WO2019010837A1 - 用于飞行器的测试夹具 - Google Patents

用于飞行器的测试夹具 Download PDF

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Publication number
WO2019010837A1
WO2019010837A1 PCT/CN2017/104948 CN2017104948W WO2019010837A1 WO 2019010837 A1 WO2019010837 A1 WO 2019010837A1 CN 2017104948 W CN2017104948 W CN 2017104948W WO 2019010837 A1 WO2019010837 A1 WO 2019010837A1
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WIPO (PCT)
Prior art keywords
battery
test fixture
dummy
aircraft
substrate
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Ceased
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PCT/CN2017/104948
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English (en)
French (fr)
Inventor
罗成
钟志勇
邓云海
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SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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Publication date
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Priority to CN201780071639.0A priority Critical patent/CN109963787A/zh
Publication of WO2019010837A1 publication Critical patent/WO2019010837A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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

Definitions

  • the present invention relates to the field of aircraft testing, and more particularly to test fixtures for aircraft.
  • Aircraft such as drones
  • Aircraft often undergo extensive and long-term testing during development, such as aging tests. Test results often directly reflect the success or failure of product design. Therefore, the accuracy of the test results is of great significance.
  • the inventors have found that there is room for improvement in the accuracy of relevant test results in the field of aircraft.
  • the invention provides a test fixture for improving the accuracy of test results.
  • a test fixture for an aircraft comprising a battery compartment for mounting a battery, the test fixture comprising a dummy battery, the dummy battery comprising a a dummy battery mounted and locked in the battery compartment and a conductive terminal, the conductive terminal contacting the battery compartment when the dummy battery is mounted in the battery compartment, so that the aircraft can be tested A power supply is obtained by the dummy battery.
  • the dummy battery includes a first portion and a second portion, and the dummy battery is provided with an opening at a junction of the first and second portions, and the conductive terminal is installed in the opening.
  • one of the first and second parts is provided with the fixing device, and the other provides a power supply function.
  • the fixing device includes a sliding slot and a locking portion, and the locking portion is connected to the sliding slot to enable the locking structure on the battery compartment to be locked with the locking slot when moving to a certain position along the sliding slot
  • the parts are meshed.
  • test fixture further includes a base and a mounting portion for mounting the dummy battery to the base;
  • the mounting portion is fixed to a side of the dummy battery away from the battery compartment.
  • one of the base and the mounting portion is provided with a slide rail, and the other is provided with a guide post, through the slide rail and the guide post, the base and the dummy battery can be Sliding mounted together.
  • the direction in which the slide rail extends is perpendicular to the mounting direction of the dummy battery mounted on the battery compartment.
  • the mounting portion has a "T" shape as a whole.
  • the susceptor includes a substrate in a plate shape, a vertical portion extending in a direction perpendicular to a plane of the substrate, and a slide portion;
  • the rail portion has an "L" shape in cross section, and includes the slide rail extending in a direction perpendicular to a plane of the substrate, and a lateral extension portion parallel to the substrate.
  • the vertical portion is provided with a circular screw hole
  • the substrate is provided with an elongated slot
  • the vertical portion is mounted to the substrate by screwing or screwing the screw hole and the elongated slot.
  • FIG. 1 and 2 are perspective structural views of a test jig according to an exemplary embodiment of the present invention, wherein FIG. 1 is an assembled view and FIG. 2 is an exploded view.
  • the words “a” or “an” and the like do not denote a quantity limitation, but mean that there is at least one. Unless otherwise indicated, the terms “front”, “rear”, “lower” and/or “upper” are used for convenience of description and are not limited to one location or one spatial orientation.
  • the words “connected” or “connected” and the like are not limited to physical or mechanical connections, and may include electrical connections, whether direct or indirect.
  • test fixture of the embodiment of the present invention will be described in detail below with reference to the accompanying drawings.
  • the features of the embodiments and embodiments described below may be combined with each other without conflict.
  • FIG. 1 and 2 are perspective structural views of a test jig according to an exemplary embodiment of the present invention, wherein FIG. 1 is an assembled view and FIG. 2 is an exploded view.
  • the test fixture can clamp or secure the aircraft during the testing of the aircraft and provide power support for the aircraft.
  • the aircraft referred to herein may include a drone or the like, and the tests referred to herein may include an aging test such as a frequency sweep aging test.
  • the aircraft may include a battery compartment for mounting a battery, and the battery installed in the battery compartment provides electrical support for the entire aircraft, including the motor used to drive the rotation of the propeller, in flight.
  • a test software can be loaded in the flight control of the aircraft, so that the motor of the aircraft can be rotated slowly and slowly, thereby achieving the purpose of testing.
  • the test fixture 1000 includes a dummy battery 100.
  • the dummy battery 100 includes fixing means 67, 69 and conductive terminals (not shown) adapted to mount and lock the dummy battery 100 in a battery compartment of the aircraft to be tested.
  • the conductive when the dummy battery 100 is mounted in the battery compartment The terminal contacts the battery compartment such that the aircraft can obtain a power supply through the dummy battery 100 during testing.
  • the aircraft to be tested can be fixed integrally with the dummy battery 100, and the aircraft to be tested can be fixed only by installing or fixing the dummy battery 100 to the base.
  • the "base” referred to herein may be a ground, a fixture, or a structure that is not fixed but not easily tipped as shown by 300 in the drawing.
  • the part to be tested is directly fixed or bound is a battery compartment located on the fuselage, and the area of the bound area is large, the aircraft to be tested can be fixed relatively firmly, and the aircraft to be tested is not easily swayed during the test. Or unstable conditions make the test structure more accurate.
  • the manner in which the pseudo-battery is used to fix the aircraft to be tested in the embodiment can also make the aircraft to be tested more easily maintained in the actual flight state, which can be beneficial to improve the accuracy of the test results.
  • the "pseudo battery” referred to herein can have two characteristics. First, it can be matched with the original battery locking device on the battery compartment, and the buckle is locked to realize the fixation between the pseudo battery and the aircraft to be tested. Second, after being fixed in the battery compartment, the conductive terminals provided on the dummy battery can be electrically connected to the metal contacts in the battery compartment, thereby providing power support for the aircraft under test.
  • the "metal contact in the battery compartment” referred to herein may be the original structure of the battery compartment; in actual use of the aircraft, the real battery installed in the battery compartment supplies power to the aircraft through the metal contact.
  • a dummy battery may have the same or substantially the same shape or structure as a genuine battery (original battery of an aircraft, an accessory battery), particularly in terms of a fixture and a conductive terminal. However, it is not required to be so. It is easy to think that the pseudo-battery with slightly different appearance can also achieve the above two features or performances.
  • the aircraft obtains the power supply through the pseudo battery in the test
  • the pseudo battery itself may have a power storage function similar to a true battery, which powers the aircraft during the test.
  • the pseudo-battery can be designed to have a larger volume and capacity, thereby providing a longer lasting life.
  • the pseudo battery can be connected to an external power source (for example, a commercial power source), and the power is continuously transmitted to the pseudo battery through the external power source.
  • the pseudo battery may not necessarily have a battery function (or a power storage function), and may only serve as a circuit path for connecting an external power source (for example, a commercial power) to the aircraft.
  • the dummy battery 100 can be assembled from a plurality of components, for example, by combining the first portion 5, the second portion 6, and the conductive terminals (or conductive terminal modules) as shown in the drawing.
  • the dummy battery 100 is provided with an opening 9 at a junction of the first and second portions 5, 6, and a conductive terminal or a conductive terminal module is mounted in the opening 9.
  • the "conductive terminal module” as used herein may include a substantially square insulator and a conductive terminal mounted on the insulator.
  • Different aircraft may correspond to different conductive terminals.
  • the conductive terminals or conductive terminal modules in the opening 9 can be replaced, so that the conductive terminals of the dummy battery are perfectly matched with the metal contacts in the battery compartment.
  • the first and second portions 5, 6 of the dummy battery 100 can be assembled by screws or bolts.
  • a plurality of screw holes may be disposed on the first portion 5, and a plurality of screw holes 65 may be disposed on the second portion 6, and the plurality of screws (not shown) are sequentially inserted into the first portion.
  • the screw holes 65 on the two portions 5, 6 can realize the assembly of the dummy battery 100.
  • Fixing means 67, 69 for mounting the dummy battery 100 to the aircraft to be tested may be disposed on the second portion 6 of the dummy battery 100.
  • the fixing device may include a chute 67 and a locking portion 69.
  • the opening 672 at the front end of the chute 67 has a larger width than the other regions of the chute 67 and is gradually narrowed such that the opening 672 has a function of guiding the corresponding portion of the battery compartment into the chute 67.
  • a locking portion 69 can be coupled to the sliding slot 67 to engage a mating structure (eg, a metal dome) on the battery compartment with the locking portion 69 when moving along the chute 67 to a position The mating structure on the battery compartment can be prevented from exiting the chute 67.
  • a mating structure eg, a metal dome
  • the locking portion 69 includes two locking portions 691 and 692 which are arranged one behind the other in the sliding direction of the chute 67. Additionally, protruding ribs 63 may be provided on the inner surface of the second portion 6 to enhance contact of the inner surface of the second portion 6 with the surface of the battery compartment.
  • the first portion 5 of the dummy battery 100 is provided with a power storage function and is in communication with an external power source (e.g., commercial power).
  • an external power source e.g., commercial power
  • the test fixture 1000 may further include a mounting portion 4 for mounting the dummy battery 100 to the base 300.
  • the mounting portion 4 can be fixed to the side (the outer side in the drawing) of the dummy battery 100 away from the battery compartment.
  • the mounting portion 4 can be fixed to the dummy battery 100 by a screw or bolt structure.
  • a plurality of screw holes 54 and 56 may be disposed in the first portion 5 of the dummy battery 100, and a plurality of screw holes 44 and 46 may be disposed in the mounting portion 4; after the screw holes 44, 46 are aligned with the screw holes 54, 56, the screws are Or bolts (not shown) are screwed in along the screw holes to fix the two.
  • One of the mounting portion 4 and the base 300 (the base 300 in this embodiment) is provided with a slide rail 37, and the other (in this embodiment, the mounting portion 4) is provided with a guide post 47.
  • the base 300 and the dummy battery 100 are slidably mounted together by the slide rail 37 and the guide post 47.
  • the direction in which the slide rails 37 extend may be perpendicular to the mounting direction (front-rear direction in the drawing) in which the dummy battery 100 is mounted on the battery compartment.
  • the two can be further fixed by screws or bolts.
  • a screw hole 42 may be disposed on the guide post 47, and a screw hole 32 may be disposed at the slide rail 37.
  • the mounting portion 4 may have a "T" shape as a whole, wherein the longitudinal portion of the "T"-shaped structure can serve as the guiding post 47, and the lateral portion of the "T"-shaped structure is mainly used.
  • the mounting portion 4 is fixed to the dummy battery 100 by mounting screws.
  • the susceptor 300 may include a substrate 1 in a plate shape, a vertical portion 2 extending in a direction perpendicular to a plane in which the substrate 1 is located, and a slide portion 3.
  • the rail portion 3 may have an "L" shape in cross section, and may include the aforementioned slide rail 37 extending in a direction perpendicular to the plane of the substrate 1, and a lateral extension portion 35 parallel to the substrate 1.
  • a plurality of screw holes 34 may be disposed on the outer side surface of the lateral extending portion 35, and a plurality of screw holes 24 may be disposed at the upper portion of the vertical portion 2; after the screw holes 24, 34 are aligned, screws or bolts (not shown) are sequentially disposed.
  • the fixing of the rail portion 3 and the vertical portion 2 can be achieved by screwing the screw holes 24, 34.
  • a circular screw hole 22 may be disposed in the vertical portion 2, and the substrate 1 may be provided with an elongated slot 12.
  • the extending direction (longitudinal direction) of the elongated slot 12 may be perpendicular to the mounting direction of the dummy battery 100 to the aircraft battery compartment (in the sliding direction of the chute 67).
  • the vertical portion 2 is attached to the substrate 1 by screwing a screw or a bolt (not shown) into the screw hole 22 and the slit 12 in this order.
  • the elongated slot 12 has a plurality of mounting positions along its length, and screws or bolts can secure the vertical portion 2 in either mounting position. In different installation positions, vertical The relative position between the straight portion 2 and the substrate 1 changes. The closer the installation position is inside, the tighter the aircraft to be tested is clamped. That is, the force of the test fixture holding the aircraft to be tested can be adjusted by the adjustment/selection of the installation position.
  • a plurality of lightening holes 14 may also be disposed on the substrate 1 to reduce the weight of the substrate 1.
  • Some aircraft fuselage may include two battery compartments and batteries arranged symmetrically.
  • the two test fixtures 1000 arranged symmetrically can be used to fix the aircraft, as shown in FIGS. 1 and 2.
  • the substrate 1, the vertical portion 2, and the rail portion 3 can be assembled into the susceptor 300 in advance, and the first and second portions 5 and 6 of the dummy battery 100 and the mounting portion 4 are integrally assembled (hereinafter referred to as "pseudo battery module”). ) and use the two as the normal state of the test fixture 1000.
  • the pseudo battery module can be installed and fixed on the aircraft to be tested; then, the dummy battery module fixed to the aircraft to be tested can be installed on the base 300 by using the guide post 47 and the slide rail 37; The dummy battery module is fixed to the base 300 by screws or bolts. Then you can start the testing process.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Battery Mounting, Suspending (AREA)

Abstract

提供了一种用于飞行器的测试夹具(1000)；该飞行器包括用于安装电池的电池仓。该测试夹具(1000)包括伪电池(100)；该伪电池（100）包括适于将伪电池（100）安装并锁定在电池仓内的固定装置（67、69）以及导电端子；在伪电池（100）安装在电池仓时，导电端子接触电池仓，以使飞行器在测试中可通过伪电池（100）获得电源供应。该测试夹具可以改善测试结果的准确性。

Description

用于飞行器的测试夹具 技术领域
本发明涉及飞行器测试领域，尤其涉及用于飞行器的测试夹具。
背景技术
飞行器(比如无人机)在开发过程中，通常要经历大量且长时间的测试，比如老化测试。测试结果常常可直接反映产品设计的成败。因而，测试结果的准确性有着重要的意义。
发明人发现，飞行器领域相关测试结果的准确性有改善的空间。
发明内容
本发明提供一种测试夹具，用以改善测试结果的准确性。
根据本发明实施例的第一方面，提供一种用于飞行器的测试夹具，所述飞行器包括用于安装电池的电池仓，所述测试夹具包括伪电池，所述伪电池包括适于将所述伪电池安装并锁定在所述电池仓内的固定装置以及导电端子，在所述伪电池安装在所述电池仓时，所述导电端子接触所述电池仓，以使所述飞行器在测试中可通过所述伪电池获得电源供应。
进一步地，所述伪电池包括第一部分与第二部分，所述伪电池在所述第一、二部分的结合处设置有开口，所述导电端子安装在所述开口内。
进一步地，所述第一、二部分中的一个设置有所述固定装置，另一个提供电源功能。
进一步地，所述固定装置包括滑槽与锁定部，所述锁定部与所述滑槽相连，以使电池仓上的配合结构在沿所述滑槽移动到某一位置时可与所述锁定 部相啮合。
进一步地，所述测试夹具还包括基座以及用于将所述伪电池安装于所述基座的安装部；
所述安装部固定在所述伪电池远离所述电池仓的一侧。
进一步地，所述基座与所述安装部中的一个设置有滑轨，另一个设置有导引柱，通过所述滑轨与所述导引柱，所述基座与所述伪电池可滑动安装在一起。
进一步地，所述滑轨延伸的方向与所述伪电池安装在所述电池仓上的安装方向相互垂直。
进一步地，所述安装部整体呈“T”型。
进一步地，所述基座包括呈板状的基板、沿垂直于所述基板所在平面的方向延伸的竖直部以及滑轨部；
所述滑轨部截面呈“L”型，包括沿垂直于所述基板所在平面的方向延伸的所述滑轨，以及平行于所述基板的横向延伸部。
进一步地，所述竖直部设置有圆形螺孔，所述基板设置有狭长槽，利用螺钉或螺栓连接所述螺孔与所述狭长槽而将所述竖直部安装于所述基板。
附图说明
图1与图2是本发明一示例性实施例测试夹具的立体结构图，其中，图1是组装图，图2是爆炸图。
具体实施方式
这里将详细地对示例性实施例进行说明，其示例表示在附图中。下面的描述涉及附图时，除非另有表示，不同附图中的相同数字表示相同或相似的要素。以下示例性实施例中所描述的实施方式并不代表与本发明相一致的所有实施方式。相反，它们仅是与如所附权利要求书中所详述的、本发明的一些方面相一致的装置和方法的例子。
在本发明使用的术语是仅仅出于描述特定实施例的目的，而非旨在限制本发明。在本发明和所附权利要求书中所使用的单数形式的“一种”、“所述”和“该”也旨在包括多数形式，除非上下文清楚地表示其他含义。还应当理解，本文中使用的术语“和/或”是指并包含一个或多个相关联的列出项目的任何或所有可能组合。
应当理解，本申请说明书以及权利要求书中使用的“第一”“第二”以及类似的词语并不表示任何顺序、数量或者重要性，而只是用来区分不同的组成部分。同样，“一个”或者“一”等类似词语也不表示数量限制，而是表示存在至少一个。除非另行指出，“前部”、“后部”、“下部”和/或“上部”等类似词语只是为了便于说明，而并非限于一个位置或者一种空间定向。“包括”或者“包含”等类似词语意指出现在“包括”或者“包含”前面的元件或者物件涵盖出现在“包括”或者“包含”后面列举的元件或者物件及其等同，并不排除其他元件或者物件。“连接”或者“相连”等类似的词语并非限定于物理的或者机械的连接，而且可以包括电性的连接，不管是直接的还是间接的。
下面结合附图，对本发明实施例的测试夹具进行详细说明。在不冲突的情况下，下述的实施例及实施方式中的特征可以相互组合。
图1与图2是本发明一示例性实施例测试夹具的立体结构图，其中，图1是组装图，图2是爆炸图。该测试夹具可在飞行器的测试过程中夹持或固定飞行器，并可为飞行器提供电源方面的支持。这里所说的飞行器可包括无人机等，这里所说的测试可包括老化测试，比如扫频老化测试等。飞行器可包括用于安装电池的电池仓，安装在电池仓内的电池可在飞行中为整个飞行器(包括用于带动螺旋桨转动的电机)提供电力支持。在扫频老化测试中，可在飞行器的飞控中加载一个测试软件，让飞行器的电机时快时慢地转动，从而达到测试的目的。
如图1与图2，测试夹具1000包括伪电池100。所述伪电池100包括适于将所述伪电池100安装并锁定在待测飞行器的电池仓内的固定装置67、69以及导电端子(图中未显示)。在所述伪电池100安装在所述电池仓时，所述导电 端子接触所述电池仓，以使所述飞行器在测试中可通过所述伪电池100获得电源供应。
通过将伪电池100安装并锁定在电池仓内，可将待测飞行器与伪电池100固定为一体，后续仅需通过安装或固定伪电池100于基座，即可实现待测飞行器的固定。这里所说的“基座”可以是大地、固定物或者如图中300所示的虽未固定但不容易倾覆的结构。
由于待测飞行器被直接固定或束缚的部位是位于机身上的电池仓，且被束缚的区域面积较大，使得待测飞行器可被固定得较为牢靠，在测试中不容易发生待测飞行器摆动或不稳定的情形，令测试结构更准确。不仅如此，实施例中利用伪电池固定待测飞行器的方式，也可使待测飞行器更容易地被保持在实际飞行状态，可有利于提高测试结果的准确性。
这里所说的“伪电池”可具有两方面特征。第一，能与电池仓上的原有电池锁扣装置配合、锁扣，实现伪电池与待测飞行器之间的固定。第二，在固定于电池仓后，伪电池上设置的导电端子能与电池仓内的金属触点导通，从而为测试中的飞行器提供电源支持。这里所说的“电池仓内的金属触点”可以是电池仓的原有结构；在飞行器实际使用中，安装在电池仓内的真正的电池通过该金属触点为飞行器供电。
通常而言，伪电池可具有与真电池(飞行器的原装电池、配套电池)相同或基本相同的形状或结构，特别是在固定装置与导电端子方面。但是，并不要求必然如此。容易想到，形貌略有差异的伪电池同样可实现上述两方面特征或性能。
这里所说“飞行器在测试中通过伪电池获得电源供应”，其方式可以有多种。比如，伪电池本身可具有类似于真电池的蓄电功能，在测试中为飞行器供电。为美观，真电池在安装于电池仓内后，通常要保证电池的表面不过分突出于机身。伪电池可不必顾忌这点，因而，伪电池可以被设计得具有更大的体积和容量，从而具备更持久的续航时间。为进一步提高续航时间，可将伪电池连接于外部电源(比如，市电)，通过该外部电源持续地输送电力至伪电池与待 测飞行器，避免测试中更换电池的困扰。在测试中，频繁更换电池既拖长了测试周期，也同样不利于测试结果的准确性。另外，伪电池可不必具有电池功能(或者说蓄电功能)，可仅作为连通外部电源(比如，市电)与飞行器的电路通道。
伪电池100可由多个部件组装而成，比如，可由如图中所示的第一部分5、第二部分6与导电端子(或导电端子模组)组合而成。伪电池100在第一、二部分5、6的结合处设置有开口9，导电端子或导电端子模组安装在开口9内。这里所说“导电端子模组”可包括大致呈方形的绝缘体与安装在该绝缘体上的导电端子。
不同飞行器可能会对应不同的导电端子。在需要时(比如，测试另一型号的飞行器时)，可更换开口9内的导电端子或导电端子模组，实现伪电池的导电端子与电池仓内的金属触点完美适配。
伪电池100的第一、二部分5、6可通过螺钉或螺栓组装为一体。比如，在第一部分5上可设置多个螺孔(图中未显示)，第二部分6上可设置多个螺孔65，通过将多个螺钉(图中未显示)依次穿入第一、二部分5、6上的所述螺孔65即可实现伪电池100的组装。
用于安装伪电池100至待测飞行器的固定装置67、69可设置在伪电池100的第二部分6上。所述固定装置可包括滑槽67与锁定部69。位于滑槽67前端的开口672宽度较大，大于滑槽67其它区域的宽度，并呈逐渐变窄状，使得该开口672具有导引电池仓对应部位进入滑槽67的作用。锁定部69可与所述滑槽67相连，以使电池仓上的配合结构(比如，金属弹片)在沿所述滑槽67移动到某一位置时可与所述锁定部69相啮合，从而可防止电池仓上的配合结构退出滑槽67。图1与图2所示实施例中，锁定部69包括两个锁定部691与692，它们沿滑槽67的滑动方向前后布置。另外，第二部分6的内表面上可设置突出的肋条63，以增强第二部分6内表面与电池仓表面的接触。
图1与图2所示实施例中，伪电池100的第一部分5具备蓄电功能，并与外部电源(比如，市电)连通。
测试夹具1000还可包括用于将伪电池100安装于基座300的安装部4。安装部4可固定在伪电池100远离电池仓的一侧(图中的外侧)。可利用螺钉或螺栓结构将安装部4固定于伪电池100。比如，可在伪电池100的第一部分5设置多个螺孔54与56，在安装部4设置多个螺孔44与46；在螺孔44、46与螺孔54、56对齐后，将螺钉或螺栓(图中未显示)依次沿螺孔旋入即可实现两者的固定。
安装部4与基座300中的一个(本实施例中是基座300)设置有滑轨37，另一个(本实施例中是安装部4)设置有导引柱47。通过滑轨37与导引柱47，基座300与伪电池100可滑动安装在一起。滑轨37延伸的方向(图中的竖直方向)可与伪电池100安装在电池仓上的安装方向(图中的前后方向)相互垂直。在滑轨37与导引柱47配合到位后，可进一步通过螺钉或螺栓将两者固定。比如，可在导引柱47上设置螺孔42，在滑轨37处设置螺孔32；滑轨37与导引柱47配合到位后，螺孔32与螺孔42对齐，将螺钉或螺栓(图中未显示)依次旋入螺孔32、42即可实现固定。如图所示实施例中，安装部4整体可呈“T”型，其中，该“T”型结构中的纵向部可作为导引柱47，该“T”型结构中的横向部主要用于安装螺钉、将安装部4固定于伪电池100。
如图所示实施例中，基座300可包括呈板状的基板1、沿垂直于基板1所在平面的方向延伸的竖直部2以及滑轨部3。其中，滑轨部3截面可呈“L”型，可包括沿垂直于基板1所在平面的方向延伸的前述滑轨37，以及平行于基板1的横向延伸部35。横向延伸部35的外侧面上可设置多个螺孔34，竖直部2的上部可设置多个螺孔24；在螺孔24、34对齐后，将螺钉或螺栓(图中未显示)依次旋入螺孔24、34即可实现滑轨部3与竖直部2的固定。
竖直部2上可设置圆形螺孔22，基板1可设置狭长槽12。该狭长槽12的延伸方向(长度方向)可垂直于伪电池100安装至飞行器电池仓的安装方向(沿滑槽67的滑动方向)。将螺钉或螺栓(图中未显示)依次旋入螺孔22与狭长槽12，即可将竖直部2安装于基板1。狭长槽12沿其长度方向具有多个安装位置，螺钉或螺栓可将竖直部2固定在任一个安装位置。在不同的安装位置，竖 直部2与基板1之间的相对位置发生变动。安装位置越靠内，待测飞行器被夹持得越紧。即，通过安装位置的调整/选择，可对测试夹具夹持待测飞行器的力作调整。
基板1上还可设置多个减重孔14，以减轻基板1的重量。
有些飞行器机身上可包括呈对称布置的两个电池仓及电池。相应的，可采用对称设置的两个测试夹具1000来固定该飞行器，如图1与图2所示。
可预先将基板1、竖直部2以及滑轨部3组装成基座300，将伪电池100的第一、二部分5、6以及安装部4组装为一体(以下简称“伪电池模组”)，并将二者作为测试夹具1000的平时状态。需要测试时，可先将伪电池模组安装并固定于待测飞行器；而后可利用导引柱47与滑轨37，将固定于待测飞行器的伪电池模组安装于基座300；最后，通过螺钉或螺栓将伪电池模组与基座300固定。随后，即可开始测试过程。
以上所述仅是本发明的较佳实施例而已，并非对本发明做任何形式上的限制，虽然本发明已以较佳实施例揭露如上，然而并非用以限定本发明，任何熟悉本专业的技术人员，在不脱离本发明技术方案的范围内，当可利用上述揭示的技术内容做出些许更动或修饰为等同变化的等效实施例，但凡是未脱离本发明技术方案的内容，依据本发明的技术实质对以上实施例所作的任何简单修改、等同变化与修饰，均仍属于本发明技术方案的范围内。
本专利文件披露的内容包含受版权保护的材料。该版权为版权所有人所有。版权所有人不反对任何人复制专利与商标局的官方记录和档案中所存在的该专利文件或者该专利披露。

Claims (10)

  1. 一种用于飞行器的测试夹具，所述飞行器包括用于安装电池的电池仓，其特征在于，所述测试夹具包括伪电池，所述伪电池包括适于将所述伪电池安装并锁定在所述电池仓内的固定装置以及导电端子，在所述伪电池安装在所述电池仓时，所述导电端子接触所述电池仓，以使所述飞行器在测试中可通过所述伪电池获得电源供应。
  2. 根据权利要求1所述的测试夹具，其特征在于，所述伪电池包括第一部分与第二部分，所述伪电池在所述第一、二部分的结合处设置有开口，所述导电端子安装在所述开口内。
  3. 根据权利要求2所述的测试夹具，其特征在于，所述第一、二部分中的一个设置有所述固定装置，另一个提供电源功能。
  4. 根据权利要求1所述的测试夹具，其特征在于，所述固定装置包括滑槽与锁定部，所述锁定部与所述滑槽相连，以使电池仓上的配合结构在沿所述滑槽移动到某一位置时可与所述锁定部相啮合。
  5. 根据权利要求1所述的测试夹具，其特征在于，所述测试夹具还包括基座以及用于将所述伪电池安装于所述基座的安装部；
    所述安装部固定在所述伪电池远离所述电池仓的一侧。
  6. 根据权利要求5所述的测试夹具，其特征在于，所述基座与所述安装部中的一个设置有滑轨，另一个设置有导引柱，通过所述滑轨与所述导引柱，所述基座与所述伪电池可滑动安装在一起。
  7. 根据权利要求6所述的测试夹具，其特征在于，所述滑轨延伸的方向与所述伪电池安装在所述电池仓上的安装方向相互垂直。
  8. 根据权利要求6所述的测试夹具，其特征在于，所述安装部整体呈“T”型。
  9. 根据权利要求5所述的测试夹具，其特征在于，所述基座包括呈板状 的基板、沿垂直于所述基板所在平面的方向延伸的竖直部以及滑轨部；
    所述滑轨部截面呈“L”型，包括沿垂直于所述基板所在平面的方向延伸的所述滑轨，以及平行于所述基板的横向延伸部。
  10. 根据权利要求9所述的测试夹具，其特征在于，所述竖直部设置有圆形螺孔，所述基板设置有狭长槽，利用螺钉或螺栓连接所述螺孔与所述狭长槽而将所述竖直部安装于所述基板。
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