Patent Description:
In the process of UAV research & development, it is necessary to simulate the actual flight conditions of UAV. Among them, the actual flight conditions comprises pitching, lifting and so on to conduct comprehensive tests on the whole UAV.

In the prior art, when the UAV needs to carry out the lifting test, it is necessary to place the UAV on the lifting device, fix the UAV on the lifting device, and complete the lifting test. When the UAV needs to conduct the pitching test, it needs to be placed on the pitching device, and the UAV is fixed on the pitching device to complete the pitching test.

It can be seen that at least two devices are required for the UAV test in the prior art so that the two devices occupy a large space. In the process of the test, the UAV needs to be removed from the lifting device and then installed on the pitching device. The intermediate transfer process takes more time, and there may involve multiple transfers, resulting in the low efficiency of the UAV test process.

<CIT> relates to an auxiliary device and a training method for indoor flight practice of an agricultural UAV. <CIT> relates to a complete machine drop test device for a UAV. <CIT> relates to a multi-rotor UAV testing and training integrated platform, which comprises an aerial vehicle and a test box.

The invention aims to provide a UAV test bench. The lifting test and pitching test of the UAV can be carried out on the UAV test bench without multiple transfers of the UAV, thereby reducing the time required for intermediate transfers and improving the efficiency of the UAV test.

The current disclosure concerns a UAV test bench as defined in independent claim <NUM>, with further embodiments being set out in dependent claims.

As conceived above, the technical solution adopted by the invention is: A UAV test bench, comprising:.

The support component includes a support frame, a first support plate, a second support plate and a plurality of support columns, the first support plate is fixedly connected to one end of the support frame, the second support plate is connected with the first support plate through the support column, the first support plate has a first through hole, the universal rotating assembly slides on the first through hole, and one end of the return component is connected to the first support plate, the second support plate is configured to support the fixing component at the original positions, where the fixing component contacts the second support plate.

The universal rotating component comprises a universal joint, a limit sleeve and a fixing shaft, the universal joint comprises a first end and a second end capable of universal rotation relative to the first end, the limit sleeve is arranged outside the universal joint and is fixedly connected to the first end, the fixing component is connected to the second end of the universal joint, and one end of the fixing shaft is connected to the first end of the universal joint, and the other end of the return component is connected to the fixing shaft.

It also includes a bearing seat, a bearing, and a connecting shaft. The bearing is installed in the shaft hole of the bearing seat, one end of the connecting shaft is rotationally connected to the bearing seat and in contact with the inner surface of the bearing, the other end of the connecting shaft is fixedly connected to the other end of the fixing shaft, and the other end of the return component is connected to the bearing seat.

It also includes a first lifting ring fixed on the bearing seat and a second lifting ring fixed on the support component. The return component includes a spring, one end of the spring is hooked on the second lifting ring, and the other end of the spring is hooked on the first lifting ring.

The UAV test bench also includes a linear bearing fixing seat fixed on the first support plate and a linear bearing installed in the linear bearing fixing seat, wherein the linear bearing is configured to guide a sliding of the fixing shaft.

It also includes a limit ring fixed in the middle of the fixed shaft, the size of the limit ring in the horizontal direction is larger than the inner diameter of the linear bearing, the fixing shaft slides to the first limit along the Z direction, and the limit ring butts with the linear bearing or the linear bearing fixing seat.

It also includes a roller and a trailer jack fixed on the roller, and the output end of the trailer jack is connected to the other end of the support frame.

The fixing component includes a connecting seat, a fixing plate and a clamping part, the connecting seat is fixedly connected to the universal rotating component and is slidably connected to the support component, the fixing plate is fixedly connected to the connecting seat, the clamping part is provided in two groups, and the two groups of the clamping parts are fixedly connected to both ends of the fixing plate, respectively.

The clamping part comprises a first clamping plate and a second clamping plate connected with each other, the top surface of the first clamping plate is provided with a first arc groove, the bottom surface of the second clamping plate is provided with a second arc groove, and the first arc groove and the second arc groove form an airfoil hole.

The invention has at least the following beneficial effects:
The UAV test bench provided by the invention, the universal rotating component and the fixing component are sliding on the support component along the Z direction, so that the UAV test bench can meet the requirements of the UAV lifting test, and one end of the universal rotating component can rotate in a universal manner relative to the other end of the universal rotating component, the UAV test bench can meet the requirements of the UAV pitching test, and then the UAV test bench provided by the invention can meet the requirements of the UAV lifting test and the pitching test at the same time, without the need to transfer the UAV for many times, thereby reducing the time required for intermediate transfer and improving the efficiency of the UAV test.

In order to make clearer the technical issues solved, the technical solution adopted and the technical effect achieved by the invention, the technical solution of the invention is further described below in combination with the figures and through the description of the preferred embodiments. It can be understood that the preferred embodiments described here are only used to explain the invention, not to limit the invention. In addition, it should be noted that for the convenience of description, only some parts related to the invention rather than all of them are shown in the figures.

In the description of the invention, it should be noted that the orientation or position relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and so on is based on the orientation or position relationship shown in the figures, only for the convenience of describing the invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, or be constructed and operated in a specific direction, so it cannot be understood as a limitation of the invention. In addition, the terms "first" and "second" are used only for descriptive purposes and cannot be understood as indicating or implying relative importance.

In the description of the invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connect" and "connection" should be understood in a broad sense, for example, it can be fixedly connected or detachably connected. It can be mechanical connection or electrical connection. It can be directly connected, or indirectly connected through an intermediate medium, and it can be the connection between two elements. For those skilled in the art, the specific meaning of the above terms in the invention can be understood in specific circumstances.

This invention provides a UAV test bench, which can be used to fix the UAV, and the lifting test and pitching test of the UAV can be carried out on the UAV test bench, without multiple transfers of the UAV, thereby reducing the time required for intermediate transfers and improving the efficiency of the UAV test. It should be noted that the lifting test involves fixing the UAV, and then manipulating the lifting and lowering of the UAV, so as to observe or detect the condition of the UAV in the process. Similarly, the pitching test involves fixing the UAV, and then manipulating the UAV to perform the pitch action, so as to observe or detect the condition of the UAV in the process. Exemplarily, the UAV in this embodiment is V400 UAV.

As shown in <FIG>, the UAV test bench comprises support component <NUM>, universal rotating component <NUM>, fixing component <NUM> and return component <NUM>.

Among others, the support component <NUM> is used to support the fixing component <NUM>. The universal rotating component <NUM> is slidably arranged on the support component <NUM> in the Z direction, that is, the universal rotating component <NUM> can slide up and down in the Z direction relative to the support component <NUM>.

Moreover, one end of the universal rotating component <NUM> can rotate in a universal manner relative to the other end of the universal rotating component <NUM>. Specifically, the top end of the universal rotating component <NUM> can rotate in a universal manner relative to the bottom end of the universal rotating component <NUM>. It should be noted that the universal rotation in this embodiment means that one end of the universal rotating component <NUM> can rotate relative to the other end of the universal rotating component <NUM> with the numerous axes on the horizontal plane as the rotation center. The numerous axes include the X axis in the X direction, the Y axis in the Y direction and the axis between the X axis and the Y axis. However, one end of the universal rotating component <NUM> cannot rotate around the Z axis.

As shown in <FIG>, the fixing component <NUM> is connected to one end of the universal rotating component <NUM>, and the fixing component <NUM> is used to fix the UAV. During the lifting test, the UAV can drive the fixing component <NUM> and the universal rotating component <NUM> to slide on the support component <NUM>. In the pitching test of the UAV, one end of the fixing component <NUM> and the universal rotating component <NUM> can be adjusted to rotate in universal direction relative to the other end of the universal rotating component <NUM>, so that the UAV test bench will not interfere with the action of the UAV while fixing the UAV.

Referring to <FIG>, one end of the return component <NUM> is connected to the support component <NUM>, and the other end of the return component <NUM> is connected to the other end of the universal rotating component <NUM>. When the universal rotating component <NUM> slides relative to the support component <NUM>, it can compress the return component <NUM>. When the external force on the universal rotating component <NUM> disappears, the return component <NUM> can drive the universal rotating component <NUM> and the fixing component <NUM> to reset, which can facilitate other tests.

The UAV test bench provided in this embodiment, the universal rotating component <NUM> and the fixing component <NUM> slide on the support component <NUM> along the Z direction, so that the UAV test bench can meet the requirements of the UAV lifting test, and one end of the universal rotating component <NUM> can rotate in a universal manner relative to the other end of the universal rotating component <NUM>, so that the UAV test bench can meet the requirements of the UAV pitching test. Thus, the UAV test bench provided in this embodiment can meet the requirements of the UAV lifting test and the pitching test at the same time, without the need to transfer the UAV for many times, thereby reducing the time required for intermediate transfer and improving the efficiency of the UAV test.

As shown in <FIG>, the support component <NUM> comprises a support frame <NUM>, a first support plate <NUM>, a second support plate <NUM>, and a plurality of support columns <NUM>. The support frame <NUM> is formed by connecting a plurality of vertical rods, horizontal rods and inclined rods, and the support frame <NUM> is in a pyramid shape in the whole. The first support plate <NUM> is fixedly connected to the top of the support frame <NUM>, the second support plate <NUM> is connected to the first support plate <NUM> through a plurality of support columns <NUM>, and the first support plate <NUM> and the second support plate <NUM> are parallel to each other and parallel to the horizontal plane. The first support plate <NUM> has a first through hole, and the universal rotating component <NUM> slides along the Z direction and is arranged in the first through hole. One end of the return component <NUM> is connected to the first support plate <NUM>, and the second support plate <NUM> is configured to support the fixing component <NUM>. When the fixing component <NUM> is in an unstressed state, the fixing component <NUM> is supported by the second support plate <NUM>. In this embodiment, the second support plate <NUM> is provided with a second through hole, and the universal rotating component <NUM> is connected to the fixing component <NUM> through the second through hole.

As shown in <FIG>, the fixing component <NUM> comprises a connecting seat <NUM>, a fixing plate <NUM>, and a clamping part <NUM>. Among others, the connecting seat <NUM> is fixedly connected to the universal rotating component <NUM> and slidably connected to the support component <NUM>. Specifically, the connecting seat <NUM> is slidably arranged in the second through hole. The fixing plate <NUM> is fixedly connected to the connecting seat <NUM>, and the clamping parts <NUM> are provided in two groups. The two groups of clamping parts <NUM> are fixedly connected to both ends of the fixing plate <NUM>, respectively, and each group of clamping parts <NUM> is used to clamp one wing of the UAV.

Among others, the clamping parts <NUM> comprise an interconnected first clamping plate <NUM> and a second clamping plate <NUM>, the first clamping plate <NUM> and the second clamping plate <NUM> match with each other to clamp the wing of the UAV, and the bottom end of the first clamping plate <NUM> is fixedly connected to the fixed plate <NUM>. In some embodiments, the first clamping plate <NUM> is bolted to the second clamping plate <NUM>, and the bottom end of the first clamping plate <NUM> is bolted to the fixing part <NUM>.

Further, referring to <FIG>, the top surface of the first clamping plate <NUM> has a first arc groove, and the bottom surface of the second clamping plate <NUM> has a second arc groove. When the first clamping plate <NUM> is connected to the second clamping plate <NUM>, the first arc groove and the second arc groove form an airfoil hole <NUM> for clamping the wing of the UAV. The shape and size of the first arc groove and the second arc groove are confirmed, respectively, according to the shape and size of the wing, which is not limited in this embodiment.

Please continue to refer to <FIG>. A plurality of first reinforcing plates <NUM> are fixed on the side of each first clamping plate <NUM>, and a plurality of first reinforcing plates <NUM> are cross fixed on the first clamping plate <NUM> to improve the structural strength of the first clamping plate <NUM>. Similarly, a plurality of second reinforcing plates (not shown) are fixed on the side of each second clamping plate <NUM>, and the plurality of second reinforcing plates are connected in turn and used to improve the structural strength of the second clamping plate <NUM>.

In this invention, a plurality of weight reduction holes are arranged on the fixing plate <NUM> to make the weight of the fixing plate <NUM> smaller and facilitate the driving of the fixing plate <NUM>. A plurality of weight reduction holes are symmetrically arranged with the fixing seat <NUM> so that the symmetrical center could prevent the weight of one end of the fixing plate <NUM> from being greater than that of the other end, thereby preventing interference with the UAV test.

Referring to <FIG>, the UAV test bench also comprises a roller <NUM> and a trailer jack <NUM> fixedly arranged on the roller <NUM>. The output end of the trailer jack <NUM> is connected to the other end of the support frame <NUM>, and the trailer jack <NUM> is used to drive the support frame <NUM> to rise and fall. Exemplarily, turning the rocker of the trailer jack <NUM> can extend or retract the output end of the trailer jack <NUM>. The support frame <NUM> can be rotated by the roller <NUM>.

<FIG> is the structural diagram of a universal rotating device provided in this embodiment. As shown in <FIG>, the universal rotating component <NUM> comprises a universal joint <NUM>, a limit sleeve <NUM> and a fixing shaft <NUM>. The universal joint <NUM> comprises a first end <NUM> and a second end <NUM> that can rotate in a universal manner relative to the first end <NUM>. The limit sleeve <NUM> is sleeved outside the universal joint <NUM> and fixedly connected to the first end <NUM>. In some embodiments, the first end <NUM> of the universal joint <NUM> is fixedly connected to the limit sleeve <NUM> through the first connector <NUM>. The fixing component <NUM> is connected to the second end <NUM> of the universal joint <NUM>, one end of the fixing shaft <NUM> is connected to the first end <NUM> of the universal joint <NUM>, and the other end of the return component <NUM> is connected to the fixing shaft <NUM>. The first connector <NUM> includes but does not limit studs, screws, bolts, etc..

Further, the inner wall of the limit sleeve <NUM> is provided with a limit connical surface, which is used to limit the movement range of the second end <NUM> of the universal joint <NUM>, and then limit the movement range of the fixing component <NUM>, to prevent the fixing component <NUM> over-movement.

In this embodiment, as shown in <FIG>, the UAV test bench also comprises a bearing seat <NUM>, a bearing <NUM> and a connecting shaft <NUM>. Among them, the bearing <NUM> is installed in the shaft hole of the bearing seat <NUM>, and one end of the connecting shaft <NUM> is rotatably connected to the bearing seat <NUM> and in contact with the inner surface of the bearing <NUM>, so that one end of the connecting shaft <NUM> is supported and limited by the bearing <NUM> in the horizontal direction. The other end of the connecting shaft <NUM> is fixedly connected to the other end of the fixing shaft <NUM>, and the fixing shaft <NUM> can drive the connecting shaft <NUM> to rotate. Moreover, when the fixing shaft <NUM> rotates, only the connecting shaft <NUM> rotates, but the bearing seat <NUM> does not rotate with the connecting shaft <NUM>. The other end of the return component <NUM> is connected to the bearing seat <NUM>, that is, the return component <NUM> is indirectly connected to the other end of the fixing shaft <NUM> through the bearing seat <NUM>. As shown in <FIG>, the connecting shaft <NUM> is rotatably connected to the bearing seat <NUM> by a second connector <NUM> passing through the bearing seat <NUM>. The second connector <NUM> includes but does not limit the structure such as studs, bolts, etc..

Further, the UAV test bench also comprises a first lifting ring <NUM> fixedly arranged on the bearing seat <NUM> and a second lifting ring <NUM> fixedly arranged on the bottom surface of the first support plate <NUM> of the support component <NUM>. The return component <NUM> includes a spring, one end of which is hooked on the second lifting ring <NUM>, and the other end of which is hooked on the first lifting ring <NUM>. When the universal rotating component <NUM> slides forward in the Z direction driven by the UAV, the fixing shaft <NUM> drives the connecting shaft <NUM> and the bearing seat <NUM> to move forward in the Z direction. Since the support component <NUM> does not move, the spring is compressed and the elastic potential energy is stored. When the external force acting on the universal rotating component <NUM> disappears, under the action of the spring force, the bearing seat <NUM> is pushed to move in the negative direction of Z, and the universal rotating component <NUM> and the fixing component <NUM> are driven to move in the negative direction of Z, so as to realize the reset of the universal rotating component <NUM> and the fixing component <NUM>. Among them, the original positions of the universal rotating component <NUM> and the fixing component <NUM> are the positions where the fixing component <NUM> shown in <FIG> contacts the second support plate <NUM>.

In order to facilitate the sliding and rotating of the fixing shaft <NUM> on the first support plate <NUM>, as shown in <FIG>, the UAV test bench also includes a linear bearing fixing seat <NUM> fixedly arranged on the first support plate <NUM> and a linear bearing <NUM> installed in the linear bearing fixing seat <NUM>. The fixing shaft <NUM> is threaded in the linear bearing <NUM>, so that the linear bearing <NUM> can guide the sliding of the fixing shaft <NUM>.

Further, referring to <FIG>, the UAV test bench also comprises a limit ring <NUM> fixedly arranged in the middle of the fixing shaft <NUM>. The limit ring <NUM> is sleeved and fixed on the fixing shaft <NUM>, and the size of the limit ring <NUM> in the horizontal direction is larger than the inner diameter of the linear bearing <NUM>, so that the limit ring <NUM> will not enter the linear bearing <NUM>. The limit ring <NUM> is used to limit the movement limit of the fixing shaft <NUM>. Specifically, the fixing shaft <NUM> slides to the first limit in the positive direction of the Z direction, and the limit ring <NUM> butts with the linear bearing <NUM> or the linear bearing fixing seat <NUM>, so that the fixing shaft <NUM> cannot continue to move in the positive direction of the Z direction, thereby realizing the limit of the fixing shaft <NUM> and the fixing component <NUM>. The second support plate <NUM> limits the lower limit of movement of the fixing shaft <NUM> and the fixing component <NUM>.

Claim 1:
A UAV test bench comprising:
a support component (<NUM>);
a universal rotating component (<NUM>), which is sliding on the support component (<NUM>) along the Z direction, and one end of the universal rotating component (<NUM>) can rotate in a universal manner relative to the other end of the universal rotating component (<NUM>);
a fixing component (<NUM>), which is connected to one end of the universal rotating component (<NUM>), and the fixing component (<NUM>) is configured to fix the UAV;
a return component (<NUM>), one end of which is connected to the support component (<NUM>), and the other end of which is connected to the other end of the universal rotating component (<NUM>), wherein,
the return component (<NUM>) is configured to drive the universal rotating component (<NUM>) and the fixing component (<NUM>) to reset at original positions,
the support component (<NUM>) comprises a support frame (<NUM>), a first support (<NUM>), a second support plate (<NUM>) and a plurality of support columns (<NUM>), the first support (<NUM>) is fixedly connected to one end of the support frame (<NUM>), and the second support plate (<NUM>) is connected with the first support (<NUM>) through the support columns (<NUM>), the first support (<NUM>) has a first through hole, the universal rotating component (<NUM>) is sliding on the first through hole, one end of the return component (<NUM>) is connected to the first support (<NUM>), and the second support plate (<NUM>) is configured to support the fixing component (<NUM>) at the original positions, where the fixing component (<NUM>) contacts the second support plate (<NUM>), and
the universal rotating component (<NUM>) comprises a universal joint (<NUM>) and a fixed shaft (<NUM>), the universal joint (<NUM>) comprises a first end (<NUM>) and a second end (<NUM>) capable of universal rotation relative to the first end (<NUM>), the fixing component (<NUM>) is connected to the second end (<NUM>) of the universal joint (<NUM>), one end of the fixed shaft (<NUM>) is connected to the first end (<NUM>) of the universal joint (<NUM>), and the other end of the return component (<NUM>) is connected to the fixed shaft (<NUM>),
characterized in that
the first support (<NUM>) is in the form of a support plate,
the universal rotating component (<NUM>) further comprises a limit sleeve (<NUM>), and the limit sleeve (<NUM>) is sleeved outside the universal joint (<NUM>) and fixedly connected to the first end (<NUM>).