CN211178915U - Separation wind tunnel test device for plane-symmetric hypersonic aircraft hood - Google Patents
Separation wind tunnel test device for plane-symmetric hypersonic aircraft hood Download PDFInfo
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- CN211178915U CN211178915U CN202020057689.2U CN202020057689U CN211178915U CN 211178915 U CN211178915 U CN 211178915U CN 202020057689 U CN202020057689 U CN 202020057689U CN 211178915 U CN211178915 U CN 211178915U
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Abstract
The utility model discloses a separation wind tunnel test device of a plane symmetry hypersonic aircraft hood. The test device comprises a projectile body model supported by a tail strut of an upper hypersonic wind tunnel mechanism and a cover body model supported by a belly support of a lower hypersonic wind tunnel mechanism; in an initial state, the cover body model covers the head of the bullet body model and is separated from and not contacted with the bullet body model; in a test state, the cover body model and the projectile body model are separated and move relatively independently; the cover body model adopts a rod type six-component balance to measure the aerodynamic force of the cover body model, and spray pipes are symmetrically arranged on the left and right of the cover body model to simulate the jet flow of the spray pipes; the elastic body model adopts a rod type six-component balance to measure the aerodynamic force of the elastic body model; the abdomen supports the pressure regulating device of the pore plate. The test device solves the key technical problems of relative postures of the two-stage model, separation distance adjustment of the two-stage model, jet flow simulation, small-size balance design, model connection and the like, improves the jet flow stability of the jet pipe, and reduces the interference of abdominal support.
Description
Technical Field
The utility model belongs to the technical field of the hypersonic wind tunnel test, concretely relates to face symmetry hypersonic aircraft hood separation wind tunnel test device.
Background
When the plane-symmetric hypersonic aerocraft flies at hypersonic speed, the head of the projectile body is inevitably subjected to atmospheric friction force to generate local high temperature and high pressure, and the temperature can reach thousands of degrees. In order to prevent the damage of the high temperature to the bullet head, a hood is usually added on the bullet head to prevent heat. The hood is made of ablation-resistant materials, when the missile reaches a specific area, the hood is thrown away, hood separation is achieved, the pneumatic characteristics in the separation process are very complex, and related pneumatic data are generally obtained by combining a wind tunnel test. Generally, the projectile body has an axisymmetric shape or a plane-symmetric shape, and for the axisymmetric shape, the internal space of the projectile body is large, and the design and connection of the internal support construction of the model are relatively easy; and to the face symmetry appearance, it is narrow and small to receive the internal space of model height restriction projectile, and is littleer to the space of the cover body among the hood separation model very much, moreover, the projectile body head can occupy a part cover body space when the head buries the cover body, brings very big degree of difficulty for cover body jet flow device and balance design. The cover body balance is positioned at the head of the cover body model, and the heat protection of the balance is also improved. The size of the cover body balance is small and is not easy to design due to the limitation of the inner space of the cover body model, so that how to improve the size of the cover body balance is a main consideration factor. For the plane-symmetric hypersonic aircraft model with a larger projectile body and a smaller hood, the proportion difference of the hood is larger, and the size of the smaller hood model brings great difficulty to the connection and positioning design of the hood. In order to reduce the pneumatic interference of the abdominal support, the size of the abdominal support cannot be too large or too small, and the requirements of strength, rigidity, resonance frequency and the like need to be met. In addition, the problems of nozzle connection, air supply pipeline arrangement and jet flow regulation in a narrow space need to be considered.
At present, a special plane-symmetric hypersonic aircraft nose cover separation wind tunnel test device needs to be developed urgently.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a separation wind tunnel test device of face symmetry hypersonic aircraft hood is provided.
The utility model discloses a separation wind tunnel test device of face symmetry hypersonic aircraft hood, its characteristics are: the testing device comprises a projectile body model supported by a tail support rod of the upper hypersonic wind tunnel mechanism and a cover body model supported by a belly support of the lower hypersonic wind tunnel mechanism; in an initial state, the cover body model covers the head of the bullet body model and is separated from and not contacted with the bullet body model; in a test state, the cover body model and the projectile body model are separated and move relatively independently; the cover body model adopts a rod type six-component balance to measure the aerodynamic force of the cover body model, and spray pipes are symmetrically arranged on the left and right of the cover body model to simulate the jet flow of the spray pipes; the elastic body model adopts a rod type six-component balance to measure the aerodynamic force of the elastic body model; the pressure regulating device for the web support communication pore plate.
The cover body model comprises a cover body front section, a cover body middle section and a cover body rear section; the hood body rod type balance is arranged in the middle section of the hood body, is fixed on a balance interface of the belly support plate through a hood body rod type balance connecting wedge key and is positioned through a hood body rod type balance positioning flat key; the front section of the cover body and the middle section of the cover body are positioned by a positioning clamping groove at the front section of the cover body; the lower part of the middle section of the cover body is provided with a middle section notch of the cover body, and the abdomen support plate passes through the middle section notch of the cover body and enters the middle section of the cover body.
The projectile body model comprises a projectile body head, a projectile body middle section, a projectile body rear section and a projectile body bottom cover plate; the elastic body rod type balance is positioned in the rear section of the elastic body, the rear end of the elastic body rod type balance is fixed on the tail support rod, and the elastic body rod type balance heat insulation sleeve is arranged on the conical surface of the front end of the elastic body rod type balance; the rear section of the elastomer is arranged on the conical surface at the front end of the elastomer rod type balance through an elastomer rod type balance steel sleeve and an elastomer rod type balance heat insulation sleeve; the sensing element of the elastic rod type balance is wrapped by the elastic rod type balance heat insulation sleeve, so that the elastic rod type balance has a heat insulation protection effect; the elastic body rod type balance heat insulation sleeve is wrapped by the elastic body rod type balance steel sleeve, and the elastic body rod type balance heat insulation sleeve has the effect of increasing the connection strength of the elastic body rod type balance and the elastic body middle section.
The upper end of an abdomen support plate of the abdomen support extends into the middle section of the cover body, and an abdomen support base at the lower end of the abdomen support plate is fixed on a lower mechanism of the hypersonic wind tunnel; the upper end of the belly support plate is provided with a spray pipe switching chamber, the front end of the spray pipe switching chamber is provided with a cover body rod type balance interface, and the middle part of the spray pipe switching chamber is respectively communicated with the air inlet pipelines in the spray pipe and the belly support plate; before the hypersonic wind tunnel test, a pressure sensor is arranged at the rear end of the spray pipe transfer parking chamber, and the pressure of the spray pipe transfer parking chamber is measured; during a hypersonic wind tunnel test, a pressure sensor at the rear end of the spray pipe transfer parking chamber is dismounted, and a jet flow pressure regulating interface plug is replaced; an air inlet pipeline interface is arranged at the position below the abdomen supporting plate and close to the abdomen supporting base.
The orifice plate pressure regulating device is arranged on the wall of the hypersonic wind tunnel, a cavity is formed in a tunnel wall joint of the orifice plate pressure regulating device, and the cavity is respectively communicated with a copper tube and an air supply pipeline system of the hypersonic wind tunnel; one end of the red copper pipe is connected with an air inlet pipeline interface of the spray pipe, and the other end of the red copper pipe is communicated with the cavity of the hole wall joint; the interface of the red copper tube is pressed on the hole wall joint through a compression nut; a pressure regulating pore plate is arranged at the interface of the red copper pipe interface and the hole wall joint; the hole wall joint is provided with a pressure sensor for measuring the pressure in the cavity of the hole wall joint.
The front section of the cover body is made of alloy steel, and the middle section of the cover body is made of carbon fiber in an integrated forming mode; the cross section of the hood rod type balance is in a variable cross section shape which is matched with the inner space of the middle section of the hood and is small at the top and big at the bottom; and a series of symmetrical clamping grooves are arranged on two sides of the cover body rod type balance positioning flat key.
The head of the projectile body is made of alloy steel, and the middle section of the projectile body is made of superhard aluminum.
The spray pipes are symmetrically arranged on two sides of the middle section of the cover body.
The pressure regulating pore plate is a flat plate with a hole in the middle, and sealing gaskets are arranged on two sides of the pressure regulating pore plate.
Furthermore, the shape of the opening of the pressure regulating pore plate is square; the sealing washer is a red copper sealing washer.
The method comprises the steps of setting the relative positions and postures of a cover body model and a projectile body model in a hypersonic wind tunnel, adjusting the step interval and the relative attack angle of the cover body model and the projectile body model, and then measuring to respectively obtain aerodynamic force data of the cover body model and the projectile body model. The conventional two-stage separation force measurement test is realized through an attack angle mechanism, two-stage models are connected to the mechanism, the attack angles of the two-stage models are simultaneously changed, the change of the relative positions of the two-stage models cannot be realized in the blowing process, the change of the relative positions of the two-stage models needs to be completed in tests of different train numbers, and the cost and the period of the test of the separation wind tunnel of the hood of the surface-symmetric hypersonic aircraft are greatly increased according to the conventional design. When the relative gesture of the cover body model and the projectile body model is more, a plurality of adapters need to be processed to meet the requirement of position adjustment, so that the processing difficulty and the frequency of replacing the gesture of the model are increased.
The hypersonic aerocraft symmetrical to a certain plane comprises a projectile body, a cover body and two shaft-push jet flow auxiliary separation devices (namely spray pipes) which are symmetrically distributed, wherein jet flow of the spray pipes is obliquely sprayed backwards to generate forward reverse thrust to assist the cover body to be separated from the projectile body. The utility model discloses a face symmetry hypersonic aircraft hood separation wind-tunnel test device is just to this type of face symmetry hypersonic aircraft and design.
The utility model discloses a plane-symmetric hypersonic aircraft hood separation wind tunnel test device needs to satisfy model states of different stage distances, particularly different small stage distances, different relative attack angles, sideslip angles and the like; the utility model discloses a jet-pipe jet flow total pressure that face symmetry hypersonic aircraft hood separation wind-tunnel test device need satisfy compares in the past approximately up to 15MPa, has higher jet pressure, and the jet flow needs to satisfy simultaneously air feed and two kinds of states of disconnection, provides higher requirement for jet pressure debugging, gas tightness, reduction loss of pressure. The utility model discloses a plane symmetry hypersonic aircraft hood separation wind-tunnel test device has adopted the cold airflow jet simulation that rocket jet was used always among the hypersonic wind-tunnel test. Simultaneously, in order to realize the requirement of the cover body and projectile separation dynamometry, measure the axle and push away the jet flow in-process, the cover body is under different positions, angle of attack, sideslip angle and relative attitude angle, the aerodynamic force of the cover body and projectile body reduces the model gesture and changes the number of times, the utility model discloses a plane symmetry hypersonic aircraft hood separation wind-tunnel test device utilizes upper and lower two sets of mechanisms to regard as the independent support of projectile body model and cover body model respectively, realizes the independent motion of projectile body model and cover body model respectively, to single-stage model, has reduced the single-stage model design degree of difficulty, has reduced single-stage model processingquantity, does not need the relative gesture that the two-stage model can be changed to the dismouting model in addition among the test process, very big improvement test efficiency. The upper mechanism of the hypersonic wind tunnel has multiple degrees of freedom and the capability of dynamically adjusting the pose of the model, so that the upper mechanism is selected to support the projectile body model in a tail support mode, and the lower mechanism is selected to support the shroud body model in a belly support mode. According to CFD simulation, when the abdomen support is positioned in the middle of the cover body and is close to the center of mass, the pneumatic interference on the cover body is minimum, the width and the front-back length of the abdomen support are reduced, the interference of the abdomen support can be controlled within an acceptable range, and the abdomen support interference amount can be further deducted by a zero-crossing correction method in the data processing process.
Because, the test of face symmetry hypersonic aircraft hood separation wind-tunnel is a jet flow interference test, and jet flow interference test's jet flow unit can not collide with test model mutually, must keep the certain distance with test model, and this gives the utility model discloses a less cover body model jet flow design of size among the face symmetry hypersonic aircraft hood separation wind-tunnel test device brings certain difficulty. The whole cover model jet device cannot leak air, the pipeline connection, the spray pipe connection and the like must meet certain air tightness requirements, and due to accumulated errors of model processing, the relative position of the spray pipe and the cover model after installation cannot meet certain deviation requirements easily.
The jet flow test usually adopts cold jet flow to simulate the momentum ratio, pressure ratio and thrust ratio of the hot jet flow of a projectile, and the modification of the inner profile of the spray pipe must meet the requirement of simulation parameters, which is easy to realize for a completely axisymmetric spray pipe, but for an outlet oblique-cutting spray pipe in a plane symmetric hypersonic aircraft hood separation wind tunnel test, the problems of determination of non-axisymmetric outlet physical quantity and conversion of cold and hot jet flow parameters are also involved. The utility model discloses a spray tube among the separation wind-tunnel test device of face symmetry hypersonic aircraft hood passes through parameters such as known spray tube export minor face hot jet mach number, pressure ratio, momentum ratio, half cone angle, obtains interior profile correction angle, the spray tube throat diameter of oblique cutting spray tube according to similar criterion and planter-meier expansion theory. For reducing the processing degree of difficulty, the utility model discloses a face symmetry hypersonic aircraft hood separation wind-tunnel test device's spray tube's internal face adopts the toper, revises the toper throat on satisfying momentum ratio simulation basis, revises expansion half cone angle according to cold and hot expansion boundary approximate simulation theory simultaneously, and the spray tube is directly welded to the both sides that the spray tube switching is resident the room, keeps spray tube axis and exit position unchangeable.
The utility model discloses an inside air supply passage that sets up of abdomen extension board that the abdomen among the hypersonic aircraft hood separation wind-tunnel test device of plane symmetry supports has reduced and has singly established the interference of air supply line to the outflow and to the incoming flow degree of jam, simultaneously, for adapting to abdomen support flat structure, the air vent adopts the dysmorphism hole mode to reduce pipeline loss of pressure. The related parameters and the front and back positions of the belly support are optimally designed as much as possible, and the pneumatic interference of the belly support on the projectile body is reduced as much as possible.
The utility model discloses a face symmetry hypersonic aircraft hood separation wind-tunnel test device utilizes upper and lower two sets of mechanisms as the mode of projectile body model and the independent support of cover body model respectively for the projectile body head of projectile body model can go deep into cover body anterior segment of cover body model, needn't consider during the model design and shorten the projectile body head. Simultaneously, in order to avoid the belly extension board upper end that the belly supported too to lean on the afterbody of cover body model, reduce the interference of belly extension board to cover body model aerodynamic force, the utility model discloses a face symmetry hypersonic aircraft hood separation wind-tunnel test device's cover body model falls into the three-section, cover body anterior segment promptly, cover body middle section and cover body back end, cover body anterior segment adopts the alloy steel material that has the effect of anti-air current impurity washout, and cover body middle section adopts carbon fiber material integrated into one piece to make and need not use cover body rod-type balance heat insulating sleeve, has increased the inner space in cover body middle section, has promoted cover body model's heat-proof.
The utility model discloses a face symmetry hypersonic aircraft hood separation wind-tunnel test device's projectile body model falls into the three-section, promptly projectile body head, projectile body middle section and projectile body back end, the projectile body head adopts the alloy steel material, the superhard aluminum material is adopted in projectile body middle section, for losing weight and improving the joint strength of projectile body middle section and projectile body back end, projectile body back end has been divided into projectile body tail section and projectile body rod formula balance steel bushing two parts, adopt fixed one whole of interference fit's mode after the processing respectively, projectile body rod formula steel bushing suit is on projectile body rod formula balance heat insulating sleeve, projectile body rod formula balance is protected to projectile body rod formula balance heat insulating sleeve, the joint strength of projectile body back end has been strengthened, it is not hard up to have avoided the in-process projectile body model of blowing. The projectile body bottom cover plate is packaged on the rear end face of the projectile body, and impact of wind tunnel airflow on the projectile body rod type balance is reduced.
The utility model discloses a circumference location is accomplished through positioning channel groove between face symmetry hypersonic aircraft hood separation wind-tunnel test device's the cover body anterior segment and the cover body middle section. The open slot under the middle section of the cover body can ensure that the cover body can be assembled and disassembled smoothly under the condition of welding the switching chamber and the web support plate.
The utility model discloses a face symmetry hypersonic aircraft hood separation wind tunnel test device's pressure regulating orifice plate's aperture is calculated according to jet flow and antechamber total pressure and obtains, and hypersonic wind tunnel test is preceding can open the flow control who realizes the spray tube jet through control hole wall joint inner chamber pressure, and the orifice plate pressure regulating device directly adjusts hole wall joint inner chamber pressure through hypersonic wind tunnel's air supply line system, and the security is better, and repeatability and stability guarantee easily.
The utility model discloses a face symmetry hypersonic aircraft hood separation wind tunnel test device has following advantage:
1. the cover body balance adopts a rod type balance with higher sensitivity, the cover body rod type balance is positioned at the front part of the cover body model, the cover body rod type balance and the spray pipe share one support, and the rear section of the cover body has a larger space for accommodating the head of the projectile body, so that aerodynamic force measurement of the relative position of the small inter-stage distance between the projectile body model and the cover body model is realized, and measurement deviation caused by shortening the head of the projectile body under the small inter-stage distance is avoided. The abdomen supporting plate of the abdomen support adopts a variable cross-section design, the cross-sectional area of the upper part of the abdomen supporting plate is smaller, the cross-sectional area of the lower part of the abdomen supporting plate is gradually increased, and the interference of the abdomen supporting plate is effectively reduced while the strength, the rigidity and the lower resonance frequency are ensured.
2. The upper and lower mechanisms are respectively used as independent supports of the projectile body model and the cover body model to respectively realize independent movement of the projectile body model and the cover body model, so that the postures of the projectile body model and the cover body model can be independently changed, the stage distance between the projectile body model and the cover body model is adjusted, and the test state is convenient to replace.
3. The belly support plate supported by the belly is used as an air supply pipeline of the spray pipe, so that the pneumatic interference of the external air supply pipeline on the projectile body model and the cover body model is avoided.
4. The pressure regulating pore plate is adopted to realize the flow regulation of different jet flows, the pressure of an air supply pipeline system of the hypersonic wind tunnel is improved, and the stability and the safety of flow control are ensured.
The utility model discloses a face symmetry hypersonic aircraft hood separation wind-tunnel test device has solved key technical problem such as two-stage model relative gesture, two-stage model separation distance adjustment, jet flow simulation, small-size balance design and model connection that hypersonic wind-tunnel face symmetry hypersonic aircraft hood separation test faces, has improved the stability of spray tube jet flow, has reduced the interference that the abdomen supported.
Drawings
FIG. 1 is a schematic perspective view of a separation wind tunnel test device for a plane-symmetric hypersonic aircraft hood of the present invention;
FIG. 2 is a schematic plan view of the separation wind tunnel test device for the surface-symmetric hypersonic aircraft hood of the present invention;
FIG. 3 is a schematic view of a cover model in a separation wind tunnel test device for a plane-symmetric hypersonic aircraft hood of the present invention;
FIG. 4 is a schematic view of a positioning slot of a front section of a hood body in a separation wind tunnel test device of a plane-symmetric hypersonic aircraft hood of the present invention;
FIG. 5 is a schematic view of a notch at the middle section of a cover body in the separation wind tunnel test device of the plane-symmetric hypersonic aircraft nose cover of the present invention;
FIG. 6 is a schematic diagram of a projectile body model in the separation wind tunnel test device for the surface-symmetric hypersonic aircraft nose cap of the present invention;
FIG. 7a is a schematic diagram of a cover body model nozzle transfer parking chamber in the separation wind tunnel test device for a plane-symmetric hypersonic aircraft hood of the present invention;
FIG. 7b is a schematic view of the installation of the nozzle transfer parking chamber of the mask body model in the separation wind tunnel test device for the surface-symmetric hypersonic aircraft hood of the present invention;
FIG. 8 is a schematic perspective view of a perforated plate pressure regulating device in a separation wind tunnel test device for a plane-symmetric hypersonic aircraft hood of the present invention;
FIG. 9 is a schematic structural view of a perforated plate pressure regulating device in a separation wind tunnel test device of a plane-symmetric hypersonic aircraft hood of the present invention;
fig. 10 is the enlarged view of the pressure regulating orifice plate of the orifice plate pressure regulating device in the surface-symmetric hypersonic aircraft hood separation wind tunnel test device of the utility model.
In the figure, 1, a cover body model 2, a bullet body model 3, a belly support 4, an orifice plate pressure regulating device 5 and a tail support rod are arranged;
101. the shield comprises a shield front section 102, a shield middle section 103, a shield rear section 104, a shield rod balance 105, a shield rod balance positioning flat key 106, a shield rod balance connecting wedge key 107, a shield front section positioning clamping groove 108 and a shield middle section notch;
201. the balance comprises a projectile head 202, a projectile middle section 203, a projectile rear section 204, a projectile bottom cover plate 205, a projectile rod type balance steel sleeve 206, a projectile rod type balance heat insulation sleeve 207 and a projectile rod type balance;
301. the jet pipe adapter chamber 302, the jet flow pressure regulating interface plug 303, the jet pipe 304, the web support plate 305, the cover body rod type balance interface 306, the web support base 307 and the air inlet pipeline interface;
401. the copper pipe 402, the compression nut 403, the pressure regulating orifice plate 404 and the hole wall joint.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1 and 2, the utility model discloses a separation wind tunnel test device of face symmetry hypersonic aircraft hood, its characterized in that: the testing device comprises a projectile body model 2 supported by a tail support rod 5 of the upper hypersonic wind tunnel mechanism and a cover body model 1 supported by a belly support 3 of the lower hypersonic wind tunnel mechanism; in an initial state, the cover body model 1 covers the head of the bullet body model 2 and is separated from and not contacted with the bullet body model 2; in a test state, the cover body model 1 and the projectile body model 2 are separated and move relatively independently; the cover body model 1 adopts a rod type six-component balance to measure the aerodynamic force of the cover body model 1, and spray pipes are symmetrically arranged on the left and right of the cover body model 1 to simulate the jet flow of the spray pipes; the bomb model 2 adopts a rod type six-component balance to measure the aerodynamic force of the bomb model 2; the belly support 3 is communicated with a pore plate pressure regulating device 4.
As shown in fig. 3, the cover model 2 includes a cover front section 101, a cover middle section 102 and a cover rear section 103; the hood rod type balance 104 is arranged in the hood middle section 102, is fixed on a balance interface of the belly support plate 3 through a hood rod type balance connecting wedge key 106 and is positioned through a hood rod type balance positioning flat key 105; as shown in fig. 4, the cover front section 101 and the cover middle section 102 are positioned by a cover front section positioning slot 107; as shown in fig. 5, a cover middle notch 108 is formed below the cover middle section 102, and the web support plate 3 passes through the cover middle notch 108 and enters the cover middle section 102.
As shown in fig. 6, the projectile model 2 includes a projectile head 201, a projectile middle section 202, a projectile rear section 203 and a projectile bottom cover plate 204; the elastic body rod type balance 207 is positioned in the elastic body rear section 203, the rear end of the elastic body rod type balance 207 is fixed on the tail support rod 5, and the elastic body rod type balance heat insulation sleeve 206 is arranged on the front end conical surface of the elastic body rod type balance 207; the rear section 203 of the elastomer is arranged on the front end conical surface of the elastomer rod type balance 207 through an elastomer rod type balance steel sleeve 205 and an elastomer rod type balance heat insulation sleeve 206; the sensing element of the elastic rod type balance 207 is wrapped by the elastic rod type balance heat insulation sleeve 206, so that the elastic rod type balance has a heat insulation protection effect; the elastic body rod type balance heat insulation sleeve 206 is wrapped by the elastic body rod type balance steel sleeve 205, and the elastic body rod type balance heat insulation sleeve has the function of increasing the connection strength of the elastic body rod type balance 207 and the elastic body middle section 202.
As shown in fig. 7a and 7b, the upper end of the abdomen support plate 304 of the abdomen support 3 extends into the cover body middle section 102, and the abdomen support base 306 at the lower end of the abdomen support plate 304 is fixed on the lower mechanism of the hypersonic wind tunnel; the upper end of the web support plate 304 is provided with a nozzle transfer parking chamber 301, the front end of the nozzle transfer parking chamber 301 is provided with a cover body rod type balance interface 305, and the middle part of the nozzle transfer parking chamber 301 is respectively communicated with an air inlet pipeline in the nozzle 303 and the web support plate 304; before the hypersonic wind tunnel test, a pressure sensor is arranged at the rear end of the nozzle transfer parking chamber 301, and the pressure of the nozzle transfer parking chamber 301 is measured; during a hypersonic wind tunnel test, a pressure sensor at the rear end of the spray pipe transfer parking chamber 301 is dismounted, and a jet flow pressure regulating interface plug 302 is replaced; an air inlet pipeline interface 307 is arranged below the abdominal plate 304 and close to the abdominal support base 306.
As shown in fig. 8 and 9, the orifice plate pressure regulating device 4 is installed on a tunnel wall of a hypersonic wind tunnel, a cavity is formed in a tunnel wall joint 404 of the orifice plate pressure regulating device 4, and the cavity is respectively communicated with a copper tube 401 and an air supply pipeline system of the hypersonic wind tunnel; one end of the red copper pipe 401 is connected with an air inlet pipeline interface 307 of the spray pipe 303, and the other end of the red copper pipe 401 is communicated with a cavity of the hole wall joint 404; the interface of the copper tube 401 is pressed on the hole wall joint 404 through a compression nut 402; a pressure regulating pore plate 403 is arranged at the interface of the red copper pipe 401 and the hole wall joint 404; a pressure sensor is mounted on the hole wall joint 404 to measure the pressure in the cavity of the hole wall joint 404.
The front cover part 101 is made of alloy steel, and the middle cover part 102 is made of carbon fiber in an integrated forming mode; the cross section of the hood rod balance 104 is in a variable cross section shape which is matched with the inner space of the hood middle section 102 and is small at the top and big at the bottom; two sides of the cover body rod type balance positioning flat key 105 are provided with symmetrical series of clamping grooves.
The projectile body head 201 is made of alloy steel, and the projectile body middle section 202 is made of superhard aluminum.
The nozzles 303 are symmetrically arranged on two sides of the cover body middle section 102.
As shown in fig. 10, the pressure-regulating orifice plate 403 is a flat plate with an opening in the middle, and sealing gaskets are installed on two sides of the pressure-regulating orifice plate 403.
Furthermore, the opening of the pressure regulating pore plate 403 is square; the sealing washer is a red copper sealing washer.
Example 1
When the concrete implementation, the utility model discloses a face symmetry hypersonic aircraft hood separation wind-tunnel test device installs strutting arrangement at first, installs jet flow unit again, waits to accomplish jet flow pressure debugging back, installs projectile body model and cover body model, constitutes complete testing arrangement.
The method comprises the following steps:
1. assembling the jet flow device: the nozzle 303, the belly support 3 and the orifice plate pressure regulating device 4 are installed first. The ventral support base 306 is first connected with the lower mechanism base, positioned by two pins, connected and locked by 8 screws, and the attack angle mechanism is adjusted to 0 degree attack angle. The orifice plate pressure regulating device 4 is installed, and the installation sequence is as follows: a red copper gasket is added on a hole wall joint 404, then the hole wall joint is connected with an air supply pipeline joint reserved on the hole wall, a pressure regulating hole plate 403 is arranged between a red copper pipe 401 and the hole wall joint 404 and inside a compression nut 402, and then the compression nut 402 is connected. The other end of the copper tube is connected with an air inlet pipeline interface 307 at the lower end of the abdomen support 3, and a sealing gasket is arranged inside the copper tube. Since the nozzle 303, the nozzle adapter 301 and the web plate 304 are welded at their upper ends, the connection of the entire jet line is completed.
2. And (3) adjusting jet flow pressure, namely, before pressure adjustment is started, respectively installing a pressure adjusting sensor and a hole wall detection sensor to an M8 × 1 threaded hole at the rear end of the spray pipe transfer parking chamber 301 and the side surface of the hole wall joint 404, trying to ventilate, checking whether the air supply pipeline and the jet flow pipeline leak air, adjusting the hole wall monitoring pressure and the total pressure of the parking chamber to target values by adjusting the air source pressure of the hole wall, namely, fixing the opening degree of a jet flow valve, repeating for 5-7 times, and completing the jet flow pressure adjustment after the requirement of repeatability precision is met.
3. Mounting a cover model: the cover body model 1 is ready to be installed, the pressure regulating sensor is removed before installation, and the jet flow pressure regulating interface plug 302 is installed. The hood rod balance 104 is installed firstly, the rear end of the hood rod balance is matched with the nozzle transfer parking chamber 301 according to the 1:10 taper, and the hood rod balance is tightly pressed to be connected with the wedge key 106. The middle section 102 of the cover body is installed, a cover body rod type balance positioning flat key 105 is added, and a brass washer and a locking nut are added. The front section 101 of the cover body is installed, the clamping groove is positioned, and finally the cover body is connected through screws. The rear cover section 103 is directly butted with the middle cover section 102, and the surface symmetry model has a self-positioning effect and can be connected by four screws. The mounting of the cover model 1 is thus completed.
4. Installing the projectile body model: the tail strut 5 is mounted to the upper mechanism first. A spring rod type balance 207 is installed and locked by a flat key positioning wedge key. Installing a projectile rod type balance heat insulation sleeve 206, a projectile rear section 203, a connecting nut, a projectile middle section 202 and a projectile head 201, and finally installing a projectile bottom cover plate 204. After the installation is finished, whether the roll angle and the attack angle of the projectile body model 2 are zero or not is detected, and if not, the projectile body model is adjusted to a zero position.
5. Adjusting the relative positions of the cover body model and the projectile body model: firstly, the posture of the cover body model 1 is adjusted to the right position through the lower mechanism, then the upper mechanism is adjusted to keep the posture angles of the projectile body model 2 and the cover body model 1 consistent, and then the relative position is adjusted under the small-step distance, so that the projectile body model 2 and the cover body model 1 are coaxial. And adjusting the grade distance after coaxiality, detecting whether the grade distance is in place by using a feeler gauge for small grade distance, a caliper gauge for large grade distance and the like, and finally rotating the projectile body model 2 by a specified angle around a mass center or a specified coordinate point.
For larger angles of attack, possibly beyond the lower mechanism angle of attack range, the web support 3 can be preset to the angle of attack to achieve a larger angle of attack model state. Because the plane symmetry model comprises the spray pipes which have the vertical symmetry characteristic, the positive attack angle can be converted into the negative attack angle, at the moment, the cover body model 1 lowers the head, the belly support 3 is positioned below the projectile body model 2 and is far away from the projectile body model 2, and the aerodynamic interference to the projectile body model 2 is small or even no interference.
6. In the plane-symmetric hypersonic aircraft hood separation wind tunnel test of the hypersonic wind tunnel, wind tunnel incoming flow parameters are obtained by calculation according to a given simulation height and are realized by controlling the total pressure and the total temperature of the incoming flow of the wind tunnel. The jet flow pressure ratio, the momentum ratio and the approximate expansion boundary simulation are realized by adjusting the pressure of a jet flow air source to a pressure debugging pressure according to jet flow parameters, and a pressure detection sensor is arranged on the wall of the hole to monitor the jet flow pressure change in the test process.
Claims (10)
1. The utility model provides a separation wind tunnel test device of face symmetry hypersonic aircraft hood which characterized in that: the testing device comprises a projectile body model (2) supported by a tail support rod (5) of the upper hypersonic wind tunnel mechanism and a cover body model (1) supported by a belly support (3) of the lower hypersonic wind tunnel mechanism; in an initial state, the cover body model (1) covers the head of the bullet body model (2) and is separated from and not contacted with the bullet body model (2); in a test state, the cover body model (1) and the projectile body model (2) are separated and move relatively independently; the cover body model (1) adopts a rod-type six-component balance to measure aerodynamic force of the cover body model (1), and spray pipes are symmetrically arranged on the left and right of the cover body model (1) to simulate spray flow of the spray pipes; the bomb model (2) adopts a rod type six-component balance to measure the aerodynamic force of the bomb model (2); the belly support (3) is communicated with the pore plate pressure regulating device (4).
2. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 1, characterized in that: the cover model (1) comprises a cover front section (101), a cover middle section (102) and a cover rear section (103); the hood rod type balance (104) is arranged in the hood middle section (102), is fixed on a balance interface of the abdomen support (3) through a hood rod type balance connecting wedge key (106), and is positioned through a hood rod type balance positioning flat key (105); the cover body front section (101) and the cover body middle section (102) are positioned through a cover body front section positioning clamping groove (107); a cover body middle section notch (108) is formed in the lower portion of the cover body middle section (102), and the abdomen support (3) penetrates through the cover body middle section notch (108) to enter the cover body middle section (102).
3. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 1, characterized in that: the projectile body model (2) comprises a projectile body head (201), a projectile body middle section (202), a projectile body rear section (203) and a projectile body bottom cover plate (204); the elastic body rod type balance (207) is positioned in the elastic body rear section (203), the rear end of the elastic body rod type balance (207) is fixed on the tail support rod (5), and the elastic body rod type balance heat insulation sleeve (206) is arranged on the conical surface of the front end of the elastic body rod type balance (207); the rear section (203) of the elastomer is arranged on the conical surface of the front end of the elastomer rod type balance (207) through an elastomer rod type balance steel sleeve (205) and an elastomer rod type balance heat insulation sleeve (206); the sensing element of the elastic rod type balance (207) is wrapped by the elastic rod type balance heat insulation sleeve (206) and has the heat insulation protection function; the elastic body rod type balance heat insulation sleeve (206) is wrapped by the elastic body rod type balance steel sleeve (205), and the elastic body rod type balance heat insulation sleeve has the function of increasing the connection strength of the elastic body rod type balance (207) and the elastic body middle section (202).
4. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 1, characterized in that: the upper end of an abdomen support plate (304) of the abdomen support (3) extends into the middle section (102) of the cover body, and an abdomen support base (306) at the lower end of the abdomen support plate (304) is fixed on a lower mechanism of the hypersonic wind tunnel; the upper end of the belly support plate (304) is provided with a spray pipe transfer chamber (301), the front end of the spray pipe transfer chamber (301) is provided with a cover body rod type balance interface (305), and the middle part of the spray pipe transfer chamber (301) is respectively communicated with an air inlet pipeline in the spray pipe (303) and the belly support plate (304); before the hypersonic wind tunnel test, a pressure sensor is arranged at the rear end of the spray pipe transfer parking chamber (301) to measure the pressure of the spray pipe transfer parking chamber (301); during a hypersonic wind tunnel test, a pressure sensor at the rear end of the spray pipe transfer parking chamber (301) is dismounted, and a jet flow pressure regulating interface plug (302) is replaced; an air inlet pipeline interface (307) is arranged below the abdomen support plate (304) and close to the abdomen support base (306).
5. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 1, characterized in that: the orifice plate pressure regulating device (4) is arranged on the wall of the hypersonic wind tunnel, a cavity is formed in a tunnel wall joint (404) of the orifice plate pressure regulating device (4), and the cavity is respectively communicated with a copper tube (401) and an air supply pipeline system of the hypersonic wind tunnel; one end of the red copper pipe (401) is connected with an air inlet pipeline interface (307) of the spray pipe (303), and the other end of the red copper pipe (401) is communicated with a cavity of the hole wall joint (404); the interface of the copper tube (401) is pressed on the hole wall joint (404) through a compression nut (402); a pressure regulating pore plate (403) is arranged at the interface of the red copper pipe (401) and the hole wall joint (404); a pressure sensor is arranged on the hole wall joint (404) to measure the pressure in the cavity of the hole wall joint (404).
6. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 2, characterized in that: the front cover body section (101) is made of alloy steel, and the middle cover body section (102) is made of carbon fiber in an integrated forming mode; the cross section of the hood rod balance (104) is in a variable cross section shape which is matched with the inner space of the hood middle section (102) and is small at the top and big at the bottom; two sides of the cover body rod type balance positioning flat key (105) are provided with symmetrical series of clamping grooves.
7. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 3, characterized in that: the projectile body head (201) is made of alloy steel, and the projectile body middle section (202) is made of superhard aluminum.
8. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 4, characterized in that: the spray pipes (303) are symmetrically arranged on two sides of the middle section (102) of the cover body.
9. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 5, characterized in that: the pressure regulating pore plate (403) is a flat plate with a hole in the middle, and sealing gaskets are arranged on two sides of the pressure regulating pore plate (403).
10. The separation wind tunnel test device for the plane-symmetric hypersonic aircraft nose cover according to claim 9, characterized in that: the shape of the opening of the pressure regulating pore plate (403) is square; the sealing washer is a red copper sealing washer.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113588200A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-flow reverse jet test device and method for hypersonic aircraft |
| CN114509234A (en) * | 2022-04-20 | 2022-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flexible pipeline device for mixed heating gas jet flow gas supply of hypersonic wind tunnel |
| CN115436010A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet pipe thrust measurement test method based on afterbody and jet pipe integrated design |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113588200A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-flow reverse jet test device and method for hypersonic aircraft |
| CN114509234A (en) * | 2022-04-20 | 2022-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flexible pipeline device for mixed heating gas jet flow gas supply of hypersonic wind tunnel |
| CN115436010A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet pipe thrust measurement test method based on afterbody and jet pipe integrated design |
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