CN114923656A - Rope supporting system for full-aircraft flutter wind tunnel test - Google Patents
Rope supporting system for full-aircraft flutter wind tunnel test Download PDFInfo
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- CN114923656A CN114923656A CN202210851916.2A CN202210851916A CN114923656A CN 114923656 A CN114923656 A CN 114923656A CN 202210851916 A CN202210851916 A CN 202210851916A CN 114923656 A CN114923656 A CN 114923656A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention discloses a rope supporting system for a full-aircraft flutter wind tunnel test, which relates to the technical field of wind tunnel tests and static or dynamic balance tests of machines or structural components, and comprises a wind tunnel test section, an airplane model arranged in the wind tunnel test section, and further comprises: the two ends of the limiting rope are connected to the inner wall of the wind tunnel test section and are positioned in front of the airplane model; a traction block located behind the aircraft model; the traction block is connected with a retractable traction rope; the horizontal main ropes are movably hung on two sides of the airplane model; the two horizontal main ropes extend forwards and then are connected to the limiting rope in a sliding mode, and the two horizontal main ropes extend backwards and then are fixedly connected to the two ends of the traction block respectively, so that the airplane model is surrounded. The method has less influence on the model body mode of the airplane model, improves the simulation test precision of the flutter test, has low requirement on the strength of the airplane model, and has the advantages of small interference on a wind tunnel test flow field and higher model attitude adjustment precision and efficiency.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests and static or dynamic balance tests of machines or structural components, in particular to a rope support system for a full-aircraft flutter wind tunnel test.
Background
Flutter is the phenomenon of aeroelastic instability caused by the coupling action of aerodynamic force, elastic force and inertia force of an aircraft. When the aircraft flies at transonic speed, the nonlinearity of aerodynamic force can cause the flutter critical speed to drop by a wide margin, and the structural vibration increases sharply, very easily leads to structural damage, threatens flight safety, restricts the flight envelope. Accurate acquisition of the transonic flutter boundary is a key fundamental problem that must be faced by aircraft design.
With the development of the structural layout of the aircraft, the interaction between the components is more complex, coupling flutter is easy to occur, and a full aircraft flutter wind tunnel test must be carried out to obtain a more accurate flutter boundary. In the test, not only the soft support of the model needs to be realized, the free flight state is simulated, but also the posture needs to be adjusted in real time to ensure the safety of the model.
At present, U.S. NASA patent 3276251 discloses a "free flight suspension system" which is mainly characterized in that two ropes are respectively passed through pulleys built in the front and back of an airplane body to form a closed loop, so as to suspend and lift the whole airplane model, and the attitude of the airplane model is adjusted through a control surface (the control surface refers to the main control surface of the airplane model body, namely, an aileron, an elevator, a hinged small wing surface or an adjustable small wing surface at the rear edge of a rudder.)
The defects of the scheme are that the body of the airplane model is directly under the tension of the front and rear ropes, the mode of the body of the airplane model is greatly influenced, the simulation test precision of the flutter test is poor, the strength requirement of the airplane model is high, the attitude control is realized by controlling the control surface to improve the flutter dangerous boundary, but the dynamic characteristic of the control surface is difficult to accurately simulate due to the size limitation of the wind tunnel and the model.
Disclosure of Invention
An object of the present invention is to solve the above problems or disadvantages and to provide advantages which will be described later; to achieve these objects and other advantages and in accordance with the purpose of the invention, there is provided a rope support system for a full-aircraft flutter wind tunnel test, comprising a wind tunnel test section and an aircraft model disposed in the wind tunnel test section, characterized by further comprising:
two ends of the limiting rope are connected to the inner wall of the wind tunnel test section and are positioned in front of the airplane model;
a traction block located behind the model airplane; the traction block is connected with a retractable traction rope;
the horizontal main ropes are movably hung on two sides of the airplane model; the two horizontal main ropes extend forwards and then are connected to the limiting rope in a sliding mode, and the two horizontal main ropes extend backwards and then are fixedly connected to the two ends of the traction block respectively, so that the airplane model is surrounded.
Preferably, the limiting rope can be configured as a vertical V rope; the front ends of the two horizontal main ropes are movably provided with a tripod; two bottom corners at the rear end of the tripod are respectively and transversely provided with a first fixed pulley; pulley bodies of the two first fixed pulleys are fixedly connected with the front ends of the two horizontal main ropes so as to form hinge joint; a first movable pulley is vertically arranged on the vertex angle at the front end of the tripod; the middle part of the vertical V-shaped rope is arranged in a pulley cavity of the first movable pulley in a penetrating mode, and therefore sliding connection is formed.
Preferably, the vertical V-rope adopts a closed-loop connection configuration, which specifically includes: the upper wall and the lower wall of the wind tunnel test section are respectively provided with two longitudinal strip-shaped holes; a plurality of second fixed pulleys are fixedly arranged on the interval path of the outer wall of the wind tunnel test section of the two strip-shaped holes; the vertical V-shaped rope sequentially passes through one of the strip-shaped holes, the second fixed pulleys and the other strip-shaped hole from the pulley cavity of the first movable pulley and then winds back to the pulley cavity of the first movable pulley to carry out closed-loop butt joint.
Preferably, wherein the limiting rope can be configured as two horizontal V-ropes; two ends of the two horizontal V ropes are respectively and fixedly connected to the left side wall and the right side wall of the wind tunnel test section; second movable pulleys are respectively arranged on the rope bodies of the two horizontal V ropes; pulley cavities of the two second movable pulleys are respectively sleeved on rope bodies of the two horizontal V-shaped ropes; and the shells of the two second movable pulleys are fixedly connected with the front ends of the two horizontal V ropes respectively, so that sliding connection is realized.
Preferably, the movable hanging mode of the two horizontal main ropes and the airplane model is as follows: the two horizontal main ropes are transversely hinged with the front end of the plane body; the two horizontal main ropes are in sliding connection with the rear end of the airplane body of the airplane model.
Preferably, the transverse hinge joint between the two horizontal main ropes and the front end of the airplane model body is specifically as follows: the device also comprises a rocker; a square hole is transversely formed in the nose of the airplane model; two ends of the rocker are respectively and fixedly arranged on the two horizontal main ropes; the middle part of the rocker is movably arranged in the square hole in a penetrating way; a round rod is vertically arranged in the middle of the square hole; a round hole is formed in the middle of the rocker; the round rod is movably arranged in the round hole in a penetrating mode.
Preferably, the sliding connection mode of the two horizontal main ropes and the rear end of the airplane body of the airplane model is as follows: slip rings are fixedly arranged on two sides of the airplane body of the airplane model; the two slip rings are respectively sleeved on the horizontal main rope, so that sliding connection is formed.
Preferably, the traction block is an i-beam; the upper side and the lower side of the left end of the I-shaped beam are respectively provided with an upper left pulley and a lower left pulley; the traction rope comprises a left rear rope and a right rear rope; three third fixed pulleys and a motor are arranged on the outer side of the upper wall of the wind tunnel test section; one end of the left rear rope is fixedly connected to the pulley body of the left upper pulley, the other end of the left rear rope penetrates through the pulley cavity of one of the third fixed pulleys and is wound on the rotating shaft of the motor, penetrates through the pulley cavities of the other two third fixed pulleys and penetrates through the pulley cavity of the fourth fixed pulley, and finally the left rear rope is fixed on the pulley body of the left lower pulley to form hinge joint, so that the closed loop of the whole rope body is completed; the right end of the I-shaped beam and a part associated with the right rear rope are arranged corresponding to the left end of the I-shaped beam.
Preferably, the device further comprises a rope tension adjusting system; the rope tension adjusting system comprises four L-shaped plates fixedly arranged on the outer side of the upper wall of the wind tunnel test section; each L-shaped plate is elastically connected with a concave box in a sliding manner; an hourglass-type roller is arranged in the concave box; the front end of the concave box is opened; the rear end of the concave box is connected to the shorter part of the L-shaped plate through a spring; the bottom of the concave box is provided with a sliding chute; a sliding strip matched with the sliding groove is arranged on the longer part of the L-shaped plate; the sliding groove is embedded in the sliding strip, so that elastic sliding connection is formed;
the left rear rope respectively passes through the pulley cavities of the two hourglass type rollers before and after being wound on the rotor of one of the motors;
the right rear rope passes through the pulley cavities of the other two hourglass type rollers respectively before and after being wound to the rotor of the other motor, so that a closed loop is completed.
The invention at least comprises the following beneficial effects:
the horizontal main rope is adopted as a foundation for supporting the whole airplane model body, the horizontal main rope is movably hung on two sides of the airplane model body, the rope is not directly sleeved in the airplane body of the airplane model (namely a pulley arranged in the airplane model), and the horizontal main rope is matched with the upper limiting rope and the traction block, so that the support mode has less influence on the mode of the airplane model body, the flutter test simulation test precision is improved, the requirement on the strength of the airplane model is low, the posture adjustment is not required to be carried out by operating the control surface of the airplane model, and the support mode has the advantages of small interference on a wind tunnel test flow field, high model posture adjustment precision and high efficiency.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
FIG. 1 is a general structure of the present invention (front end connected to vertical V-rope);
FIG. 2 is a detail view of the tripod of the present invention;
FIG. 3 is a general structure view of the present invention (front end connecting horizontal V rope)
FIG. 4 is a detailed structural view of a second movable sheave of the present invention;
FIG. 5 is a cross-hinged structural view of the front end of the plane model body of the present invention;
FIG. 6 is a structural view of the rocker of the present invention connected to two horizontal main ropes;
FIG. 7 is a block diagram of the rocker of the present invention connected to a round bar in an airplane model;
FIG. 8 is a block diagram of the rear end sliding connection of the aircraft model body of the present invention;
FIG. 9 is a detailed structural view of the traction block (I-beam) of the present invention;
fig. 10 is a detailed structural view of the rope tension adjusting system of the present invention;
fig. 11 is a detailed structural view of the concave pulley of the present invention.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings so that those skilled in the art can implement the invention with reference to the description; it should be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more elements or combinations thereof;
fig. 1-11 show a rope supporting system for a full-aircraft flutter wind tunnel test provided by the invention, which comprises a wind tunnel test section 1 and an aircraft model 11 arranged in the wind tunnel test section 1, and is characterized in that,
further comprising:
the two ends of the limiting rope 3 are connected to the inner wall of the wind tunnel test section 1 and are positioned in front of the airplane model 11;
a traction block 4 located behind the model airplane 11; the traction block 4 is connected with a retractable traction rope 5;
the horizontal main ropes 2 are movably hung on two sides of the airplane model 11; the two horizontal main ropes 2 extend forwards and then are connected to the limiting rope 3 in a sliding mode, and the two horizontal main ropes 2 extend backwards and then are fixedly connected to the two ends of the traction block 4 respectively, so that the airplane model 11 is surrounded.
The working principle is as follows: the elastic airplane model 11 is flexibly supported in the wind tunnel test section 1 through the rope supporting system, a flutter wind tunnel test is carried out under the action of airflow 12, the flutter frequency of the airplane model 11 is obtained in real time through a corresponding detection instrument, and the airplane model 11 is ensured to be in a safe flutter boundary without instability through ceaseless attitude adjustment of the airplane model 11;
the horizontal main ropes 2 are movably hung on two sides of the fuselage of the airplane model 11, so that the plane supporting capacity of the foundation is provided for the fuselage of the airplane model 11, and the whole airplane model 11 can be stably hung in the wind tunnel test section 1, which is the foundation of the rope supporting system; because the two ends of the limiting rope 3 are arranged on the wind tunnel test section 1 (inner wall), the middle part (rope body) of the limiting rope 3 plays a role of longitudinal support for the front end of the horizontal main rope 2, and simultaneously can keep the front end of the horizontal main rope 2 to have the capability of swinging left, right, up and down, so that the front end of the airplane model 11 can be stably supported longitudinally, and the attitude can be adjusted more smoothly; because the front end of the traction block 4 is fixedly connected with the horizontal main rope 2, the traction block 4 can be continuously retracted and pulled through the traction rope 5 at the rear end of the traction block 4, so that the traction block 4 can make descending, ascending, side falling and other actions, and the actions are made through the traction block 4 to drive the tail part of the airplane model 11 to perform corresponding actions, namely, the real-time adjustment (pitching adjustment and rolling adjustment) of the flight attitude of the airplane model 11 is realized.
In the design, the main advantages are that the horizontal main rope 2 is used as a base for supporting the whole body of the airplane model 11, and because the horizontal main rope 2 is movably hung at two sides of the body of the airplane model 11, rather than directly sleeving the rope inside the body of the airplane model 11 (namely, a pulley built in the airplane model 11),
and the upper limiting rope 3 and the traction block 4 are matched, the support mode has smaller influence on the fuselage mode of the airplane model 11, the simulation test precision of the flutter test is improved, the requirement on the strength of the airplane model 11 is low, the posture adjustment is not required to be carried out by operating the control surface of the airplane model 10, and the wind tunnel test has the advantages of small interference on a wind tunnel test flow field and higher model posture adjustment precision and efficiency.
(see fig. 11) to supplement the description: all the pulley parts mentioned in the following technical scheme are concave pulleys; the pulley body of the concave pulley refers to a roller body with a concave surface; the pulley cavity of the concave pulley refers to a cavity which is used for penetrating a rope to slide between the pulley body and the inner wall of the shell;
(as shown in fig. 1-2) in the above technical solution, the limiting rope 3 may be specifically configured as a vertical V-rope; the front ends of the two horizontal main ropes 2 are movably provided with a tripod 21; two bottom corners at the rear end of the tripod 21 are respectively and transversely provided with a first fixed pulley 211; pulley bodies of the two first fixed pulleys 211 are fixedly connected with the front ends of the two horizontal main ropes 2 so as to form a hinge joint; a first movable pulley 212 is vertically arranged on the vertex angle at the front end of the tripod 21; the middle part of the vertical V-shaped rope is arranged in the pulley cavity of the first movable pulley 212 in a penetrating way, so that a sliding connection is formed.
The working principle is as follows: the vertical V-shaped rope is matched with the upper triangular support 21 and then connected with the two horizontal main ropes 2, and the device has the further advantages that the triangular structure of the triangular support 21 is stable, the overall supporting stability of the device is further improved, more stable longitudinal supporting capability and uniform and smooth transverse shaking capability can be provided for the front ends of the two horizontal main ropes 2, and therefore the posture of the follow-up airplane model 11 is ensured to be more uniform and stable; meanwhile, only one single rope is used for the vertical V-shaped rope, so that the material cost of the rope is saved, and the configuration of the limiting rope 3 is simplified.
In the above technical solution (as shown in fig. 1), the vertical V-rope adopts a closed-loop connection configuration mode, which specifically includes: the upper wall and the lower wall of the wind tunnel test section 1 are respectively provided with two longitudinal strip-shaped holes 13; a plurality of second fixed pulleys 14 are fixedly arranged on the two strip-shaped holes 13 on the interval path of the outer wall of the wind tunnel test section 1; the vertical V-shaped rope passes through one of the strip-shaped holes 13, the plurality of second fixed pulleys 14 and the other strip-shaped hole 13 from the pulley cavity of the first movable pulley 212 in sequence, and then winds back to the pulley cavity of the first movable pulley 212 to carry out closed-loop butt joint.
The working principle is as follows: in this kind of design, vertical V rope is not with the simple adoption rope directly hangs from top to bottom and connects the inboard of fixing the upper and lower wall at wind tunnel test section 1, but has adopted one kind and has let vertical V rope go back the closed mode of loop completely, let the apex angle of whole tripod 21 can pass through the direct sliding connection of first movable pulley 212 on this vertical V rope that has formed the loop, cooperate the roll of going up a plurality of second fixed pulleys 14 again, its further advantage lies in, can let vertical V rope keep a more movable state of relaxing, but the stiff state of non-dying, the flexibility ratio is bigger, let the activity space of the front end of two horizontal main ropes 2 bigger, can carry out more nimble up-and-down horizontal hunting, with the attitude adjustment of better adaptation aircraft model 11.
(as shown in fig. 3-4) in the above technical solution, the limiting rope 3 may be specifically configured as two horizontal V ropes; two ends of the two horizontal V ropes are respectively and fixedly connected to the left side wall and the right side wall of the wind tunnel test section 1; the rope bodies of the two horizontal V ropes are respectively provided with a second movable pulley 22; pulley cavities of the two second movable pulleys 22 are respectively sleeved on the rope bodies of the two horizontal V-shaped ropes; the shells of the two second movable pulleys 22 are fixedly connected with the front ends of the two horizontal V ropes 2 respectively, so that sliding connection is realized.
The working principle is as follows: in the design, the two horizontal V ropes can provide more stable longitudinal supporting capability for the front ends of the two horizontal main ropes 2; meanwhile, the horizontal main rope 2 has more stable and uniform transverse movement capability and better support property by matching with the two second movable pulleys 22 capable of sliding horizontally, and the horizontal main rope 2 can be provided with more stable and smooth and uniform transverse movement capability when the aircraft model 11 is subjected to subsequent posture adjustment; it has further advantages over vertical V-ropes: when two horizontal V ropes are used for supporting the two horizontal main ropes 2, the large flexibility is guaranteed, and meanwhile, the limiting capacity is further provided to a certain degree in the vertical direction, so that the upper wall of the wind tunnel test section 1 can be effectively prevented from being touched by the airplane model 11 in the flutter wind tunnel test process.
In the above technical solution (as shown in fig. 1), the movable hanging mode of the two horizontal main ropes 2 and the airplane model 11 is specifically as follows: the two horizontal main ropes 2 are transversely hinged with the front end of the body of the airplane model 11; the two horizontal main ropes 2 are in sliding connection with the rear end of the airplane body of the airplane model 11.
The working principle is as follows: in the design, different connection modes are respectively adopted at the front section and the rear section of the fuselage of the airplane model 11, so that the airplane model 11 obtains a plurality of supporting points on a horizontal plane; the transverse hinging provides stable horizontal rotation capability for the nose part of the airplane model 11, so that the yaw attitude adjustment of the airplane model 11 is realized; the sliding connection ensures that the airplane model 11 can keep a little activity while being supported by the two horizontal main ropes 2, so that the posture of the airplane model 11 can be adjusted more uniformly and flexibly.
In the above technical solution (as shown in fig. 5-7), the transverse hinge joint between the two horizontal main ropes 2 and the front end of the fuselage of the airplane model 11 specifically includes: also comprises a rocker 23; a square hole 24 is transversely arranged on the nose of the airplane model 11; two ends of the rocker 23 are respectively fixedly arranged on the two horizontal main ropes 2; the middle part of the rocker 23 is movably arranged in the square hole 24 in a penetrating way; a round rod 27 is vertically arranged in the middle of the square hole 24; a round hole 26 is formed in the middle of the rocker 23; the round rod 27 is movably arranged in the round hole 26 in a penetrating way.
The working principle is as follows: in the design, the key point is that two ends of a rocker 23 are respectively fixed on two horizontal main ropes 2, a square hole 24 provides a certain moving space for the rocker 23 to swing in the horizontal direction, when the airplane model 11 is pulled by a rear traction block 4, the nose of the airplane model 11 can rotate to a certain degree in a round hole 26 in the middle of the rocker 23 through a vertically arranged round rod 27, so that a certain yaw capacity is provided for the airplane model 11, and as the two horizontal main ropes 2, the rocker 23 and the traction block 4 form a movable parallelogram mechanism, the 'soft support' in the true sense is realized, so that the yaw freedom degree of the airplane model 11 is further released to a certain degree.
In the above technical solution (as shown in fig. 8), the sliding connection mode between the two horizontal main ropes 2 and the rear end of the airplane body of the airplane model 11 is specifically as follows: slip rings 25 are fixedly arranged on two sides of the airplane body of the airplane model 11; the two slip rings 25 are respectively sleeved on the horizontal main rope 2, so that sliding connection is formed.
The working principle is as follows: in this design, it is further advantageous that the two slip rings 25 cooperate with the horizontal main ropes 2 to make the horizontal main ropes 2 stably support the rear end of the airplane model 11, and since the front fuselage section of the airplane model is supported by the two horizontal main ropes 2 through the rocker 23 and the vertically arranged round rod 27, and the rear fuselage section is slidably connected with the two horizontal main ropes 2 through the slip rings 25, the airplane model 11 has the above three support points, and the support is more stable; meanwhile, certain sliding capacity is guaranteed, the whole airplane model 11 can be loosened and flexible on the horizontal main rope 2 as much as possible, the soft support effect of the device on the airplane model 11 is further improved, the constraint on the airplane model 11 is reduced, and the flutter wind tunnel test simulation precision of the airplane model 11 is improved.
(as shown in fig. 1 and 9) in the above technical solution, the traction block 4 is specifically an i-beam; the upper side and the lower side of the left end of the I-beam are respectively provided with a left upper pulley 41 and a left lower pulley 42; the hauling cable 5 comprises a left rear cable 51 and a right rear cable 52; the outer side of the upper wall of the wind tunnel test section 1 is provided with three third fixed pulleys 53 and a motor 54; one end of the left rear rope 51 is fixedly connected to the pulley body of the upper left pulley 41, the other end of the left rear rope passes through the pulley cavity of one of the third fixed pulleys 53, is wound on the rotating shaft of the motor 54, passes through the pulley cavities of the other two third fixed pulleys 53, passes through the pulley cavity of the fourth fixed pulley 55, and is finally fixed on the pulley body of the lower left pulley 42 to form a hinge joint, so that the closed loop of the whole rope body is completed; the right end of the i-beam and the components associated with the right rear cord 52 are disposed in correspondence with the left end of the i-beam.
The working principle is as follows: in this design, we can realize two attitude adjustments of the airplane model:
(1) pitch adjustment: when the two motors 54 rotate forwards simultaneously, the left rear rope 51 on the left upper pulley 41 is tightened, the left rear rope 51 on the left lower pulley 42 is loosened, and the right rear rope 52 is subjected to the same steps, so that the whole I-beam performs ascending motion, the whole two horizontal main ropes 2 are pulled upwards, and the nose part of the airplane model 11 is adjusted to move down;
when the two motors 54 rotate reversely at the same time, the left rear rope 51 on the upper left pulley 41 is loosened, the left rear rope 51 on the lower left pulley 42 is tightened, and the right rear rope 52 is subjected to the same steps, so that the whole i-beam descends, the whole two horizontal main ropes 2 are pulled downwards, and the nose part of the airplane model 11 is adjusted to move upwards;
(2) rolling adjustment: when the motor 54 on the left rear rope 51 rotates forwards and the motor 54 on the right rear rope 52 rotates backwards, according to the motion principle explained above, the left end of the whole i-beam will rise, the right end of the i-beam will fall, and the whole two horizontal main ropes 2 are pulled and pulled to the right and below side, so that the airplane model 11 can be driven to roll to the right, and the attitude adjustment is realized;
when the motor 54 on the left rear rope 51 rotates reversely and the motor on the right rear rope 52 rotates positively, according to the motion principle explained above, the right end of the whole i-beam will rise, the left end of the i-beam will fall, and the whole two horizontal main ropes 2 are pulled and pulled leftwards and rightwards, so that the airplane model 11 can be driven to roll leftwards and realize attitude adjustment;
in conclusion, one of the further advantages is that the device takes an external I-beam separated from the airplane model device body as a traction component for airplane model attitude adjustment; because the traction piece is externally arranged, the requirement on the strength of the airplane model 11 is lower, and the aerodynamic interference is smaller; meanwhile, the pitching and rolling postures of the airplane model 11 can be adjusted through the homodromous or reverse linkage of the left rear rope and the right rear rope, and the posture adjustment precision and efficiency of the airplane model 11 are higher;
the second further advantage is that the aircraft model 11 is attitude-adjusted by using the external i-beam, and control is performed without depending on the control surface of the aircraft model 11 body, so that the limitations of the wind tunnel size, the aircraft model 11 and the control surface size can be effectively removed, and a safe flutter wind tunnel test is performed under the condition that the requirement of the support frequency of the aircraft model 11 is met.
(fig. 10) in the above solution, a rope tension adjusting system 6 is further included; the rope tension adjusting system comprises four L-shaped plates 61 fixedly arranged on the outer side of the upper wall of the wind tunnel test section 1; each L-shaped plate 61 is elastically connected with a concave box 62 in a sliding manner; an hourglass-type roller 63 is arranged inside the concave box 62; the front end of the concave box 62 is opened; the rear end of the concave box 62 is connected to the shorter part of the L-shaped plate 61 through a spring 64; the bottom of the concave box 62 is provided with a sliding groove 65; a slide bar 66 matched with the sliding groove 65 is arranged on the longer part of the L-shaped plate 61; the sliding groove 65 is embedded in the sliding strip 66, so that an elastic sliding connection is formed;
the left rear rope passes through the pulley cavities of the two hourglass type rollers 63 before and after being wound on the rotor of one of the motors 54;
the right rear rope passes through the pulley cavities of the other two hourglass rollers 63 before and after being wound around the rotor of the other motor 54, respectively, thereby completing a closed loop.
The working principle is as follows: in the design of an actual rope suspension system, the front-rear rigidity of the whole system must be reasonably distributed, and the vibration frequency of the system is less than 1/3-1/5 of the lowest-order elastic first-order modal frequency of a typical flutter model structure, so that the stability of the whole support system can be ensured.
In this design, the springs 64 with different stiffness coefficients are respectively replaced between the shorter parts of the four L-shaped plates 61 and the four concave boxes 62, so that the vibration frequencies of the left rear rope 51 and the right rear rope 52 in the whole supporting system can be completely and freely regulated, and the supporting frequency of the whole airplane model 11 can be quickly and efficiently regulated, so as to ensure that the whole supporting system is more stable, and improve the testing accuracy of the flutter test.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (9)
1. The utility model provides a rope braced system for full aircraft flutter wind tunnel test, includes the wind tunnel test section to and set up the aircraft model in the wind tunnel test section, its characterized in that still includes:
the two ends of the limiting rope are connected to the inner wall of the wind tunnel test section and are positioned in front of the airplane model;
a traction block located behind the model airplane; the traction block is connected with a retractable traction rope;
the horizontal main ropes are movably hung on two sides of the airplane model; the two horizontal main ropes extend forwards and then are connected to the limiting rope in a sliding mode, and the two horizontal main ropes extend backwards and then are fixedly connected to the two ends of the traction block respectively, so that the airplane model is surrounded.
2. The rope support system for the full-aircraft flutter wind tunnel test according to claim 1, wherein the limiting rope is configured as a vertical V rope; the front ends of the two horizontal main ropes are movably provided with a tripod; two bottom corners at the rear end of the tripod are respectively and transversely provided with a first fixed pulley; pulley bodies of the two first fixed pulleys are fixedly connected with the front ends of the two horizontal main ropes so as to form a hinge joint; a first movable pulley is vertically arranged on the vertex angle at the front end of the tripod; the middle part of the vertical V-shaped rope is arranged in a pulley cavity of the first movable pulley in a penetrating mode, and therefore sliding connection is formed.
3. The rope support system for the full-aircraft flutter wind tunnel test according to claim 2, wherein the vertical V rope adopts a closed-loop connection configuration mode, and specifically comprises: the upper wall and the lower wall of the wind tunnel test section are respectively provided with two longitudinal strip-shaped holes; a plurality of second fixed pulleys are fixedly arranged on the interval path of the outer wall of the wind tunnel test section of the two strip-shaped holes; the vertical V-shaped rope sequentially passes through one of the strip-shaped holes, the second fixed pulleys and the other strip-shaped hole from the pulley cavity of the first movable pulley and then winds back to the pulley cavity of the first movable pulley to carry out closed-loop butt joint.
4. The rope support system for the full-aircraft flutter wind tunnel test according to claim 1, wherein the limiting rope is configured into two horizontal V ropes; two ends of the two horizontal V ropes are respectively and fixedly connected to the left side wall and the right side wall of the wind tunnel test section; second movable pulleys are respectively arranged on the rope bodies of the two horizontal V ropes; pulley cavities of the two second movable pulleys are respectively sleeved on rope bodies of the two horizontal V-shaped ropes; and the shells of the two second movable pulleys are fixedly connected with the front ends of the two horizontal V ropes respectively, so that sliding connection is realized.
5. The rope support system for the full-aircraft flutter wind tunnel test according to claim 1, wherein the movable hanging mode of the two horizontal main ropes and the aircraft model is as follows: the two horizontal main ropes are transversely hinged with the front end of the airplane body of the airplane model; the two horizontal main ropes are in sliding connection with the rear end of the airplane body of the airplane model.
6. The rope support system for the whole aircraft flutter wind tunnel test according to claim 1, wherein the transverse hinging mode of the two horizontal main ropes and the front end of the aircraft model body is specifically as follows: the device also comprises a rocker; a square hole is transversely formed in the nose of the airplane model; two ends of the rocker are respectively and fixedly arranged on the two horizontal main ropes; the middle part of the rocker is movably arranged in the square hole in a penetrating way; a round rod is vertically arranged in the middle of the square hole; a round hole is formed in the middle of the rocker; the round rod is movably arranged in the round hole in a penetrating mode.
7. The rope support system for the whole aircraft flutter wind tunnel test according to claim 1, wherein the sliding connection mode of the two horizontal main ropes and the rear end of the aircraft model body is specifically as follows: slip rings are fixedly arranged on two sides of the airplane body of the airplane model; the two slip rings are respectively sleeved on the horizontal main rope, so that sliding connection is formed.
8. The rope support system for the full-aircraft flutter wind tunnel test according to claim 1, wherein the traction block is an I-beam; the upper side and the lower side of the left end of the I-beam are respectively provided with a left upper pulley and a left lower pulley; the traction rope comprises a left rear rope and a right rear rope; three third fixed pulleys and a motor are arranged on the outer side of the upper wall of the wind tunnel test section; one end of the left rear rope is fixedly connected to the pulley body of the left upper pulley, the other end of the left rear rope penetrates through the pulley cavity of one of the third fixed pulleys and is wound on the rotating shaft of the motor, penetrates through the pulley cavities of the other two third fixed pulleys and penetrates through the pulley cavity of the fourth fixed pulley, and finally the left rear rope is fixed on the pulley body of the left lower pulley to form hinge joint, so that the closed loop of the whole rope body is completed; the right end of the I-beam and the part associated with the right rear rope are arranged corresponding to the left end of the I-beam.
9. The rope support system for the full-aircraft flutter wind tunnel test according to claim 8, further comprising a rope tension adjusting system; the rope tension adjusting system comprises four L-shaped plates fixedly arranged on the outer side of the upper wall of the wind tunnel test section; each L-shaped plate is elastically connected with a concave box in a sliding manner; an hourglass-type roller is arranged in the concave box; the front end of the concave box is opened; the rear end of the concave box is connected to the shorter part of the L-shaped plate through a spring; the bottom of the concave box is provided with a sliding chute; a sliding strip matched with the sliding groove is arranged on the longer part of the L-shaped plate; the sliding groove is embedded in the sliding strip, so that elastic sliding connection is formed; the left rear rope respectively passes through the pulley cavities of two hourglass-type rollers before and after being wound on the rotor of one of the motors; the right rear rope respectively passes through the pulley cavities of the other two hourglass type pulleys before and after being wound to the rotor of the other motor, so that a closed loop is completed.
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| CN115655635A (en) * | 2022-12-14 | 2023-01-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-freedom-degree supporting system for full-body freedom-degree flutter or gust test |
| CN117433740A (en) * | 2023-12-20 | 2024-01-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Connecting device for wind tunnel flight test and aircraft model |
| CN117740312A (en) * | 2024-02-21 | 2024-03-22 | 中国空气动力研究与发展中心空天技术研究所 | Detachable reference suspension system suitable for high-speed wind tunnel large-scale heavy model test |
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