CN109747799B - Supercavitation torpedo - Google Patents
Supercavitation torpedo Download PDFInfo
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- CN109747799B CN109747799B CN201910032836.2A CN201910032836A CN109747799B CN 109747799 B CN109747799 B CN 109747799B CN 201910032836 A CN201910032836 A CN 201910032836A CN 109747799 B CN109747799 B CN 109747799B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention discloses a supercavitation torpedo, which adopts a gas turbine engine, a steering engine device driven and controlled by a motor, gas nozzles uniformly arranged along the inner circumference of the wall of a ventilating bowl and the like; the gas turbine is used as power, high-speed movement and ultra-long stroke of the heavy thermal power torpedo can be realized, and large-scale speed change or depth change of the torpedo can be realized. The tail gas gathering cabin is arranged in the front cabin section, so that tail gas generated by an engine is gathered and then discharged through the ventilation bowl at the front end, and the ventilation bowl is uniformly provided with the gas nozzles, so that supercavitation formed outside the supercavitation torpedo is surrounded by more uniform and stable gas, and the supercavitation formed outside the supercavitation torpedo is more uniform and stable, so that the forward resistance of the torpedo is greatly reduced, and the forward speed and range of the torpedo are improved.
Description
[ technical field ] A method for producing a semiconductor device
The invention belongs to the field of underwater supercavitation navigation, and particularly relates to a supercavitation torpedo.
[ background of the invention ]
The faster the navigation body navigates underwater, the higher the speed of the liquid flowing around the object, and the lower the pressure according to the fluid mechanics law. When the pressure is reduced to the critical pressure of water, the water is changed from liquid phase to gas phase to form water vapor bubbles, which helps to reduce the navigation resistance of the navigation body. The number of bubbles generated by natural cavitation is limited, and the bubbles are not compact and uniform, cannot completely wrap an underwater vehicle, and cannot adjust the size, the size and the thickness of the underwater vehicle, so that the resistance reducing effect is difficult to accurately control. In order to achieve the desired drag reduction effect, the generation of bubbles must be quantitatively controlled. At present, the main method is to inject gas into the environmental water body through a vent hole at the head of the navigation body, so that bubbles can develop downstream along the wall surface under the action of incoming flow to form an air bag covering the surface of the navigation body. A cavity is called a supercavity once it is large enough to cover most or all of the surface of the vehicle. The frictional resistance of the navigation body in water is about 850 times of the frictional resistance in air, and the underwater frictional resistance of the navigation body can be greatly reduced after the supercavity is formed. The supercavitation torpedo is an underwater weapon designed by utilizing the principle of supercavitation.
The engine applied in the supercavitation torpedo is originally a rocket engine, but the rocket engine has extremely low propelling efficiency in water, the consumption of a propellant is large, the working time of the engine is short, and the thrust is reduced along with the increase of the pressure when the depth is increased, so that the voyage of the torpedo is greatly reduced. The metal fuel water-thrust engine is a novel power system of an underwater vehicle, has the characteristics of high energy density, simple structure and the like, and is an important technical support for developing the underwater high-speed vehicle together with a supercavitation technology, but the prior art is immature and has obvious defects. For example, since the reaction is difficult to start and the metal fuel is difficult to react with water at low temperature, when the metal fuel powder is first heated to a molten or gasified state and aluminum is used as water to react with the metal fuel, a dense oxide film (alumina) is easily formed on the surface of the aluminum, and the oxide film can prevent the reaction between the aluminum and the water. The water-thrust engine technology is not mature, the initial combustion temperature of fuel entering a combustion chamber is low due to a carrier gas/carrier liquid feeding mode, so that the reaction is difficult to start, and a metal particle oxide film is difficult to remove, so that the reaction efficiency is influenced; the solid grain feeding mode grain is inconvenient for long-term storage, has large danger, is inconvenient for controlling the whole reaction process, and is not easy to control the reaction rate after the ingredients of the grain are determined.
The steering engine in the supercavitation torpedo is a traditional steering engine, and a traditional steering engine control device adopts hydraulic drive, so that the supercavitation torpedo occupies a large space and has high requirements on environment. For example, the supercavitation navigation body model with the built-in steering engine, which is proposed by the invention patent with the publication number of CN103926051A, cannot realize the automatic switching between the synchronous equidirectional rotation and the synchronous opposite-directional rotation of the two steering shafts, and is complex to operate. On the other hand, the conventional ventilation device for the supercavitation torpedo comprises a ventilation bowl and a gas nozzle, the assembly airtightness requirement is high, the manufacturing difficulty is high, and the controllability of gas introduced into the supercavitation is poor and uneven.
[ summary of the invention ]
The invention aims to overcome the defects of the prior art and provide a supercavitation torpedo. The torpedo adopts a gas turbine engine, a motor drive control steering engine device, and gas nozzles and other devices which are uniformly distributed along the inner circumference of the wall of the ventilating bowl, so that the torpedo is more stable in running, and the advancing speed of the torpedo is improved.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
a supercavitation torpedo, comprising: the rear end of the front cabin section is fixedly connected with the front end of the rear cabin section; a steering engine device is arranged at the joint of the front cabin section and the rear cabin section;
the steering engine device comprises a control mechanism, wherein a left rudder and a right rudder are fixedly connected to two ends of the control mechanism respectively, the left rudder penetrates through the upper end of the joint of the front cabin section and the rear cabin section, and the right rudder penetrates through the lower end of the joint of the front cabin section and the rear cabin section; the control mechanism is fixed on the base, and the base is fixed inside the supercavitation torpedo;
the front cabin section comprises a cartridge cabin and a first space, the cartridge cabin and the first space are separated by a rear side wall of the cartridge cabin, and the outer side walls of the cartridge cabin and the first space are integrated; a front section of the air channel is arranged between the common outer side wall of the ammunition cabin and the first space and the inner wall of the front cabin section, and the front section of the air channel is a gap-shaped space; the front end of the outer side of the front cabin section is fixedly provided with a ventilation bowl;
a second space is arranged in the rear cabin section, an air duct rear section is arranged between the outer wall of the second space and the inner wall of the rear cabin section, and the air duct rear section is a gap-shaped space; the rear section of the air duct is communicated with the front section of the air duct; a compressed gas storage tank and a gas turbine engine which are communicated are arranged in the second space from front to back, and the rear end of the gas turbine engine is communicated with the rear section of the air duct; a speed reducer is fixedly arranged at the rear end of the outer side of the rear cabin section, and a propeller is fixedly arranged at the rear end of the outer side of the supercavitation torpedo; the gas turbine engine, the speed reducer and the propeller are linked through the connecting rod.
The invention is further improved in that:
preferably, the front cabin section is provided with a tail gas gathering cabin at the front end of the outer side of the ammunition cabin, the front end of the tail gas gathering cabin is provided with a vent, and the vent is communicated with the vent bowl; the rear end of the tail gas gathering cabin is communicated with the front section of the air duct; the first space is fixedly provided with a control system and a battery system on the rear side wall of the cartridge chamber.
Preferably, the ventilation bowl is provided with a large end face and a small end face which are opposite, and the large end face faces the front cabin section; the center of the ventilating bowl is provided with an air channel vertical to the large end surface; a plurality of gas nozzles are evenly distributed on the large end surface of the ventilation bowl along the circumferential direction, and the gas nozzles are communicated with the gas channel in the ventilation bowl; the outer side of the gas channel is communicated with the vent; a cavitator is fixedly arranged at the front end of the ventilation bowl; the ventilation bowl is made by 3D printing.
Preferably, the gas turbine engine is provided with an engine shell, and a combustion chamber, a Wall nozzle and an exhaust passage are sequentially arranged in the engine shell from front to back; the front end of the Laval nozzle is communicated with the combustion chamber, the rear end of the Laval nozzle is communicated with the exhaust passage, and a turbine guider and a turbine are arranged at the communication position of the Laval nozzle and the exhaust passage; the rear end of the exhaust passage is communicated with the rear section of the air passage.
Preferably, the rear end of the compressed gas storage tank is provided with a gas channel communicated to the combustion chamber; a gas speed regulating valve is fixedly arranged on the rear end face of the compressed gas storage tank, an annular fuel tank is fixedly arranged around the gas speed regulating valve, and a fuel flow speed regulating valve is fixedly arranged on the annular fuel tank; compressed oxygen is filled in the compressed gas storage tank, and fuel oil is filled in the annular fuel tank.
Preferably, the control mechanism comprises a driving part and a reversing part, wherein the driving part comprises a first base and a reversing gear fixing seat which are both fixed on the base; a motor is fixedly arranged outside one end of the first base, the motor drives the first screw rod to rotate through a first coupler, and two ends of the first screw rod are erected on two ends of the first base; a screw rod nut is arranged on the first screw rod and can do linear motion relative to the first base; the left end and the right end of the feed screw nut are respectively provided with a left rack and a right rack; the reversing gear fixing seat is provided with a reversing gear which can rotate relative to the reversing gear fixing seat; and a right steering gear is fixedly arranged on the right rudder, and the reversing gear is meshed with the right steering gear and the right rack.
Preferably, the lower end of the feed screw nut is fixedly arranged on a first sliding block, a first guide rail is fixedly arranged on a first base, and the first sliding block is in sliding fit with the first guide rail.
Preferably, the reversing part comprises a second base fixed on the base, a synchronous counter-rotating motor is fixedly arranged outside one end of the second base, and the synchronous counter-rotating motor drives the second screw rod to rotate on the second base through a second coupler; the second screw rod is provided with a deflector rod which can do linear motion on the second base; the upper end suit of driving lever is in the outside of driving pin, and the one end suit of driving pin is equipped with the gear moving piece, and the gear moving piece internal fixation is provided with left rudder gear, and left rudder gear's inside and left rudder's one end are connected, and left rudder gear can be along the axial displacement of left rudder, and then with left rack toothing.
Preferably, the transmission pin is provided with a left square pin, a first annular groove, a second annular groove and a right square pin from one side to the other side, and the diameters of the cross sections of the first annular groove and the second annular groove are different; the square round pin in left side can insert to the first square inslot of left rudder, and the tip suit of gear moving member is on first ring channel, and the driving lever suit is on the second ring channel, and the square round pin in right side can insert to the second square inslot of right rudder.
Preferably, the lower end of the shifting lever is fixedly connected with a second sliding block, a second guide rail is fixedly arranged on the second base along the length direction, and the second sliding block is in sliding fit with the second guide rail.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a supercavitation torpedo, wherein a gas turbine engine, a steering engine device and a gas channel capable of transmitting high-temperature gas generated by the engine to a front cabin section are arranged in the torpedo. Compared with a piston machine, the structure of the gas turbine is simpler, and the gas turbine has the advantages of high power, low noise, low air consumption, large enthalpy drop, long-time operation and high reliability. The gas turbine is used as power, high-speed movement and ultra-long stroke of the heavy thermal power torpedo can be realized, and large-scale speed change or depth change of the torpedo can be realized. Meanwhile, the gas turbine has mature technology, is easy to start and has high safety and reliability. The gas required by combustion of the gas turbine engine in the power system is provided by a compressed gas storage tank, so that a pressure gas wheel and a diffuser are omitted; the combustion chamber is used for continuously feeding air and combusting, the working process is stable, no reciprocating part exists, no inertia force is generated, the vibration and impact of the whole machine are small, the noise is reduced, and the concealment is improved; the gas for generating supercavity is provided by the combustion tail gas of the engine, and an additional gas generating device is not needed.
Furthermore, a tail gas gathering cabin is arranged in the front cabin section, tail gas generated by an engine is gathered and then discharged through a ventilation bowl at the front end, and gas nozzles are uniformly distributed on the ventilation bowl, so that supercavitation formed outside the supercavitation torpedo is surrounded by more uniform and stable gas, supercavitation formed outside the supercavitation torpedo is more uniform and stable, resistance of the torpedo in advancing is greatly reduced, and advancing speed and range of the torpedo are improved.
Furthermore, the ventilating bowl manufactured by the 3D printing technology and the ventilating nozzle on the ventilating bowl are adopted, the structure of the ventilating bowl manufactured by the 3D printing technology is simplified compared with that of a traditional ventilating device, the ventilating bowl is easy to process, the assembling tightness of the ventilating device does not need to be considered, the sprayed gas is more continuous, uniform and stable along the circumferential direction of the outer side of the cabin body, the opening angle of the air hole in the ventilating bowl can be adjusted, the direction of the sprayed gas bubbles is controlled, and the spraying direction can change along with the taper of the front end cone of the front cabin section.
Furthermore, the steering engine device is driven and controlled by the motor, so that the steering engine device is simple to operate, small in size, light in weight and easy to realize, and the steering engine device adopts a screw rod sliding table driving mode to ensure that the rudder can be stably self-locked in the driving process, so that errors caused by the fact that the rudder is stressed and shaken are reduced.
[ description of the drawings ]
FIG. 1 is a general cross-sectional view of a supercavitation vehicle of the present invention;
FIG. 2 is a cross-sectional view of a forward bay section of a supercavitation of the present invention;
FIG. 3 is an enlarged external view of portion I of FIG. 2 according to the present invention;
FIG. 4 is a cross-sectional view of the vent bowl of the present invention;
FIG. 5 is a sectional view of the aft bay section of the supercavitation of the present invention;
FIG. 6 is a side view of the steering engine assembly of the present invention;
FIG. 7 is another side view of the steering engine assembly of the present invention;
FIG. 8 is a detail view of the drive pin of the present invention;
FIG. 9 is a cross-sectional view of the drive pin feature of the present invention;
FIG. 10 is an assembly view of the drive pin and gear shift of the present invention;
FIG. 11 is a diagram of a reversing device of the present invention;
wherein: 1 is a cavitator; 2, a ventilating bowl; 3 is a gas nozzle; 4 is a tail gas gathering cabin; 5 is an ammunition cabin; 6-1 is the front section of the air duct; 6-2 is the rear section of the air duct; 7 is a front cabin section; 8 is a control system; 9 is a battery system; 10 is a steering engine device; 11 is a rear cabin section; 12 is a compressed gas storage tank; 13 is an annular fuel tank; 14 is a gas speed regulating valve; 15 is a fuel flow rate regulating valve; 16 is an engine housing; 17 is a combustion chamber, and 18 is a Laval nozzle; 19 is an exhaust passage; 20 is a reducer; 21 is a propeller; 22 is a turbine guide; 23 is a turbine; 24-a first space; 25-a second space; 26-a connecting rod;
10-1 is a motor; 10-2 is a first base; 10-3 is a first coupling; 10-4 is a right rack; 10-5 is a screw nut; 10-6 is a first screw rod; 10-7 is a left rack; 10-8 is a left rudder gear; 10-9 is a left rudder; 10-10 is a right rudder; 10-11 is a reversing gear fixing seat; 10-12 are reversing gears; 10-13 is a right steering engine gear; 10-14 is a first slide block; 10-15 is a first guide rail; 10-16 is a second screw rod; 10-17 is a second guide rail; 10-18 is a second slide block; 10-19 is a deflector rod; 10-20 is a second base; 10-21 are second couplings; 10-22 are synchronous counter-rotating motors; 10-23 are driving pins; 10-23-1 is a first annular groove; 10-23-2 is a second annular groove; 10-23-3 is a left square pin; 10-23-4 is a right shaped pin; 10-24 are gear moving parts; 10-24-1 is a gear fixing groove; 10-25 are first square grooves; 10-26 are second square grooves; 10-27 are control mechanisms.
[ detailed description ] embodiments
The invention is described in further detail below with reference to the accompanying drawings:
referring to fig. 1, the cabin body comprises a front cabin section 7 and a rear cabin section 11, the front cabin section and the rear cabin section are fixedly connected to form the whole cabin body, a steering engine device 10 is arranged between the front cabin section 7 and the rear cabin section 11, a rudder is arranged at the rear end of the front cabin section 7, an air ventilation bowl 2 is sleeved at the front end of a head conical section of the front cabin section 7, and a cavitator 1 is arranged at the front end of the air ventilation bowl 2. A tail gas gathering cabin 4, a front air channel section 6-1, an ammunition cabin 5, a control system 8, a battery system 9, a steering engine device 10, a compressed gas storage tank 12, an annular fuel tank 13, a gas speed regulating valve 14, a fuel oil flow speed regulating valve 15, an engine shell 16 combustion chamber 17, a laval nozzle 18, a turbine guider 22, a turbine 23, an exhaust passage 19, a rear air channel end 6-2, a speed reducer 20 and a propeller 21 are sequentially arranged in the cabin body from a front cabin section 7 to a rear cabin section 11 along the axial direction;
referring to fig. 2, the head of the front cabin section 7 is a cone with a forward-reduced cross section, and the front end of the head cone section of the front cabin section 7 is fixedly connected with the ventilation bowl 2; referring to fig. 3 and 4, the ventilation bowl 2 is provided with 18 gas nozzles 3 uniformly distributed along the circumferential direction, the inside of the ventilation bowl is provided with a gas channel 2-1, and the gas channel 2-1 is communicated with the gas channel at the foremost end of the head of the front cabin section 7; the gas nozzle 3 is communicated with the gas channel 2-1 in the ventilating bowl 2; this gas nozzle 3 is along being on a parallel with head cone cabin body direction towards the torpedo afterbody, whole air vent bowl 2 is through the preparation of 3D printing technique, the leakproofness is good, the formability is good, gas nozzle 3 is adjustable in the trend of air vent bowl 2 inside simultaneously, angle between the axial through adjusting gas nozzle 3 and the big terminal surface of air vent bowl 2, the direction of 3 spun gas of gas nozzle can be adjusted, guarantee the lateral wall of spun bubble along preceding cabin section, 2 front end fixed mounting at air vent bowl have a cavitator 1, along with liquid relative flow speed increases, according to Bernoulli's equation, the vaporization phenomenon just can appear naturally in cavitator 1 marginal also liquid. The interior of the front cabin section 7 is sequentially separated into an exhaust gas gathering cabin 4, a cartridge cabin 5 and a first space 24 from front to back; the first space 24 is between the rear side wall of the cartridge bay 5 and the steering engine arrangement 10; a control system 8 and a battery system 9 are fixedly arranged outside the rear side wall of the ammunition cabin 5, the control system 8 and the battery system 9 are arranged in the first space 24, and the control system 8 realizes automatic control; the outer side wall of the cartridge chamber 5 and the outer side wall of the first space 24 are integrated and are separated by the rear side wall of the cartridge chamber 5, and an air duct front section 6-1 is arranged between the outer side wall of the cartridge chamber 5 and the outer side wall of the first space 24 and the bulkhead of the front chamber section 7; the front section 6-1 of the air duct is communicated with the rear section 6-2 of the air duct; the cartridge chamber 5 is filled with the required explosive for the attack.
Referring to fig. 5, a second space 25 is provided in the rear cabin section 11, an outer wall of the second space 25 is arranged around the rear cabin section 11, and an air duct rear end is provided between the outer wall of the second space 25 and the inner wall of the rear cabin section 11; the second space 25 is internally provided with a whole power system of the supercavitation torpedo from front to back, wherein the whole power system of the supercavitation torpedo consists of a compressed gas storage tank 12, an annular fuel tank 13, a gas speed regulating valve 14, a fuel flow speed regulating valve 15, an engine shell 16, a combustion chamber 17, a Laval nozzle 18, a turbine guider 22, a turbine 23, an exhaust passage 19, a vent passage rear section 6-2, a speed reducer 20 and a propeller 21. The gas turbine engine is composed of an engine casing 16, a combustor 17, a laval nozzle 18, a turbine nozzle 22, a turbine 23, and an exhaust passage 19. The rear end of the compressed gas storage tank 12 is provided with a gas channel communicated to the combustion chamber 17; a gas speed regulating valve 14 is fixedly arranged on the rear end face of the compressed gas storage tank 12, and an annular fuel tank 13 is fixedly arranged around the gas speed regulating valve 14; an engine is arranged at the rear side of the compressed gas storage tank 12, and a combustion chamber 17 and a Laval nozzle 18 exhaust passage 19 are arranged in an engine shell 16; the front end of the Laval nozzle 18 is communicated with the combustion chamber 17, the rear end of the Laval nozzle 18 is communicated with the exhaust passage 19, the shells of the Laval nozzle and the exhaust passage are communicated into a whole, and a turbine guider 22 and a turbine 23 are arranged in the communicated part of the Laval nozzle and the exhaust passage; the rear end of the exhaust passage 19 is communicated with the rear section 6-2 of the air passage, the rear end of the rear cabin section 11 is fixedly provided with a speed reducer 20, the rear end of the supercavitation torpedo is provided with a propeller 21, and a space is reserved between the propeller 21 and the speed reducer 20; from back to front, the propeller 21, the speed reducer 20 and the combustion chamber 17 are fixedly connected and linked through a connecting rod 26; the connecting rod 26 passes through the laval nozzle 18 and the exhaust duct 19. The compressed gas storage tank 12 is filled with compressed oxygen, and the annular fuel tank 13 is filled with fuel oil.
The working principle of forward movement of the torpedo is as follows:
when the torpedo car is in operation, compressed oxygen in a compressed gas storage tank 12 is filled with compressed oxygen with a fixed quantity and a fixed pressure into a combustion chamber 17 according to the working condition under the control of a gas speed regulating valve 14, an annular fuel tank 13 is filled with proper fuel oil into the combustion chamber 17 according to the working condition under the control of a fuel oil flow speed regulating valve 15, the fuel oil and the oxygen are combusted in the combustion chamber 17 to generate high-temperature and high-pressure gas, the high-temperature and high-pressure gas is further accelerated to obtain supersonic high-temperature gas when flowing through a Laval nozzle 18, the supersonic gas drives a turbine 23 to rotate at a high speed under the guidance of a turbine guider 22, the high-speed rotation motion generated by the high-speed rotating turbine 23 is decelerated by a decelerator 20 to drive a propeller 21 to rotate to generate advancing power, and in the advancing process of the torpedo car, the steering engine device 10 realizes the automatic synchronization of, The asynchronous rotation realizes the control of the advancing track of the torpedo, avoids interception and realizes the directional tracking of the target.
High-temperature tail gas generated after working flows into the rear section 6-2 of the air duct and the front section 6-1 of the air duct in sequence through the exhaust duct 19, and after the tail gas reaches the tail gas gathering cabin 4 and is gathered stably, the air bowl 2 is provided with 18 gas nozzles 3 which are uniformly distributed along the circumferential direction and are sprayed out, so that the supercavity formed outside the supercavity torpedo is surrounded by gas continuously, uniformly and stably, the resistance of the torpedo in advancing is reduced, the speed and the range of the torpedo in advancing is greatly increased, and the supercavity torpedo is formed.
The high-temperature tail gas discharged by the exhaust passage 19 flows to the tail gas gathering cabin 4 from the rear section 6-2 of the air passage and the rear section 6-2 of the air passage which are tightly attached to the inner side of the outer wall of the cabin body, the high-temperature tail gas is directly contacted with the inner side of the outer wall of the rear cabin section 11 in the flowing process of the rear section 6-2 of the air passage to heat the outer side of the outer wall of the rear cabin section 11 to high temperature, the outer side of the outer wall of the rear cabin section 11 in high-speed motion is contacted with liquid in which torpedo motion is positioned, shearing force, pressure, inertia force and heat are transferred to the liquid to effectively atomize the liquid, so that a plurality of small bubbles are formed on the outer side of the outer wall of the rear cabin section 11, the formation of supercavity is facilitated, meanwhile, the high-temperature tail gas is cooled in the rear section 6-2 of the air passage of the rear cabin section.
Referring to fig. 6 and 7, the steering engine device 10 includes control mechanisms 10 to 27, and the control mechanisms 10 to 27 include a driving portion and a reversing portion. The driving part comprises a motor 10-1, a first base 10-2, a first coupler 10-3, a right rack 10-4, a screw rod nut 10-5, a first screw rod 10-6, a left rack 10-7, a right rudder 10-10, a reversing gear fixing seat 10-11, a reversing gear 10-12, a right steering gear 10-13, a sliding block 10-14 and a guide rail 10-15; the first base 10-2 and the reversing gear fixing seat 10-11 are both fixedly arranged on a base, and the base is fixedly arranged in the cabin body; the motor 10-1 is arranged on the first base 10-2, the first lead screw 10-6 is driven to rotate on the first base 10-2 through the first coupler 10-3, the lead screw nut 10-5 is arranged on the first lead screw 10-6, and the first lead screw 10-6 rotates to drive the lead screw nut 10-5 to do linear motion; the lower part of a screw nut 10-5 is arranged on a first slide block 10-14 of a first screw slide block consisting of a first slide block 10-14 and a first guide rail 10-15, the first guide rail 10-15 is fixed on a first base 10-2, the left end and the right end of the screw nut 10-5 are respectively provided with a left rack 10-7 and a right rack 10-4, a reversing gear 10-12 is arranged on a reversing gear fixing seat 10-11, the right rack 10-4 is meshed with a reversing gear 10-12, and the reversing gear 10-12 is meshed with a right steering gear 10-13 arranged on a right rudder 10-10.
The reversing part comprises synchronous counter-rotating motors 10-22, a second base 10-20, a second coupling 10-21, a shifting lever 10-19, a second sliding block 10-18, a second guide rail 10-17, a second screw rod 10-16, a shifting lever 10-19, a gear moving part 10-24, a transmission pin 10-23, a left rudder gear 10-8 and a left rudder 10-9; the second base 10-20 is fixedly arranged on a base inside the cabin body, the synchronous counter-rotating motor 10-22 is arranged on the second base 10-20, the second screw rod 10-16 is driven to rotate on the base 10-20 through the second coupling 10-21, the deflector rod 10-19 is arranged on the second screw rod 10-16, the deflector rod 10-19 can be driven to do linear motion by the rotation of the second screw rod 10-16, the second slider 10-18 of the screw rod slider consisting of the second slider 10-18 and the second guide rail 10-17 is arranged at the lower part of the deflector rod 10-19, and the second guide rail 10-17 is fixed on the base 10-20;
referring to fig. 8 and 9, the driving pin 23 is a left square pin, a first annular groove 10-23-1, a second annular groove 10-23-2 and a right square pin 10-23-4 sequentially from left to right;
referring to fig. 10 and 11, the driving pin 10-23 is sleeved on the driving lever 10-19 through the second annular groove 10-23-2 on the driving pin; the end part of the gear moving piece 10-24 is sleeved on a first annular groove 10-23-1 on the transmission pin 10-23, a left rudder gear 10-8 is installed in a gear fixing groove 10-24-1 on the gear moving piece, meanwhile, the left rudder gear 10-8 is installed on a left rudder 10-9 and can move on a shaft on the left rudder 10-9 under the driving of the gear moving piece 10-24 to realize the engagement and disengagement with a left rack 10-7, a left square pin 10-23-3 can be inserted into a first annular groove 10-25 in a left rudder 19, and the left square pin 10-23-3 can realize the insertion and disengagement with the first annular groove 10-25 on the left rudder 10-9 under the movement of a deflector rod 10-19; the right square pin 10-23-4 can be inserted into a second square groove 10-26 arranged at the end part of the right rudder 10-10; the right square pin 10-23-4 can be inserted into and separated from the second square groove 10-26 on the right rudder 10-10 under the movement of the deflector rod 10-19;
synchronous rotation in different directions: the synchronous counter-rotating motor 10-22 drives the screw rod 10-16 to rotate through the coupler 10-21 to drive the shift lever 10-19 to move rightwards on a slide block guide rail formed by the guide rail 10-17 and the slide block 10-18, drives the transmission pin 10-23 to move rightwards to enable the left square pin 10-23-3 on the transmission pin to be separated from the first square groove 10-25 on the left rudder, but the right square pin 10-23-4 is still not separated from the second square groove 10-26 of the right rudder 10-10 and has enough length, the transmission pin 10-23 drives the gear moving piece 10-24 to drive the left rudder gear 10-8 to move to the rightmost end of the left rudder 10-9 to be meshed with the left rack 10-7, and at the moment, the left rack 10-7 and the right rack 10-4 which are arranged on the screw rod nut 10-5 are driven by the motor 10-1, the left rudder gear 10-8 and the right rudder gear 10-13 are driven to synchronously rotate in different directions by translating back and forth under the guidance of a slide block guide rail formed by a slide block 10-14 and a guide rail 10-15, so that the left rudder gear and the right rudder gear synchronously rotate in different directions, and the synchronous rotation in different directions of the left rudder and the right rudder is realized.
Synchronous equidirectional rotation: the synchronous counter-rotating motor 10-22 drives the screw rod 10-16 to rotate through the coupler 10-21 to drive the deflector rod 10-19 to move leftwards on a slide block guide rail formed by the slide block 10-17 and the guide rail 10-18, drives the transmission pin 10-23 to move leftwards so that the left square pin 10-23-3 on the transmission pin enters the first square groove 10-25 on the left rudder, the transmission pin 10-23 drives the gear moving piece 10-24 to drive the left rudder gear 10-8 to move leftwards and is disengaged from the left rack 10-7, at the moment, the right rack 10-4 arranged on the screw rod nut 10-5 is driven by the motor 10-1 to translate forwards and backwards under the guidance of a slide block guide rail formed by the slide block 10-14 and the guide rail 10-15, so as to drive the reversing gear 10-12 to drive the right rudder gear 10-13 to rotate and drive the right rudder gear 10-10 to rotate And the right rudder 10-10 drives the left rudder 10-9 to synchronously rotate through a transmission pin 10-23.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
1. A supercavitation torpedo, comprising: the rear cabin section (7) is fixedly connected with the front end of the rear cabin section (11); a steering engine device (10) is arranged at the joint of the front cabin section (7) and the rear cabin section (11);
the steering engine device (10) comprises a control mechanism (10-27), two ends of the control mechanism (10-27) are fixedly connected with a left rudder (10-9) and a right rudder (10-10) respectively, the left rudder (10-9) penetrates out of the upper end of the joint of the front cabin section (7) and the rear cabin section (11) and the right rudder (10-10) penetrates out of the super-cavity torpedo from the lower end of the joint of the front cabin section (7) and the rear cabin section (11); the control mechanisms (10-27) are fixed on the base, and the base is fixed inside the supercavitation torpedo;
the front cabin section (7) internally comprises a cartridge chamber (5) and a first space (24), the cartridge chamber (5) and the first space (24) are separated by the rear side wall of the cartridge chamber (5), and the outer side walls of the cartridge chamber (5) and the first space are integrated; an air duct front section (6-1) is arranged between the common outer side wall of the ammunition cabin (5) and the first space (24) and the inner wall of the front cabin section (7), and the air duct front section (6-1) is a gap-shaped space; the front end of the outer side of the front cabin section (7) is fixedly provided with a ventilation bowl (2);
a second space (25) is arranged in the rear cabin section (11), an air duct rear section (6-2) is arranged between the outer wall of the second space (25) and the inner wall of the rear cabin section (11), and the air duct rear section (6-2) is a gap-shaped space; the rear section (6-2) of the air duct is communicated with the front section (6-1) of the air duct; a compressed gas storage tank (12) and a gas turbine engine which are communicated are arranged in the second space (25) from front to back, and the rear end of the gas turbine engine is communicated with the rear section (6-2) of the air duct; a speed reducer (20) is fixedly arranged at the rear end of the outer side of the rear cabin section (11), and a propeller (21) is fixedly arranged at the rear end of the outer side of the supercavitation torpedo; the gas turbine engine, the speed reducer (20) and the propeller (21) are linked through a connecting rod (26);
the front end of the outer side of the ammunition cabin (5) of the front cabin section (7) is provided with a tail gas gathering cabin (4), the front end of the tail gas gathering cabin (4) is provided with a vent hole (27), and the vent hole (27) is communicated with the vent bowl (2); the rear end of the tail gas gathering cabin (4) is communicated with the front section (6-1) of the air duct; the first space (24) is fixedly provided with a control system (8) and a battery system (9) on the rear side wall of the ammunition cabin (5);
the ventilation bowl (2) is provided with a large end face and a small end face which are opposite, and the large end face faces the front cabin section (7); a gas channel (2-1) vertical to the large end surface is arranged at the center of the ventilating bowl (2); a plurality of gas nozzles (3) are uniformly distributed on the large end surface of the ventilating bowl (2) along the circumferential direction, and the gas nozzles (3) and the gas channel (2-1) are communicated in the ventilating bowl (2); the outer side of the gas channel (2-1) is communicated with the vent (27); a cavitator (1) is fixedly arranged at the front end of the ventilation bowl (2); the ventilation bowl (2) is made through 3D printing.
2. The supercavitation torpedo of claim 1, wherein the gas turbine engine is provided with an engine casing (16), and a combustion chamber (17), a laval nozzle (18) and an exhaust passage (19) are arranged in the engine casing (16) from front to back; the front end of the Laval nozzle (18) is communicated with the combustion chamber (17), the rear end of the Laval nozzle (18) is communicated with the exhaust passage (19), and a turbine guider (22) and a turbine (23) are arranged at the communication position of the Laval nozzle (18) and the exhaust passage (19); the rear end of the exhaust passage (19) is communicated with the rear section (6-2) of the air passage.
3. The supercavitation torpedo of claim 2, wherein a gas passage is opened at the rear end of the compressed gas storage tank (12) to communicate with the combustion chamber (17); a gas speed regulating valve (14) is fixedly arranged on the rear end face of the compressed gas storage tank (12), an annular fuel tank (13) is fixedly arranged around the gas speed regulating valve (14), and a fuel flow speed regulating valve (15) is fixedly arranged on the annular fuel tank (13); compressed oxygen is filled in the compressed gas storage tank (12), and fuel oil is filled in the annular fuel tank (13).
4. A supercavitation torpedo according to any of claims 1 to 3, characterised in that the control means (10-27) comprises a driving portion and a reversing portion, the driving portion comprising a first base (10-2) and a reversing gear holder (10-11) both fixed to the base; a motor (10-1) is fixedly arranged outside one end of the first base (10-2), the motor (10-1) drives the first screw rod (10-6) to rotate through a first coupler (10-3), and two ends of the first screw rod (10-6) are erected on two ends of the first base (10-2); a screw rod nut (10-5) is arranged on the first screw rod (10-6), and the screw rod nut (10-5) can do linear motion relative to the first base (10-2); the left end and the right end of the feed screw nut (10-5) are respectively provided with a left rack (10-7) and a right rack (10-4); a reversing gear (10-12) is arranged on the reversing gear fixing seat (10-11), and the reversing gear (10-12) can rotate relative to the reversing gear fixing seat (10-11); a right steering gear (10-13) is fixedly arranged on the right rudder (10-10), and the reversing gears (10-12) are all meshed with the right steering gear (10-13) and the right rack (10-4).
5. A supercavitation torpedo according to claim 4, characterized in that the lower end of the feed screw nut (10-5) is fixedly arranged on a first slide block (10-14), a first guide rail (10-15) is fixedly arranged on the first base (10-2), and the first slide block (10-14) and the first guide rail (10-15) are in sliding fit.
6. The supercavitation torpedo according to claim 5, wherein the reversing part comprises a second base (10-20) fixed on the base, a synchronous counter-rotating motor (10-22) is fixedly arranged outside one end of the second base (10-20), and the synchronous counter-rotating motor (10-22) drives a second screw rod (10-16) to rotate on the second base (10-20) through a second coupling (10-21); the second screw rod (10-16) is provided with a deflector rod (10-19), and the deflector rod (10-19) can do linear motion on the second base (10-20); the upper end of a deflector rod (10-19) is sleeved outside a transmission pin (10-23), one end of the transmission pin (10-23) is sleeved with a gear moving piece (10-24), a left rudder gear (10-8) is fixedly arranged in the gear moving piece (10-24), the inside of the left rudder gear (10-8) is connected with one end of a left rudder (10-9), and the left rudder gear (10-8) can move along the axial direction of the left rudder (10-9) and is further meshed with a left rack (10-7).
7. The supercavitation torpedo according to claim 6, characterized in that the driving pin (10-23) is provided with a left square pin (10-23-3), a first annular groove (10-23-1), a second annular groove (10-23-2) and a right square pin (10-23-4) from one side to the other, the first annular groove (10-23-1) and the second annular groove (10-23-2) having different cross-sectional diameters; the left square pin (10-23-3) can be inserted into a first square groove (10-25) of the left rudder (10-9), the end part of the gear moving piece (10-24) is sleeved on the first annular groove (10-23-1), the deflector rod (10-19) is sleeved on a second annular groove (10-23-2), and the right square pin (10-23-4) can be inserted into a second square groove (10-26) of the right rudder (10-10).
8. The supercavitation torpedo of claim 6, wherein the lower end of the deflector rod (10-19) is fixedly connected with a second sliding block (10-18), a second guide rail (10-17) is fixedly arranged on the second base (10-20) along the length direction, and the second sliding block (10-18) is in sliding fit with the second guide rail (10-17).
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| CN110143254B (en) * | 2019-05-15 | 2021-09-21 | 南京理工大学 | Supercavitation generation device |
| CN110758695B (en) * | 2019-11-27 | 2020-09-18 | 中国人民解放军国防科技大学 | Self-adaptive continuously adjustable cavitator structure |
| CN111028649B (en) * | 2019-12-27 | 2021-09-10 | 哈尔滨工程大学 | Head is given vent to anger and is moved experimental model at high speed under water |
| CN112224367A (en) * | 2020-09-25 | 2021-01-15 | 广东石油化工学院 | Winged extruded water bag type intelligent underwater unmanned aircraft |
| CN112729852B (en) * | 2020-12-22 | 2023-08-04 | 西安精密机械研究所 | Combined test device and test method for power combustion subsystem of three-component turbine |
| CN112781448A (en) * | 2020-12-29 | 2021-05-11 | 哈尔滨工程大学 | Anti-submarine missile based on water inlet buffer device and control method |
| CN113091531B (en) * | 2021-03-03 | 2023-03-17 | 上海机电工程研究所 | Supercavitation navigation carrier |
| CN113882965B (en) * | 2021-09-29 | 2023-12-29 | 中国人民解放军战略支援部队航天工程大学 | Metal hydrogen storage powder water ramjet engine |
| CN115180061B (en) * | 2022-06-24 | 2023-05-16 | 哈尔滨工程大学 | High Wen Konghua device, supercavitation navigation body comprising high Wen Konghua device and method |
| CN115195979A (en) * | 2022-07-21 | 2022-10-18 | 江苏科技大学 | Modularized magnetic coupling electric pod propeller |
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| US6962121B1 (en) * | 2004-07-30 | 2005-11-08 | The United States Of America As Represented By The Secretary Of The Navy | Boiling heat transfer torpedo |
| CN100383014C (en) * | 2006-04-28 | 2008-04-23 | 上海大学 | Super cavitation method and device with introduced hot steam for underwater high speed navigating equipment |
| KR20120065454A (en) * | 2010-05-24 | 2012-06-21 | 박효상 | Air lubrication submarine |
| CN103926051B (en) * | 2014-05-06 | 2016-07-06 | 中国船舶重工集团公司第七○二研究所 | Supercavitating vehicle model with built-in helm gear |
| CN207611540U (en) * | 2017-07-24 | 2018-07-13 | 杭州中天模型有限公司 | It is electronic from boat torpedo model component and its electronic from boat torpedo model |
| CN107543462B (en) * | 2017-08-14 | 2019-06-28 | 江苏大学 | A kind of supercavitating vehicle |
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