CN108827588A - Rocket prizes design method and rocket sled - Google Patents
Rocket prizes design method and rocket sled Download PDFInfo
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- CN108827588A CN108827588A CN201810789509.7A CN201810789509A CN108827588A CN 108827588 A CN108827588 A CN 108827588A CN 201810789509 A CN201810789509 A CN 201810789509A CN 108827588 A CN108827588 A CN 108827588A
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- jet pipe
- rocket
- rocket sled
- mach number
- sled
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to flow field simulation technical field, a kind of rocket sled design method and rocket sled are disclosed.Wherein, this method includes：Jet pipe is set on the Rocket sled test platform of rocket sled；The exit Mach number Ma of the jet pipe is determined according to test mission demand1With dynamic pressure Q1；According to the exit Mach number Ma1With the dynamic pressure Q1Calculate the entrance Mach number Ma of the jet pipe0；According to the entrance Mach number Ma0With the exit Mach number Ma1Determine the jet pipe molded line of the jet pipe；Numerical simulation calculation is carried out to identified jet pipe molded line, and judges the starting capability of the jet pipe according to calculated result；Determine whether that jet pipe, which is arranged, starts accessory according to judging result.Thus, it is possible to design to obtain it is a kind of it is sub- based on capable of covering for rocket sled, across, the fast domain high dynamic pressure aerodynamic testing platform of super, hypersonic width, can be realized the ground simulation ability of wide fast field width dynamic pressure uniform flow field.
Description
Technical field
The present invention relates to flow field simulation technical field more particularly to a kind of rocket sled design method and rocket sleds.
Background technique
Wind-tunnel is to carry out that aerodynamic experiment is the most frequently used, most effective equipment, is to obtain flight vehicle aerodynamic power, heat, load
The essential ground installation of data.At present wind tunnel simulation speed can cover it is sub-, across, it is super, hypersonic.With the bore of wind-tunnel
With the raising of simulated Mach number, it is increasing that wind-tunnel consumes energy.Wind-tunnel is dropped to reduce energy consumption using the velocity of sound is reduced
Low static temperature realizes the simulation of high-speed flow.Therefore, although wind tunnel test is identical as the Mach number of flight test, wind tunnel simulation
Absolute velocity is more much lower than live flying speed, can not simulated flight dynamic pressure.However dynamic pressure directly determines the exhausted of aerodynamic force
It is particularly important analog parameter in the test such as aerodynamic loading, air intake duct protective cover Dynamic Separation to value.It is set at present by wind-tunnel
The standby simulation lower limitation of dynamic pressure can not true simulated flight condition, bring very big uncertainty to this kind of test.
In addition to wind-tunnel, rocket sledge is also a kind of important aerodynamics testing equipment for test simulation, is mostly used
Aeroelasticity, load test in aircraft.However, there is also following two major defects for rocket sledge at present：First is that rocket sledge
The velocity interval of simulation is relatively narrow.Although the maximum speed record of rocket sledge is 8.5 in the world at present, develop more mature available
4 or so are only reached in test.Second is that static pressure, the static temperature of rocket sledge simulation high-speed flow are exactly atmosphere static pressure, the static temperature on ground,
Its analog parameter is fixed.
In conclusion the problem that wind tunnel simulation dynamic pressure is lower than flying condition exists in the prior art, and existing rocket sledge
The fast domain of simulation is low and analog parameter is single.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, a kind of rocket sled design method and rocket sled, energy are provided
Enough solve above-mentioned the problems of the prior art.
Technical solution of the invention：A kind of rocket prizes design method, wherein this method includes：
Jet pipe is set on the Rocket sled test platform of rocket sled；
The exit Mach number Ma of the jet pipe is determined according to test mission demand1With dynamic pressure Q1；
According to the exit Mach number Ma1With the dynamic pressure Q1Calculate the entrance Mach number Ma of the jet pipe0；
According to the entrance Mach number Ma0With the exit Mach number Ma1Determine the jet pipe molded line of the jet pipe；
Numerical simulation calculation is carried out to identified jet pipe molded line, and judges the kinetic energy of the jet pipe according to calculated result
Power；
Determine whether that jet pipe, which is arranged, starts accessory according to judging result.
Preferably, by following formula according to the exit Mach number Ma1With the dynamic pressure Q1Calculate the entrance Mach of the jet pipe
Number Ma0：
Wherein, γ is specific heats of gases ratio, p0It is the input static pressure of jet pipe.
Preferably, numerical simulation calculation is carried out to identified jet pipe molded line, and the jet pipe is judged according to calculated result
Starting capability include：
The flow field that numerical simulation calculation obtains the test section of entire jet pipe and rocket sled is carried out to identified jet pipe molded line
Parameter cloud atlas；
Determine whether part corresponding with the test section of rocket sled is uniform flow place in the cloud atlas；
For uniform flow place, judge that the jet pipe can start, otherwise judges that the jet pipe can not start.
Preferably, determine whether that jet pipe starting accessory, which is arranged, includes according to judging result：
In the case where judging result is that the jet pipe can start, no setting is required, and the jet pipe starts accessory；
In the case where judging result is that the jet pipe can not start, described in the test section corresponding position setting of rocket sled
Jet pipe starts accessory.
Preferably, the jet pipe starting accessory is arranged in the test section corresponding position of rocket sled includes：
In outer wall outlet circumferentially multiple starting accessories of the test section of rocket sled.
Preferably, the starting accessory is injection mouse.
Preferably, the jet pipe starting accessory is arranged in the test section corresponding position of rocket sled includes：
The rocket sled test section arranged downstream described in start accessory.
Preferably, the starting accessory is diffuser.
Preferably, the jet pipe molded line includes Rafael nozzle molded line and flaring molded line.
The present invention also provides a kind of rocket sleds, wherein the rocket sled is prized design method by above-mentioned rocket and is made.
Through the above technical solutions, can design to obtain it is a kind of it is sub- based on capable of covering for rocket sled, across, super, high ultrasound
The fast domain high dynamic pressure aerodynamic testing platform of the width of speed, solves the problems, such as current wind tunnel simulation dynamic pressure lower than flying condition, especially
It extends rocket sledge and simulates that fast domain is low and the single status of analog parameter, so as to realize wide fast field width dynamic pressure uniform flow field
Ground simulation ability (that is, high dynamic pressure uniform incoming flow under the conditions of realizing simulated flight under corresponding speed domain).
Detailed description of the invention
Included attached drawing is used to provide to be further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together to illustrate the principle of the present invention with verbal description.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, be also possible to obtain other drawings based on these drawings.
Fig. 1 is the flow chart that a kind of rocket provided in an embodiment of the present invention prizes design method；
Fig. 2 is a kind of schematic diagram of rocket sled provided in an embodiment of the present invention；
Fig. 3 is the jet pipe schematic diagram for using flaring molded line in the embodiment of the present invention under supersonic speed；
Fig. 4 is test section outlet arrangement injection mouse schematic diagram in the embodiment of the present invention；
Fig. 5 is the schematic diagram of diffuser in the embodiment of the present invention.
Description of symbols
1 rocket sledge sliding rail；2 Rocket sled test platforms；3 rockets；4 high-speed flows；5 jet pipes；6 jet pipe molded line；7 test sections；8 examinations
Test body；The support of 9 testing stand tails；10 flaring molded line；11 injection mouses；12 diffusers.
Specific embodiment
Specific embodiments of the present invention are described in detail below in conjunction with attached drawing.In the following description, for solution
Purpose and not restrictive is released, elaborates detail, to help to be apparent from the present invention.However, to those skilled in the art
It is readily apparent that the present invention can also be practiced in the other embodiments departing from these details for member.
It should be noted that only showing in the accompanying drawings in order to avoid having obscured the present invention because of unnecessary details
Gone out with closely related device structure and/or processing step according to the solution of the present invention, and be omitted with relationship of the present invention not
Big other details.
Fig. 1 is the flow chart that a kind of rocket provided in an embodiment of the present invention prizes design method.
As shown in Figure 1, the embodiment of the invention provides a kind of rockets to prize design method, wherein this method may include：
Jet pipe is arranged on the Rocket sled test platform of rocket sled in S100；
S102 determines the exit Mach number Ma of the jet pipe according to test mission demand1(it is referred to as Mach to be simulated
Number) and dynamic pressure Q1(being referred to as dynamic pressure to be simulated)；
For example, in the situation known to test mission demand, available flight profile, mission profile, flight profile, mission profile contains horse
The corresponding relationship of conspicuous number and dynamic pressure, thus the Mach number of simulation needed for can determining test mission according to flight profile, mission profile and dynamic
Pressure.
S104, according to the exit Mach number Ma1With the dynamic pressure Q1Calculate the entrance Mach number Ma of the jet pipe0(that is,
The work Mach number of rocket sledge)；
S106, according to the entrance Mach number Ma0With the exit Mach number Ma1Determine the jet pipe molded line of the jet pipe；
For example, those skilled in the art can use theory of characteristics or other mature nozzle type line design methods
Jet pipe molded line is designed, the present invention is defined not to this.
S108 carries out numerical simulation calculation to identified jet pipe molded line, and judges the jet pipe according to calculated result
Starting capability；
S110 determines whether that jet pipe, which is arranged, starts accessory according to judging result.
Through the above technical solutions, can design to obtain it is a kind of it is sub- based on capable of covering for rocket sled, across, super, high ultrasound
The fast domain high dynamic pressure aerodynamic testing platform of the width of speed, solves the problems, such as current wind tunnel simulation dynamic pressure lower than flying condition, especially
It extends rocket sledge and simulates that fast domain is low and the single status of analog parameter, so as to realize wide fast field width dynamic pressure uniform flow field
Ground simulation ability (that is, high dynamic pressure uniform incoming flow under the conditions of realizing simulated flight under corresponding speed domain).Also, by this hair
The rocket sled that the bright design method obtains can advantageous support aerodynamic loading, aeroelastic effect test and Dynamic Separation test
Deng.
It according to an embodiment of the present invention, can be by following formula according to the exit Mach number Ma1With the dynamic pressure Q1It calculates
The entrance Mach number Ma of the jet pipe0：
Wherein, γ is specific heats of gases ratio, p0It is the input static pressure of jet pipe.
According to an embodiment of the present invention, numerical simulation calculation is carried out to identified jet pipe molded line, and is tied according to calculating
Fruit judges that the starting capability of the jet pipe may include：
The flow field that numerical simulation calculation obtains the test section of entire jet pipe and rocket sled is carried out to identified jet pipe molded line
Parameter cloud atlas obtains entirely for example, can carry out numerical simulation calculation according to nozzle entry parameter and identified jet pipe molded line
The flow field parameter cloud atlas of the test section of jet pipe and rocket sled, wherein nozzle entry parameter includes entrance Mach number, the jet pipe of jet pipe
Input static pressure and jet pipe entrance static temperature；
Determine whether part corresponding with the test section of rocket sled is uniform flow place in the cloud atlas；
For uniform flow place, judge that the jet pipe can start, otherwise judges that the jet pipe can not start.
Thus, it is possible to which the starting capability to jet pipe judges, and then corresponding reply can be made based on judging result
Measure.
According to an embodiment of the present invention, determine whether that jet pipe starting accessory, which is arranged, can wrap according to judging result
It includes：
In the case where judging result is that the jet pipe can start, no setting is required, and the jet pipe starts accessory；
In the case where judging result is that the jet pipe can not start, described in the test section corresponding position setting of rocket sled
Jet pipe starts accessory.
It is, dynamic auxiliary can be arranged by the corresponding position in test section in the case where jet pipe can not be started
Component is to promote the starting capability of jet pipe.
According to an embodiment of the present invention, the jet pipe is set in the test section corresponding position of rocket sled and starts accessory
May include：
In outer wall outlet circumferentially multiple starting accessories of the test section of rocket sled.
Wherein, the starting accessory can be injection mouse.
Thus, it is possible to promote jet pipe starting capability using ejector action.
According to an embodiment of the present invention, alternatively, the jet pipe is arranged in the test section corresponding position of rocket sled to rise
Dynamic auxiliary component may include：
The rocket sled test section arranged downstream described in start accessory.
Wherein, the starting accessory can be diffuser.
The pressure ratio needed for jet pipe starts can effectively reduce by diffuser as a result, to promote jet pipe starting capability.
According to an embodiment of the present invention, the jet pipe molded line may include Rafael nozzle molded line and flaring molded line.
Fig. 2 is a kind of schematic diagram of rocket sled provided in an embodiment of the present invention.
As shown in Fig. 2, the embodiment of the invention provides a kind of rocket sled, the rocket sled can through the foregoing embodiment in
The rocket sled design method is made.
A kind of aerodynamic testing platform of the rocket sled as wide fast field width dynamic pressure, simulation uniform flow field speed covering Asia, across,
Super, hypersonic, the dynamic pressure coverage area of simulation is big, especially can be with simulated flight condition dynamic pressure.
In Fig. 2, Rocket sled test platform 2 is placed on rocket sled sliding rail 1, and rocket 3 is placed in Rocket sled test platform 2 in the following, fire
Jet pipe 5 (for example, accelerating jet pipe) is installed, Rocket sled test platform 2 accelerates to scheduled speed, high speed gas on arrow sledge testing stand 2
Stream (that is, entrance incoming flow of jet pipe) 4 is further speeded up after just flowing through jet pipe 5,5 exit flow of jet pipe, that is, rocket of the present invention
Prize the higher speed uniform flow field of simulation.Test section 7 maintains biggish uniform flow field.Test body 8 is fixed by testing stand tail support 9
It on Rocket sled test platform 2, is placed in test section 7, relevant test can be carried out to it.If 8 size of test body is smaller,
Test body 8 can be directly placed in jet pipe 5, so as to save the test section 7 being separately configured (it is, direct in test body 8
In the case where being placed in jet pipe 5, the corresponding part of jet pipe 5 is with respect to test section).
On the one hand rocket sled of the present invention is further speeded up by jet pipe 5 realizes the expansion that rocket sledge simulates fast domain
Exhibition, to realize that covering is hypersonic；On the other hand pass through the matching of the operating rate of Rocket sled test platform 2 and jet pipe molded line 6
(in fig. 2 it is shown that a kind of Rafael nozzle molded line) realizes the simulation of wide scope dynamic pressure.
Table 1 shows corresponding parameter and institute of the present invention when existing rocket sledge work Mach number (Ma number) is respectively 2 and 4
The rocket sled (the aerodynamic testing platform of wide speed field width dynamic pressure) stated is using existing rocket sled work Mach number (that is, 2 and 4) as jet pipe
The major parameter of hypersonic (5,6,7) that entry condition is simulated.From table 1 it follows that rocket sledge of the present invention
While covering hypersonic, the simulation of wide scope dynamic pressure is realized.
The example of parameters of the existing rocket sledge of table 1 simulation and the hypersonic example of parameters of rocket of the present invention sled simulation
In addition, dotted line indexes in Fig. 10 and 1 respectively indicates the entrance and exit of jet pipe 5.
Fig. 3 is the jet pipe schematic diagram for using flaring molded line in the embodiment of the present invention under supersonic speed.
As shown in figure 3, jet pipe 5 has flaring molded line 10.
Fig. 4 is test section outlet arrangement injection mouse schematic diagram in the embodiment of the present invention.
As shown in figure 4, in the case where jet pipe can not start, the outer wall outlet for the test section 7 that can be prized in the rocket
A circumferentially circle injection mouse 11, so as to promote the starting capability of jet pipe using ejector action.
The quantity of injection mouse 11 may be set according to actual conditions in those skilled in the art, and the present invention is not to this progress
It limits.
Fig. 5 is the schematic diagram of diffuser in the embodiment of the present invention.
Diffuser 12 shown in Fig. 5 can be right with test section 7 shown in Fig. 2 in the case where jet pipe can not be started
It connects, the pressure ratio of jet pipe starting is effectively reduced, to promote jet pipe starting capability.
As above it describes for a kind of embodiment and/or the feature that shows can be in a manner of same or similar at one or more
It is used in a number of other embodiments, and/or combines or substitute the feature in other embodiments with the feature in other embodiments
It uses.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when using herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step, component or combinations thereof.
The device and method more than present invention can be by hardware realization, can also be by combination of hardware software realization.The present invention
It is related to such computer-readable program, when the program is performed by logical block, the logical block can be made to realize above
The device or component parts, or the logical block is made to realize various method or steps described above.The invention further relates to
For storing the storage medium of procedure above, such as hard disk, disk, CD, DVD, flash memory.
The many features and advantage of these embodiments are clear according to the detailed description, therefore appended claims are intended to
Cover all these feature and advantage of these embodiments fallen into its true spirit and range.Further, since this field
Technical staff is readily apparent that many modifications and changes, therefore is not meant to for the embodiment of the present invention to be limited to illustrated and description essence
Really structurally and operationally, but all suitable modifications and the equivalent fallen within the scope of its can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (10)
1. a kind of rocket prizes design method, which is characterized in that this method includes：
Jet pipe is set on the Rocket sled test platform of rocket sled；
The exit Mach number Ma of the jet pipe is determined according to test mission demand1With dynamic pressure Q1；
According to the exit Mach number Ma1With the dynamic pressure Q1Calculate the entrance Mach number Ma of the jet pipe0；
According to the entrance Mach number Ma0With the exit Mach number Ma1Determine the jet pipe molded line of the jet pipe；
Numerical simulation calculation is carried out to identified jet pipe molded line, and judges the starting capability of the jet pipe according to calculated result；
Determine whether that jet pipe, which is arranged, starts accessory according to judging result.
2. the method according to claim 1, wherein by following formula according to the exit Mach number Ma1It is moved with described
Press Q1Calculate the entrance Mach number Ma of the jet pipe0：
Wherein, γ is specific heats of gases ratio, p0It is the input static pressure of jet pipe.
3. the method according to claim 1, wherein to identified jet pipe molded line carry out numerical simulation calculation,
And judge that the starting capability of the jet pipe includes according to calculated result：
The flow field parameter that numerical simulation calculation obtains the test section of entire jet pipe and rocket sled is carried out to identified jet pipe molded line
Cloud atlas；
Determine whether part corresponding with the test section of rocket sled is uniform flow place in the cloud atlas；
For uniform flow place, judge that the jet pipe can start, otherwise judges that the jet pipe can not start.
4. according to the method described in claim 3, it is characterized in that, determining whether that jet pipe, which is arranged, plays dynamic auxiliary according to judging result
Component includes：
In the case where judging result is that the jet pipe can start, no setting is required, and the jet pipe starts accessory；
In the case where judging result is that the jet pipe can not start, the jet pipe is set in the test section corresponding position of rocket sled
Start accessory.
5. according to the method described in claim 4, it is characterized in that, the jet pipe is arranged in the test section corresponding position in rocket sled
Starting accessory includes：
In outer wall outlet circumferentially multiple starting accessories of the test section of rocket sled.
6. according to the method described in claim 5, it is characterized in that, the starting accessory is injection mouse.
7. according to the method described in claim 4, it is characterized in that, the jet pipe is arranged in the test section corresponding position in rocket sled
Starting accessory includes：
The rocket sled test section arranged downstream described in start accessory.
8. the method according to the description of claim 7 is characterized in that the starting accessory is diffuser.
9. method according to claim 1 to 8, which is characterized in that the jet pipe molded line includes Rafael nozzle
Molded line and flaring molded line.
10. a kind of rocket sled, which is characterized in that the rocket sled is set by rocket of any of claims 1-9 sled
Meter method is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810789509.7A CN108827588A (en) | 2018-07-18 | 2018-07-18 | Rocket prizes design method and rocket sled |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810789509.7A CN108827588A (en) | 2018-07-18 | 2018-07-18 | Rocket prizes design method and rocket sled |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108827588A true CN108827588A (en) | 2018-11-16 |
Family
ID=64140027
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810789509.7A Withdrawn CN108827588A (en) | 2018-07-18 | 2018-07-18 | Rocket prizes design method and rocket sled |
Country Status (1)
| Country | Link |
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| CN (1) | CN108827588A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110207943A (en) * | 2019-06-26 | 2019-09-06 | 中国航天空气动力技术研究院 | Hypersonic wind tunnel virtual flight pilot system and test method |
| CN112067232A (en) * | 2020-08-21 | 2020-12-11 | 中国航天空气动力技术研究院 | Hypersonic wind tunnel test system and method for simulating rocket sled ground effect |
| RU2739537C1 (en) * | 2020-06-25 | 2020-12-25 | Федеральное казенное предприятие "Научно-исследовательский институт "Геодезия" (ФКП "НИИ "Геодезия") | Rocket carriage with controlled braking |
| RU2739546C1 (en) * | 2020-06-25 | 2020-12-25 | Федеральное казенное предприятие "Научно-исследовательский институт "Геодезия" (ФКП "НИИ "Геодезия") | Rocket carriage with controlled vector of thrust |
| CN114136336A (en) * | 2021-11-05 | 2022-03-04 | 江西洪都航空工业股份有限公司 | Acceleration and rocket sled testing device and method |
-
2018
- 2018-07-18 CN CN201810789509.7A patent/CN108827588A/en not_active Withdrawn
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110207943A (en) * | 2019-06-26 | 2019-09-06 | 中国航天空气动力技术研究院 | Hypersonic wind tunnel virtual flight pilot system and test method |
| RU2739537C1 (en) * | 2020-06-25 | 2020-12-25 | Федеральное казенное предприятие "Научно-исследовательский институт "Геодезия" (ФКП "НИИ "Геодезия") | Rocket carriage with controlled braking |
| RU2739546C1 (en) * | 2020-06-25 | 2020-12-25 | Федеральное казенное предприятие "Научно-исследовательский институт "Геодезия" (ФКП "НИИ "Геодезия") | Rocket carriage with controlled vector of thrust |
| CN112067232A (en) * | 2020-08-21 | 2020-12-11 | 中国航天空气动力技术研究院 | Hypersonic wind tunnel test system and method for simulating rocket sled ground effect |
| CN114136336A (en) * | 2021-11-05 | 2022-03-04 | 江西洪都航空工业股份有限公司 | Acceleration and rocket sled testing device and method |
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| PB01 | Publication | ||
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| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20181116 |
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| WW01 | Invention patent application withdrawn after publication |