CN211401612U - Combined force measuring balance for high lift-drag ratio model of hypersonic wind tunnel - Google Patents
Combined force measuring balance for high lift-drag ratio model of hypersonic wind tunnel Download PDFInfo
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- CN211401612U CN211401612U CN202020263698.7U CN202020263698U CN211401612U CN 211401612 U CN211401612 U CN 211401612U CN 202020263698 U CN202020263698 U CN 202020263698U CN 211401612 U CN211401612 U CN 211401612U
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Abstract
The utility model discloses a combination dynamometry balance that is used for hypersonic wind-tunnel high lift-drag ratio model. The combined force measuring balance comprises a rod type inner balance and a ring type outer balance which are coaxial with each other, wherein the inner balance and the outer balance are matched through a front conical section of the inner balance and an inner conical surface at the front end of the outer balance; the inner balance flat key groove is aligned with the outer balance flat key groove hole, and the circumferential positioning key is sequentially inserted into the outer balance flat key groove hole and the inner balance flat key groove from outside to inside, so that the inner balance and the outer balance are prevented from rotating relatively; the tensioning bolt is screwed into an inner balance threaded hole on the horizontal axis of the front conical section of the inner balance, and the head of the tensioning bolt is tightly pressed on the front end faces of the inner balance and the outer balance through a flat pad and an elastic pad, so that the inner balance and the outer balance are prevented from being loosened axially. The utility model discloses a combination dynamometry balance for hypersonic wind tunnel high lift drag ratio model can realize that each component measuring element structure size of balance matches the optimization, on the basis that keeps balance rigidity, has improved horizontal course aerodynamic characteristic measurement accuracy.
Description
Technical Field
The utility model belongs to the technical field of the hypersonic wind tunnel test, concretely relates to combination force measuring balance that is used for hypersonic wind tunnel to rise lift-drag ratio model.
Background
Hypersonic speed is an important direction for the development of various aircrafts and strategic tactical weapons in the future. At present, all aviation and astronomical countries pay strong attention to hypersonic aircrafts and related technologies. Compared with the traditional aircraft, the hypersonic aircraft has obvious differences, not only shows that the hypersonic aircraft is more complex in appearance, but also has obvious layout characteristics of a lifting body, and has the characteristics of stronger maneuverability, strong control capability and the like. Due to the characteristics of the high lift-drag ratio aerodynamic configuration profile aircraft, the high coupling effect of longitudinal and transverse channels of the aircraft and the difficulty of operation and control are increased, and particularly, the great change of the attitude angle in the reentry and maneuvering flight processes can cause inaccurate prediction of aerodynamic parameters, very obvious influence on maneuverability and stability and even out of control of the aircraft. The HTV-2 fails in both 2010 and 2011 flight tests, one reason is that in the reentry/glide flight mode conversion stage, due to inaccurate ground prediction of pneumatic data, the flight stability and the manipulation performance of an aircraft are insufficient during flight tests, roll/yaw coupling motion occurs, the overshoot yaw/roll torque is induced and far exceeds the actual controllable capacity, and although an RCS (remote control system) is adopted for horizontal-direction manipulation, the manipulation capacity is still limited, and the attitude is out of control. Therefore, a high-precision balance technology is developed in the hypersonic wind tunnel, the accuracy of force measurement test data of the high lift-drag ratio appearance is improved, particularly the accuracy of lateral-course aerodynamic test data is improved, and the high-precision balance method has important significance for solving the aerodynamic force and control problems faced by the design of a new generation hypersonic aircraft with the high lift-drag ratio.
At present, a hypersonic wind tunnel usually adopts a six-component strain balance to measure aerodynamic force and moment coefficient of a model, and the difference between the longitudinal load range and the transverse load range of the balance is small. The new generation hypersonic speed aircraft with high lift-drag ratio has the characteristics of large lift-drag ratio and large longitudinal and transverse aerodynamic load ratio, the load of the transverse directional component is smaller than that of the longitudinal load by more than one magnitude, and the design ranges of all components are not matched seriously. The aerodynamic performance characteristics of the high lift-drag ratio aircraft enable the balance structure to have an abnormal conflict between the rigidity and strength design and guarantee of the lateral course measurement component sensitivity and precision.
The difficulty in balance design is always to improve the measurement accuracy of the horizontal and horizontal pneumatic loads under the condition of large difference between the vertical and horizontal pneumatic loads, solve the contradiction between the sensitivity and the rigidity of the balance and reduce the mutual interference among all components of the force measuring balance.
Currently, in order to solve the above problems, there is a need to develop a high-precision force measuring balance for a hypersonic wind tunnel model with a high lift-drag ratio.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a combination dynamometry balance that is used for hypersonic wind-tunnel high lift-drag ratio model is provided.
The utility model discloses a combination force measuring balance for hypersonic wind tunnel high lift drag ratio model, its characteristics are, combination force measuring balance include with the inner balance of the rod-type of horizontal axis and ring type outer balance, the inner balance inserts outer balance central cavity, through inner balance front end conical surface cooperation with outer balance front end in inner balance front end between inner balance and the outer balance; the inner balance flat key groove is aligned with the outer balance flat key groove hole, the circumferential positioning key is sequentially inserted into the outer balance flat key groove hole and the inner balance flat key groove from outside to inside, and the circumferential positioning key is used for fixing the inner balance and the outer balance and preventing the inner balance and the outer balance from rotating relatively; the tensioning bolt is screwed into a threaded hole of the inner balance on the horizontal axis of the front conical section of the inner balance, the head of the tensioning bolt is tightly pressed on the front end surfaces of the inner balance and the outer balance through the flat pad and the elastic pad, the inner balance and the outer balance are tightly connected, and the inner balance and the outer balance are prevented from being loosened axially.
The inner balance is a rod balance and sequentially comprises an inner balance front conical section, an inner balance column beam I, an inner balance supporting beam, an inner balance column beam II and an inner balance rear conical section from front to back; an inner balance threaded hole matched with the tensioning bolt is formed in the central axis of the front cone section of the balance, and an inner balance flat key groove parallel to the horizontal axis of the inner balance is further formed in the front cone section of the balance; a group of strain gauges for measuring a normal force Y, a lateral force Z, a yawing moment My and a pitching moment Mz are adhered on the inner balance column beam I, and another group of strain gauges for measuring the normal force Y, the lateral force Z, the yawing moment My and the pitching moment Mz are adhered on the inner balance column beam II; the front section and the rear section of the internal balance supporting beam are provided with a plurality of internal balance supporting beams which are symmetrical front and back, the middle part of the internal balance supporting beam is provided with an internal balance axial force T-shaped beam which is symmetrical left and right, the vertical section of the internal balance axial force T-shaped beam is vertical to the central axis of the internal balance from top to bottom, the section area of the vertical section is linearly reduced from top to bottom, and the vertical section of the internal balance axial force T-shaped beam is adhered with a strain gauge for measuring the axial force A; the rear conical section of the inner balance is provided with a conical section matched with the conical surface of the tail support rod, and the rear conical section of the inner balance is also provided with a positioning key groove and a tensioning wedge hole.
The external balance is a ring balance; the front section of the outer balance is provided with an inner cone at the front end of the outer balance which is assembled with the front cone section of the inner balance, and the front section of the outer balance is also provided with an outer balance flat key slot hole which is assembled with the inner balance flat key slot; the middle section of the external balance is provided with a rolling moment Mx design central plane, two sides of the rolling moment Mx design central plane are provided with two groups of ring-type rolling moment Mx measurement areas which are symmetrical front and back, each group of ring-type rolling moment Mx measurement areas are provided with a plurality of external balance supporting beams at the positions of 0 DEG and 180 DEG in the circumferential direction of the external balance, the positions of 90 DEG and 270 DEG in the circumferential direction of the external balance are provided with external balance rolling moment supporting beams, the cross-sectional area of the horizontal section of each external balance rolling moment supporting beam is linearly reduced from the rolling moment Mx design central plane to the outside, and the horizontal section of each external balance rolling moment supporting beam is pasted with a strain gauge for measuring the rolling moment Mx; and the rear section of the external balance is provided with a flange matched with the test model.
The material of the inner balance and the outer balance is F141 steel.
The strain gauge is a medium temperature strain gauge.
It should be noted that the utility model discloses a combination dynamometry balance for hypersonic wind-tunnel high lift-drag ratio model need carry out the compensation that floats of zero point temperature at room temperature to operating temperature within range, and the compensation postnatal flat temperature drift satisfies GJB 2244A-2011 "wind-tunnel strain balance standard" requirement.
The utility model discloses a combination dynamometry balance for hypersonic wind-tunnel high lift-drag ratio model is including the combination balance of outer balance and interior balance, is six weight balances, and outer balance measurement roll moment Mx component, five weight of axial force A, normal force Y, yawing moment Z, yawing moment My and the pitching moment Mz of interior balance measurement test model. The range of the rolling moment Mx is 1 N.m, the range of the normal force Y is 2-3 orders of magnitude larger than that of the rolling moment Mx, the range of the axial force A is 1 order of magnitude larger than that of the rolling moment Mx, and the range of the lateral force Z and the range of the axial force A are the same order of magnitude.
The utility model discloses an outer balance that is arranged in the combination dynamometric balance of hypersonic wind-tunnel high lift-drag ratio model is ring type outer balance, adopts cavity ring type structure. The external balance rolling moment is designed with a rolling moment Mx element on the beam; the external balance rolling torque is designed in a variable cross section mode, the cross section area of the horizontal section of the external balance rolling torque is linearly reduced from the design center face of the rolling torque Mx to the outside, the average strain is increased, the sensitivity is improved, and meanwhile the stress concentration of the root of an element is reduced; the external balance is provided with a plurality of supporting beams, so that the external balance can bear larger normal force Y and lateral force Z, and meanwhile, higher sensitivity of rolling moment Mx is ensured.
The utility model discloses an interior balance that is arranged in the combination dynamometry balance of hypersonic wind-tunnel high lift-drag ratio model is rod-type interior balance, adopts rod-type structure. The axial force a element is a relatively independent element; the internal balance axial force T-shaped beam is arranged on the center of the balance design, a variable cross section design is adopted, the vertical section of the internal balance axial force T-shaped beam is perpendicular to the central axis of the internal balance, and the cross section area of the vertical section is linearly reduced from top to bottom; and a plurality of internal balance supporting beams are arranged in front of and behind the internal balance axial force T-shaped beam. The measuring beams of the internal balance normal force Y, the lateral force Z, the yawing moment My and the pitching moment Mz are of a column-beam structure and are symmetrically arranged at two ends of the axial force A element; the normal force Y and the pitching moment Mz are measured on the plane of the column beam and the vertical plane of the symmetry plane, and the lateral force Z and the yawing moment My are measured on the side surface of the column beam parallel to the symmetry plane. Because the internal balance does not need to consider measuring the roll moment Mx (but a roll moment Mx measuring circuit is still reserved on the roll moment Mx sensitive beam during actual mounting), the internal balance is relatively easy to match in structural dimension, and the sensitivity of lateral heading measurement is improved while the requirement of longitudinal large-load measurement is ensured.
The utility model discloses a variable cross section design that interior balance axial force T roof beam and external balance roll-over torque limit beam adoption that is arranged in hypersonic wind-tunnel high lift-drag ratio model's combination force balance, can reduce paster position required precision.
The utility model discloses a material that is used for outer balance and interior balance in the combination dynamometry balance of hypersonic wind-tunnel high lift drag ratio model is F141 steel, adopts the same ripe processing technology, is convenient for process manufacturing.
The utility model discloses a tail end design that is arranged in the outer balance of the combination dynamometric balance of hypersonic wind-tunnel high lift drag ratio model and interior balance has the interface of being connected with test model and tail branch. Because the interface is positioned at the tail end of the combined force-measuring balance and the middle rear part of the test model, the temperature rise of the middle rear part of the test model is slower than that of the front end interface which is usually adopted during the test, which is beneficial to reducing the balance temperature effect in the test process, and particularly, the measuring element in the combined force-measuring balance is not in contact with the test model, which is more beneficial to reducing the balance temperature effect.
The utility model discloses an outer balance and the equal exclusive use of interior balance that is arranged in the combination dynamometry balance of hypersonic wind-tunnel high lift-drag ratio model, outer balance still can use with current other rod-type balance combinations, has higher availability factor.
The utility model discloses a combination dynamometry balance for hypersonic wind tunnel high lift drag ratio model is high accuracy combination balance, has adopted inside and outside nested combination balance structure, has realized that each weight measuring element structure size of balance matches the optimization, on the basis that keeps balance rigidity, has improved horizontal course measurement accuracy, is applicable to the aerodynamic characteristic who measures hypersonic high lift drag ratio appearance aircraft test model.
Drawings
FIG. 1 is a schematic perspective view of the combined force measuring balance for the high lift-drag ratio model of the hypersonic wind tunnel according to the present invention;
FIG. 2 is a schematic plane structure diagram of the combined force measuring balance for the high lift-drag ratio model of the hypersonic wind tunnel according to the present invention;
FIG. 3 is a schematic diagram of the planar structure of the internal balance used in the combined force measuring balance of the hypersonic wind tunnel model with high lift-drag ratio according to the present invention;
FIG. 4 is an axial sectional view of the internal balance used in the combined force measuring balance of the hypersonic wind tunnel model with high lift-drag ratio according to the present invention;
FIG. 5 is a schematic view of the three-dimensional structure of the internal balance used in the combined force-measuring balance of the hypersonic wind tunnel model with high lift-drag ratio;
FIG. 6 is a schematic diagram of the plane structure of the external balance used in the combined force measuring balance of the hypersonic wind tunnel model with high lift-drag ratio according to the present invention;
FIG. 7 is an axial sectional view of an external balance used in the combined force measuring balance of the hypersonic wind tunnel model with high lift-drag ratio according to the present invention;
FIG. 8 is a schematic view of the three-dimensional structure of an external balance used in the combined force-measuring balance of the hypersonic wind tunnel model with high lift-drag ratio according to the present invention;
fig. 9 is the wind tunnel assembly schematic view of the combined force measuring balance for the hypersonic wind tunnel high lift-drag ratio model of the present invention.
In the figure, 1, an inner balance 2, an outer balance 3, a flat pad 4, an elastic pad 5, a tension bolt 6 and a circumferential positioning key are arranged;
101. the balance comprises an inner balance front conical section 102, an inner balance column beam I103, an inner balance multi-blade support beam 104, an inner balance axial force T-shaped beam 105, an inner balance rear conical section 106, an inner balance flat key groove 107, an inner balance threaded hole 108, an inner balance column beam II 109 and an inner balance support beam;
201. the external balance multi-plate support beam 202, external balance roll torque, cross beam 203, external balance flat key slot 204, external balance front end internal cone.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and examples.
As shown in fig. 1 and fig. 2, the combined force measuring balance for the hypersonic wind tunnel high lift-drag ratio model of the present invention comprises a rod-type inner balance 1 and a ring-type outer balance 2, wherein the rod-type inner balance 1 and the ring-type outer balance 2 are arranged on the same horizontal axis, the inner balance 1 is inserted into the central cavity of the outer balance 2, and the inner balance 1 and the outer balance 2 are in conical surface fit through a front conical section 101 of the inner balance and a front inner cone 204 of the outer balance; the inner balance flat key groove 106 is aligned with the outer balance flat key groove hole 203, the circumferential positioning key 6 is sequentially inserted into the outer balance flat key groove hole 203 and the inner balance flat key groove 106 from outside to inside, and the circumferential positioning key 6 is used for fixing the inner balance 1 and the outer balance 2 and preventing the inner balance 1 and the outer balance 2 from rotating relatively; the tensioning bolt 5 is screwed into an inner balance threaded hole 107 on the horizontal axis of the front conical section 101 of the inner balance, the head of the tensioning bolt 5 is tightly pressed on the front end faces of the inner balance 1 and the outer balance 2 through the flat pad 3 and the elastic pad 4, the inner balance 1 and the outer balance 2 are tightly connected, and the inner balance 1 and the outer balance 2 are prevented from being loosened axially.
As shown in fig. 3 to 5, the inner balance 1 is a rod balance, and sequentially comprises an inner balance front cone section 101, an inner balance column beam i 102, an inner balance support beam 109, an inner balance column beam ii 108 and an inner balance rear cone section 105 from front to back; an inner balance threaded hole 107 matched with the tensioning bolt 5 is formed in the central axis of the front conical section 101 of the balance, and an inner balance flat key groove 106 parallel to the horizontal axis of the inner balance 1 is further formed in the front conical section 101 of the balance; a group of strain gauges for measuring a normal force Y, a lateral force Z, a yawing moment My and a pitching moment Mz are adhered to the inner balance column beam I102, and another group of strain gauges for measuring the normal force Y, the lateral force Z, the yawing moment My and the pitching moment Mz are adhered to the inner balance column beam II 108; front and back symmetrical inner balance multiple supporting beams 103 are arranged on the front section and the back section of the inner balance supporting beam 109, a left and right symmetrical inner balance axial force T-shaped beam 104 is arranged in the middle of the inner balance supporting beam 109, the vertical section of the inner balance axial force T-shaped beam 104 is perpendicular to the central axis of the inner balance 1 from top to bottom, the cross section area of the vertical section is linearly reduced from top to bottom, and strain gauges for measuring axial force A are adhered on the vertical section of the inner balance axial force T-shaped beam 104; the rear conical section 105 of the inner balance is provided with a conical section matched with the conical surface of the tail support rod, and the rear conical section 105 of the inner balance is further provided with a positioning key groove and a tensioning wedge hole.
As shown in fig. 6 to 8, the external balance 2 is a ring balance; the front section of the external balance 2 is provided with an internal cone 204 at the front end of the external balance which is assembled with the front cone 101 of the internal balance 1, and the front section of the external balance 2 is also provided with an external balance flat key slot hole 203 which is assembled with the internal balance flat key slot 106; the middle section of the external balance 2 is provided with a rolling moment Mx design central plane, two sides of the rolling moment Mx design central plane are provided with two groups of ring-type rolling moment Mx measurement areas which are symmetrical front and back, each group of ring-type rolling moment Mx measurement areas are provided with external balance multi-plate supporting beams 201 at the positions of 0 DEG and 180 DEG in the circumferential direction of the external balance 2, external balance rolling moment supporting beams 202 are arranged at the positions of 90 DEG and 270 DEG in the circumferential direction of the external balance 2, the sectional area of the external balance rolling moment supporting beam 202 is linearly reduced from the rolling moment Mx design central plane to the outside, and strain gauges for measuring the rolling moment Mx are adhered to the horizontal section of the external balance rolling moment supporting beam 202; the rear section of the external balance 2 is provided with a flange assembled with the test model.
The inner balance 1 and the outer balance 2 are made of F141 steel.
The strain gauge is a medium temperature strain gauge.
Example 1
The utility model discloses a wind-tunnel assembly schematic diagram of a combination dynamometric balance for hypersonic wind-tunnel high lift-drag ratio model is shown in FIG. 9, and concrete step is as follows:
1. assembling an inner balance 1 and an outer balance 2 in a combined manner, and fixedly connecting with a tail support rod;
2. mounting a tail strut on a supporting device of a test section of the hypersonic wind tunnel;
3. fixing the rear section of the test model through an end face flange at the rear end of the external balance 2;
4. fixing the front section of the test model on the rear section of the test model;
5. and carrying out a wind tunnel test according to the hypersonic wind tunnel force measurement test flow.
Claims (5)
1. A combined force measuring balance for a high lift-drag ratio model of a hypersonic wind tunnel is characterized by comprising a rod type inner balance (1) and a ring type outer balance (2) which are coaxial with each other, wherein the inner balance (1) is inserted into a central cavity of the outer balance (2), and the inner balance (1) is matched with the outer balance (2) through a front cone section (101) of the inner balance and a conical surface of an inner cone (204) at the front end of the outer balance; the inner balance flat key groove (106) is aligned with the outer balance flat key groove hole (203), the circumferential positioning key (6) is sequentially inserted into the outer balance flat key groove hole (203) and the inner balance flat key groove (106) from outside to inside, and the circumferential positioning key (6) is used for fixing the inner balance (1) and the outer balance (2) and preventing the inner balance (1) and the outer balance (2) from relatively rotating; the tensioning bolt (5) is screwed into an inner balance threaded hole (107) in the horizontal axis of the front conical section (101) of the inner balance, the head of the tensioning bolt (5) is tightly pressed on the front end faces of the inner balance (1) and the outer balance (2) through the flat pad (3) and the elastic pad (4), the inner balance (1) and the outer balance (2) are tightly connected, and the inner balance (1) and the outer balance (2) are prevented from being loosened axially.
2. The combined force-measuring balance for the hypersonic wind tunnel high lift-drag ratio model according to claim 1, wherein the inner balance (1) is a rod balance, and comprises a front cone section (101) of the inner balance, an inner balance column beam I (102), an inner balance supporting beam (109), an inner balance column beam II (108) and a rear cone section (105) of the inner balance from front to back in sequence; an inner balance threaded hole (107) matched with the tensioning bolt (5) is formed in the central axis of the front conical section (101) of the balance, and an inner balance flat key groove (106) parallel to the horizontal axis of the inner balance (1) is further formed in the front conical section (101) of the balance; a group of strain gauges for measuring a normal force Y, a lateral force Z, a yawing moment My and a pitching moment Mz are adhered to the inner balance column beam I (102), and another group of strain gauges for measuring the normal force Y, the lateral force Z, the yawing moment My and the pitching moment Mz are adhered to the inner balance column beam II (108); front and back symmetrical inner balance multiple support beams (103) are arranged on the front section and the back section of the inner balance support beam (109), a bilateral symmetrical inner balance axial force T-shaped beam (104) is arranged in the middle of the inner balance support beam (109), the vertical section of the inner balance axial force T-shaped beam (104) is perpendicular to the central axis of the inner balance (1) from top to bottom, the cross section area of the vertical section is linearly reduced from top to bottom, and a strain gauge for measuring the axial force A is adhered to the vertical section of the inner balance axial force T-shaped beam (104); the rear conical section (105) of the inner balance is provided with a conical section matched with the conical surface of the tail support rod, and the rear conical section (105) of the inner balance is also provided with a positioning key slot and a tensioning wedge hole.
3. The combined force measuring balance for the hypersonic wind tunnel high lift-drag ratio model according to claim 1, characterized in that the external balance (2) is a ring balance; the front section of the outer balance (2) is provided with an inner cone (204) at the front end of the outer balance, which is assembled with the front cone section (101) of the inner balance (1), and the front section of the outer balance (2) is also provided with an outer balance flat key slot hole (203) which is assembled with the inner balance flat key slot (106); the middle section of the external balance (2) is provided with a rolling moment Mx design central plane, two groups of ring-type rolling moment Mx measurement areas which are symmetrical front and back are arranged on two sides of the rolling moment Mx design central plane, each group of ring-type rolling moment Mx measurement areas are provided with a plurality of external balance supporting beams (201) at the circumferential positions of 0 degree and 180 degree of the external balance (2), the circumferential positions of 90 degrees and 270 degrees of the external balance (2) are provided with external balance rolling moment integrated beams (202), the cross-sectional area of the horizontal section of the external rolling moment integrated beams (202) is linearly reduced outwards from the rolling moment Mx design central plane, and strain gauges for measuring the rolling moment Mx are pasted on the horizontal section of the external balance rolling moment integrated beams (202); the rear section of the external balance (2) is provided with a flange assembled with the test model.
4. The combined force measuring balance for the hypersonic wind tunnel high lift-drag ratio model according to claim 1, wherein the inner balance (1) and the outer balance (2) are made of F141 steel.
5. The combined force measuring balance for the hypersonic wind tunnel high lift-drag ratio model according to claim 2 or 3, characterized in that the strain gauge is a medium temperature strain gauge.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111189610A (en) * | 2020-03-06 | 2020-05-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Combined force measuring balance for high lift-drag ratio model of hypersonic wind tunnel |
| CN112857736A (en) * | 2021-01-11 | 2021-05-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of flow field nonuniformity on model aerodynamic characteristics |
| CN118549083A (en) * | 2024-07-26 | 2024-08-27 | 中国航空工业集团公司沈阳空气动力研究所 | Pitching dynamic derivative angle balance correction method |
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2020
- 2020-03-06 CN CN202020263698.7U patent/CN211401612U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111189610A (en) * | 2020-03-06 | 2020-05-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Combined force measuring balance for high lift-drag ratio model of hypersonic wind tunnel |
| CN111189610B (en) * | 2020-03-06 | 2024-05-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Combined force balance for hypersonic wind tunnel high lift-drag ratio model |
| CN112857736A (en) * | 2021-01-11 | 2021-05-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of flow field nonuniformity on model aerodynamic characteristics |
| CN112857736B (en) * | 2021-01-11 | 2022-04-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of flow field nonuniformity on model aerodynamic characteristics |
| CN118549083A (en) * | 2024-07-26 | 2024-08-27 | 中国航空工业集团公司沈阳空气动力研究所 | Pitching dynamic derivative angle balance correction method |
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