CN111307401A - Test device for measuring hinge moment of control surface of axisymmetric ventilation model - Google Patents
Test device for measuring hinge moment of control surface of axisymmetric ventilation model Download PDFInfo
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- CN111307401A CN111307401A CN202010260064.0A CN202010260064A CN111307401A CN 111307401 A CN111307401 A CN 111307401A CN 202010260064 A CN202010260064 A CN 202010260064A CN 111307401 A CN111307401 A CN 111307401A
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- G—PHYSICS
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- 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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- 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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- 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 test device for measuring hinge moment of an axisymmetric ventilation model control surface, which comprises: the axial symmetry ventilation model is characterized in that an air inlet channel of the axial symmetry ventilation model adopts a lower jaw type, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric ventilation model comprises a model forebody and a model afterbody; the bottom of the hinge moment balance is arranged in the model rear body through a balance mounting seat; the hinge moment balance is vertical to the inner flow channel of the model rear body; three non-measuring rudders which are uniformly arranged on the outer wall surface of the model rear body; the measuring rudder is connected with the top of the hinge moment balance, and the measuring rudder and the three non-measuring rudders are uniformly arranged on the outer wall surface of the rear body of the model; the front end of the tail support rod is connected with the end part of the model rear body, and the aerodynamic characteristics of the control surface of the axisymmetric ventilation model can be accurately obtained through the hypersonic wind tunnel test under the condition of effectively ensuring the rigidity of the test device by using the test device, so that a reliable test data basis is provided for the design of an aircraft.
Description
Technical Field
The invention relates to a test device for measuring hinge moment of an axisymmetric ventilation model control surface, belonging to the technical field of wind tunnel tests.
Background
The hinge moment test of the control surface of the model is one of important wind tunnel test items in the development stage of an aircraft, and the purpose is to accurately predict the aerodynamic force of each control surface and the hinge moment relative to a rotating shaft and provide a basis for steering engine selection, aerodynamic shape design and structural design.
When the hinge moment test device is designed, the tested control surface is connected with the model end of the hinge moment balance, the fixed end of the balance is connected with the aircraft model main body, and a gap with a certain width must be reserved between the tested control surface and the model main body to ensure that the balance can generate certain strain, so that the pneumatic force and the moment of the tested control surface can be accurately measured. Due to the existence of the gap, the external air flow inevitably influences the measurement result of the balance through the gap in the test process. Particularly, under the condition of a hypersonic test, the temperature and the pressure of the external air flow are high, and the influence on the measurement result of the balance is very obvious. In order to avoid as far as possible the direct action of external air currents on the balance, it is customary to design the hinge moment balance in the interior of the model body and to install a heat shield between the control surface to be measured and the balance. This is the most commonly used layout of the present hinge moment test device design.
For the hypersonic air suction type aircraft with a lifting body structure, sufficient space can be reserved for the installation of a balance, a heat insulation sleeve and a support rod by changing the expansion angle of the tail spray pipe. Therefore, the above design was used to conduct the relevant experiments. For a hypersonic air-breathing aircraft with an axisymmetric structure, because a tail nozzle of a propulsion system occupies most space at the tail part of the aircraft, if a modification mode which is the same as that of a lifting body is adopted, two contradictory problems are difficult to be considered: (1) the single side of the inner flow channel is greatly contracted inwards, so that a large installation space can be provided for the balance, the size limitation of the balance is small, and meanwhile, the support rod can be designed to be thick and strong, so that the rigidity of the test device is effectively ensured; (2) the insufficient shrinkage of the inner runner can seriously limit the size of the balance and the support rod, so that the installation is inconvenient, the rigidity of the test device is insufficient, and the test risk is greatly increased.
Therefore, the method for designing the control surface hinge moment measurement test device suitable for the axisymmetric ventilation model has great significance for developing the test in the hypersonic wind tunnel in future. At present, no relevant literature reports exist at home and abroad.
Disclosure of Invention
The invention aims to provide a test device for measuring the hinge moment of a control surface of an axisymmetric ventilation model. The device can accurately obtain the aerodynamic characteristics of the control surface of the axisymmetric ventilation model through a hypersonic wind tunnel test under the condition of effectively ensuring the rigidity of the test device, and provides reliable test data basis for aircraft design.
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages described hereinafter.
To achieve these objects and other advantages in accordance with the purpose of the invention, there is provided an axisymmetric ventilating model control surface hinge moment measurement test device, including:
the axial symmetry ventilation model is characterized in that an air inlet channel of the axial symmetry ventilation model adopts a lower jaw type, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric venting model comprises a model forebody and a model afterbody; a leveling platform is arranged on the model rear body;
the bottom of the hinge moment balance is arranged in the model rear body through a balance mounting seat; the hinge moment balance is vertical to an inner flow channel of the model rear body;
three non-measuring rudders which are uniformly arranged on the outer wall surface of the model rear body;
the measuring rudder is connected with the top of the hinge moment balance, and the measuring rudder and the three non-measuring rudders are uniformly arranged on the outer wall surface of the model rear body;
and the front end of the tail support rod is connected with the end part of the model rear body.
Preferably, the inner runner profile at the front end of the model rear body is a circular profile, the inner runner profile at the rear end is a rectangular profile, and the hinge moment balance is located in the rectangular profile.
Preferably, the hinge moment balance comprises a model end, a measuring section and a fixed end which are integrally formed, wherein the model end is a 1:5 standard conical surface, and a key groove and a wedge key groove are arranged on the conical surface; the measuring section is in a four-column beam form; the fixed end is set to be 1:5, standard conical surface; cylindrical surface transition is adopted between the model end and the measuring section as well as between the measuring section and the fixed end; a boss with a chamfer angle is arranged behind the fixed end of the hinge moment balance, and a threaded hole is formed in the center of the boss.
Preferably, the balance mounting base comprises a bottom plate and a rectangular boss which are integrally formed; the center of the rectangular boss is provided with a 1:5 standard conical surface hole; a round hole is formed in the bottom of the 1:5 standard conical surface hole and is positioned on the bottom plate; a rectangular groove I for mounting a non-measuring rudder is arranged on the bottom plate, and a rectangular groove II communicated with the round hole is arranged in the middle of the rectangular groove I; a balance wiring groove I is formed in the side face of the rectangular boss, and a balance wiring groove III communicated with the balance wiring groove I is formed in the rectangular molded surface of the model rear body; one of the three non-measuring rudders is connected in the rectangular groove I, the outer wall surface of the model rear body is provided with a non-measuring rudder rectangular groove for mounting the other two non-measuring rudders, and the non-measuring rudders are mounted in the non-measuring rudder rectangular grooves through screws; the fixed end of the hinge moment balance is provided with a balance fixed end heat insulation sleeve, and the model end of the hinge moment balance is provided with a balance model end heat insulation sleeve; the balance fixed end heat insulation sleeve and the balance model end heat insulation sleeve are both glass fiber reinforced plastic heat insulation sleeves, the inner conical surface of the balance fixed end heat insulation sleeve is matched with the fixed end, and the outer conical surface of the balance fixed end heat insulation sleeve is matched with a 1:5 standard conical hole arranged in the center of the rectangular boss; a U-shaped groove I for balance wiring is formed in the cylindrical surface of the heat insulation sleeve at the fixed end of the balance; the inner conical surface at the upper end of the balance model end heat insulation sleeve is matched with the 1:5 standard conical surface at the model end, and the upper end of the balance model end heat insulation sleeve is provided with a heat insulation sleeve key groove and a heat insulation sleeve wedge key groove which are matched with the key groove and the wedge key groove at the model end; the minimum inner diameter of the lower end of the heat insulation sleeve at the balance model end is larger than the maximum inner diameter of the upper end of the heat insulation sleeve at the balance model end; the lower end of the balance model end heat insulation sleeve is sleeved on the balance fixed end heat insulation sleeve and is not contacted with the outer wall of the balance fixed end heat insulation sleeve; the lower end of the heat insulation sleeve at the balance model end is provided with a U-shaped groove II for balance wiring, and the U-shaped groove I and the U-shaped groove II are oppositely arranged; the connection mode of the fixed end of the hinge moment balance and the balance mounting seat is as follows: rectangular channel II places back font angle piece, sets up the boss of taking the chamfer of hinge moment balance in the centre bore of returning font angle piece to be connected through the screw hole that the center of screw and boss set up, be connected hinge moment balance's stiff end and balance mount pad are taut, the head top of screw is tightly at the surface of returning font angle piece.
Preferably, the mode that the balance mounting base is arranged on the model rear body is as follows: a rectangular groove III is formed in the wall surface of the rear body of the model, and a rectangular hole I is formed in the rectangular groove III; the bottom plate of the balance mounting seat is connected in the rectangular groove III in a matched mode, and the rectangular boss of the balance mounting seat is arranged in the rectangular hole I in a matched mode.
Preferably, balance fairings are arranged outside the balance model end heat insulating sleeve and the balance fixed end heat insulating sleeve of the hinge moment balance, the balance fairings are formed by two plates and integrally form a balance fairing with a hexagonal structure, the front and the back of the balance fairing are wedge-shaped, the planes of the left side and the right side are parallel to the planes of the left side and the right side of the inner flow channel, the front wedge and the right plane are in arc transition, the wedge angle at the front end is 50 degrees, and the wedge angle at the back end is 60 degrees; a fairing round hole for accommodating the hinge moment balance is formed in the balance fairing, and the interfaces of the two plates are selected to be behind the front wedge and in front of the rear wedge and are connected through screws; and a balance wiring groove II is processed between the rear wedge and the circular hole of the fairing.
Preferably, the connection mode of the measuring rudder and the model end of the hinge moment balance is as follows: a rectangular hole II is arranged on the wall surface of the model rear body opposite to the rectangular groove III, a measuring rudder cover plate is connected on the rectangular hole II, the outer side boundary line of the two measuring rudder cover plates is vertical to the measuring rudder shaft, the contact surfaces of the two measuring rudder cover plates are in a shape like the Chinese character 'ji', the two measuring rudder cover plates are positioned and connected by a threaded pin, the upper surface of the measuring rudder cover plate is used as one part of the outer molded surface of the model rear body, the lower surface of the measuring rudder cover plate is used as one part of the molded surface of the inner flow passage, the measuring rudder cover plate is connected with the model rear body by a screw, a measuring rudder cover plate round hole is arranged at the position of the measuring rudder rotating shaft of the measuring rudder cover plate, the diameter of the measuring rudder cover plate round hole is 1mm, processing a cylindrical groove on the inner side of the circular hole of the measuring rudder cover plate, wherein the diameter of the cylindrical groove is larger than that of the measuring rudder mounting cap, and a gap of 2mm is reserved between the lower surface of the circular hole of the rudder cover plate and the upper surface of the measuring rudder mounting cap; the measuring rudder is connected to the measuring rudder mounting cap, and the inner wall of the measuring rudder mounting cap is 1:5 standard conical surface, measure the rudder installation cap cover and establish the upper end at balance model end heat insulating sleeve, just be provided with on the measurement rudder installation cap with the keyway matched with waist type groove of model end, it is 6 installation cap wedge keyway that the wedge angle that still is provided with two the same, opposite direction of size on the measurement rudder installation cap, wherein the installation cap wedge keyway of upper end is as dismantling the keyway of balance and measurement rudder installation cap, and the installation cap wedge keyway of lower extreme cooperates with the wedge keyway of model end in order to lock hinge moment balance.
Preferably, the front end of the tail support rod is a first cylindrical section, the outer surface of the tail support rod is cylindrical, the inner surface of the tail support rod is rectangular, and four rectangular planes are respectively superposed with four planes at the end part of the model rear body; the support rod behind the first cylindrical section is a first conical end, and the outer surface of the support rod is conical; the first conical section is followed by a second cylindrical section; processing a wiring groove and a front wiring hole and a rear wiring hole on the second cylindrical section; the second cylindrical section is followed by a second conical section, a third cylindrical section and a third conical section, respectively.
Preferably, the inner surface of the support rod behind the first cylindrical section is sequentially provided with a drain hole and a wedge-shaped wedge, and the symmetrical plane of the wedge-shaped wedge is superposed with the symmetrical plane of the balance fairing.
The invention at least comprises the following beneficial effects: the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model can accurately obtain the aerodynamic characteristics of the control surface of the axisymmetric ventilation model through a hypersonic wind tunnel test under the condition of effectively ensuring the rigidity of the test device, and provides reliable test data basis for aircraft design.
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.
Description of the drawings:
FIG. 1 is a schematic view of the overall structure of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the invention;
FIG. 2 is a schematic partial structure diagram of a model precursor of an axisymmetric venting model of the present invention;
FIG. 3 is a schematic view of the construction of the back body of the axisymmetric ventilation model of the present invention;
FIG. 4 is a schematic structural diagram of another perspective view of a phantom afterbody of the axisymmetric ventilation phantom of the present invention;
FIG. 5 is a schematic view of a partial structure of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 6 is a partial structural diagram of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 7 is a partial structural diagram of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 8 is a partial structural diagram of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 9 is a partial structural view of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 10 is a partial structural view of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 11 is a schematic structural diagram of a balance fairing of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the invention;
FIG. 12 is a schematic structural diagram of another view angle of the balance fairing of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilating model of the invention;
FIG. 13 is a schematic structural view of a measuring rudder of the test device for measuring hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 14 is a partial structural view of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 15 is a partial schematic structural view of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 16 is a partial structural view of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 17 is a schematic view of a partial cross-sectional structure of another view angle of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilating model according to the present invention;
FIG. 18 is a partial structural view of another view of the hinge moment measurement test device for the control surface of the axisymmetric ventilation model of the present invention;
FIG. 19 is a partial structural view of another view of the hinge moment measurement test device for the control surface of the axisymmetric ventilation model of the present invention;
FIG. 20 is a partial structural view of another view of the hinge moment measurement test device for the control surface of the axisymmetric ventilation model of the present invention;
FIG. 21 is a schematic structural diagram of a balance mounting base of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the invention;
FIG. 22 is a schematic structural diagram of another view angle of the balance mounting base of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilating model of the present invention;
FIG. 23 is a schematic structural diagram of a hinge moment balance of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the invention;
FIG. 24 is a schematic structural diagram of a hinge moment balance of the axisymmetric ventilating model control surface hinge moment measurement test device of the present invention, and a balance model end heat insulating sleeve and a balance fixed end heat insulating sleeve thereof;
FIG. 25 is a schematic structural diagram of another view angle of the hinge moment balance of the axisymmetric ventilating model control surface hinge moment measurement test device and the balance model end heat insulating sleeve and the balance fixed end heat insulating sleeve thereof;
FIG. 26 is a schematic structural diagram of a hinge moment balance and a heat insulating sleeve at a fixed end of the balance of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model according to the invention;
FIG. 27 is a schematic cross-sectional view of a hinge moment balance of the test device for measuring hinge moment of control surface of axisymmetric ventilating model according to the present invention, and a heat insulating sleeve at the model end and a heat insulating sleeve at the fixed end of the balance;
FIG. 28 is a schematic structural diagram of a tail strut of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 29 is a schematic structural diagram of another view angle of the tail strut of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilating model of the present invention;
FIG. 30 is a schematic structural view of a rudder cover plate of the test device for measuring hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 31 is a schematic structural diagram of another view angle of the rudder cover plate of the test device for measuring hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 32 is a schematic structural view of a clip angle sheet of the test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of the present invention;
FIG. 33 is a schematic sectional view of the rear body of the control surface hinge moment measurement test device of the axisymmetric ventilating model of the present invention.
The specific implementation mode is as follows:
the present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
Fig. 1 to 33 show a test device for measuring hinge moment of a control surface of an axisymmetric ventilation model, which comprises:
the axial symmetry ventilation model 1 has an air inlet channel of a mandible type, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric venting model comprises a model forebody 10 and a model afterbody 11; a leveling platform 110 is arranged on the model rear body 11 and is used as an installation reference of the axisymmetric ventilation model;
the bottom of the hinge moment balance 2 is arranged in the model rear body 11 through a balance mounting seat 6; the hinge moment balance 2 is vertical to an inner flow channel of the model rear body 11;
three non-measuring rudders 3 uniformly mounted on the outer wall surface of the model rear body 11;
the measuring rudder 4 is connected with the top of the hinge moment balance 2, and the measuring rudder 4 and the three non-measuring rudders 3 are uniformly arranged on the outer wall surface of the model rear body 11;
and the front end of the tail support rod 5 is connected with the end part of the model rear body 11.
In the technical scheme, the model front body and the model rear body are assembled into a whole in a cylindrical surface matching and pin positioning mode, namely, the front end of the model front body is inserted into the model rear body and fixedly connected through pins on the wall surface.
In the above technical solution, the inner flow channel profile at the front end of the model rear body 11 is a circular profile, the inner flow channel profile at the rear end is a rectangular profile, and the hinge moment balance 2 is located in the rectangular profile.
In the technical scheme, the hinge moment balance 2 comprises a model end 20, a measuring section 21 and a fixed end 22 which are integrally formed, wherein the model end 20 is a 1:5 standard conical surface, and a key groove 200 and a wedge key groove 201 are arranged on the conical surface; the measuring section 21 adopts a four-column beam form, and measures four-component aerodynamic force and moment of a control surface (without measuring lateral force and yaw moment of the control surface); the fixed end 22 is set to 1:5, standard conical surface; cylindrical surface transition is adopted between the model end 20 and the measuring section 21, and between the measuring section 21 and the fixed end 22; a boss 23 with a chamfer is arranged behind the fixed end 22 of the hinge moment balance 2, and a threaded hole 230 is arranged in the center of the boss 23 and is used as a balance tensioning hole.
In the above technical solution, the balance mounting base 6 includes a bottom plate 60 and a rectangular boss 61 which are integrally formed; the center of the rectangular boss 61 is provided with a 1:5 standard conical hole 610; a round hole 611 is arranged at the bottom of the 1:5 standard conical hole 610, and the round hole 611 is positioned on the bottom plate 60; a rectangular groove I601 for mounting a non-measuring rudder is formed in the bottom plate 60, a rectangular groove II 602 communicated with the round hole 611 is formed in the middle of the rectangular groove I601, the left end and the right end of the outer surface of the bottom plate of the balance mounting seat are part of the outer surface of the rear body of the model, and a balance wiring groove I612 is formed in the side face of the rectangular boss 61; a balance wiring groove III 1110 communicated with the balance wiring groove I612 is arranged in the rectangular molded surface of the model rear body 11; one of the three non-measuring rudders 3 is connected in the rectangular groove I601, the outer wall surface of the model rear body 11 is provided with a non-measuring rudder rectangular groove 1000 for mounting the other two non-measuring rudders, and the non-measuring rudders are mounted in the non-measuring rudder rectangular groove 1000 through screws and are fixedly connected through the screws; a balance fixed end heat insulation sleeve 220 is arranged on the fixed end 22 of the hinge moment balance 2, and a balance model end heat insulation sleeve 203 is arranged on the model end 20 of the hinge moment balance; the balance fixed end heat insulation sleeve 220 and the balance model end heat insulation sleeve 203 are both glass fiber reinforced plastic heat insulation sleeves, the inner conical surface of the balance fixed end heat insulation sleeve 220 is matched with the fixed end 22, and the outer conical surface of the balance fixed end heat insulation sleeve 220 is matched with the 1:5 standard conical surface hole 610 arranged in the center of the rectangular boss 61; a U-shaped groove I204 for balance routing is arranged on the cylindrical surface of the heat insulation sleeve 220 at the fixed end of the balance; the inner conical surface at the upper end of the balance model end heat insulation sleeve 203 is matched with the 1:5 standard conical surface of the model end 20, and the upper end of the balance model end heat insulation sleeve 203 is provided with a heat insulation sleeve key groove 2030 and a heat insulation sleeve wedge key groove 2031 which are matched with the key groove 200 and the wedge key groove 201 of the model end 20; the minimum inner diameter of the lower end 2033 of the scale model end insulating sleeve 203 is larger than the maximum inner diameter of the upper end 2034; the lower end of the balance model end heat insulation sleeve 203 is sleeved on the balance fixed end heat insulation sleeve 220 and is not contacted with the outer wall of the balance fixed end heat insulation sleeve 220; the lower end of the heat insulation sleeve 203 at the end of the balance model is provided with a U-shaped groove II 2032 for balance routing, and the U-shaped groove I204 and the U-shaped groove II 2032 are oppositely arranged; the connection mode of the fixed end 22 of the hinge moment balance 2 and the balance mounting seat 6 is as follows: rectangular channel II 602 places back font angle piece 7, sets up the boss 23 of taking the chamfer of hinge moment balance 2 in the centre bore 70 of returning font angle piece 7 to be connected through the screw hole 230 that the center of screw 231 and boss 23 set up, be connected hinge moment balance 2's stiff end 22 and balance mount pad 6 are taut, the head top of screw 231 tightly is at the surface of returning font angle piece 7, and in this kind of technical scheme, the change of control plane declination is realized through changing the relative corner of returning the interior limit of font angle piece and outside, returns font angle piece outside and controls both sides and balance mount pad cooperation, and both sides leave certain gap around with balance mount pad both sides, inboard and balance cube head (boss 23) cooperation.
In the above technical solution, the manner of mounting the balance mount 6 on the model rear body 11 is as follows: a rectangular groove III 112 is formed in the wall surface of the model rear body 11, and a rectangular hole I113 is formed in the rectangular groove III 112; the bottom plate 60 of the balance mounting seat 6 is connected in the rectangular groove III 112 in a matching manner and is fixedly connected through a screw; and the rectangular boss 61 of the balance mounting seat 6 is arranged in the rectangular hole I113 in a matching manner.
In the technical scheme, the balance fairing 8 is arranged outside the balance model end heat insulation sleeve 203 and the balance fixed end heat insulation sleeve 220 of the hinge moment balance 2, the balance fairing 8 is a balance fairing which is formed by two plates (80, 81) and integrally has a hexagonal structure, the front and the back of the balance fairing are in wedge shapes, the left and the right side planes of the balance fairing are parallel to the left and the right side planes of the inner flow channel, the front and the back wedges and the left and the right planes are in arc transition, the wedge angle at the front end is 50 degrees, and the wedge angle at the back end is 60 degrees; a fairing round hole 82 for accommodating the hinge moment balance is formed in the balance fairing 8, and the interfaces of the two plates are selected to be behind the front wedge and in front of the rear wedge and are connected through screws; and a balance wiring groove II 83 is processed between the rear wedge and the fairing circular hole 82 so as to facilitate leading-out of a balance lead.
In the above technical solution, the connection mode between the measuring rudder 4 and the model end 20 of the hinge moment balance 2 is as follows: a rectangular hole II 114 is formed in the wall surface of the model rear body 11 opposite to the rectangular groove III 112, the rectangular hole II 114 is connected with a measuring rudder cover plate 115 through a screw (a screw hole is formed in the entity of the model rear body on two sides of the rectangular hole II 114, the measuring rudder cover plate is installed and measured through a screw), the measuring rudder cover plate 115 is divided into two parts, the outer side boundary line of the two measuring rudder cover plates 115 is perpendicular to a measuring rudder shaft, the contact surface of the two measuring rudder cover plates 115 is in a shape like the Chinese character 'ji', the two measuring rudder cover plates are connected in a positioning mode through a screw pin, the upper surface of the measuring rudder cover plate is used as a part of the outer molded surface of the model rear body, the lower surface of the measuring rudder cover plate 115 is used as a part of the molded surface of an inner flow channel, the measuring rudder cover plate 115 is connected with the model rear body 11 through a screw, a measuring rudder cover plate round hole, a cylindrical groove 117 is processed on the inner side of the circular hole 116 of the measuring rudder cover plate, the diameter of the cylindrical groove 117 is larger than that of the measuring rudder mounting cap 118, and a gap of 2mm is reserved between the lower surface of the circular hole 116 of the measuring rudder cover plate and the upper surface of the measuring rudder mounting cap 118; the measuring rudder 4 is connected to a measuring rudder mounting cap 118, and the inner wall of the measuring rudder mounting cap 118 is 1:5 standard conical surface, measure rudder installation cap 118 cover and establish the upper end at balance model end heat insulating sleeve 203, just be provided with on the measurement rudder installation cap 118 with model end 20's keyway 200 matched with waist type groove 1180, it is 6 installation cap wedge keyway (1181,1182) that the wedge angle that still is provided with two the size the same, opposite direction on the measurement rudder installation cap 118, wherein the installation cap wedge keyway 1181 of upper end cooperatees with locking hinge moment balance as the keyway of dismantling balance and installation cap, the installation cap wedge keyway 1182 of lower extreme and the wedge keyway 201 of model end 20.
In the technical scheme, the front end of the tail support rod 9 is a first cylindrical section 90, the outer surface of the first cylindrical section is cylindrical, the inner surface of the first cylindrical section is rectangular, four rectangular planes are respectively superposed with four planes at the end part of the model rear body, a screw through hole is arranged on the first cylindrical section, the position of the screw through hole is the same as that of a threaded hole at the tail part of the model rear body, and the screw through hole and the threaded hole are fixed by screws; the strut behind the first cylindrical section 90 is a first conical end 91, the outer surface of which is conical; the first conical section 91 is followed by a second cylindrical section 92; a wiring groove 920 and two wiring holes 921 in front and back are processed on the second cylindrical section 92 to facilitate the wiring of the balance; behind the second cylindrical section 92 are a second conical section 93, a third cylindrical section 94 and a third conical section 95, respectively; wherein, a balance wiring groove IV 903 is arranged on the first cylindrical section and is communicated with a wiring hole of the tail support rod (positioned on the connecting end with the model rear body), the balance wiring groove IV 903 is communicated with a balance wiring groove III 1110 in the model rear body 11, and a protection plate 1111 is arranged above the balance wiring groove IV and the balance wiring groove III;
in the above technical scheme, the inner surface of the strut behind the first cylindrical section 90 is sequentially provided with a drain hole 901 and a wedge-shaped wedge 902, and the symmetry plane of the wedge-shaped wedge 902 coincides with the symmetry plane of the balance fairing.
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 an axisymmetric model control surface hinge moment measurement test device of ventilating which characterized in that includes:
the axial symmetry ventilation model is characterized in that an air inlet channel of the axial symmetry ventilation model adopts a lower jaw type, and inner flow channels behind the air inlet channel are all in an axial symmetry configuration; the axisymmetric venting model comprises a model forebody and a model afterbody; a leveling platform is arranged on the model rear body;
the bottom of the hinge moment balance is arranged in the model rear body through a balance mounting seat; the hinge moment balance is vertical to an inner flow channel of the model rear body;
three non-measuring rudders which are uniformly arranged on the outer wall surface of the model rear body;
the measuring rudder is connected with the top of the hinge moment balance, and the measuring rudder and the three non-measuring rudders are uniformly arranged on the outer wall surface of the model rear body;
and the front end of the tail support rod is connected with the end part of the model rear body.
2. The test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of claim 1, wherein the inner flow channel profile at the front end of the model rear body is a circular profile, the inner flow channel profile at the rear end is a rectangular profile, and the hinge moment balance is located in the rectangular profile.
3. The test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of claim 1, wherein the hinge moment balance comprises a model end, a measuring section and a fixed end which are integrally formed, the model end is a 1:5 standard conical surface, and a key groove and a wedge key groove are arranged on the conical surface; the measuring section is in a four-column beam form; the fixed end is set to be 1:5, standard conical surface; cylindrical surface transition is adopted between the model end and the measuring section as well as between the measuring section and the fixed end; a boss with a chamfer angle is arranged behind the fixed end of the hinge moment balance, and a threaded hole is formed in the center of the boss.
4. The test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model as claimed in claim 3, wherein the balance mounting seat comprises a bottom plate and a rectangular boss which are integrally formed; the center of the rectangular boss is provided with a 1:5 standard conical surface hole; a round hole is formed in the bottom of the 1:5 standard conical surface hole and is positioned on the bottom plate; a rectangular groove I for mounting a non-measuring rudder is arranged on the bottom plate, and a rectangular groove II communicated with the round hole is arranged in the middle of the rectangular groove I; a balance wiring groove I is formed in the side face of the rectangular boss, and a balance wiring groove III communicated with the balance wiring groove I is formed in the rectangular molded surface of the model rear body; one of the three non-measuring rudders is connected in the rectangular groove I; the outer wall surface of the model rear body is provided with a rectangular groove for mounting other two non-measuring rudders, the fixed end of the hinge moment balance is provided with a balance fixed end heat insulation sleeve, and the model end of the hinge moment balance is provided with a balance model end heat insulation sleeve; the balance fixed end heat insulation sleeve and the balance model end heat insulation sleeve are both glass fiber reinforced plastic heat insulation sleeves, the inner conical surface of the balance fixed end heat insulation sleeve is matched with the fixed end, and the outer conical surface of the balance fixed end heat insulation sleeve is matched with a 1:5 standard conical hole arranged in the center of the rectangular boss; a U-shaped groove I for balance wiring is formed in the cylindrical surface of the heat insulation sleeve at the fixed end of the balance; the inner conical surface at the upper end of the balance model end heat insulation sleeve is matched with the 1:5 standard conical surface at the model end, and the upper end of the balance model end heat insulation sleeve is provided with a heat insulation sleeve key groove and a heat insulation sleeve wedge key groove which are matched with the key groove and the wedge key groove at the model end; the minimum inner diameter of the lower end of the heat insulation sleeve at the balance model end is larger than the maximum inner diameter of the upper end of the heat insulation sleeve at the balance model end; the lower end of the balance model end heat insulation sleeve is sleeved on the balance fixed end heat insulation sleeve and is not contacted with the outer wall of the balance fixed end heat insulation sleeve; the lower end of the heat insulation sleeve at the balance model end is provided with a U-shaped groove II for balance wiring, and the U-shaped groove I and the U-shaped groove II are oppositely arranged; the connection mode of the fixed end of the hinge moment balance and the balance mounting seat is as follows: rectangular channel II places back font angle piece, sets up the boss of taking the chamfer of hinge moment balance in the centre bore of returning font angle piece to be connected through the screw hole that the center of screw and boss set up, be connected hinge moment balance's stiff end and balance mount pad are taut, the head top of screw is tightly at the surface of returning font angle piece.
5. The test device for measuring the hinge moment of the control surface of the axisymmetrical ventilated model according to claim 4, wherein the manner of installing the balance installation seat on the model rear body is as follows: a rectangular groove III is formed in the wall surface of the rear body of the model, and a rectangular hole I is formed in the rectangular groove III; the bottom plate of the balance mounting seat is connected in the rectangular groove III in a matched mode, and the rectangular boss of the balance mounting seat is arranged in the rectangular hole I in a matched mode.
6. The test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model according to claim 4, wherein a balance fairing is arranged outside a balance model end heat insulating sleeve and a balance fixed end heat insulating sleeve of the hinge moment balance, the balance fairing is a balance fairing which is formed by two plates and integrally has a hexagonal structure, the front and the back of the balance fairing are wedge-shaped, planes of the left side and the right side are parallel to planes of the left side and the right side of the inner flow channel, the front wedge and the right plane are in circular arc transition, the wedge angle at the front end is 50 degrees, and the wedge angle at the back end is 60 degrees; a fairing round hole for accommodating the hinge moment balance is formed in the balance fairing, and the interfaces of the two plates are selected to be behind the front wedge and in front of the rear wedge and are connected through screws; and a balance wiring groove II is processed between the rear wedge and the circular hole of the fairing.
7. The test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of claim 5, wherein the connection mode of the measuring rudder and the model end of the hinge moment balance is as follows: a rectangular hole II is formed in the wall surface of the model rear body opposite to the rectangular groove III, a measuring rudder cover plate is connected to the rectangular hole II, and the upper surface of the measuring rudder cover plate is a part of the outer surface of the model rear body; the measuring rudder cover plates are two, the outer side boundary lines of the two measuring rudder cover plates are perpendicular to the measuring rudder shaft, the contact surfaces of the two measuring rudder cover plates are in a shape like the Chinese character 'ji', the two measuring rudder cover plates are connected in a positioning mode through threaded pins, the upper surface of each measuring rudder cover plate is used as a part of the outer molded surface of the rear body of the model, the lower surface of each measuring rudder cover plate is used as a part of the molded surface of the inner flow channel, the measuring rudder cover plates are connected with the rear body of the model through screws, measuring rudder cover plate round holes are formed in the measuring rudder shaft, the diameter of each measuring rudder cover plate round hole is 1mm larger than that of the measuring rudder shaft, a cylindrical groove is machined in the inner side of each measuring rudder cover plate round hole, the diameter of each cylindrical groove is larger than that of each measuring rudder mounting cap;
the measuring rudder is connected to the measuring rudder mounting cap, and the inner wall of the measuring rudder mounting cap is 1:5 standard conical surface, the big footpath 28mm of conical surface, the upper end at balance model end heat insulating sleeve is established to the installation cap cover, just be provided with on the measurement rudder installation cap with the keyway matched with waist type groove of model end, still be provided with two the same, the opposite direction's of size wedge angle is 6 installation cap wedge keyway on the measurement rudder installation cap, wherein the installation cap wedge keyway of upper end is as dismantling the keyway of balance with the measurement rudder installation cap, and the installation cap wedge keyway of lower extreme cooperatees with the wedge keyway of model end with locking hinge moment balance.
8. The test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of claim 6, wherein the front end of the tail strut is a first cylindrical section, the outer surface of the first cylindrical section is cylindrical, the inner surface of the first cylindrical section is rectangular, and four rectangular planes are respectively superposed with four planes at the end part of the model rear body; the support rod behind the first cylindrical section is a first conical end, and the outer surface of the support rod is conical; the first conical section is followed by a second cylindrical section; processing a wiring groove and a front wiring hole and a rear wiring hole on the second cylindrical section; the second cylindrical section is followed by a second conical section, a third cylindrical section and a third conical section, respectively.
9. The test device for measuring the hinge moment of the control surface of the axisymmetric ventilation model of claim 8, wherein the inner surface of the strut behind the first cylindrical section is provided with a drain hole and a wedge-shaped wedge in sequence, and the symmetrical surface of the wedge-shaped wedge is coincident with the symmetrical surface of the balance fairing.
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