KR102050002B1 - The method and apparatus for testing an altitude in the ground - Google Patents

Abstract

Embodiments relate to a method and an apparatus for testing an altitude on the ground. According to an embodiment, a method for testing an altitude on the ground is configured to estimate an amount of air supplied to an engine from a condition of the total pressure and a stagnation temperature of the air currently flowing to simulate a flight condition, and infer flight altitude and Mach number information therefrom in real time. Therefore, a conventional apparatus for testing an altitude on the ground is used to perform a test to simulate a condition similar to a flight test for a reliable engine performance verification process to be performed.

Description

The method and apparatus for testing an altitude in the ground}

The present invention relates to a ground altitude test apparatus and method, and more particularly to a ground altitude test apparatus and method for estimating flight information simulated in the ground altitude test operation.

In order to develop an air intake engine mounted on a supersonic vehicle, the engine must be fixed on the ground prior to the flight test of the test body, and various tests must be performed to verify the engine performance. Indeed, supersonic air-suction engines fly at high speed, inhaling and compressing air to burn with fuel to achieve the desired thrust. However, on the ground, there is a limit to moving the specimen at a desired speed as in actual flight. Therefore, in order to test a supersonic air intake engine, in general, the engine is fixed and the air is flowed at a high speed to simulate the test conditions. Will be performed. Therefore, although basic test equipment is important for accurate performance testing of supersonic air-suction engines, the test results are simulated under the desired conditions, and the results of the ground altitude test are similar to those of the actual flight test. It is more important to be able to derive

Since the ground altitude test is an essential process for developing an air intake engine, a test apparatus for performance testing of a high-speed propulsion engine, a high pressure of 10 Mpa and a high temperature of 1800 K or more for a performance test of a special engine such as a scramjet engine Test apparatus for performance testing have been proposed. The basic components of the test apparatus and the role of each component in performing the performance test of the supersonic air-suction engine on the ground allow the basic ground combustion test to be performed.

The above-mentioned prior arts only propose a physical test apparatus, and there is no description of a detailed test technique for simulating flight conditions. In addition, a technique for measuring voltage force and static pressure, which is essential information when performing the ground altitude test, has been proposed. Through this technique, it is possible to perform the performance evaluation of the engine under test by obtaining desired information through the ground altitude test. As with the previous inventions, however, no detailed test technique or flight condition estimation technique based on such a technique is proposed. That is, the techniques and inventions related to the ground altitude test of the proposed supersonic air intake engine are limited to basic or physical test apparatuses, and more important studies on flight condition estimation and test techniques are insufficient.

[Prior art document number]

Prior Art Document 1: Korean Patent Publication No. 2010-0071184

Prior Art Document 2: Korean Patent No. 10-1357862

Prior Art Document 3: Korean Patent No. 10-1268393

Embodiments use the existing ground altitude test apparatus by estimating the amount of air supplied to the engine from the total pressure and total temperature conditions of the current air to simulate flight conditions, and inferring the flight altitude and Mach number information in real time therefrom. It is to provide a ground altitude test method and apparatus that can perform a reliable engine performance verification procedure by performing a test simulating conditions similar to the flight test.

Ground altitude test method according to an embodiment of the present invention comprises the steps of measuring the total force and temperature conditions of the current air to simulate the flight conditions of the aircraft; Estimating the amount of air supplied to the engine of the vehicle from the measured voltage force and total temperature condition; And determining flight conditions including at least one of flight altitude information and flight Mach number information from the estimated air amount.

Sensor unit for measuring the voltage force and the total temperature of the current air to simulate the flight conditions of the aircraft according to another embodiment; And a processor for estimating the amount of air supplied to the engine of the vehicle from the measured voltage force and the total temperature condition, and determining a flight condition including at least one of flight altitude and Mach number information from the estimated air amount.

According to another embodiment includes a recording medium recording a program for executing the above ground altitude test method on a computer.

The ground altitude test method and apparatus according to the embodiment may perform an engine performance test under conditions similar to actual flight tests in the ground altitude test apparatus.

Ground elevation test method and apparatus according to the embodiment by estimating the amount of air supplied to the engine from the total pressure and total temperature conditions of the current air to simulate the flight conditions, by infer the flight altitude and Mach number information in real time, Tests simulating conditions similar to flight tests using existing ground altitude test equipment allow reliable engine performance verification procedures.

In addition, it is possible to provide a fuel supply technique that uses the estimated amount of air to satisfy a desired air excess rate condition.

1 is a schematic diagram of a ground test altitude device 100 according to an embodiment.
2 is a view showing a relationship between the density of air and the intake air flow rate according to the air constant temperature conditions.
3 is a diagram illustrating a relationship between air density and static pressure according to standard / hot / cold day conditions.

The terminology used in the present embodiments is a general term that is currently widely used as possible while considering the functions of the present embodiments, but may vary according to the intention or precedent of a person skilled in the art, the emergence of new technology, etc. . In addition, in certain cases, there is also a term arbitrarily selected, and in this case, the meaning will be described in detail in the description of the corresponding embodiment. Therefore, the terms used in the present exemplary embodiments should be defined based on the meanings of the terms and the contents throughout the present exemplary embodiments, rather than simply names of the terms.

In the description of the embodiments, when a part is connected to another part, this includes not only a case in which the part is directly connected, but also a case in which another part is electrically connected in between. In addition, when a part includes a certain component, this means that it may further include other components, without excluding other components unless otherwise stated. In addition, the term "unit" described in the embodiments means a unit for processing at least one function or operation, which may be implemented in hardware or software, or a combination of hardware and software.

Terms such as “consisting of” or “comprising” as used in the present embodiments should not be construed as necessarily including all of the various elements or steps described in the specification, and some or some of them It should be understood that the steps may not be included or may further include additional components or steps.

The description of the following embodiments should not be construed as limiting the scope of the right, it should be construed as belonging to the scope of the embodiments that can be easily inferred by those skilled in the art. Hereinafter, only exemplary embodiments will be described in detail with reference to the accompanying drawings.

The embodiments describe a method of determining the conditions of the engine and the air flowing around the engine and the amount of fuel supplied to the engine in order to simulate the desired flight conditions when performing the ground altitude test of the supersonic air intake engine.

To simulate the test conditions similar to a flying supersonic engine, the total power, temperature, and flight Mach number and angle of attack of the incoming air should be simulated according to flight altitude. At this time, since it is difficult to perform the ground altitude test while changing the angle of attack, the present invention describes a test method considering only the condition of the angle of attack is zero.

1 is a schematic diagram of a ground test altitude device 100 according to an embodiment.

Referring to FIG. 1, the ground elevation test apparatus 100 includes a sensor unit 110 and a processor 120. The ground altitude test apparatus 100 may perform the performance evaluation of the engine 120 to be tested by obtaining desired information through the ground altitude test for the engine 120.

The sensor unit 110 measures the voltage force and all temperature conditions of the air flowing into the engine in order to simulate the flight conditions of the vehicle. The sensor unit 110 may include a pressure sensor, a temperature sensor, and the like.

The processor 120 estimates the amount of air supplied to the engine of the vehicle from the voltage force and the total temperature condition measured by the sensor unit 110, and determines a flight condition including flight altitude and Mach number information from the estimated amount of air. In addition, the processor 120 may determine the real-time fuel amount that satisfies the predetermined air excess rate condition using the estimated air amount.

) 및 전압력(

)을 측정하면 공급되는 공기의 유량은 다음 수학식 1과 같이 계산할 수 있다.First, the total air temperature supplied to the engine in the ground altitude test device of the supersonic air suction type engine (

) And high pressure (

) Can be calculated as shown in Equation 1 below.

[Equation 1]

는 공기공급장치의 초킹 출구면적이다. 여기서, 전압력은 둘 이상의 기체가 섞여 있을 때, 그 혼합기체 전체의 압력을 의미하고, 전온도는 흐름, 특히 고속 기류 속에 온도계를 넣으면 국부적으로 흐름이 저지됨으로써 흐름이 가지는 운동 에너지가 열에너지로 변환되어 이것이 흐름의 실제 온도에 가해진 양으로 온도계에 나타나는 온도를 의미한다. From the stomach

Is the choking outlet area of the air supply. Here, the total pressure means the pressure of the entire mixture gas when two or more gases are mixed, and the total temperature means that the flow is prevented locally, especially when the thermometer is placed in the high speed air flow, so that the kinetic energy of the flow is converted into thermal energy. This is the temperature displayed on the thermometer in the amount applied to the actual temperature of the flow.

)와 공기 밀도(

)는

가 고정되어 있을 경우 1:1 함수 관계를 가지게 되며, 공기 전온도가 350 ~ 1000 K의 범위에서 고정될 경우 도 2와 같은 분포를 가지게 되며, 이를 고정된 전온도 조건에서 2차 함수로 근사화 할 수 있다. Next, the amount of air intake into the engine (

) And air density (

)

If it is fixed, it has a 1: 1 function relation. If the air temperature is fixed in the range of 350 to 1000 K, it has the distribution as shown in FIG. Can be.

는 다음의 수학식 2와 같이

의 2차 함수로 표현할 수 있다.therefore

Is as shown in Equation 2 below.

Can be expressed as a quadratic function of.

[Equation 2]

는 2차 근사 함수의 계수로 공기 전온도의 데이터 테이블로 정리할 수 있다. 도 2를 참조하면, 빨간색 별표로 나타낸 것은 실제 시험 데이터를 의미하며 이를 위의 수식과 같이 2차 다항식으로 근사화하여 파란색 실선으로 표기하였다.At this time

Can be summarized in the data table of the total air temperature as a coefficient of the quadratic approximation function. Referring to FIG. 2, the red asterisk means actual test data, and this is represented by a blue solid line by approximating the second polynomial as shown in the above equation.

)은 도 3와 같이

의 함수로 고려할 수 있으며, 각각 standard/hot/cold day의 조건에 따라 다음 수학식 3과 같이, 2차의 함수로 근사화 할 수 있다.On the other hand, depending on the atmospheric conditions,

) Is as shown in FIG. 3

It can be considered as a function of, and can be approximated as a quadratic function, as shown in Equation 3, according to the conditions of standard / hot / cold day, respectively.

[Equation 3]

As shown in FIG. 3, this may also be expressed by approximating a quadratic polynomial as in the above equation.

Here, the static pressure means a normal strain force that pushes the planes vertically to each other assuming a plane placed parallel to the flow of the fluid, and has a constant value regardless of the motion state of the fluid and the plane of the fluid.

를 결정할 수 있으며, 공기의 정압력과 고도는 1:1 함수 관계를 가지게 되므로 대기 모델을 이용하여 최종적으로 고도 정보를 추정할 수 있다. 또한 같은 방식으로 공기의 정압력과 밀도가 결정되면 이상기체 방정식으로부터 다음 수학식 4와 같이 공기의 정온도(

)를 계산할 수 있다. Static pressure of air supplied by Equation 3,

Since the static pressure of the air and the altitude have a 1: 1 function relationship, the altitude information can be finally estimated using the atmospheric model. In addition, if the static pressure and density of the air are determined in the same manner, the static temperature of the air (

) Can be calculated.

[Equation 4]

와 측정된

을 이용하여 다음 수학식 5의 등 엔트로피 방정식을 통해서 비행 마하수(M)를 추정할 수 있다.So determined

And measured

Using can be estimated the flight Mach number (M) through the isentropic equation of the following equation (5).

[Equation 5]

In this way, the engine excess air ratio may be determined according to the estimated flight conditions, and the air excess rate condition of the desired engine may be satisfied by the following equation (6) using the air intake amount introduced into the engine. The excess air ratio means the ratio of the amount of air flowing into the engine and the amount of fuel, which can be expressed by Equation 6 below.

[Equation 6]

는 특정 상수를 의미하며,

는 엔진에 공급되는 연료량을 의미한다. 이 때

는 추정을 통해 계산할 수 있으므로, 원하는 공기과잉율 조건(

)을 만족시키기 위한 실시간 연료량 명령(

)은 다음 수학식 7과 같이 결정할 수 있다.here,

Means a certain constant,

Is the amount of fuel supplied to the engine. At this time

Can be calculated by estimation, so the desired excess air condition (

Real-time fuel level command to satisfy

) May be determined as in Equation 7 below.

[Equation 7]

Ground elevation test method and apparatus according to the embodiment by estimating the amount of air supplied to the engine from the total pressure and total temperature conditions of the current air to simulate the flight conditions, by infer the flight altitude and Mach number information in real time, Tests simulating conditions similar to flight tests using existing ground altitude test equipment allow reliable engine performance verification procedures. In addition, it is possible to provide a fuel supply technique that uses the estimated amount of air to satisfy a desired air excess rate condition.

One embodiment of the present invention can also be implemented in the form of a recording medium containing instructions executable by a computer, such as a program module executed by the computer. Computer readable media can be any available media that can be accessed by a computer and includes both volatile and nonvolatile media, removable and non-removable media. In addition, computer readable media may include both computer storage media and communication media. Computer storage media includes both volatile and nonvolatile, removable and non-removable media implemented in any method or technology for storage of information such as computer readable instructions, data structures, program modules or other data. Communication media typically includes computer readable instructions, data structures, program modules, or other data in a modulated data signal such as a carrier wave, or other transmission mechanism, and includes any information delivery media.

The foregoing description of the present invention is intended for illustration, and it will be understood by those skilled in the art that the present invention may be easily modified in other specific forms without changing the technical spirit or essential features of the present invention. will be. Therefore, it should be understood that the embodiments described above are exemplary in all respects and not restrictive. For example, each component described as a single type may be implemented in a distributed manner, and similarly, components described as distributed may be implemented in a combined form.

The scope of the present invention is shown by the following claims rather than the above description, and all changes or modifications derived from the meaning and scope of the claims and their equivalents should be construed as being included in the scope of the present invention. do.

Claims (10)

Measuring the total pressure and total temperature of the current air to simulate flight conditions of the vehicle;
Estimating the amount of air supplied to the engine of the vehicle from the measured voltage force and total temperature condition; And
Determining a flight condition including at least one of flight altitude information and flight Mach number information from the estimated air amount;
The flight altitude information,
The static pressure of air determined by the following equation (3)

And ground altitude test method, which is determined based on the atmospheric model.
[Equation 3]

The method of claim 1,
And determining a real-time fuel amount satisfying a predetermined air excess rate condition using the estimated air amount. The method of claim 2,
The excess air ratio is a ratio of the amount of air and the amount of fuel flowing into the engine, the ground altitude test method, characterized in that defined as shown in Equation 6.
[Equation 6]

(here,

Is the amount of air intake into the engine,

Means a certain constant,

Means the amount of fuel supplied to the engine) The method of claim 3, wherein
The real time fuel amount,
Ground altitude test method, characterized in that as defined by Equation 7.
[Equation 7]

The method of claim 1,
The air amount is,
Ground altitude test method characterized in that estimated by the following equation (1).
[Equation 1]

(here,

The full temperature of air,

Is the full force of air,

Is the choking outlet area of the air supply) delete The method of claim 1,
The flight Mach number information is ground altitude test method, characterized in that determined by the following equation (5).
[Equation 5]

(

Is the full temperature of the air,

Is the constant temperature of the air) A recording medium on which a program for executing a ground altitude test method according to any one of claims 1 to 5 and 7 on a computer is recorded. Sensor unit for measuring the voltage force and total temperature conditions of the current air to simulate the flight conditions of the aircraft; And
A processor for estimating the amount of air supplied to the engine of the vehicle from the measured voltage force and all temperature conditions, and determining a flight condition including at least one of flight altitude information and flight Mach number information from the estimated air amount;
The flight altitude information,
The static pressure of air determined by the following equation (3)

And ground altitude test apparatus, characterized in that determined based on the atmospheric model.
[Equation 3]

The method of claim 9,
The processor,
The ground altitude test apparatus, characterized in that for determining the real-time fuel amount that satisfies a predetermined air excess rate condition using the estimated air amount.

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