CN208298022U - The tilt angle detection device and control system of aircraft tilting rotor - Google Patents
The tilt angle detection device and control system of aircraft tilting rotor Download PDFInfo
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- CN208298022U CN208298022U CN201821018762.4U CN201821018762U CN208298022U CN 208298022 U CN208298022 U CN 208298022U CN 201821018762 U CN201821018762 U CN 201821018762U CN 208298022 U CN208298022 U CN 208298022U
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- tilt angle
- mandril
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Abstract
The utility model discloses a kind of tilt angle detection devices of aircraft tilting rotor, including arcuation resistance, are sheathed on aircraft and vert on horn and rotate synchronously；Mandril is fixedly installed in rack and conducts with arcuation resistance；Measure loop, the resistance between one end and mandril for detecting arcuation resistance is with the tilt angle for the horn that obtains verting.The invention also discloses a kind of detection device, including arcuation resistance, it is sheathed in rack and insulate with rack；Mandril is fixedly installed in and verts on horn, conducts with arcuation resistance；Measure loop, the resistance between one end and mandril for detecting arcuation resistance is with the tilt angle for the horn that obtains verting.The invention also discloses a kind of control system, including control unit and detection device as described above, the tilt angle that control unit is detected according to detection device carries out the closed-loop control of tilt angle to tilting rotor.The detection device and control system of the utility model all have the advantages that detection is accurate.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to a kind of tilt angle detection of aircraft tilting rotor
Device and control system.
Background technique
As the improvement of people's living standards, for recreation and amusement, producing the small aircraft of purposes increasingly by people
Attention.Currently, small aircraft is used to carry various measuring instruments (such as camera) mostly, aerological sounding or high-altitude are carried out
On object is thrown, it can apply in various fields such as agricultural, detection, meteorological, hazard forecasting and rescues.
Existing aircraft is divided into Fixed Wing AirVehicle and two kinds of rotor craft.Fixed Wing AirVehicle mainly passes through acquisition
Larger initial velocity forms lift in aerofoil and realizes flight, but can not hover, and stability is poor when low speed, be easy because stall and
Air crash, and need biggish ground run distance.Another is rotor craft, and wherein rotor is primarily used to form lift, is flown
Scanning frequency degree needs form lateral resultant force by adjusting posture and are just able to achieve, so as to cause energy consumption is larger and route speed compared with
It is low.There is less producer to design dependency structure at present to be adjusted with the direction to rotor, due to rotor craft spiral arm and its
Between executing agency, is connected by components such as shaft coupling, transmission gears, due to manufacturing, assembling equal error, executing agency is caused to stop
Only under state, spiral arm has biggish rotation surplus, in flight due to the judder of spiral arm, controls to the tilt angle of flight
Difficulty is brought, and spiral arm connecting component may be caused, fatigue failure occurs, causes aircraft accident.
Utility model content
The technical problems to be solved in the utility model is that for technical problem of the existing technology, this is practical new
Type provides a kind of tilt angle detection device and control system for detecting accurately aircraft tilting rotor.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
A kind of tilt angle detection device of aircraft tilting rotor, including
Arcuation resistance is sheathed on aircraft and verts on horn, insulate with the horn that verts and turns with the horn that verts is synchronous
It is dynamic；
Mandril is fixedly installed in the rack of aircraft and insulate with rack, and the arcuation Ohmic contact and conducts；
Measure loop, one end are connected with one end of the arcuation resistance, and the other end is connected with the mandril, for detecting arc
Resistance between one end and mandril of shape resistance is with the tilt angle for the horn that obtains verting.
As a further improvement of the above technical scheme:
The mandril is installed in the rack by mounting assembly, and the mounting assembly includes mounting rack, sleeve and pressure
Contracting spring, the mounting rack are fixedly installed in the rack, and the sleeve is installed on the mounting rack, and the one of the mandril
End be slidedly arranged in the cavity of the sleeve, the compressed spring be located at the hollow cavity of sleeve bottom and mandril end it
Between, for making the other end of mandril and the arcuation resistance resilient abutment.
The mandril includes mandril ontology and thimble portion, and the one end in the thimble portion is connected with mandril ontology fastening,
The other end and the arcuation Ohmic contact, the arcuation resistance are equipped with the arc groove matched with thimble portion.
The thimble portion is thimble made of conductive material, and the mandril ontology is mandril ontology made of rubber material.
The arcuation resistance is installed on described vert on horn by cyclic annular cutting ferrule；The ring-type cutting ferrule includes inner ring and outer
Circle, the inner ring be anchored on it is described vert on horn, the arcuation resistance card is set between the inner ring and outer ring.
The ring-type cutting ferrule is cutting ferrule made of rubber material.
The invention also discloses a kind of tilt angle detection devices of aircraft tilting rotor, including
Arcuation resistance is sheathed in the rack of aircraft and insulate with rack；
Mandril is fixedly installed in aircraft and verts on horn, insulate with the horn that verts, with the arcuation Ohmic contact
And it conducts；
Measure loop, one end are connected with one end of the arcuation resistance, and the other end is connected with the mandril, for detecting arc
Resistance between one end and mandril of shape resistance is with the tilt angle for the horn that obtains verting.
The invention also discloses a kind of tilt angle control system of aircraft tilting rotor, including control unit and
The tilt angle detection device of aircraft tilting rotor as described above, described control unit is according to the aircraft tilting rotor
Tilt angle detection device detection tilt angle to tilting rotor carry out tilt angle closed-loop control.
Compared with the prior art, the advantages of the utility model are:
The tilt angle detection device and control system of the aircraft tilting rotor of the utility model, pass through measure loop pair
Resistance between arcuation resistance and mandril measures, and conversion obtains verting the actual rotation angle of horn, so as to obtain
Vert the practical tilt angle of horn, is accurately controlled convenient for the tilting rotor to aircraft；And arcuation resistance cooperates
The mode of mandril, structure is simple, convenient for disassembly and assembly and be easily achieved.
Detailed description of the invention
Fig. 1 is the detection device three-dimensional structure diagram of the utility model.
Fig. 2 is the detonation configuration figure of the detection device of the utility model.
Fig. 3 is the implementation example figure of the detection device of the utility model in specific application.
Fig. 4 is the control system architecture schematic diagram of the utility model.
Figure label indicates: 1, detection device；11, arcuation resistance；111, cyclic annular cutting ferrule；112, arc groove；12, it pushes up
Bar；121, mandril ontology；122, thimble portion；113, mounting rack；114, sleeve；115, compressed spring；2, control unit；3, it verts
Horn；4, rack.
Specific embodiment
The utility model is further described below in conjunction with Figure of description and specific embodiment.
As shown in Figure 1 to Figure 3, the tilt angle detection device of the aircraft tilting rotor of the present embodiment is applied to flight
On the tilting rotor of motor, hovercar or unmanned plane, the tilt angle of tilting rotor is detected, tilting rotor with vert
Horn 3 is connected, and the horn 3 that verts then is rotatablely installed in (being arranged with bearing on the horn 3 that such as verts, bearing is mounted on rack in rack 4
On 4 bearing block).Tilt angle detection device 1 specifically includes arcuation resistance 11, is arranged and is anchored on aircraft and verts horn 3
On, it insulate with the horn 3 that verts and is rotated synchronously with the horn 3 that verts；Mandril 12, be fixedly installed in the rack 4 of aircraft and with
Rack 4 insulate, and one end of mandril 12 contacts and conducts with arcuation resistance 11；The one of measure loop, one end and arcuation resistance 11
End is connected, and the other end is connected with mandril 12, (or electric for detecting the resistance between one end of arcuation resistance 11 and mandril 12
Stream, voltage etc.) with the tilt angle for the horn 3 that obtains verting.Certainly, in other embodiments, can also to arcuation resistance 11 with
The installation site of mandril 12 is exchanged, and specific mounting means is constant.The tilt angle of the aircraft tilting rotor of the utility model
Detection device is spent, the resistance between arcuation resistance 11 and mandril 12 is measured by measure loop, conversion obtains the machine that verts
The actual rotation angle of arm 3, so as to the practical tilt angle for the horn 3 that obtains verting, convenient for the tilting rotor to aircraft
It is accurately controlled；And arcuation resistance 11 cooperates the mode of mandril 12, and structure is simple, convenient for disassembly and assembly and be easily achieved.
In the present embodiment, mandril 12 is installed in rack 4 by mounting assembly.Mounting assembly includes mounting rack 113, sleeve
114 and compressed spring 115, mounting rack 113 is fixedly installed in rack 4 close to side (such as bearing block for the horn 3 that verts by screw
On), sleeve 114 is installed on mounting rack 113 (such as sleeve 114 is integrated with mounting rack 113 to be formed), and one end cunning of mandril 12 is set
In in the cavity of sleeve 114, compressed spring 115 is located between the bottom of the hollow cavity of sleeve 114 and the end of mandril 12, uses
In the other end and 11 resilient abutment of arcuation resistance that force mandril 12.Wherein mandril 12 includes mandril ontology 121 and thimble portion
122, the one end in thimble portion 122 is connected with the fastening of mandril ontology 121, and the other end is contacted with arcuation resistance 11.Wherein thimble portion 122
For conductive metal material (such as copper), mandril ontology 121 is nonconducting plastic material, can pass through the side such as bonding between the two
Formula connection.Mounting rack 113 and sleeve 114 are also made of nonconducting plastic material.In addition, in order to guarantee thimble portion 122 with
The reliable contacts of arcuation resistance 11 can be provided with arc groove 112 on arcuation resistance 11, rotate in arcuation resistance 11 same
When, thimble portion 122 is then equivalent to be slided in arc groove 112, guarantees good contact.Certainly, in other embodiments, push up
Other mutually matched modes can also be used between needle portion 122 and arcuation resistance 11, as being provided with protrusion on arcuation resistance 11
Portion is provided with corresponding groove etc. in thimble portion 122.
In the present embodiment, arcuation resistance 11 is installed on by cyclic annular cutting ferrule 111 to vert on horn 3；Cyclic annular cutting ferrule 111 includes
Inner ring and outer ring, and be that rubber material is made, inner ring, which is anchored on, to vert on horn 3, and arcuation resistance 11 is arranged in inner ring and outer
Between circle.If the side of inner ring is provided with ring-shaped step, arcuation resistance 11 is placed between inner ring and outer ring, then passes through the other side
Plastics circlip limited.Certainly, in other embodiments, arcuation resistance 11 can also be carried out using other limit methods
It fixes.
As shown in figure 3, the utility model further correspondingly discloses a kind of tilt angle control system of aircraft tilting rotor,
Tilt angle detection device 1 including control unit 2 and aircraft tilting rotor as described above, control unit 2 is according to flight
The tilt angle that the tilt angle detection device 1 of device tilting rotor detects carries out the closed-loop control of tilt angle to tilting rotor.
Since the tilt angle to the horn 3 that verts directly is detected (since there are shaft couplings, biography between actuator and the horn 3 that verts
Motivation structure etc.), so as to obtain comparing accurately tilt angle, consequently facilitating being carried out to the tilting rotor of aircraft accurate
Control.
The utility model further discloses a kind of tilt angle control based on aircraft tilting rotor as described above
The control method of system, comprising the following steps:
S01, during tilting rotor is verted, pass through the tilt angle detection device 1 of aircraft tilting rotor
The tilt angle that the tilt angle for the horn 3 that verts is measured in real time, and will test is sent to control unit 2；
S02, control unit 2 are adjusted to realize and close the tilt angle of tilting rotor according to the tilt angle of detection
Ring control.
In the present embodiment, it will test tilt angle compared with the default tilt angle of output, obtain difference, be judged to verting
The deviation tilt angle of rotor, i.e., due to components such as transmission gear, shaft coupling, bearings between actuator and the horn 3 that verts
Misalignment angle caused by manufacture, assembly equal error, to facilitate operator to understand each component operation when obtaining misalignment angle
Situation, to carry out upkeep operation in time with each component.
Above are merely preferred embodiments of the utility model, the protection scope of the utility model is not limited merely to above-mentioned
Embodiment, technical solution belonging to the idea of the present invention belong to the protection scope of the utility model.It should be pointed out that pair
For those skilled in the art, several improvements and modifications without departing from the principle of the utility model,
It should be regarded as the protection scope of the utility model.
Claims (8)
1. a kind of tilt angle detection device of aircraft tilting rotor, which is characterized in that including
Arcuation resistance (11) is sheathed on aircraft and verts on horn (3), insulate with the horn that verts (3) and with the horn that verts
(3) it rotates synchronously；
Mandril (12) is fixedly installed in the rack (4) of aircraft and insulate with rack (4), connects with the arcuation resistance (11)
It touches and conducts；
Measure loop, one end are connected with one end of the arcuation resistance (11), and the other end is connected with the mandril (12), for examining
The resistance surveyed between the one end and mandril (12) of arcuation resistance (11) is with the tilt angle for horn (3) that obtain verting.
2. the tilt angle detection device of aircraft tilting rotor according to claim 1, which is characterized in that the mandril
(12) it is installed on the rack (4) by mounting assembly, the mounting assembly includes mounting rack (113), sleeve (114) and pressure
Contracting spring (115), the mounting rack (113) are fixedly installed on the rack (4), and the sleeve (114) is installed on the peace
It shelves on (113), one end of the mandril (12) is slidedly arranged in the cavity of the sleeve (114), compressed spring (115) position
Between the bottom of the hollow cavity of sleeve (114) and the end of mandril (12), for make the other end of mandril (12) with it is described
Arcuation resistance (11) resilient abutment.
3. the tilt angle detection device of aircraft tilting rotor according to claim 2, which is characterized in that the mandril
It (12) include mandril ontology (121) and thimble portion (122), one end of the thimble portion (122) and the mandril ontology (121) are tight
Solid phase connects, and the other end is contacted with the arcuation resistance (11), and the arcuation resistance (11) is equipped with and matches with thimble portion (122)
Arc groove (112).
4. the tilt angle detection device of aircraft tilting rotor according to claim 3, which is characterized in that the thimble
Portion (122) is thimble portion made of conductive material, and the mandril ontology (121) is mandril ontology made of rubber material.
5. the tilt angle detection device of aircraft tilting rotor as claimed in any of claims 1 to 4, feature
It is, the arcuation resistance (11) passes through cyclic annular cutting ferrule (111) and be installed on described vert on horn (3)；The ring-type cutting ferrule
(111) include inner ring and outer ring, the inner ring be anchored on it is described vert on horn (3), the arcuation resistance (11) is arranged in institute
It states between inner ring and outer ring.
6. the tilt angle detection device of aircraft tilting rotor according to claim 5, which is characterized in that the ring-type
Cutting ferrule (111) is cutting ferrule made of rubber material.
7. a kind of tilt angle detection device of aircraft tilting rotor, which is characterized in that including
Arcuation resistance (11) is sheathed in the rack (4) of aircraft and insulate with rack (4)；
Mandril (12) is fixedly installed in aircraft and verts on horn (3), insulate with the horn that verts (3), with the arcuation electricity
Resistance (11) is contacted and is conducted；
Measure loop, one end are connected with one end of the arcuation resistance (11), and the other end is connected with the mandril (12), for examining
The resistance surveyed between the one end and mandril (12) of arcuation resistance (11) is with the tilt angle for horn (3) that obtain verting.
8. a kind of tilt angle control system of aircraft tilting rotor, which is characterized in that including control unit (2) and such as right
It is required that the tilt angle detection device (1) of aircraft tilting rotor described in any one of 1 to 7, described control unit (2) root
Tilt angle is carried out to tilting rotor according to the tilt angle that the tilt angle detection device (1) of the aircraft tilting rotor detects
Closed-loop control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018762.4U CN208298022U (en) | 2018-06-29 | 2018-06-29 | The tilt angle detection device and control system of aircraft tilting rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821018762.4U CN208298022U (en) | 2018-06-29 | 2018-06-29 | The tilt angle detection device and control system of aircraft tilting rotor |
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| Publication Number | Publication Date |
|---|---|
| CN208298022U true CN208298022U (en) | 2018-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821018762.4U Active CN208298022U (en) | 2018-06-29 | 2018-06-29 | The tilt angle detection device and control system of aircraft tilting rotor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108572664A (en) * | 2018-06-29 | 2018-09-25 | 长沙市云智航科技有限公司 | Tilt angle detection device, control system and the method for aircraft tilting rotor |
-
2018
- 2018-06-29 CN CN201821018762.4U patent/CN208298022U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108572664A (en) * | 2018-06-29 | 2018-09-25 | 长沙市云智航科技有限公司 | Tilt angle detection device, control system and the method for aircraft tilting rotor |
| CN108572664B (en) * | 2018-06-29 | 2023-08-04 | 长沙市云智航科技有限公司 | Tilting angle detection device, control system and method for tilting rotor wing of aircraft |
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