阅读说明：本技术 一种弹射起飞的无人机全机静力试验柔性支持方法 (Flexible support method for catapult-assisted take-off unmanned aerial vehicle full-aircraft static test ) 是由 董天智 曹文斌 傅芳 刘畅 刘迪威 刘海峰 饶勇刚 于 2021-08-25 设计创作，主要内容包括：本申请涉及无人机技术领域,公开了一种弹射起飞的无人机全机静力试验柔性支持方法,本方法在弹射起飞无人机机身非考核结构框处粘贴胶布带,垂向支持通过三个起吊葫芦与连接件对拉,起吊葫芦和连接件都与加载框架相连。当试验未进行加载时,无人机依靠三个起吊葫芦调整飞机初始姿态,当向上载荷施加时,通过连接件约束飞机垂向位移、俯仰和滚转,飞机框两侧的胶布带通过连接件连接至立柱,约束无人机的侧向位移和偏航,而无人机的航向约束则通过连接杆连接至飞机假发,由此达到飞机静定支持状态。本申请既节约了试验经费又缩短了试验周期,并且对试验结果的影响也很小,整个过程操作简单,具有较大实际应用价值。(The application relates to the technical field of unmanned aerial vehicles, and discloses a flexible support method for a full-mechanical static test of an catapult-assisted take-off unmanned aerial vehicle. When the experiment was not carried out the loading, unmanned aerial vehicle relied on the three calabash of lifting by crane to adjust the aircraft initial attitude, when the upward load was applyed, retrained vertical displacement of aircraft, every single move and roll over through the connecting piece, and the rubberized fabric area of aircraft frame both sides is connected to the stand through the connecting piece, retrains unmanned aerial vehicle's lateral displacement and driftage, and unmanned aerial vehicle's course restraint then is connected to the aircraft wig through the connecting rod, reaches the quiet supporting state of aircraft from this. The method and the device have the advantages that the test cost is saved, the test period is shortened, the influence on the test result is small, the operation of the whole process is simple, and the method and the device have great practical application value.)

1. A flexible support method for a catapult-assisted take-off unmanned aerial vehicle full-aircraft static test is characterized by comprising the following steps: the method specifically comprises the following steps:

A. determining a supporting constraint form;

B. determining a support position;

C. determining an aircraft support altitude;

D. sticking and connecting the adhesive tape;

E. hoisting the unmanned aerial vehicle;

F. adjusting the connecting piece to restrain and support the unmanned aerial vehicle;

G. and adjusting the posture of the unmanned aerial vehicle and connecting pretightening force.

2. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle as claimed in claim 1, wherein the method comprises the following steps: in the step A, three lifting points are firstly set, three vertical constraint points are correspondingly set and used for constraining the vertical displacement, pitching and rolling of the unmanned plane, then four opposite-pulling lateral constraint points are set to constrain the lateral displacement and yawing of the plane, and finally a connecting piece is used for connecting an engine dummy piece to constrain the course of the unmanned plane.

3. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle as claimed in claim 1, wherein the method comprises the following steps: and in the step B, selecting a structural position which has higher strength of a front body frame and a rear body frame of the ejection unmanned aerial vehicle and is far away from the wing body connecting joint and does not influence the normal deformation of the unmanned aerial vehicle body and the stress distribution of the examination part as a full-static test support position according to a finite element calculation result.

4. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle as claimed in claim 1, wherein the method comprises the following steps: and in the step C, determining the support height of the unmanned aerial vehicle according to the installation requirement of the test loading equipment and the height of the test loading frame.

5. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle as claimed in claim 1, wherein the method comprises the following steps: and D, sticking a plurality of adhesive tapes on the left and right sides of the front and rear frames of the machine body at the selected support positions according to the test load, and simultaneously sticking a plurality of adhesive tapes on the belly and the top of the machine body respectively to uniformly distribute the test load on the frame structure of the machine body.

6. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle as claimed in claim 1, wherein the method comprises the following steps: and E, connecting the lifting hoist with an adhesive tape on the top of the machine body, and lifting the unmanned aerial vehicle to a corresponding supporting height.

7. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle as claimed in claim 1, wherein the method comprises the following steps: and in the step F, after the unmanned aerial vehicle is lifted to a supporting height, connecting the unmanned aerial vehicle belly, the lateral adhesive tape of the body and the engine dummy piece of the unmanned aerial vehicle to the upright post of the loading frame through the connecting piece with the left and right thread structures, respectively installing a vertical constraint force load sensor, a lateral constraint force load sensor and a heading constraint force load sensor on the connecting piece, and then adjusting the length of the connecting piece on the engine dummy piece to enable the numerical value of the heading force load sensor to be close to zero.

8. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle as claimed in claim 1, wherein the method comprises the following steps: and G, measuring horizontal measuring points of the front and rear bodies of the unmanned aerial vehicle, the height of the wing tip measuring points of the left and right wings from the load bearing terrace by using a laser measuring instrument, adjusting the length of a hoisting hoist of a hoisting point according to a measuring result, then adjusting the length of a connecting piece at the lateral constraint point of the body, so that the values of the lateral constraint force load sensors at the left and right sides are equal, and finally adjusting the pretightening force of the connecting piece at the vertical constraint point of the body to 0.1KN according to the feedback value of the vertical constraint force load sensors.

9. The method for flexibly supporting the full-aircraft static test of the catapult-assisted take-off unmanned aerial vehicle according to any one of claims 1 or 5, characterized in that: the strength of the adhesive tape is 3 times of the load borne by the machine body frame.

Technical Field

The application relates to the technical field of unmanned aerial vehicles, in particular to a flexible support method for a full-aircraft static test of an unmanned aerial vehicle taking off by catapulting.

Background

In the ground static test of the airplane, the airplane needs to have a certain supporting state so as to ensure the stable attitude of the airplane in the test process. The support of the test airplane should simulate the state of the test airplane in the actual use and flight process as much as possible, meanwhile, the test load application and the installation and the inspection of other corresponding test equipment must be facilitated, and the normal deformation of the test airplane body and the stress distribution of an examined part cannot be influenced. For the situation that the test support position needs to be applied with passive load, the situation that the aircraft support position is arranged at a position which is not an important examination part and has higher rigidity needs to be considered, and meanwhile, errors caused by the passive load, the test loading and the installation errors are considered to be accumulated to the passive loading point.

At present, in a conventional aircraft full-aircraft static test, an undercarriage is usually selected as a support device of the aircraft static test, and vertical constraint points are arranged at a front main crane and a main crane to constrain the vertical displacement, pitching and rolling of the aircraft; a lateral constraint point is arranged on the left main crane to constrain lateral displacement; the left and right main cranes set a heading constraint point to constrain displacement and yaw so that the aircraft reaches a static support state to evaluate the test load application error through load error monitoring of the support position. However, for an unmanned aerial vehicle which does not have a landing gear, adopts catapult takeoff, and lands with a parachute, it is obviously impossible to carry out a full-static test by adopting the method, while the existing method generally adopts the method of inverting the aircraft, then suspending the aircraft by a crane, and loading the wings of the aircraft downwards, so that the method cannot load the load of the aircraft body, which is different from the actual stress of the aircraft.

Disclosure of Invention

In order to overcome the problems and the defects in the prior art, the application provides the full-static test flexible support method of the unmanned aerial vehicle which adopts the catapult takeoff and is specially used for no undercarriage.

In order to achieve the above object, the technical solution of the present application is as follows:

a flexible support method for a catapult-assisted take-off unmanned aerial vehicle full-aircraft static test specifically comprises the following steps:

A. determining a supporting constraint form;

B. determining a support position;

C. determining an aircraft support altitude;

D. sticking and connecting the adhesive tape;

E. hoisting the unmanned aerial vehicle;

F. adjusting the connecting piece to restrain and support the unmanned aerial vehicle;

G. and adjusting the posture of the unmanned aerial vehicle and connecting pretightening force.

Furthermore, in the step a, at first, three lifting points are set, three vertical constraint points are correspondingly set for constraining the vertical displacement, pitching and rolling of the unmanned aerial vehicle, then, four opposite-pulling lateral constraint points are set for constraining the lateral displacement and yawing of the aircraft, and finally, a connecting piece is used for connecting the engine dummy piece to constrain the heading of the unmanned aerial vehicle.

And further, in the step B, selecting a structural position which has higher strength of a front body frame and a rear body frame of the ejection unmanned aerial vehicle and is far away from the wing body connecting joint and does not influence the normal deformation of the unmanned aerial vehicle body and the stress distribution of the check part as a full-static test support position according to a finite element calculation result.

Further, in the step C, the support height of the unmanned aerial vehicle is determined according to the installation requirement of the test loading device and the height of the test loading frame.

Furthermore, in the step D, according to the test load, a plurality of adhesive tapes are adhered to the left and right sides of the front and rear frames of the body at the selected support position, and a plurality of adhesive tapes are also adhered to the belly and the top of the body respectively, so that the test load is uniformly distributed on the frame structure of the body.

Further, in the step E, the hoisting gourd is connected with the adhesive tape on the top of the unmanned aerial vehicle body, and the unmanned aerial vehicle is hoisted to the corresponding supporting height.

Further, in the step F, after the unmanned aerial vehicle is lifted to the supporting height, the connecting pieces with the left and right thread structures are used for respectively connecting the rubber cloth belts on the lateral sides of the belly and the body of the unmanned aerial vehicle and the engine dummy piece of the unmanned aerial vehicle to the upright post of the loading frame, the connecting pieces are respectively provided with a vertical constraint force load sensor, a lateral constraint force load sensor and a heading constraint force load sensor, and then the length of the connecting pieces on the engine dummy piece is adjusted to enable the numerical value of the heading force load sensor to be close to zero.

And G, measuring horizontal measuring points of the front and rear bodies of the unmanned aerial vehicle and the heights of wing tips measuring points of the left and right wings from the bearing terrace by using a laser measuring instrument, adjusting the length of a lifting hoist of a lifting point according to a measuring result, then adjusting the length of a connecting piece at a lateral constraint point of the body, so that the values of lateral constraint force load sensors on the left and right sides are equal, and finally adjusting the pretightening force of the connecting piece at the vertical constraint point of the body to 0.1KN according to the feedback value of the vertical constraint force load sensors.

Further, it is characterized in that: the strength of the adhesive tape is 3 times of the load borne by the machine body frame.

The beneficial effect of this application:

(1) the method is convenient to install, saves test cost, shortens test period, has little influence on test results, is simple to operate in the whole process, and has great practical application value.

(2) This application leads to directly sets up unmanned aerial vehicle restraint support position through the rubberized tape on the fuselage frame, does not destroy fuselage structural integrity and directly supports unmanned aerial vehicle, adopts three lifting point can conveniently adjust the unmanned aerial vehicle gesture simultaneously to carry out the static test to whole unmanned aerial vehicle, and can also play the guard action to unmanned aerial vehicle in experimental loading process.

(3) The test restriction support is 6-degree-of-freedom static support, the restriction support position is far away from the main checking part, the stress is real, the influence on the test result is small, and the precision is high.

Drawings

FIG. 1 is a flow chart of the method of the present application;

FIG. 2 is a schematic side view of a full-aircraft static test flexible support shaft of the catapult takeoff unmanned aerial vehicle;

FIG. 3 is a schematic top view of a full-aircraft static test flexible support of the catapult takeoff unmanned aerial vehicle of the present application;

fig. 4 is a schematic structural diagram of the connector of the present application.

Detailed Description

The present application will be described in further detail with reference to examples, but the embodiments of the present application are not limited thereto.

Because the catapult type take-off unmanned aerial vehicle adopts catapult take-off, and does not have an undercarriage, and also depends on a parachute to land when landing, therefore, the conventional and universal flexible support mode of the full-aircraft static test of the aircraft is not applicable to the catapult type take-off unmanned aerial vehicle. With reference to the attached figures 1-4 of the specification, the method specifically comprises the following seven steps:

step one, determining a supporting constraint form

Firstly, three lifting points are arranged on a fuselage, then three vertical constraint points are correspondingly arranged on the fuselage and are used for constraining the vertical displacement, pitching and rolling of the flying unmanned aerial vehicle, then four opposite-pulling lateral constraint points are arranged on the fuselage and constrain the lateral displacement and yawing of the aircraft, finally a connecting piece is used for connecting an engine dummy of the unmanned aerial vehicle and constraining the course of the unmanned aerial vehicle, and the unmanned aerial vehicle realizes a six-degree-of-freedom static support state;

the lifting point is used for lifting the unmanned aerial vehicle and adjusting the posture of the unmanned aerial vehicle after the unmanned aerial vehicle enters the test derrick, the lifting point usually adopts a lifting rope with a higher safety coefficient as connection, after the whole unmanned aerial vehicle is subjected to test deduction, the load of the lifting point is close to zero, the safety of the unmanned aerial vehicle is protected in the test process, and the unmanned aerial vehicle can be protected from falling and is always in a suspended state after the test is structurally damaged or abnormally unloaded; further, when the unmanned aerial vehicle has a lateral yaw trend, the lateral constraint point realizes the stability of the lateral attitude of the aircraft through the pulling force of opposite pulling at two sides;

step two, determining a supporting position

According to a finite element calculation result, selecting a structural position which has higher strength of a front body frame and a rear body frame of the ejection unmanned aerial vehicle and is far away from a wing body connecting joint, and does not influence the normal deformation of the unmanned aerial vehicle body and the stress distribution of an examination part as a full-static test support position, wherein the support position is the setting position of each lifting point and a constraint point in the first step, and the support position selects two frames with far distances, so that the arm of force is longer, and the limitation of pitching, rolling and yawing of the unmanned aerial vehicle is facilitated; the lifting points, the vertical constraint points and the lateral constraint points are arranged on the front machine body frame and the rear machine body frame and are positioned at the top of the machine body, the vertical constraint points are arranged on the front machine body frame and the rear machine body frame and are positioned at the belly of the machine body, and the lateral constraint points are arranged on the front machine body frame and the rear machine body frame and are positioned at the left side and the right side of the machine body;

step three, determining the supporting altitude of the airplane

Finally determining the support height of the unmanned aerial vehicle according to the installation requirement of the test loading equipment, the height of the test loading frame and the convenience of personnel operation; the unmanned aerial vehicle can be supported to a position about 2500mm away from the horizontal line of the airplane;

step four, sticking and connecting adhesive tape

Because the unmanned aerial vehicle of catapult takeoff does not have the undercarriage, can't the structure of the direct connection plane, in order to fix the plane, adopt the form of the rubberized tape to fix the unmanned aerial vehicle, and while pasting the rubberized tape, in order not to destroy the structural integrality of unmanned aerial vehicle itself, so according to the test load, paste a plurality of rubberized tapes on the fuselage front and back frame both sides of the selected support position, also paste a plurality of rubberized tapes respectively at belly and top of fuselage at the same time, distribute the test load on the fuselage frame structure evenly; the selection of the adhesive tape is selected according to 3 times of the load borne by the machine body frame, namely the strength of the adhesive tape is at least 3 times of the load borne by the machine body frame;

step five, lifting the unmanned aerial vehicle

After the adhesive tape is firmly adhered, the hoisting block is connected to the adhesive tape positioned at the top of the unmanned aerial vehicle body, and the unmanned aerial vehicle is hoisted to a corresponding supporting height by using the hoisting block;

step six, adjusting connecting piece to restrain and support the unmanned aerial vehicle

After the airplane is lifted to an approximate supporting height, connecting pieces with left and right thread structures, which are usually adopted in a static test, are respectively connected with the abdomen of the unmanned aerial vehicle and a lateral rubberized fabric belt of a machine body, the other end of each connecting piece is connected to a stand column of a loading frame, then a connecting piece with left and right thread structures is continuously adopted to connect an engine dummy piece of the unmanned aerial vehicle to the stand column of the loading frame, then a vertical constraint force load sensor, a lateral constraint force load sensor and a course constraint force load sensor are respectively installed on the connecting pieces, the vertical constraint force load sensor is positioned on the connecting pieces of the abdomen of the unmanned aerial vehicle, the lateral constraint force load sensor is positioned on the lateral connecting pieces of the machine body of the unmanned aerial vehicle, the course constraint force load sensor is positioned on the connecting pieces of the engine dummy piece of the unmanned aerial vehicle, then the length of the connecting pieces on the engine dummy piece is adjusted to enable the value of the course force load sensor to be close to zero value, finally, connecting the unmanned aerial vehicle belly with an adhesive tape at the unmanned aerial vehicle belly through a connecting piece, and connecting the unmanned aerial vehicle belly to a force bearing terrace; the connecting piece is the prior art well known to the person skilled in the art, and consists of a plurality of adjustable-length connecting pieces and fixed-length connecting pieces;

and seventhly, adjusting the posture of the unmanned aerial vehicle and connecting the pretightening force.

The laser measuring instrument is adopted to measure the height between the horizontal measuring points of the front and the rear fuselage of the unmanned aerial vehicle and the wing tip measuring points of the left and the right wings and the force bearing terrace, the length of a hoisting block at a hoisting point is adjusted according to the measurement result, so that the theoretical horizontal height of the unmanned aerial vehicle is within 2500mm +/-1 mm, then the connecting piece at the lateral restraining point of the machine body is tightened or loosened, so that the center line of the machine head and the machine tail of the unmanned aerial vehicle is kept at the test installation position, the connecting piece at the lateral restraining point can be tightened at the moment, finally, the values of the lateral restraining force load sensors at the left side and the right side are equal, according to the force bearing condition of the structure frame, can be kept at about 0.1KN, and finally the connecting piece at the vertical constraint point is tightened, the pre-tightening force of the connecting piece at the vertical constraint point of the machine body is adjusted to be about 0.1KN according to the feedback numerical value of the vertical constraint force load sensor, and the effect of tensioning the unmanned aerial vehicle is achieved.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The foregoing is directed to embodiments of the present invention, which are not limited thereto, and any simple modifications and equivalents thereof according to the technical spirit of the present invention may be made within the scope of the present invention.