CN111959820B - Gap detection method for folding wings of high aspect ratio unmanned aerial vehicle - Google Patents
Gap detection method for folding wings of high aspect ratio unmanned aerial vehicle Download PDFInfo
- Publication number
- CN111959820B CN111959820B CN202010637691.1A CN202010637691A CN111959820B CN 111959820 B CN111959820 B CN 111959820B CN 202010637691 A CN202010637691 A CN 202010637691A CN 111959820 B CN111959820 B CN 111959820B
- Authority
- CN
- China
- Prior art keywords
- folding
- test tool
- mechanism assembly
- gap
- unfolding mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
According to the method, a test tool is designed and installed on the folding and unfolding mechanism assembly, rotation gap measurement and up-down shaking gap measurement are respectively carried out, and the influence of tool deflection is considered to correct measurement data. The invention can simply, quickly and effectively detect the system clearance of the folding and unfolding mechanism assembly. After the gap of the folding wing system is accurately measured, on one hand, the gap of the folding wing system can be quantitatively analyzed and controlled, and on the other hand, the problems of high rejection rate, high processing difficulty and high cost caused by blindly tightening mechanical dimensional deviation of each matching piece can be avoided after the gap is quantitatively analyzed and controlled.
Description
Technical Field
The invention belongs to the field of high-aspect-ratio fixed wing unmanned aerial vehicles, and particularly relates to a gap detection method for a folding wing.
Background
In recent years, the market size of unmanned aerial vehicles is increased year by year, and the unmanned aerial vehicle has a large application space in the fields of military, scientific research, government, commercial activities, personal consumer products and the like. Most unmanned aerial vehicles are fixed wing layout, but the storage and transportation of the unmanned aerial vehicles are inconvenient due to the structure, so that the wings of the fixed wing unmanned aerial vehicles are folded during storage and transportation, and then are unfolded under the action of a power element during use, so that the unmanned aerial vehicle becomes an effective scheme for solving the problems.
After the wing of the fixed-wing unmanned aerial vehicle is folded, the required space can be reduced to the maximum extent, and the fixed-wing unmanned aerial vehicle has very important effects of improving the transportation and storage of the unmanned aerial vehicle, reducing the size of a packing box and the like; especially in the military application field, the adaptability with the carrier can be enhanced, the number of the carriers which can be mounted on the carrier is increased, and the fight capacity of the carrier is improved.
The mechanism assembly for folding and unfolding the wing needs to be provided with an unfolding implementation mechanism, a locking mechanism after unfolding and an unfolding driving force. Firstly, wing unfolding is a process of rotating around a wing shaft, in order to rotate the wing, moment needs to be applied to the wing, and an implementation mechanism is generally a gear mechanism or a link mechanism; after the device is unfolded in place, a spring pin is generally required to be arranged for position locking; the driving force during deployment may be selected from springs, compressed gas, electric motors, and the like.
In summary, the structure of the mechanism assembly for the folding and unfolding functions of the wing is complex. The assembly is a movable mechanism, a system gap is unavoidable, and meanwhile, the gap size has great influence on the function and performance of the mechanism. Too small a gap may cause movement jamming of the mechanism, causing dysfunction; the too large gap can cause the change of the sweepback angle and the dihedral angle (or the dihedral angle) of the wing after the wing span is opened in place, the sweepback wing is turned up and is more serious along with the increase of the aspect ratio, the aerodynamic characteristics of the aircraft are adversely affected, the flight attitude of the aircraft is further affected, and the flight failure is seriously caused.
In the existing engineering application, because test flight test failure caused by the clearance of the folding wing system frequently happens, engineers improve the clearance by continuously increasing the mechanical dimensional deviation of each matching piece in the mechanism assembly, and the measurement of the system clearance of the folding and unfolding mechanism assembly does not propose an effective detection technology. In the prior art, the detection of the relevant clearance of the control surface of the airplane is carried out, but the detection of the clearance of the control surface of the airplane is not completely suitable for a folding wing system, and the detection system used in the detection process is huge and complex; in addition, in the prior art, the research and analysis on the flutter caused by the clearance of the wing surface folding system are carried out, but the clearance of the folding system is inconsistent with the generation principle of the folding wing clearance of the unmanned aerial vehicle, and the corresponding detection method is not applicable.
Disclosure of Invention
Aiming at the gap problem of the folding and unfolding mechanism assembly of the fixed-wing unmanned aerial vehicle with the large aspect ratio, the invention provides a wing gap detection method, which mainly detects the up-and-down shaking gap and the front-and-back (the heading of the unmanned aerial vehicle is the front) rotating gap after the wing is unfolded in place, thereby providing data support for gap control of the folding wing and enabling the key characteristics of the folding wing of the unmanned aerial vehicle to realize quantitative analysis.
The technical scheme of the invention is as follows:
the gap detection method of the folding wing of the high aspect ratio unmanned aerial vehicle is characterized by comprising the following steps of: the method comprises the following steps:
step 1: the test tool and the folding and unfolding mechanism assembly are assembled, and the connection is stable and reliable;
the interface structure used for being connected with the folding and unfolding mechanism assembly in the test fixture is the same as the interface structure used for being connected with the folding and unfolding mechanism assembly in the folding wing, and the deviation design of the interface structure is also the same;
step 2: fixing the assembled test tool and the folding and unfolding mechanism assembly on a horizontal table top, so that the folding and unfolding mechanism assembly cannot move in position in the detection process, and setting the folding and unfolding mechanism assembly to be in an unfolded and locked state; and respectively performing rotation clearance measurement and up-down shaking clearance measurement:
and (3) measuring a rotation clearance:
selecting a certain point on one end of the test tool, which is far away from the folding and unfolding mechanism assembly, as an observation point, driving the test tool to rotate to a limit position around a rotating shaft seat in the folding and unfolding mechanism assembly, recording the point A at the moment, driving the test tool to rotate to the limit position around the rotating shaft seat in the folding and unfolding mechanism assembly in the opposite direction, recording the point B at the moment, and obtaining the angle between the point AB and the central point of the rotating shaft seat as a rotating gap initial value theta of the folding and unfolding mechanism assembly AB ；
When the test tool is driven to rotate to two limit positions around a rotating shaft seat in the folding and unfolding mechanism assembly, measuring the horizontal force applied to the test tool when the observation point position is recorded;
and (3) measuring up-and-down shaking gaps:
one end of the test tool, which is far away from the folding and unfolding mechanism assembly, is pressed down to a limit position, the point C of the observation point at the moment is recorded, one end of the test tool, which is far away from the folding and unfolding mechanism assembly, is lifted up to the limit position, the point D of the observation point at the moment is recorded, and the angles of the two points CD and the center point of the rotating shaft seat are obtained and are used as the initial value theta of the up-down shaking gap of the folding and unfolding mechanism assembly CD ；
When one end of the driving test tool far away from the folding and unfolding mechanism assembly is pressed down and lifted up to two limit positions, measuring the force of pressing down and lifting up the test tool;
step 3: correction of measurement data
Correcting and calculating deflection of the test tool, namely calculating rotating deflection of the test tool and up-and-down shaking deflection of the tool, respectively obtaining rotating angles generated by deflection factors of the tool when the test tool is positioned at two sides and at upper and lower limiting positions, and respectively subtracting corresponding rotating angles generated by deflection factors of the tool from a rotating gap initial value and an up-and-down shaking gap initial value obtained in the step 2 to obtain a rotating gap and an up-and-down shaking gap of the final unmanned aerial vehicle folding and unfolding mechanism assembly.
In step 1, the rigidity of the test tool is enabled to meet the design requirement by selecting the test tool material and adopting a hollow and internal frame structure form in the structural design.
Further, in step 1, the length of the test tool along the span direction of the machine is greater than the span length of the folding wing.
Further, in step 2, by measuring the distance between AB and combining the distance from the observation point to the center point of the rotating shaft seat, the central angle with the two points AB as the arc point and the center point of the rotating shaft seat as the center point is calculated and obtained as the initial value θ of the rotation gap of the folding and unfolding mechanism assembly AB The method comprises the steps of carrying out a first treatment on the surface of the By measuring the distance between the CDs and combining the distance from the observation point to the center point of the rotating shaft seat, calculating to obtain the central angle taking the two points of the CD as the circular arc points and the center point of the rotating shaft seat as the center point, and taking the central angle of the center point of the rotating shaft seat as the initial value theta of the up-down shaking gap of the folding and unfolding mechanism assembly CD 。
Further, in step 3, a corresponding rotation angle generated by testing the deflection factor of the tool is calculated, and is obtained through equivalent calculation:
the equivalent calculation uses a typical cantilever beam as a model and utilizes a formula
Calculating the outer end rotation angle of the tool, wherein F is the outer end loading force, and calculatingThe force applied to the test tool, which is recorded when the test tool obtained in the step 2 is positioned at the limit position, is adopted, c is the arm length of the loading force, and EI is the bending rigidity of the test tool; when the test tool is positioned at the limit positions on two sides according to the formula, the corresponding rotation angle theta generated by the deflection factor of the test tool is calculated 1 ，θ 2 And when the test tool is positioned at the upper limit position and the lower limit position, the corresponding rotation angle theta is generated due to the deflection factor of the test tool 3 ，θ 4 The rotation clearance of the finally obtained unmanned aerial vehicle folding and unfolding mechanism assembly is theta AB -θ 1 -θ 2 The up-and-down shaking gap is theta CD -θ 3 -θ 4 。
Further, in step 3, a corresponding rotation angle generated by testing the deflection factor of the tool is calculated, and is obtained through simulation calculation: and (3) establishing a three-dimensional model of the test tool in the three-dimensional configuration software, adopting end fixing and supporting constraint, and performing simulation calculation on the force applied by the test tool by utilizing the force recorded when the test tool obtained in the step (2) is positioned at the limit position, so as to obtain the rotation angle generated by the deflection factor of the tool when the test tool is positioned at the two sides and the upper and lower limit positions, and further obtain the rotation gap and the up and down shaking gap of the final unmanned aerial vehicle folding and unfolding mechanism assembly.
Advantageous effects
Compared with the prior art, the invention has the beneficial effects that: the system clearance of the folding and unfolding mechanism assembly can be simply, quickly and effectively detected. After the gap of the folding wing system is accurately measured, on one hand, the gap of the folding wing system can be quantitatively analyzed and controlled, and on the other hand, the problems of high rejection rate, high processing difficulty and high cost caused by blindly tightening mechanical dimensional deviation of each matching piece can be avoided after the gap is quantitatively analyzed and controlled.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
The foregoing and/or additional aspects and advantages of the invention will become apparent and may be better understood from the following description of embodiments taken in conjunction with the accompanying drawings in which:
fig. 1: a rotational gap schematic;
fig. 2: schematic diagram of up-and-down shaking gap.
Wherein: 1. a rotating shaft seat; 2. testing a tool; 3. and the folding and unfolding mechanism assembly.
Detailed Description
The invention provides a gap detection method which is easy to operate, low in cost, high in speed and high in precision and focuses on the importance of gap control of a folding wing on a fixed wing unmanned aerial vehicle with a large aspect ratio. Meanwhile, the gap detection method is also applicable to fixed wing unmanned aerial vehicles with small aspect ratios.
The pneumatic layout of the folding wing comprises a conventional layout, a simple tandem wing layout, a duck wing, a diamond back, a folding wing and the like, but the gap detection technology provided by the invention is applicable to the folding wing with each pneumatic layout.
The following detailed description of embodiments of the invention is exemplary and intended to be illustrative of the invention and not to be construed as limiting the invention.
In this embodiment, the gap detection method for a folding and unfolding mechanism assembly of an unmanned aerial vehicle includes the steps of:
step 1: the test tool and the folding and unfolding mechanism assembly are assembled, and the connection is stable and reliable; the interface structure used for being connected with the folding and unfolding mechanism assembly in the test fixture is the same as the interface structure used for being connected with the folding and unfolding mechanism assembly in the folding wing, and the deviation design of the interface structure is also the same.
In the method, the clearance measurement is carried out by utilizing the modes of front-back rotation and up-down shaking of the test tool, so that the influence of the deflection of the test tool on the detection result is reduced as much as possible, the test tool is made of materials with higher rigidity, and the rigidity of the tool is improved by adopting a hollow and internal frame structure mode in structural design.
In addition, according to the principle that the angle is fixed, the arc chord length is larger when the radius is larger, the length of the test tool in the machine span direction is longer than that of the folding wing per se, so that the clearance angle can be measured more accurately. Of course, the length of the test tool is increased and the rigidity of the test tool is ensured to be contradictory, so that the length of the test tool is not infinitely increased, the length of the test tool in the machine span direction is 1.5 times of the length of the folding wing per se, and the rigidity requirement of the tool is met by combining the material and structural design of the test tool per se.
Step 2: fixing the assembled test tool and the folding and unfolding mechanism assembly on a horizontal table top, ensuring that the folding and unfolding mechanism assembly cannot move in position in the detection process, and setting the folding and unfolding mechanism assembly to be in an unfolded and locked state; and respectively performing rotation clearance measurement and up-down shaking clearance measurement:
and (3) measuring a rotation clearance:
and selecting a certain point on one end of the test tool, which is far away from the folding and unfolding mechanism assembly, as an observation point, driving the test tool to rotate to a limit position around a rotating shaft seat in the folding and unfolding mechanism assembly, recording the point A at the moment, driving the test tool to rotate to the limit position around the rotating shaft seat in the folding and unfolding mechanism assembly in the opposite direction, and recording the point B at the moment, so as to obtain the angle between the point AB and the central point of the rotating shaft seat, and taking the angle as a rotating gap initial value of the folding and unfolding mechanism assembly.
In practical measurement, it is difficult to directly measure the angle, so in this embodiment, the distance between AB is measured by using the vernier caliper, and the distance between the observation point and the center point of the rotating shaft seat is combined, so as to calculate and obtain the initial value θ of the rotation gap using the two points AB as arc points and the center point of the rotating shaft seat as the center point AB 。
In addition, in order to carry out data correction of the next step, when the test tool is driven to rotate to two limit positions around a rotating shaft seat in the folding and unfolding mechanism assembly, in order to keep the test tool at the limit positions, horizontal force is applied to the test tool, and the force applied to the test tool when the position of an observation point is recorded is measured by adopting a dynamometer.
And (3) measuring up-and-down shaking gaps:
selecting a certain point on one end of the test tool, which is far away from the folding and unfolding mechanism assembly, as an observation point, pressing one end of the test tool, which is far away from the folding and unfolding mechanism assembly, down to a limit position, recording the point C at the observation point, lifting the end of the test tool, which is far away from the folding and unfolding mechanism assembly, up to the limit position, recording the point D at the observation point, and obtaining the angles between two points of CD and the center point of the rotating shaft seat, and taking the angles as an initial value theta of an up-down shaking gap of the folding and unfolding mechanism assembly CD 。
Similarly, in this embodiment, the distance between CDs is measured by using the height ruler, and the distance from the observation point to the center point of the rotating shaft seat is combined, so that the central angle with the two points of CD as arc points and the center point of the rotating shaft seat as the center point is calculated and obtained as the initial value of the up-down shaking gap of the folding and unfolding mechanism assembly.
In addition, in order to correct data in the next step, when one end of the driving test tool far away from the folding and unfolding mechanism assembly is pressed down and lifted up to two limit positions, a dynamometer is adopted to measure the force of the pressing down and lifting up test tool.
Step 3: correction of measurement data
In step 1, the tool with higher rigidity is adopted to avoid the influence of the deflection of the test tool on the measurement precision, but because the actual length of the test tool is larger than the length of the folding wing in order to improve the measurement precision from the angle of test data, correction calculation is needed to be carried out on the deflection of the test tool, the calculation comprises calculation of the rotation deflection of the test tool and calculation of the deflection of the tool in the vertical direction, and when the test tool is positioned at two sides and in the vertical limit position, the rotation angle generated by the deflection factors of the tool is obtained respectively, and the corresponding rotation angle generated by subtracting the deflection factors of the tool from the initial value of the rotation gap and the initial value of the vertical swing gap obtained in step 2 is used to obtain the rotation gap and the vertical swing gap of the final unmanned aerial vehicle folding and unfolding mechanism assembly.
The corresponding rotation angle generated by testing the deflection factor of the tool can be calculated through equivalent calculation or simulation calculation.
The equivalent calculation uses a typical cantilever beam as a model and utilizes a formula
Calculating the outer end rotation angle of the tool, wherein F is the outer end loading force, the force applied to the test tool recorded when the test tool obtained in the step 2 is located at the limit position is adopted in calculation, c is the arm length of the loading force, in the embodiment, the length from the observation point to the interface between the test tool and the folding and unfolding mechanism assembly is the length, and EI is the bending rigidity of the test tool. When the test tool is positioned at the limit positions of the two sides, the corresponding rotation angle theta generated by the deflection factor of the test tool is calculated 1 ，θ 2 And when the test tool is positioned at the upper limit position and the lower limit position, the corresponding rotation angle theta is generated due to the deflection factor of the test tool 3 ，θ 4 In this way, the rotation clearance of the finally obtained unmanned aerial vehicle folding and unfolding mechanism assembly is theta AB -θ 1 -θ 2 The up-and-down shaking gap is theta CD -θ 3 -θ 4 。
And through simulation calculation, a three-dimensional model of the test tool is built in three-dimensional configuration software, end fixing constraint is adopted, simulation calculation is carried out on the force applied by the test tool by using the force recorded when the test tool obtained in the step 2 is positioned at the limit position, and the rotation angle generated by the deflection factor of the tool when the test tool is positioned at the two sides and the upper and lower limit positions is obtained, so that the rotation gap and the upper and lower shaking gap of the final unmanned aerial vehicle folding and unfolding mechanism assembly are obtained.
Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations may be made in the above embodiments by those skilled in the art without departing from the spirit and principles of the invention.
Claims (6)
1. A gap detection method of a folding wing of a high aspect ratio unmanned aerial vehicle is characterized by comprising the following steps: the method comprises the following steps:
step 1: the test tool and the folding and unfolding mechanism assembly are assembled, and the connection is stable and reliable;
the interface structure used for being connected with the folding and unfolding mechanism assembly in the test fixture is the same as the interface structure used for being connected with the folding and unfolding mechanism assembly in the folding wing, and the deviation design of the interface structure is also the same;
step 2: fixing the assembled test tool and the folding and unfolding mechanism assembly on a horizontal table top, so that the folding and unfolding mechanism assembly cannot move in position in the detection process, and setting the folding and unfolding mechanism assembly to be in an unfolded and locked state; and respectively performing rotation clearance measurement and up-down shaking clearance measurement:
and (3) measuring a rotation clearance:
selecting a certain point on one end of the test tool, which is far away from the folding and unfolding mechanism assembly, as an observation point, driving the test tool to rotate to a limit position around a rotating shaft seat in the folding and unfolding mechanism assembly, recording the point A at the moment, driving the test tool to rotate to the limit position around the rotating shaft seat in the folding and unfolding mechanism assembly in the opposite direction, recording the point B at the moment, and obtaining the angle between the point AB and the central point of the rotating shaft seat as a rotating gap initial value theta of the folding and unfolding mechanism assembly AB ；
When the test tool is driven to rotate to two limit positions around a rotating shaft seat in the folding and unfolding mechanism assembly, measuring the horizontal force applied to the test tool when the observation point position is recorded;
and (3) measuring up-and-down shaking gaps:
one end of the test tool, which is far away from the folding and unfolding mechanism assembly, is pressed down to a limit position, the point C of the observation point at the moment is recorded, one end of the test tool, which is far away from the folding and unfolding mechanism assembly, is lifted up to the limit position, the point D of the observation point at the moment is recorded, and the angles of the two points CD and the center point of the rotating shaft seat are obtained and are used as the initial value theta of the up-down shaking gap of the folding and unfolding mechanism assembly CD ；
When one end of the driving test tool far away from the folding and unfolding mechanism assembly is pressed down and lifted up to two limit positions, measuring the force of pressing down and lifting up the test tool;
step 3: correction of measurement data
Correcting and calculating deflection of the test tool, namely calculating rotating deflection of the test tool and up-and-down shaking deflection of the tool, respectively obtaining rotating angles generated by deflection factors of the tool when the test tool is positioned at two sides and at upper and lower limiting positions, and respectively subtracting corresponding rotating angles generated by deflection factors of the tool from a rotating gap initial value and an up-and-down shaking gap initial value obtained in the step 2 to obtain a rotating gap and an up-and-down shaking gap of the final unmanned aerial vehicle folding and unfolding mechanism assembly.
2. The gap detection method for the folding wings of the high aspect ratio unmanned aerial vehicle according to claim 1, wherein the gap detection method comprises the following steps: in the step 1, the rigidity of the test tool meets the design requirement by selecting the materials of the test tool and adopting a hollow and internal frame structure form in the structural design.
3. The gap detection method for the folding wings of the high aspect ratio unmanned aerial vehicle according to claim 1, wherein the gap detection method comprises the following steps: in the step 1, the length of the test tool along the span direction of the machine is larger than the span direction length of the folding wing.
4. The gap detection method for the folding wings of the high aspect ratio unmanned aerial vehicle according to claim 1, wherein the gap detection method comprises the following steps: in step 2, by measuring the distance between AB and combining the distance from the observation point to the center point of the rotating shaft seat, calculating to obtain a central angle taking AB two points as arc points and the center point of the rotating shaft seat as the center point as a rotation gap initial value theta of the folding and unfolding mechanism assembly AB The method comprises the steps of carrying out a first treatment on the surface of the By measuring the distance between the CDs and combining the distance from the observation point to the center point of the rotating shaft seat, calculating to obtain the central angle taking the two points of the CD as the circular arc points and the center point of the rotating shaft seat as the center point, and taking the central angle of the center point of the rotating shaft seat as the initial value theta of the up-down shaking gap of the folding and unfolding mechanism assembly CD 。
5. The gap detection method for the folding wings of the high aspect ratio unmanned aerial vehicle according to claim 1, wherein the gap detection method comprises the following steps: in the step 3, corresponding rotation angles generated by testing the deflection factors of the tool are calculated, and the corresponding rotation angles are obtained through equivalent calculation:
the equivalent calculation uses a typical cantilever beam as a model and utilizes a formula
Calculating the outer end rotation angle of the tool, wherein F is the outer end loading force, the force applied to the test tool recorded when the test tool obtained in the step 2 is positioned at the limit position is adopted in the calculation, c is the arm length of the loading force, and EI is the bending rigidity of the test tool; when the test tool is positioned at the limit positions on two sides according to the formula, the corresponding rotation angle theta generated by the deflection factor of the test tool is calculated 1 ，θ 2 And when the test tool is positioned at the upper limit position and the lower limit position, the corresponding rotation angle theta is generated due to the deflection factor of the test tool 3 ，θ 4 The rotation clearance of the finally obtained unmanned aerial vehicle folding and unfolding mechanism assembly is theta AB -θ 1 -θ 2 The up-and-down shaking gap is theta CD -θ 3 -θ 4 。
6. The gap detection method for the folding wings of the high aspect ratio unmanned aerial vehicle according to claim 1, wherein the gap detection method comprises the following steps: in the step 3, corresponding rotation angles generated by testing the deflection factors of the tool are calculated, and the corresponding rotation angles are obtained through simulation calculation: and (3) establishing a three-dimensional model of the test tool in the three-dimensional configuration software, adopting end fixing and supporting constraint, and performing simulation calculation on the force applied by the test tool by utilizing the force recorded when the test tool obtained in the step (2) is positioned at the limit position, so as to obtain the rotation angle generated by the deflection factor of the tool when the test tool is positioned at the two sides and the upper and lower limit positions, and further obtain the rotation gap and the up and down shaking gap of the final unmanned aerial vehicle folding and unfolding mechanism assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010637691.1A CN111959820B (en) | 2020-07-05 | 2020-07-05 | Gap detection method for folding wings of high aspect ratio unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010637691.1A CN111959820B (en) | 2020-07-05 | 2020-07-05 | Gap detection method for folding wings of high aspect ratio unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111959820A CN111959820A (en) | 2020-11-20 |
| CN111959820B true CN111959820B (en) | 2023-11-28 |
Family
ID=73361338
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010637691.1A Active CN111959820B (en) | 2020-07-05 | 2020-07-05 | Gap detection method for folding wings of high aspect ratio unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111959820B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB490151A (en) * | 1936-05-08 | 1938-08-10 | Bayerische Flugzeugwerke A G H | Improvements relating to folding wings for aeroplanes |
| CN103407580A (en) * | 2013-08-19 | 2013-11-27 | 空气动力学国家重点实验室 | Manufacturing method of light aerofoil with super-high aspect ratio and high lift-drag ratio and aerofoil manufactured thereby |
| CN203638109U (en) * | 2013-09-30 | 2014-06-11 | 中国航天科工集团第六研究院二一○所 | Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft |
| CN203732237U (en) * | 2013-12-30 | 2014-07-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Connecting device for folding wing surface folding gap of flutter wind tunnel model |
| CN106927022A (en) * | 2017-03-23 | 2017-07-07 | 清华大学 | Based on the super high-aspect-ratio aircraft for self-deploying folding wings technology |
| EP3246244A1 (en) * | 2016-05-20 | 2017-11-22 | Airbus Operations GmbH | A system for locking a foldable wing tip on a wing end of an aircraft |
| CN108045596A (en) * | 2017-12-04 | 2018-05-18 | 国网山东省电力公司电力科学研究院 | The flying quality inspection and detection system and method for a kind of fixed-wing unmanned plane |
| KR102125040B1 (en) * | 2019-04-12 | 2020-06-19 | 주식회사 피스퀘어 | Test apparatus of drone |
-
2020
- 2020-07-05 CN CN202010637691.1A patent/CN111959820B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB490151A (en) * | 1936-05-08 | 1938-08-10 | Bayerische Flugzeugwerke A G H | Improvements relating to folding wings for aeroplanes |
| CN103407580A (en) * | 2013-08-19 | 2013-11-27 | 空气动力学国家重点实验室 | Manufacturing method of light aerofoil with super-high aspect ratio and high lift-drag ratio and aerofoil manufactured thereby |
| CN203638109U (en) * | 2013-09-30 | 2014-06-11 | 中国航天科工集团第六研究院二一○所 | Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft |
| CN203732237U (en) * | 2013-12-30 | 2014-07-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Connecting device for folding wing surface folding gap of flutter wind tunnel model |
| EP3246244A1 (en) * | 2016-05-20 | 2017-11-22 | Airbus Operations GmbH | A system for locking a foldable wing tip on a wing end of an aircraft |
| CN106927022A (en) * | 2017-03-23 | 2017-07-07 | 清华大学 | Based on the super high-aspect-ratio aircraft for self-deploying folding wings technology |
| CN108045596A (en) * | 2017-12-04 | 2018-05-18 | 国网山东省电力公司电力科学研究院 | The flying quality inspection and detection system and method for a kind of fixed-wing unmanned plane |
| KR102125040B1 (en) * | 2019-04-12 | 2020-06-19 | 주식회사 피스퀘어 | Test apparatus of drone |
Non-Patent Citations (2)
| Title |
|---|
| 基于GPS位置信息的无人机自动测量弧垂系统研究与应用;陆布健;何琨才;莫品伟;谢义;;电工技术(第06期);全文 * |
| 折叠翼间隙对其颤振特性影响的试验研究;雷博淇;冉玉国;李秋彦;孔斌;张召明;;四川理工学院学报(自然科学版)(第03期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111959820A (en) | 2020-11-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107247839B (en) | Design method of low-speed wind tunnel virtual flight test airplane model | |
| CN101726401B (en) | Scale measuring device for pitching dynamic derivative experiment | |
| CN102507218B (en) | Mechanical arm type simulation test platform for tire comprehensive performances | |
| CN102288381B (en) | Wing tip support device for wind tunnel test | |
| EP2664907B1 (en) | Wind tunnel model measuring system and method | |
| WO2021227878A1 (en) | Chassis for track inspection robot and track inspection robot | |
| CN115493798B (en) | A high-speed jet wind tunnel aircraft maneuvering motion decoupling simulation test device | |
| CN103308023B (en) | A kind of angle displacement measuring device and measuring method | |
| CN106769013A (en) | A kind of loading inertia test apparatus of motor-driven cylinder | |
| CN106844838B (en) | A method for evaluating the performance of an aircraft air rudder | |
| CN104965129A (en) | Single-probe near-field antenna test system | |
| CN104931250A (en) | High-lift system whole-aircraft loading dynamic test method | |
| CN111024362A (en) | Test device and test method for estimating interstage separation track in symmetric plane | |
| CN111959820B (en) | Gap detection method for folding wings of high aspect ratio unmanned aerial vehicle | |
| CN103674474B (en) | Full machine wind tunnel experiment rudder face operating control crash simulation device | |
| CN114964695A (en) | A wind tunnel test half-mould support device with two degrees of freedom | |
| CN112484951B (en) | A portable wind tunnel test support device with adjustable attack angle two degrees of freedom elastic support | |
| CN111551340A (en) | Pneumatic force measuring and adjusting device for free jet wind tunnel test model | |
| CN113371227A (en) | Test bench of flap motion mechanism | |
| CN111891384B (en) | Bird-like flapping-wing aircraft testing device and testing method thereof | |
| CN109060291A (en) | For short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative angle measurement and experimental rig | |
| CN114166496A (en) | Tilt rotor wing test device | |
| CN205209733U (en) | Torgue measurement balance | |
| CN104880962B (en) | A kind of Dynamic Flight Simulator real time kinematics control method | |
| CN102944207A (en) | Springback type angle displacement measurement device and measurement method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |