CN102828851A - Cold flow test device for scaling linear plug type spray pipe carrier - Google Patents
Cold flow test device for scaling linear plug type spray pipe carrier Download PDFInfo
- Publication number
- CN102828851A CN102828851A CN2012102921897A CN201210292189A CN102828851A CN 102828851 A CN102828851 A CN 102828851A CN 2012102921897 A CN2012102921897 A CN 2012102921897A CN 201210292189 A CN201210292189 A CN 201210292189A CN 102828851 A CN102828851 A CN 102828851A
- Authority
- CN
- China
- Prior art keywords
- lifting body
- plug nozzle
- rear portion
- force balance
- plug
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Abstract
The invention discloses a cold flow test device for a scaling linear plug type spray pipe carrier. The cold flow test device comprises a lifting body component, a plug type spray pipe component, a force-measuring balance component and a supporting component, wherein a front part of a lifting body, a middle part of the lifting body and a rear part of the lifting body all have hollow structures and are fixedly connected in turn, so as to form a lifting body appearance of the carrier; the lifting body component comprises the front part of the lifting body, the middle part of the lifting body, the rear part of the lifting body, a vertical tail, a horizontal airfoil, an airfoil pin, a bottom cover plate and a belly cover plate; the plug type spray pipe component comprises a tail shell, a plug type spray pipe engine and an engine pin; the plug type spray pipe engine is mounted in the tail shell; the force-measuring balance component comprises a force-measuring balance and a balance protecting cover; and the supporting component comprises a supporting arm, a front rectifying cover and a rear rectifying cover. The cold flow test device has a simple structure and is low in cost; the plug type spray pipe engine of the cold flow test device is a single part, so that the structure is simple; the device is only applied to a cold flow test; and the ordinary carbon steel is selected as the raw material, so that the cost is low.
Description
Technical field
The present invention relates to Aero-Space engine test technical field, a kind of specifically multi-functional, simple in structure, with low cost contracting than linear plug nozzle vehicle cold-flow test device.
Background technique
Improving nozzle efficiency, alleviate jet pipe weight, is the main target of rocket motor design.Because the Aero-Space vehicle will experience different flying heights in flight course; Tradition bell jet pipe only could obtain best performance at design height; Be higher or lower than design height and all can cause certain performance loss, promptly owe expansion-loss or overexpansion loss.Pneumatic plug nozzle is because the open fluidal texture in its outside; Making that combustion gas is one-sided communicates with external pressure; Influenced by the environment back-pressure and regulate swelling state automatically, combustion gas is on whole flying height fully or near the state of complete expansion, the height performance of jet pipe has automatic compensation characteristic.Research both at home and abroad shows that near the performance of plug nozzle design point is close with desirable bell jet pipe, and low-altitude performance obviously is superior to the bell jet pipe, and nozzle efficiency can improve 20%～30% at most; Area plug nozzle length when identical is short more than the bell jet pipe, and weight can alleviate.The application prospect of plug nozzle is extremely extensive, and its altimetric compensation characteristic makes it to be particularly useful for the aloft work environment of the big or large size ratio of requirement exit area ratio excursion.The reusable vehicle that is the basis with the plug nozzle motor is expected to be used for many important space industries as a general space means of transportation, like manned space flight, the transportation of space station goods and materials, interspace transportation, moonfall transportation, satellite lift-launch etc.
It is to derive from the open fluidal texture in its outside that plug nozzle has the altimetric compensation characteristic; But the influence that this semi-open fluidal texture is outflowed easily; Particularly transonic speed with the influence of ultrasound velocity outflow, be one of importance of comprehensive assessment plug nozzle performance to the research of outflow influence.Owing to the plug nozzle performance loss that causes of influence of outflow stream field comprises following two-part: first portion's loss derives from the drag losses of vehicle bottom.The pressure of vehicle bottom is lower than environmental stress, and the vehicle bottom can produce certain resistance, but the vehicle that this base drag is lost being power with traditional bell jet pipe motor also exists.The second portion loss derives from the variation of plug poppet surface pressure.Flow separation takes place in outflow in vehicle bottom, cause near plug awl main flow local compression to be lower than the external pressure of infinite distant place, causes plug awl main flow the overexpansion phenomenon to occur, and the pressure of plug awl wall reduces.
The tradition rocket motor is normally realized what thrust vectoring was controlled through gimbaled nozzle, and solid rocket motor nozzle is installed flexible linking device in throat, and liquid propellant rocket engine is installed gimbal mount assembly usually to realize the swing of entire engine.Because the plug nozzle motor often adopts the mode of dispersion that thrust is transferred on the vehicle; Just can change the thrust size through the flow size that difference is regulated symmetrical two groups of jet pipes to realize the thrust vectoring control of motor; The advantage of difference Flow-rate adjustment thrust vectoring control is that system can loss of weight; Increase thrust weight ratio, not interference flowing field etc.
Summary of the invention
To the objective of the invention is in order addressing the above problem, to propose a kind of multi-functional, simple in structure, with low cost contracting than linear plug nozzle vehicle cold-flow test device.This device is the plug nozzle vehicle subscale test model that has the lifting body profile, the regime of flight of the more approaching actual vehicle of test result.This device is equipped with high-precision six component force balances, can measure six component values of vehicle under the different tests operating mode, and is provided with the measurement interface of collection chamber stagnation pressure and plug awl wall static pressure.
A kind of contracting than linear plug nozzle vehicle cold-flow test device comprises lifting body assembly, plug nozzle assembly, force balance assembly and supporting component;
The lifting body assembly comprises lifting body front portion, lifting body middle part, lifting body rear portion, vertical fin, horizontal tail, aerofoil pin, bottom cover plate and belly cover plate; Lifting body front portion, lifting body middle part and lifting body rear portion are hollow structure, and lifting body front portion, lifting body middle part and lifting body rear portion are fixedly connected sequentially, and constitute the lifting body profile of vehicle; Anterior and the inner hollow structure in lifting body middle part of lifting body is used to install the force balance assembly, and lifting body rear portion inner hollow structure is used for installing stopper formula nozzle component; Two vertical fins and two horizontal tails are installed on the lifting body rear portion through aerofoil pin symmetry respectively, and vertical fin is installed in the top at lifting body rear portion, and horizontal tail is installed in two sides at lifting body rear portion; The plug nozzle motor of plug nozzle component internal is given prominence to tail end plane, lifting body rear portion; In outstanding plug nozzle motor both sides; Each installs a bottom cover plate, and bottom cover plate is fixedly connected the lifting body rear portion, and the force balance assembly is fixedly connected supporting component; At belly cover plate of each side installation of supporting component, the belly cover plate is fixedly connected the bottom of lifting body;
The plug nozzle assembly comprises tail shell, plug nozzle motor and motor pin; It is inner that the plug nozzle motor is installed in the tail shell; Plug nozzle motor and tail shell are fixed in the lifting body rear portion through the motor pin; Plug nozzle motor front portion is provided with upper and lower two collection chambers, and the front portion of each collection chamber is provided with a collection chamber total pressure measurement interface, connects the normal pressure sensor through welding thin copper pipe; Be used for measuring the stagnation pressure of collection chamber; Arrange respectively that on the centre symmetry line of the upper and lower plug awl wall of plug nozzle motor three plug awl wall static pressures measure interfaces, connect the normal pressure sensor, be used for measuring the static pressure of plug awl wall through welding thin copper pipe; Be symmetrical set a pressurized gas interface in the left and right sides of each collection chamber, connect high-pressure air through welding air feed copper pipe and supply with gas cylinder;
The force balance assembly comprises force balance and balance safety cover; Force balance and balance safety cover are positioned at the inside at lifting body front portion and lifting body middle part; The front portion of force balance is through the support arm of balance safety cover fixed connection supporting component, and the rear portion of force balance is fixed on the lifting body middle part;
Supporting component comprises support arm, front fairing and back cowling; Support arm one end connects the balance safety cover in the force balance assembly; The other end is provided with tapped hole; Be fixed on the test air tunnel wallboard through tapped hole; Front fairing, back cowling are installed on the support arm, and front fairing inside is used for placing the connecting line of force balance, and back cowling inside is used for placing the thin copper pipe of connection of normal pressure sensor and the air feed copper pipe that plug nozzle motor collection chamber connects.
The invention has the advantages that:
(1) research range is wide, research contents is abundant: testing apparatus both can have been studied outer flow disturbance to linear plug nozzle Effect on Performance; The difference Flow-rate adjustment thrust vectoring control performance of linear plug nozzle can be studied again, the characteristics of flow disturbance lower linear plug nozzle difference Flow-rate adjustment thrust vectoring control outside can also be studied;
(2) test result rationally, reliably: testing apparatus is the plug nozzle vehicle subscale test model that has the lifting body profile, the regime of flight of the more approaching actual vehicle of test result;
(3) multiple functional: testing apparatus and corresponding test air tunnel cooperate, and can study the performance of different outflow Mach numbers and outflow angle of attack lower linear plug nozzle.Test adopts high-precision six component force balances to measure six component values of vehicle, and is provided with the measurement interface of collection chamber stagnation pressure and plug awl wall static pressure;
(4) simple in structure, with low cost: the plug nozzle motor of testing apparatus is single component, and is simple in structure, and device only is used for cold-flow test, and the material selection Ordinary Steel is with low cost.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is a complete section schematic representation of the present invention;
Fig. 3 is lifting body assembly of the present invention and force balance assembly schematic representation;
Fig. 4 is a plug nozzle assembly schematic representation of the present invention;
Fig. 5 is a testing apparatus supporting component schematic representation of the present invention.
Among the figure:
1-lifting body assembly 2-plug nozzle assembly 3-force balance assembly
The anterior 6-lifting body of 4-supporting component 5-lifting body middle part
7-lifting body rear portion 8-vertical fin 9-aerofoil pin
10-horizontal tail 11-bottom cover plate 12-belly cover plate
13-force balance 14-balance safety cover 15-plug nozzle motor
16-plug awl wall static pressure is measured interface 17-collection chamber 18-pressurized gas interface
19-motor pin 20-tail shell 21-collection chamber total pressure measurement interface
Cowling behind the 22-front fairing 23-support arm 24-
Embodiment
To combine accompanying drawing and embodiment that the present invention is done further detailed description below.
The present invention is a kind of contracting than linear plug nozzle vehicle cold-flow test device, and is as depicted in figs. 1 and 2, comprises lifting body assembly 1, plug nozzle assembly 2, force balance assembly 3 and supporting component 4.
As shown in Figure 3, lifting body assembly 1 comprises that lifting body is anterior 5, lifting body middle part 6, lifting body rear portion 7, two vertical fins 8, two 10,12 aerofoil pins of horizontal tail 9, two bottom cover plate 11 and two belly cover plates 12.
Lifting body is anterior 5, lifting body middle part 6 and lifting body rear portion 7 are hollow structure, and lifting body is anterior 5, lifting body middle part 6 is connected the lifting body profile of formation vehicle successively with lifting body rear portion 7 through screw; The hollow structure of lifting body anterior 5 and 6 inside, lifting body middle part is used to install force balance assembly 3, and lifting body rear portion 7 inner hollow structures are used for installing stopper formula nozzle component 2; Two vertical fins 8 and two horizontal tails 10 respectively adopt three aerofoil pin 9 symmetries to be installed on the lifting body rear portion 7; Vertical fin 8 is installed in the top at lifting body rear portion 7; Horizontal tail 10 is installed in two sides at lifting body rear portion 7; Vertical fin 8 and horizontal tail 10 actings in conjunction, the aerodynamic stbilization of maintenance lifting body flight attitude; Plug nozzle assembly 2 inner plug nozzle motors 15 are given prominence to 7 tail end planes, lifting body rear portion; In outstanding plug nozzle motor 15 both sides, each installs a bottom cover plate 11, and bottom cover plate 11 is fixedly connected lifting body rear portion 7; Force balance assembly 3 is fixedly connected supporting component 4; At belly cover plate 12 of each side installation of supporting component 4, belly cover plate 12 is fixedly connected the bottom of lifting body, the integrity of bottom cover plate 11 and belly cover plate 12 common guarantee lifting body pneumatic structures.
As shown in Figure 4; Plug nozzle assembly 2 comprises tail shell 20, plug nozzle motor 15 and motor pin 19, and plug nozzle motor 15 is installed in tail shell 20 inside, and plug nozzle motor 15 is fixed in the lifting body rear portion 7 through two motor pins 19 with tail shell 20; Before the installation; At tail shell 20 inner filling gels, play the seal action between plug nozzle motor 15 and the tail shell 20, plug nozzle motor 15 front portions are provided with upper and lower two collection chambers 17; The front portion of each collection chamber 17 is provided with a collection chamber total pressure measurement interface 21; Connect the normal pressure sensor through welding thin copper pipe, be used for measuring the stagnation pressure of collection chamber 17, arrange respectively that on the centre symmetry line of the upper and lower plug awl wall of plug nozzle motor 15 three plug awl wall static pressures measure interfaces 16; Connect the normal pressure sensor through welding thin copper pipe, be used for measuring the static pressure of plug awl wall.Be symmetrical set a pressurized gas interface 18 in the left and right sides of each collection chamber 17, connect high-pressure air through welding air feed copper pipe and supply with gas cylinder, can eliminate the influence of input stroke during air feed motor power.
As shown in Figure 5; Force balance assembly 3 comprises force balance 13 and balance safety cover 14; Force balance 13 and balance safety cover 14 are positioned at the inside at lifting body anterior 5 and lifting body middle part 6; The front portion of force balance 13 adopts interference fit to be fixedly connected the support arm 23 of supporting component 4 through balance safety cover 14, and the rear portion of force balance 13 adopts interference fit to be fixed on the lifting body middle part 6.
The highi degree of accuracy six component force balances that described force balance 12 provides for Chinese aerodynamic investigation institute can six the component values of experiment with measuring device under different operating modes.
Like Fig. 1, Fig. 2, shown in Figure 5, supporting component 4 comprises support arm 23, front fairing 22 and back cowling 23.Support arm 23 1 ends connect the balance safety cover 14 in the force balance assembly 3; The other end is provided with tapped hole; Be fixed on the test air tunnel wallboard through tapped hole, support arm 23 bottom mounting planes are multistage broken line structure, through changing installment state to realize the different angle of attack state of testing apparatus.Front fairing 22, back cowling 23 are installed on the support arm 23; Front fairing 22 inside are used for placing the connecting line of force balance 13, and back cowling 23 inside are used for placing the thin copper pipe of connection of normal pressure sensor and the air feed copper pipe that plug nozzle motor 15 collection chambers 17 connect.
Accuracy in order to ensure force balance 12 measurements; The air feed copper pipe that plug nozzle motor 15 collection chambers 17 connect with being connected of normal pressure sensor thin copper pipe and support arm 23 and lifting body assembly 1 internal cavities wall between leave enough gaps, to prevent that motor power is through the air feed copper pipe or connect thin copper pipe and pass to support arm 23.
Claims (6)
1. one kind is contracted than linear plug nozzle vehicle cold-flow test device, it is characterized in that, comprises lifting body assembly, plug nozzle assembly, force balance assembly and supporting component;
The lifting body assembly comprises lifting body front portion, lifting body middle part, lifting body rear portion, vertical fin, horizontal tail, aerofoil pin, bottom cover plate and belly cover plate; Lifting body front portion, lifting body middle part and lifting body rear portion are hollow structure, and lifting body front portion, lifting body middle part and lifting body rear portion are fixedly connected sequentially, and constitute the lifting body profile of vehicle; Anterior and the inner hollow structure in lifting body middle part of lifting body is used to install the force balance assembly, and lifting body rear portion inner hollow structure is used for installing stopper formula nozzle component; Two vertical fins and two horizontal tails are installed on the lifting body rear portion through aerofoil pin symmetry respectively, and vertical fin is installed in the top at lifting body rear portion, and horizontal tail is installed in two sides at lifting body rear portion; The plug nozzle motor of plug nozzle component internal is given prominence to tail end plane, lifting body rear portion; In outstanding plug nozzle motor both sides; Each installs a bottom cover plate, and bottom cover plate is fixedly connected the lifting body rear portion, and the force balance assembly is fixedly connected supporting component; At belly cover plate of each side installation of supporting component, the belly cover plate is fixedly connected the bottom of lifting body;
The plug nozzle assembly comprises tail shell, plug nozzle motor and motor pin; It is inner that the plug nozzle motor is installed in the tail shell; Plug nozzle motor and tail shell are fixed in the lifting body rear portion through the motor pin; Plug nozzle motor front portion is provided with upper and lower two collection chambers, and the front portion of each collection chamber is provided with a collection chamber total pressure measurement interface, connects the normal pressure sensor through welding thin copper pipe; Be used for measuring the stagnation pressure of collection chamber; Arrange respectively that on the centre symmetry line of the upper and lower plug awl wall of plug nozzle motor three plug awl wall static pressures measure interfaces, connect the normal pressure sensor, be used for measuring the static pressure of plug awl wall through welding thin copper pipe; Be symmetrical set a pressurized gas interface in the left and right sides of each collection chamber, connect high-pressure air through welding air feed copper pipe and supply with gas cylinder;
The force balance assembly comprises force balance and balance safety cover; Force balance and balance safety cover are positioned at the inside at lifting body front portion and lifting body middle part; The front portion of force balance is through the support arm of balance safety cover fixed connection supporting component, and the rear portion of force balance is fixed on the lifting body middle part;
Supporting component comprises support arm, front fairing and back cowling; Support arm one end connects the balance safety cover in the force balance assembly; The other end is provided with tapped hole; Be fixed on the test air tunnel wallboard through tapped hole; Front fairing, back cowling are installed on the support arm, and front fairing inside is used for placing the connecting line of force balance, and back cowling inside is used for placing the thin copper pipe of connection of normal pressure sensor and the air feed copper pipe that plug nozzle motor collection chamber connects.
2. a kind of contracting than linear plug nozzle vehicle cold-flow test device according to claim 1 is characterized in that, described two vertical fins and two horizontal tails respectively adopt three aerofoil pin symmetries to be installed on the lifting body rear portion.
3. a kind of contracting than linear plug nozzle vehicle cold-flow test device according to claim 1 is characterized in that described tail shell inside is filled with silica gel, plays the seal action between plug nozzle motor and the tail shell.
4. a kind of contracting according to claim 1 than linear plug nozzle vehicle cold-flow test device; It is characterized in that; Described balance safety cover adopts interference fit to be fixedly connected with support arm, and the rear portion of force balance adopts interference fit to be fixedly connected with the lifting body middle part.
5. a kind of contracting than linear plug nozzle vehicle cold-flow test device according to claim 1 is characterized in that described force balance is highi degree of accuracy six component force balances, can six the component values of experiment with measuring device under different operating modes.
6. a kind of contracting than linear plug nozzle vehicle cold-flow test device according to claim 1 is characterized in that described support arm bottom mounting plane is a multistage broken line structure, through changing installment state to realize the different angle of attack state of testing apparatus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102921897A CN102828851A (en) | 2012-08-16 | 2012-08-16 | Cold flow test device for scaling linear plug type spray pipe carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102921897A CN102828851A (en) | 2012-08-16 | 2012-08-16 | Cold flow test device for scaling linear plug type spray pipe carrier |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102828851A true CN102828851A (en) | 2012-12-19 |
Family
ID=47332115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012102921897A Pending CN102828851A (en) | 2012-08-16 | 2012-08-16 | Cold flow test device for scaling linear plug type spray pipe carrier |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102828851A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106679923A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司沈阳空气动力研究所 | Pressure decoupling apparatus for high-speed jet-flow impact force-measuring model |
| CN106768798A (en) * | 2016-11-28 | 2017-05-31 | 中国航天空气动力技术研究院 | One kind is used for big angle of attack rear lateral jet flow dynamometer check structure |
| CN107165739A (en) * | 2017-07-26 | 2017-09-15 | 北京航空航天大学 | Solid-liquid rocket circular seam type plug nozzle |
| CN108088649A (en) * | 2018-01-22 | 2018-05-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | The model equipment and test method that jet pipe is connected with shape in wind tunnel test |
| CN109250149A (en) * | 2018-09-26 | 2019-01-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation |
| CN110705157A (en) * | 2019-03-19 | 2020-01-17 | 北京理工大学 | Rectifying cover similar structure extrapolation correction method based on scaling model |
| EP4042006A4 (en) * | 2019-11-27 | 2023-10-18 | Stoke Space Technologies, Inc. | Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1419044A (en) * | 2002-12-26 | 2003-05-21 | 北京航空航天大学 | Stopper type jet pipe |
| WO2006028516A2 (en) * | 2004-04-13 | 2006-03-16 | Aerojet-General Corporation | Thrust vector control system for a plug nozzle rocket engine |
| US7823376B2 (en) * | 2005-09-13 | 2010-11-02 | Aerojet-General Corporation | Thrust augmentation in plug nozzles and expansion-deflection nozzles |
| WO2011107090A2 (en) * | 2010-03-05 | 2011-09-09 | Technische Universität Dresden | Method for operating a rocket engine and rocket engine |
-
2012
- 2012-08-16 CN CN2012102921897A patent/CN102828851A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1419044A (en) * | 2002-12-26 | 2003-05-21 | 北京航空航天大学 | Stopper type jet pipe |
| WO2006028516A2 (en) * | 2004-04-13 | 2006-03-16 | Aerojet-General Corporation | Thrust vector control system for a plug nozzle rocket engine |
| US7823376B2 (en) * | 2005-09-13 | 2010-11-02 | Aerojet-General Corporation | Thrust augmentation in plug nozzles and expansion-deflection nozzles |
| WO2011107090A2 (en) * | 2010-03-05 | 2011-09-09 | Technische Universität Dresden | Method for operating a rocket engine and rocket engine |
Non-Patent Citations (1)
| Title |
|---|
| 程诚等: "线性塞式喷管外流干扰数值计算与冷流试验", 《航空动力学报》, vol. 27, no. 4, 30 April 2012 (2012-04-30) * |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768798B (en) * | 2016-11-28 | 2019-03-12 | 中国航天空气动力技术研究院 | One kind being used for big angle of attack rear lateral jet flow dynamometer check structure |
| CN106768798A (en) * | 2016-11-28 | 2017-05-31 | 中国航天空气动力技术研究院 | One kind is used for big angle of attack rear lateral jet flow dynamometer check structure |
| CN106679923A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司沈阳空气动力研究所 | Pressure decoupling apparatus for high-speed jet-flow impact force-measuring model |
| CN106679923B (en) * | 2016-12-15 | 2018-11-16 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of pressure decoupling device influencing dynamometry model for high speed jet |
| CN107165739A (en) * | 2017-07-26 | 2017-09-15 | 北京航空航天大学 | Solid-liquid rocket circular seam type plug nozzle |
| CN107165739B (en) * | 2017-07-26 | 2019-03-22 | 北京航空航天大学 | Solid-liquid rocket circular seam type plug nozzle |
| CN108088649A (en) * | 2018-01-22 | 2018-05-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | The model equipment and test method that jet pipe is connected with shape in wind tunnel test |
| CN108088649B (en) * | 2018-01-22 | 2023-07-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Model device for fixedly connecting spray pipe with shape in wind tunnel test and test method |
| CN109250149A (en) * | 2018-09-26 | 2019-01-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation |
| CN109250149B (en) * | 2018-09-26 | 2023-09-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel test device for separation simulation of air suction type hypersonic vehicle fairing |
| CN110705157A (en) * | 2019-03-19 | 2020-01-17 | 北京理工大学 | Rectifying cover similar structure extrapolation correction method based on scaling model |
| CN110705157B (en) * | 2019-03-19 | 2021-02-26 | 北京理工大学 | Rectifying cover similar structure extrapolation correction method based on scaling model |
| EP4042006A4 (en) * | 2019-11-27 | 2023-10-18 | Stoke Space Technologies, Inc. | Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102828851A (en) | Cold flow test device for scaling linear plug type spray pipe carrier | |
| CN102607799B (en) | Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method | |
| CN107436219B (en) | Inlet and exhaust pipeline device in unconventional layout form | |
| CN113899516B (en) | Ground simulation device and method for rocket engine jet flow interference effect | |
| CN106679930B (en) | Vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measurement method and device | |
| CN109100110B (en) | Be applied to two throat thrust vectoring nozzle support arm device of ventilating | |
| CN106092494A (en) | Drive aircraft pushes away resistance characteristic world conversion method | |
| CN102438893B (en) | Casing for a lifting aid | |
| CN114235321B (en) | Wind tunnel force measurement experimental device integrating gas rudder and spray pipe | |
| Gebbink et al. | High-speed wind tunnel test of the CAE aerodynamic validation model | |
| CN106017857B (en) | The measuring method of Air-breathing hypersonic vehicle segmented part aerodynamic force | |
| CN211740626U (en) | Combined power multichannel spray pipe test device | |
| CN114216649B (en) | Hypersonic separation flow control test device and method | |
| CN207336021U (en) | Low thrust jet nozzle feeder in wind tunnel test | |
| Stevens et al. | Measurements of the boundary-layer growth in annular diffusers | |
| Rodi | Preliminary ramjet/scramjet integration with vehicles using osculating flowfield waverider forebodies | |
| CN102817744B (en) | Six-unit tile-shaped plug nozzle cold flow test device | |
| CN114476123B (en) | Design method for hose type air refueling butt joint simulation test device | |
| CN112415220B (en) | Method and system for estimating toppling wind speed of winged aircraft in vertical state | |
| Bresnahan et al. | Cold flow investigation of a low angle turbojet plug nozzle with fixed throat and translating shroud at Mach numbers from 0 to 2.0 | |
| CN115077853A (en) | Six-component balance for wind tunnel jet flow experiment and application mode thereof | |
| Otis | Induced interference effects on a four-jet VTOL configuration with various wing planforms in the transition speed range | |
| Anscombe et al. | Some comments on high-lift testing in wind tunnels with particular reference to jet-blowing models | |
| Damljanović et al. | Selection criteria of optimal conditions for supersonic tests in a blowdown wind tunnel | |
| Yin | High Speed Pneumatic Theory and Technology Volume I: Servo System |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121219 |