CN115438550B - Rocket launching tube gap dynamic measurement method and safety gap design method - Google Patents
Rocket launching tube gap dynamic measurement method and safety gap design method Download PDFInfo
- Publication number
- CN115438550B CN115438550B CN202211234411.8A CN202211234411A CN115438550B CN 115438550 B CN115438550 B CN 115438550B CN 202211234411 A CN202211234411 A CN 202211234411A CN 115438550 B CN115438550 B CN 115438550B
- Authority
- CN
- China
- Prior art keywords
- launch
- carrier rocket
- rocket
- moment
- gap
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 60
- 238000013461 design Methods 0.000 title claims abstract description 18
- 238000000691 measurement method Methods 0.000 title claims abstract description 8
- 239000013598 vector Substances 0.000 claims abstract description 34
- 238000004364 calculation method Methods 0.000 claims abstract description 18
- 238000005259 measurement Methods 0.000 claims abstract description 14
- 238000007599 discharging Methods 0.000 claims description 10
- 238000009434 installation Methods 0.000 claims description 3
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 2
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 2
- 241001330002 Bambuseae Species 0.000 claims description 2
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 2
- 239000011425 bamboo Substances 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 7
- 230000007547 defect Effects 0.000 abstract description 3
- 230000005284 excitation Effects 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000035772 mutation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Length Measuring Devices With Unspecified Measuring Means (AREA)
Abstract
The invention discloses a rocket launching tube gap dynamic measurement method and a safety gap design method, wherein the rocket launching tube gap dynamic measurement method comprises the following steps: extracting the position of the axis of the carrier rocket and the position of the launch nozzle at each moment in the rocket launching process; calculating an included angle between a rocket axis at a certain moment and a normal vector of a plane where a launch nozzle is located, and calculating a carrier rocket launch nozzle gap at the current moment based on the included angle; obtaining a carrier rocket ejection gap at each moment, and realizing dynamic measurement of the ejection gap of the carrier rocket based on the movable platform; the safety clearance design method is based on the dynamic measuring method of the clearance between the discharge cylinders, and judges whether the clearance between the discharge cylinders at each moment in the process of rocket launching the discharge cylinders meets the requirement of the safety clearance. The invention overcomes the defects of large amount of data processing and insufficient precision in the prior art, reduces the calculation cost and improves the efficiency.
Description
Technical Field
The invention belongs to the technical field of computer digital measurement, and particularly relates to a rocket launching tube gap dynamic measurement method and a safety gap design method.
Background
When designing a carrier rocket and a launch canister (or a launch frame or a launch box) in a rocket launching system, a certain fit clearance is reserved between the carrier rocket and the launch canister according to actual assembly requirements, but the fit clearance is an important reason for causing the disturbance of the launch of the carrier rocket in the process of launching the carrier rocket: firstly, under the conditions of deviation of thrust or shaking, interference, vibration and the like of a launching platform, the too small fit clearance can cause mutation of constraint states and dynamic characteristics of the carrier rocket, so that the automatic control of the carrier rocket after leaving a track and a barrel is seriously influenced, the deflection of the rocket is adversely influenced, and hidden danger is brought to launching safety; secondly, due to the manufacturing precision deviation of the assembly surface, the contact surface of the carrier rocket and the launching barrel in actual assembly is a non-ideal smooth surface, the attitude of the carrier rocket launching barrel is further disturbed, and the abnormal rolling of the rocket launching barrel is aggravated. Thus, accurate measurement and safe fit clearance design of the minimum distance between the inside of the launch nozzle cross-sectional position and the outer surface of the launch vehicle (hereinafter simply referred to as launch vehicle exit clearance) at each instant during launch is a desirable feature to reduce launch disturbance of the launch vehicle.
In the finite element simulation research of the launch dynamics of the existing carrier rocket, the measurement of the clearance between the carrier rocket and the carrier rocket is mainly carried out by the following modes: and directly extracting the space information of the nodes on the outer surface of the carrier rocket and the space information of the monitoring points of the launcher, judging the distance between the inner side of the section position of the launcher opening at each moment and the outer surface of the carrier rocket, and selecting the minimum distance as the clearance of the launcher.
However, although the existing method for directly extracting the finite element node gap can obtain the carrier rocket barrel gap, the following three problems exist: firstly, referring to fig. 1, because the finite element node coordinate acquisition of the carrier rocket depends on the finite element scale of the carrier rocket, only the minimum distance between two adjacent nodes of the outer surface of the carrier rocket along the length direction of the rocket and a launch nozzle can be obtained respectively, referring to L1 and L3 in fig. 1, smaller values in L1 and L3 are selected as a launch nozzle gap, and the minimum distance (namely L2 in fig. 1) from the position between the two nodes of the outer surface of the carrier rocket along the length direction of the rocket to the launch nozzle cannot be obtained, so that the extracted gap information is discrete data and the precision is not enough; secondly, the judgment of barrel outlet needs to be carried out on all outer surface nodes and adjacent barrel port nodes of the carrier rocket, so that the data processing capacity is large and the efficiency is low; thirdly, under the condition that the shaking of the launching tube caused by the motion of the moving platform can be mutually coupled with the motion excitation of the carrier rocket and the speed of the carrier rocket discharging tube is increased to a certain degree, the judgment of the gap value of the corresponding position of the node near the tube opening relative to the carrier rocket discharging tube can be further influenced due to the limitation of the existing computing resource to the finite element time step, and the error is increased.
Disclosure of Invention
In view of the above, the invention provides a dynamic measuring method for the clearance between the launch canister of the carrier rocket based on the moving platform, which has small data processing amount and higher efficiency.
The invention is realized by the following technical scheme:
a dynamic measuring method for the gap between the launch canister of a carrier rocket based on a moving platform comprises the following steps:
extracting the position of the axis of the carrier rocket and the position of the launch nozzle at each moment in the rocket launching process;
calculating an included angle between a rocket axis at a certain moment and a normal vector of a plane where a launch nozzle is located, and calculating a carrier rocket launch nozzle gap at the current moment based on the included angle;
and obtaining the barrel gap of the carrier rocket at each moment, and realizing dynamic measurement of the barrel gap emitted by the carrier rocket based on the moving platform.
Further, the specific process for calculating the included angle between the rocket axis and the normal vector of the plane where the launch nozzle is located at a certain moment is as follows: and extracting coordinates corresponding to any three points which are not collinear on the launch nozzle, a central point of the launch nozzle and two points on the launch nozzle axis in each moment in the launch process, intercepting coordinates of the points corresponding to a certain moment, and performing geometric calculation to obtain an included angle between the launch nozzle axis and a normal vector of a plane where the launch nozzle is located at the corresponding moment.
Further, calculating an included angle between the rocket axis at a certain moment and a normal vector of a plane where the launch nozzle is located, and calculating a launch gap of the carrier rocket at the current moment based on the included angle is as follows:
according to t i Coordinate information of any three points which are not collinear on a transmitting cylinder opening at moment is obtained, and t i Normal to plane of emission nozzle at momentAn amount of;
according to t i Coordinate information of two points on the axis position of the carrier rocket at any moment is obtained, and vectors in the axis direction of the carrier rocket are obtained;
according to the normal vector of the plane of the launch barrel opening and the vector of the axis direction of the carrier rocket, calculating to obtain the cosine value of the included angle between the normal vector of the plane of the launch barrel opening and the vector of the axis direction of the carrier rocket;
and calculating the carrier rocket cylinder outlet gap according to the cosine value of the included angle.
Further, the calculating the carrier rocket barrel clearance according to the cosine value of the included angle is as follows:
calculating t according to the following formula i Time carrier rocket's play of a section of thick bamboo clearance delta i ：
Wherein, the point O' is the center point of the launch nozzle, the point O is the intersection point of the axis of the carrier rocket and the plane of the launch nozzle,the distance between the point O and the point O 'is L, the distance from the center O' of the launch nozzle to the two sides of the launch nozzle, r is the radius of the section of the carrier rocket passing through the point O, and θ is the included angle between the axis of the carrier rocket and the normal vector of the plane of the launch nozzle.
A rocket launching safety clearance design method is based on the dynamic measuring method of the barrel outlet clearance, and comprises the following specific processes:
step one, based on the overall structure of the launch canister, the carrier rocket and the launch platform, determining the initial dimensions of the launch canister opening and the carrier rocket according to the strength of the launch unit and the initial disturbance design requirement, and determining the fit clearance and the installation position between the launch canister opening and the carrier rocket;
step two, according to the method for dynamically measuring the play of the rocket in any one of claims 1 to 4, the play of the rocket in the process of launching the rocket is dynamically measured, and the play of the rocket in each moment in the process of launching the rocket is obtained;
step three, judging whether the discharge gap at each moment in the process of discharging the rocket from the second step meets the safety gap requirement; if the requirement is met, entering the next link, and evaluating the safety clearance of the carrier rocket for launching the multiple working stations; and if the requirements are not met, updating the sizes of the launch nozzle and the carrier rocket, the fit clearance between the launch nozzle and the carrier rocket and the mounting position.
The beneficial effects are that:
(1) The invention calculates the cylinder gap by adopting the included angle between the axis of the carrier rocket and the normal vector of the plane where the launch cylinder opening is located, and has the following beneficial effects: firstly, the defect that all node information on the outer surface of a carrier rocket body and all node information on a launch nozzle are required to be extracted and a large amount of data processing is carried out is overcome, the calculation cost is reduced, and secondly, the problem that the precision of finite element analysis discrete data on the outer surface of the carrier rocket is insufficient is overcome, so that the accurate launch gap of the carrier rocket is determined; finally, under the condition that the shaking of the launching tube caused by the motion of the moving platform can be mutually coupled with the motion excitation of the carrier rocket and the barrel discharging speed of the carrier rocket is increased to a certain degree, the calculation of the barrel discharging gap is not limited by calculation resources on finite element time step, and the judgment of the barrel discharging gap is not influenced.
(2) According to the invention, only any three points which are not collinear on the launch nozzle, the center point of the launch nozzle and coordinates corresponding to each moment in the launch process of two points on the launch rocket axis are required to be extracted to calculate the included angle between the launch rocket axis and the normal vector of the plane where the launch nozzle is located, the data processing amount is small, the calculation is simple, the calculation cost is further reduced, and the efficiency is improved.
(3) The invention provides a rocket launching safety clearance design method, which is based on a rocket launching barrel clearance dynamic measurement method and has more accurate data base.
(4) The invention is applicable to gap measurement and safe fit gap design similar to working conditions, such as measurement of the gap of the grenade launching barrel, safe fit gap design and the like.
Drawings
FIG. 1 is a schematic illustration of the gap between a carrier rocket outer surface node and a launch nozzle;
FIG. 2 is an assembly view of a launch vehicle, launch canister and launch platform;
FIG. 3 is a schematic diagram of the geometric relationship between the plane of the axis of the launch vehicle and the launch platform;
FIG. 4 illustrates the positional relationship between the inner wall of the launch nozzle and the launch vehicle;
fig. 5 is a flow chart of a method of designing a secure fit clearance.
1-carrier rocket, 2-launch nozzle, 3-launch barrel, 4-saddle, 5-movable launch platform and 6-carrier rocket axis.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
The embodiment provides a dynamic measurement method for the clearance between the launch canister of a carrier rocket based on a moving platform, wherein the assembly relation of the carrier rocket based on the moving platform is as follows: referring to fig. 2 and 3, the launch canister 3 is positioned on a mobile launch platform 5, and the launch vehicle 1 is mounted substantially coaxially within the launch canister 3 and is positioned on a cradle 4 of the mobile launch platform 5.
The process of the dynamic measuring method for the play clearance of the cylinder is as follows:
extracting the position of the carrier rocket axis 6 and the position of the launch barrel opening 2 at each moment in the rocket launching process from finite element simulation data;
calculating an included angle between a rocket axis at a certain moment and a normal vector of a plane where a launch nozzle is located, and calculating a carrier rocket launch nozzle gap at the current moment based on the included angle;
and obtaining the barrel gap of the carrier rocket at each moment, and realizing dynamic measurement of the barrel gap emitted by the carrier rocket based on the moving platform.
According to the embodiment, only the included angle between the carrier rocket axis 6 and the normal vector of the plane where the launch nozzle 2 is located is calculated, so that the defects that all node information on the outer surface of the carrier rocket and all node information of the launch nozzle need to be extracted and a large amount of data processing are carried out in the prior art are overcome, and the calculation cost is reduced; under the condition that the launching tube shake caused by the motion of the moving platform can be mutually coupled with the motion excitation of the carrier rocket and the launching tube speed of the carrier rocket is increased to a certain extent, the embodiment of the application calculates the tube clearance by adopting the included angle between the carrier rocket axis 6 and the normal vector of the plane where the launching tube opening 2 is positioned, so that the calculation of the tube clearance is not limited by calculation resources to finite element time step and the judgment of the tube clearance is not influenced.
In yet another embodiment of the present application, the process of calculating the included angle between the carrier rocket axis 6 and the normal vector of the plane of the launch nozzle 2 is: and extracting coordinates corresponding to any three points which are not collinear on the launch nozzle 2, the center point of the launch nozzle 2 and two points on the position of the launch nozzle axis 6 at each moment in the launching process, intercepting the coordinates of the points corresponding to a certain moment, and performing geometric calculation to obtain an included angle between the launch nozzle axis 6 and the normal vector of the plane where the launch nozzle 2 is located at the corresponding moment.
According to the method, only any three non-collinear points on the launch nozzle 2, coordinates corresponding to two points on the center point of the launch nozzle 2 and the position of the carrier rocket axis 6 at each moment in the launching process are required to be extracted, the data processing amount is small, the calculation cost is further reduced, the efficiency is improved, an accurate barrel outlet gap can be obtained through geometric calculation, and the problem that the precision of finite element analysis discrete data on the outer surface of the carrier rocket is insufficient is solved.
The method for dynamically measuring the clearance of the launch canister of the carrier rocket is specifically described below with reference to specific examples:
step one, extracting the position of a carrier rocket 1 at each moment in the rocket launching process in batches through codes in data of a finite element simulation test, so as to obtain the position of a carrier rocket axis 6 at each moment; the position of the launch nozzle 2 at each moment in the rocket launching process is extracted.
Step two, extracting coordinates corresponding to any three points which are not collinear on the launch barrel opening 2, the center point of the launch barrel opening 2 and two points on the launch barrel axis 6 at each moment in the launching process, and intercepting the coordinates of the points corresponding to a certain moment, so as to calculate and obtain cosine values of included angles between the launch barrel axis 6 and normal vectors of planes of the launch barrel opening 2 at the moment, and determining the barrel outlet gap of the launch barrel 1 at the moment according to geometric relation calculation; the specific process and calculation mode are as follows:
step 2-1, see fig. 4, extracting coordinates corresponding to any three non-collinear points A, B and C of the launch nozzle 2, a center point O 'of the launch nozzle 2 and two points R and R' on the axis 6 of the launch vehicle at each moment in the launching process in one time in the data obtained in the step one;
step 2-2, enabling the intersection point of the carrier rocket axis 6 and the plane of the launch nozzle 2 to be O; acquiring t according to the coordinate information in the step 2-1 i Normal vector of plane of the emission nozzle 2 at momentThe specific process is as follows:
at t i At the moment, the coordinates corresponding to the three points A, B and C where the nozzle 2 is not collinear are A (x A ,y A ,z A )，B(x B ,y B ,z B )，C(x C ,y C ,z C ) Then
The normal vector of the plane of the transmitting cylinder mouth 2 is obtained through the points A, B and C
Step 2-3, according to the normal vector of the plane of the emission nozzle 2 in the step 2-2And t in step 2-1 i Coordinates of two points R and R' on the position of the carrier rocket axis 6 corresponding to the moment obtain cosine values of an included angle theta between the normal direction of the plane where the launch nozzle 2 is positioned at the same moment and the carrier rocket axis 6, and the specific steps are as follows:
at t i At the moment, the coordinates corresponding to the two points R and R' on the position of the carrier rocket axis 6 are R (x R ,y R ,z R ) And R' (x) R' ,y R' ,z R' ) The vector of the carrier rocket axis 6 direction is
The cosine value of the included angle theta between the normal direction of the plane where the launch barrel opening 2 is positioned and the axis of the carrier rocket is as follows:
step 2-4, according to t in step 2-1 i The coordinates of the center point O' of the launch nozzle 2 corresponding to the moment and the coordinates of the intersection point O of the carrier rocket axis 6 and the plane of the launch nozzle 2 obtain that the distance between the two points isCombining the cosine value of the included angle theta between the normal direction of the plane of the launch nozzle 2 and the axis of the carrier rocket, which is obtained in the step 2-3, so as to obtain t i Barrel outlet gap delta of carrier rocket 1 at moment i The method comprises the following steps:
wherein, referring to fig. 4, l is the distance from the center O ' of the transmitting nozzle 2 to the two sides of the transmitting nozzle 2, i.e. the length of AO ' or CO '; r is the radius of the section of the carrier rocket 1 passing through the O point, namely the length of OE.
Step three, measuring t in the launching process of the carrier rocket 1 according to the step two i The carrier rocket 1 at each moment launches the barrel gap, the barrel gap of the carrier rocket at each moment is obtained, and accurate dynamic measurement of the barrel gap launched by the carrier rocket based on the moving platform is realized.
According to the method, related parameters of carrier rocket barrel clearance measurement, namely any three points which are not collinear on the launch barrel opening, the center point of the launch barrel opening and two point coordinate information on the axis position of the carrier rocket are extracted in batches through codes, a large number of parameters (all information of nodes on the outer surface of the carrier rocket and space information of plane nodes of the barrel opening) are not required to be extracted manually, and therefore calculation cost and efficiency are improved.
In yet another embodiment of the present application, a method for designing a safety gap based on the dynamic measurement of the gap between the launch canister of the launch vehicle comprises the following specific steps:
step one, based on the integral structural characteristics of the launch canister 3, the carrier rocket 1 and the launch platform, determining the initial dimensions of the launch canister 3 and the carrier rocket 1 according to the design requirements of the strength, initial disturbance and the like of a launch unit, and determining the fit clearance and the mounting position between the launch canister 3 and the carrier rocket 1;
step two, according to the dynamic measuring method of the discharge gap, the discharge gap of the carrier rocket 1 is dynamically measured, and the discharge gap at each moment in the process of discharging the rocket is obtained;
step three, judging whether the discharge gap at each moment in the process of discharging the rocket from the second step meets the safety gap requirement; if the requirement is met, entering the next link, and evaluating the safety clearance of the carrier rocket for launching the multiple working stations; if the requirements are not met, redesigning the sizes of the launch nozzle 2 and the carrier rocket 1, the fit clearance between the launch nozzle 2 and the carrier rocket 1 and the installation position, and repeating the three steps of the design method of the safety fit clearance until the requirements are met, entering the next link, and evaluating the safety clearance of the carrier rocket for launching the carrier rocket under multiple working conditions.
The dynamic measuring method of the clearance between the carrier rocket and the launching barrel provides a more accurate data basis for the design of the safety fit clearance between the carrier rocket and the launching barrel, and the design of the size of the carrier rocket and the launching barrel, the safety fit clearance between the carrier rocket and the launching barrel and the relative position of the carrier rocket and the launching barrel by the method has great significance for reducing the disturbance of the launch of the carrier rocket; the dynamic measuring method for the clearance of the discharge tube can be suitable for clearance measurement and safe fit clearance design under similar working conditions, such as measurement of the clearance of the discharge tube of the rocket gun, safe fit clearance design and the like.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. The dynamic measuring method for the clearance between the ejection cylinders of the carrier rocket based on the moving platform is characterized by comprising the following steps of:
extracting the position of the axis of the carrier rocket and the position of the launch nozzle at each moment in the rocket launching process;
calculating an included angle between a rocket axis at a certain moment and a normal vector of a plane where a launch nozzle is located, and calculating a carrier rocket launch nozzle gap at the current moment based on the included angle;
obtaining a carrier rocket ejection gap at each moment, and realizing dynamic measurement of the ejection gap of the carrier rocket based on the movable platform;
the specific process for calculating the included angle between the rocket axis and the normal vector of the plane where the launch nozzle is located at a certain moment is as follows: for the position of the axis of the carrier rocket and the position of the launch nozzle, extracting coordinates corresponding to any three points which are not collinear on the launch nozzle, the center point of the launch nozzle and two points on the axis of the carrier rocket at each moment in the launching process, intercepting the coordinates of the points corresponding to a certain moment, and performing geometric calculation to obtain an included angle between the axis of the carrier rocket at the corresponding moment and the normal vector of the plane of the launch nozzle;
calculating an included angle between a rocket axis at a certain moment and a normal vector of a plane where a launch nozzle is located, and calculating a launch gap of the carrier rocket at the current moment based on the included angle as follows:
according to t i Coordinate information of any three points which are not collinear on a transmitting cylinder opening at moment is obtained, and t i A normal vector of a plane where the transmitting cylinder port is positioned at moment;
according to t i Coordinate information of two points on the axis position of the carrier rocket at any moment is obtained, and vectors in the axis direction of the carrier rocket are obtained;
according to the normal vector of the plane of the launch barrel opening and the vector of the axis direction of the carrier rocket, calculating to obtain the cosine value of the included angle between the normal vector of the plane of the launch barrel opening and the vector of the axis direction of the carrier rocket;
and calculating the carrier rocket cylinder outlet gap according to the cosine value of the included angle.
2. The dynamic measurement method of the launch vehicle barrel gap based on the movable platform according to claim 1, wherein the calculation of the launch vehicle barrel gap according to the cosine value of the included angle is as follows:
calculating t according to the following formula i Time carrier rocket's play of a section of thick bamboo clearance delta i ：
Wherein, the point O' is the center point of the launch nozzle, the point O is the intersection point of the axis of the carrier rocket and the plane of the launch nozzle,the distance between the point O and the point O 'is L, the distance from the center O' of the launch nozzle to the two sides of the launch nozzle, r is the radius of the section of the carrier rocket passing through the point O, and θ is the included angle between the axis of the carrier rocket and the normal vector of the plane of the launch nozzle.
3. A rocket launching safety clearance planning method based on the dynamic measuring method of the discharge cylinder clearance according to claim 1 or 2, comprising the following specific processes:
step one, based on the overall structure of the launch canister, the carrier rocket and the launch platform, determining the initial dimensions of the launch canister opening and the carrier rocket according to the strength of the launch unit and the initial disturbance design requirement, and determining the fit clearance and the installation position between the launch canister opening and the carrier rocket;
step two, according to the dynamic measuring method of the discharge gap of claim 1 or 2, the discharge gap of the carrier rocket is dynamically measured to obtain the discharge gap at each moment in the process of discharging the rocket;
step three, judging whether the discharge gap at each moment in the process of discharging the rocket from the second step meets the safety gap requirement; if the requirement is met, entering the next link, and evaluating the safety clearance of the carrier rocket for launching the multiple working stations;
and if the requirements are not met, updating the sizes of the launch nozzle and the carrier rocket, the fit clearance between the launch nozzle and the carrier rocket and the mounting position.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2022106823026 | 2022-06-15 | ||
| CN202210682302 | 2022-06-15 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115438550A CN115438550A (en) | 2022-12-06 |
| CN115438550B true CN115438550B (en) | 2024-02-27 |
Family
ID=84251646
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211234411.8A Active CN115438550B (en) | 2022-06-15 | 2022-10-10 | Rocket launching tube gap dynamic measurement method and safety gap design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115438550B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116244836B (en) * | 2023-03-21 | 2024-05-07 | 蓝箭航天空间科技股份有限公司 | ADAMS-based carrier rocket take-off drift safety gap design method |
| CN116659321A (en) * | 2023-07-31 | 2023-08-29 | 东方空间技术(山东)有限公司 | Rocket take-off drift amount measuring system and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869097A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | A kind of posture control system and Small Launch Vehicle |
| CN110907208A (en) * | 2019-11-26 | 2020-03-24 | 蓝箭航天空间科技股份有限公司 | Modal test method of carrier rocket |
| CN215399393U (en) * | 2021-04-13 | 2022-01-04 | 浙江蓝箭航天空间科技有限公司 | Carrier rocket reverse-thrust device and carrier rocket |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7237488B2 (en) * | 2005-02-25 | 2007-07-03 | Cameron Michael Duescher | Fireworks bottle rocket launcher |
-
2022
- 2022-10-10 CN CN202211234411.8A patent/CN115438550B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869097A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | A kind of posture control system and Small Launch Vehicle |
| CN110907208A (en) * | 2019-11-26 | 2020-03-24 | 蓝箭航天空间科技股份有限公司 | Modal test method of carrier rocket |
| CN215399393U (en) * | 2021-04-13 | 2022-01-04 | 浙江蓝箭航天空间科技有限公司 | Carrier rocket reverse-thrust device and carrier rocket |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115438550A (en) | 2022-12-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115438550B (en) | Rocket launching tube gap dynamic measurement method and safety gap design method | |
| CN112218306B (en) | Method and device for predicting coverage performance of base station and computer equipment | |
| WO2022148400A1 (en) | Automobile door mounting method and device, and industrial robot and storage medium | |
| CN114623823B (en) | UWB (ultra wide band) multi-mode positioning system, method and device integrating odometer | |
| CN115081251B (en) | Virtual battlefield-based artillery striking effect evaluation method | |
| CN113324544A (en) | Indoor mobile robot co-location method based on UWB/IMU (ultra wide band/inertial measurement unit) of graph optimization | |
| CN117444991B (en) | Dynamic path planning method, multi-mechanical arm platform structure and related device | |
| CN110968113A (en) | Unmanned aerial vehicle autonomous tracking take-off and landing system and tracking positioning method | |
| CN112380786B (en) | Air rudder thermal environment modeling method, equipment and storage medium | |
| CN110068832A (en) | A kind of high-precision locating method of laser navigation AGV | |
| CN117213871A (en) | Point-to-point test method, device and equipment for horizontal free impact and storage medium | |
| CN116702439A (en) | Reentry landing point prediction method of simulation aircraft based on reentry landing point prediction model | |
| KR101836778B1 (en) | Measuring apparatus for missile assembly state and method thereof | |
| CN114414378B (en) | Detection system and method for missile adapter of missile packing box | |
| CN110411707A (en) | Series connection Flight Vehicle Stage Separation aerodynamic characteristic interference volume prediction technique | |
| CN116424565A (en) | Unmanned aerial vehicle rocket boosting emission thrust axis design | |
| CN114325610A (en) | Radar installation error correction method based on dynamic measurement data | |
| CN114353823A (en) | Parameter matching method for inertia unit shock absorber | |
| CN115453514B (en) | Sight correction method for gun external trajectory initial speed measurement radar | |
| CN117092610B (en) | Reverse expansion Kalman trajectory extrapolation method based on long and short pulse combination design | |
| CN117705106B (en) | MEMS IMU full-automatic full-temperature compensation calibration method | |
| CN109190191A (en) | A kind of ship load stabilized platform structure design method based on performance | |
| CN215147713U (en) | Grinding device with casting posture detection function | |
| CN113686739B (en) | Method for measuring volume of tiny liquid drop by adopting 8 ellipsoids for fitting | |
| CN116592863B (en) | Gyroscope module precision measurement and optimization method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |