised in that second mounting seat is provided with two, described the
The two ends of two rotating shafts are rotated by two second bearings with second mounting seat be connected respectively, the second mounting seat described in two
The second groove along the axial direction extension of second rotating shaft is internally formed, the second bearing is located at second groove
It is interior；
Second bearing described in two is ball bearing, and the ball bearing includes inner ring and outer rings, and second groove deviates from described second
Provided with the second tabletting for being connected to the inner ring collar extension edge and be tightly connected with the notch second at the notch of rotating shaft
Enclosing cover, second enclosing cover abuts second tabletting.
7. the winged control test device as described in claim 5 or 6, it is characterised in that second arrestment mechanism includes the 3rd lock
Tight part, second body is provided with the second mounting hole, and the 3rd body is provided with the 3rd mounting hole, the 3rd locking member
Through second mounting hole and the 3rd mounting hole, second body and the 3rd body are fixedly connected.
8. as claimed in claim 5 fly control test device, it is characterised in that the 3rd body includes and second rotating shaft
The 3rd substrate and the 3rd mounting seat on the 3rd substrate of connection, the 3rd rotating shaft and the 3rd mounting seat are logical
Cross 3rd bearing and rotate connection.
9. as claimed in claim 8 fly control test device, it is characterised in that the 3rd mounting seat is provided with two, described the
The two ends of three rotating shafts are rotated by 3rd bearing with the 3rd mounting seat be connected respectively, and the 3rd mounting seat is internally formed described in two
There is the 3rd groove along the axial direction extension of the 3rd rotating shaft, the 3rd bearing is in the 3rd groove；
3rd bearing described in two is ball bearing, and the ball bearing includes inner ring and outer rings, and the 3rd groove deviates from the described 3rd
At 3rd notch of rotating shaft company is sealed provided with the 3rd tabletting for being connected to the inner ring collar extension edge and with the 3rd notch
The 3rd enclosing cover connect, the 3rd enclosing cover abuts the 3rd tabletting.
10. fly control test device as claimed in claim 8 or 9, it is characterised in that the 3rd arrestment mechanism includes the 4th lock
Tight part, the 3rd body is provided with the 4th mounting hole, and the connector is provided with the 5th mounting hole, and the 4th locking member is worn
The 4th mounting hole and the 5th mounting hole are crossed, the 3rd body is fixedly connected with connector.
11. the winged control test device as described in any one in claim 1 to 6, it is characterised in that the first rotating shaft edge is perpendicular
Nogata is to setting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720111476.1U CN206494143U (en) | 2017-02-06 | 2017-02-06 | Fly control test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720111476.1U CN206494143U (en) | 2017-02-06 | 2017-02-06 | Fly control test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206494143U true CN206494143U (en) | 2017-09-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720111476.1U Active CN206494143U (en) | 2017-02-06 | 2017-02-06 | Fly control test device |
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| Country | Link |
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| CN (1) | CN206494143U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108128480A (en) * | 2017-11-28 | 2018-06-08 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine lower-grade fuel bracket car |
| CN109367819A (en) * | 2018-12-05 | 2019-02-22 | 智灵飞（北京）科技有限公司 | One kind being used for rotor wing unmanned aerial vehicle attitude-simulating system and method |
| CN109720600A (en) * | 2018-12-18 | 2019-05-07 | 武汉科技大学 | Unmanned plane test platform |
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2017
- 2017-02-06 CN CN201720111476.1U patent/CN206494143U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108128480A (en) * | 2017-11-28 | 2018-06-08 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine lower-grade fuel bracket car |
| CN108128480B (en) * | 2017-11-28 | 2021-03-23 | 中国航发沈阳黎明航空发动机有限责任公司 | Bracket vehicle for fuel accessories of aircraft engine |
| CN109367819A (en) * | 2018-12-05 | 2019-02-22 | 智灵飞（北京）科技有限公司 | One kind being used for rotor wing unmanned aerial vehicle attitude-simulating system and method |
| CN109720600A (en) * | 2018-12-18 | 2019-05-07 | 武汉科技大学 | Unmanned plane test platform |
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