CN111964861B - Experimental device for compensating insufficient vertical acceleration of light model method - Google Patents
Experimental device for compensating insufficient vertical acceleration of light model method Download PDFInfo
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- CN111964861B CN111964861B CN202010682523.4A CN202010682523A CN111964861B CN 111964861 B CN111964861 B CN 111964861B CN 202010682523 A CN202010682523 A CN 202010682523A CN 111964861 B CN111964861 B CN 111964861B
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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
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention relates to an experimental device for compensating the insufficient vertical acceleration of a light model method, which is arranged in a wind tunnel experimental section and thrown with an embedded weaponPlacing the model for connection, comprising: the embedded missile launching system comprises a carrier model, an embedded missile model, an ejection mechanism, a traction block, a protective sleeve and a traction block line, wherein the embedded missile is connected with the traction block through the traction block line to move downwards, and the traction block line penetrates through the center of mass of the embedded missile to provide a virtual force F with unchanged size and vertical direction for the embedded missile V Due to F V Acting at the centre of mass of the buried missile, F V The relative mass center of the embedded missile is not acted, and the effect is only exerted on the displacement Z of the embedded missile in the vertical direction. The device has the advantages of simple design, processing and assembly, strong adaptability of model size, constant virtual force, no influence on the flow field near the external hanging object and the like.
Description
Technical Field
The invention relates to a high-speed wind tunnel throwing experimental device.
Background
The machine-bullet separation compatibility is one of key technologies in the process of developing a novel combat aircraft supersonic velocity buried weapon system, and the main task of the machine-bullet separation compatibility research is to verify the safe separation of a weapon and an aircraft carrier and ensure that the separated weapon has a good flight attitude, so that the weapon launching envelope of the aircraft is determined.
A wind tunnel launching experiment based on motion dynamics similarity is an unsteady simulation Method for researching separation compatibility of an embedded weapon machine cartridge, for a high-speed wind tunnel launching experiment (Ma > 0.8), the influence of air compressibility on the separation compatibility of the embedded weapon machine cartridge must be considered, the Mach number Ma becomes a main similar parameter, and the wind tunnel experiment has a Heavy Model Method (Heavy Model Method) and a Light Model Method (Light Model Method) on the premise of ensuring the Ma to be the same.
The movements of the heavy model method are strictly similar, but the disadvantage is that the model is heavy, sometimes suitable material processing cannot be found, and the method is not practical. Light model method except that the vertical acceleration is insufficient ("missing" vertical acceleration is Δ g' = (k) T /k l -1)g，k T 、k l Respectively, static temperature shrinkage ratio and size shrinkage ratio, g is gravity acceleration), and the rest are all transportedThe motions are strictly similar, and the model design and the processing are easier. Therefore, the scholars at home and abroad put in experimental research on high speed (Ma) by adopting wind tunnel>0.8 For separation compatibility of cartridge in case of buried weapon, light model method is mainly used.
The vertical displacement and the horizontal displacement of the model when the model falls are not proportional due to insufficient vertical acceleration of a light model method, so that the vertical displacement of the model throwing deviates from the physical displacement, and the problem that the mechanical-elastic separation incompatibility of the embedded weapon obtained by a wind tunnel throwing experiment is the inherent separation characteristic of the embedded weapon or is caused by the defects of the wind tunnel experiment method is not forbidden.
Therefore, the problem of insufficient vertical acceleration caused by the scaling law of the light model in the high-speed wind tunnel launching experiment needs to be compensated urgently, and the defect of the high-speed wind tunnel launching experiment means is avoided.
The conventional methods for compensating the insufficient vertical acceleration of the light model mainly comprise the following steps:
(1) The carrier model is moved upwards by Δ g', or the model is placed in an externally applied magnetic field, causing the model to increase the vertical acceleration of the model. However, these two methods are complicated in apparatus, and are not often used because they are difficult to implement when the model scale is 10 to 20 times.
(2) When the model is thrown downwards, the ejection force of the model is increased, and an additional ejection speed is generated on the model to make up for the defect. But the most important disadvantage is that the instantaneous separation speed and separation angular speed of the unlocking of the test model cannot be accurately simulated.
(3) Correcting the motion trail of the throwing object model in the vertical direction by adopting a formula correction method, wherein the formula is as follows:
in the formula: Δ Z 'represents the vertical displacement of the deletion, t' represents the separation time, t e 'represents the ejection force action time,. DELTA.F' represents the additional ejection force,. DELTA.F '= m' (Δ g '), and m' represents the model mass.
The method has certain limitation in use, and if the free flight state of the model is limited (such as collision between a carrier and a put object), the formula correction rule can not be used any more.
(4) The full-size experimental model is adopted to carry out the wind tunnel launching experiment, so that the problem of insufficient vertical acceleration caused by the scaling of the model is avoided. However, the model has no scaling, so the size requirement of the wind tunnel is high, and the model is difficult to realize in domestic wind tunnels at present.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention provides an experimental device for compensating the insufficient vertical acceleration of a light model method, which solves at least the problems and/or the defects, and ensures that the experimental device is simple in design, processing and assembly, strong in model size adaptability and constant in virtual force, and does not influence the flow field near a pendant.
The technical scheme adopted by the invention is as follows: an experimental device for compensating for insufficient vertical acceleration of a light model method comprises: the device comprises a carrier model, an ejection mechanism, an embedded missile model, a traction wire, a traction block and a protective sleeve;
the carrier model is installed in the wind tunnel test section through a tail support rod; the embedded missile model is fixed on the ejection mechanism and is arranged in a weapon cabin of the vehicle model together with the ejection mechanism; the upper end of the traction wire is connected with the mass center of the embedded missile model, the traction block is connected with the lower end of the high-strength traction wire, the protective sleeve is installed at the bottom of the wind tunnel experiment section, and the traction block moves in the protective sleeve; when a control signal is received, the ejection mechanism pushes the embedded missile model to move downwards, when the preset unlocking position is reached, the embedded missile model is separated from the ejection mechanism, and the traction block and the embedded missile model move downwards.
The ejection mechanism includes: the movable hanging rack comprises a front air cylinder body, a rear air cylinder body, a front piston rod, a rear piston rod, a fixed beam and a movable hanging rack; the front cylinder body and the rear cylinder body are connected with the fixed beam; preceding piston rod, back piston rod place respectively in preceding cylinder body and the back cylinder body and be connected with the removal stores pylon, for removing the stores pylon and provide drive power, bury the guided missile model and be connected with the removal stores pylon, gas promotion removal stores pylon downstream in preceding cylinder body and the back cylinder body, when reaching predetermined unblock position, bury the guided missile model and continue downstream with the removal stores pylon separation.
The traction wire is a molybdenum wire.
The traction block is a cylindrical lead block.
The central axis of the protective sleeve coincides with the central axis of the cylindrical lead block.
Compared with the prior art, the invention has the beneficial effects that:
in the process of establishing the wind tunnel flow field, the embedded missile model can be reliably mounted on the vehicle model through the ejection mechanism, does not move in a non-throwing state, and reduces the internal stress of the system as much as possible. The former method of applying the virtual force is to adopt a cylinder mode, the downward thrust generated by the cylinder changes along with the time t moment and does not meet the condition of constant virtual acting force, and a cylinder push rod is not connected with a model in a contact way, so that the phenomenon of slipping easily occurs. The device is not only used for the wind tunnel release model test of the separation compatibility of the built-in weapon machine projectile, but also can be widely applied to all the problems of the separation compatibility of multiple bodies researched by adopting the high-speed wind tunnel release test technology.
Drawings
FIG. 1 shows the application of a constant force F V The stress of the rear buried missile is shown schematically;
FIG. 2 is a schematic view of an ejection mechanism;
FIG. 3 is a diagram of an experimental apparatus for compensating for vertical acceleration deficiency in a light model method.
Detailed Description
The invention is described in further detail below with reference to the drawings so that those skilled in the art can practice the invention with reference to the description.
The invention provides an experimental device for compensating the insufficient vertical acceleration of a high-speed wind tunnel throwing experiment light model method, which is arranged in a wind tunnel test section and connected with an embedded missile model, and comprises:
as shown in figure 1, the method for compensating the insufficient vertical acceleration of the light model method is to apply a virtual force F at the mass center of the buried missile model V = m Δ g ', where m is the model mass, = (k) (= m Δ g' = T /k l -1)g，k T 、k l Respectively, the static temperature shrinkage ratio and the size shrinkage ratio, and g is the gravity acceleration.
As shown in fig. 3, the experimental apparatus for compensating for the insufficient vertical acceleration of the light model method includes:
the carrier model 12 is connected with a tool rest in the wind tunnel test section through a tail support rod 11;
as shown in fig. 2, the ejection mechanism mainly includes: the cylinder comprises a front cylinder body 1, a rear cylinder body 2, a front piston rod 3, a rear piston rod 4, a fixed beam 5 and a movable hanging frame 6. The front cylinder body 1 and the rear cylinder body 2 are in threaded connection with the fixed beam 5, the front piston rod 3 and the rear piston rod 4 are respectively arranged in the front cylinder body 1 and the rear cylinder body 2 and are connected with the movable hanging rack 6 to provide driving force for the movable hanging rack 6, the embedded missile model 7 and the movable hanging rack 6 are connected into a whole, and the whole ejection mechanism is arranged in a weapon cabin of the carrier model 12.
And the embedded missile model 7 is fixed on the movable hanging rack 6 of the driving ejection mechanism with the double cylinders, is arranged in the weapon cabin of the carrier model 12 together with the whole ejection mechanism, and pushes the movable hanging rack 6 to move downwards by high-pressure gas when receiving a control signal, so that the embedded missile model 7 is separated from the movable hanging rack 6 to continue to move downwards when reaching a preset unlocking position.
The high-strength molybdenum wire 8 has the characteristics of small diameter (d =0.12 mm), high strength and the like, can bear 10-30N of force, and is connected with the center of mass (CG) of the embedded missile model 7 at the upper end.
The cylindrical lead block 9 is connected with the lower end of the high-strength molybdenum wire 8 and has a certain distance with the embedded missile model 7, after the embedded missile model 7 is unlocked with the movable hanging frame 6, the cylindrical lead block 9 and the embedded missile model 7 are connected into a whole to move downwards, and the cylindrical lead block 9 provides constant virtual force for the embedded missile model 7.
The protective sleeve 10 is connected with the bottom of the wind tunnel experiment section through a bolt, the central axis of the protective sleeve is basically superposed with the central axis of the cylindrical lead block 9, and the cylindrical lead block 9 moves in the protective sleeve 10 from beginning to end so as to ensure that the cylindrical lead block 9 does not swing.
In the separation process, the cylindrical lead block 9 only provides a constant virtual force for the buried missile model 7, and the center of mass rotation of the buried missile model 7 is not influenced. When different wind tunnel experiment states are simulated, only different cylindrical lead blocks 9 need to be replaced, and therefore different flight Mach numbers are guaranteed to correspond to different virtual forces.
While embodiments of the invention have been disclosed above, it is not limited to buried missile launch separation, as described and illustrated in the embodiments, but is fully applicable to a variety of fields of art to which the invention pertains, and additional modifications will be readily apparent to those skilled in the art, and the invention is not to be limited to the details and illustrations contained herein, without departing from the general concepts defined in the claims and the scope of equivalents thereof.
Claims (2)
1. An experimental device for compensating for insufficient vertical acceleration of a light model method is characterized by comprising: the missile launching device comprises a carrier model (12), an ejection mechanism, an embedded missile model (7), a traction wire, a traction block and a protective sleeve (10);
the carrier model (12) is installed in the wind tunnel test section through the tail supporting rod (11); the embedded missile model (7) is fixed on the ejection mechanism and is arranged in a weapon cabin of the vehicle model (12) together with the ejection mechanism; the upper end of the traction wire is connected with the mass center of the embedded missile model (7), the traction block is connected with the lower end of the high-strength traction wire, the protective sleeve (10) is installed at the bottom of the wind tunnel experiment section, and the traction block moves in the protective sleeve (10); when a control signal is received, the ejection mechanism pushes the embedded missile model (7) to move downwards, when a preset unlocking position is reached, the embedded missile model (7) is separated from the ejection mechanism, and the traction block and the embedded missile model (7) move downwards;
the ejection mechanism includes: the device comprises a front cylinder body (1), a rear cylinder body (2), a front piston rod (3), a rear piston rod (4), a fixed beam (5) and a movable hanging frame (6); the front cylinder body (1) and the rear cylinder body (2) are connected with the fixed beam (5); the front piston rod (3) and the rear piston rod (4) are respectively arranged in the front cylinder body (1) and the rear cylinder body (2) and connected with the movable hanging rack (6) to provide driving force for the movable hanging rack (6), the embedded missile model (7) is connected with the movable hanging rack (6), gas in the front cylinder body (1) and the rear cylinder body (2) pushes the movable hanging rack (6) to move downwards, and when a preset unlocking position is reached, the embedded missile model (7) is separated from the movable hanging rack (6) and continues to move downwards;
applying virtual force F at the position of mass center of embedded missile model V = m Δ g ', where m is the model mass, = (k) (= m Δ g' = T /k l -1)g，k T 、k l Respectively representing static temperature shrinkage ratio and size shrinkage ratio, and g represents gravity acceleration;
the traction wire is a molybdenum wire (8);
the traction block is a cylindrical lead block (9).
2. The experimental device for compensating the vertical acceleration insufficiency of the light model method according to claim 1, characterized in that the central axis of the protective sleeve (10) coincides with the central axis of the cylindrical lead block (9).
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| CN114486158B (en) * | 2021-12-30 | 2023-10-17 | 中国航天空气动力技术研究院 | Quick pre-estimating method for initial throwing condition of separation compatibility of machine and bullet of embedded weapon |
| CN114486159A (en) * | 2021-12-30 | 2022-05-13 | 中国航天空气动力技术研究院 | Control and verification method for embedded weapon machine bomb separation compatibility front edge sawtooth spoiler |
| CN114781281B (en) * | 2022-03-31 | 2024-08-06 | 中国航天空气动力技术研究院 | Method and device for correcting vertical acceleration simulation deficiency of mechanical-elastic separation release test |
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| RU692347C (en) * | 1978-01-06 | 1994-07-30 | Васильев Камиль Исхакович | Device for suspension of aircraft models in wind tunnel |
| CN106153291B (en) * | 2016-06-24 | 2018-08-07 | 中国航天空气动力技术研究院 | Compensated high-speed wind-tunnel launches the insufficient method of domestic model normal acceleration |
| CN205785747U (en) * | 2016-06-24 | 2016-12-07 | 中国航天空气动力技术研究院 | High-speed wind tunnel machine bullet free drop-test device |
| CN105865743B (en) * | 2016-06-24 | 2018-08-07 | 中国航天空气动力技术研究院 | High-speed wind tunnel launches drop-test mechanism |
| CN107328547B (en) * | 2017-06-21 | 2019-07-12 | 中国航天空气动力技术研究院 | Inside bury weapon domestic model gravity-compensated device |
| CN111220342B (en) * | 2020-03-18 | 2024-04-05 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel embedded test model throwing mechanism |
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