CN112985681B - RBCC injection mode internal thrust experiment measurement and evaluation method - Google Patents
RBCC injection mode internal thrust experiment measurement and evaluation method Download PDFInfo
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
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Abstract
The invention discloses a RBCC injection mode internal thrust experiment measurement and evaluation method, which is characterized in that an inlet pipeline of an engine is arranged perpendicular to the thrust direction, and an outlet section is inserted into a backpressure injector, and comprises the following steps: acquiring push-pull force on an engine, ambient pressure and pressure of an outlet section; obtaining the suction force of the back pressure ejector to the engine based on the environmental pressure of the engine and the pressure of the outlet section; obtaining the outlet impulse of the engine based on the push-pull force on the engine and the suction force of the back pressure ejector to the engine; obtaining an inlet impulse of the engine based on an air flow in the engine; and obtaining the internal thrust of the engine based on the outlet impulse and the inlet impulse. The method avoids the limitation of the geometric inlet of the engine on the air flow, can obtain the maximum induced flow of the engine through the pneumatic blockage, estimates the maximum air flow corresponding to the inner flow passage of the engine at the moment, carries out reverse design on the air inlet passage, optimizes the flow setting of the engine and enables the engine performance to be optimal.
Description
Technical Field
The invention relates to the technical field of thrust measurement, in particular to an experimental measurement and evaluation method for thrust in an RBCC injection mode.
Background
An RBCC (Rocket-Based Combined Cycle) engine injection mode is an important working mode of the RBCC engine. The jet flow of air is limited by various factors, namely a geometric throat, a pneumatic block and a thermal block. The injection mode of the RBCC combined power engine is an important working mode different from other air-breathing ramjet engines. The low speed of the incoming air flow in the injection mode is generally Mach 0 to Mach 2.5. In the mode, the air has a weak ram effect, so that the rocket jet and the air are required to be mixed and pressurized in an inner flow passage, and then the thrust is provided for the engine, so that the oil consumption is high in the stage, and the main oil consumption stage of the RBCC engine is realized.
If the air flow is limited by the geometric throat of the air inlet, the injection performance extreme value of the engine is difficult to directly obtain in basic research. The injection mode internal thrust of the RBCC engine can be directly used for evaluating the performance of different injection mode schemes. By adopting a conventional direct connection type experimental method, the internal thrust of the engine cannot be obtained, and only the thrust gain in the through-flow and afterburning processes of the engine can be obtained; by adopting the free jet experiment, the internal thrust of the engine can not be directly obtained due to factors such as external resistance, the throat part of an air inlet and the like. In addition, the total air pressure of a large part of the RBCC engine under the injection mode working condition is near 100kpa, and the direct connection mode and the free jet mode are not suitable.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides an experimental measurement and evaluation method for the thrust in the RBCC injection mode, which can be beneficial to the design optimization of an RBCC engine and the acceleration performance improvement.
In order to achieve the purpose, the invention provides an RBCC injection mode internal thrust experiment measurement and evaluation method, an inlet pipeline of an engine is arranged perpendicular to the thrust direction, the outlet section of the RBCC engine is inserted into a back pressure injector, a sealing structure is arranged between the engine and the back pressure injector, and no force is transmitted between the engine and the back pressure injector, the measurement and evaluation method specifically comprises the following steps:
step 1, acquiring push-pull force on an engine, ambient pressure of the engine and pressure of an outlet section of the engine;
step 2, obtaining the suction force of the back pressure ejector to the engine based on the environmental pressure of the engine and the pressure of the outlet section of the engine;
step 3, obtaining the outlet impulse of the engine based on the push-pull force on the engine and the suction force of the back pressure ejector to the engine;
step 4, obtaining the inlet impulse of the engine based on the air flow in the engine;
and 5, obtaining the internal thrust of the engine based on the outlet impulse and the inlet impulse of the engine.
In one embodiment, a push-pull sensor is provided on the engine.
In one embodiment, the engine is provided with pressure sensors in the air inlet section, the air outlet section and along the way.
In one embodiment, in step 2, the obtaining of the suction force of the back pressure ejector to the engine based on the ambient pressure of the engine and the pressure of the outlet cross section of the engine specifically includes:
F3＝(Ps-Pb)Aout
in the formula, F3For suction of the back-pressure ejector to the engine, PsIs the ambient pressure, P, at which the engine is locatedbPressure at the outlet cross-section of the engine, AoutIs the area of the cross section of the engine outlet.
In one embodiment, in step 3, the obtaining of the outlet impulse of the engine based on the push-pull force on the engine and the suction force of the back pressure ejector to the engine specifically includes:
F2+F3+F4＝0
in the formula, F2Is a push-pull force on the engine, F3For suction of the back-pressure ejector to the engine, F4Is the outlet impulse of the engine.
In one embodiment, in step 4, the intake impulse of the engine is obtained based on the air flow in the engine, specifically:
in the formula, F1Is the inlet impulse of the engine and is,
is the air flow rate, gamma, in the enginesIs the specific heat ratio constant of air, PsIs the ambient pressure, P, at which the engine is locatedbIs the pressure at the outlet cross section of the engine; c. CsPressure of the outlet cross section being PbIn this case, the sound velocity corresponding to the flying height is large.
In one embodiment, in step 5, the obtaining of the internal thrust of the engine based on the outlet impulse and the inlet impulse of the engine specifically includes:
FN＝F4-F1
in the formula, FNIs the internal thrust of the engine, F4Is the outlet impulse of the engine, F1Is the inlet impulse of the engine.
The RBCC injection mode internal thrust experimental measurement and evaluation method avoids the limitation of an engine geometric inlet on air flow, directly researches the performance of an engine internal flow passage on thrust, and then can obtain the maximum injection flow of an engine through a pneumatic block in the experimental process to ensure that the engine performance is optimal.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an experimental measurement and evaluation system for thrust in an RBCC injection mode in an embodiment of the invention;
fig. 2 is a schematic flow chart of an experimental measurement and evaluation method for thrust in an RBCC injection mode in the embodiment of the invention.
The reference numbers illustrate: the system comprises an engine 1, an air inlet pipeline 101, an ejector 2, a driving air inlet 201, an equal straight section 202, an expansion section 203, a rocket 102, a push-pull sensor 3 and a pressure sensor 4.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 1 shows a measurement and evaluation system for thrust test in an RBCC injection mode, which includes an RBCC engine (hereinafter referred to as "engine"), a pressurized injector (hereinafter referred to as "injector"), a push-pull sensor 3 and a plurality of pressure sensors 4, the push-pull sensor 3 being disposed on the engine 1. Wherein, the head of the engine 1 is provided with an air inlet pipeline 101, and the air inlet pipeline is vertical to the thrust direction of the engine 1; the push-pull sensor 3 is arranged at the head of the engine 1 to obtain the push-pull force on the engine 1; the number of the pressure sensors 4 is plural, and each of the pressure sensors 4 is provided on a side wall surface of the air inlet duct 101, on an outlet section of the engine 1, and on an inner flow passage way of the engine 1 to obtain a pressure of the outlet section of the engine 1 and a distribution of the on-way pressure.
A rocket 102 is arranged in the engine 1, and fuel gas of the rocket 102 is mixed with air injected by an air inlet pipeline in the engine 1. The cross section of the outlet of the engine 1 is inserted into the ejector 2, the engine 1 and the ejector 2 are sealed through rubber pads, and force transmission does not exist between the engine 1 and the backpressure ejector 2. The driving air of the ejector 2 enters the ejector 2 through a driving air inlet 201, and the mixed air in the engine 1 is mixed with the driving air of the ejector 2 and then discharged into the atmosphere through the equal-straight section 202 of the ejector 2 and the expansion section 203 of the ejector 2.
Because the engine 1 and the ejector 2 are not mutually transmitted, in the working process of the engine 1, the thrust direction of the engine 1, the acting force of the pressure sensor 4, the acting force of the backpressure ejector 2, the suction force of the ejector 2 to the engine 1 and the thrust in the rack of the engine 1 are balanced in stress. Therefore, the internal thrust of the engine 1 can be obtained by the acting force of the pressure sensor 4, the acting force of the back pressure ejector 2 and the suction force of the ejector 2 to the engine 1.
The force of the pressure sensor 4 can be obtained by reading the force of the injector 2 at the outlet section of the engine 1The suction force on the engine 1 can be determined by the cross-sectional area A of the outlet of the engine 1outAnd the pressure sensor 4, so that the thrust in the stand of the engine 1 can be obtained. But the thrust in the gantry at this time is different from the thrust in the real case because the air inlet is perpendicular to the thrust direction of the engine 1 at this time, and thus the force of the air inlet impulse on the engine 1 in the real case is offset. The corresponding flying environment pressure of the engine 1 at the moment can be obtained through conversion according to the pressure sensor 4, the flying Mach number and the flying speed are obtained according to the total static pressure relation, and the jet flow of the air is obtained through the pressure sensor 4. Thus, aircraft inlet momentum can be obtained. The internal thrust of the RBCC engine 1 in the injection mode can be measured and obtained through the calculation method.
Based on the measurement and evaluation system for the RBCC injection mode internal thrust experiment, the embodiment also discloses a measurement and evaluation method for the RBCC injection mode internal thrust experiment, and referring to fig. 2, the measurement and evaluation method specifically comprises the following steps:
step 1, acquiring push-pull force on an engine, ambient pressure of the engine and pressure of an outlet section of the engine;
step 2, obtaining the suction force of the back pressure ejector to the engine based on the environmental pressure of the engine and the pressure of the outlet section of the engine, and specifically comprising the following steps:
F3＝(Ps-Pb)Aout
in the formula, F3For suction of the back-pressure ejector to the engine, PsThe ambient pressure of the engine is about 101325pa if the pressure is at sea level; pbPressure at the outlet cross-section of the engine, AoutIs the area of the engine outlet cross section;
and 3, obtaining the outlet impulse of the engine based on the push-pull force on the engine and the suction force of the back pressure ejector to the engine, and specifically comprising the following steps:
F2+F3+F4＝0
in the formula, F2Is a push-pull force on the engine, F4Is the outlet impulse of the engine;
step 4, the engine is subjected to impulse of airflow to the inlet of the engine during flying, and the total pressure and the total temperature of air are atmospheric parameters during experiment, so that the pressure of the section of the outlet of the engine is PbFrom the on-way pressure distribution on the engine and the determined geometry, the air flow rate can be estimated
The estimation process is a conventional counting method, and therefore, the present embodiment is not described in detail. Therefore, the inlet impulse of the engine can be obtained based on the air flow in the engine, and specifically:
in the formula, F1Is the inlet impulse of the engine and is,
is the air flow rate, gamma, in the enginesIs the specific heat ratio constant of air; c. CsPressure of the outlet cross section being PbUnder the condition, the sound velocity corresponding to the flight altitude is large;
and 5, obtaining the internal thrust of the engine based on the outlet impulse and the inlet impulse of the engine, which specifically comprises the following steps:
FN＝F4-F1
in the formula, FNIs the internal thrust of the engine.
The measurement and evaluation method avoids the limitation of the geometric inlet of the engine on the air flow, directly researches the performance of the inner flow passage of the engine on the thrust, can obtain the maximum jet flow of the engine through the pneumatic block plug in the experimental process to ensure that the performance of the engine is optimal, can estimate the maximum air flow corresponding to the inner flow passage of the engine at the moment in actual operation, and then performs reverse design on an air inlet passage to optimize the flow setting of the engine to ensure that the performance of the engine is optimal.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (7)
1. The method for measuring and evaluating the internal thrust experiment in the RBCC injection mode is characterized in that an inlet pipeline of an engine is perpendicular to the thrust direction, the outlet section of the RBCC engine is inserted into a back pressure ejector, a sealing structure is arranged between the engine and the back pressure ejector, and force transmission does not exist between the engine and the back pressure ejector, and the method for measuring and evaluating the internal thrust experiment in the RBCC injection mode specifically comprises the following steps:
step 1, acquiring push-pull force on an engine, ambient pressure of the engine and pressure of an outlet section of the engine;
step 2, obtaining the suction force of the back pressure ejector to the engine based on the environmental pressure of the engine and the pressure of the outlet section of the engine;
step 3, obtaining the outlet impulse of the engine based on the push-pull force on the engine and the suction force of the back pressure ejector to the engine;
step 4, obtaining the inlet impulse of the engine based on the air flow in the engine;
and 5, obtaining the internal thrust of the engine based on the outlet impulse and the inlet impulse of the engine.
2. The experimental measurement and evaluation method for thrust in an RBCC injection mode is characterized in that a push-pull sensor is arranged on the engine.
3. The experimental measurement and evaluation method for thrust in an RBCC injection mode is characterized in that a pressure sensor is arranged on the air inlet section, the air outlet section and the path of the engine.
4. The RBCC injection mode internal thrust experimental measurement and evaluation method according to claim 1, 2 or 3, wherein in the step 2, the suction force of the back pressure injector to the engine is obtained based on the ambient pressure of the engine and the pressure of the outlet section of the engine, and specifically comprises the following steps:
F3＝(Ps-Pb)Aout
in the formula, F3For suction of the back-pressure ejector to the engine, PsIs the ambient pressure, P, at which the engine is locatedbPressure at the outlet cross-section of the engine, AoutIs the area of the cross section of the engine outlet.
5. The experimental measurement and evaluation method for thrust in an RBCC injection mode according to claim 1, 2 or 3, wherein in the step 3, the outlet impulse of the engine is obtained based on the push-pull force on the engine and the suction force of the backpressure injector to the engine, and specifically comprises the following steps:
F2+F3+F4＝0
in the formula, F2Is a push-pull force on the engine, F3For suction of the back-pressure ejector to the engine, F4Is the outlet impulse of the engine.
6. The experimental measurement and evaluation method for thrust in an RBCC injection mode according to claim 1, 2 or 3, wherein in the step 4, the inlet impulse of the engine is obtained based on the air flow in the engine, and specifically comprises the following steps:
in the formula, F1Is the inlet impulse of the engine and is,
is the air flow rate, gamma, in the enginesIs the specific heat ratio constant of air, PsIs the ambient pressure, P, at which the engine is locatedbIs the pressure at the outlet cross section of the engine; c. CsPressure of the outlet cross section being PbIn case of corresponding fly heightThe sound velocity of the degree.
7. The experimental measurement and evaluation method for internal thrust of an RBCC injection mode according to claim 1, 2 or 3, wherein in the step 5, the internal thrust of the engine is obtained based on the outlet impulse and the inlet impulse of the engine, and specifically comprises the following steps:
FN＝F4－F1
in the formula, FNIs the internal thrust of the engine, F4Is the outlet impulse of the engine, F1Is the inlet impulse of the engine.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8598925B1 (en) * | 2012-07-16 | 2013-12-03 | Nanowave Technologies Inc. | Frequency determination circuit and method |
| CN110362783A (en) * | 2019-05-31 | 2019-10-22 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine thrust calculation method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8598925B1 (en) * | 2012-07-16 | 2013-12-03 | Nanowave Technologies Inc. | Frequency determination circuit and method |
| CN110362783A (en) * | 2019-05-31 | 2019-10-22 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine thrust calculation method |
Non-Patent Citations (1)
| Title |
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| 国外组合推进技术研究现状;杨潮兴等;《飞航导弹》;20121231(第5期);全文 * |
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