CN114923656B - Rope supporting system for full-machine flutter wind tunnel test - Google Patents
Rope supporting system for full-machine flutter wind tunnel test Download PDFInfo
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- CN114923656B CN114923656B CN202210851916.2A CN202210851916A CN114923656B CN 114923656 B CN114923656 B CN 114923656B CN 202210851916 A CN202210851916 A CN 202210851916A CN 114923656 B CN114923656 B CN 114923656B
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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
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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
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Abstract
The invention discloses a rope support 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 aircraft 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 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 rope is movably hung on two sides of the airplane model; the two horizontal main ropes are connected to the limiting ropes in a sliding mode after extending forwards, and are fixedly connected to two ends of the traction block respectively after extending backwards, so that the airplane model is surrounded. The method has less influence on the model body mode of the aircraft model, improves the simulation test precision of the flutter test, has low requirement on the strength of the aircraft model, and has the advantages of small interference on the flow field of the wind tunnel test, and higher model posture 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-machine flutter wind tunnel test.
Background
Flutter is a phenomenon of aeroelastic instability caused by an aircraft under the coupling action of aerodynamic force, elastic force and inertial force. When the aircraft flies transonically, the nonlinear of aerodynamic force can lead to the critical speed of flutter to be greatly reduced, the structural vibration is rapidly increased, the structural damage is extremely easy to be caused, the flight safety is threatened, and the flight envelope is restricted. Accurate acquisition of transonic flutter boundaries is a critical fundamental problem that aircraft design must face.
With the development of the structural layout of the aircraft, the interaction between the components is more complex, coupling flutter is very easy to occur, and a full-machine flutter wind tunnel test is required to be carried out to obtain a more accurate flutter boundary. In the test, not only the soft support of the model is needed to be realized, the free flight state is simulated, but also the gesture is regulated in real time to ensure the safety of the model.
Currently, in NASA patent 3276251, a "free flight suspension system" is disclosed, which mainly uses two ropes to respectively pass through pulleys built in front and back of a fuselage to form a closed loop, so as to suspend and lift the whole aircraft model, and uses a rudder to adjust the attitude of the aircraft model, (the rudder refers to the main control surface of the aircraft model body, namely an aileron, an elevator, a hinged winglet at the rear edge of the rudder, or a tunable winglet.)
The method has the defects that the fuselage of the airplane model is directly subjected to the tensile force action of front and rear ropes, the fuselage mode of the airplane model is greatly affected, the simulation test precision of the flutter test is poor, the strength requirement on the airplane model is very high, the attitude control is realized by controlling the control surface to change the flutter dangerous boundary, and the dynamics characteristic of the control surface is difficult to accurately simulate due to the limitation of the wind tunnel and the size of the model.
Disclosure of Invention
The present invention has been made to solve the above problems or disadvantages and to provide advantages which will be described later; to achieve these objects and 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, including a wind tunnel test section, and an aircraft model disposed in the wind tunnel test section, characterized by further comprising:
the two ends of the limiting rope are connected to the inner wall of the wind tunnel test section and 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 rope is movably hung on two sides of the airplane model; the two horizontal main ropes are connected to the limiting ropes in a sliding mode after extending forwards, and are fixedly connected to two ends of the traction block respectively after extending backwards, so that the airplane model is surrounded.
Preferably, the limiting rope can be specifically configured as a vertical V rope; tripod is movably arranged at the front ends of the two horizontal main ropes; the two bottom corners of the rear end of the tripod are respectively transversely provided with a first fixed pulley; the pulley bodies of the two first fixed pulleys are fixedly connected with the front ends of the two horizontal main ropes, so that a hinge is formed; 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 rope is arranged in the pulley cavity of the first movable pulley in a penetrating way, so that sliding connection is formed.
Preferably, the vertical V-rope adopts a configuration mode of closed loop connection, which specifically comprises: the upper wall and the lower wall of the wind tunnel test section are respectively provided with two longitudinal strip-shaped holes; the two strip-shaped holes are fixedly provided with a plurality of second fixed pulleys on the interval path of the outer wall of the wind tunnel test section; the vertical V rope starts from the pulley cavity of the first movable pulley, sequentially passes through one of the strip-shaped holes, the second fixed pulleys and the other strip-shaped hole, and then winds back to the pulley cavity of the first movable pulley to be in closed-loop butt joint.
Preferably, the limiting ropes can 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; the rope bodies of the two horizontal V ropes are respectively provided with a second movable pulley; pulley cavities of the two second movable pulleys are respectively sleeved on rope bodies of the two horizontal V ropes; 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 specifically as follows: the two horizontal main ropes are transversely hinged with the front end of the airplane model body; the two horizontal main ropes are in sliding connection with the rear end of the aircraft model body.
Preferably, the transverse hinging manner between the two horizontal main ropes and the front end of the aircraft model body is specifically as follows: the device also comprises a rocker; square holes are transversely formed in the aircraft nose of the aircraft model; the 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; the middle part of the rocker is provided with a round hole; the round rod is movably arranged in the round hole in a penetrating way.
Preferably, the sliding connection mode between 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.
Preferably, 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 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 motors 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 passes through the pulley cavity of one third fixed pulley and is wound on the rotating shaft of the motor, then passes through the pulley cavities of the other two third fixed pulleys, then passes through the pulley cavity of the fourth fixed pulley, and finally is fixed on the pulley body of the left lower pulley 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 parts associated with the right rear rope are arranged corresponding to the left end of the I-beam.
Preferably, the system 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 provided with an opening; 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 chute; a slide bar matched with the chute is arranged on the longer part of the L-shaped plate; the sliding groove is embedded and arranged on the sliding strip, so that elastic sliding connection is formed;
the left rear rope respectively passes through pulley cavities of two hourglass type rollers before and after being wound to a rotor of one motor;
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 the closed loop is completed.
The invention at least comprises the following beneficial effects:
the horizontal main rope is adopted as the basis for supporting the whole aircraft model body, and is movably hung on two sides of the aircraft model body, so that the rope is not directly sleeved in the aircraft model body (namely, a pulley arranged in the aircraft model), and is matched with the limiting rope and the traction block.
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 block diagram of the present invention (front end connected vertical V-string);
FIG. 2 is a detailed construction diagram of a tripod according to the present invention;
FIG. 3 is a general construction diagram of the present invention (front end connecting horizontal V rope)
FIG. 4 is a detailed construction diagram of a second movable pulley according to the present invention;
FIG. 5 is a block diagram of the transverse hinge of the forward end of the aircraft model body of the present invention;
FIG. 6 is a block diagram of the rocker of the present invention attached to two horizontal main ropes;
FIG. 7 is a block diagram of the connection of a rocker to a round bar in an aircraft model according to the invention;
FIG. 8 is a block diagram of a rear end sliding connection of an aircraft model body according to the present invention;
fig. 9 is a detailed construction view of the traction block (i-beam) of the present invention;
fig. 10 is a detailed construction diagram of the rope tension adjusting system of the present invention;
fig. 11 is a detailed construction diagram of the concave pulley of the present invention.
Detailed Description
The present invention is described in further detail below with reference to the drawings to enable those skilled in the art to practice the invention by referring to the description; it will be appreciated 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 support system for a full-aircraft flutter wind tunnel test provided by the invention, comprising a wind tunnel test section 1, and an aircraft model 11 arranged in the wind tunnel test section 1, characterized in that,
further comprises:
the two ends of the limiting rope 3 are connected to the inner wall of the wind tunnel test section 1 and positioned in front of the airplane model 11;
a traction block 4 located behind the aircraft model 11; the traction block 4 is connected with a retractable traction rope 5;
the horizontal main rope 2 is movably hung on two sides of the airplane model 11; the two horizontal main ropes 2 are connected to the limiting rope 3 in a sliding mode after extending forwards, and the two horizontal main ropes 2 are fixedly connected to two ends of the traction block 4 after extending backwards respectively, so that the airplane model 11 is surrounded.
Working principle: the elastic aircraft model 11 is flexibly supported in the wind tunnel test section 1 through the rope support system, a flutter wind tunnel test is carried out under the action of the airflow 12, the flutter frequency of the aircraft model 11 is obtained in real time through a corresponding detecting instrument, and the aircraft model 11 is ensured not to be unstable in a safe flutter boundary through continuous posture adjustment of the aircraft model 11;
the horizontal main ropes 2 are movably hung on two sides of the fuselage of the aircraft model 11, so that the plane supporting capability of a foundation is provided for the fuselage of the aircraft model 11, and the whole aircraft model 11 can be stably suspended in the wind tunnel test section 1, which is the foundation of the rope supporting system; because both 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 in longitudinally supporting the front end of the horizontal main rope 2, and meanwhile, the front end of the horizontal main rope 2 can be kept to have the capability of swaying left, right, up and down, so that a stable longitudinal supporting effect is achieved on the front end of the aircraft model 11, and the attitude adjustment can be carried out 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, sideways tilting and other actions, and the tail of the aircraft model 11 is driven to make corresponding actions through the actions made by the traction block 4, namely, the real-time adjustment (pitch adjustment and roll adjustment) of the flight attitude of the aircraft model 11 is realized.
In this design, the main advantage is that the horizontal main rope 2 is used as the basis for supporting the whole aircraft model 11 fuselage, because the horizontal main rope 2 is movably hung on both sides of the aircraft model 11 fuselage, instead of directly sleeving the rope inside the aircraft model 11 fuselage (i.e. the pulleys built in the aircraft model 11),
and the upper limit rope 3 and the traction block 4 are matched, so that the supporting mode has smaller influence on the model body mode of the aircraft model 11, the simulation test precision of the flutter test is improved, the strength requirement on the aircraft model 11 is low, the attitude adjustment is not required by operating the control surface of the aircraft model 10, and the supporting mode has the advantages of small interference on the flow field of the wind tunnel test and higher model attitude adjustment precision and efficiency.
(as in fig. 11) supplementary explanation: all mentioned pulley parts in the following technical proposal 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 between the pulley body and the inner wall of the shell, and the cavity is used for passing through a rope to slide;
(as shown in fig. 1-2), in the above technical solution, the limit rope 3 may be specifically configured as a vertical V-rope; tripod 21 is movably arranged at the front ends of the two horizontal main ropes 2; the two bottom corners of the rear end of the tripod 21 are respectively transversely provided with a first fixed pulley 211; the pulley bodies of the two first fixed pulleys 211 are fixedly connected with the front ends of the two horizontal main ropes 2, so that a hinge is formed; a first movable pulley 212 is vertically arranged on the vertex angle at the front end of the tripod 21; the vertical V-rope middle portion is threaded in the pulley cavity of the first movable pulley 212, thereby forming a sliding connection.
Working principle: the vertical V-shaped ropes are matched with the triangular frames 21 and then connected with the two horizontal main ropes 2, so that the triangular structure of the triangular frames 21 is stable, the overall support stability of the device is further improved, more stable longitudinal support capacity and even and smooth transverse shaking capacity can be provided for the front ends of the two horizontal main ropes 2, and further, the subsequent posture adjustment of the aircraft 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 configuration mode of closed loop connection, 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; the two strip-shaped holes 13 are fixedly provided with a plurality of second fixed pulleys 14 on the interval path of the outer wall of the wind tunnel test section 1; the vertical V-ropes start from the pulley cavity of the first movable pulley 212, sequentially pass through one of the bar-shaped holes 13, the plurality of second fixed pulleys 14 and the other bar-shaped hole 13, and then wind back to the pulley cavity of the first movable pulley 212 for closed-loop butt joint.
Working principle: in this design, the vertical V-ropes are not directly suspended and fixed on the inner sides of the upper wall and the lower wall of the wind tunnel test section 1 by a simple rope, but a mode of completely closing the vertical V-ropes in a loop is adopted, so that the vertex angle of the whole tripod 21 can be directly connected onto the vertical V-ropes which form the loop in a sliding manner through the first movable pulley 212, and then the vertical V-ropes are matched with the rolling of the second fixed pulleys 14.
(as shown in fig. 3 to 4), in the above technical solution, the limit 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 rope bodies of the two horizontal V 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.
Working principle: in this design, two horizontal V-ropes can provide a more stable longitudinal support capability for the front ends of two horizontal main ropes 2; meanwhile, by matching with two second movable pulleys 22 capable of sliding horizontally, the horizontal main rope 2 has more stable and uniform transverse movement capability and better support, so that more stable and smooth and uniform transverse movement capability can be provided for the horizontal main rope 2 when the aircraft model 11 is subjected to subsequent posture adjustment; it is still further advantageous from vertical V-ropes: when two horizontal V ropes are used for supporting two horizontal main ropes 2, the vertical direction has a certain limiting capacity while ensuring a large flexibility, so that the aircraft model 11 can be effectively prevented from touching the upper wall of the wind tunnel test section 1 in the flutter wind tunnel test process.
In the above technical solution (as shown in fig. 1), the movable hooking manner of the two horizontal main ropes 2 and the airplane model 11 is specifically: the two horizontal main ropes 2 are transversely hinged with the front end of the airplane body of the airplane model 11; the two horizontal main ropes 2 are in sliding connection with the rear end of the aircraft model 11.
Working principle: in this design, by adopting different connection modes at the front and rear sections of the fuselage of the aircraft model 11, a plurality of support points are obtained for the aircraft model 11 on the horizontal plane; the transverse hinge provides stable horizontal rotation capability for the nose part of the aircraft model 11, so that yaw attitude adjustment of the aircraft model 11 is realized; the sliding connection ensures that the aircraft model 11 is supported by the two horizontal main ropes 2 while maintaining a little mobility, so that the attitude adjustment of the aircraft model 11 is more uniform and flexible.
In the above technical solution (as shown in fig. 5 to 7), the transverse hinging manner between the two horizontal main ropes 2 and the front end of the fuselage of the aircraft model 11 is specifically: also comprises a rocker 23; square holes 24 are transversely formed in the aircraft nose of the aircraft model 11; the two ends of the rocker 23 are respectively and 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.
Working principle: in this design, the key point is that the two ends of the rocker 23 are fixed on the two horizontal main ropes 2 respectively, the square hole 24 provides a certain movable space for the rocker 23 to swing in the horizontal direction, when the aircraft model 11 is pulled by the rear traction block 4, the aircraft nose of the aircraft model 11 rotates in the round hole 26 in the middle of the rocker 23 to a certain extent through the round rod 27 which is vertically arranged, so that a certain extent of yaw capacity is provided for the aircraft model 11, and the two horizontal main ropes 2, the rocker 23 and the traction block 4 form a movable parallelogram mechanism to realize a truly "soft support" so as to further release the yaw freedom degree of the aircraft model 11 to a certain extent.
In the above technical solution, as shown in fig. 8, the sliding connection manner between the two horizontal main ropes 2 and the rear end of the fuselage of the airplane model 11 is specifically: 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 ropes 2, so that sliding connection is formed.
Working principle: in this design, it has the further advantage that the horizontal main ropes 2 are matched with the horizontal main ropes 2 through the two slip rings 25, so that the rear end of the airplane model 11 can be stably supported, and the support is more stable because the front section of the airplane body of the airplane model is supported by the two horizontal main ropes 2 through the rocking bars 23 and the round rods 27 which are vertically arranged, and the rear section of the airplane body is in sliding connection with the two horizontal main ropes 2 through the slip rings 25, so that the airplane model 11 has the three supporting points; meanwhile, certain sliding capacity is guaranteed, the whole aircraft model 11 can be loosened and flexible on the horizontal main rope 2 as much as possible, the soft supporting effect of the device on the aircraft model 11 is further improved, the constraint on the aircraft model 11 is reduced, and the simulation precision of the flutter wind tunnel test of the aircraft 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 rope 5 comprises a left rear rope 51 and a right rear rope 52; three third fixed pulleys 53 and motors 54 are arranged on the outer side of the upper wall of the wind tunnel test section 1; one end of the left rear rope 51 is fixedly connected to the pulley body of the left upper pulley 41, the other end of the left rear rope passes through the pulley cavity of one third fixed pulley 53 and is wound on the rotating shaft of the motor 54, then passes through the pulley cavities of the other two third fixed pulleys 53 and then passes through the pulley cavity of the fourth fixed pulley 55, and finally is fixed on the pulley body of the left lower 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 rope 52 are disposed in correspondence with the left end of the i-beam.
Working principle: in this design, we can implement two kinds of attitude adjustments for the aircraft model:
(1) Pitch adjustment: when the two motors 54 rotate positively at the same time, the left rear rope 51 on the left upper pulley 41 will be tightened, the left rear rope 51 on the left lower pulley 42 will be loosened, the right rear rope 52 will perform the same steps, thus the whole I-beam will perform the ascending movement, and the traction of the whole two horizontal main ropes 2 will be realized, so that the nose part of the aircraft model 11 will realize the adjustment of the 'low head' movement;
when the two motors 54 are simultaneously reversed, the left rear rope 51 positioned on the left upper pulley 41 is loosened, the left rear rope 51 positioned on the left lower pulley 42 is tightened, and the right rear rope 52 performs the same steps, so that the whole I-beam can perform descending movement, and the whole two horizontal main ropes 2 are pulled downwards to adjust the head-up action of the aircraft model 11;
(2) And (3) rolling adjustment: when the motor 54 on the left rear rope 51 rotates positively and the motor 54 on the right rear rope 52 rotates reversely, the left end of the whole I-beam will rise and the right end of the I-beam will fall according to the movement principle explained above, and the side pulling traction of the right lower part of the whole two horizontal main ropes 2 is realized, so that the aircraft model 11 can be driven to roll to the right side, and the posture 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, the right end of the whole I-beam will rise and the left end of the I-beam will descend according to the movement principle explained above, and the left side pulling traction of the whole two horizontal main ropes 2 is realized, so that the aircraft model 11 can be driven to roll leftwards, and the posture adjustment is realized;
in summary, one of the further advantages is that the device uses an external I-beam separated from the body of the airplane model device as a traction component for adjusting the posture of the airplane model; because the traction piece is externally arranged, the strength requirement on the aircraft model 11 is lower, and the pneumatic interference is smaller; meanwhile, the pitching and rolling postures of the aircraft model 11 can be adjusted through the same-direction or reverse-direction linkage of the left rear rope and the right rear rope, and the posture adjustment precision and efficiency of the aircraft model 11 are higher;
the second advantage is that the external i-beam is used for adjusting the posture of the aircraft model 11, so that the control surface of the aircraft model 11 body is not required to be controlled, the limitations of the wind tunnel size, the aircraft model 11 and the control surface size can be effectively relieved, and the safe flutter wind tunnel test can be performed under the condition that the supporting frequency requirement of the aircraft model 11 is met.
(as in fig. 10) in the above technical solution, a rope tension adjusting system 6 is also 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 and slidably connected with a concave box 62; an hourglass type roller 63 is arranged in 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 by a set spring 64; a chute 65 is arranged at the bottom of the concave box 62; a slide bar 66 matched with the slide groove 65 is arranged on the longer part of the L-shaped plate 61; the sliding groove 65 is embedded and arranged on the sliding strip 66, so that elastic sliding connection is formed;
the left rear rope passes through the pulley cavities of two of the hourglass-shaped rollers 63 before and after being wound to the rotor of one of the motors 54, respectively;
the right rear rope passes through the pulley cavities of the other two hourglass rollers 63 before and after being wound to the rotor of the other motor 54, respectively, thereby completing a closed loop.
Working principle: in the design of an actual rope suspension system, the front and back rigidity of the whole system is required to be reasonably distributed, and the vibration frequency of the system is smaller 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, it is further advantageous that the vibration frequencies of the left and right rear ropes 51 and 52 in the whole support system can be completely and freely controlled by only replacing springs 64 with different rigidity coefficients between the shorter portions of the four L-shaped plates 61 and the four concave boxes 62, so as to achieve rapid and efficient control of the support frequency of the whole aircraft model 11, thereby ensuring more stable whole support system and improving the test accuracy of the flutter test.
Although embodiments of the present invention have been disclosed above, it is not limited to the details and embodiments shown and described, it is well suited to various fields of use for which the invention would be readily apparent to those skilled in the art, and accordingly, the invention is not limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.
Claims (2)
1. 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:
the two ends of the limiting rope are connected to the inner wall of the wind tunnel test section and 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 rope is movably hung on two sides of the airplane model; the two horizontal main ropes are connected to the limiting ropes in a sliding mode after extending forwards, and are fixedly connected to two ends of the traction block respectively after extending backwards, so that the airplane model is surrounded;
the movable hanging mode of the two horizontal main ropes and the airplane model is specifically as follows: the two horizontal main ropes are transversely hinged with the front end of the airplane model body, and the transverse hinging mode is specifically as follows: the device also comprises a rocker; square holes are transversely formed in the aircraft nose of the aircraft model; the 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; the middle part of the rocker is provided with a round hole; the round rod is movably arranged in the round hole in a penetrating way;
the two horizontal main ropes are in sliding connection with the rear end of the aircraft model body;
the traction block is specifically an I-beam; the upper side and the lower side of the left end of the I-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 motors 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 passes through the pulley cavity of one third fixed pulley and is wound on the rotating shaft of the motor, then passes through the pulley cavities of the other two third fixed pulleys, then passes through the pulley cavity of the fourth fixed pulley, and finally is fixed on the pulley body of the left lower pulley 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 part associated with the right back rope are arranged corresponding to the left end of the I-beam;
also 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 provided with an opening; 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 chute; a slide bar matched with the chute is arranged on the longer part of the L-shaped plate; the sliding groove is embedded and arranged on the sliding strip, so that elastic sliding connection is formed; the left rear rope respectively passes through pulley cavities of two hourglass type rollers before and after being wound to a rotor of one motor; the right rear rope respectively passes through pulley cavities of the other two hourglass type rollers before and after being wound to a rotor of the other motor, so that closed loop is completed;
the limiting ropes are 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; the rope bodies of the two horizontal V ropes are respectively provided with a second movable pulley; pulley cavities of the two second movable pulleys are respectively sleeved on rope bodies of the two horizontal V ropes; the shells of the two second movable pulleys are fixedly connected with the front ends of the two horizontal main ropes respectively, so that sliding connection is realized;
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.
2. The rope support system for an all-machine flutter wind tunnel test of claim 1, wherein said limit rope is specifically configured as a vertical V-rope; tripod is movably arranged at the front ends of the two horizontal main ropes; the two bottom corners of the rear end of the tripod are respectively transversely provided with a first fixed pulley; the pulley bodies of the two first fixed pulleys are fixedly connected with the front ends of the two horizontal main ropes, so that a hinge is formed; 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 rope is arranged in a pulley cavity of the first movable pulley in a penetrating way, so that sliding connection is formed;
the vertical V rope adopts a configuration mode of closed loop connection, and is specifically as follows: the upper wall and the lower wall of the wind tunnel test section are respectively provided with two longitudinal strip-shaped holes; the two strip-shaped holes are fixedly provided with a plurality of second fixed pulleys on the interval path of the outer wall of the wind tunnel test section; the vertical V rope starts from the pulley cavity of the first movable pulley, sequentially passes through one of the strip-shaped holes, the second fixed pulleys and the other strip-shaped hole, and then winds back to the pulley cavity of the first movable pulley to be in closed-loop butt joint.
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| CN115655635B (en) * | 2022-12-14 | 2023-03-07 | 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 |
| CN117433740B (en) * | 2023-12-20 | 2024-03-15 | 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 |
| CN117740312B (en) * | 2024-02-21 | 2024-05-07 | 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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| CN206450396U (en) * | 2017-02-06 | 2017-08-29 | 中国航天空气动力技术研究院 | A kind of aircraft haulage gear for wind tunnel test |
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| JP3842725B2 (en) * | 2002-12-19 | 2006-11-08 | 財団法人鉄道総合技術研究所 | Wind tunnel testing equipment |
| JP3809525B2 (en) * | 2003-02-10 | 2006-08-16 | 防衛庁技術研究本部長 | Dynamic wind tunnel test equipment |
| CN100589859C (en) * | 2005-10-15 | 2010-02-17 | 陈文才 | Automatic protection device used for climbing height training |
| CN202793734U (en) * | 2012-05-11 | 2013-03-13 | 中国航空工业集团公司西安飞机设计研究所 | Novel system for hanging whole low-speed flutter plane model for wind tunnel test |
| CN105910792A (en) * | 2016-05-31 | 2016-08-31 | 中国航空工业集团公司西安飞机设计研究所 | Airplane wind tunnel test model installation device |
| CN109163055B (en) * | 2018-11-12 | 2024-01-19 | 苏州东菱振动试验仪器有限公司 | Rope tightness adjusting component and application thereof |
| CN109765027B (en) * | 2019-03-06 | 2023-07-21 | 哈尔滨工业大学 | Quadrilateral mechanism type large attack angle supporting system |
| CN110514394A (en) * | 2019-09-18 | 2019-11-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Model in wind tunnel support device and system |
| CN113092053B (en) * | 2021-04-15 | 2022-09-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Rope hangs full quick-witted experimental strutting arrangement that shimmys |
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