CN109141903B - Gas rudder hot test method and system - Google Patents
Gas rudder hot test method and system Download PDFInfo
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- CN109141903B CN109141903B CN201811162659.1A CN201811162659A CN109141903B CN 109141903 B CN109141903 B CN 109141903B CN 201811162659 A CN201811162659 A CN 201811162659A CN 109141903 B CN109141903 B CN 109141903B
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Abstract
The invention provides a hot test method and a hot test system for a gas vane, which comprises the following steps: arranging the four rudder surfaces in an X shape on a tail jet pipe of the engine, and executing the following steps: deflecting the control surfaces according to the deflection instructions, wherein the deflection instructions of the two control surfaces on the same diagonal line are the same; acquiring aerodynamic force/moment data of each control surface in real time; and carrying out arithmetic mean operation on the control surfaces adopting the same deflection command. The invention adopts the force measuring device and the gas control surface which are arranged in an X shape at the rear part of the tail nozzle of the engine, and can overcome the defects that the upper force measuring device is burnt out and the lower force measuring device is difficult to install due to the fact that the tail flame of the tail of the engine runs; the gas aerodynamic force of every two control surfaces on the diagonal line of the X shape is subjected to arithmetic average processing, so that the measurement error of the gas aerodynamic force of the control surfaces caused by the eccentricity of the flame of the engine and the self weight of the measuring device can be effectively eliminated.
Description
Technical Field
The invention relates to the technical field of detection, in particular to a gas vane hot test method and a gas vane hot test system.
Background
The gas rudder hot test is a test for acquiring gas aerodynamic force and moment borne by a control surface in real time through the deflection of the gas control surface in the gas flow of a rocket engine and through a force measuring device arranged with the control surface. The engine carrying hot test is a way for obtaining the relatively reliable pneumatic performance of the control surface in the gas flow at present.
In a conventional horizontal engine carrying test, four sets of force measuring devices 1 (an upper force measuring device, a right force measuring device, a lower force measuring device and a left force measuring device) and four corresponding control surfaces 2 are generally installed, and each set of force measuring device corresponds to one control surface. Seen from the rear part of the engine forward along the gas flow direction, the four control surfaces are distributed in a cross shape, as shown in figure 1. After the test is finished, the data collected by each set of force measuring device is independently processed into the pneumatic load of the control surface.
The conventional test method has the following disadvantages: the lower force measuring device is too close to the ground, so that the installation is difficult; the upper force measuring device is easily burnt out due to the fact that the tail flame of the tail of the engine runs after the work of the engine is finished; mounting errors of the nozzle 3 of the engine or vibration in a test easily cause eccentricity of gas flow and four control surfaces, so that the pneumatic load borne by the control surfaces deviates from a normal value; the dead weight of the device and the control surface interferes the data and is not easy to eliminate.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a hot test method and a hot test system for a gas vane.
The invention provides a hot test method for a gas vane, which comprises the following steps: arranging the four rudder surfaces in an X shape on a tail jet pipe of the engine, and executing the following steps:
deflection step: deflecting the control surfaces according to the deflection instructions, wherein the deflection instructions of the two control surfaces on the same diagonal line are the same;
the collection step comprises: acquiring aerodynamic force/moment data of each control surface in real time;
and (3) operation steps: and carrying out arithmetic mean operation on the control surfaces adopting the same deflection command.
Preferably, in the step of deflecting, the deflection commands of the two control surfaces on the same diagonal are the same, and the deflection commands of the control surfaces on different diagonals are different.
Preferably, in the calculating step, the aerodynamic force/moment data of two control surfaces on the same diagonal line are added and divided by 2.
Preferably, in the step of deflecting, the deflection commands of the four control surfaces are the same.
Preferably, in the calculating step, the aerodynamic force/moment data of the four control surfaces are added and divided by 4.
The invention provides a gas vane hot test run test system, which comprises: the four rudder surfaces are distributed in an X shape on the tail spray pipe of the engine, and the following modules are executed:
a deflection module: deflecting the control surfaces according to the deflection instructions, wherein the deflection instructions of the two control surfaces on the same diagonal line are the same;
an acquisition module: acquiring aerodynamic force/moment data of each control surface in real time;
an operation module: and carrying out arithmetic mean operation on the control surfaces adopting the same deflection command.
Preferably, the deflection module has the same deflection instruction for two control surfaces on the same diagonal line, and the deflection instruction for the control surfaces on different diagonal lines is different.
Preferably, the calculation module adds aerodynamic force/moment data of two control surfaces on the same diagonal and divides the added aerodynamic force/moment data by 2.
Preferably, the deflection module has the same deflection instruction for the four control surfaces.
Preferably, the calculation module adds the aerodynamic force/moment data of the four control surfaces and divides the added aerodynamic force/moment data by 4.
Compared with the prior art, the invention has the following beneficial effects:
the invention adopts the force measuring device and the gas control surface which are arranged in an X shape at the rear part of the tail nozzle of the engine, and can overcome the defects that the upper force measuring device is burnt out and the lower force measuring device is difficult to install due to the fact that the tail flame of the tail of the engine runs; the gas aerodynamic force of every two control surfaces on the diagonal line of the X shape is subjected to arithmetic average processing, so that the measurement error of the gas aerodynamic force of the control surfaces caused by the eccentricity of the flame of the engine and the self weight of the measuring device can be effectively eliminated.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural diagram of a prior gas vane hot test run test;
FIG. 2 is a schematic diagram of a hot test structure of the gas vane of the present invention;
FIG. 3 is a schematic diagram of the operation of the present invention;
FIG. 4 is a schematic diagram of the operation of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 2, the hot-test method for the gas vane provided by the invention comprises the following steps: arranging the four rudder surfaces in an X shape on a tail jet pipe of the engine, and executing the following steps:
deflection step: deflecting the control surfaces according to the deflection instructions, wherein the deflection instructions of the two control surfaces on the same diagonal line are the same;
the collection step comprises: acquiring aerodynamic force/moment data of each control surface in real time;
and (3) operation steps: and carrying out arithmetic mean operation on the control surfaces adopting the same deflection command.
Specifically, there are the following two calculation methods:
1. in the deflection step, the deflection commands of the two control surfaces on the same diagonal line are the same, and the deflection commands of the control surfaces on different diagonal lines are different. In the operation step, aerodynamic force/moment data of two control surfaces on the same diagonal line are added and divided by 2.
2. In the step of deflecting, the deflection commands of the four control surfaces are the same. In the calculation step, the aerodynamic force/moment data of the four control surfaces are added and divided by 4.
On the basis of the gas rudder heat test method, the invention also provides a gas rudder heat test system, which comprises
A deflection module: deflecting the control surfaces according to the deflection instructions, wherein the deflection instructions of the two control surfaces on the same diagonal line are the same;
an acquisition module: acquiring aerodynamic force/moment data of each control surface in real time;
an operation module: and carrying out arithmetic mean operation on the control surfaces adopting the same deflection command.
Specifically, there are the following two calculation methods:
1. in the deflection module, the deflection instructions of two control surfaces on the same diagonal line are the same, and the deflection instructions of the control surfaces on different diagonal lines are different. In the operation module, aerodynamic force/moment data of two control surfaces on the same diagonal line are added and divided by 2.
2. In the deflection module, the deflection instructions of the four control surfaces are the same. In the operation module, aerodynamic force/moment data of four control surfaces are added and divided by 4.
Generally, two diagonal lines of the X shape form an included angle of 45 degrees with the ground, the control surface and the force measuring device at the upper left corner are marked as 1#, the control surface and the force measuring device at the upper right corner are marked as 2#, the control surface and the force measuring device at the lower right corner are marked as 3#, and the control surface and the force measuring device at the lower left corner are marked as 4 #. The X-shaped layout can enable the flame of the engine tailing section to pass through the middle of the devices 1# and 2# so as to avoid burning of the force measuring device caused by rising of the engine tailing tail flame, and meanwhile, the force measuring device unit under the engine tailing section is not arranged, so that the installation difficulty is reduced.
The X-shaped layout is combined with the following data processing method, so that the aerodynamic error of the control surface caused by the eccentricity of the flame of the engine can be effectively reduced. For simplicity, the section is taken along the line of the 1# -3# rudder, see fig. 3. In the ideal state, the engine flame CFIntersection point C of central point connecting line of rudder surfaceHAnd (4) overlapping. The main measurement of the gas rudder carrying is the aerodynamic efficiency of the control surface, and the normal force F of the gas rudder carrying and the control surfaceHAre directly related. Theoretical surface of investigation, FHThe windward area S of the flameFIn a linear relationship, i.e. F for rudders 1# and 3#HCan be expressed as
FH-1#,3#∝SF＝k·SF-1#,3#.............(1)
Wherein k is a constant, F, for a particular engineHFor control surface aerodynamic forces/moments, SFIs the area of the control surface immersed in the engine flame. In an eccentric state, CFAnd CHMisaligned, off-center flame centers CF', misalignment can be defined as the length of eccentricity between the twobAnd (4) showing. If the 1# and 3# control surfaces execute the same deflection instruction, the 1# and 3# control surfaces have
FH-1#＝k·SF-1#＝k·(SF-Lb*WH).............(2)
FH-3#＝k·SF-3#＝k·(SF+Lb*WH).............(3)
In the formula WHIs the control surface chord length, and is obtained by (2) + (3)
FH-1#+FH-3#＝2·k·SF＝2·FH-1#,3#
Namely, it is
FH-1#,3#＝1/2·(FH-1#+FH-3#).............(4)
(4) The formula shows that when the flame is in an eccentric state, the aerodynamic force of the control surface caused by eccentricity elimination in a corresponding state can be obtained by carrying out arithmetic mean on the aerodynamic forces of the control surfaces of the No. 1 and the No. 3. Similarly, 2# and 4# have similar formulas
FH-2#,4#＝1/2·(FH-2#+FH-4#).............(5)
In addition, the dead weight of the measurement system and the dead weight of the gas vane itself will cause errors to the measurement system. Analyzing 1# -4# force measuring units, wherein the control surfaces and the balance have the same self weight, and the assumption is that m isgBecause the polarities of the normal forces of the balances corresponding to the 1# -3# and 2# -4# control surfaces are opposite in space, see fig. 4, the balance has
FH-1#＝k·SF-1#-mg·cosθ.............(6)
FH-3#＝k·SF-3#+mg·cosθ.............(7)
Similarly, there are 2# -4# control surfaces
FH-2#＝k·SF-2#+mg·sinθ.............(8)
FH-4#＝k·SF-4#-mg·sinθ.............(9)
If the same deflection command is executed in pairs of 1# -3# and 2# -4#, respectively (6) + (7) and (8) + (9), then there are
FH-1#,3#＝1/2·(k·SF-1#+k·SF-3#).............(10)
FH-2#,4#＝1/2·(k·SF-2#+k·SF-4#).............(11)
Namely, the influence of the self weight of the balance and the control surface can be eliminated by the arithmetic mean calculation result of the aerodynamic force/moment measurement data of the control surface on the diagonal. The data processing method is used for the moment M caused by the normal force of the gas control surfaceHThe same applies.
Before the engine is tested in a hot state, a gas control surface and a corresponding force measuring device are arranged in an X shape. And keeping a gap between the measuring units 1# -2# and 3# -4# to allow the tail flame of the engine to pass through smoothly.
After the engine is ignited, the gas control surface is deflected according to the control surface deflection instruction curve, the two groups of diagonal 1# -3# and 2# -4# control surfaces execute the same deflection instruction, and aerodynamic force data of the control surface are collected. The acquired data is subjected to filtering, balance coefficient matrix transformation, zero drift (Y direction) correction and zero point (X direction) translation, and finally the independent gas aerodynamic force/moment data of each control surface can be obtained.
According to the content of the invention, in the processed data of each control surface, if the control surfaces 1# -3# and 2# -4# execute the same time sequence command pairwise, the gas aerodynamic coefficients of the control surfaces 1# -3# and 2# -4# can be respectively subjected to arithmetic addition and divided by 2; if the four control surfaces deflect to execute the same time sequence instruction, the gas aerodynamic coefficients of the four gas control surfaces of 1#, 2#, 3#, 4# participating in the test can be subjected to arithmetic addition and divided by 4; the final data which eliminates the eccentricity and self-weight influence can be used as the gas aerodynamic force/moment characteristic data of the real control surface.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (2)
1. A hot test run test method for a gas vane is characterized by comprising the following steps: arranging the four rudder surfaces in an X shape on a tail jet pipe of the engine, and executing the following steps:
deflection step: deflecting the control surfaces according to the deflection instructions, wherein the deflection instructions of the two control surfaces on the same diagonal line are the same;
the collection step comprises: acquiring aerodynamic force/moment data of each control surface in real time;
and (3) operation steps: carrying out arithmetic mean operation on the control surfaces adopting the same deflection instruction;
in the deflection step, the deflection instructions of two control surfaces on the same diagonal line are the same, the deflection instructions of the control surfaces on different diagonal lines are different, and in the operation step, the aerodynamic force/moment data of the two control surfaces on the same diagonal line are added and then divided by 2; alternatively, the first and second electrodes may be,
in the step of deflecting, the deflecting instructions of the four control surfaces are the same, and in the step of calculating, the aerodynamic force/moment data of the four control surfaces are added and then divided by 4;
wherein, it includes at the engine tail nozzle to be the X font overall arrangement with four rudders:
two diagonal lines of the X shape form an included angle of 45 degrees with the ground, the control surface and the force measuring device at the upper left corner are marked as 1#, the control surface and the force measuring device at the upper right corner are marked as 2#, the control surface and the force measuring device at the lower right corner are marked as 3#, and the control surface and the force measuring device at the lower left corner are marked as 4 #;
the X-shaped layout installation is combined with the following data processing method:
in the ideal state, the engine flame CFIntersection point C of central point connecting line of rudder surfaceHSuperposition, gas rudder carrying main measurement rudder surface aerodynamic efficiency, normal force F with rudder surfaceHDirect correlation, FHWith the windward area S immersed in the flameFIn a linear relationship, i.e. normal force F of the control surface of the 1# and 3# ruddersH-1#，3#Expressed as:
FH-1＃，3#∝SF＝k·SF-1＃，3#1
wherein k is a constant, SF-1#，3#The areas of the control surfaces 1# and 3# soaked in the flame of the engine, and in an eccentric state, CFAnd CHMisaligned, off-center flame centers CF', misalignment length L between thembThe normal force F of the control surface of the 1# and 3# control surfaces is shown if the 1# and 3# control surfaces execute the same set of deflection instructionsH-1#、FH-3#Comprises the following steps:
FH-1#＝k·SF-1#＝k·(SF-Lb*WH) 2
FH-3#＝k·SF-3#＝k·(SF+Lb*WH) 3
in the formula WHFor the control surface chord length, equation 2+ equation 3 yields:
FH-1#+FH-3#＝2·k·SF＝2·FH-1＃，3#
namely, it is
FH-1#，3#＝1/2·(FH-1#+FH-3#) 4
Formula 4 shows that, when the flame is in an eccentric state, the aerodynamic force of the control surface of the No. 1 and the No. 3 is arithmetically averaged to obtain the aerodynamic force error of the control surface caused by the elimination of the eccentricity in a corresponding state, and similarly, the control surface of the No. 2 and the control surface of the No. 4 also have the formula:
FH-2#，4#＝1/2·(FH-2#+FH-4#) 5
in addition, the dead weight of the measuring system and the dead weight of the gas vane generate errors on the measuring system, a 1# -4# force measuring unit is analyzed, and the control surface and the balance are m in the same dead weightgTheta is FHAnd mgThe polarities of the normal forces of the balances corresponding to the control surfaces 1# -3# and 2# -4# are opposite in space, so that the included angle has
FH-1#＝k·SF-1#-mg·cosθ 6
FH-3#＝k·SF-3#+mg·cosθ 7
Similarly, there are 2# -4# control surfaces
FH-2#＝k·SF-2#+mg·sinθ 8
FH-4#＝k·SF-4#-mg·sinθ 9
If the same deflection command is executed in pairs of 1# -3# and 2# -4#, the formula 6+ the formula 7 and the formula 8+ the formula 9 will have
FH-1#，3#＝1/2·(k·SF-1#+k·SF-3#) 10
FH-2#，4#＝1/2·(k·SF-2#+k·SF-4#) 11
That is, the influence of the balance and the dead weight of the control surface can be eliminated by the arithmetic mean calculation result of the aerodynamic force/moment measurement data of the control surface on the diagonal, and the moment M caused by the normal force of the gas control surface can be processed by the data processing methodHThe same applies.
2. The utility model provides a gas vane hot test run test system which characterized in that includes: the four rudder surfaces are distributed in an X shape on the tail spray pipe of the engine, and the following modules are executed:
a deflection module: deflecting the control surfaces according to the deflection instructions, wherein the deflection instructions of the two control surfaces on the same diagonal line are the same;
an acquisition module: acquiring aerodynamic force/moment data of each control surface in real time;
an operation module: carrying out arithmetic mean operation on the control surfaces adopting the same deflection instruction;
the deflection module has the same deflection instruction for two control surfaces on the same diagonal line, has different deflection instructions for the control surfaces on different diagonal lines, and divides the added aerodynamic force/moment data of the two control surfaces on the same diagonal line by 2; or the deflection instructions of the four control surfaces by the deflection module are the same, and the aerodynamic force/moment data of the four control surfaces are added by the operation module and then divided by 4;
wherein, it includes at the engine tail nozzle to be the X font overall arrangement with four rudders:
two diagonal lines of the X shape form an included angle of 45 degrees with the ground, the control surface and the force measuring device at the upper left corner are marked as 1#, the control surface and the force measuring device at the upper right corner are marked as 2#, the control surface and the force measuring device at the lower right corner are marked as 3#, and the control surface and the force measuring device at the lower left corner are marked as 4 #;
the X-shaped layout installation is combined with the following data processing method:
in the ideal state, the engine flame CFIntersection point C of central point connecting line of rudder surfaceHSuperposition, gas rudder carrying main measurement rudder surface aerodynamic efficiency, normal force F with rudder surfaceHDirect correlation, FHWith the windward area S immersed in the flameFIn a linear relationship, i.e. normal force F of the control surface of the 1# and 3# ruddersH-1#，3#Expressed as:
FH-1#，3#∝SF＝k·SF-1＃，3#1
wherein k is a constant, SF-1#，3#The areas of the control surfaces 1# and 3# soaked in the flame of the engine, and in an eccentric state, CFAnd CHMisaligned, off-center flame centers CF', misalignment length L between thembThe normal force F of the control surface of the 1# and 3# control surfaces is shown if the 1# and 3# control surfaces execute the same set of deflection instructionsH-1#、FH-3#Comprises the following steps:
FH-1#＝k·SF-1#＝k·(SF-Lb*WH) 2
FH-3#＝k·SF-3#＝k·(SF+Lb*WH) 3
in the formula WHFor the control surface chord length, equation 2+ equation 3 yields:
FH-1#+FH-3#＝2·k·SF＝2·FH-1＃，3#
namely, it is
FH-1#，3#＝1/2·(FH-1#+FH-3#) 4
Formula 4 shows that, when the flame is in an eccentric state, the aerodynamic force of the control surface of the No. 1 and the No. 3 is arithmetically averaged to obtain the aerodynamic force error of the control surface caused by the elimination of the eccentricity in a corresponding state, and similarly, the control surface of the No. 2 and the control surface of the No. 4 also have the formula:
FH-2#，4#＝1/2·(FH-2#+FH-4#) 5
in addition, the dead weight of the measuring system and the dead weight of the gas vane generate errors on the measuring system, a 1# -4# force measuring unit is analyzed, and the control surface and the balance are m in the same dead weightgTheta is FHAnd mgThe polarities of the normal forces of the balances corresponding to the control surfaces 1# -3# and 2# -4# are opposite in space, so that the included angle has
FH-1#＝k·SF-1#-mg·cosθ 6
FH-3#＝k·SF-3#+mg·cosθ 7
Similarly, there are 2# -4# control surfaces
FH-2#＝k·SF-2#+mg·sinθ 8
FH-4#＝k·SF-4#-mg·sinθ 9
If the same deflection command is executed in pairs of 1# -3# and 2# -4#, the formula 6+ the formula 7 and the formula 8+ the formula 9 will have
FH-1#，3#＝1/2·(k·SF-1#+k·SF-3#) 10
FH-2#，4#＝1/2·(k·SF-2#+k·SF-4#) 11
That is, the influence of the balance and the dead weight of the control surface can be eliminated by the arithmetic mean calculation result of the aerodynamic force/moment measurement data of the control surface on the diagonal, and the moment M caused by the normal force of the gas control surface can be processed by the data processing methodHThe same applies.
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| CN110987399B (en) * | 2019-12-19 | 2021-11-23 | 武汉天拓宇航智能装备有限公司 | Gas rudder testing device |
| CN112284750B (en) * | 2020-09-10 | 2022-11-22 | 湖北航天飞行器研究所 | Method for testing performance of gas rudder of solid rocket engine |
| CN113932966B (en) * | 2021-09-15 | 2023-12-12 | 航天科工防御技术研究试验中心 | Force measuring device, system and application method of gas rudder |
| CN114235321B (en) * | 2022-02-25 | 2022-04-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel force measurement experimental device integrating gas rudder and spray pipe |
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