CN115593653B - High-speed air-water medium crossing test recovery test device and test method - Google Patents
High-speed air-water medium crossing test recovery test device and test method Download PDFInfo
- Publication number
- CN115593653B CN115593653B CN202211335429.7A CN202211335429A CN115593653B CN 115593653 B CN115593653 B CN 115593653B CN 202211335429 A CN202211335429 A CN 202211335429A CN 115593653 B CN115593653 B CN 115593653B
- Authority
- CN
- China
- Prior art keywords
- cabin
- test
- control
- recovery
- test device
- 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
- 238000012360 testing method Methods 0.000 title claims abstract description 153
- 238000011084 recovery Methods 0.000 title claims abstract description 66
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 59
- 238000010998 test method Methods 0.000 title claims abstract description 16
- 238000007667 floating Methods 0.000 claims abstract description 47
- 238000000034 method Methods 0.000 claims abstract description 7
- 230000007246 mechanism Effects 0.000 claims description 40
- 239000002360 explosive Substances 0.000 claims description 22
- 230000000977 initiatory effect Effects 0.000 claims description 22
- 230000005540 biological transmission Effects 0.000 claims description 20
- 238000007789 sealing Methods 0.000 claims description 14
- 238000005259 measurement Methods 0.000 claims description 13
- 239000002775 capsule Substances 0.000 claims description 11
- 230000009471 action Effects 0.000 claims description 6
- 238000004458 analytical method Methods 0.000 claims description 6
- 230000008859 change Effects 0.000 claims description 3
- 238000005474 detonation Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 230000007613 environmental effect Effects 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- 238000004880 explosion Methods 0.000 claims 1
- 238000011160 research Methods 0.000 abstract description 8
- 108010066114 cabin-2 Proteins 0.000 description 11
- 108010066057 cabin-1 Proteins 0.000 description 9
- 108010066278 cabin-4 Proteins 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 238000004088 simulation Methods 0.000 description 3
- 238000012795 verification Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a high-speed air-water medium crossing test recovery test device and a test method, which are used for meeting the requirements of effectively recovering tested load and test data after the tested load crosses the air-water medium at a high speed and completes an underwater high-speed sailing task under the test conditions of narrow water area and accurate requirement of a water inlet position. The test recovery test device and the test method of the invention adapt to the accurate test conditions required by narrow water areas and water entering positions through the guidance control function; the aerofoil is folded and unfolded in the air and underwater at proper time to provide air stability and a speed reduction function after entering water, so that good conditions are provided for underwater recovery; the tested load is effectively recovered through the floating bag inflation and floating, and more comprehensive test data is obtained, so that the method has important significance for key technical research of the high-speed air-water medium crossing aircraft.
Description
Technical Field
The invention relates to the technical field of high-speed cross-medium tests, in particular to a high-speed air-water medium cross-medium test recovery test device and a test method.
Background
The high-speed cross-medium aircraft has very wide application prospect in military and civil fields such as cross-domain sudden attack prevention and investigation, rapid throwing of unmanned systems in water, emergency rescue of marine disasters, deep sea resource exploration and the like. At present, the high-speed cross-medium aircraft is still in a key technology research stage, a large number of simulations and experiments are needed to be carried out as research basis and verification support for high-speed cross-medium transition mechanism research, high-speed water entry and underwater navigation mechanism research and the like, and experimental measured data are powerful supports for simulation analysis and verification, so that the accumulation and analysis of real-flight experiments and test data have very important significance for key technology research. But are limited by test methods, conditions and recovery means, most of tests and tests of high-speed air-water medium crossing aircrafts are verified by steps in stages or by a scaling model, or in the test implementation, the recovery of products is abandoned due to the fact that the speed is too high and no corresponding recovery means exists, so that mutual comparison verification is difficult between simulation analysis and test, test data are not obtained comprehensively, and research work is not facilitated.
Therefore, a high-speed air-water medium crossing test recovery test device and a test method need to be developed to solve the problems.
Disclosure of Invention
The invention aims to solve the problems and designs a high-speed air-water medium crossing test recovery test device and a test method.
The invention realizes the above purpose through the following technical scheme:
high-speed sky-water medium strides over test recovery test device includes:
a load compartment to be tested;
the gas source cabin is used for providing high-pressure gas;
a collapsible-unfoldable airfoil structure; the foldable-unfolding airfoil structure is arranged on the outer wall of the air source cabin;
a buoyancy capsule cabin; the air source cabin is arranged between the first end of the floating bag cabin and the load cabin to be tested; the floating bag cabin is internally provided with a floating bag, and a high-pressure gas outlet of the gas source cabin is connected with the floating bag;
a control cabin; the second end of the buoyancy capsule cabin is connected with the control cabin;
a control surface structure; the control surface structure is arranged on the control cabin;
data test recovery, program control, positioning electronics components and power components; the signal ends of the data test recovery, program control and positioning electronic component and the power supply component are respectively connected with the signal end of the tested load cabin, the signal end of the air source cabin and the signal end of the foldable-unfolding airfoil structure.
Specifically, the control surface structure comprises a control surface control mechanism, a guidance control system and a plurality of control surfaces; the control surfaces are uniformly distributed on the side wall of the control cabin, and the signal end of the guidance control system is connected with the signal end of the control surface control mechanism.
Specifically, a high-pressure gas cylinder is arranged in the gas source cabin, and a high-pressure gas outlet of the high-pressure gas cylinder is connected with the floating bag.
Specifically, be provided with the opening on the buoyancy module cabin, be provided with the sealed lid of buoyancy module cabin on the opening, the sealed installation department of lid of buoyancy module cabin is provided with the first initiating explosive device that is used for exploding sealed lid of buoyancy module cabin, and the signal end of the detonation mechanism of first initiating explosive device is connected with the signal end of data test recovery, program control, location electronics subassembly and power module.
Specifically, the top surface of the buoyancy bag is provided with a satellite antenna for positioning.
The foldable-unfolding airfoil structure comprises an airfoil folding and unfolding driver, a transmission mechanism and a plurality of airfoils, wherein the airfoil folding and unfolding driver and the transmission mechanism are in transmission connection with the airfoils, and grooves for placing the airfoils after folding are formed in the outer wall of the air source cabin.
Specifically, a second initiating explosive device is arranged at the joint of the control cabin and the buoyancy bag cabin.
The high-speed air-water medium crossing test recovery test method comprises the following steps:
step (1): the test device sails in the air; the method comprises the steps that an airfoil in an initial state is folded, a test device is separated from a rocket engine after the rocket engine is boosted to reach a certain height and speed in the air, a data test recovery, program control, positioning electronics assembly and a power assembly are started, and measurement data are acquired and stored, wherein the measurement data comprise environmental parameters and track parameters of a tested load cabin;
step (2): the airfoil is unfolded in the air; the data test recovery, program control and positioning electronics assembly and the power supply assembly send signals to the airfoil folding and unfolding driver and the transmission mechanism to drive a plurality of airfoils to unfold, so as to provide pneumatic stability for the test device;
step (3): the test device is controlled; the control surface control mechanism is controlled by the guidance control system to control a plurality of control surfaces, so that aerial track and attitude control is performed until the requirements of attitude, speed and position before entering water are met;
step (4): separating a control cabin of the test device; the data test recovery, program control, positioning electronic assembly and power supply assembly send ignition signals to a second initiating explosive device, the second initiating explosive device explodes to disconnect the buoyancy capsule cabin from the control cabin, and the control cabin is separated;
step (5): folding the airfoil in the air; before entering water, the data test recovery, program control, positioning electronics assembly and power supply assembly send signals to the airfoil folding and unfolding driver and the transmission mechanism to drive a plurality of airfoils to fold, so as to reduce the water entering resistance of the test device and provide conditions for the tested load cabin to complete the air-water medium crossing;
step (6): the test device is filled with water; the tested load cabin generates cavitation resistance by means of its own hydrodynamic shape or cavitation generator, and is used for reducing speed loss and completing underwater high-speed navigation task;
step (7): the airfoil surface is unfolded underwater; after the under-water high-speed sailing task of the load cabin to be tested is finished, the speed of the test device is reduced in order to meet the floating recovery condition; the data test recovery, program control, positioning electronics assembly and power supply assembly send signals to the airfoil folding and unfolding driver and the transmission mechanism to drive the airfoils to unfold, cavitation bubbles are collapsed after the airfoils are unfolded, and meanwhile, resistance is suddenly increased due to the change of the hydrodynamic shape of the test device, so that the speed of the test device is rapidly reduced, and the floating recovery condition is met;
step (8): throwing a cover of the buoyancy capsule cabin; the data test recovery, program control, positioning electronic assembly and power supply assembly send ignition signals to a first initiating explosive device, the first initiating explosive device explodes to disconnect the buoyancy chamber and the buoyancy chamber sealing cover, and the buoyancy chamber sealing cover is separated;
step (9): the floating bag is inflated and floats upwards; the data test recovery, program control and positioning electronic assembly and the power supply assembly control the valve of the high-pressure gas cylinder in the gas source cabin to be opened, the high-pressure gas cylinder is inflated into the floating bag through the pipeline until the pressure difference between the inside and the outside of the floating bag reaches a certain value, and in the process, the test device gradually floats under the buoyancy effect generated by the floating bag;
step (10): floating and folding the airfoil surface; after the test device begins to float upwards, a driver of the airfoil folding and unfolding mechanism receives folding signals sent by the data test recovery, the program control, the positioning electronics assembly and the power supply assembly, and drives the folding and unfolding mechanism to execute airfoil folding action, so that the floating resistance of the test device is reduced, and good conditions are provided for the floating of the test device;
step (11): the positioning component sends out a positioning signal; the test device floats upwards under the action of the buoyancy bag until the positioning antenna at the top of the buoyancy bag is exposed out of the water surface, and the data test recovery, program control and positioning electronic component and the power supply component send the position information of the test device to ground equipment for receiving through the antenna;
step (12): recovering a test device; searching and recovering the test device according to the position information received by the ground equipment;
step (13): disassembling the test device, taking out a storage component of the measurement data, and obtaining the measurement data;
meanwhile, the tested load cabin is disassembled, and test condition analysis is carried out.
Preferably, the test device is also aerial launched by the aircraft at an altitude and speed in the air.
The invention has the beneficial effects that:
the test recovery test device and the test method solve the problem of completing the test and recovery of the underwater high-speed sailing task of the load to be tested by crossing the air-water medium at a high speed, can effectively recover the load to be tested, acquire more comprehensive test data, are suitable for test conditions such as narrow water area, accurate requirement on the water inlet position and the like, and have important significance for the key technical research of the high-speed air-water medium crossing aircraft.
Drawings
FIG. 1 is a schematic illustration of a positive triaxial test of a test apparatus;
FIG. 2 is a front view of the test rig (airfoil deployment);
FIG. 3 is a cross-sectional view A-A of FIG. 2;
FIG. 4 is a front view of the test rig (airfoil fold);
FIG. 5 is a schematic diagram of the test method (aerial part);
FIG. 6 is a schematic diagram of the test method (underwater portion);
wherein, 1-the load compartment to be tested; 2-an air source cabin; 3-airfoil; 4-a buoyancy capsule cabin; 5-sealing cover of the buoyancy chamber; 6-a control cabin; 7-a control surface; 8-guidance control system; 9-a control surface control mechanism; 10-floating bags; 11-high pressure gas cylinder; 12-data test recovery, program control, positioning electronics components and power components; 13-airfoil fold and unfold drive and transmission mechanism.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present invention, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "inner", "outer", "left", "right", etc. are based on the directions or positional relationships shown in the drawings, or the directions or positional relationships conventionally put in place when the inventive product is used, or the directions or positional relationships conventionally understood by those skilled in the art are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific direction, be configured and operated in a specific direction, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, terms such as "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
The following describes specific embodiments of the present invention in detail with reference to the drawings.
As shown in fig. 1-4, the high-speed air-water medium crossing test recovery test device comprises:
a load compartment 1 to be tested; the tested load cabin 1 is a tested object, has good aerodynamic and hydrodynamic shapes, is generally in an axisymmetric or plane-symmetric configuration, and can reduce resistance by generating cavitation after high-speed water entering so as to further complete a high-speed underwater navigation task in order to meet the requirements of high-speed air-water medium crossing and high-speed water entering;
a gas source module 2 for supplying high-pressure gas;
a collapsible-unfoldable airfoil 3 structure; the foldable-unfolding airfoil 3 is structurally arranged on the outer wall of the air source cabin 2;
a buoyancy module 4; the air source cabin 2 is arranged between the first end of the floating bag cabin 4 and the load cabin 1 to be tested; the floating bag 10 is arranged in the floating bag cabin 4, and a high-pressure gas outlet of the gas source cabin 2 is connected with the floating bag 10; the buoyancy chamber 4 is used for accommodating the buoyancy 10 in a folded state. The float 10 is generally made of flexible rubber material and is communicated with a high-pressure gas cylinder 11 in the gas source cabin 2 through a pipeline. Before entering water, the buoyancy bag 10 is emptied of gas and is accommodated in the buoyancy bag cabin 4 in a folded state; when the buoyancy is recovered, the sealing cover at the bottom end of the buoyancy chamber 4 is thrown away by an initiating explosive device, and the buoyancy chamber 10 is inflated and unfolded to be similar to a hot air balloon shape so as to generate enough buoyancy to float the whole test device to the water surface. The satellite antenna of the positioning assembly is positioned on the inner top surface (after inflation) of the buoyancy bag 10 and is used for realizing the positioning of the test device after floating on the water surface.
A control cabin 6; the second end of the buoyancy chamber 4 is connected with the control chamber 6; the control cabin 6 is used for realizing guidance control and program control of the test device in the air, and ensuring that the state of the test device before water entering meets the water entering conditions (namely water entering posture, speed, position and the like); the guidance control system 8 is arranged in the control cabin 6;
a control surface 7 structure; the control surface 7 is structurally arranged on the control cabin 6;
data test reclamation, program control, positioning electronics components, and power components 12 (including collection and hard reclamation storage components, program control components, positioning components, batteries, etc.); the signal ends of the data test recovery, program control and positioning electronic component and the power supply component 12 are respectively connected with the signal end of the tested load cabin 1, the signal end of the air source cabin 2 and the signal end of the foldable-unfolding airfoil 3 structure.
As shown in fig. 1-2, the control surface 7 structure includes a control surface control mechanism 9, a guidance control system 8 (the guidance control system 8 includes an inertial measurement unit, a flight integrated control unit, a satellite receiving unit, a battery, etc.), and a plurality of control surfaces 7; the control surfaces 7 are uniformly distributed on the side wall of the control cabin 6, and the signal end of the guidance control system 8 is connected with the signal end of the control surface control mechanism 9. The control surface 7 deflects through an operating mechanism so as to ensure that the test device has good operability and stability in the air. The control surface 7 is generally in an X shape or an inverted Y shape and symmetrically arranged around the control cabin 6, and the specific installation position, the control surface 7 configuration and the like of the control surface should meet the pneumatic and control requirements.
As shown in fig. 1 and 3, a high-pressure gas cylinder 11 is arranged in the gas source cabin 2, and a high-pressure gas outlet of the high-pressure gas cylinder 11 is connected with a buoyancy bag 10.
As shown in fig. 1, an opening is formed in the buoyancy chamber 4, a buoyancy chamber sealing cover 5 is arranged on the opening, a first initiating explosive device for frying the buoyancy chamber sealing cover 5 is arranged at the installation position of the buoyancy chamber sealing cover 5, and a signal end of a detonation mechanism of the first initiating explosive device is connected with a signal end of a data test recovery, program control, positioning electronic assembly and power supply assembly 12.
The top surface of the float 10 is provided with a satellite antenna for positioning.
As shown in fig. 1-3, the foldable-unfolding airfoil 3 structure comprises an airfoil folding and unfolding driver and transmission mechanism 13 and a plurality of airfoils 3, wherein the airfoil folding and unfolding driver and transmission mechanism 13 is in transmission connection with the airfoils 3, and a groove for placing the airfoils 3 after folding is arranged on the outer wall of the air source cabin 2. The aerofoils 3 are symmetrically arranged around the front end of the air source cabin 2, have the functions of expanding in the air to provide lifting force, folding to reduce resistance before entering water, guaranteeing the hydrodynamic shape of the load cabin 1 to be tested, expanding and decelerating after the underwater navigation mission is finished, and folding to reduce resistance during recovery and floating. The wing surface 3 is generally in an X shape or a "+" shape or a "<" shape or a "-" shape and other layout shapes when being unfolded, and is folded in the air source cabin 2 or is conformal with the air source cabin 2, so that the protrusion of the cabin body after the wing surface 3 is folded is reduced or avoided as much as possible, and the specific installation position, the wing surface 3 configuration, the number and the like meet the pneumatic requirements. The folding and unfolding of the airfoil 3 is effected by corresponding mechanisms, typically drives and corresponding transmission mechanisms, such as electric drives, hydraulic drives, pneumatic drives, etc. Figure 2 shows an airfoil 3 "x" configuration wherein the airfoil 3 is folded to collapse within a channel structure within the air supply compartment 2.
A second initiating explosive device is arranged at the joint of the control cabin 6 and the buoyancy chamber 4.
As shown in fig. 5 and 6, the high-speed air-water medium crossing test recovery test method comprises the following steps:
step (1): the test device sails in the air; the airfoil 3 in the initial state is folded, the test device is separated from the rocket engine after the rocket engine is boosted to reach a certain height and speed in the air, the data test recovery, the program control, the positioning electronics assembly and the power assembly 12 are started, and the measurement data are collected and stored, wherein the measurement data comprise the environmental parameters and the track parameters of the load cabin 1 to be tested; the test device can also be thrown in the air by an airplane at a certain altitude and speed in the air.
Step (2): the airfoil 3 is spread in the air; the data test recovery, program control and positioning electronics assembly and power supply assembly 12 sends signals to the airfoil folding and unfolding driver and transmission mechanism 13 to drive the plurality of airfoils 3 to unfold for providing aerodynamic stability for the test device;
step (3): the test device is controlled; the control surface control mechanism 9 is controlled by the guidance control system 8 to control a plurality of control surfaces 7, so that the aerial track and the gesture are controlled until the requirements of gesture, speed and position before entering water are met;
step (4): the test device control cabin 6 is separated; the data test recovery, program control and positioning electronic assembly and power supply assembly 12 sends an ignition signal to a second initiating explosive device, the second initiating explosive device explodes to disconnect the buoyancy capsule cabin 4 from the control cabin 6 and separate the control cabin 6;
step (5): folding the airfoil surface 3 in the air; before entering water, the data test recovery, program control and positioning electronic assembly and power supply assembly 12 send signals to the airfoil folding and unfolding driver and transmission mechanism 13 to drive the airfoils 3 to fold, so as to reduce the water entering resistance of the test device and provide conditions for the tested load cabin 1 to complete the air-water medium crossing;
step (6): the test device is filled with water; the tested load cabin 1 generates cavitation resistance by means of its own hydrodynamic shape or cavitation generator, and is used for completing underwater high-speed navigation tasks with reduced speed loss;
step (7): the airfoil 3 is deployed underwater; after the underwater high-speed sailing task of the load cabin 1 to be tested is finished, the speed of the test device is reduced in order to meet the floating recovery condition; the data test recovery, program control and positioning electronic assembly and power supply assembly 12 send signals to the airfoil folding and unfolding driver and transmission mechanism 13 to drive the airfoils 3 to unfold, cavitation bubbles are collapsed after the airfoils 3 unfold, and meanwhile, resistance is suddenly increased due to the change of the hydrodynamic shape of the test device, so that the speed of the test device is rapidly reduced, and the floating recovery condition is met;
step (8): the floating capsule cabin 4 is covered; the data test recovery, program control and positioning electronic assembly and power supply assembly 12 sends an ignition signal to a first initiating explosive device, the first initiating explosive device explodes to disconnect the buoyancy chamber 4 from the buoyancy chamber sealing cover 5 and separate the buoyancy chamber sealing cover 5;
step (9): the floating bag 10 is inflated and floats upwards; the data test recovery, program control and positioning electronic assembly and power supply assembly 12 control the valve of the high-pressure gas cylinder 11 in the gas source cabin 2 to be opened, the high-pressure gas cylinder 11 is inflated into the floating bag 10 through a pipeline until the pressure difference between the inside and the outside of the floating bag 10 reaches a certain value, and in the process, the test device gradually floats upwards under the buoyancy effect generated by the floating bag 10;
step (10): the airfoil surface 3 floats and folds; after the test device begins to float upwards, a driver of the wing surface 3 folding and unfolding mechanism receives folding signals sent by the data test recovery, the program control, the positioning electronics assembly and the power supply assembly, and drives the folding and unfolding mechanism to execute the folding action of the wing surface 3, so that the floating resistance of the test device is reduced, and good conditions are provided for the floating of the test device;
step (11): the positioning component sends out a positioning signal; the test device floats upwards under the action of the buoyancy bag 10 until the positioning antenna at the top of the buoyancy bag 10 is exposed out of the water surface, and the data test recovery, program control and positioning electronic component and the power supply component 12 send the position information of the test device to ground equipment through the antenna for receiving;
step (12): recovering a test device; searching and recovering the test device according to the position information received by the ground equipment;
step (13): disassembling the test device, taking out a storage component of the measurement data, and obtaining the measurement data; meanwhile, the load cabin 1 to be tested is disassembled, and test condition analysis is performed.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that it will be apparent to those skilled in the art that modifications and variations can be made without departing from the technical principles of the present invention, and these modifications and variations should also be regarded as the scope of the invention.
Claims (2)
1. The high-speed air-water medium crossing test recovery test method is applied to a high-speed air-water medium crossing test recovery test device, and the high-speed air-water medium crossing test recovery test device comprises:
a load compartment to be tested;
the gas source cabin is used for providing high-pressure gas;
a collapsible-unfoldable airfoil structure; the foldable-unfolding airfoil structure is arranged on the outer wall of the air source cabin;
a buoyancy capsule cabin; the air source cabin is arranged between the first end of the floating bag cabin and the load cabin to be tested; the floating bag cabin is internally provided with a floating bag, and a high-pressure gas outlet of the gas source cabin is connected with the floating bag;
a control cabin; the second end of the buoyancy capsule cabin is connected with the control cabin;
a control surface structure; the control surface structure is arranged on the control cabin;
data test recovery, program control, positioning electronics components and power components; the signal ends of the data test recovery, program control and positioning electronic component and the power supply component are respectively connected with the signal end of the tested load cabin, the signal end of the air source cabin and the signal end of the foldable-unfolding airfoil structure;
the control surface structure comprises a control surface control mechanism, a guidance control system and a plurality of control surfaces; the control surfaces are uniformly distributed on the side wall of the control cabin, and the signal end of the guidance control system is connected with the signal end of the control surface control mechanism;
a high-pressure gas cylinder is arranged in the gas source cabin, and a high-pressure gas outlet of the high-pressure gas cylinder is connected with the floating bag;
the device comprises a buoyancy bag cabin, a data test recovery, program control, positioning electronic components and a power supply component, wherein an opening is formed in the buoyancy bag cabin, a buoyancy bag cabin sealing cover is arranged on the opening, a first initiating explosive device for explosion of the buoyancy bag cabin sealing cover is arranged at the mounting position of the buoyancy bag cabin sealing cover, and the signal end of a detonation mechanism of the first initiating explosive device is connected with the signal end of the data test recovery, program control and positioning electronic components and the power supply component;
the top surface of the floating bag is provided with a satellite antenna for positioning;
the foldable-unfolding airfoil structure comprises an airfoil folding and unfolding driver, a transmission mechanism and a plurality of airfoils, wherein the airfoil folding and unfolding driver and the transmission mechanism are in transmission connection with the airfoils, and a groove for placing the airfoils after folding is formed in the outer wall of the air source cabin;
a second initiating explosive device is arranged at the joint of the control cabin and the buoyancy bag cabin;
the method is characterized in that the high-speed air-water medium crossing test recovery test method comprises the following steps:
step (1): the test device sails in the air; the method comprises the steps that an airfoil in an initial state is folded, a test device is separated from a rocket engine after the rocket engine is boosted to reach a certain height and speed in the air, a data test recovery, program control, positioning electronics assembly and a power assembly are started, and measurement data are acquired and stored, wherein the measurement data comprise environmental parameters and track parameters of a tested load cabin;
step (2): the airfoil is unfolded in the air; the data test recovery, program control and positioning electronics assembly and the power supply assembly send signals to the airfoil folding and unfolding driver and the transmission mechanism to drive a plurality of airfoils to unfold, so as to provide pneumatic stability for the test device;
step (3): the test device is controlled; the control surface control mechanism is controlled by the guidance control system to control a plurality of control surfaces, so that aerial track and attitude control is performed until the requirements of attitude, speed and position before entering water are met;
step (4): separating a control cabin of the test device; the data test recovery, program control, positioning electronic assembly and power supply assembly send ignition signals to a second initiating explosive device, the second initiating explosive device explodes to disconnect the buoyancy capsule cabin from the control cabin, and the control cabin is separated;
step (5): folding the airfoil in the air; before entering water, the data test recovery, program control, positioning electronics assembly and power supply assembly send signals to the airfoil folding and unfolding driver and the transmission mechanism to drive a plurality of airfoils to fold, so as to reduce the water entering resistance of the test device and provide conditions for the tested load cabin to complete the air-water medium crossing;
step (6): the test device is filled with water; the tested load cabin generates cavitation resistance by means of its own hydrodynamic shape or cavitation generator, and is used for reducing speed loss and completing underwater high-speed navigation task;
step (7): the airfoil surface is unfolded underwater; after the under-water high-speed sailing task of the load cabin to be tested is finished, the speed of the test device is reduced in order to meet the floating recovery condition; the data test recovery, program control, positioning electronics assembly and power supply assembly send signals to the airfoil folding and unfolding driver and the transmission mechanism to drive the airfoils to unfold, cavitation bubbles are collapsed after the airfoils are unfolded, and meanwhile, resistance is suddenly increased due to the change of the hydrodynamic shape of the test device, so that the speed of the test device is rapidly reduced, and the floating recovery condition is met;
step (8): throwing a cover of the buoyancy capsule cabin; the data test recovery, program control, positioning electronic assembly and power supply assembly send ignition signals to a first initiating explosive device, the first initiating explosive device explodes to disconnect the buoyancy chamber and the buoyancy chamber sealing cover, and the buoyancy chamber sealing cover is separated;
step (9): the floating bag is inflated and floats upwards; the data test recovery, program control and positioning electronic assembly and the power supply assembly control the valve of the high-pressure gas cylinder in the gas source cabin to be opened, the high-pressure gas cylinder is inflated into the floating bag through the pipeline until the pressure difference between the inside and the outside of the floating bag reaches a certain value, and in the process, the test device gradually floats under the buoyancy effect generated by the floating bag;
step (10): floating and folding the airfoil surface; after the test device begins to float upwards, a driver of the airfoil folding and unfolding mechanism receives folding signals sent by the data test recovery, the program control, the positioning electronics assembly and the power supply assembly, and drives the folding and unfolding mechanism to execute airfoil folding action, so that the floating resistance of the test device is reduced, and good conditions are provided for the floating of the test device;
step (11): the positioning component sends out a positioning signal; the test device floats upwards under the action of the buoyancy bag until the positioning antenna at the top of the buoyancy bag is exposed out of the water surface, and the data test recovery, program control and positioning electronic component and the power supply component send the position information of the test device to ground equipment for receiving through the antenna;
step (12): recovering a test device; searching and recovering the test device according to the position information received by the ground equipment;
step (13): disassembling the test device, taking out a storage component of the measurement data, and obtaining the measurement data; meanwhile, the tested load cabin is disassembled, and test condition analysis is carried out.
2. The high-speed air-water medium crossing test recovery test method according to claim 1, wherein the test device is further capable of being thrown in the air by an aircraft at a certain altitude and speed in the air.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211335429.7A CN115593653B (en) | 2022-10-28 | 2022-10-28 | High-speed air-water medium crossing test recovery test device and test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211335429.7A CN115593653B (en) | 2022-10-28 | 2022-10-28 | High-speed air-water medium crossing test recovery test device and test method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115593653A CN115593653A (en) | 2023-01-13 |
| CN115593653B true CN115593653B (en) | 2024-04-16 |
Family
ID=84850244
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211335429.7A Active CN115593653B (en) | 2022-10-28 | 2022-10-28 | High-speed air-water medium crossing test recovery test device and test method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115593653B (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6082675A (en) * | 1998-08-17 | 2000-07-04 | The United States Of America As Represented By The Secretary Of The Navy | Standoff delivered sonobuoy |
| GB0313979D0 (en) * | 2003-06-17 | 2003-07-23 | Coupland Bell Ltd | Improvements in and relating to an amphibious craft |
| CN102243038A (en) * | 2010-09-21 | 2011-11-16 | 哈尔滨工业大学 | Rapidly-controlled aeration releasing mechanism |
| CN106068438A (en) * | 2014-03-28 | 2016-11-02 | 波音公司 | The long-distance sand transport of UAV navigation |
| CN106644388A (en) * | 2017-03-03 | 2017-05-10 | 中国工程物理研究院总体工程研究所 | Unmanned underwater vehicle folding swim bladder deepwater floating-upward test device and method |
| CN106956555A (en) * | 2016-11-22 | 2017-07-18 | 中国人民解放军空军工程大学 | The empty dual-purpose variant of water based on the conformal semi-ring wing crosses over ROV |
| CN107300456A (en) * | 2017-07-06 | 2017-10-27 | 中国人民解放军国防科学技术大学 | A kind of supercavity experimental rig and test method |
| CN109896008A (en) * | 2019-03-29 | 2019-06-18 | 武汉理工大学 | A kind of empty amphibious unmanned plane of adaptive water using rotor inclining rotary mechanism |
| WO2019119556A1 (en) * | 2017-12-20 | 2019-06-27 | 上海交通大学 | Fixed-wing sea-air amphibious aircraft and control method |
| CN110239712A (en) * | 2019-07-10 | 2019-09-17 | 中国科学院自动化研究所 | A kind of empty amphibious across medium bionic machine flying fish of water |
| CN111301079A (en) * | 2019-12-31 | 2020-06-19 | 中国海洋大学 | Cross-medium air-sea amphibious unmanned aerial vehicle |
| CN112208706A (en) * | 2020-09-30 | 2021-01-12 | 中国科学院深海科学与工程研究所 | Real-time submerged buoy communication floating body and motion control method |
| CN215475719U (en) * | 2021-06-09 | 2022-01-11 | 丰县汉祖圣境文化旅游发展有限公司 | Floating device of amphibious unmanned aerial vehicle |
| CN114993107A (en) * | 2022-04-21 | 2022-09-02 | 湖北航天技术研究院总体设计所 | Submarine striking system and striking method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9493235B2 (en) * | 2002-10-01 | 2016-11-15 | Dylan T X Zhou | Amphibious vertical takeoff and landing unmanned device |
| US9194678B2 (en) * | 2012-04-25 | 2015-11-24 | Wilcox Industries Corp. | Modular rocket system |
| US20180086450A1 (en) * | 2016-09-27 | 2018-03-29 | Young Chan Park | Amphibious flying vehicle |
| US11780580B2 (en) * | 2019-10-09 | 2023-10-10 | California Institute Of Technology | Passive and active stability systems for ballistically launched multirotors |
-
2022
- 2022-10-28 CN CN202211335429.7A patent/CN115593653B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6082675A (en) * | 1998-08-17 | 2000-07-04 | The United States Of America As Represented By The Secretary Of The Navy | Standoff delivered sonobuoy |
| GB0313979D0 (en) * | 2003-06-17 | 2003-07-23 | Coupland Bell Ltd | Improvements in and relating to an amphibious craft |
| CN102243038A (en) * | 2010-09-21 | 2011-11-16 | 哈尔滨工业大学 | Rapidly-controlled aeration releasing mechanism |
| CN106068438A (en) * | 2014-03-28 | 2016-11-02 | 波音公司 | The long-distance sand transport of UAV navigation |
| CN106956555A (en) * | 2016-11-22 | 2017-07-18 | 中国人民解放军空军工程大学 | The empty dual-purpose variant of water based on the conformal semi-ring wing crosses over ROV |
| CN106644388A (en) * | 2017-03-03 | 2017-05-10 | 中国工程物理研究院总体工程研究所 | Unmanned underwater vehicle folding swim bladder deepwater floating-upward test device and method |
| CN107300456A (en) * | 2017-07-06 | 2017-10-27 | 中国人民解放军国防科学技术大学 | A kind of supercavity experimental rig and test method |
| WO2019119556A1 (en) * | 2017-12-20 | 2019-06-27 | 上海交通大学 | Fixed-wing sea-air amphibious aircraft and control method |
| CN109896008A (en) * | 2019-03-29 | 2019-06-18 | 武汉理工大学 | A kind of empty amphibious unmanned plane of adaptive water using rotor inclining rotary mechanism |
| CN110239712A (en) * | 2019-07-10 | 2019-09-17 | 中国科学院自动化研究所 | A kind of empty amphibious across medium bionic machine flying fish of water |
| CN111301079A (en) * | 2019-12-31 | 2020-06-19 | 中国海洋大学 | Cross-medium air-sea amphibious unmanned aerial vehicle |
| CN112208706A (en) * | 2020-09-30 | 2021-01-12 | 中国科学院深海科学与工程研究所 | Real-time submerged buoy communication floating body and motion control method |
| CN215475719U (en) * | 2021-06-09 | 2022-01-11 | 丰县汉祖圣境文化旅游发展有限公司 | Floating device of amphibious unmanned aerial vehicle |
| CN114993107A (en) * | 2022-04-21 | 2022-09-02 | 湖北航天技术研究院总体设计所 | Submarine striking system and striking method |
Non-Patent Citations (3)
| Title |
|---|
| 共轴式水空双动力跨介质无人机结构设计与动力性能研究;张硕;《优秀硕士论文全文数据库工程科技Ⅱ辑》;20220316;第1-48页 * |
| 无人潜航器上浮运动的非线性流固耦合研究;张晓光;《中国力学大会论文集》;20190815;第32-37页 * |
| 水空两栖跨介质无人飞行器研究现状;杨兴帮;《机器人》;20180115;第79-83页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115593653A (en) | 2023-01-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108216532B (en) | Fixed-wing sea-air multi-purpose aircraft and control method | |
| JP6813997B2 (en) | Small aircraft with airbag device | |
| US10110323B2 (en) | Systems and methods for transmitting data from an underwater station | |
| US11312466B1 (en) | Inflatable structure deployment | |
| US7097136B2 (en) | Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea | |
| US3181809A (en) | Aircraft crash recorder unit | |
| US10514232B2 (en) | Launching aerial devices | |
| CN113212713B (en) | Underwater vehicle supporting vertical emission and attitude conversion control method thereof | |
| Maydew et al. | Design and testing of high-performance parachutes (la conception et les essais des parachutes a hautes performances) | |
| US4240601A (en) | Method for observing the features characterizing the surface of a land mass | |
| Rohrschneider et al. | Survey of ballute technology for aerocapture | |
| CN110966898B (en) | Missile projectile recovery system after completion of assessment flight test | |
| US10569908B1 (en) | Self-preserved amphibious landing of space hardware | |
| EP3392142B1 (en) | Deployable apparatus to prevent helicopter rollover | |
| CN115593653B (en) | High-speed air-water medium crossing test recovery test device and test method | |
| US4040583A (en) | Methods and apparatus for effecting recovery of a high speed aircraft from a condition of incipient or developed spin | |
| DiNonno et al. | Low-Earth Orbit Flight Test of an Inflatable Decelerator (LOFTID) Mission Overview and Science Return | |
| US3282539A (en) | Recovery system | |
| CN113247313A (en) | Flexible variant airship for recycling carrier rocket booster and recycling method | |
| Guo et al. | Design and development of a transition propulsion system for bimodal unmanned vehicles | |
| Groenenboom et al. | SPH simulations of free surface waves and the interaction with objects | |
| Pepper et al. | Aerodynamic decelerators-an engineering review | |
| KR20160057594A (en) | Buoyancy apparatus of unmanned vtol plane and unmanned vtol plane | |
| JP3284616B2 (en) | Aircraft recovery device and recovery method | |
| CN116331549A (en) | Unmanned aerial vehicle search and rescue system capable of being rapidly laid on water surface |
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 |