CN111982458A - Interference simulation system - Google Patents
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- CN111982458A CN111982458A CN202010846039.0A CN202010846039A CN111982458A CN 111982458 A CN111982458 A CN 111982458A CN 202010846039 A CN202010846039 A CN 202010846039A CN 111982458 A CN111982458 A CN 111982458A
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- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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Abstract
The application provides an interference simulation system, including: a vacuum subsystem; the test model subsystem comprises an incoming flow simulation engine, a jet flow simulation engine and an aircraft test model, wherein the incoming flow simulation engine is used for simulating hypersonic test airflow in the flight process of the aircraft, and the jet flow simulation engine is arranged on the aircraft test model and used for simulating jet flow generated in the flight process of the aircraft; a propellant supply subsystem; and a measurement and control subsystem. In the scheme, firstly, the interference simulation test is carried out in the vacuum chamber, a thinner low-pressure atmospheric environment can be provided, and the gas jet flow generated by the inflow simulation engine is adopted to provide hypersonic test airflow under the low-pressure atmospheric environment, so that the requirements of high speed and high enthalpy can be met simultaneously, and the manufactured test environment is closer to the flight environment. Therefore, the use time of the device can be increased on the basis of reducing the requirements on equipment, and the accuracy of the simulation result can be improved.
Description
Technical Field
The application relates to the field of aircrafts, in particular to an interference simulation system.
Background
A general hypersonic wind tunnel converts driven gas into hypersonic test airflow required by an experiment in a conventional heating mode or a shock wave heating mode. However, the above method is intended to realize high enthalpy test conditions, and has high requirements on heating equipment, vacuum pumping equipment and the like, and the working time of the wind tunnel is short. In addition, the test environment manufactured by the method still has a relatively large difference with the flight environment, and the requirements of the flight condition on Mach number, enthalpy value, low density, low pressure and the like are difficult to simulate, so that the accuracy of a simulation result is low.
Disclosure of Invention
An object of the embodiment of the present application is to provide an interference simulation system, so as to solve the technical problem that the accuracy of a simulation result of a hypersonic flight vehicle is low.
In order to achieve the above purpose, the technical solutions provided in the embodiments of the present application are as follows:
the embodiment of the present application provides an interference simulation system, including: the vacuum subsystem comprises a vacuum cabin and a vacuum pump, wherein the vacuum pump is used for maintaining a vacuum environment inside the vacuum cabin; the test model subsystem is arranged inside the vacuum chamber; the test model subsystem comprises an incoming flow simulation engine, a jet flow simulation engine and an aircraft test model, wherein the incoming flow simulation engine is used for simulating hypersonic test airflow in the flight process of the aircraft, and the jet flow simulation engine is arranged on the aircraft test model and used for simulating jet flow generated in the flight process of the aircraft; a propellant supply subsystem, connected to said test model subsystem, for providing propellant to said incoming flow simulation engine and said jet simulation engine; and the measurement and control subsystem is used for measuring test data and processing the test data. In the scheme, firstly, the interference simulation test is carried out in the vacuum chamber, a thinner low-pressure atmospheric environment can be provided, and the gas jet flow generated by the inflow simulation engine is adopted to provide hypersonic test airflow under the low-pressure atmospheric environment, so that the requirements of high speed and high enthalpy can be met simultaneously, and the manufactured test environment is closer to the flight environment. Therefore, the use time of the device can be increased on the basis of reducing the requirements on equipment, and the accuracy of the simulation result can be improved.
In an alternative embodiment of the present application, the test model subsystem further comprises: the jet flow simulation engine and the aircraft test model are arranged on the three-dimensional moving mechanism; and the measurement and control subsystem controls the three-dimensional moving mechanism to move along the track according to the simulation parameters. In the scheme, the jet flow simulation engine and the aircraft test model can be arranged on the movable three-dimensional moving mechanism, and the measurement and control subsystem can control the three-dimensional moving mechanism to move along the track according to the simulation parameters, so that the positions of the jet flow simulation engine and the aircraft test model can be flexibly adjusted according to the simulation parameters, and the accuracy of a simulation result is ensured.
In an alternative embodiment of the present application, the propellant supply subsystem comprises: a high pressure gas cylinder filled with the propellant; a pipeline, one end of which is connected with the high-pressure gas cylinder and the other end of which is connected with the incoming flow simulation engine and the jet flow simulation engine; and the valve is arranged on the pipeline. In the above scheme, the high-pressure gas cylinder can be used as a propellant of the inflow simulation engine and the jet flow simulation engine, and the control of the operation or the closing of the inflow simulation engine and the jet flow simulation engine is realized by controlling the opening or the closing of the valve.
In an alternative embodiment of the present application, the propellant supply subsystem further comprises: and the pressure gauge and the flowmeter are arranged on the pipeline. In the scheme, the pipeline can be provided with the pressure gauge and the flow meter, so that the running states of the incoming flow simulation engine and the jet flow simulation engine can be adjusted according to parameters on the pressure gauge and the flow meter, and the accuracy of a simulation result is ensured under the condition of different simulation parameters.
In an optional embodiment of the present application, a cabin penetrating flange is disposed on the vacuum cabin, and the pipeline is connected to the high pressure gas cylinder and the inflow simulation engine and the jet simulation engine through the cabin penetrating flange. In the above scheme, the vacuum chamber can be provided with the chamber-passing flange, so that the situation that the vacuum environment is damaged due to the fact that the pipeline penetrates through the vacuum chamber is avoided, and the accuracy of a simulation result is guaranteed.
In an optional embodiment of the present application, the measurement and control subsystem includes: the sensor is arranged on the aircraft test model and used for acquiring data in the test process; and the control box is in communication connection with the sensor and is used for receiving the data sent by the sensor and processing the data. In the scheme, data in the test process can be collected through the sensor arranged on the aircraft test model, and the collected data can be processed, so that the stability of the aircraft can be researched according to the test result.
In an optional embodiment of the present application, the measurement and control subsystem further includes: and the display terminal is arranged on the control box. In the scheme, the measurement and control subsystem can be provided with a display terminal, so that a tester can know the test state in real time.
In an alternative embodiment of the present application, the vacuum pump comprises: an external mechanical pump. In the above scheme, an external mechanical pump can be used for providing a vacuum environment in the vacuum chamber.
In an alternative embodiment of the present application, the vacuum pump further comprises: an external molecular pump and an internal cryogenic pump. In the above manner, an external mechanical pump, an external molecular pump and an internal cryogenic pump can be used to provide a vacuum environment in the vacuum chamber, so that the vacuum degree of the provided vacuum environment is higher.
In order to make the aforementioned objects, features and advantages of the present application more comprehensible, embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments of the present application will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and that those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
Fig. 1 is a block diagram of an interference simulation system according to an embodiment of the present disclosure;
FIG. 2 is a block diagram of a test model subsystem according to an embodiment of the present disclosure;
fig. 3 is a schematic diagram of an interference simulation system according to an embodiment of the present application.
Icon: 100-an interference simulation system; 110-a vacuum subsystem; 111-vacuum chamber; 112-a vacuum pump; 113-a cross cabin flange; 120-a test model subsystem; 121-incoming flow simulation engine; 122-jet simulation engine; 123-aircraft test model; 124-three-dimensional moving mechanism; 125-a scaffold; 130-a propellant supply subsystem; 131-a high-pressure gas cylinder; 132-a conduit; 133-a valve; 134-pressure gauge; 135-a flow meter; 140-a measurement and control subsystem; 141-a control box; 142-display terminal.
Detailed Description
The hypersonic aircraft is an aircraft with the flight speed of more than five Mach (such as aircraft with flight speed of more than five times of sound speed, guided missiles, shells and the like, with wings or without wings), has the characteristic of high penetration success rate, and has great military value and potential economic value. Therefore, the development and development of the hypersonic aircraft can not only greatly change the modern war style, but also greatly promote and promote the fusion development of countries in the relevant fields of space exploration, civil aerospace and the like, and further play an important strategic significance in the international military, political and economic aspects in the future.
The near space is an airspace with the altitude of 20-100 kilometers, is beyond the aviation field of aircraft flight and the space of common spacecrafts, and has the absolute advantages of safe and stable working environment and being difficult to find and intercept.
The near space aircraft is an aircraft or a sub-orbital aircraft which can only or continuously fly in the near space for a long time or a hypersonic cruising aircraft which flies in the near space, has the advantages which are not possessed by aviation and aerospace aircrafts, and particularly has great development potential in the aspects of communication guarantee, information collection, electronic suppression, early warning, civil use and the like.
The high-speed near space aircraft is a near space aircraft with the flight speed not less than Ma 3, has the characteristics of quick response, super-strong penetration, flexible maneuvering and the like, is a new concept weapon with strategic deterrence and actual combat application capability, and has important effects on deterrence of strong enemies, control of crisis and win-win wars.
A Reaction Control System (RCS) is an important means for controlling the flight attitude and flight trajectory of a hypersonic flight vehicle. The reaction control system applies a reverse acting force to the aircraft through engine jet flow, so that high-speed maneuvering flight or attitude adjustment of the aircraft is realized, and compared with an air-operated rudder control technology, the reaction control system provides high-angle maneuvering flight in a wider range and is suitable for a higher airspace with thin air.
However, in the working process, the jet flow generated by the engine of the reaction control system interferes with the high-speed incoming flow encountered in the flying process of the aircraft to form a complex flow field structure, which has great influence on the accurate prediction of the engine control capability of the specific reaction control system and the pneumatic control characteristic of the aircraft. Therefore, the method accurately predicts the interference flow field generated by jet flow interference and the influence of the interference flow field on the aerodynamic characteristics of the hypersonic flight in the adjacent space, and has important significance for further improving the jet flow control efficiency of the engine and ensuring the flight stability of the hypersonic aircraft in the adjacent space.
At present, the research on the lateral jet flow interference characteristic of a hypersonic aircraft is mainly carried out in modes of high-altitude flight tests, numerical simulation, ground tests and the like. In the aspect of high-altitude flight test, the cost, the period and the difficulty are suffered, and the high-altitude flight test can be only carried out in model development, so that the test data which can be provided is very limited. In the aspect of numerical simulation, due to the existence of a high-temperature effect and a rarefaction effect, the accuracy of calculation of hydrodynamic flow field simulation and aerodynamic heat prediction is high for complex problems such as jet flow and hypersonic incoming flow interference.
In the aspect of ground tests, a large number of hypersonic wind tunnels are built at home and abroad for simulating hypersonic incoming flow conditions, including conventional heating hypersonic wind tunnels and shock wave heating type wind tunnels. The shock wave heating type wind tunnel can be divided into a heating light gas driving shock wave wind tunnel, a free piston driving shock wave wind tunnel and a detonation driving shock wave wind tunnel according to the shock wave generating mode. Ground tests on jet flow and hypersonic incoming flow interference are basically carried out in the hypersonic wind tunnel. However, the above method is intended to realize high enthalpy test conditions, and has high requirements on heating equipment, vacuum pumping equipment and the like, and the working time of the wind tunnel is short. In addition, the test environment manufactured by the method still has a relatively large difference with the flight environment, and the requirements of the flight condition on Mach number, enthalpy value, low density, low pressure and the like are difficult to simulate, so that the accuracy of a simulation result is low.
Based on the analysis, the embodiment of the application provides an interference simulation system, which is used for simulating the interference of jet flow and hypersonic incoming flow in the flight process of a high-speed and high-speed aircraft. The interference simulation system can provide a high-altitude low-density gas environment, high-temperature gas airflow generated by the engine is simulated by using the incoming flow, hypersonic airflow is provided to simulate high supersonic incoming flow in actual flight of an aircraft, and the test requirements of hypersonic speed and high enthalpy airflow can be met.
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
Referring to fig. 1, fig. 1 is a block diagram of an interference simulation system according to an embodiment of the present disclosure, where the interference simulation system 100 may include: a vacuum subsystem 110, a test model subsystem 120, a propellant supply subsystem 130, and a measurement and control subsystem 140. The vacuum subsystem 110 comprises a vacuum cabin 111 and a vacuum pump 112, the test model subsystem 120 is arranged inside the vacuum cabin 111, and the vacuum pump 112, the propellant supply subsystem 130 and the measurement and control subsystem 140 are all connected with the test model subsystem 120.
In the disturbance simulation system 100, firstly, a disturbance simulation test is performed in the vacuum chamber 111, so that a rarer low-pressure atmosphere environment can be provided, and a gas jet flow generated by the incoming flow simulation engine 121 is used for providing hypersonic test airflow under the low-pressure atmosphere environment, so that the requirements of high speed and high enthalpy can be met simultaneously, and the manufactured test environment is closer to the flight environment. Therefore, the use time of the device can be increased on the basis of reducing the requirements on equipment, and the accuracy of the simulation result can be improved.
First, various components of the vacuum subsystem 110 will be described.
Specifically, the vacuum chamber 111 may provide a vacuum environment for the test model subsystem 120 disposed inside, and the vacuum pump 112 is used for drawing the airflow inside the vacuum chamber 111, thereby maintaining the vacuum environment inside the vacuum chamber 111. It should be noted that, depending on the actual situation, the vacuum environment in the vacuum chamber 111 may not be a complete vacuum environment as long as the current vacuum environment meets the requirements of the test.
In one embodiment, the vacuum pump 112 may include an external mechanical pump when the vacuum level requirement for the environment in the vacuum chamber 111 is not high. As another embodiment, the vacuum pump 112 may further comprise an external molecular pump and/or an internal cryogenic pump when the vacuum level requirement for the environment in the vacuum chamber 111 is high. It will be appreciated that even though the vacuum pump 112 includes a plurality of pumps, one or more of the pumps may be selectively turned on during use, depending on the circumstances. The embodiment of the present application does not specifically limit which pumps are used and which pumps are specifically turned on in the use process for the vacuum pump 112, and those skilled in the art can appropriately select the pumps according to actual situations.
In the above scheme, an external mechanical pump may be used to maintain the vacuum environment in the vacuum chamber 111. In addition to the external mechanical pump, an external molecular pump and an internal cryogenic pump may be used to maintain the vacuum environment in the vacuum chamber 111, so that the vacuum degree of the vacuum environment in the vacuum chamber 111 is relatively high.
Next, the test model subsystem 120 is described.
Referring to fig. 2, fig. 2 is a block diagram of a test model subsystem according to an embodiment of the present disclosure, where the test model subsystem 120 may include an incoming flow simulation engine 121, a jet flow simulation engine 122, and an aircraft test model 123.
Specifically, the aircraft test model 123 may be a scaling model of an actual hypersonic aircraft, where the scaling of the aircraft test model 123 may be adjusted according to actual conditions, for example: the size of the aircraft test model 123 can be determined according to the size of the parameter uniformity region of the plume field of the incoming flow simulation engine 121. Under the low-pressure environment, the high-temperature gas flow uniform area generated by the incoming flow simulation engine 121 is wide, and the size of the aircraft test model 123 can be relatively larger, so that the aircraft test model has the advantage of obtaining more measurement parameters.
To simulate the oncoming flow encountered during flight of a hypersonic aircraft, an oncoming flow simulation engine 121 may be disposed within the vacuum chamber 111. The inflow simulation engine 121 can be arranged right in front of the aircraft test model 123, and when the inflow simulation engine 121 is started, the generated high-temperature gas airflow faces the aircraft test model 123, so that the purpose of simulating inflow interference is achieved. Likewise, in order to simulate the jet generated during the flight of a hypersonic aircraft, a jet simulation engine 122 may be provided within the vacuum chamber 111. Jet simulation engine 122 may be provided on aircraft test model 123, and when jet simulation engine 122 is started, the purpose of simulating jet disturbance may be achieved.
In one embodiment, the test model subsystem 120 may further include a three-dimensional moving mechanism 124, and the jet simulation engine 122 and the aircraft test model 123 may be disposed on the three-dimensional moving mechanism 124. The three-dimensional moving mechanism 124 can move in the vacuum chamber 111, and the three-dimensional moving mechanism 124, the jet simulation engine 122 thereon and the aircraft test model 123 can be placed at different positions in the vacuum chamber 111 according to different simulation parameters during the test.
Wherein, before the test, the simulation parameter requirements of the test can be determined, such as: in the test process, the parameter distribution (including parameters such as speed, temperature and density), mach number, reynolds number, knudsen number and the like of the plume field of the incoming flow simulation engine 121 are combined with the numerical value plume field simulation result (namely the distribution in the space corresponding to the parameters in the plume field of the incoming flow simulation engine 121), and a specific spatial point position is determined, so that the parameters at the position meet the simulation parameter requirement of the test, and the position is the installation position of the test model subsystem 120.
Similarly, the test model subsystem 120 may also include a cradle 125, and the inflow simulation engine 121 may be disposed on the cradle 125. The support 125 is movable in the vacuum chamber 111, and the support 125 and the inflow simulation engine 121 thereon can be placed at different positions in the vacuum chamber 111 according to simulation parameters during a test.
It should be noted that, when the three-dimensional moving mechanism 124 and the bracket 125 are placed, the relative positions of the jet simulation engine 122 and the aircraft test model 123 and the incoming flow simulation engine 121 need to be considered according to the simulation parameters of the test so as to meet the test requirements. Of course, test model subsystem 120 may include only three-dimensional movement mechanism 124, or only support 125, or both three-dimensional movement mechanism 124 and support 125, or neither three-dimensional movement mechanism 124 nor support 125, as appropriate by those skilled in the art.
As another embodiment, the test model subsystem 120 may further include a rail, and the three-dimensional moving mechanism 124 and/or the support 125 may be disposed on and may move along the rail. The three-dimensional movement mechanism 124 and/or the carriage 125 may be controlled by 140 of the interference simulation system 100 to move along the track according to the simulation parameters. It is understood that the movement of the three-dimensional moving mechanism 124 and/or the support 125 may also be controlled manually.
In the above scheme, the jet simulation engine 122 and the aircraft test model 123 may be disposed on the movable three-dimensional moving mechanism 124, the incoming flow simulation engine 121 may be disposed on the support 125, and the measurement and control subsystem 140 may control the three-dimensional moving mechanism 124 and/or the support 125 to move along the track according to the simulation parameters, so that the positions of the incoming flow simulation engine 121, the jet simulation engine 122, and the aircraft test model 123 may be flexibly adjusted according to the simulation parameters, so as to ensure the accuracy of the simulation result.
Next, the propellant supply subsystem 130 will be described.
In particular, propellant supply subsystem 130 may be used to provide propellant to jet simulation engine 121 as well as jet simulation engine 122. As an embodiment, the propellant supply subsystem 130 may include a high pressure gas cylinder 131, a line 132, and a valve 133. The propellant is contained in the high-pressure gas cylinder 131, one end of the pipeline 132 is connected to the high-pressure gas cylinder 131, the other end of the pipeline 132 is connected to the inflow simulation engine 121 and the jet simulation engine 122, and the propellant in the high-pressure gas cylinder 131 can reach the inflow simulation engine 121 and the jet simulation engine 122 through the pipeline 132, so that the inflow simulation engine 121 and the jet simulation engine 122 can normally operate. Valve 133 is disposed in conduit 132 to control the operation or shut-off of the inflow simulation engine 121 and the jet simulation engine 122 by controlling the opening or closing of valve 133 to effect the delivery of propellant. Furthermore, the control of the operating conditions of the inflow simulation engine 121 and the jet simulation engine 122 can be achieved by varying the amount of propellant delivered by controlling the valve 133.
As another embodiment, the propellant supply subsystem 130 may further include a pressure gauge 134 and a flow meter 135, both the pressure gauge 134 and the flow meter 135 being disposed on the line 132. The pressure gauge 134 can measure the pressure value of the propellant in the pipeline 132 in real time, and the flow meter 135 can measure the flow rate of the propellant in the pipeline 132 in real time, so that the operation states of the inflow simulation engine 121 and the jet flow simulation engine 122 can be adjusted according to the parameters of the pressure gauge 134 and the flow meter 135, and the accuracy of the simulation result can be ensured under the condition of different simulation parameters.
As another embodiment, a through-cabin flange 113 may be disposed on the vacuum cabin 111, and the pipeline 132 in the propellant supply subsystem 130 may connect the high-pressure gas cylinder 131 and the inflow simulation engine 121 and the outflow simulation engine 122 through the through-cabin flange 113, so as to avoid the vacuum environment from being damaged due to the pipeline 132 passing through the vacuum cabin 111, thereby ensuring the accuracy of the simulation result.
Finally, a description of the instrumentation subsystem 140 is provided.
The measurement and control subsystem 140 may include sensors and a control box 141. Wherein the sensors may be arranged within the vacuum chamber 111, for example: the device can be arranged on an aircraft test model 123, an incoming flow simulation engine 121 and the like and is used for collecting data in the test process; the control box 141 is in communication connection with the sensors, and is used for receiving data sent by the sensors and processing the data. As an embodiment, the measurement and control subsystem 140 may further include a display terminal 142, and the display terminal 142 may be disposed on the control box 141 or may be an independent terminal device, and is configured to display a measurement result in real time, so that a tester may know a test state in real time.
The measurement and control subsystem 140 may also control other modules in the interference simulation system 100. For example: the vacuum pump 112 can be controlled to be turned on and off, and the sequence in which the vacuum pump 112 is turned on; the opening and closing of the valves in the propellant supply subsystem 130 can be controlled to control the flow rate of the airflow generated by the inflow simulation engine 121 and the jet simulation engine 122, and the like, which is not specifically limited in the embodiments of the present application.
It should be noted that, during the test, the airflow parameter in front of the aircraft test model 123 may be changed by adjusting the flow rate of the incoming flow simulation engine 121, or the airflow parameter in front of the aircraft test model 123 may be changed by moving the position of the three-dimensional moving mechanism 124, so as to achieve different measurement results.
In the above scheme, data in the test process can be collected through the sensor arranged on the aircraft test model 123, and the collected data can be processed, so that the stability of the aircraft can be researched according to the test result.
For example, referring to fig. 3, fig. 3 is a schematic diagram of an interference simulation system according to an embodiment of the present disclosure, in which the interference simulation system 100 includes a vacuum subsystem 110, a test model subsystem 120, a propellant supply subsystem 130, and a measurement and control subsystem 140. The vacuum subsystem 110 comprises a vacuum chamber 111 and a vacuum pump 112, the test model subsystem 120 comprises an inflow simulation engine 121, a jet simulation engine 122, an aircraft test model 123, a three-dimensional moving mechanism 124 and a support 125, the propellant supply subsystem 130 comprises a high-pressure gas cylinder 131, a pipeline 132, a valve 133, a pressure gauge 134 and a flow meter 135, and the measurement and control subsystem 140 comprises a sensor, a control box 141 and a display terminal 142.
In the test using the disturbance simulation system 100, first, the installation positions of the inflow simulation engine 121, the jet simulation engine 122, the aircraft test model 123, the three-dimensional moving mechanism 124, and the bracket 125 are determined as appropriate according to the requirements of the simulation parameters, and the appropriate measurement positions and measurement parameters are set. After the test pipeline 132 (for air tightness inspection, etc.) and the cable line (for on-off test, etc.) work normally, the door of the vacuum chamber 111 can be closed, and then the external mechanical pump, the external molecular pump and the internal cryogenic pump are sequentially opened according to the environmental pressure required by the test until the required environmental pressure is reached. And starting the incoming flow simulation engine 121, the jet flow simulation engine 122 and the measurement and control subsystem 140, and measuring to obtain required test data.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the units is only one logical division, and there may be other divisions when actually implemented, and for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection of devices or units through some communication interfaces, and may be in an electrical, mechanical or other form.
In addition, units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
Furthermore, the functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
In this document, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.
The above description is only an example of the present application and is not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (9)
1. An interference modeling system, comprising:
the vacuum subsystem comprises a vacuum cabin and a vacuum pump, wherein the vacuum pump is used for maintaining a vacuum environment inside the vacuum cabin;
the test model subsystem is arranged inside the vacuum chamber;
the test model subsystem comprises an incoming flow simulation engine, a jet flow simulation engine and an aircraft test model, wherein the incoming flow simulation engine is used for simulating hypersonic test airflow in the flight process of the aircraft, and the jet flow simulation engine is arranged on the aircraft test model and used for simulating jet flow generated in the flight process of the aircraft;
a propellant supply subsystem, connected to said test model subsystem, for providing propellant to said incoming flow simulation engine and said jet simulation engine;
and the measurement and control subsystem is used for measuring test data and processing the test data.
2. The interference simulation system of claim 1, wherein the test model subsystem further comprises:
the jet flow simulation engine and the aircraft test model are arranged on the three-dimensional moving mechanism;
and the measurement and control subsystem controls the three-dimensional moving mechanism to move along the track according to the simulation parameters.
3. The jamming simulation system of claim 1, wherein the propellant supply subsystem comprises:
a high pressure gas cylinder filled with the propellant;
a pipeline, one end of which is connected with the high-pressure gas cylinder and the other end of which is connected with the incoming flow simulation engine and the jet flow simulation engine;
and the valve is arranged on the pipeline.
4. The jamming simulation system of claim 3, wherein the propellant supply subsystem further comprises: and the pressure gauge and the flowmeter are arranged on the pipeline.
5. The interference simulation system according to claim 3, wherein a cabin penetration flange is provided on the vacuum cabin, and the pipeline connects the high-pressure gas cylinder and the inflow simulation engine and the jet simulation engine through the cabin penetration flange.
6. The interference simulation system of claim 1, wherein the measurement and control subsystem comprises:
the sensor is arranged on the aircraft test model and used for acquiring data in the test process;
and the control box is in communication connection with the sensor and is used for receiving the data sent by the sensor and processing the data.
7. The interference simulation system of claim 6, wherein the measurement and control subsystem further comprises: and the display terminal is arranged on the control box.
8. The interference simulation system of claim 1, wherein the vacuum pump comprises: an external mechanical pump.
9. The interference simulation system of claim 8, wherein the vacuum pump further comprises: an external molecular pump and an internal cryogenic pump.
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| CN115541168A (en) * | 2022-11-28 | 2022-12-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Device and method for simulating free flight of wind tunnel in air refueling docking of double machines |
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