CN210083545U

CN210083545U - Aerodynamic test glider

Info

Publication number: CN210083545U
Application number: CN201920775023.8U
Authority: CN
Inventors: 许诗雨; 王艳伟; 张栋; 吕方怡; 董剑; 柴碧波; 胡洁
Original assignee: Wenzhou University
Current assignee: Wenzhou University
Priority date: 2019-05-27
Filing date: 2019-05-27
Publication date: 2020-02-18
Anticipated expiration: 2029-05-27

Abstract

The utility model provides an aerodynamic test glider, which comprises a glider body, wings, an empennage and a counterweight module, wherein the wings, the empennage and the counterweight module are detachably connected with the glider body, and the wings, the empennage and the counterweight module can move along the length direction of the glider body to adjust the lift force and the gravity center; the section of the machine body facing the machine head is provided with wing positioning holes which are arranged at intervals, and the section of the machine body facing the machine tail is provided with tail wing positioning holes which are arranged at intervals; the wing comprises a main U-shaped beam and a main wing panel, the fuselage is buckled in the U-shaped opening of the main U-shaped beam, the wing positioning hole of the fuselage is matched and positioned with the main U-shaped beam, the tail wing comprises an auxiliary U-shaped beam and a tail wing panel, and the fuselage is buckled in the U-shaped opening of the auxiliary U-shaped beam, and the tail wing positioning hole of the fuselage is matched and positioned with the auxiliary U-shaped beam. The utility model has the advantages of be convenient for dismantle and adjust fuselage focus and lift overall arrangement for research glider wholeness ability parameter, can carry out folding in good time reduction damage to the wing when the machine is dropped into to the appearance.

Description

Aerodynamic test glider

Technical Field

The utility model relates to a glider field, concretely relates to experimental glider of aerodynamic.

Background

The design scheme of the glide mechanism theory is that on the basis of specified materials, the concrete design scheme of the sizes and the shapes of a fuselage, wings and an empennage of the glider is provided by combining related knowledge of fluid mechanics, aeromechanics, structural mechanics and the like from the aspects of a structural layout, a computational sketch, load analysis, flight performance estimation and the like.

Present glider is after making, its fuselage, the wing, fin size focus position, weight isoparametric has often been fixed dead, be difficult to carry out effective quick change to it in the experimentation, consequently, be unfavorable for data collection, if need compare then need make many gliders in the experiment, this can have the error that the preparation technology brought, make preparation error and actual test error enlarge the collection that leads to final data each other at last and become comparatively unstable, the emergence that leads to the crash condition can difficult to avoid appearing the misoperation simultaneously in the experiment, in case the fuselage causes the damage and probably influences follow-up experimental effect, cause the glider to scrap even.

SUMMERY OF THE UTILITY MODEL

Based on the problem, the utility model aims to provide a fuselage focus and lift overall arrangement are adjusted to convenient to detach for research glider wholeness ability parameter, can carry out the aerodynamic test glider that reduces the damage by folding in good time to the wing when the machine is dropped to the appearance.

Aiming at the problems, the following technical scheme is provided: the aerodone for the aerodynamic test comprises a body, wings positioned on the body, an empennage positioned at the tail part of the body and a counterweight module, wherein the wings, the empennage and the counterweight module are detachably connected with the body, and the wings, the empennage and the counterweight module can move along the length direction of the body to adjust the lift force and the gravity center; a section of the fuselage, which faces the nose, is provided with a plurality of wing positioning holes which are arranged at intervals along the length direction of the fuselage, and a section of the fuselage, which faces the tail, is provided with a plurality of tail wing positioning holes which are arranged at intervals along the length direction of the fuselage; the wing comprises a main U-shaped beam and main wing pieces located on two sides of the main U-shaped beam, the fuselage is buckled in the U-shaped opening of the main U-shaped beam, wing positioning holes of the fuselage are matched and located with the main U-shaped beam, the tail wing comprises an auxiliary U-shaped beam and tail wing pieces located on two sides of the auxiliary U-shaped beam, and the fuselage is buckled in the U-shaped opening of the auxiliary U-shaped beam, and tail wing positioning holes of the fuselage are matched and located with the auxiliary U-shaped beam.

In the structure, through setting up removable wing, fin, counter weight module, make it can in time quick replacement when the damage appears, accessible dismantles the installation simultaneously and adjusts the position of three on the fuselage in order to reach different experimental effect and purpose in the experiment, and wing locating hole and fin locating hole can guarantee that wing, fin remain fixed for the position of fuselage to improve experimental data acquisition's precision.

The utility model is further arranged that the main wing pieces are hinged at two sides of the U-shaped opening of the main U-shaped beam, and the hinge axes are parallel to the length direction of the machine body; the tail wing pieces are hinged to two sides of a U-shaped opening of the auxiliary U-shaped beam, the hinged axis of the tail wing pieces is parallel to the length direction of the machine body, the belly of the machine body faces towards the bottom of the U-shaped opening of the main U-shaped beam and the auxiliary U-shaped beam, one ends, far away from the machine body, of the main wing pieces and the tail wing pieces are lifted along the hinged point, the two main wing pieces are abutted and abutted above the U-shaped opening of the main U-shaped beam and the two tail wing pieces are abutted above the U-shaped opening of the auxiliary U-shaped beam, mounting grooves are formed in abutting surfaces, abutted with each other, of the main wing pieces and the tail wing pieces, and magnets enabling the two main wing pieces and the two tail wing pieces to be mutually attracted are arranged.

In the structure, the main U-shaped beam and the auxiliary U-shaped beam are clamped with the fuselage through the U-shaped openings of the main U-shaped beam and the auxiliary U-shaped beam to ensure the stability, the hinged main wing pieces and the tail wing pieces are adsorbed by magnets, the wings and the tail wing pieces can be folded reversely when the aircraft is crashed to reduce the possibility of damage and fracture of the wings and the tail wing pieces, the main wing pieces and the tail wing pieces can be folded reversely when the positions of the wings and the tail wing pieces on the fuselage are required to be adjusted or the wings and the tail wing pieces are disassembled, the fixed extrusion on the fuselage is carried out when the two main wing pieces and the two tail wing pieces are mutually attracted, the U-shaped openings of the main U-shaped beam and the auxiliary U-shaped beam are in an open state, the fuselage is taken out, the dead weight of the fuselage can be borne on the main U-shaped beam and the auxiliary U-shaped beam when the aircraft normally flies.

The utility model is further arranged that the bottom of the U-shaped opening of the main U-shaped beam is provided with a main positioning bulge matched with the wing positioning hole; and the bottom of the U-shaped opening of the auxiliary U-shaped beam is provided with an auxiliary positioning bulge matched with the empennage positioning hole.

In the structure, the main positioning bulge and the auxiliary positioning bulge can be matched with the wing positioning hole and the tail wing positioning hole to keep a good positioning effect when the mutually-absorbed positions of the main wing piece and the tail wing piece generate downward pressure on the airplane body when flying.

The utility model is further provided with two main positioning bulges at the bottom of the U-shaped opening of the main U-shaped beam; two auxiliary positioning bulges are arranged at the bottom of the U-shaped opening of the auxiliary U-shaped beam.

In the structure, the main positioning bulge and the auxiliary positioning bulge can be connected with the machine body, the wings and the tail wing by stronger supporting force when falling occurs.

The utility model discloses further set up as, the fin is still including being located the perpendicular fin on vice U-shaped roof beam bottom surface.

The utility model discloses further set up as, the counter weight module includes two spliced poles that the interval set up, spliced pole one end is equipped with the bayonet joint that is used for the plug-in to wing locating hole, the other end is equipped with the support head, it has inflation gum cover, expansion sliding sleeve and supporting spring to overlap in proper order between bayonet joint and the support head, the inflation gum cover is equipped with the inner chamfer towards the one end of expansion sliding sleeve, the expansion sliding sleeve is equipped with the outer chamfer with the inner chamfer adaptation towards the one end of expansion gum cover, the supporting spring both ends are supported and are pushed the expansion sliding sleeve to the expansion gum cover direction between support head and the expansion sliding sleeve, the expansion gum cover is located the wing locating hole; the two inserting columns are connected through a connecting beam, and a balancing weight is arranged on the connecting beam.

In the structure, when the counterweight module is installed, the support spring is compressed through the expansion sliding sleeve, the plug connector and the expansion rubber sleeve are inserted into the wing positioning hole in the machine body, the expansion sliding sleeve is loosened to enable the support spring to push the expansion sliding sleeve to slide towards the expansion rubber sleeve, the outer chamfer of the expansion sliding sleeve is in contact with the inner chamfer of the expansion rubber sleeve, the diameter of the expansion rubber sleeve is enlarged under the pushing of the outer chamfer of the expansion sliding sleeve, the expansion rubber sleeve is tightly attached to the inner wall of the wing positioning hole to be fixed, the position of the counterweight module is convenient to adjust, and the gravity center.

The utility model discloses further set up as, its U-shaped opening bottom of main U-shaped roof beam is equipped with the counter weight module spliced eye that sets up and set up with wing locating hole equidistance to leading to.

In the structure, the plug-in holes of the counterweight module can enable the plug-in posts to pass through, so that the counterweight module is prevented from being installed when the main U-shaped beam is matched with the machine body.

The utility model discloses further set up to, two at least wing locating hole intervals in interval between two pegs graft posts, the balancing weight focus is located two wherein wing locating hole between two pegs graft posts on the tie-beam that the position corresponds placed in the middle between the posts.

In the structure, because the main U-shaped beam is provided with the main positioning bulge, the partial position of the main U-shaped beam can not be provided with the counterweight module inserting hole, two fewer inserting columns are needed to be separated to form a distance between two wing positioning holes so as to stride over the main positioning bulge, meanwhile, in order to ensure the consistency of the adjustment distance of the gravity center on the machine body, the gravity center of the counterweight block is placed on the connecting beam corresponding to the middle position of the two wing positioning holes, if the wing positioning hole of the next position is just sheltered by the main positioning bulge when the gravity center of the counterweight module is adjusted, the positions of the two inserting columns can be reversed and inserted and fixed again to realize the adjustment of the gravity center of the next position, and the situation that the gravity center is adjusted insufficiently and finely due to the fact that the main positioning bulge crosses over.

The utility model discloses further set up to, be equipped with the unblock push jack that extends along its radial direction on the expansion sliding sleeve.

In the structure, the unlocking push piece is used as an acting point when the counterweight module is detached or adjusted.

The utility model discloses further set up to, the fuselage middle section is equipped with and link up the heavy groove of seting up along fuselage top surface to fuselage belly.

In the structure, most weight of the airplane always faces the ground vertically when flying, and the bending strength in the left and right directions is far less than that in the vertical direction, so that the weight reduction groove penetrates through the top surface of the airplane body and the belly of the airplane to reduce the weight under the condition of ensuring reasonable strength.

The utility model has the advantages that: the detachable wing, the empennage and the counterweight module can be quickly replaced in time when being damaged, meanwhile, the positions of the three on the fuselage can be adjusted through disassembly and assembly in an experiment to achieve different experimental effects and purposes, and the wing positioning holes and the empennage positioning holes can ensure that the positions of the wing and the empennage relative to the fuselage are kept fixed, so that the accuracy of experimental data acquisition is improved; meanwhile, when the aircraft crashes, the main wing pieces and the tail wing pieces can be reversely folded at a proper contact position and at a proper angle, and the wings, the empennage and the aircraft body are automatically separated, so that the damage is reduced.

Drawings

Fig. 1 is a schematic view of the flight state of the present invention.

Fig. 2 is a schematic view of the overall belly structure of the present invention.

Fig. 3 is a schematic structural view of the present invention in an exploded state in a downward direction.

Fig. 4 is a structural schematic view of the present invention in a disassembled state viewed from the bottom.

Fig. 5 is an enlarged schematic view of a portion a of fig. 2 according to the present invention.

Fig. 6 is an enlarged schematic view of a portion B of fig. 2 according to the present invention.

Fig. 7 is an enlarged schematic view of the part C of fig. 3 according to the present invention.

Fig. 8 is an enlarged schematic view of a portion D of fig. 3 according to the present invention.

Fig. 9 is an enlarged schematic view of the part E of fig. 4 according to the present invention.

The reference numbers in the figures mean: 10-a fuselage; 11-wing positioning holes; 12-empennage positioning holes; 13-weight reduction slots; 20-an airfoil; 21-a main U-beam; 22-a main flap; 23-a primary positioning boss; 24-counterweight module plug holes; 30-tail fin; 31-an auxiliary U-shaped beam; 32-tail fin; 33-auxiliary positioning protrusions; 34-vertical tail; 40-a counterweight module; 41-a plug column; 42-a plug-in connector; 43-support head; 44-expansion rubber sleeve; 441-inner chamfer; 45-expanding the sliding sleeve; 451-outer chamfer; 452-unlocking the push piece; 46-a support spring; 47-connecting beam; 48-a counterweight block; 50-mounting grooves; 51-magnet.

Detailed Description

The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.

Referring to fig. 1 to 9, an aerodynamic test glider as shown in fig. 1 to 9 includes a fuselage 10, a wing 20 located on the fuselage 10, a tail 30 located at the tail of the fuselage 10, and a weight module 40, wherein the wing 20, the tail 30, and the weight module 40 are detachably connected to the fuselage 10, and the wing 20, the tail 30, and the weight module 40 can move along the length direction of the fuselage 10 to adjust the lift and the center of gravity; a section of the fuselage 10 facing the nose is provided with a plurality of wing positioning holes 11 arranged at intervals along the length direction of the fuselage 10, and a section of the fuselage 10 facing the tail is provided with a plurality of tail wing positioning holes 12 arranged at intervals along the length direction of the fuselage 10; the wing 20 comprises a main U-shaped beam 21 and main wings 22 located on two sides of the main U-shaped beam 21, the fuselage 10 is buckled in a U-shaped opening of the main U-shaped beam 21, wing locating holes 11 of the fuselage are matched and located with the main U-shaped beam 21, the empennage 30 comprises an auxiliary U-shaped beam 31 and tail wings 32 located on two sides of the auxiliary U-shaped beam 31, and the fuselage 10 is buckled in the U-shaped opening of the auxiliary U-shaped beam 31, and empennage locating holes 12 of the fuselage are matched and located with the auxiliary U-shaped beam 31.

In the above-mentioned structure, through setting up removable wing 20, fin 30, counter weight module 40, make it can in time quick replacement when the damage appears, the accessible is dismantled the installation simultaneously and is adjusted the position of three on fuselage 10 in order to reach different experimental effect and mesh in the experiment, and wing locating hole 11 and fin locating hole 12 can guarantee that wing 20, fin 30 remain fixed for fuselage 10's position to improve experimental data acquisition's precision.

In this embodiment, the main wing pieces 22 are hinged to two sides of the U-shaped opening of the main U-shaped beam 21, and the hinge axes thereof are parallel to the length direction of the body 10; the tail fins 32 are hinged to two sides of a U-shaped opening of the auxiliary U-shaped beam 31, the hinged axis of the tail fins is parallel to the length direction of the fuselage 10, the belly of the fuselage 10 faces the bottom of the U-shaped openings of the main U-shaped beam 21 and the auxiliary U-shaped beam 31, one ends, far away from the fuselage 10, of the main fins 22 and the tail fins 32 are lifted along the hinged point, so that the two main fins 22 are butted and abutted above the U-shaped opening of the main U-shaped beam 21 and the two tail fins 32 are butted and abutted above the U-shaped opening of the auxiliary U-shaped beam 31, mounting grooves 50 are formed in butt-joint surfaces, butted and abutted against each other, of the main fins 22 and the tail fins 32, mounting grooves 50 are internally provided with magnets 51 which enable the two main fins 22 and the two tail fins 32 to attract each other, and the magnets 51 are rubidium-iron.

In the above structure, the main U-shaped beam 21 and the auxiliary U-shaped beam 31 are engaged with the fuselage 10 through their own U-shaped openings to ensure stability, and the hinged main wing pieces 22 and the tail wing pieces 32 are attracted by the magnets 51, so that they can be folded reversely to reduce the possibility of damage and fracture of the wings 20 and the tail wings 30 during crash, when the positions of the wings 20 and the tail wings 30 on the fuselage 10 need to be adjusted or the wings 20 and the tail wings 30 are detached, the main wing pieces 22 and the tail wing pieces 32 can be folded reversely, and when the two main wing pieces 22 and the two tail wing pieces 32 are removed and attracted to each other, the fuselage 10 is fixed and extruded, so that the U-shaped openings of the main U-shaped beam 21 and the auxiliary U-shaped beam 31 are opened to take out the fuselage 10, and during normal flight, the self-weight of the fuselage 10 can be borne on the main U-shaped beam 21 and the auxiliary U-shaped beam 31, so that the main wing pieces 22 and the tail wing pieces 32 are pressed against the fuselage 10 to ensure flight stability.

In this embodiment, the bottom of the U-shaped opening of the main U-shaped beam 21 is provided with a main positioning protrusion 23 adapted to the wing positioning hole 11; and the bottom of the U-shaped opening of the auxiliary U-shaped beam 31 is provided with an auxiliary positioning bulge 33 matched with the empennage positioning hole 12.

In the above structure, the main positioning protrusion 23 and the auxiliary positioning protrusion 33 can cooperate with the wing positioning hole 11 and the tail wing positioning hole 12 to maintain a good positioning effect when the mutually attracted positions of the main wing 22 and the tail wing 32 generate a downward pressure on the fuselage 10 during flight.

In this embodiment, two main positioning protrusions 23 are arranged at the bottom of the U-shaped opening of the main U-shaped beam 21; two auxiliary positioning protrusions 33 are arranged at the bottom of the U-shaped opening of the auxiliary U-shaped beam 31.

In the above configuration, main positioning protrusion 23 and sub positioning protrusion 33 can be made to have a stronger supporting force to connect body 10, wing 20, and tail wing 30 when a crash occurs.

In this embodiment, the tail 30 further includes a vertical tail 34 on the bottom surface of the secondary U-shaped beam 31.

In this embodiment, the counterweight module 40 includes two insertion columns 41 arranged at intervals, one end of each insertion column 41 is provided with an insertion joint 42 for being inserted into the wing positioning hole 11, and the other end of each insertion column 41 is provided with a support head 43, an expansion rubber sleeve 44, an expansion sliding sleeve 45 and a support spring 46 are sequentially sleeved between the insertion joint 42 and the support head 43, one end of the expansion rubber sleeve 44 facing the expansion sliding sleeve 45 is provided with an inner chamfer 441, one end of the expansion sliding sleeve 45 facing the expansion rubber sleeve 44 is provided with an outer chamfer 451 matched with the inner chamfer 441, two ends of the support spring 46 are supported between the support head 43 and the expansion sliding sleeve 45 to push the expansion sliding sleeve 45 towards the expansion rubber sleeve 44, and the expansion rubber sleeve 44 is located in the wing positioning hole 11; the two inserting columns 41 are connected through a connecting beam 47, and a balancing weight 48 is arranged on the connecting beam 47.

In the above structure, when the counterweight module 40 is installed, the expansion sliding sleeve 45 compresses the support spring 46, the plug-in connector 42 and the expansion rubber sleeve 44 are inserted into the wing positioning hole 11 on the fuselage 10, the expansion sliding sleeve 45 is released to enable the support spring 46 to push the expansion sliding sleeve 45 to slide towards the expansion rubber sleeve 44, the outer chamfer 451 of the expansion sliding sleeve 45 is in contact with the inner chamfer 441 of the expansion rubber sleeve 44, and the expansion rubber sleeve 44 is pushed by the outer chamfer 451 of the expansion sliding sleeve 45 to expand in diameter to be tightly attached to the inner wall of the wing positioning hole 11 for fixation, so that the position of the counterweight module 40 is conveniently adjusted, and the gravity center of the fuselage 10 is changed.

In this embodiment, the bottom of the U-shaped opening of the main U-shaped beam 21 is provided with counterweight module insertion holes 24 that are opened oppositely and are arranged at equal intervals with the wing positioning holes 11.

In the above structure, the insertion holes 24 of the counterweight module enable the insertion posts 41 to pass through, so as to prevent the installation of the counterweight module 40 from being blocked when the main U-shaped beam 21 is adapted to the body 10.

In this embodiment, the two inserting columns 41 are spaced by at least two intervals between the wing positioning holes 11, and the center of gravity of the balancing weight 48 is located on the connecting beam 47 corresponding to the central position of two wing positioning holes 11 between the two inserting columns 41.

In the above structure, because the main U-shaped beam 21 is provided with the main positioning protrusion 23, part of the main U-shaped beam 21 cannot be provided with the counterweight module insertion hole 24, two insertion posts 41 need to be spaced by two wing positioning holes 11 to stride over the main positioning protrusion 23, and meanwhile, to ensure the consistency of the adjustment distance of the center of gravity on the airframe 10, the center of gravity of the counterweight block 48 is placed on the connecting beam 47 corresponding to the central position of the two wing positioning holes 11, if the wing positioning hole 11 at the next position is just shielded by the main positioning protrusion 23 when the center of gravity of the counterweight module 40 is adjusted, the positions of the two insertion posts 41 can be changed down and inserted and fixed again to adjust the center of gravity at the next position, so that the problem that the center of gravity adjustment is not fine enough due to the main positioning protrusion 23 crossing the wing positioning hole 11 at the specific position on the airframe 10.

In this embodiment, the expansion sliding sleeve 45 is provided with an unlocking pushing piece 452 extending along the radial direction thereof.

In the above structure, the unlocking push piece 452 serves as an acting point when the weight module 40 is removed or adjusted.

In this embodiment, a weight-reducing slot 13 is formed in the middle section of the body 10 and runs through the top surface of the body 10 to the belly of the body 10.

In the above structure, most of the weight of the airplane is always vertical to the ground when flying, and the bending strength in the left and right directions is far less than that in the vertical direction, so that the weight reduction groove 13 penetrates through the top surface and the belly of the airplane body 10 to reduce the weight under the condition of ensuring reasonable strength.

The utility model has the advantages that: the detachable wing 20, the empennage 30 and the counterweight module 40 are arranged, so that the detachable wing 20, the empennage 30 and the counterweight module 40 can be quickly replaced in time when being damaged, meanwhile, the positions of the three on the fuselage 10 can be adjusted through disassembly and assembly in an experiment to achieve different experimental effects and purposes, and the wing positioning holes 11 and the empennage positioning holes 12 can ensure that the positions of the wing 20 and the empennage 30 relative to the fuselage 10 are kept fixed, so that the accuracy of experimental data acquisition is improved; meanwhile, when the airplane crashes, the main wing pieces 22 and the tail wing pieces 32 can be reversely retracted at a proper contact position and angle, and the wings 20 and the tail wing 30 can be automatically separated from the airplane body 10, so that the damage is reduced.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations of the above assumption should also be regarded as the protection scope of the present invention.

Claims

1. The utility model provides an experimental glider of aerodynamic, includes the fuselage, is located the wing on the fuselage and is located the fin of fuselage afterbody, its characterized in that: the wing, the empennage and the counterweight module can move along the length direction of the fuselage to adjust the lift force and the gravity center; a section of the fuselage, which faces the nose, is provided with a plurality of wing positioning holes which are arranged at intervals along the length direction of the fuselage, and a section of the fuselage, which faces the tail, is provided with a plurality of tail wing positioning holes which are arranged at intervals along the length direction of the fuselage; the wing comprises a main U-shaped beam and main wing pieces located on two sides of the main U-shaped beam, the fuselage is buckled in the U-shaped opening of the main U-shaped beam, wing positioning holes of the fuselage are matched and located with the main U-shaped beam, the tail wing comprises an auxiliary U-shaped beam and tail wing pieces located on two sides of the auxiliary U-shaped beam, and the fuselage is buckled in the U-shaped opening of the auxiliary U-shaped beam, and tail wing positioning holes of the fuselage are matched and located with the auxiliary U-shaped beam.

2. An aerodynamic test glider according to claim 1, wherein: the main wing pieces are hinged to two sides of the U-shaped opening of the main U-shaped beam, and the hinge axes of the main wing pieces are parallel to the length direction of the airplane body; the tail wing pieces are hinged to two sides of a U-shaped opening of the auxiliary U-shaped beam, the hinged axis of the tail wing pieces is parallel to the length direction of the machine body, the belly of the machine body faces towards the bottom of the U-shaped opening of the main U-shaped beam and the auxiliary U-shaped beam, one ends, far away from the machine body, of the main wing pieces and the tail wing pieces are lifted along the hinged point, the two main wing pieces are abutted and abutted above the U-shaped opening of the main U-shaped beam and the two tail wing pieces are abutted above the U-shaped opening of the auxiliary U-shaped beam, mounting grooves are formed in abutting surfaces, abutted with each other, of the main wing pieces and the tail wing pieces, and magnets enabling the two main wing pieces and the two tail wing pieces to be mutually attracted are arranged.

3. An aerodynamic test glider according to claim 1 or 2, wherein: the bottom of the U-shaped opening of the main U-shaped beam is provided with a main positioning bulge matched with the wing positioning hole; and the bottom of the U-shaped opening of the auxiliary U-shaped beam is provided with an auxiliary positioning bulge matched with the empennage positioning hole.

4. An aerodynamic test glider according to claim 3, wherein: two main positioning bulges are arranged at the bottom of the U-shaped opening of the main U-shaped beam; two auxiliary positioning bulges are arranged at the bottom of the U-shaped opening of the auxiliary U-shaped beam.

5. An aerodynamic test glider according to claim 1, wherein: the empennage also comprises a vertical empennage positioned on the bottom surface of the auxiliary U-shaped beam.

6. An aerodynamic test glider according to claim 1, wherein: the counterweight module comprises two splicing columns which are arranged at intervals, one end of each splicing column is provided with a splicing head used for being spliced into the wing positioning hole, the other end of each splicing column is provided with a supporting head, an expansion rubber sleeve, an expansion sliding sleeve and a supporting spring are sequentially sleeved between the splicing head and the supporting head, one end of the expansion rubber sleeve, facing the expansion sliding sleeve, is provided with an inner chamfer, one end of the expansion sliding sleeve, facing the expansion rubber sleeve, is provided with an outer chamfer matched with the inner chamfer, the two ends of the supporting spring are supported between the supporting head and the expansion sliding sleeve to push the expansion sliding sleeve towards the expansion rubber sleeve, and the expansion rubber sleeve is positioned in the wing positioning hole; the two inserting columns are connected through a connecting beam, and a balancing weight is arranged on the connecting beam.

7. An aerodynamic test glider according to claim 6, wherein: and the bottom of the U-shaped opening of the main U-shaped beam is provided with counterweight module plug-in holes which are arranged oppositely and are arranged at equal intervals with the wing positioning holes.

8. An aerodynamic test glider according to claim 7, wherein: the two inserting columns are spaced by at least two wing positioning holes, and the gravity center of the balancing weight is positioned on a connecting beam corresponding to the central position of two wing positioning holes between the two inserting columns.

9. An aerodynamic test glider according to claim 6, wherein: and the expansion sliding sleeve is provided with an unlocking push sheet extending along the radial direction of the expansion sliding sleeve.

10. An aerodynamic test glider according to claim 1, wherein: and the middle section of the machine body is provided with a weight reduction groove which is communicated and arranged from the top surface of the machine body to the belly of the machine body.