CN114279671B - Method for designing low-Mach-number total-enthalpy flight platform based on existing hypersonic wind tunnel - Google Patents
Method for designing low-Mach-number total-enthalpy flight platform based on existing hypersonic wind tunnel Download PDFInfo
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Abstract
The invention belongs to the field of hypersonic wind tunnel test equipment and discloses a method for designing a low-Mach-number total-enthalpy flight platform based on an existing hypersonic wind tunnel. The method utilizes the existing hypersonic wind tunnels with different apertures to carry out corresponding matching of a spray pipe and a stable section with a transition section and a diffuser, so as to build a low-Mach number 2-4 range flight total enthalpy wind tunnel test platform of the recurrent aircraft with different apertures, wherein the simulated total temperature range is 390K-950K, the simulated height is 15-30 kilometers, the effective operation time of the test platform is more than or equal to 30 seconds, and the requirements of carrying out basic theory and test technology researches on engine combination dynamic performance test, internal and external flow integrated force and heat coupling test of the aircraft, pneumatic thermal load test of the aircraft and the like under the low Mach number of the aircraft are met, and special tests and verifications are carried out, so that test data and test verification support are provided for aircraft development.
Description
Technical Field
The invention belongs to the field of hypersonic wind tunnel test equipment, and particularly relates to a method for designing a low-Mach-number total-enthalpy-of-flight platform based on an existing hypersonic wind tunnel.
Background
In the early stage, the main measurement of the wind tunnel test carried out by the supersonic aircraft is the aerodynamic characteristics (aerodynamic force, flight attitude, aerodynamic shape and the like) or performance of the aircraft, and the wind tunnel operation needs to meet the total temperature requirement because in the supersonic speed or hypersonic speed wind tunnel using air as a test medium, the airflow is violently expanded through a spray pipe, so that the static temperature of the airflow is rapidly reduced. If the temperature of the air flow in the stable section of the wind tunnel is 288K when M is more than or equal to 5, the temperature of the air flow in the test section of the wind tunnel is reduced to 48K, and at the low temperature, the air is condensed, and condensation heat is released along with the condensation and transferred to the air flow, so that the air flow becomes flow with unequal entropy. In addition, because the condensation is uneven, the flow field is uneven, and the test data is inaccurate. To suppress air condensation, the total temperature of the air flow in the stable section needs to be increased. Therefore, a heater needs to be added to the hypersonic wind tunnel using air as a medium, which is the most common method for the hypersonic wind tunnel.
In fact, when the aircraft test is carried out in the conventional hypersonic wind tunnel, the temperature in the test section is different from the atmospheric temperature of the flight environment, and the ground test condition of the aircraft is different from the actual flight environment.
With the development of high temperature materials and high performance propulsion systems, aircraft have become feasible for supersonic or hypersonic flight. Thus, with the development of aircraft, in particular missiles or manned aircraft, new gas thermodynamic problems arise.
The advanced aircraft can stably and durably fly at the flight speed of Mach 3, a wind tunnel test platform capable of simulating the total temperature exceeding 644K is needed, and a wind tunnel test platform capable of simulating the total temperature exceeding 866K is needed for the aircraft to fly at the flight speed of Mach 4. In this state, in addition to significant thermal structural problems, other problems arise, such as radome or infrared fairing ablated structure failure, ground sensor signal transmission misinterpretation, and missile mission failure. On the other hand, in the case of corrosion of the aircraft in a high-temperature environment for a long time, the output signal of an actuator, such as a battery, in the aircraft interior is weakened. The thermal load of an aircraft in a critical environment is a complex combination of convective, conductive, and radiative heat transfer. Aircraft structures composed of complex outer lines and composite materials may result in failure to provide convincing reliable numerical evaluations and therefore ground tests are to be carried out to achieve the same flight environment and conditions.
At present, a conventional hypersonic wind tunnel with the magnitude levels of phi 0.5 meter, phi 1 meter and phi 2 meter simulates the Mach number range of 3-10. The conventional hypersonic wind tunnel forms a large, medium and small matched test capacity system, has reasonable size, is necessary for simulating the flight Mach number, local pressure, flight angle and the like of an aircraft, and cannot simulate the local total break under the real flight state.
Therefore, the existing hypersonic wind tunnel is utilized to build a recurrent total enthalpy ground wind tunnel test platform which has long running time and adopts clean air as an incoming flow medium through proper local transformation, so that the simulation of the low-Mach number aircraft on the real environment temperature and the environment pressure is feasible.
At present, a method for designing a low-mach-number total enthalpy of flight platform based on the existing hypersonic wind tunnel is urgently needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for designing a low-Mach-number total-enthalpy flight platform based on the existing hypersonic wind tunnel, and aims to properly improve and transform the local total enthalpy of an aircraft flying at a low Mach number on the conventional hypersonic wind tunnel by utilizing an air source system, a high-temperature heater and a power system of the existing conventional hypersonic wind tunnel, finally achieve the aim of reproducing the local total enthalpy of the aircraft flying at the low Mach number on the conventional hypersonic wind tunnel, meet the requirements of carrying out ground special tests on the aircraft on engine combined power performance test at the low Mach number, aircraft internal and external flow integrated force thermal coupling test, aerodynamic heat load test and the like, and provide support aircraft development data and ground test verification.
The invention discloses a method for designing a low-Mach total enthalpy of flight platform based on the existing hypersonic wind tunnel, which is characterized by comprising the following steps of:
s10, planning a low-Mach-number flight total enthalpy platform;
dividing the caliber of a spray pipe of the existing hypersonic velocity high wind tunnel into a phi 0.5 meter magnitude, a phi 1 meter magnitude and a phi 2 meter magnitude, and planning and respectively establishing corresponding low-Mach-number total-enthalpy flight platforms, specifically phi 0.3 meter, phi 0.5 meter and phi 1 meter magnitude low-Mach-number total-enthalpy flight platforms;
the low-Mach-number flight total enthalpy platform below the phi 0.5 meter magnitude level is used for testing the combined dynamic performance of a low-Mach-number aircraft, testing the internal and external flow integrated force-heat coupling of the aircraft and testing the aerodynamic heat load, and developing theoretical foundation research and experimental technology research;
the phi 1-meter-magnitude low-Mach-number total-enthalpy flight platform is used for theoretical foundation research, test technology research, special test and verification required by engineering development of a low-Mach-number aircraft;
s20, determining an operation mode, a heating mode and a test medium of the low-Mach-number total-enthalpy flight platform;
the wind tunnel test platform with low Mach number flight total enthalpy adopts an operation driving mode of blowing under high pressure and vacuum suction, adopts a metal plate heat storage type heater or a tubular electric adder to heat a test medium, and adopts high-pressure pure air as the test medium;
s30, determining a simulation technical index of a low-Mach-number flight total enthalpy platform;
the total simulation technical indexes are as follows:
the low-Mach-number total-enthalpy flight platform achieves Mach number of 2-4, simulation temperature of 390K-950K, simulation height of 15-30 kilometers and effective operation time of the test platform is more than or equal to 30 seconds;
and (3) segmental simulation technical indexes:
the method comprises the steps of utilizing an existing wind tunnel Mach 8 heater to achieve a ground simulation test within the Mach 2-3 range with the highest pressure of 8.0MPa and the highest temperature of 800K, and achieving technical indexes of simulation height of 15-30 kilometers, the highest total pressure of 0.5MPa and the highest total temperature of 634K;
the method comprises the steps of utilizing an existing wind tunnel Mach number 10 heater, enabling the highest pressure to be 12.0MPa and the highest temperature to be 1082K, achieving a ground simulation test within the Mach number range of 3.5-4, and achieving technical indexes of simulation height of 17-30 kilometers, highest total pressure to be 1.5MPa and highest total temperature to be 950K;
s40, determining original equipment and a matched system which need to be reserved for the low-Mach-number flight total enthalpy platform;
the method comprises the following steps of reserving the conventional hypersonic wind tunnel plant, the conventional wind tunnel high-pressure air source system, the conventional wind tunnel Mach number 8 heater, the conventional wind tunnel Mach number 10 heater, the conventional wind tunnel Mach number 8 thermal valve, the conventional wind tunnel Mach number 10 thermal valve, the conventional wind tunnel equipment supporting device, the conventional wind tunnel test section, the conventional wind tunnel diffuser, the cooler, the wind tunnel measurement and control system and the model mechanism system; the method comprises the steps that the rapid establishment and operation of a flow field of a low-Mach-number total-enthalpy flight platform are realized by utilizing an existing wind tunnel high-pressure air source system, a power supply and distribution system, an operation control system, a vacuum system or an injection system and a cooling water supply system in an existing conventional hypersonic wind tunnel power system; the data acquisition and processing of the low-Mach-number total-enthalpy-of-flight platform are completed by utilizing a data acquisition system and a schlieren system of the conventional hypersonic wind tunnel;
s50, determining newly-added equipment of a low-Mach-number total-enthalpy-of-flight platform;
s51, a spray pipe;
the nozzle is divided into two mach number scales: the spray pipes with the Mach numbers of 2-3 and the spray pipes with the Mach numbers of 3.5-4, wherein the Mach number set points of the single-point Mach number spray pipe are Mach numbers of 2, 2.5, 3, 3.5 and 4;
s52, a stabilizing section and a transition section;
corresponding to the spray pipe, the stable section and the transition section are divided into two Mach number scales: a Mach number 2-3 stable section and a transition section, and a Mach number 3.5-4 stable section and a transition section;
the size of a front end interface of the stabilizing section is consistent with that of a corresponding hot valve interface on the heater, the flow speed range in the stabilizing section is 5 m/s-30 m/s, and the diameter size of the stabilizing section is determined according to the flow speed range; the heat insulation layers and the corresponding flow equalizing devices are designed in the stabilizing section and the transition section, and the water cooling jackets are arranged outside the stabilizing section and the transition section;
s53, connecting sections;
corresponding to the spray pipes, arranging a connecting section of a new spray pipe with Mach number of 2-3 and the original test section and a connecting section of a new spray pipe with Mach number of 3.5-4 and the original test section;
s54, a platform diffuser;
the method comprises the following steps that a platform diffuser matched with the diffuser is arranged, the platform diffuser is sleeved in an inner cavity of the diffuser of the existing hypersonic wind tunnel through a dismounting device, and the platform diffuser and the diffuser are the same as the central axis; determining the diameter of a second throat of the platform diffuser, the size of an inlet of the platform diffuser and the total length of the platform diffuser according to the starting pressure ratio of the low-Mach-number total-enthalpy flight platform;
s55, overall requirements of each component are met;
in order to ensure that the newly added equipment can be installed at the corresponding position of the existing hypersonic speed, the sum of the length of each single-point Mach number spray pipe, the length of the corresponding connecting section and the length of the corresponding stable section and the length of the corresponding transition section are equal, namely the total lengths are equal.
Furthermore, the single-point Mach number nozzle is an axisymmetric profile fixed-wall nozzle;
when the diameter of the outlet of the single-point Mach number nozzle is less than or equal to phi 0.5m, a martensite or austenite stainless steel forging is selected for manufacturing, and a water cooling structure is not arranged;
when the diameter of the outlet of the single-point Mach number nozzle is larger than 0.5m, the throat section of the single-point Mach number nozzle is made of a martensite or austenite stainless steel forging and is provided with a water cooling structure; the single-point Mach number nozzle diffusion section is made of a martensitic stainless steel plate, an austenitic stainless steel plate coil, a martensitic stainless steel forging or an austenitic stainless steel forging, and is not provided with a water cooling structure.
The method for designing the low-Mach-number total-enthalpy-of-flight platform based on the existing hypersonic wind tunnel has the following advantages:
1. the wind tunnel test platform for reproducing the total enthalpy of flight with the low Mach number built by the method fully utilizes the high-temperature pure air test airflow of the existing hypersonic wind tunnel, and meets special test requirements which cannot be developed by the existing hypersonic wind tunnel, such as performance test, internal and external flow integrated force thermal coupling, aerodynamic thermal load and the like of an aircraft combined power aircraft facing the Mach number of 2-4;
2. the wind tunnel test platform for reproducing the total enthalpy of flight with the low Mach number built by the method can utilize equipment facilities of the existing hypersonic wind tunnel, quickly realize the ground simulation of the total enthalpy of flight with the low Mach number of the reproducing aircraft on the premise of not changing the structure, the performance and the operation rule of the existing hypersonic wind tunnel, and meet the ground facility condition guarantee required by the development test of the low Mach number aircraft.
3. By adopting the method, the investment efficiency of the existing hypersonic velocity high wind tunnel can be further improved, the test capability range of the existing hypersonic velocity high wind tunnel is expanded, and the test capability system of the hypersonic velocity wind tunnel is improved.
4. Compared with the method for rebuilding a set of full-system device, the wind tunnel test platform built by the method for reproducing the low-Mach number total flight enthalpy can greatly reduce the investment cost and form the test capability more quickly.
The method for designing the low-Mach-number total-enthalpy-of-flight platform based on the existing hypersonic wind tunnel can make full use of the established conventional hypersonic wind tunnels with different apertures to carry out corresponding low-Mach-number profile spray pipes to be matched with the stable sections to establish the recurrent low-Mach-number total-enthalpy-of-flight wind tunnel test platforms with different apertures, and meets the requirements of special test research and aircraft verification.
Drawings
FIG. 1 is a schematic diagram of a conventional hypersonic wind tunnel utilizing a main body device;
FIG. 2 is a wind tunnel test platform for reproducing Mach number 2-3 total enthalpy of flight in embodiment 1;
FIG. 3 is a wind tunnel test platform for reproducing Mach number 3.5-4 total enthalpy of flight in embodiment 2.
In the figure, 1, a high-pressure air source system of a wind tunnel is in existence; 2. the prior wind tunnel Mach number 8 heater; 3. the prior wind tunnel Mach number 10 heater; 4. the prior wind tunnel Mach 8 thermal valve; 5. the prior wind tunnel Mach number 10 thermal valve; 6. existing wind tunnel equipment support devices; 7. an existing wind tunnel test section; 8. existing wind tunnel diffusers; 9. a Mach number 2-3 stabilizing section and a transition section; 10. a Mach number of 2-3 spray pipes; 11. connecting sections of new spray pipes with Mach numbers of 2-3 and the original test sections; 12. a platform diffuser; 13. a Mach number of 3.5-4 of a stable section and a transition section; 14. a spray pipe with the Mach number of 3.5-4; 15. and connecting the new spray pipe with the Mach number of 3.5-4 with the original test section.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The invention discloses a method for designing a low-Mach-number total-enthalpy flight platform based on an existing hypersonic wind tunnel, which comprises the following steps of:
s10, planning a low-Mach-number flight total enthalpy platform;
dividing the caliber of a spray pipe of the existing hypersonic velocity high wind tunnel into a phi 0.5 meter magnitude, a phi 1 meter magnitude and a phi 2 meter magnitude, and planning and respectively establishing corresponding low-Mach-number total-enthalpy flight platforms, specifically phi 0.3 meter, phi 0.5 meter and phi 1 meter magnitude low-Mach-number total-enthalpy flight platforms;
the low-Mach-number flight total enthalpy platform below the phi 0.5 meter magnitude level is used for testing the combined dynamic performance of a low-Mach-number aircraft, testing the internal and external flow integrated force-heat coupling of the aircraft and testing the aerodynamic heat load, and developing theoretical foundation research and experimental technology research;
the phi 1-meter-magnitude low-Mach-number total-enthalpy flight platform is used for theoretical basis research, test technology research, special tests and verification required by engineering development of a low-Mach-number aircraft;
s20, determining an operation mode, a heating mode and a test medium of the low-Mach-number total-enthalpy flight platform;
the wind tunnel test platform with low Mach number flight total enthalpy adopts an operation driving mode of blowing under high pressure and vacuum suction, adopts a metal plate heat storage type heater or a tubular electric adder to heat a test medium, and adopts high-pressure pure air as the test medium;
s30, determining a simulation technical index of a low-Mach-number flight total enthalpy platform;
the total simulation technical indexes are as follows:
the low-Mach-number total-enthalpy flight platform achieves Mach number of 2-4, simulation temperature of 390K-950K, simulation height of 15-30 kilometers and effective operation time of the test platform is more than or equal to 30 seconds;
and (3) segmental simulation technical indexes:
the method comprises the steps of utilizing an existing wind tunnel Mach number 8 heater 2, the highest pressure 8.0MPa and the highest temperature 800K to realize a ground simulation test within the Mach number 2-3 range, and realizing technical indexes of simulation height of 15-30 kilometers, the highest total pressure of 0.5MPa and the highest total temperature of 634K;
the method comprises the steps of utilizing an existing wind tunnel Mach number 10 heater 3, the highest pressure 12.0MPa and the highest temperature 1082K to realize a ground simulation test with a Mach number of 3.5-4, and realizing technical indexes of a simulation height of 17-30 kilometers, a highest total pressure of 1.5MPa and a highest total temperature of 950K;
s40, determining original equipment and a matched system which need to be reserved for the low-Mach-number flight total enthalpy platform;
as shown in fig. 1, the existing hypersonic wind tunnel plant, the existing wind tunnel high-pressure air source system 1, the existing wind tunnel mach number 8 heater 2, the existing wind tunnel mach number 10 heater 3, the existing wind tunnel mach number 8 thermal valve 4, the existing wind tunnel mach number 10 thermal valve 5, the existing wind tunnel equipment supporting device 6, the existing wind tunnel test section 7, the existing wind tunnel diffuser 8, the cooler, the wind tunnel measurement and control system and the model mechanism system are reserved; the method comprises the steps that the rapid establishment and operation of a flow field of a low-Mach-number total-enthalpy flight platform are realized by utilizing an existing wind tunnel high-pressure air source system 1, a power supply and distribution system, an operation control system, a vacuum system or an injection system and a cooling water supply system in an existing conventional hypersonic wind tunnel power system; the data acquisition and processing of the low-Mach-number total-enthalpy-of-flight platform are completed by utilizing a data acquisition system and a schlieren system of the conventional hypersonic wind tunnel;
s50, determining newly-added equipment of a low-Mach-number total-enthalpy flight platform;
s51, a spray pipe;
the nozzle is divided into two mach number scales: the jet pipe 10 with Mach number of 2-3 and the jet pipe 14 with Mach number of 3.5-4, wherein the Mach number set points of the single-point Mach number jet pipe are Mach numbers of 2, 2.5, 3, 3.5 and 4;
s52, a stabilizing section and a transition section;
corresponding to the spray pipe, the stable section and the transition section are divided into two Mach number scales: a Mach number 2-3 stable section and a transition section 9, and a Mach number 3.5-4 stable section and a transition section 13;
the size of a front end interface of the stabilizing section is consistent with that of a corresponding hot valve interface on the heater, the flow speed range in the stabilizing section is 5 m/s-30 m/s, and the diameter size of the stabilizing section is determined according to the flow speed range; the heat insulation layers and the corresponding flow equalizing devices are designed in the stabilizing section and the transition section, and the water cooling jackets are arranged outside the stabilizing section and the transition section;
s53, connecting sections;
corresponding to the spray pipes, arranging a new spray pipe and original test section connecting section 11 with Mach number of 2-3 and a new spray pipe and original test section connecting section 15 with Mach number of 3.5-4;
s54, a platform diffuser;
a platform diffuser 12 matched with the diffuser 8 is arranged, the platform diffuser 12 is sleeved in an inner cavity of the diffuser 8 of the existing hypersonic wind tunnel through a dismounting device, and the platform diffuser 12 and the diffuser 8 have the same central axis; determining the diameter of a second throat of the platform diffuser 12, the size of an inlet of the platform diffuser 12 and the total length of the platform diffuser 12 according to the starting pressure ratio of the low-Mach-number total-enthalpy flight platform;
s55, overall requirements of each component are met;
in order to ensure that the newly added equipment can be installed at the corresponding position of the existing hypersonic speed, the sum of the length of each single-point Mach number spray pipe, the length of the corresponding connecting section and the length of the corresponding stable section and the length of the corresponding transition section are equal, namely the total lengths are equal.
Furthermore, the single-point Mach number nozzle is an axisymmetric profile fixed-wall nozzle;
when the diameter of the outlet of the single-point Mach number nozzle is less than or equal to phi 0.5m, a martensite or austenite stainless steel forging is selected for manufacturing, and a water cooling structure is not arranged;
when the diameter of the outlet of the single-point Mach number nozzle is larger than 0.5m, the throat section of the single-point Mach number nozzle is made of a martensite or austenite stainless steel forging and is provided with a water cooling structure; the single-point Mach number spray pipe diffusion section is made of a martensitic stainless steel plate, an austenitic stainless steel plate coil, a martensitic stainless steel forging or an austenitic stainless steel forging, and is not provided with a water cooling structure.
Example 1
The embodiment is a wind tunnel test platform for reproducing Mach number 2-3 total flight enthalpy.
As shown in fig. 2, in the embodiment, an existing wind tunnel mach number 8 heater 2 is selected to establish a wind tunnel test platform which reproduces mach numbers 2-3 of total flight enthalpy. On the existing wind tunnel equipment supporting device 6, an existing wind tunnel high-pressure air source system 1, an existing wind tunnel Mach number 8 thermal valve 4, a Mach number 2-3 stabilizing section and transition section 9, Mach number 2-3 spray pipes 10, a new spray pipe and original test section connecting section 11 of Mach number 2-3, an existing wind tunnel test section 7 and an existing wind tunnel diffuser 8 are sequentially connected, and a platform diffuser 12 is installed in an inner cavity of the existing wind tunnel diffuser 8 in a sleeved mode.
Example 2
The embodiment is a wind tunnel test platform for reproducing the total flight enthalpy of Mach number 3.5-4.
As shown in fig. 3, in the embodiment, an existing wind tunnel mach number 10 heater 3 is selected to establish a wind tunnel test platform which reproduces mach numbers 2-3 of total flight enthalpy. The method is characterized in that an existing wind tunnel high-pressure air source system 1, an existing wind tunnel Mach number 10 thermal valve 5, a Mach number 3.5-4 stabilizing section and transition section 13, Mach number 3.5-4 spray pipes 14, new spray pipes with Mach number 3.5-4, an original test section connecting section 15, an existing wind tunnel test section 7 and an existing wind tunnel diffuser 8 are sequentially connected to an existing wind tunnel device supporting device 6, and a platform diffuser 12 is installed in an inner cavity of the existing wind tunnel diffuser 8 in a sleeved mode.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements of the present invention will readily occur to those skilled in the art without departing from the principles of the present invention, and therefore the present invention is not limited to the specific details and illustrations shown and described herein without departing from the general concept defined by the claims and their equivalents.
Claims (2)
1. The method for designing the low-Mach-number total-enthalpy flight platform based on the existing hypersonic wind tunnel is characterized by comprising the following steps of:
s10, planning a low-Mach-number flight total enthalpy platform;
dividing the caliber of a spray pipe of the existing hypersonic velocity high wind tunnel into a phi 0.5 meter magnitude, a phi 1 meter magnitude and a phi 2 meter magnitude, and planning and respectively establishing corresponding low-Mach-number total-enthalpy flight platforms, specifically phi 0.3 meter, phi 0.5 meter and phi 1 meter magnitude low-Mach-number total-enthalpy flight platforms;
the low-Mach-number flight total enthalpy platform below the phi 0.5 meter magnitude level is used for testing the combined dynamic performance of a low-Mach-number aircraft, testing the internal and external flow integrated force-heat coupling of the aircraft and testing the aerodynamic heat load, and developing theoretical foundation research and experimental technology research;
the phi 1-meter-magnitude low-Mach-number total-enthalpy flight platform is used for theoretical basis research, test technology research, special tests and verification required by engineering development of a low-Mach-number aircraft;
s20, determining an operation mode, a heating mode and a test medium of the low-Mach-number total-enthalpy flight platform;
the wind tunnel test platform with low Mach number flight total enthalpy adopts an operation driving mode of blowing under high pressure and vacuum suction, adopts a metal plate heat storage type heater or a tubular electric adder to heat a test medium, and adopts high-pressure pure air as the test medium;
s30, determining a simulation technical index of a low-Mach-number flight total enthalpy platform;
the total simulation technical indexes are as follows:
the low-Mach-number total-enthalpy flight platform achieves Mach number of 2-4, simulation temperature of 390K-950K, simulation height of 15-30 kilometers and effective operation time of the test platform is more than or equal to 30 seconds;
and (3) segmental simulation technical indexes:
the method comprises the steps of utilizing an existing wind tunnel Mach 8 heater (2), the highest pressure being 8.0MPa and the highest temperature being 800K to realize a ground simulation test within the Mach 2-3 range, and realizing technical indexes of simulation height being 15-30 kilometers, the highest total pressure being 0.5MPa and the highest total temperature being 634K;
the method comprises the steps of utilizing an existing wind tunnel Mach number 10 heater (3), the highest pressure being 12.0MPa and the highest temperature being 1082K to realize a ground simulation test with the Mach number being 3.5-4, and realizing technical indexes of simulation height being 17-30 kilometers, the highest total pressure being 1.5MPa and the highest total temperature being 950K;
s40, determining original equipment and a matched system which need to be reserved for the low-Mach-number total-enthalpy flight platform;
the method comprises the following steps of reserving the conventional hypersonic wind tunnel plant, the conventional wind tunnel high-pressure air source system (1), the conventional wind tunnel Mach number 8 heater (2), the conventional wind tunnel Mach number 10 heater (3), the conventional wind tunnel Mach number 8 thermal valve (4), the conventional wind tunnel Mach number 10 thermal valve (5), the conventional wind tunnel equipment supporting device (6), the conventional wind tunnel test section (7), the conventional wind tunnel diffuser (8), a cooler, a wind tunnel measurement and control system and a model mechanism system; the method comprises the steps that the rapid establishment and operation of a flow field of a low-Mach-number total-enthalpy flight platform are realized by utilizing an existing wind tunnel high-pressure air source system (1), a power supply and distribution system, an operation control system, a vacuum system or an injection system and a cooling water supply system in an existing conventional hypersonic wind tunnel power system; the data acquisition and processing of the low-Mach-number total-enthalpy-of-flight platform are completed by utilizing a data acquisition system and a schlieren system of the conventional hypersonic wind tunnel;
s50, determining newly-added equipment of a low-Mach-number total-enthalpy flight platform;
s51, a spray pipe;
the spray pipe is divided into two Mach number scales: the spray pipe (10) with the Mach number of 2-3 and the spray pipe (14) with the Mach number of 3.5-4, wherein the Mach number set points of the single-point Mach number spray pipe are Mach numbers of 2, 2.5, 3, 3.5 and 4;
s52, a stabilizing section and a transition section;
corresponding to the spray pipe, the stable section and the transition section are divided into two Mach number scales: a Mach number 2-3 stable section and a transition section (9), and a Mach number 3.5-4 stable section and a transition section (13);
the size of a front end interface of the stabilizing section is consistent with that of a corresponding hot valve interface on the heater, the flow speed range in the stabilizing section is 5 m/s-30 m/s, and the diameter size of the stabilizing section is determined according to the flow speed range; the heat insulation layers and the corresponding flow equalizing devices are designed in the stabilizing section and the transition section, and the water cooling jackets are arranged outside the stabilizing section and the transition section;
s53, connecting sections;
corresponding to the spray pipes, a connecting section (11) of a new spray pipe with Mach number of 2-3 and an original test section and a connecting section (15) of a new spray pipe with Mach number of 3.5-4 and an original test section are arranged;
s54, a platform diffuser;
a platform diffuser (12) matched with the diffuser (8) is arranged, the platform diffuser (12) is sleeved in an inner cavity of the diffuser (8) of the existing hypersonic wind tunnel through a dismounting device, and the platform diffuser (12) and the diffuser (8) have the same central axis; determining the diameter of a second throat of the platform diffuser (12), the size of an inlet of the platform diffuser (12) and the total length of the platform diffuser (12) according to the starting pressure ratio of the low-Mach-number total-enthalpy flight platform;
s55, overall requirements of each component are met;
in order to ensure that the newly added equipment can be installed at the corresponding position of the existing hypersonic speed, the sum of the length of each single-point Mach number spray pipe, the length of the corresponding connecting section and the length of the corresponding stable section and the length of the corresponding transition section are equal, namely the total lengths are equal.
2. The method for designing the low-Mach-number total-enthalpy-of-flight platform based on the existing hypersonic wind tunnel according to claim 1, wherein the single-point Mach-number nozzle is an axisymmetric profile fixed-wall nozzle;
when the diameter of the outlet of the single-point Mach number nozzle is less than or equal to phi 0.5m, a martensite or austenite stainless steel forging is selected for manufacturing, and a water cooling structure is not arranged;
when the diameter of the outlet of the single-point Mach number nozzle is larger than 0.5m, the throat section of the single-point Mach number nozzle is made of a martensite or austenite stainless steel forging and is provided with a water cooling structure; the single-point Mach number nozzle diffusion section is made of a martensitic stainless steel plate, an austenitic stainless steel plate coil, a martensitic stainless steel forging or an austenitic stainless steel forging, and is not provided with a water cooling structure.
Priority Applications (1)
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| CN114563159B (en) * | 2022-04-28 | 2022-07-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic low-density wind tunnel nozzle inner axis Mach number measuring device and method |
| CN115165289B (en) * | 2022-09-07 | 2022-11-18 | 中国航空工业集团公司沈阳空气动力研究所 | Ultrasonic explosion phenomenon wind tunnel test simulation system and method |
| CN115493793B (en) * | 2022-10-08 | 2024-03-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device for reducing low Mach number airflow pulsation of large-caliber hypersonic wind tunnel |
| CN115420458B (en) * | 2022-11-04 | 2023-02-17 | 中国航空工业集团公司沈阳空气动力研究所 | System for simulating high-Mach ultrahigh-temperature environment and generation method |
| CN117405349B (en) * | 2023-12-14 | 2024-02-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Trace impurity gas scattering system with high boiling point at low temperature and test method thereof |
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