CN109963787A - Test fixture for aircraft - Google Patents
Test fixture for aircraft Download PDFInfo
- Publication number
- CN109963787A CN109963787A CN201780071639.0A CN201780071639A CN109963787A CN 109963787 A CN109963787 A CN 109963787A CN 201780071639 A CN201780071639 A CN 201780071639A CN 109963787 A CN109963787 A CN 109963787A
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- CN
- China
- Prior art keywords
- battery
- pseudo
- test fixture
- aircraft
- fixture according
- 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.)
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Classifications
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- 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
Abstract
The test fixture (1000) that present disclose provides a kind of for aircraft.The aircraft includes the battery compartment for installing battery.The test fixture (1000) includes pseudo- battery (100), the puppet battery (100) includes fixation device (67,69) and the conductive terminal suitable for being installed and locked at pseudo- battery (100) in battery compartment, when pseudo- battery (100) is mounted on battery compartment, conductive terminal contacts battery compartment, so that aircraft can obtain power supply supply by pseudo- battery (100) in testing.The test fixture can improve the accuracy of test result.
Description
The present invention relates to Aerospace vehicle test fields, the more particularly, to test fixture of aircraft.
Aircraft (such as unmanned plane) in the process of development, will usually undergo a large amount of and prolonged test, such as burn-in test.Test result usually can directly reflect the success or failure of product design.Thus, the accuracy of test result has great significance.
Inventors have found that the accuracy of aircraft field dependence test result has improved space.
Summary of the invention
The present invention provides a kind of test fixture, to improve the accuracy of test result.
According to a first aspect of the embodiments of the present invention, a kind of test fixture for aircraft is provided, the aircraft includes the battery compartment for installing battery, the test fixture includes pseudo- battery, the puppet battery includes fixation device and the conductive terminal suitable for being installed and locked at the pseudo- battery in the battery compartment, when the pseudo- battery is mounted on the battery compartment, battery compartment described in the conductive terminal contacts, so that the aircraft can obtain power supply supply by the pseudo- battery in testing.
Further, the pseudo- battery includes first part and second part, and the puppet battery is provided with opening in the junction of first and second part, and the conductive terminal installation is in the opening.
Further, one in first and second part is provided with the fixed device, another provides power supply function.
Further, the fixed device includes sliding slot and sticking department, and the sticking department is connected with the sliding slot, so that the fit structure on battery compartment can be with the locking when being moved to a certain position along the sliding slot
Portion is meshed.
Further, the test fixture further includes pedestal and the mounting portion for the pseudo- battery to be installed on to the pedestal；
The mounting portion is fixed on the side of the pseudo- battery far from the battery compartment.
Further, one in the pedestal and the mounting portion is provided with sliding rail, another is provided with guide posts, and by the sliding rail and the guide posts, the pedestal and the pseudo- battery are slidably mounted together.
Further, the installation direction that the direction that the sliding rail extends is mounted on the battery compartment with the pseudo- battery is mutually perpendicular to.
Further, the mounting portion is integrally in T-shape.
Further, the pedestal includes plate-like substrate, along the vertical portion and sliding rail portion of the direction extension perpendicular to substrate place plane；
Sliding rail portion section is L-shaped, the sliding rail that the direction including the plane where perpendicular to the substrate extends, and is parallel to the lateral extensions of the substrate.
Further, the vertical portion is provided with circular screwhole, and the substrate is provided with elongate slot, using screw or is bolted the screw hole and the elongate slot and the vertical portion is installed on the substrate.
Fig. 1 and Fig. 2 is the three-dimensional structure diagram of an exemplary embodiment test fixture of the invention, wherein Fig. 1 is assembling figure, and Fig. 2 is explosive view.
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.In the following description when referring to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Embodiment described in following exemplary embodiment does not represent all embodiments consistented with the present invention.On the contrary, they are only the examples of consistent with some aspects of the invention as detailed in the appended claims device and method.
It is only to be not intended to limit the invention merely for for the purpose of describing particular embodiments in terminology used in the present invention.It is also intended to including most forms, unless the context clearly indicates other meaning in the present invention and the "an" of singular used in the attached claims, " described " and "the".It is also understood that term "and/or" used herein refers to and includes that one or more associated any or all of project listed may combine.
It should be appreciated that " first " " second " and similar word used in present specification and claims are not offered as any sequence, quantity or importance, and it is used only to distinguish different component parts.Equally, the similar word such as "one" or " one " does not indicate that quantity limits yet, but indicates that there are at least one.Unless otherwise noted, the similar word such as " front ", " rear portion ", " lower part " and/or " top " is only to facilitate illustrate, and be not limited to a position or a kind of spatial orientation.The similar word such as " comprising " or "comprising" means to appear in element or object before " comprising " or "comprising" and covers the element for appearing in " comprising " or "comprising" presented hereinafter or object and its be equal, it is not excluded that other elements or object." connection " either the similar word such as " connected " is not limited to physics or mechanical connection, and may include electrical connection, either direct or indirect.
With reference to the accompanying drawing, the test fixture of the embodiment of the present invention is described in detail.In the absence of conflict, the feature in following embodiment and embodiment can be combined with each other.
Fig. 1 and Fig. 2 is the three-dimensional structure diagram of an exemplary embodiment test fixture of the invention, wherein Fig. 1 is assembling figure, and Fig. 2 is explosive view.The test fixture can clamp in the test process of aircraft or fixed aircraft, and the support in terms of power supply can be provided for aircraft.Aircraft mentioned here may include unmanned plane etc., and test mentioned here may include burn-in test, such as frequency sweep burn-in test etc..Aircraft may include the battery compartment for installing battery, and the battery being installed in the battery compartment can awing be that entire aircraft (including for driving the motor of propeller rotational) provides electric power support.In frequency sweep burn-in test, a test software can be loaded in the winged control of aircraft, allows the motor of aircraft to rotate sometimes fast and sometimes slowly, to achieve the purpose that test.
Such as Fig. 1 and Fig. 2, test fixture 1000 includes pseudo- battery 100.The puppet battery 100 includes fixation device 67,69 and the conductive terminal (not shown) suitable for being installed and locked at the pseudo- battery 100 in the battery compartment of aircraft to be measured.When the pseudo- battery 100 is mounted on the battery compartment, the conduction
Battery compartment described in termination contact, so that the aircraft can obtain power supply supply by the pseudo- battery 100 in testing.
By the way that pseudo- battery 100 to be installed and locked in battery compartment, aircraft to be measured and pseudo- battery 100 can be fixed as one, it is subsequent only to need that the fixation of aircraft to be measured can be realized by installing or fixing pseudo- battery 100 in pedestal." pedestal " mentioned here though can be the earth, fixture or as shown in 300 in figure it is unlocked but be not easy the structure toppled.
Since the position that aircraft to be measured is directly fixed or fettered is the battery compartment on fuselage, and bound region area is larger, so that aircraft to be measured can be fixed more firm, it is less likely to occur aircraft swing to be measured or unstable situation in testing, enables test structure more acurrate.Moreover, aircraft to be measured can also be made to be more readily retained at actual flight state in the way of the fixed aircraft to be measured of pseudo- battery in embodiment, the accuracy for improving test result can be conducive to.
" pseudo- battery " mentioned here can have two aspect features.First, it can cooperate with original battery fastening device on battery compartment, lock, realize the fixation between pseudo- battery and aircraft to be measured.Second, after being fixed on battery compartment, the conductive terminal being arranged on pseudo- battery can be connected with the hard contact in battery compartment, support to provide power supply for the aircraft in test." hard contact in battery compartment " mentioned here can be the original structure of battery compartment；In aerocraft real in use, it is aircraft power supply that the real battery being installed in the battery compartment, which passes through the hard contact,.
Typically, pseudo- battery can have the shape or structure identical or essentially identical with true battery (original-pack battery, the mating battery of aircraft), especially in terms of fixed device and conductive terminal.But, it is not required that it is inevitable such.It is readily apparent that, above-mentioned two aspects feature or performance equally can be achieved in the slightly discrepant pseudo- battery of pattern.
" aircraft passes through pseudo- battery in testing and obtains power supply supply " referred to herein, mode can there are many.For example, pseudo- battery itself can have the storage function similar to true battery, it is in testing aircraft power supply.For beauty, true battery will usually guarantee that the surface of battery does not protrude from fuselage excessively after being installed in battery compartment.Pseudo- battery can need not scruple this point, thus, pseudo- battery, which can be designed to be, has bigger volume and capacity, to have more longlasting cruise duration.To further increase cruise duration, pseudo- battery can be connected to external power supply (for example, alternating current), by the external power supply constantly transmit electric power to pseudo- battery with to
Aircraft is surveyed, the puzzlement for replacing battery in test is avoided.In testing, frequently replacement battery has both spun out test period, is similarly unfavorable for the accuracy of test result.In addition, pseudo- battery can need not have battery functi on (storage function in other words), it can be only as the circuit path for being connected to external power supply (for example, alternating current) and aircraft.
Pseudo- battery 100 can be assembled by multiple components, for example, can be composed of first part 5 as illustrated in the drawing, second part 6 and conductive terminal (or conducting end submodule group).Pseudo- battery 100 is provided with opening 9 in the junction of the first and second part 5,6, and conductive terminal or conducting end submodule group are mounted in opening 9." conducting end submodule group " referred to herein may include the conductive terminal of substantially square insulator and installation on the body.
Different aircraft may correspond to different conductive terminals.When needed (for example, when testing the aircraft of another model), the conductive terminal or conducting end submodule group in replaceable opening 9 realizes that the conductive terminal of pseudo- battery is adapted to the hard contact perfection in battery compartment.
First and second part 5,6 of pseudo- battery 100 can be assembled into one by screw or bolt.Such as, settable multiple screw hole (not shown) in first part 5, settable multiple screw holes 65 on second part 6, the assembling of pseudo- battery 100 can be realized by the screw hole 65 for successively penetrating multiple screw (not shown) on the first and second part 5,6.
It may be provided at the second part 6 of pseudo- battery 100 for installing pseudo- battery 100 to the fixation device 67,69 of aircraft to be measured.The fixed device may include sliding slot 67 and sticking department 69.672 width of opening positioned at 67 front end of sliding slot is larger, greater than the width in the other regions of sliding slot 67, and in shape is become narrow gradually, so that the opening 672 has the function of that guiding battery compartment corresponding position enters sliding slot 67.Sticking department 69 can be connected with the sliding slot 67, so that on battery compartment fit structure (such as, metal clips) it can be meshed with the sticking department 69 when being moved to a certain position along the sliding slot 67, thus prevent the fit structure on battery compartment to exit sliding slot 67.In Fig. 1 and embodiment illustrated in fig. 2, sticking department 69 includes two sticking departments 691 and 692, they are arranged before and after 67 glide direction along the chute.In addition, settable rib 63 outstanding on the inner surface of second part 6, to enhance the contact of second part 6 inner surface and battery compartment surface.
In Fig. 1 and embodiment illustrated in fig. 2, the first part 5 of pseudo- battery 100 has storage function, and is connected to external power supply (for example, alternating current).
Test fixture 1000 may also include the mounting portion 4 for pseudo- battery 100 to be installed on to pedestal 300.Mounting portion 4 can be fixed on side (outside in figure) of the pseudo- battery 100 far from battery compartment.Mounting portion 4 is fixed on pseudo- battery 100 using screw or bolt arrangement.For example, multiple screw holes 54 and 56 can be arranged in the first part 5 of pseudo- battery 100, multiple screw holes 44 and 46 are set in mounting portion 4；After screw hole 44,46 is aligned with screw hole 54,56, screw or bolt (not shown) are successively screwed in the fixation that the two can be realized along screw hole.
One (being pedestal 300 in the present embodiment) in mounting portion 4 and pedestal 300 is provided with sliding rail 37, another (being mounting portion 4 in the present embodiment) is provided with guide posts 47.By sliding rail 37 and guide posts 47, pedestal 300 and pseudo- battery 100 are slidably mounted together.The installation direction (front-rear direction in figure) that the direction (vertical direction in figure) that sliding rail 37 extends can be mounted on battery compartment with pseudo- battery 100 is mutually perpendicular to.After sliding rail 37 and guide posts 47 cooperate in place, further the two can be fixed by screw or bolt.For example, screw hole 42 can be arranged in guide posts 47, screw hole 32 is set at sliding rail 37；After sliding rail 37 and guide posts 47 cooperate in place, screw hole 32 is aligned with screw hole 42, and screw or bolt (not shown), which are successively screwed in screw hole 32,42, can be realized fixation.In embodiment as shown in the figure, it can be in T-shape that mounting portion 4 is whole, wherein longitudinal portion in the T-shape structure can be used as guide posts 47, and the transverse part in the T-shape structure is mainly used for mounting screw, mounting portion 4 is fixed on pseudo- battery 100.
In embodiment as shown in the figure, pedestal 300 may include plate-like substrate 1, along the vertical portion 2 and sliding rail portion 3 of the direction extension perpendicular to 1 place plane of substrate.Wherein, 3 section of sliding rail portion can be L-shaped, it may include the aforementioned sliding rail 37 extended along the direction perpendicular to 1 place plane of substrate, and it is parallel to the lateral extensions 35 of substrate 1.Settable multiple screw holes 34 on the lateral surface of lateral extensions 35, the settable multiple screw holes 24 in the top of vertical portion 2；After the alignment of screw hole 24,34, screw or bolt (not shown), which are successively screwed in screw hole 24,34, can be realized the fixation in sliding rail portion 3 Yu vertical portion 2.
Settable circular screwhole 22 on vertical portion 2, the settable elongate slot 12 of substrate 1.The extending direction (length direction) of the elongate slot 12 can be installed perpendicular to pseudo- battery 100 to the installation direction (67 glide directions along the chute) in aircraft battery storehouse.Screw or bolt (not shown) are successively screwed in into screw hole 22 and elongate slot 12, vertical portion 2 can be installed on substrate 1.Elongate slot 12 has multiple installation sites along its length, and vertical portion 2 can be fixed on any one installation site by screw or bolt.In different installation sites, erect
Relative position between straight portion 2 and substrate 1 changes.Installation site is more inner, and aircraft to be measured is tightlyer clamped.That is, the masterpiece adjustment of aircraft to be measured can be clamped to test fixture by adjustment/selection of installation site.
Also settable multiple lightening holes 14 on substrate 1, to mitigate the weight of substrate 1.
It may include two battery compartments and battery being arranged symmetrically on some aircraft fuselages.Correspondingly, symmetrically arranged two test fixtures 1000 can be used to fix the aircraft, as shown in Figures 1 and 2.
Substrate 1, vertical portion 2 and sliding rail portion 3 can be assembled into pedestal 300 in advance, first and second part 5,6 of pseudo- battery 100 and mounting portion 4 are assembled into one (hereinafter referred to as " pseudo- battery modules "), and will be both as the peacetime state of test fixture 1000.When needing to test, pseudo- battery modules first can be mounted and fixed to aircraft to be measured；Then using guide posts 47 and sliding rail 37, the pseudo- battery modules for being fixed on aircraft to be measured are installed on pedestal 300；Finally, by screw or bolt that pseudo- battery modules and pedestal 300 are fixed.Then, process that the test can be started.
The above is only presently preferred embodiments of the present invention, limitation in any form not is done to the present invention, although the present invention has been disclosed as a preferred embodiment, however, it is not intended to limit the invention, any person skilled in the art, in the range of not departing from technical solution of the present invention, when the technology contents using the disclosure above are modified or are modified to the equivalent embodiment of equivalent variations, but anything that does not depart from the technical scheme of the invention content, any simple modification to the above embodiments according to the technical essence of the invention, equivalent variations and modification, all of which are still within the scope of the technical scheme of the invention.
This patent document disclosure includes material protected by copyright.The copyright is all for copyright holder.Copyright holder does not oppose that the patent document or the patent in the presence of anyone replicates the proce's-verbal of Patent&Trademark Office and archives disclose.
Claims (10)
- A kind of test fixture for aircraft, the aircraft includes the battery compartment for installing battery, it is characterized in that, the test fixture includes pseudo- battery, the puppet battery includes fixation device and the conductive terminal suitable for being installed and locked at the pseudo- battery in the battery compartment, when the pseudo- battery is mounted on the battery compartment, battery compartment described in the conductive terminal contacts, so that the aircraft can obtain power supply supply by the pseudo- battery in testing.
- Test fixture according to claim 1, which is characterized in that the puppet battery includes first part and second part, and the puppet battery is provided with opening in the junction of first and second part, and the conductive terminal installation is in the opening.
- Test fixture according to claim 2, which is characterized in that one in first and second part is provided with the fixed device, another provides power supply function.
- Test fixture according to claim 1, it is characterized in that, the fixed device includes sliding slot and sticking department, and the sticking department is connected with the sliding slot, so that the fit structure on battery compartment can be meshed when being moved to a certain position along the sliding slot with the sticking department.
- Test fixture according to claim 1, which is characterized in that the test fixture further includes pedestal and the mounting portion for the pseudo- battery to be installed on to the pedestal；The mounting portion is fixed on the side of the pseudo- battery far from the battery compartment.
- Test fixture according to claim 5, which is characterized in that one in the pedestal and the mounting portion is provided with sliding rail, another is provided with guide posts, and by the sliding rail and the guide posts, the pedestal and the pseudo- battery are slidably mounted together.
- Test fixture according to claim 6, which is characterized in that the installation direction that the direction that the sliding rail extends is mounted on the battery compartment with the pseudo- battery is mutually perpendicular to.
- Test fixture according to claim 6, which is characterized in that the mounting portion is integrally in T-shape.
- Test fixture according to claim 5, which is characterized in that the pedestal includes plate-like Substrate, the vertical portion and sliding rail portion that extend along the direction perpendicular to plane where the substrate；Sliding rail portion section is L-shaped, the sliding rail that the direction including the plane where perpendicular to the substrate extends, and is parallel to the lateral extensions of the substrate.
- Test fixture according to claim 9, which is characterized in that the vertical portion is provided with circular screwhole, and the substrate is provided with elongate slot, using screw or is bolted the screw hole and the elongate slot and the vertical portion is installed on the substrate.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720834343.7 | 2017-07-10 | ||
| CN201720834343.7U CN206969003U (en) | 2017-07-10 | 2017-07-10 | test fixture for aircraft |
| PCT/CN2017/104948 WO2019010837A1 (en) | 2017-07-10 | 2017-09-30 | Test fixture for aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109963787A true CN109963787A (en) | 2019-07-02 |
Family
ID=61402459
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720834343.7U Expired - Fee Related CN206969003U (en) | 2017-07-10 | 2017-07-10 | test fixture for aircraft |
| CN201780071639.0A Pending CN109963787A (en) | 2017-07-10 | 2017-09-30 | Test fixture for aircraft |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720834343.7U Expired - Fee Related CN206969003U (en) | 2017-07-10 | 2017-07-10 | test fixture for aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN206969003U (en) |
| WO (1) | WO2019010837A1 (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201876346U (en) * | 2010-11-05 | 2011-06-22 | 深圳出入境检验检疫局工业品检测技术中心 | Testing clamp |
| CN102520215A (en) * | 2012-01-11 | 2012-06-27 | 东莞市钜大电子有限公司 | Adjustable clamp for testing battery and mounting method thereof |
| CN104684688A (en) * | 2013-09-30 | 2015-06-03 | 株式会社Lg化学 | Test jig |
| CN105352588A (en) * | 2015-09-08 | 2016-02-24 | 北京航空航天大学 | Design of vibration detection system of brushless direct current motor |
| CN205373595U (en) * | 2016-01-28 | 2016-07-06 | 宁德新能源科技有限公司 | Test clamp |
| US20170149257A1 (en) * | 2015-10-30 | 2017-05-25 | Engineering Design, Inc. | Field charging unit for various batteries in multiple deployable devices |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205365355U (en) * | 2015-11-23 | 2016-07-06 | 中国航天空气动力技术研究院 | Test equipment is synthesized on unmanned aerial vehicle undercarriage ground |
-
2017
- 2017-07-10 CN CN201720834343.7U patent/CN206969003U/en not_active Expired - Fee Related
- 2017-09-30 WO PCT/CN2017/104948 patent/WO2019010837A1/en active Application Filing
- 2017-09-30 CN CN201780071639.0A patent/CN109963787A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201876346U (en) * | 2010-11-05 | 2011-06-22 | 深圳出入境检验检疫局工业品检测技术中心 | Testing clamp |
| CN102520215A (en) * | 2012-01-11 | 2012-06-27 | 东莞市钜大电子有限公司 | Adjustable clamp for testing battery and mounting method thereof |
| CN104684688A (en) * | 2013-09-30 | 2015-06-03 | 株式会社Lg化学 | Test jig |
| CN105352588A (en) * | 2015-09-08 | 2016-02-24 | 北京航空航天大学 | Design of vibration detection system of brushless direct current motor |
| US20170149257A1 (en) * | 2015-10-30 | 2017-05-25 | Engineering Design, Inc. | Field charging unit for various batteries in multiple deployable devices |
| CN205373595U (en) * | 2016-01-28 | 2016-07-06 | 宁德新能源科技有限公司 | Test clamp |
Also Published As
| Publication number | Publication date |
|---|---|
| CN206969003U (en) | 2018-02-06 |
| WO2019010837A1 (en) | 2019-01-17 |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190702 |