JP2017129518A - Verification test system of flight device and verification test method - Google Patents

Abstract

PROBLEM TO BE SOLVED: To carry out a verification test of a test nozzle of rocket engine in a non-combustion manner in a simple manner at a low cost.SOLUTION: In a state that pebbles 12 in a pebble heater tank 10 are heated, after evacuating inside of a tank main body 11 with an ejector 41, a carbon dioxide gas as an injection gas is introduced into the tank main body 11 by vacuum from an injected gas supply source 30. The carbon dioxide gas introduced into the tank main body 11 gets high temperature and high pressure. The high temperature and high-pressure carbon dioxide gas is blown out into a test chamber 20 to which a test nozzle N is attached. Thus, a verification test is carried out by ejecting the gas from the test nozzle N. Inside of the test chamber 20 is vacuumed by the ejector 41 to generate a negative pressure.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a flying device verification test apparatus and a verification test method, and verification of elements of a flying device (rocket engine components, jet engine components, etc.) flying in the high sky, such as a rocket or jet flying in the high sky. The test is devised so that the test can be performed in a non-burning state easily and at low cost.

  In a liquid rocket engine, as a propellant, for example, liquid hydrogen as a fuel and liquid oxygen as an oxidant are sent to a combustion chamber for combustion, and high temperature and high pressure combustion gas is injected at high speed from a nozzle to obtain thrust. . In developing such a rocket engine, a combustion test is conducted at a ground performance confirmation test site to verify it.

  For example, in order to improve the aerodynamic performance and thermal performance of nozzles, which are elements of rocket engines, an ejector is provided for a prototype nozzle (hereinafter referred to as a “prototype nozzle”) at a ground performance confirmation test site. Using the combustion wind tunnel device, the ambient environment conditions are set to the same conditions as the respective positions from the ground to the high sky (for example, 30 km above the ground), and a combustion test is performed. As a result, various verification tests were performed with different ambient environment conditions and combustion conditions, etc., to verify whether the prototype nozzle shape was appropriate, whether unstable vibration occurred, cooling was performed properly, etc. (For example, refer to Patent Document 1).

  As a result of the verification test, if the performance of the prototype nozzle is good, the prototype nozzle is used as an actual nozzle. In other words, the prototype nozzle has a shape, size, and material that can be used as a nozzle of an actual machine.

  Conventionally, when a verification test of a prototype nozzle having the same dimensions as an actual machine is performed, an actual rocket propellant (for example, liquid oxygen, liquid hydrogen, gas hydrogen, liquefied natural gas, gas methane, kerosene, etc.) The combustion gas (mainstream gas) was burned from the prototype nozzle in the same state as the actual rocket launch state, and various performances were confirmed.

JP-A-62-45965

In the prior art, for example, when a verification test is performed on a prototype nozzle at a ground performance confirmation test site, since the following conditions (1) to (3) are satisfied, the performance confirmation test site is large-scale. The test cost was high.
(1) A combustion test is performed by setting the ambient environment conditions to the same conditions as the respective positions from the ground to the high sky (for example, 30 km above the ground).
(2) The prototype nozzle has the same dimensions as the actual machine and is large.
(3) When performing a combustion test, the actual rocket propellant (eg, liquid oxygen, liquid hydrogen, gas hydrogen, liquefied natural gas, gas methane, kerosene, etc.) In a similar state, spray from the prototype nozzle.

  In the present invention, in view of the above-mentioned conventional technology, the verification test of the components (elements) of flying equipment flying in the high sky, such as a rocket engine of a rocket and a jet engine of a jet (next-generation supersonic jet engine), is put in a non-combustion state. It is an object of the present invention to provide a flight equipment verification test apparatus and verification test method that can be performed easily and at low cost.

The flight equipment verification test apparatus of the present invention that solves the above problems is as follows.
An injection gas supply source for supplying an injection gas which is a gas not containing moisture;
A heating container device that is connected to the jet gas supply source by a jet gas pipe provided with a jet gas valve, and that heats the contained gas,
A test chamber in which components of the flying equipment are miniaturized is attached, and a test chamber connected to the heating container device by a blowdown pipe in which a blowdown valve is interposed,
A suction mechanism that is connected to the heating container device by a negative pressure generation pipe in which a negative pressure generation valve is interposed, and is connected to the test chamber by a back pressure generation pipe;
It is characterized by having.

In addition, the flight equipment verification test apparatus of the present invention is
The heating container device is a pebble heater tank provided with a tank body, a pebble housed in the tank body, and a heating device for heating the pebble.

In addition, the flight equipment verification test apparatus of the present invention is
The suction mechanism includes an ejector and a high-pressure air source that sends high-pressure air to the ejector to perform suction operation of the ejector.

In addition, the flight equipment verification test apparatus of the present invention is
The propellant gas is carbon dioxide gas.

In addition, the flight device verification test method of the present invention,
A method for performing a verification test using the above-described flying device verification test apparatus,
Attaching the specimen to the test chamber,
Next, the inside of the heating container device is heated,
Next, the blowdown valve and the injection gas valve are closed and the negative pressure generation valve is opened, and the suction mechanism sucks the inside of the heating container device into a negative pressure state.
Next, the injection gas valve is opened to send the gas from the injection gas supply source into the heating container device, and when the pressure in the heating container device reaches a preset pressure, the injection gas valve is closed. ,
Next, the inside of the test chamber is sucked into the negative pressure state by the suction mechanism,
Next, the blowdown valve is opened, and the injection gas that has become high temperature and high pressure in the heating container device is sent to a test chamber to expose the specimen to the injection gas.
It is characterized by that.

  According to the present invention, it is possible to perform a verification test of elements (parts) of a flying device easily and at low cost without burning an actual rocket propellant.

It is a systematic conceptual diagram which shows the verification test apparatus which concerns on the Example of this invention.

  Hereinafter, a verification test apparatus and a verification test method for a flying device according to the present invention will be described in detail based on examples.

〔Example〕
FIG. 1 is a system conceptual diagram illustrating a verification test apparatus 100 according to an embodiment. In the present embodiment, for example, a verification test of a rocket engine nozzle is performed.
The verification test apparatus 100 is a pebble heater tank 10 that is a heating container device that heats a jet gas and stores it in a pressurized state, a test chamber 20, and a jet that supplies carbon dioxide (CO ₂ ) that is a jet gas. The gas supply source 30 and the suction mechanism 40 are configured as main members.

  In the pebble heater tank 10, a large number of pebbles (alumina balls) 12 are accommodated in a tank body 11. A gas burner 13 is provided in the tank body 11. The pebble 12 can be heated by supplying fuel gas (propane gas) to the gas burner 13 through the pipe L1 and combusting in the tank body 11. A valve V1 is interposed in the pipe L1.

The test chamber 20 is a chamber in which a test nozzle N that is a test body is arranged. Although details will be described later, a high temperature / high pressure injection gas (carbon dioxide gas) is supplied from the pebble heater tank 10 to the test chamber 20, and this high temperature / high pressure injection gas is injected from the test nozzle N. A test nozzle N is attached to the test chamber 20. That is, the test nozzle N is attached to the test chamber 20 so that the test nozzle N is exposed to the injection gas in the same state as when the actual nozzle is exposed to the combustion gas. Then, the injection gas injected from the test nozzle N (exposed to the test nozzle N) is injected into the test chamber 20.
The test nozzle N is a simulated nozzle in which the actual nozzle is downsized. The test nozzle N is smaller in size than the actual nozzle (for example, 1/10 size), but the nozzle function is equivalent to that of the actual nozzle.
The test chamber 20 is connected to the tank body 11 of the pebble heater tank 10 by a pipe (blowdown pipe) L2 in which a valve (blowdown valve) V2 is interposed.

  The injection gas supply source 30 includes a gas cylinder 31 filled with liquefied carbon dioxide gas and a vaporizer 32. The gas cylinder 31 and the vaporizer 32 are connected by a pipe (jet gas pipe) L31 in which a valve (jet gas valve) V31 is interposed. The vaporizer 32 is connected to the tank body 11 of the pebble heater tank 10 by a pipe (pump for injection gas) L32 in which a valve (pump for injection gas) V32 is interposed.

The suction mechanism 40 includes an ejector 41, a silencer 42, an air tank 43, and a compressor 44. The air tank 43 and the compressor 44 form a high pressure air source.
The ejector 41 and the tank body 11 of the pebble heater tank 10 are connected by a pipe (negative pressure generating pipe) L41 provided with a valve (negative pressure generating valve) V41. The ejector 41 and the test chamber 20 are connected by a pipe (back pressure generating pipe) L42. The ejector 41 and the air tank 43 are connected by a pipe (ejector drive pipe) L43 provided with valves (ejector drive valves) V43-1, V43-2. The air tank 43 and the compressor 44 are connected by a pipe L44.
The silencer 42 is attached to the downstream side of the ejector 41 so as to surround the outlet opening of the ejector 41.

  Next, a procedure (test method) for performing a verification test using the verification test apparatus 100 having the above-described configuration will be described.

  In the preparation procedure, the test nozzle N is attached to the test chamber 20. Further, the gas cylinder 31 is filled with liquefied carbon dioxide gas at a high pressure with the valves V31 and V32 closed. Furthermore, by driving the compressor 44 with the valves V43-1 and V43-2 closed, the compressed air is sent to the air tank 43 and the compressed air is stored in the air tank 43. The pressure of the compressed air stored in the air tank 43 is set to several tens of MPa. When the air pressure stored in the air tank 43 reaches a predetermined pressure, the compressor 44 is stopped.

  When the above preparation procedure is completed, the valves V2 and V41 are closed, the valve V1 is opened, fuel gas (propane gas) is supplied to the gas burner 13, the fuel gas is burned in the gas burner 13, and the pebble 12 is heated. To do. The pebble 12 is heated to several hundred degrees Celsius in a short time. When the pebble 12 reaches a preset target temperature, the valve V1 is closed and heating by the gas burner 13 is stopped.

  Next, the valves V43-1, V43-2 are opened, compressed air is sent from the air tank 43 to the ejector 41, and the suction operation of the ejector 41 is started. When the suction operation of the ejector 41 starts, the valve V41 is opened. Then, the air in the tank body 11 of the pebble heater tank 10 is sucked by the ejector 41 through the pipe L41. When the air pressure in the tank body 11 reaches a preset negative pressure, the valve V41 is closed to maintain the negative pressure state in the tank body 11, and the valves V43-1 and V43-2 are closed to the ejector 41. The supply of compressed air is interrupted, and the suction operation of the ejector 41 is stopped.

In this way, when the pebble 12 is heated and the inside of the tank body 11 becomes negative pressure, the valves V31 and V32 are opened. Then, the liquefied carbon dioxide gas is sent to the vaporizer 32 through the pipe L31 and becomes carbon dioxide gas (CO ₂ ). This carbon dioxide gas does not contain moisture. Carbon dioxide gas is sucked into the tank body 11 of the pebble heater tank 10 through the pipe L32 and supplied to the tank body 11.
When carbon dioxide gas is sucked by the negative pressure in the tank body 11 and carbon dioxide gas of several MPa set in advance is accumulated in the tank body 11, the valves V31 and V32 are closed to supply the carbon dioxide gas to the tank body 11. Stop.

  The high-pressure (several MPa) carbon dioxide gas accumulated in the tank body 11 of the pebble heater tank 10 is heated by the pebble 12, and the temperature rises to several hundred degrees Celsius. In this way, high-pressure and high-temperature carbon dioxide gas is stored in the tank body 11 in the tank body 11 of the pebble heater tank 10.

  Next, the valves V43-1, V43-2 are opened again, compressed air is sent from the air tank 43 to the ejector 41, and the suction operation of the ejector 41 is resumed. By this suction operation, the air in the test chamber 20 is sucked through the pipe L42, and the inside of the test chamber 20 becomes negative pressure. That is, the inside of the test chamber 20 is set to a negative pressure (back pressure) state corresponding to a high air environment state.

  When the valve V2 is opened, high-temperature and high-pressure carbon dioxide gas is sent to the test chamber 20 through the pipe L2, and the high-temperature and high-pressure carbon dioxide gas is fed from the test nozzle N to the negative pressure inside the test chamber 20. It is injected (blow down) while expanding. Various verification tests can be performed by inspecting the state of the test nozzle N at the time of injection.

When high-temperature and high-pressure carbon dioxide gas is injected while expanding from the test nozzle N, the pressure after the injection of carbon dioxide gas is one-hundredth of the pressure before the injection, The temperature of the carbon dioxide gas rapidly decreases due to the sudden decrease in pressure. Even if such a rapid temperature drop occurs, the carbon dioxide gas, which is the injection gas, does not contain moisture, so that there is no problem that ice condensed with water adheres to the test nozzle N.
If air is used instead of carbon dioxide, when high-temperature and high-pressure air is injected and expands, the temperature of the air rapidly decreases as the pressure decreases rapidly, condensing moisture contained in the air. The ice may adhere to the test nozzle N. When ice adheres to the test nozzle N, an event such as a change in the vibration state of the test nozzle N occurs, which causes a problem that accurate verification cannot be performed.

  The carbon dioxide gas injected from the test nozzle N is sucked by the ejector 41 through the pipe L42, silenced through the silencer 42, and then released to the atmosphere. The compressed air sent from the air tank 43 to the ejector 41 is also discharged from the ejector 41 and then silenced through the silencer 42 and then released to the atmosphere.

  In this example, when carbon dioxide gas is being injected from the test nozzle N, the suction force of the ejector 41 is adjusted by adjusting the opening of the valve V43-2 while the valve V43-1 is open. By doing so, the negative pressure (back pressure) in the test chamber 20 at the time of injection can be adjusted. By doing in this way, the verification test under each environmental condition in which back pressure conditions differ can be performed.

  In this example, it is possible to conduct a verification test using an injection gas (carbon dioxide) that does not contain moisture without burning actual rocket propellants (for example, liquid hydrogen and liquid oxygen). A combustor or the like for burning is unnecessary. Further, the test nozzle N scaled down with respect to the actual nozzle is used instead of the actual nozzle. For this reason, the verification test apparatus 100 of the present example can perform a verification test easily and at low cost while being simple and small in size.

  In the above example, the test nozzle N is tested for verification, but the cone (payload), which is the first part of the rocket, is downsized, and the nozzle of the next-generation ultra-high speed jet engine. By attaching a test nozzle having a reduced size (downsize) to the test chamber 20, a verification test of such an element (part) can be performed.

  In the above example, carbon dioxide gas is used as the injection gas, but air, nitrogen, helium gas, etc. can also be used as the injection gas.

  Further, in the above example, the pebble heater tank 10 is used as the heating container device. However, the pebble heater tank is not limited to the pebble heater tank as long as it is a device that can store and heat the injected gas at a high pressure. For example, a device having a high-pressure tank equipped with a heating device such as a heat exchanger can be employed.

  INDUSTRIAL APPLICABILITY The present invention can be used to perform verification tests on elements (parts) of flying devices that fly in the high sky such as rockets and jet aircraft.

DESCRIPTION OF SYMBOLS 10 Pebble heater tank 11 Tank main body 12 Pebble 13 Gas burner 20 Test chamber 30 Injection gas supply source 31 Gas cylinder 32 Vaporizer 40 Suction mechanism 41 Ejector 42 Silencer 43 Air tank 44 Compressor 100 Verification test device N Test nozzle

Claims (5)

An injection gas supply source for supplying an injection gas which is a gas not containing moisture;
A heating container device that is connected to the jet gas supply source by a jet gas pipe provided with a jet gas valve, and that heats the contained gas,
A test chamber in which components of the flying equipment are miniaturized is attached, and a test chamber connected to the heating container device by a blowdown pipe in which a blowdown valve is interposed,
A suction mechanism that is connected to the heating container device by a negative pressure generation pipe in which a negative pressure generation valve is interposed, and is connected to the test chamber by a back pressure generation pipe;
A flight equipment verification test apparatus characterized by comprising: In claim 1,
The flying container verification test apparatus according to claim 1, wherein the heating container apparatus is a pebble heater tank including a tank body, a pebble housed in the tank body, and a heating device for heating the pebble. In claim 1 or claim 2,
The flying device verification test apparatus according to claim 1, wherein the suction mechanism includes an ejector and a high-pressure air source that sends high-pressure air to the ejector to cause the ejector to perform suction operation. In any one of Claims 1-3,
The flying device verification apparatus, wherein the jet gas is carbon dioxide. A method for performing a verification test using the flying device verification test apparatus according to claim 1,
Attaching the specimen to the test chamber,
Next, the inside of the heating container device is heated,
Next, the blowdown valve and the injection gas valve are closed and the negative pressure generation valve is opened, and the suction mechanism sucks the inside of the heating container device into a negative pressure state.
Next, the injection gas valve is opened to send the gas from the injection gas supply source into the heating container device, and when the pressure in the heating container device reaches a preset pressure, the injection gas valve is closed. ,
Next, the inside of the test chamber is sucked into the negative pressure state by the suction mechanism,
Next, the blowdown valve is opened, and the injection gas that has become high temperature and high pressure in the heating container device is sent to a test chamber to expose the specimen to the injection gas.
A method for verifying a flying device.

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