CN112883491B - Hovercraft land static stability calculation method based on three-dimensional apron deformation - Google Patents

Hovercraft land static stability calculation method based on three-dimensional apron deformation Download PDF

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CN112883491B
CN112883491B CN202110258367.3A CN202110258367A CN112883491B CN 112883491 B CN112883491 B CN 112883491B CN 202110258367 A CN202110258367 A CN 202110258367A CN 112883491 B CN112883491 B CN 112883491B
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hovercraft
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徐圣杰
刘晖
熊逸凡
方雄伟
汤宇嘉
孙轶凡
张宗科
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708th Research Institute of CSIC
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Abstract

The invention relates to a hovercraft land static and lateral stability calculation method based on three-dimensional apron deformation, which is characterized in that based on given aerodynamic moment, the air cushion pressures of a left air chamber and a right air chamber are obtained according to the balance of force and moment on the heave and roll motion freedom of the whole hovercraft, and the flow of the left air chamber and the right air chamber, the roll angle and the gravity center height of the hovercraft are solved; calculating the deformation of the apron, and further obtaining the restoring moment caused by the increase of the area of the air cushion due to the deformation of the apron; meanwhile, the transverse inclination and the gravity center height change of the boat body cause the inclination moment of gravity; the curve of the dimensionless external moment and the roll angle obtained by repeating the steps can be used as a standard for measuring the land static stability and the land roll stability of the hovercraft. The numerical calculation method for the stability of the three-dimensional hovercraft can provide guidance in the process of designing the apron, the fan and the air cushion parameters, and has great engineering practical value for improving the overall performance of the hovercraft.

Description

Hovercraft land static stability calculation method based on three-dimensional apron deformation
Technical Field
The invention relates to a hovercraft land static stability calculation method based on three-dimensional apron deformation, in particular to a three-dimensional apron stability calculation method based on air cushion dynamics, apron dynamics and boat motion.
Background
The hovercraft has the advantages of high speed, amphibious property, small underwater physical field and the like, and is widely applied to the fields of beach landing, rescue, border patrol, mine sweeping, material personnel transportation and the like. The apron is a heavy device which ensures that the hovercraft has amphibious characteristics, and is closely related to the lifting property, stability, seaworthiness and safety of the hovercraft.
Stability is an important characteristic closely related to the navigation safety of the hovercraft, and is mainly provided by air cushion segmentation restoring moment, apron deformation restoring moment and the like. The stability is an important characteristic of the overall performance of the hovercraft, is related to the safety of the hovercraft in use, is different from the stability of a conventional hovercraft by buoyancy, and is mainly provided by air cushion restoring moment, restoring moment generated by deformation of an apron and the like, so that the stability is closely related to the air cushion parameters of the hovercraft and the deformation performance of the apron. The stability of the hovercraft should meet the requirement of a certain range, the stability is too small, the cushion navigation safety of the hovercraft is affected, and the response performance of the hovercraft is poor due to too large stability, so that the seaworthiness is poor. Therefore, calculation of stationarity is crucial to ensure the overall performance of the hovercraft. The hovercraft sails at a certain stern inclination angle, so that the longitudinal stability is easy to meet the requirement, the transverse width is short, and the hovercraft is easy to float laterally during sailing, so that the transverse stability is a close concern in the design of the hovercraft apron.
The air cushion ship static and transverse stability is mainly divided into onshore static and overwater static and transverse stability, and the calculation and simulation difficulty of the overwater static and transverse stability is higher due to the three-phase coupling effect of the gas-water-flexible apron. Through experimental comparison and analysis, the water static stability is about 0.7 of the land static stability in general conditions, so that the static stability characteristic of the hovercraft can be mastered by calculating the land static stability.
At present, when stability is estimated in a public document, an air cushion is approximate to a rectangle, the deformation of the apron is calculated based on a typical section of a two-dimensional apron, and then the tilting moment of the hovercraft under different postures is calculated, so that the dimensionless stability of the hovercraft is high. However, the skirt of the hovercraft is of a three-dimensional complex curved surface structure, errors exist when the deformation of the skirt is calculated through a typical section of the two-dimensional skirt, and the deformation of the skirt and the grounding characteristics are difficult to carry out image comparison and analysis, so that in engineering design, the stability of the hovercraft needs to be verified through a hovercraft model test, time and labor are wasted, and the economy is poor. Therefore, a calculation method for the three-dimensional apron stability based on the hovercraft is urgently needed in engineering, so that the apron design can be effectively guided according to the overall performance requirement.
Disclosure of Invention
The purpose of the invention is: the onshore static stability and stability calculation method for the hovercraft can quantitatively analyze the static uplift stability of the hovercraft so as to guide the design of the apron and the hovercraft system.
In order to achieve the aim, the technical scheme of the invention provides a hovercraft land static stability calculation method based on three-dimensional apron deformation, which is characterized by comprising the following steps of:
step 1, obtaining air cushion characteristic parameters of the hovercraft in an initial balance state, wherein when the hovercraft is in the initial balance state, the transverse inclination angle of the hovercraft is 0 degree;
step 2, establishing a finite element model of the hovercraft, respectively applying the air cushion characteristic parameters obtained in the step 1 to obtain the geometric molding of the apron in a design state, and extracting the characteristic parameters of the apron;
step 3, dividing the moment M at a given air cushioncThen, the cushion pressure P of the left air chamber is calculated according to the balance of the forces and moments on the heave freedom degree and the roll freedom degreecLAnd right air chamber cushion pressure PcRThe heave freedom is represented by the change of the height of the gravity center, and the roll is represented by the roll angle; solving according to the fan characteristic curve and the fan-air duct-big bag-air cushion flow continuity equation to obtain the left air chamber bag pressure PbLAnd right air cell bag pressure PbRAnd the roll angle alpha and the height h of the center of gravity of the hovercraftg；
Step 4, pressing the left air chamber obtained in the step 3 to obtain pressure PcLRight air chamber cushion pressure PcRLeft air chamber bag pressure PbLRight air chamber bag pressure PbRThe transverse inclination angle alpha of the hovercraft, and the gravity center height h of the hovercraftgAs boundary conditions and loadsAfter the load is applied to the finite element model of the hovercraft established in the step 2, extracting apron characteristic parameters;
step 5, calculating the deformation of the apron based on the apron characteristic parameters obtained in the step 4 and the apron characteristic parameters obtained in the step 2, and further obtaining the restoring moment M caused by the increase of the air cushion area due to the deformation of the aprons(ii) a Simultaneously obtains the gravity tilting moment M generated by the hovercraft due to the transverse inclination and the gravity center height changeg；
Step 6, setting different air cushion segmentation moments McAnd repeating the steps 3 to 5 to obtain a curve of the dimensionless external moment M/(GB) and the roll angle alpha, and obtaining the dimensionless stability based on the curve, wherein the dimensionless stability can be used as a standard for measuring the static padding stability of the hovercraft.
Preferably, in step 1, the air cushion characteristic parameters of the hovercraft in the initial balance state are obtained based on a fan characteristic curve equation and a fan-flow channel-big bag-air cushion flow continuity equation according to the geometrical parameters and the fan characteristic parameters of the hovercraft.
Preferably, in step 1, the air cushion characteristic parameter includes a left air chamber cushion pressure PcL0And left air cell pressure PbL0Right air chamber cushion pressure PcR0And right air cell bag pressure PbR0Balanced discharge height he0。
Preferably, in step 2, when the finite element model of the hovercraft is established, the typical section of the side skirt corresponding to the longitudinal partition skirt of the hovercraft is selected, the geometric model of the typical section of the hovercraft skirt is established through CATIA according to the skirt profile, and the finite element model of the hovercraft is established based on Abaqus.
Preferably, in step 1, Matlab programming is used as a platform, the characteristic parameters of the air cushion are obtained by calling an air cushion dynamics module, and are transmitted to an apron dynamics module;
in step 2, an apron dynamics module calls a CATIA secondary development module to carry out parametric modeling on an apron geometrical structure, introduces a geometrical model into Abaqus and realizes parametric finite element model modeling based on Python secondary development to obtain a finite element model of the hovercraft, and applies characteristic parameters of the air cushion to generate a calculation file;
in step 3, calling an Abaqus structure solver to solve, realizing data analysis on a result file by adopting Python secondary development, and calling a boat attitude module to obtain the transverse inclination angle alpha and the gravity center height h of the hovercraftg。
Preferably, in step 3, non-linear finite calculations are performed by Abaqus Python-based quadratic development, solving with display dynamics.
Preferably, in step 2, a dynamic display solution method is adopted to obtain the geometric molding of the apron in the design state, and the apron characteristic parameters are extracted, wherein the apron characteristic parameters comprise the height h of the apron on the port sidesL0And width x of apron on port sidesL0Starboard apron skirt height hsR0And width x of starboard apronsR0。
Preferably, in step 4, the apron characteristic parameters include a height h of the port apron skirtsLAnd width x of apron on port sidesLStarboard apron skirt height hsRAnd width x of starboard apronsR(ii) a In step 5, the skirt deformation is calculated by Abaqus.
Preferably, the hovercraft onshore stationarity calculating method is realized based on an apron-air cushion-boat posture interactive information platform which is used for realizing air cushion dynamics, apron dynamics, boat postures and mutual information exchange among the apron-air cushion-boat postures.
Preferably, in the finite element model of the hovercraft, the apron adopts a thin film unit, in order to improve the calculation efficiency, the rigid plane representation is analyzed by 3D on the ground, and the rigid body representation is adopted by the hovercraft body; the apron is in universal contact with the ground, the apron is in friction contact with the ground, and the friction coefficient is 0.03.
Compared with the prior art, the invention has the following advantages and effects: stability of the hovercraft is an important characteristic related to navigation safety of the hovercraft, and stability calculation can guide design of an apron, air cushion parameters and a fan in the design process of an apron air cushion system of the hovercraft so as to improve the overall performance of the hovercraft. Therefore, the stability of the hovercraft is ensured to meet the standard requirement by designing the air cushion system and the apron system, but the airworthiness of the hovercraft is also deteriorated due to overhigh stability, so that the stability of the hovercraft needs to be comprehensively considered. The calculation method for the three-dimensional apron stability of the hovercraft, which is provided by the invention, is based on the hovercraft dynamics, the apron dynamics, the boat posture and a coupling action platform among the hovercraft dynamics, the apron dynamics, the boat posture and the three, can carry out quantitative analysis on the stability of the hovercraft, considers the real configuration of the three-dimensional apron and has a guiding function for guiding the design of an hovercraft apron air cushion system.
Drawings
FIG. 1 is a flow chart of a hovercraft land stationarity value calculation;
FIG. 2 is a block diagram of a hovercraft stationarity calculation routine implementation;
FIG. 3 is a diagram of a three-dimensional apron model of a whole hovercraft;
FIG. 4 is a typical section of a hovercraft side skirt (corresponding to the longitudinal skirt, 5 finger length), in this view 1-skirt, 2-hull, 3-ground;
FIG. 5 is a typical segmented finite element model diagram of a three-dimensional apron of a hovercraft, wherein 1-apron, 2-hull, 3-ground;
FIG. 6 is a diagram of calculation of finite element deformation of a three-dimensional apron of a hovercraft;
FIG. 7 is a Hovercraft land stationarity curve (M/(GB) - α).
Detailed Description
The invention will be further illustrated with reference to the following specific examples. It should be understood that these examples are for illustrative purposes only and are not intended to limit the scope of the present invention. Further, it should be understood that various changes or modifications of the present invention may be made by those skilled in the art after reading the teaching of the present invention, and such equivalents may fall within the scope of the present invention as defined in the appended claims.
With reference to fig. 1, the hovercraft land static stability calculation method based on three-dimensional apron deformation provided by the invention comprises the following steps:
step 1, obtaining an original balance state of the hovercraft according to geometrical parameters and characteristic parameters of a fan of the hovercraft and based on a fan characteristic curve equation and a fan-flow channel-big bag-air cushion flow continuity equationCharacteristic air cushion parameters (with 0 degree of lateral inclination), e.g. left air chamber cushion pressure PcL0And the bag pressure PbL0Right air chamber cushion pressure PcR0And the bag pressure PbR0And a height h of the dischargee0And the like.
And 2, selecting a side skirt typical section corresponding to the longitudinal separation skirt, and establishing a hovercraft skirt typical section geometric model through CATIA according to the skirt profile. Establishing a finite element model of the hovercraft based on Abaqus, and respectively applying the characteristic parameters of the air cushion obtained in the step (1), such as cushion pressure P of a left air chambercL0And the bag pressure PbL0Right air chamber cushion pressure PcR0And the bag pressure PbR0And a height h of the dischargee0And obtaining the geometric shape of the apron in the design state by adopting a dynamic display solution method, and extracting the characteristic parameters of the apron, such as the height h of the apron on the portsL0And width x of apron on port sidesL0Starboard apron skirt height hsR0And width x of starboard apronsR0。
Step 3, dividing the moment M at a given air cushioncThen, the cushion pressure P of the left air chamber is calculated according to the balance of the upward force and the moment of the heave and roll freedom degreescLAnd right air chamber cushion pressure PcR. Solving the left air chamber bag pressure P according to the fan characteristic curve and the fan-air duct-big bag-air cushion flow continuity equationbLRight air chamber bag pressure PbRAnd the roll angle alpha and the height of the center of gravity h of the boatg。
Step 4, pressing the left air chamber with pressure PcLRight air chamber cushion pressure PcRLeft air chamber bag pressure PbLRight air chamber bag pressure PbRAnd the transverse inclination angle alpha and the gravity center height h of the boatgApplying the equal parameters as boundary conditions and loads to a finite element model of the hovercraft, calculating the deformation of the apron through Abaqus, and extracting the characteristic parameters of the apron, such as the height h of the apron on the portsLAnd width x of apron on port sidesLStarboard apron skirt height hsRAnd width x of starboard apronsR. Thereby obtaining the restoring moment M caused by the increase of the air cushion area due to the deformation of the apronsWhile the transverse inclination and the gravity center height change of the boat body lead to the inclination moment M generating gravityg。
Step 5, setting different air cushion segmentation moments McThe curve (M/(GB) -alpha) of the dimensionless external moment and the roll angle can be obtained, and the obtained dimensionless stability is high and can be used as a standard for measuring the static lifting stability of the hovercraft.
With reference to fig. 2, the framework flow of the computation procedure for the stationarity of land of the hovercraft is as follows:
the apron-air cushion-boat posture interaction information platform mainly takes Matlab programming as a platform, and information exchange is carried out by calling a boat posture module, an air cushion dynamic module and a flexible apron structure dynamic module.
In the boat attitude module, on the basis of given pressure and apron geometric parameters, the roll inclination angle alpha and the gravity center height h of the hovercraft are obtained through a force and moment balance equation on the roll and heave freedom degreesgAnd the dynamic module of the air cushion and the dynamic module of the flexible apron structure are provided.
In the air cushion dynamics module, on the basis of given boat posture and apron geometric parameters, aerodynamic characteristic parameters of the hovercraft, such as cushion pressure P, are obtained based on a fan characteristic curve equation and a fan-air flue-big bag-air cushion flow continuity equationcAnd the bag pressure PbAnd the like, and are submitted to a flexible apron structure dynamics module and a boat posture module.
In the flexible apron structure dynamics module, apron geometric structure parametric modeling (stp format geometric model file) is carried out by calling a CATIA secondary development module. And (3) importing the geometric model into Abaqus, realizing finite element model modeling based on Python secondary development, and applying cushion pressure, bag pressure and boundary conditions to generate a calculation file (inp format finite element calculation file). And then calling an Abaqus structure solver to solve, performing data analysis on a result file (odb format result file) by adopting Python secondary development, and outputting the analyzed result file (dat format result file) to the air cushion dynamics and boat posture module.
The method is adopted for calculating the stability of the hovercraft aiming at the typical hovercraft and the finger-type apron, and the three-dimensional geometric model of the hovercraft is shown in figure 3. The stability calculation mainly depends on the side skirt sections corresponding to the mediastinum skirt, so that a side typical section corresponding to the mediastinum skirt is selected, the length of the side typical section is 5 finger lengths, a three-dimensional geometric model as shown in figure 4 is established, an apron typical sectional finite element model as shown in figure 4 is established according to the model, and the left side skirt and the right side skirt are respectively connected to the ship body; the apron adopts a thin film unit.
According to the calculation process, the land static stability and the land stability of the hovercraft are calculated, fig. 6 is a cloud chart calculated by the apron in a touchdown mode at a certain roll angle, display dynamics are adopted for solving, in order to improve the calculation efficiency, a rigid body plane is adopted for representing the ground, and a rigid body is adopted for representing the rigid hull.
Given different McAt this time, a dimensionless external moment versus roll angle curve (M/(GB) - α) can be obtained as shown in FIG. 7. Meanwhile, the stability numerical value calculation method is verified by adopting a hovercraft scale ship model stability test, and the theoretical simulation calculation and test result are better in conformity through the graph 7, so that the hovercraft model stability numerical value calculation method can be used for hovercraft apron stability design.

Claims (10)

1. A hovercraft land static stability calculation method based on three-dimensional apron deformation is characterized by comprising the following steps:
step 1, obtaining air cushion characteristic parameters of the hovercraft in an initial balance state, wherein when the hovercraft is in the initial balance state, the transverse inclination angle of the hovercraft is 0 degree;
step 2, establishing a finite element model of the hovercraft, respectively applying the air cushion characteristic parameters obtained in the step 1 to obtain the geometric molding of the apron in a design state, and extracting the characteristic parameters of the apron;
step 3, dividing the moment M at a given air cushioncThen, the cushion pressure P of the left air chamber is calculated according to the balance of the forces and moments on the heave freedom degree and the roll freedom degreecLAnd right air chamber cushion pressure PcRThe heave freedom is represented by the change of the height of the gravity center, and the roll is represented by the roll angle; solving according to the fan characteristic curve and the fan-air duct-big bag-air cushion flow continuity equation to obtain the left air chamber bag pressure PbLAnd right air cell bag pressure PbRAnd the roll angle alpha and the height h of the center of gravity of the hovercraftg；
Step 4, filling the left air chamber obtained in the step 3Pressure PcLRight air chamber cushion pressure PcRLeft air chamber bag pressure PbLRight air chamber bag pressure PbRThe transverse inclination angle alpha of the hovercraft, and the gravity center height h of the hovercraftgAfter the boundary conditions and the loads are applied to the finite element model of the hovercraft established in the step 2, extracting apron characteristic parameters;
step 5, calculating the deformation of the apron based on the apron characteristic parameters obtained in the step 4 and the apron characteristic parameters obtained in the step 2, and further obtaining the restoring moment M caused by the increase of the air cushion area due to the deformation of the aprons(ii) a Simultaneously obtains the gravity tilting moment M generated by the hovercraft due to the transverse inclination and the gravity center height changeg；
Step 6, setting different air cushion segmentation moments McAnd repeating the steps 3 to 5 to obtain a curve of the dimensionless external moment M/(GB) and the roll angle alpha, and obtaining the dimensionless stability based on the curve, wherein the dimensionless stability can be used as a standard for measuring the static padding stability of the hovercraft.
2. The hovercraft land stationarity calculating method based on three-dimensional apron deformation as claimed in claim 1, wherein in step 1, the hovercraft air cushion characteristic parameter in the initial balance state is obtained based on a fan characteristic curve equation and a fan-flow channel-big bag-air cushion flow continuity equation according to a hovercraft air cushion geometric parameter and a fan characteristic parameter.
3. The hovercraft land stationarity calculating method based on three-dimensional apron deformation as claimed in claim 1, wherein in step 1, the air cushion characteristic parameter includes left air chamber cushion pressure PcL0And left air cell pressure PbL0Right air chamber cushion pressure PcR0And right air cell bag pressure PbR0Balanced discharge height he0。
4. The hovercraft land stationarity calculating method based on three-dimensional apron deformation as claimed in claim 3, wherein in step 2, when the hovercraft finite element model is established, a side apron typical segment corresponding to the hovercraft longitudinal separation skirt is selected, a hovercraft apron typical segment geometric model is established through CATIA according to the skirt profile, and the hovercraft finite element model is established based on Abaqus.
5. The hovercraft land stationarity calculating method based on three-dimensional apron deformation according to claim 4, wherein in step 1, Matlab programming is used as a platform, the characteristic parameters of the air cushion are obtained by calling an air cushion dynamics module and are transmitted to the apron dynamics module;
in step 2, an apron dynamics module calls a CATIA secondary development module to carry out parametric modeling on an apron geometrical structure, introduces a geometrical model into Abaqus and realizes parametric finite element model modeling based on Python secondary development to obtain a finite element model of the hovercraft, and applies characteristic parameters of the air cushion to generate a calculation file;
in step 3, calling an Abaqus structure solver to solve, realizing data analysis on a result file by adopting Python secondary development, and calling a boat attitude module to obtain the transverse inclination angle alpha and the gravity center height h of the hovercraftg。
6. The hovercraft land stationarity calculating method based on three-dimensional apron deformation according to claim 5, wherein in the step 3, the nonlinear finite calculation is performed through Abaqus Python-based quadratic development, and the display dynamics is adopted for solving.
7. The hovercraft land static stability calculation method based on three-dimensional apron deformation as claimed in claim 1, wherein in step 2, apron geometric shaping in the design state is obtained by using a dynamic display solution method, and apron characteristic parameters are extracted, wherein the apron characteristic parameters comprise height h of a port apronsL0And width x of apron on port sidesL0Starboard apron skirt height hsR0And width x of starboard apronsR0。
8. A method as claimed in claim 1, based onThe land static stability calculation method of the hovercraft with the three-dimensional apron deformation is characterized in that in the step 4, the apron characteristic parameters comprise the height h of the apron on the port sidesLAnd width x of apron on port sidesLStarboard apron skirt height hsRAnd width x of starboard apronsR(ii) a In step 5, the skirt deformation is calculated by Abaqus.
9. The hovercraft land stationarity calculating method based on three-dimensional apron deformation as claimed in claim 1, wherein the hovercraft land stationarity calculating method is implemented based on an apron-air cushion-boat attitude mutual information platform which requires mutual information exchange among air cushion dynamics, apron dynamics, boat attitude and the three.
10. The hovercraft land stationarity calculating method based on three-dimensional apron deformation as claimed in claim 1, wherein in the hovercraft finite element model, the apron adopts thin film elements, the ground adopts 3D analysis rigid body plane representation, and the hovercraft hull adopts rigid body representation; the apron is in universal contact with the ground, the apron is in friction contact with the ground, and the friction coefficient is 0.03.
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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7296526B1 (en) * 2006-08-31 2007-11-20 Textron Inc. Dual stability seal skirt system for air cushion vehicle
CN103387038A (en) * 2013-07-30 2013-11-13 大连理工大学 Analysis method for reducing rolling motion of ship
CN103407443A (en) * 2013-07-11 2013-11-27 哈尔滨工程大学 Hovercraft navigation safety coordination and control method
CN104760588A (en) * 2014-11-27 2015-07-08 哈尔滨工程大学 Safety clearance control method for air cushion vehicle and emergency working condition control method based on safety clearance
CN105204508A (en) * 2015-09-24 2015-12-30 哈尔滨工程大学 Hovercraft course control method based on course and slew rate coordination control strategy
CN105856994A (en) * 2016-05-23 2016-08-17 中国船舶重工集团公司第七○二研究所 Air-propelled ship automatic trim adjustment device
CN111666633A (en) * 2020-06-10 2020-09-15 中国船舶工业集团公司第七0八研究所 Calculation method for three-dimensional apron responsivity of hovercraft

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7296526B1 (en) * 2006-08-31 2007-11-20 Textron Inc. Dual stability seal skirt system for air cushion vehicle
CN103407443A (en) * 2013-07-11 2013-11-27 哈尔滨工程大学 Hovercraft navigation safety coordination and control method
CN103387038A (en) * 2013-07-30 2013-11-13 大连理工大学 Analysis method for reducing rolling motion of ship
CN104760588A (en) * 2014-11-27 2015-07-08 哈尔滨工程大学 Safety clearance control method for air cushion vehicle and emergency working condition control method based on safety clearance
CN105204508A (en) * 2015-09-24 2015-12-30 哈尔滨工程大学 Hovercraft course control method based on course and slew rate coordination control strategy
CN105856994A (en) * 2016-05-23 2016-08-17 中国船舶重工集团公司第七○二研究所 Air-propelled ship automatic trim adjustment device
CN111666633A (en) * 2020-06-10 2020-09-15 中国船舶工业集团公司第七0八研究所 Calculation method for three-dimensional apron responsivity of hovercraft

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