CN213168606U - Bird-like flapping-wing aircraft testing device - Google Patents
Bird-like flapping-wing aircraft testing device Download PDFInfo
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- CN213168606U CN213168606U CN202021581286.4U CN202021581286U CN213168606U CN 213168606 U CN213168606 U CN 213168606U CN 202021581286 U CN202021581286 U CN 202021581286U CN 213168606 U CN213168606 U CN 213168606U
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Abstract
The utility model discloses an imitative bird flapping wing aircraft testing arrangement belongs to unmanned aerial vehicle test equipment technical field. Comprises a test frame body and a comprehensive stress detection device for the test frame body; the test frame body comprises a sensor detection support, a bearing frame and an aircraft connecting seat; the sensor detection bracket is an isosceles triangle horizontal bracket which is horizontally arranged; the force bearing frame comprises an aircraft axial positioning support and an oblique beam; the comprehensive stress detection device for the test rack body comprises three force measurement supports; the hinged ends of the sensor detection supports of the three force measurement supports are respectively hinged with two bottom angle ends and a top angle end of an isosceles triangle horizontal support formed by the sensor detection supports through a sensor detection support hinged structure, so that the sensor detection supports are positioned in a horizontal position, and the plane of the resultant force direction detected by each combined type force measurement sensor is parallel to the vertical bisector of the bottom beam of the isosceles triangle horizontal support formed by the sensor detection supports. The device has the characteristics of reasonable structure, convenience and quickness in operation, accuracy in test and the like.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle test equipment technical field.
Background
The miniature aircraft has small size and high efficiency, and is considered to have great significance in the military field. The bird-like flapping-wing micro aircraft has small size and high concealment, has the load capacity enough to carry reconnaissance equipment or attack weapons, and is very suitable for carrying reconnaissance of individual soldiers and special operations. In the civil field, the bird-like flapping-wing micro aircraft has high maneuverability, low noise and high flying efficiency, and can be competent for tasks such as urban flight, low-altitude inspection, disaster search and rescue and the like.
Because the aerodynamic mechanism of the miniature bird-like flapping-wing aircraft is complex, the flapping of the flapping wing of the miniature bird-like flapping-wing aircraft relates to multiple disciplines such as structure science, aerodynamics, kinematics and the like, the force and moment generated by the flapping of the flapping wing in the flight of the miniature bird-like flapping-wing aircraft are difficult to obtain through calculation, and a set of equipment capable of accurately measuring the flapping force and moment of the flapping wing through tests and a corresponding test method are urgently needed. Compared with the insect-simulated and hummingbird-simulated aircraft, the bird-simulated aircraft has larger size and weight, the force and the moment generated when the flapping wings flap are far larger than the former, and the magnitude order of the force and the moment is close, which puts higher requirements on test measurement equipment. However, at present, a test platform for a bird-like flapping-wing aircraft is relatively lacking, and the problems that the force measuring range is small, the measuring torque range is far smaller than the force measuring range, the space for installing the aircraft is limited and the like exist, so that the problems that the related aircraft force measuring test is complex in equipment, complex in operation, low in precision, poor in universality and the like exist, and the research and development of the miniature bird-like flapping-wing aircraft are greatly hindered.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide an imitative bird flapping wing aircraft testing arrangement, it has rational in infrastructure, the simple operation, characteristics such as test accuracy.
In order to solve the technical problem, the utility model discloses the technical scheme who takes is:
a bird-like flapping-wing aircraft testing device comprises a testing frame body and a comprehensive testing device for testing the stress of the testing frame body;
the test frame body comprises a sensor detection support, a bearing frame and an aircraft connecting seat;
the sensor detection support is an isosceles triangle horizontal support which is horizontally arranged and comprises a bottom beam and two side beams with the same length, one ends of the two side beams are respectively and fixedly connected with two ends of the bottom beam to form two bottom angle ends of the isosceles triangle horizontal support, and the other ends of the two side beams are fixedly connected together to form a top angle end of the isosceles triangle horizontal support;
the force bearing frame comprises an aircraft axial positioning support and an oblique beam, the aircraft axial positioning support is an (upward) isosceles triangle vertical support and comprises two side beams with equal lengths, the bottom ends of the two side beams are fixedly connected with the two ends of the bottom beam respectively to form two bottom angle ends of the isosceles triangle vertical support, the top ends of the two side beams are fixedly connected together to form a vertex angle end of the isosceles triangle vertical support, the bottom end of the oblique beam is fixedly connected with a vertex angle end of the sensor detection support, the top end of the oblique beam is fixedly connected with the vertex angle end of the aircraft axial positioning support to form a force bearing support for the aircraft axial positioning support, and the aircraft connecting seat is fixed at the vertex angle end of the aircraft axial positioning support so that the vertical projection position of the aircraft connecting seat is positioned on a vertical bisector of the bottom beam of the isosceles triangle horizontal support formed by the sensor detection support;
the comprehensive stress detection device for the test rack body comprises three force measurement supports, each force measurement support comprises a base and a combined type force measurement sensor, and each combined type force measurement sensor comprises a horizontal pull pressure sensor and a vertical pull pressure sensor; the base is provided with a combined type force measuring sensor mounting space, one end of a horizontal pull pressure sensor is hinged with the side wall of the combined type force measuring sensor mounting space through a support hinge structure, one end of a vertical pull pressure sensor is hinged with the bottom side wall of the combined type force measuring sensor mounting space through a support hinge structure, and the other ends of the horizontal pull pressure sensor and the vertical pull pressure sensor are hinged together through a sensor detection support hinge structure to form a sensor detection support hinge end; the horizontal tension and pressure sensor and the vertical tension and pressure sensor are arranged in the installation space of the combined type force measuring sensor in a right angle mode, the horizontal tension and pressure sensor detects the tension and pressure in the horizontal direction, the vertical tension and pressure sensor detects the tension and pressure in the vertical direction, and the hinged end of the sensor detection support can freely move along the resultant force direction detected by the combined type force measuring sensor;
the hinged ends of the sensor detection supports of the three force measurement supports are respectively hinged with two bottom angle ends and a top angle end of an isosceles triangle horizontal support formed by the sensor detection supports through a sensor detection support hinged structure, so that the sensor detection supports are positioned in a horizontal position, and the plane of the resultant force direction detected by each combined type force measurement sensor is parallel to the vertical bisector of the bottom beam of the isosceles triangle horizontal support formed by the sensor detection supports.
The utility model discloses the further improvement lies in:
the base is provided with a vertical surface and a horizontal surface, the side end part of the horizontal surface is intersected with the bottom end part of the vertical surface, and a composite force transducer mounting space is formed between the vertical surface and the horizontal surface; the vertical surface is a side wall of the installation space of the combined type force measuring sensor, and the horizontal surface is a bottom side wall of the installation space of the combined type force measuring sensor.
The support hinged structure comprises a first bearing seat and a bearing arranged in the first bearing seat, a hinge shaft and a pair of hinge supports, wherein the hinge shaft is arranged between the two hinge supports, and the first bearing seat is embedded in a gap between the two hinge supports and enables a bearing hole to be in running fit with the hinge shaft; a first bearing seat in the support hinged structure and a bearing arranged in the first bearing seat are positioned at one end of a horizontal pull pressure sensor and one end of a vertical pull pressure sensor, and a pair of hinge supports in the support hinged structure are positioned on a vertical plane and a horizontal plane;
the sensor detection support hinge structure comprises two second bearing seats, bearings, a rotating shaft and a pair of lug plates, wherein the bearings are arranged in the two second bearing seats; two second bearing blocks in the sensor detection support hinge structure and bearings installed in the two second bearing blocks are respectively located at the other ends of the horizontal pull pressure sensor and the vertical pull pressure sensor, and a pair of lugs in the sensor detection support hinge structure are located at the bottoms of two bottom angle ends and a top angle end of an isosceles triangle horizontal support formed by the sensor detection support.
The hinged ends of the sensor detection supports installed at the two bottom corner ends of the sensor detection supports face the front of the bird-like flapping wing aircraft to be detected, and the hinged ends of the sensor detection supports installed at the top corner ends of the sensor detection supports face the rear of the bird-like flapping wing aircraft to be detected.
Adopt the produced beneficial effect of above-mentioned technical scheme to lie in:
the bird-like flapping wing aircraft testing device can measure the force and moment generated in the flapping process of the bird-like flapping wing aircraft and the flapping frequency, and meets the test requirement in the design process of the bird-like flapping wing aircraft; the data of the existing sensor is used for carrying out autocorrelation analysis to obtain the flapping frequency, so that a special flapping frequency sensor and a matched frequency meter or oscilloscope thereof are omitted, the test cost and the complexity of a test system are reduced, and the overall reliability of the system is improved; the utility model discloses a data acquisition system highly integrates, and circuit connection is simple convenient, and data acquisition analysis degree of automation is high, and the commonality is strong, only needs to do simple circuit connection and software setting can accomplish experimental data acquisition automatically in the experimentation, and it is more convenient to make the experiment.
The device has the characteristics of reasonable structure, convenience and quickness in operation, accuracy in test and the like.
Drawings
FIG. 1 is a schematic structural view of the bird-like flapping wing aircraft to be tested;
FIG. 2 is a schematic structural view of the test rack of FIG. 1;
FIG. 3 is a schematic structural view of the load cell of FIG. 1;
FIG. 4 is a schematic view of the horizontal pull pressure sensor of FIG. 3 with hinge structures at both ends;
FIG. 5 is a schematic view of the vertical pull pressure sensor of FIG. 3 with hinge structures at both ends;
FIG. 6 is a diagram illustrating parameters associated with a calculation formula in a test method;
FIG. 7 is test data information for a model bird-like ornithopter tested by the apparatus.
In the drawings: 1. an aircraft connection mount; 2. a bottom beam; 3. a boundary beam; 4. a side beam; 5. an oblique beam; 6. a base; 6-1, vertical plane; 6-2. horizontal plane; 7. a horizontal pull pressure sensor; 8. a vertical pull pressure sensor; 9. a first bearing housing; 10. a hinge axis; 11. a hinge support; 12. a second bearing housing; 13. a rotating shaft; 14. a tab; 15. the bird-like flapping-wing aircraft to be tested.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The utility model discloses the standard part that well used all can be purchased from the market, and dysmorphism piece all can be customized according to the description with the record of attached drawing, and the concrete connection mode of each part all adopts conventional means such as ripe bolt, rivet, welding, pasting among the prior art, no longer detailed description here.
As can be seen from the embodiments shown in fig. 1 to 5, the embodiment includes a test frame body and a comprehensive stress detection device for the test frame body;
the test frame body comprises a sensor detection support, a bearing frame and an aircraft connecting seat 1;
the sensor detection support is an isosceles triangle horizontal support which is horizontally arranged and comprises a bottom beam 2 and two side beams 3 with the same length, one ends of the two side beams 3 are respectively and fixedly connected with two ends of the bottom beam 2 to form two base angle ends of the isosceles triangle horizontal support, and the other ends of the two side beams 3 are fixedly connected together to form a top angle end of the isosceles triangle horizontal support;
the bearing frame comprises an aircraft axial positioning support and an oblique beam 5, the aircraft axial positioning support is an isosceles triangle vertical support arranged (upwards), the device comprises two side beams 4 with the same length, wherein the bottom ends of the two side beams 4 are respectively and fixedly connected with the two ends of a bottom beam 2 to form two bottom angle ends of an isosceles triangle vertical bracket, the top ends of the two side beams 4 are fixedly connected together to form a vertex angle end of the isosceles triangle vertical bracket, the bottom end of an oblique beam 5 is fixedly connected with the vertex angle end of a sensor detection bracket, the top end of the oblique beam 5 is fixedly connected with the vertex angle end of an aircraft axial positioning bracket, so as to form bearing support for the aircraft axial positioning support, the aircraft connecting seat 1 is fixed at the vertex angle end of the aircraft axial positioning support, so that the vertical projection position is positioned on the vertical bisector of the bottom beam 2 of the isosceles triangle horizontal bracket formed by the sensor detection bracket;
the comprehensive stress detection device for the test rack body comprises three force measurement supports, each force measurement support comprises a base 6 and a combined type force measurement sensor, and each combined type force measurement sensor comprises a horizontal pull pressure sensor 7 (model: ZNLBS) and a vertical pull pressure sensor 8 (model: ZNLBS); the base 6 is provided with a combined type force measuring sensor mounting space, one end of a horizontal pull pressure sensor 7 is hinged with the side wall beside the combined type force measuring sensor mounting space through a support hinge structure, one end of a vertical pull pressure sensor 8 is hinged with the bottom side wall of the combined type force measuring sensor mounting space through a support hinge structure, and the other ends of the horizontal pull pressure sensor 7 and the vertical pull pressure sensor 8 are hinged together through a sensor detection support hinge structure to form a sensor detection support hinge end; the horizontal tension and pressure sensor 7 and the vertical tension and pressure sensor 8 are arranged in the installation space of the combined type force measuring sensor in a right angle mode, the horizontal tension and pressure sensor 7 detects the tension and pressure in the horizontal direction, the vertical tension and pressure sensor 8 detects the tension and pressure in the vertical direction, and the hinged end of the sensor detection support can freely move along the resultant force direction detected by the combined type force measuring sensor;
the hinged ends of the sensor detection supports of the three force measurement supports are respectively hinged with two bottom angle ends and top angle ends of an isosceles triangle horizontal support formed by the sensor detection supports through a sensor detection support hinged structure, so that the sensor detection supports are in a horizontal position, and the plane of the resultant force direction detected by each combined force measurement sensor is parallel to the vertical bisector of the bottom beam 2 of the isosceles triangle horizontal support formed by the sensor detection supports; the combined type force measuring sensors installed at the two bottom angle ends are arranged on the two sides of a vertical bisector of the isosceles triangle horizontal bracket bottom beam 2 formed by the sensor detection bracket in a bilateral symmetry mode, and the combined type force measuring sensors installed at the top angle ends are arranged on the vertical bisector of the isosceles triangle horizontal bracket bottom beam 2 formed by the sensor detection bracket.
The base 6 is provided with a vertical surface 6-1 and a horizontal surface 6-2, the side end part of the horizontal surface 6-2 is intersected with the bottom end part of the vertical surface 6-1, and a composite force transducer mounting space is formed between the vertical surface 6-1 and the horizontal surface 6-2; the vertical surface 6-1 is a side wall of the installation space of the composite force measuring sensor, and the horizontal surface 6-2 is a bottom wall of the installation space of the composite force measuring sensor.
The support hinged structure comprises a first bearing seat 9 and a bearing arranged in the first bearing seat 9, a hinge shaft 10 and a pair of hinge support seats 11, wherein the hinge shaft 10 is arranged between the two hinge support seats 11, the first bearing seat 9 is embedded in a gap between the two hinge support seats 11, and a bearing hole is in running fit with the hinge shaft 10; a first bearing seat 9 in the support hinged structure and a bearing arranged in the first bearing seat 9 are positioned at one end of a horizontal pulling pressure sensor 7 and one end of a vertical pulling pressure sensor 8, and a pair of hinge supports 11 in the support hinged structure are positioned on a vertical surface 6-1 and a horizontal surface 6-2;
the sensor detection support hinge structure comprises two second bearing seats 12 and bearings arranged in the two second bearing seats 12, a rotating shaft 13 and a pair of lugs 14, wherein the rotating shaft 13 is arranged between the two lugs 14, the two second bearing seats 12 are embedded in a gap between the two lugs 14, and two bearing holes are in running fit with the rotating shaft 13; two second bearing blocks 12 in the sensor detection support hinge structure and bearings installed in the two second bearing blocks 12 are respectively located at the other ends of the horizontal pull pressure sensor 7 and the vertical pull pressure sensor 8, and a pair of lugs 14 in the sensor detection support hinge structure are located at the bottoms of two bottom angle ends and a top angle end of an isosceles triangle horizontal support formed by the sensor detection support.
The hinged ends of the sensor detection supports installed at the two bottom corner ends of the sensor detection supports face the front of the bird-like flapping wing aircraft 15 to be detected, and the hinged ends of the sensor detection supports installed at the top corner ends of the sensor detection supports face the rear of the bird-like flapping wing aircraft 15 to be detected.
In the following, a simple description is made of the testing method of the bird-like ornithopter testing device of the present embodiment in combination with the structure of the present embodiment, including the following steps:
a. the bird-like flapping-wing aircraft 15 to be tested is fixed on an aircraft connecting seat 1 of the testing device, and the axis of the bird-like flapping-wing aircraft is parallel to the vertical bisector of an isosceles triangle horizontal support bottom beam 2 formed by a sensor detection support and is positioned on the same vertical plane; the front end points to the direction of the vertex angle end of an isosceles triangle formed by the sensor detection bracket;
b. the testing device is installed in place, the testing device is fixed to the ground or a wind tunnel through the three bases 6, and the sensor detection support is located at the horizontal position;
c. the testing device is connected with a circuit and is powered by a stabilized voltage power supply and a horizontal pull pressure sensor 7 and a vertical pull pressure sensor 8 in each force measuring support; the I/O port of the computer is in circuit connection with the bird-like flapping-wing aircraft 15 to be tested, and is used for controlling the flapping frequency of the flapping wing of the bird-like flapping-wing aircraft 15 to be tested by the computer (the flapping-wing flapping frequency control signal is a voltage adjusting signal of a flapping-wing driving motor, the rotating speed of the flapping-wing driving motor of the bird-like flapping-wing aircraft 15 to be tested is controlled by adjusting the voltage value of the flapping-wing driving motor, and the flapping frequency of the flapping wing of the bird-like flapping-wing aircraft 15 to be tested is controlled); the I/O port of the computer is in circuit connection with the horizontal pulling pressure sensor 7 and the vertical pulling pressure sensor 8 of each force measuring support, and is used for receiving the moment signals of the horizontal pulling pressure sensor 7 and the moment signals of the vertical pulling pressure sensor 8 of each force measuring support by the computer;
d. the bird-like flapping wing aircraft to be tested is tested, and according to the detection index, the control computer outputs a corresponding flapping wing frequency control signal to control the flapping wing to generate corresponding flapping motionFrequency, calculating the lift force F at the corresponding frequency according to the following formulaL(Positive in upward direction), thrust FT(forward is positive) and pitching moment M;
FL＝Fv1+Fv2+Fv3 (1)
FT＝-Fh1+Fh2+Fh3 (2)
M＝Fv1L+FTH＝Fv1L+H(-Fh1+Fh2+Fh3) (3)
in the formula, FL: a lifting force; fT: a thrust force; m: a pitching moment; fh1: a horizontal pulling pressure sensor 7 arranged at the vertex angle end of the sensor detection bracket detects the value; fh2: a horizontal pulling pressure sensor 7 arranged at the left bottom corner end of the sensor detection bracket; fh3: a horizontal pulling pressure sensor 7 arranged at the right bottom corner end of the sensor detection bracket; fv1: a detection value of a vertical pull pressure sensor 8 arranged at the vertex angle end of the sensor detection bracket; fv2: a detection value of a vertical pulling pressure sensor 8 arranged at the left bottom corner end of the sensor detection bracket; fv3: a detection value of a vertical pulling pressure sensor 8 arranged at the right bottom corner end of the sensor detection bracket; l: aircraft axial positioning bracket height (in m) H: the sensor detects the vertical bisector (unit m) of the isosceles triangle horizontal bracket base beam 2 formed by the bracket (see fig. 6);
e. generating a test result, and comparing the thrust F generated by the computer at each flapping frequency of the bird-like ornithopter obtained in the step dTLifting force FLAnd recording the pitching moment M to generate test data information.
The test data information is the flapping wing frequency and the thrust FTLifting force FLAnd a synchronous superposition curve of the pitching moment M.
Claims (4)
1. The utility model provides an imitative bird flapping wing aircraft testing arrangement which characterized in that: comprises a test frame body and a comprehensive stress detection device for the test frame body;
the test frame body comprises a sensor detection support, a bearing frame and an aircraft connecting seat (1);
the sensor detection support is an isosceles triangle horizontal support which is horizontally arranged and comprises a bottom beam (2) and two side beams (3) with equal length, one ends of the two side beams (3) are respectively and fixedly connected with two ends of the bottom beam (2) to form two bottom angle ends of the isosceles triangle horizontal support, and the other ends of the two side beams (3) are fixedly connected together to form a top angle end of the isosceles triangle horizontal support;
the force bearing frame comprises an aircraft axial positioning support and an oblique beam (5), the aircraft axial positioning support is an upward isosceles triangle vertical support and comprises two side beams (4) with equal lengths, the bottom ends of the two side beams (4) are respectively fixedly connected with the two ends of the bottom beam (2) to form two bottom angle ends of the isosceles triangle vertical support, the top ends of the two side beams (4) are fixedly connected together to form a top angle end of the isosceles triangle vertical support, the bottom end of the oblique beam (5) is fixedly connected with the top angle end of the sensor detection support, the top end of the oblique beam (5) is fixedly connected with the top angle end of the aircraft axial positioning support to form force bearing support for the aircraft axial positioning support, and the aircraft connecting seat (1) is fixed at the top angle end of the aircraft axial positioning support, so that the vertical projection position of the sensor detection bracket is positioned on the vertical bisector of an isosceles triangle horizontal bracket bottom beam (2) formed by the sensor detection bracket;
the comprehensive stress detection device for the test frame body comprises three force measurement supports, wherein each force measurement support comprises a base (6) and a combined type force measurement sensor, and each combined type force measurement sensor comprises a horizontal pull pressure sensor (7) and a vertical pull pressure sensor (8); the base (6) is provided with a combined type force measuring sensor mounting space, one end of the horizontal pulling pressure sensor (7) is hinged to the side wall of the combined type force measuring sensor mounting space through a support hinge structure, one end of the vertical pulling pressure sensor (8) is hinged to the bottom side wall of the combined type force measuring sensor mounting space through a support hinge structure, and the other ends of the horizontal pulling pressure sensor (7) and the vertical pulling pressure sensor (8) are hinged together through a sensor detection support hinge structure to form a sensor detection support hinge end; the horizontal tension and pressure sensor (7) and the vertical tension and pressure sensor (8) are arranged in the installation space of the combined type force measuring sensor in a right angle mode, the horizontal tension and pressure sensor (7) detects the tension and pressure in the horizontal direction, the vertical tension and pressure sensor (8) detects the tension and pressure in the vertical direction, and the hinged end of the sensor detection support can freely move along the resultant force direction detected by the combined type force measuring sensor;
the hinged ends of the sensor detection supports of the three force measurement supports are respectively hinged with two bottom angle ends and a top angle end of an isosceles triangle horizontal support formed by the sensor detection supports through a sensor detection support hinged structure, so that the sensor detection supports are in a horizontal position, and the plane of the resultant force direction detected by each combined type force measurement sensor is parallel to the vertical bisector of an isosceles triangle horizontal support bottom beam (2) formed by the sensor detection supports.
2. The bird-like ornithopter test device of claim 1, wherein: the base (6) is provided with a vertical surface (6-1) and a horizontal surface (6-2), the side end part of the horizontal surface (6-2) is intersected with the bottom end part of the vertical surface (6-1), and a composite type force measuring sensor mounting space is formed between the vertical surface (6-1) and the horizontal surface (6-2); the vertical surface (6-1) is a side wall of the installation space of the combined type force measuring sensor, and the horizontal surface (6-2) is a bottom wall of the installation space of the combined type force measuring sensor.
3. The bird-like ornithopter test device of claim 2, wherein: the support hinged structure comprises a first bearing seat (9) and a bearing arranged in the first bearing seat (9), a hinge shaft (10) and a pair of hinge supports (11), wherein the hinge shaft (10) is arranged between the two hinge supports (11), and the first bearing seat (9) is embedded in a gap between the two hinge supports (11) and enables a bearing hole to be in running fit with the hinge shaft (10); a first bearing seat (9) in the support hinged structure and a bearing installed in the first bearing seat (9) are positioned at one end of the horizontal pulling and pressing force sensor (7) and one end of the vertical pulling and pressing force sensor (8), and a pair of hinge supports (11) in the support hinged structure are positioned on the vertical surface (6-1) and the horizontal surface (6-2);
the sensor detection support hinge structure comprises two second bearing seats (12), bearings arranged in the two second bearing seats (12), a rotating shaft (13) and a pair of lugs (14), wherein the rotating shaft (13) is arranged between the two lugs (14), and the two second bearing seats (12) are embedded in a gap between the two lugs (14) so that two bearing holes are in running fit with the rotating shaft (13); two second bearing blocks (12) in the sensor detection support hinge structure and bearings installed in the two second bearing blocks (12) are respectively located at the other ends of the horizontal pull pressure sensor (7) and the vertical pull pressure sensor (8), and a pair of lugs (14) in the sensor detection support hinge structure are located at the bottoms of two bottom angle ends and a top angle end of an isosceles triangle horizontal support formed by the sensor detection support.
4. The bird-like ornithopter test device of claim 3, wherein: the hinged end of the sensor detection support faces towards the front of the bird-like ornithopter (15) to be detected, and the hinged end of the sensor detection support faces towards the rear of the bird-like ornithopter (15) to be detected.
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| CN111891384A (en) * | 2020-08-03 | 2020-11-06 | 西北工业大学太仓长三角研究院 | Bird-like flapping-wing aircraft testing device and testing method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111891384A (en) * | 2020-08-03 | 2020-11-06 | 西北工业大学太仓长三角研究院 | Bird-like flapping-wing aircraft testing device and testing method thereof |
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