CN114923657B - Vertical rod rope supporting system for full-aircraft flutter wind tunnel test - Google Patents
Vertical rod rope supporting system for full-aircraft flutter wind tunnel test Download PDFInfo
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- CN114923657B CN114923657B CN202210856838.5A CN202210856838A CN114923657B CN 114923657 B CN114923657 B CN 114923657B CN 202210856838 A CN202210856838 A CN 202210856838A CN 114923657 B CN114923657 B CN 114923657B
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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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- 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 vertical rod 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 and an aircraft model, and further comprises: a drop rod; the sliding cylinder is sleeved outside the vertical rod in a sliding manner; the bases of the two turntables are respectively arranged on two sides of the sliding cylinder; the middle part of the airplane model is provided with a through hole; the rotating ends of the two rotating discs are respectively and fixedly connected to the two sides of the inner wall of the through hole. The airplane model sinking and floating freedom is realized by the sliding of the sliding barrel on the vertical rod and the cooperation of the two turntables, the balancing weight, the sinking and floating traction system and the sinking and floating spring system; the real-time braking of the sinking and floating displacement of the airplane model is realized through the first motor and the clutch braking system; the aircraft model can be subjected to pitching attitude adjustment through the two pitching traction systems of the head and the tail of the model, so that the attitude adjustment precision and efficiency of the aircraft model are high, and the accuracy of a flutter test result is improved.
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 vertical rod rope supporting 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 flutter critical speed is greatly reduced due to the nonlinearity of aerodynamic force, the structural vibration is rapidly increased, the structure is easily damaged, the flight safety is threatened, and the flight envelope is restricted. Accurate acquisition of the transonic flutter boundary is a key fundamental problem that must be faced by aircraft design.
Along 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. The freedom degrees in the ups and downs and the pitching directions are used as main concern factors of rigid body motion in the research on longitudinal dynamic characteristics such as flutter of the freedom degrees of an aircraft model body, gust alleviation tests and the like, and a supporting device capable of providing the freedom degrees in the ups and downs and the pitching degrees is required to be provided when the tests are carried out. 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.
The existing body freedom flutter test device is complex in structure, weak in pneumatic load bearing capacity and easy to damage, the aircraft model is greatly restrained when being subjected to pitching attitude adjustment, the freedom degree is small, and the attitude adjustment precision and efficiency of the aircraft model are low, so that the flutter test result is not accurate.
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; in order to achieve these objects and advantages according to the present invention, there is provided a vertical rod rope support system for a full-aircraft flutter wind tunnel test, comprising a wind tunnel test section and an aircraft model arranged in the wind tunnel test section, characterized by further comprising:
two ends of the vertical rod are respectively and fixedly connected with the upper wall and the lower wall of the wind tunnel test section;
the sliding cylinder is sleeved outside the vertical rod in a sliding manner;
the bases of the two turntables are respectively arranged on two sides of the sliding cylinder; the middle part of the airplane model is provided with a through hole; the rotating ends of the two rotating discs are respectively and fixedly connected to the two sides of the inner wall of the through hole.
Wherein, preferably, the device also comprises a sinking and floating traction system; the ups and downs traction system includes:
the two first fixed pulleys are respectively positioned at the upper ends of the two sides of the airplane model; one first fixed pulley is fixedly arranged on the upper wall of the wind tunnel test section; the other first fixed pulley is fixedly arranged on the edge of the upper end of the right wall of the wind tunnel test section; a first wire guide port is formed in the upper wall of the wind tunnel test section;
the two second fixed pulleys are respectively positioned at the lower ends of the two sides of the airplane model; one second fixed pulley is fixedly arranged on the lower wall of the wind tunnel test section; the other second fixed pulley is fixedly arranged on the edge of the lower end of the right wall of the wind tunnel test section; a second wire guide port is formed in the edge of the lower end of the right wall of the wind tunnel test section;
the first motor is arranged on the outer side of the upper wall of the wind tunnel test section; the counterweight block is suspended on the outer side of the right wall of the wind tunnel test section and is matched with the weight of the airplane model;
one end of the ascending and descending traction rope is fixedly connected with the upper end of the sliding cylinder; the other end of the upper lifting traction rope penetrates through the first wire guide opening, is wound and connected to penetrate through one of the first fixed pulleys, is wound and connected to penetrate through a rotating shaft of the first motor, is wound and connected to penetrate through the other first fixed pulley, and is fixedly connected to the upper end of the balancing weight;
one end of the lower lifting traction rope is fixedly connected with the lower end of the sliding cylinder; and the other end of the lower lifting traction rope penetrates through one of the second fixed pulleys in a winding way, then penetrates through the second wire guide port, then penetrates through the other second fixed pulley in a winding way, and finally is fixedly connected to the lower end of the balancing weight.
Wherein, preferably, the sinking and floating traction system also comprises a sinking and floating spring system; the ups and downs spring system includes:
the two L-shaped plates are respectively and fixedly arranged on the outer side of the upper wall of the wind tunnel test section;
the two concave boxes are respectively and elastically arranged at the longer parts of the two L-shaped plates in a sliding manner; an hourglass type roller is arranged in each 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 first spring, so that elastic connection is realized; 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 and the sliding strip are matched and embedded, so that sliding connection is realized;
the upper lifting traction rope is wound and connected through one hourglass-shaped roller before being wound and connected through a rotor of the first motor; after the upper lifting traction rope is wound and connected through the rotor of the first motor, the upper lifting traction rope is wound and connected through the other hourglass-shaped roller, and then the upper lifting traction rope is in butt joint with a subsequent component.
Preferably, the sinking and floating traction system further comprises a clutch braking system; the clutch brake system includes:
the working ends of the two clutch brakes are respectively and correspondingly arranged at the outer sides of the two concave boxes, so that the function of intermittently locking the two concave boxes is realized.
Wherein, preferably, also comprises a head pitching traction system; the head pitch traction system comprises:
the two third fixed pulleys are fixedly arranged on the upper wall of the wind tunnel test section and are positioned in front of the airplane model; the rear end of one third fixed pulley is connected to the upper wall of the wind tunnel test section through a spring, so that elastic connection is realized;
the second motor is fixedly arranged on the upper wall of the wind tunnel test section;
one end of the upper front rope is fixedly arranged on the upper side of the head of the airplane model; the other end of the upper front rope is sequentially wound and connected to pass through the two third fixed pulleys and is finally wound and connected to be fixed on a rotating shaft of the second motor;
a lower front rope, which is in a corresponding mirror image configuration with respect to the upper front rope on the underside of the head of the model airplane and contains all the components associated with the upper front rope.
Wherein, preferably, the system also comprises a tail pitching traction system; the tail pitch traction system comprises:
the three fifth fixed pulleys are respectively fixedly arranged on the inner side and the outer side of the upper wall of the wind tunnel test section and are positioned behind the airplane model;
the sixth fixed pulleys are fixedly arranged on the lower wall edge line of the wind tunnel test section and are positioned behind the airplane model;
the third motor is fixedly arranged on the outer side of the upper wall of the wind tunnel test section and is positioned behind the airplane model;
one end of the left rear rope is fixedly connected to the upper end of the left side of the tail part of the airplane model; the other end of the left rear rope sequentially penetrates through two fifth fixed pulleys, then penetrates through a rotating shaft of a third motor, penetrates through the other fifth fixed pulley, penetrates through one sixth fixed pulley, and is finally fixed at the lower end of the left side of the tail of the airplane model, so that the closed loop of the whole rope body of the left rear rope is completed;
a right rear rope in a substantially corresponding mirror image configuration to the left rear rope on the right side of the tail of the model aircraft and containing all left rear rope associated components.
Wherein, preferably, the vertical rod is a round rod; the sliding cylinder and the vertical rod are coaxially and movably sleeved.
Wherein, preferably, a rope tension adjusting system is further included in the tail pitching traction system; the rope tension adjustment system comprises:
the two seventh fixed pulleys are respectively fixedly arranged on the outer side of the upper wall of the wind tunnel test section and are positioned behind the airplane model; the rear ends of the two seventh fixed pulleys are connected to the outer side of the upper wall of the wind tunnel test section through a spring, so that elastic connection is formed;
the left rear rope is wound and penetrated on one seventh fixed pulley before being wound and penetrated on a rotating shaft of a third motor; and the left rear rope is firstly wound and penetrated on another seventh fixed pulley after being wound and penetrated to the rotating shaft of the third motor, and then is butted with a subsequent component.
The invention at least comprises the following beneficial effects: firstly, the sliding barrel slides up and down on the vertical rod to provide floating and sinking movement capacity for the airplane model, meanwhile, the airplane model can rotate by taking the middle parts of the two turntables as axes through the configuration of the two turntables, and then the head or the tail of the airplane model is pulled through a subsequent external traction device, so that the pitching and swinging posture adjustment of the airplane model can be realized, the operation and the control are convenient, and the support is stable; the device is simple in structure, strong in borne pneumatic load capacity, not easy to damage, large in constraint during pitching attitude adjustment of the aircraft model, large in degree of freedom release, high in attitude adjustment precision and efficiency of the aircraft model, and capable of improving accuracy of a flutter test result.
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 block diagram of a basic structure of the present invention fitted with a head pitch traction system;
FIG. 2 is a block diagram of the basic mechanism of the present invention fitted with a tail pitch traction system;
FIG. 3 is a view showing a structure of a connection between the model airplane and a boom according to the present invention;
FIG. 4 is a detailed structural view of the turntable of the present invention;
fig. 5 is a detailed structural view of the sinking and floating spring system of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying 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 to 5 show a vertical rod 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 10 arranged in the wind tunnel test section 1, and is characterized by further comprising:
two ends of the vertical rod 2 are respectively and fixedly connected with the upper wall and the lower wall of the wind tunnel test section 1;
the slide cylinder 3 is sleeved outside the vertical rod 2 in a sliding manner;
two turntables 4, the bases of which are respectively arranged at two sides of the sliding cylinder 3; the middle part of the airplane model 10 is provided with a through hole 100; the rotating ends of the two rotating discs 4 are respectively fixedly connected to the two sides of the inner wall of the through hole 100.
The working principle is as follows:
in the design, the airplane model 10 is flexibly supported in the wind tunnel test section 1 through the whole vertical rod rope supporting system, a flutter wind tunnel test is carried out under the action of airflow, the flutter frequency of the airplane model 10 is obtained in real time through a corresponding detection instrument, and the airplane model 10 is ensured to be not unstable in a safe flutter boundary by carrying out ceaseless attitude adjustment on the airplane model 10.
Firstly, the sliding barrel 3 slides up and down on the vertical rod 2 to provide floating and sinking movement capability for the airplane model 10, meanwhile, the airplane model 10 can rotate by taking the middle parts of the two turntables 4 as axes through the configuration of the two turntables 4, and then the head or the tail of the airplane model 10 is pulled through a subsequent external traction device, so that the pitching and swinging posture adjustment of the airplane model 10 can be realized, the operation and the control are convenient, and the support is stable; the device is simple in structure, strong in borne pneumatic load capacity, not easy to damage, small in constraint when pitching attitude adjustment is carried out on the airplane model 10, large in degree of freedom release, high in attitude adjustment precision and efficiency of the airplane model 10, and capable of improving accuracy of a flutter test result.
In the technical scheme, the device also comprises a sinking and floating traction system; the ups and downs traction system includes:
two first fixed pulleys 11 respectively positioned at the upper ends of both sides of the airplane model 10; one first fixed pulley 11 is fixedly arranged on the upper wall of the wind tunnel test section 1; the other first fixed pulley 11 is fixedly arranged on the edge of the upper end of the right wall of the wind tunnel test section 1; a first wire guide port is formed in the upper wall of the wind tunnel test section 1;
two second fixed pulleys 12 respectively located at the lower ends of both sides of the airplane model 10; one of the second fixed pulleys 12 is fixedly arranged on the lower wall of the wind tunnel test section 1; the other second fixed pulley 12 is fixedly arranged on the edge of the lower end of the right wall of the wind tunnel test section 1; a second wire guide port is formed in the edge of the lower end of the right wall of the wind tunnel test section 1;
the first motor 13 is arranged on the outer side of the upper wall of the wind tunnel test section 1;
the counterweight block 14 is hung on the outer side of the right wall of the wind tunnel test section 1 and is matched with the weight of the airplane model 10;
an upper lifting traction rope 15, one end of which is fixedly connected with the upper end of the sliding cylinder 3; the other end of the upper lifting traction rope 15 penetrates through the first wire guide opening, then is wound and connected to penetrate through one of the first fixed pulleys 11, then is wound and connected to penetrate through a rotating shaft of the first motor 13, then is wound and connected to penetrate through the other first fixed pulley 11, and finally is fixedly connected to the upper end of the balancing weight 14;
a lower lifting traction rope 16, one end of which is fixedly connected with the lower end of the sliding cylinder 3; the other end of the lower lifting traction rope 16 is wound and connected to penetrate one of the second fixed pulleys 12, then penetrates through the second wire guide port, is wound and connected to penetrate the other second fixed pulley 12, and finally is fixedly connected to the lower end of the counterweight 14.
The working principle is as follows: in the design, the floating and sinking displacement adjustment of the airplane model 10 can be realized by controlling the retraction and release of the upper lifting traction rope 15 and the lower lifting traction rope 16, and the airplane model is convenient to operate and control and has strong flexibility.
(1) When the first motor 13 rotates positively, one end of the lifting traction rope 15 is wound and tensioned, the whole sliding barrel 3 is pulled to move upwards, and the other end of the lifting traction rope 15 is loosened, so that the whole balancing weight 14 is driven to move downwards; one end of the lower lifting traction rope 16 moves upwards along with the sliding barrel 3, the other end of the lower lifting traction rope 16 descends along with the balancing weight 14, and the whole device keeps a balanced stable state continuously, so that the function of upward displacement of the airplane model 10 is realized;
(2) When the first motor 13 rotates reversely, one end of the lifting traction rope 15 is extended and loosened, so that the whole sliding drum 3 moves downwards, and the other end of the lifting traction rope 15 is wound and tightened, so that the counterweight block 14 is driven to lift; one end of the lower lifting traction rope 16 moves downwards along with the sliding barrel 3, the other end of the lower lifting traction rope 16 rises along with the counterweight block 14, and the whole device continues to keep a balanced stable state, so that the function of downward displacement of the airplane model 10 is realized.
In the above technical solution, the sinking and floating traction system further comprises a sinking and floating spring system 20; the ups and downs spring system 20 includes:
the two L-shaped plates 21 are respectively and fixedly arranged on the outer side of the upper wall of the wind tunnel test section 1;
two concave boxes 22 respectively arranged at the longer parts of the two L-shaped plates 21 in an elastic sliding manner; an hourglass-type roller 23 is arranged inside each concave box 22; the front end of the concave box 22 is opened; the rear end of the concave box 22 is connected to the shorter part of the L-shaped plate 21 through a first spring 24, so that elastic connection is realized; the bottom of the concave box 22 is provided with a sliding groove 25; a slide bar 26 matched with the sliding groove 25 is arranged on the longer part of the L-shaped plate 21; the sliding groove 25 is matched and embedded with the sliding strip 26, so that sliding connection is realized;
the hoisting and lowering traction rope 15 is wound and passed through one of the hourglass-shaped rollers 23 before being wound and passed through the rotor of the first motor 13; after being wound through the rotor of the first motor 13, the hoisting and lowering traction rope 15 is wound through another hourglass-shaped roller 23 and then is butted with a subsequent component.
The working principle is as follows: in this kind of design, can guarantee that the structure is more stable, go up and descend haulage rope 15 and carry out elastic restriction by two first springs 24, elasticity through two first springs 24 provides to let aircraft model 10 can possess the ups and downs displacement degree of freedom under the pneumatic load effect, satisfy aircraft model's soft stay requirement.
In the above technical solution, the sinking and floating traction system further comprises a clutch braking system 30; the clutch brake system 30 includes:
the working ends of the two clutch brakes 31 are respectively and correspondingly arranged at the outer sides of the two concave boxes 22, so that the function of intermittently locking the two concave boxes 22 is realized.
The working principle is as follows: in the design, the two concave boxes 22 are locked by encircling and locking through controlling the clutch brake 31, so that the two first springs 24 are disabled, the first motor 13 is started again at the moment, the ascending and descending traction rope 15 and the descending and ascending traction rope 16 are used for carrying out up-and-down dragging adjustment on the airplane model 10, synchronous displacement adjustment is achieved, the position is more accurate, the situation that the first spring 24 is not stable enough when the airplane model 10 is subjected to ascending and descending adjustment due to elasticity is avoided, and real-time braking of the ascending and descending displacement of the airplane model 10 is realized by matching the first motor 13 with the clutch brake 31; the significance of this is that when the aircraft model 10 swings to a dangerous position (i.e. close to the inner wall of the wind tunnel test section 1) or the first spring 24 is damaged, the clutch brake 31 can be controlled in time to lock the two concave boxes 22 in a surrounding manner, then the aircraft model 10 is pulled back to a standard position (a safe position) again in time through the rotation of the first motor 13, relevant problems are eliminated, the clutch brake 31 is released again, the aircraft model 10 starts to swing in a sinking and floating manner again at the standard position (the safe position), and the test is continued.
In the above technical solution, the system further comprises a head pitch traction system 40; the head pitch traction system 40 comprises:
the two third fixed pulleys 41 are fixedly arranged on the upper wall of the wind tunnel test section 1 and are positioned in front of the airplane model 10; the rear end of one of the third fixed pulleys 41 is connected to the upper wall of the wind tunnel test section 1 through a spring, so that elastic connection is realized;
the second motor 43 is fixedly arranged on the upper wall of the wind tunnel test section 1;
an upper front rope 44, one end of which is fixedly arranged on the upper side of the head of the airplane model 10; the other end of the upper front rope 44 is sequentially wound and connected through two third fixed pulleys 41, and finally wound and connected on a rotating shaft of a second motor 43;
a lower front cord 45, which is in a substantially corresponding mirror image configuration with respect to said upper front cord 44 on the underside of the head of the airplane model 10 and contains all the associated components of the upper front cord 44.
The working principle is as follows: in the design, the pitching attitude of the airplane model 10 can be adjusted by controlling the retraction and release of the upper front rope 44 and the lower front rope 45 of the airplane model 10, and the airplane model is convenient to operate and control and high in flexibility.
(1) When one of the second motors 43 rotates forwards and the other second motor 43 rotates backwards, the upper front rope 44 is wound and tensioned, and the lower front rope 45 is extended and loosened, so that the head of the airplane model 10 is pulled upwards, and the upper two turnplates 4 rotate clockwise, so that the whole airplane model 10 is adjusted to face upwards;
(2) When one of the second motors 43 rotates reversely and the other second motor 43 rotates forwardly, the upper front rope 44 is extended and loosened, and the lower front rope 45 is wound and tightened, so that the head of the airplane model 10 is pulled downwards, and the upper two turnplates 4 rotate anticlockwise, so that the airplane model 10 is integrally adjusted for bending down.
In the above technical solution, a tail pitch traction system 50 is further included; the tail pitch traction system 50 includes:
the three fifth fixed pulleys 51 are respectively fixedly arranged on the inner side and the outer side of the upper wall of the wind tunnel test section 1 and are positioned behind the airplane model 10;
the sixth fixed pulleys 52 are fixedly arranged on the lower wall edge line of the wind tunnel test section 1 and are positioned behind the airplane model 10;
the third motor 53 is fixedly arranged on the outer side of the upper wall of the wind tunnel test section 1 and is positioned behind the airplane model 10;
a left rear rope 54 having one end fixedly connected to the left upper end of the tail of the airplane model 10; the other end of the left rear rope passes through two fifth fixed pulleys 51 in a winding manner, then passes through a rotating shaft of a third motor 53 in a winding manner, then passes through the other fifth fixed pulley 51 in a winding manner, then passes through one sixth fixed pulley 52 in a winding manner, and finally is fixed at the lower end of the left side of the tail part of the airplane model 10, so that the closed loop of the whole rope body of the left rear rope 54 is completed;
a right rear rope 55, which is in a substantially corresponding mirror image configuration with respect to the left rear rope 54 on the right side of the tail of the airplane model 10, and which contains all the left rear rope 54 associated components.
The working principle is as follows: in the design, the pitching attitude of the airplane model 10 can be adjusted by controlling the retraction of the left rear rope 54 and the right rear rope 55 at the tail part of the airplane model 10, and the airplane model is convenient to operate and control and has strong flexibility.
(1) When the two third motors 53 rotate forwards simultaneously, the left rear rope 54 at the upper end of the left side of the tail of the airplane model 10 is tightened, the left rear rope 54 at the lower end of the left side of the tail of the airplane model 10 is loosened, and the right rear rope 55 is subjected to the same steps, so that the tail of the whole airplane model 10 is subjected to ascending motion, the head part of the airplane model 10 is subjected to head lowering motion, and the motion adjustment of the airplane body for bending down is realized;
(2) When the two third motors 53 rotate reversely at the same time, the left rear rope 54 at the upper end of the left side of the tail portion of the airplane model 10 is tightened, the left rear rope 54 at the lower end of the left side of the tail portion of the airplane model 10 is loosened, and the right rear rope 55 is subjected to the same steps, so that the tail portion of the whole airplane model 10 is subjected to descending motion, the head portion of the airplane model 10 is subjected to head raising motion, and the motion adjustment of the machine body in the raising motion is realized.
In summary, one of the further advantages is that the aerodynamic disturbance to the aircraft model 10 is smaller, the constraint is smaller when the pitching attitude adjustment is performed, and the degree of freedom release is larger; meanwhile, the pitching attitude of the airplane model 10 can be directly adjusted through the homodromous linkage of the left rear rope 54 and the right rear rope 55, so that the attitude adjustment precision and efficiency of the airplane model 10 are higher;
the second advantage is that the tail of the airplane model is adjusted by using the left rear rope 54 and the right rear rope 55 to adjust the attitude of the airplane model 10, so that the control surface of the airplane model 10 body is not needed to control, the limitation of the size of the wind tunnel and the size of the airplane model 10 can be effectively removed, and the dynamic characteristics of the airplane model 10 can be better simulated.
In the above technical solution, the hanging rod 2 is a round rod; the sliding cylinder 3 and the vertical rod 2 are coaxially and movably sleeved.
The working principle is as follows: in this design, the slide 3 is allowed to rotate circumferentially around the vertical rod 2, so that the yaw attitude adjustment (i.e., left/right yaw) of the airplane model 10 can be realized by the same motion principle through the same directional linkage of the left rear rope 54 and the right rear rope 55 (i.e., one normal rotation, one reverse rotation, and one normal rotation of the two third motors 53);
in the above technical solution, the tail pitch traction system 50 further includes a rope tension adjusting system 60; the rope tension adjusting system 60 comprises:
the two seventh fixed pulleys 61 are respectively fixedly arranged on the outer side of the upper wall of the wind tunnel test section 1 and behind the airplane model 10; the rear ends of the two seventh fixed pulleys 61 are connected to the outer side of the upper wall of the wind tunnel test section 1 through a spring, so that elastic connection is formed;
the left rear rope 54 is wound and threaded on one of the seventh fixed pulleys 61 before being wound and threaded on the rotating shaft of the third motor 53; the left rear rope 54 is wound around the rotation shaft of the third motor 53, and then is wound around another seventh fixed pulley 61, and then is abutted with the subsequent components.
The working principle is as follows: in the design of an actual rope suspension system, the front and rear rigidity of the whole system must be reasonably distributed, and the requirement that the vibration frequency of the support system is less than 1/3-1/5 of the lowest-order elasticity first-order modal frequency of a typical flutter model structure is met, so that the stability of the whole support system can be ensured.
In this design, the further advantage is that we only need to replace the spring 62 with different stiffness coefficients at the rear end of the fourth fixed pulley 61, so as to be able to completely and freely adjust and control the vibration frequency of the whole supporting system 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 (4)
1. The utility model provides a hang down rod rope braced system for full quick-witted 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:
two ends of the vertical rod are respectively and fixedly connected with the upper wall and the lower wall of the wind tunnel test section;
the sliding cylinder is sleeved outside the vertical rod in a sliding manner;
the bases of the two turntables are respectively arranged on two sides of the sliding cylinder; the middle part of the airplane model is provided with a through hole; the rotating ends of the two rotating discs are respectively and fixedly connected to the two sides of the inner wall of the through hole;
still include ups and downs traction system, include:
the two first fixed pulleys are respectively positioned at the upper ends of the two sides of the airplane model; one first fixed pulley is fixedly arranged on the upper wall of the wind tunnel test section; the other first fixed pulley is fixedly arranged on the edge of the upper end of the right wall of the wind tunnel test section; a first wire guide port is formed in the upper wall of the wind tunnel test section;
the two second fixed pulleys are respectively positioned at the lower ends of the two sides of the airplane model; one second fixed pulley is fixedly arranged on the lower wall of the wind tunnel test section; the other second fixed pulley is fixedly arranged on the edge of the lower end of the right wall of the wind tunnel test section; a second wire guide port is formed in the edge of the lower end of the right wall of the wind tunnel test section;
the first motor is arranged on the outer side of the upper wall of the wind tunnel test section;
the counterweight block is suspended on the outer side of the right wall of the wind tunnel test section and is matched with the weight of the airplane model;
one end of the lifting traction rope is fixedly connected with the upper end of the sliding cylinder; the other end of the upper lifting traction rope penetrates through the first wire guide opening, then is wound and connected to penetrate through one of the first fixed pulleys, then is wound and connected to penetrate through a rotating shaft of the first motor, then is wound and connected to penetrate through the other first fixed pulley, and finally is fixedly connected to the upper end of the balancing weight;
one end of the lower lifting traction rope is fixedly connected with the lower end of the sliding cylinder; the other end of the lower lifting traction rope is wound and connected to penetrate through one of the second fixed pulleys, penetrates through the second wire guide port, is wound and connected to penetrate through the other second fixed pulley, and is fixedly connected to the lower end of the balancing weight;
the sinking and floating traction system also comprises a sinking and floating spring system, which comprises:
the two L-shaped plates are respectively and fixedly arranged on the outer side of the upper wall of the wind tunnel test section;
the two concave boxes are respectively and elastically arranged at the longer parts of the two L-shaped plates in a sliding manner; an hourglass-type roller is arranged in each 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 first spring, so that elastic connection is realized; 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 and the sliding strip are matched and embedded, so that sliding connection is realized;
the upper lifting traction rope is wound and connected through one hourglass-shaped roller before being wound and connected through a rotor of the first motor; after the upper lifting traction rope is wound and connected with a rotor of the first motor, the upper lifting traction rope is wound and connected with another hourglass-type roller in a penetrating mode and then is in butt joint with a subsequent component;
also includes a head pitch traction system; the head pitch traction system comprises:
the two third fixed pulleys are fixedly arranged on the upper wall of the wind tunnel test section and are positioned in front of the airplane model; the rear end of one third fixed pulley is connected to the upper wall of the wind tunnel test section through a spring, so that elastic connection is realized;
the second motor is fixedly arranged on the upper wall of the wind tunnel test section;
one end of the upper front rope is fixedly arranged on the upper side of the head of the airplane model; the other end of the upper front rope is sequentially wound and connected through two third fixed pulleys and finally wound and connected and fixed on a rotating shaft of a second motor;
a lower front rope, which is configured in a mirror image with respect to the upper front rope in a corresponding manner on the underside of the head of the aircraft model and contains all the components associated with the upper front rope;
also included is a tail pitch traction system comprising:
the three fifth fixed pulleys are respectively fixedly arranged on the inner side and the outer side of the upper wall of the wind tunnel test section and are positioned behind the airplane model;
the sixth fixed pulleys are fixedly arranged on the lower wall edge line of the wind tunnel test section and are positioned behind the airplane model;
the third motor is fixedly arranged on the outer side of the upper wall of the wind tunnel test section and is positioned behind the airplane model;
one end of the left rear rope is fixedly connected to the upper end of the left side of the tail part of the airplane model; the other end of the left rear rope sequentially penetrates through two fifth fixed pulleys, then penetrates through a rotating shaft of a third motor, penetrates through the other fifth fixed pulley, penetrates through one sixth fixed pulley, and is finally fixed at the lower end of the left side of the tail of the airplane model, so that the closed loop of the whole rope body of the left rear rope is completed;
a right rear rope in a substantially corresponding mirror image configuration to the left rear rope on the right side of the tail of the model aircraft and containing all left rear rope associated components.
2. The dip rod rope supporting system for the full-aircraft flutter wind tunnel test according to claim 1, wherein the sinking and floating traction system further comprises a clutch braking system; the clutch brake system includes:
the working ends of the two clutch brakes are respectively and correspondingly arranged at the outer sides of the two concave boxes, so that the function of intermittently locking the two concave boxes is realized.
3. The drop rod rope support system for the full-aircraft flutter wind tunnel test according to claim 1, wherein the drop rod is a round rod; the sliding cylinder and the vertical rod are coaxially and movably sleeved.
4. The dip rod rope supporting system for the full-aircraft flutter wind tunnel test according to claim 1, wherein the tail pitching traction system further comprises a rope tension adjusting system; the rope tension adjustment system comprises:
the two seventh fixed pulleys are respectively fixedly arranged on the outer side of the upper wall of the wind tunnel test section and are positioned behind the airplane model; the rear ends of the two seventh fixed pulleys are connected to the outer side of the upper wall of the wind tunnel test section through a spring, so that elastic connection is formed;
the left rear rope is wound and penetrated on one seventh fixed pulley before being wound and penetrated on a rotating shaft of a third motor; and the left rear rope is firstly wound and penetrated on another seventh fixed pulley after being wound and penetrated to the rotating shaft of the third motor, and then is butted with a subsequent component.
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| CN202210856838.5A CN114923657B (en) | 2022-07-21 | 2022-07-21 | Vertical rod rope supporting system for full-aircraft flutter wind tunnel test |
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| CN202210856838.5A CN114923657B (en) | 2022-07-21 | 2022-07-21 | Vertical rod rope supporting system for full-aircraft flutter wind tunnel test |
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| CN115326344B (en) * | 2022-10-14 | 2022-12-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Gravity-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
| 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 |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11322284A (en) * | 1998-05-19 | 1999-11-24 | Inoue Kinzoku Kk | Domestic elevating and lowering equipment |
| JP2003279439A (en) * | 2003-02-10 | 2003-10-02 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel testing device and method |
| JP2004290327A (en) * | 2003-03-26 | 2004-10-21 | Kasatani:Kk | Model helicopter, and operation training device for the same |
| JP2012170776A (en) * | 2011-02-24 | 2012-09-10 | Hirobo Ltd | Maneuvering training device of remote controlled helicopter |
| CN103698101A (en) * | 2013-12-15 | 2014-04-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | High-load and high-precision pneumatic force measurement device and measurement method |
| CN104913899A (en) * | 2015-06-23 | 2015-09-16 | 中国航空工业集团公司西安飞机设计研究所 | Supporting and limiting device for wind tunnel and wind tunnel test system provided with same |
| CN110686857A (en) * | 2019-10-30 | 2020-01-14 | 厦门大学 | Full-aircraft flutter wind tunnel test model suspension system and state adjustment method thereof |
| CN113092053A (en) * | 2021-04-15 | 2021-07-09 | 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 |
| CN114563156A (en) * | 2022-03-04 | 2022-05-31 | 北方工业大学 | Four-cable supporting system for full-mode flutter wind tunnel test |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6619127B2 (en) * | 2002-01-08 | 2003-09-16 | The Boeing Company | Structural test soft support system |
| US8839675B2 (en) * | 2012-04-17 | 2014-09-23 | The Boeing Company | System and method for ground vibration testing and weight and balance measurement |
| CN205300891U (en) * | 2015-12-11 | 2016-06-08 | 中国特种飞行器研究所 | Unpowered model pond test device of full machine of anti unrestrained ability of surface of water aircraft |
| US10837864B2 (en) * | 2018-03-05 | 2020-11-17 | Dalian University Of Technology | Large-amplitude vertical-torsional coupled free vibration setup for wind tunnel test |
| CN111929023B (en) * | 2020-08-11 | 2021-08-06 | 日照坤仑智能科技有限公司 | Aircraft model driving system in wind tunnel and performance measuring method |
| CN113358321B (en) * | 2021-08-11 | 2021-11-19 | 中国飞机强度研究所 | Body degree of freedom flutter wind tunnel test device |
| CN114310734B (en) * | 2022-03-14 | 2022-10-28 | 中国空气动力研究与发展中心低速空气动力研究所 | Airplane model sinking and floating supporting device and four-degree-of-freedom supporting device |
-
2022
- 2022-07-21 CN CN202210856838.5A patent/CN114923657B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11322284A (en) * | 1998-05-19 | 1999-11-24 | Inoue Kinzoku Kk | Domestic elevating and lowering equipment |
| JP2003279439A (en) * | 2003-02-10 | 2003-10-02 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel testing device and method |
| JP2004290327A (en) * | 2003-03-26 | 2004-10-21 | Kasatani:Kk | Model helicopter, and operation training device for the same |
| JP2012170776A (en) * | 2011-02-24 | 2012-09-10 | Hirobo Ltd | Maneuvering training device of remote controlled helicopter |
| CN103698101A (en) * | 2013-12-15 | 2014-04-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | High-load and high-precision pneumatic force measurement device and measurement method |
| CN104913899A (en) * | 2015-06-23 | 2015-09-16 | 中国航空工业集团公司西安飞机设计研究所 | Supporting and limiting device for wind tunnel and wind tunnel test system provided with same |
| CN110686857A (en) * | 2019-10-30 | 2020-01-14 | 厦门大学 | Full-aircraft flutter wind tunnel test model suspension system and state adjustment method thereof |
| CN113092053A (en) * | 2021-04-15 | 2021-07-09 | 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 |
| CN114563156A (en) * | 2022-03-04 | 2022-05-31 | 北方工业大学 | Four-cable supporting system for full-mode flutter wind tunnel test |
Non-Patent Citations (4)
| Title |
|---|
| FD-09风洞单点腹支撑系统研制;张永升 等;《实验流体力学》;20140220;第28卷(第01期);第75-79页 * |
| 一种两自由度全机模型阵风试验支撑装置研制;唐建平 等;《实验流体力学》;20210615;第35卷(第03期);第94-99页 * |
| 全模颤振风洞试验三索悬挂系统多体动力学分析;赵振军 等;《航空学报》;20200403;第41卷(第11期);第277-287页 * |
| 绳牵引并联支撑弹箭模型气动干扰特性分析;卜凡楠 等;《哈尔滨工程大学学报》;20220331;第43卷(第03期);第407-413页 * |
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