Disclosure of Invention
The invention aims to provide a method for launching and quickly turning a guided vehicle, which is a fully generalized guided vehicle launching and turning method and can meet the working conditions of most modern roadbeds, surface ships, underwater submarines and other different vehicles for launching the guided vehicle in a plurality of modes of vertical or inclined.
A method for launching and fast turning a guided vehicle, which is characterized in that a booster engine device 13 is connected with the tail of the guided vehicle 1 in a sealing way by explosion bolts,
Firstly, installing a turning attitude control device 14 at the front end of a guided vehicle 1, wherein the end head of the guided vehicle 1 is inserted into the inner space of the turning attitude control device 14, so that the annular lower end part of the turning attitude control device 14 and the outer wall of the upper part of the guided vehicle 1 are sealed and installed together by explosion screws, wherein the turning attitude control device 14 at least comprises a pair of separation engines 23, and the air nozzles of the separation engines 23 are installed on the inner wall of the turning attitude control device 14 and can jet air to the right rear of the movement direction of the guided vehicle 1;
The specific emission process comprises the following steps:
During launching, the gunpowder accumulator 12 at the bottom of the transport launching cylinder 2 starts to work, the gunpowder accumulator 12 generates high-pressure fuel gas in the space at the bottom of the transport launching cylinder 2, the high-pressure fuel gas acts on the bottom of the guide aircraft 1, and the guide aircraft 1 starts to move in the transport launching cylinder 2;
Step three, after the guided vehicle 1 moves in the transport launching tube 2, according to different launching modes, the control system of the guided vehicle 1 decides the time for starting the low thrust mode of the boosting engine device 13;
Step four, when the guided vehicle 1 reaches the set height, the control system of the guided vehicle 1 decides to start or not to start the turning function of the turning attitude control device 14 according to different emission modes, and the turning attitude control device 14 performs the action of attitude control according to the direction specified by the flight task until the rapid large-angle turning is completed or the turning attitude control device 14 keeps not to act;
Step five, after the guided vehicle 1 is adjusted to the direction specified by the flight mission, the separation engine 23 in the turning attitude control device 14 is started, and the separation engine 23 outputs impulse along the movement direction of the guided vehicle 1, so that the turning attitude control device 14 is separated from the guided vehicle 1 and is thrown forward and downward to the subsequent flight trajectory;
and step six, immediately starting a large thrust mode of the boosting engine device 13 after the turning attitude control device 14 is separated, rapidly accelerating the guided vehicle 1 to continue flying along a program trajectory, and detonating an explosion bolt connected with the boosting engine device 13 by the guided vehicle 1 after the guided vehicle 1 is accelerated to a speed capable of starting the ramjet engine, wherein the boosting engine device 13 is thrown off, then starting the ramjet engine, and pushing the guided vehicle to complete cruising flying along a preset track.
When the guided vehicle 1 vertically launches from the underwater submarine, the second step is to open the launching cabin cover before the guided vehicle 1 starts to move in the launching tube, the third step is to start the boosting engine device 13 to work in a small thrust mode after the tail of the guided vehicle 1 passes through the launching tube opening, meanwhile, the guided vehicle 1 rapidly opens the air rudder and the missile wing, and then the fourth step is to enter, and when the guided vehicle 1 reaches the set height, the set height is above the water surface.
When the guided vehicle 1 is launched at a small horizontal angle of a water surface ship, namely 10-30 degrees, in the third step, after the guided vehicle 1 moves in the transport launching cylinder 2, the booster engine device 13 is started to work in a small thrust mode, the turning function of the turning attitude control device 14 is not started in the fourth step, the guided vehicle directly enters the fifth step, after the guided vehicle 1 is regulated to a direction regulated by a flight mission, the guided vehicle is regulated to the direction regulated by the flight mission to implement target course turning through the ship and a cylinder projectile rigidly connected to the guided vehicle, or the rotary launching device provided with the cylinder projectile turns the target, the separation engine 23 in the turning attitude control device 14 is started in the process of moving the guided vehicle in the launching cylinder, and after the booster engine device 13 is started in a large thrust mode in the sixth step, the guided vehicle synchronously opens an air rudder and a missile wing so as to ensure the stable movement of the guided vehicle on a subsequent trajectory.
When the guided vehicle 1 vertically launches on land or on water, in the third step, after the guided vehicle 1 moves in the transport launching tube 2, the booster engine device 13 is started to work in a small thrust mode immediately, and in the fourth step, the turning attitude control device 14 performs the action of attitude control until the rapid large-angle turning is completed, the guided vehicle 1 opens an air rudder and a missile wing to ensure that the guided vehicle 1 receives small aerodynamic resistance in the rapid large-angle turning process.
When the guided vehicle 1 is launched at a larger horizontal angle of the water surface ship, namely 30-45 degrees, in the third step, after the guided vehicle 1 moves in the transport launching cylinder 2, the booster engine device 13 is started to work in a small thrust mode immediately, and in the fourth step, when the turning attitude control device 14 performs the action of attitude control, the guided vehicle 1 is started to open an air rudder and a missile wing until the rapid large-angle turning is completed, so that the guided vehicle 1 is ensured to receive smaller aerodynamic resistance in the rapid large-angle turning process.
The turning attitude control device 14 further includes a yaw control engine 20, a pitch control engine 21, and a roll control engine 22.
The boost motor arrangement 13 includes a low thrust solid motor 16 and a high thrust solid motor 17.
The invention has the beneficial effects that:
1. the turning attitude control device can realize omnibearing large-angle quick turning of the guided aircraft in the target direction after being launched;
2. The turning attitude control device can protect the ramjet inlet channel of the head part of the guided vehicle (the ramjet inlet channel sucks air from the annular gap of the head part of the guided vehicle for combustion and provides propulsion power);
3. The invention is suitable for various guidance aircrafts, can meet the requirement that most modern roadbeds, water-surface ships, underwater submarines and other different carriers launch the guidance aircrafts in various modes of being vertical or inclined, and can realize quick turning of the guidance aircrafts.
4. The turning attitude control device and the boosting engine device are two independent devices, are externally installed with the guidance aircraft, greatly reduce the complexity of a design interface of the guidance aircraft, have simple structure, convenient installation and wide adaptability, and greatly reduce the cost and the assembly time.
5. According to the invention, after the turning attitude control device completes quick turning of the guided vehicle, the guided vehicle can be separated from the head of the guided vehicle in an autonomous and controllable manner, so that the safety of the launching platform is ensured, the weight and the volume of the whole guided vehicle are reduced by throwing away the negative weight, the accelerating performance of the guided vehicle air accelerating section boosting engine device (or the main engine) after ignition is greatly enhanced, the boosting engine device can be selected according to the characteristics of the guided vehicle, and after the boosting accelerating action is completed, the boosting engine device can be separated from the tail of the guided vehicle in the flying process of the guided vehicle, so that the safety influence on the launching platform is avoided, the weight and the volume of the guided vehicle are further reduced, the maneuvering performance and the range of the guided vehicle are comprehensively improved, and the hitting or defending capability of the guided vehicle is further improved.
6. The invention provides a complete set of thought for controlling the rolling, pitching and yawing of the ascending section of the launching tube of the guided aircraft and separating the launching tube, can completely replace a control mode of a gas generator and an air rudder, effectively improves the severe working environment of the air rudder, reduces the design complexity of the air rudder (such as removing an internal flow passage of the rudder, reducing the thickness of a rudder root and the like) after removing the gas generator and accessories thereof, simultaneously avoids the problem of large thrust loss of the gas generator and the air rudder mode, selectively installs functional modules in the attitude control device according to the characteristics of different guided aircraft, so as to realize specific functions (such as only selecting to install and separate pulse engines), and further reduces the cost.
7. According to different launching modes and different types of guided aircrafts, the invention also comprises a set of launching and turning systems, and the components in the systems are selected or only the working procedures and the operation methods of the components in the systems are changed, so that the specific functions (effects) of the different types of guided aircrafts can be realized, the mass production cost is greatly reduced, and the use difficulty of the systems on technical arrays and carriers is also reduced.
Detailed Description
An aircraft launching and rapid large-angle turning method, which is characterized in that a booster engine device 13 is connected with the tail of a guided aircraft 1 in a sealing way by explosion bolts,
Firstly, installing a turning attitude control device 14 at the front end of a guided vehicle 1, wherein the end head of the guided vehicle 1 is inserted into the inner space of the turning attitude control device 14, so that the annular lower end part of the turning attitude control device 14 and the outer wall of the upper part of the guided vehicle 1 are sealed and installed together by explosion screws, wherein the turning attitude control device 14 at least comprises a pair of separation engines 23, and the air nozzles of the separation engines 23 are installed on the inner wall of the turning attitude control device 14 and can jet air to the right rear of the movement direction of the guided vehicle 1;
The specific emission process comprises the following steps:
During launching, the gunpowder accumulator 12 at the bottom of the transport launching cylinder 2 starts to work, the gunpowder accumulator 12 generates high-pressure fuel gas in the space at the bottom of the transport launching cylinder 2, the high-pressure fuel gas acts on the bottom of the guide aircraft 1, and the guide aircraft 1 starts to move in the transport launching cylinder 2;
Step three, after the guided vehicle 1 moves in the transport launching tube 2, according to different launching modes, the control system of the guided vehicle 1 decides the time for starting the low thrust mode of the boosting engine device 13;
Step four, when the guided vehicle 1 reaches the set height, the control system of the guided vehicle 1 decides to start or not to start the turning function of the turning attitude control device 14 according to different emission modes, and the turning attitude control device 14 performs the action of attitude control according to the direction specified by the flight task until the rapid large-angle turning is completed or the turning attitude control device 14 keeps not to act;
Step five, after the guided vehicle 1 is adjusted to the direction specified by the flight mission, the separation engine 23 in the turning attitude control device 14 is started, and the separation engine 23 outputs impulse along the movement direction of the guided vehicle 1, so that the turning attitude control device 14 is separated from the guided vehicle 1 and is thrown forward and downward to the subsequent flight trajectory;
and step six, immediately starting a large thrust mode of the boosting engine device 13 after the turning attitude control device 14 is separated, rapidly accelerating the guided vehicle 1 to continue flying along a program trajectory, and detonating an explosion bolt connected with the boosting engine device 13 by the guided vehicle 1 after the guided vehicle 1 is accelerated to a speed capable of starting the ramjet engine, wherein the boosting engine device 13 is thrown off, then starting the ramjet engine, and pushing the guided vehicle to complete cruising flying along a preset track.
When the guided vehicle 1 vertically launches from the underwater submarine, the second step is to open the launching cabin cover before the guided vehicle 1 starts to move in the launching tube, the third step is to start the boosting engine device 13 to work in a small thrust mode after the tail of the guided vehicle 1 passes through the launching tube opening, meanwhile, the guided vehicle 1 rapidly opens the air rudder and the missile wing, and then the fourth step is to enter, and when the guided vehicle 1 reaches the set height, the set height is above the water surface.
When the guided vehicle 1 is launched at a small horizontal angle of a water surface ship, namely 10-30 degrees, in the third step, after the guided vehicle 1 moves in the transport launching cylinder 2, the booster engine device 13 is started to work in a small thrust mode, the turning function of the turning attitude control device 14 is not started in the fourth step, the guided vehicle directly enters the fifth step, after the guided vehicle 1 is regulated to a direction regulated by a flight mission, the guided vehicle is regulated to the direction regulated by the flight mission to implement target course turning through the ship and a cylinder projectile rigidly connected to the guided vehicle, or the rotary launching device provided with the cylinder projectile turns the target, the separation engine 23 in the turning attitude control device 14 is started in the process of moving the guided vehicle in the launching cylinder, and after the booster engine device 13 is started in a large thrust mode in the sixth step, the guided vehicle synchronously opens an air rudder and a missile wing so as to ensure the stable movement of the guided vehicle on a subsequent trajectory.
When the guided vehicle 1 vertically launches on land or on water, in the third step, after the guided vehicle 1 moves in the transport launching tube 2, the booster engine device 13 is started to work in a small thrust mode immediately, and in the fourth step, the turning attitude control device 14 performs the action of attitude control until the rapid large-angle turning is completed, the guided vehicle 1 opens an air rudder and a missile wing to ensure that the guided vehicle 1 receives small aerodynamic resistance in the rapid large-angle turning process.
When the guided vehicle 1 is launched at a larger horizontal angle of the water surface ship, namely 30-45 degrees, in the third step, after the guided vehicle 1 moves in the transport launching cylinder 2, the booster engine device 13 is started to work in a small thrust mode immediately, and in the fourth step, when the turning attitude control device 14 performs the action of attitude control, the guided vehicle 1 is started to open an air rudder and a missile wing until the rapid large-angle turning is completed, so that the guided vehicle 1 is ensured to receive smaller aerodynamic resistance in the rapid large-angle turning process.
The turning attitude control device 14 further includes a yaw control engine 20, a pitch control engine 21, and a roll control engine 22.
The boost motor arrangement 13 includes a low thrust solid motor 16 and a high thrust solid motor 17.
Example 1:
Underwater vertical emission:
The launcher 3 is mounted vertically on the submarine and the guided vehicle 1 is launched from a transport launcher 2 mounted on the launcher 3 in the sequence of action shown in figure 1.
The control system executes the pre-programmed underwater launching execution equipment control instructions according to the corresponding sequence according to the 'underwater vertical launching' launching task type symbol marked on the surface of the guided aircraft 1. The gunpowder accumulator 12 works, high-pressure fuel gas is generated in the bottom space of the transport launching tube 2 (time T1) and acts on the bottom of the guided vehicle 1, the guided vehicle 1 starts to move in the launching tube (T2), when the tail of the guided vehicle 1 passes through the launching tube opening, the sensor in the electric equipment records, the boosting engine device 13 is started to push the guided vehicle to move at a medium and nearly uniform speed in water (T3), the air rudder and the missile wing are opened to ensure that the guided vehicle moves stably along the trajectory of an underwater program, the turning attitude control device 14 starts (T4) after the guided vehicle goes out of water and is recorded by the sensor, the guided vehicle 1 is ensured to finish a quick turning process (G1) according to the direction specified by a flight task according to the data of the command system, then the engine is separated from the turning attitude control device 14 to start (T5), the impulse is output along the movement direction of the guided vehicle, and the turning attitude control device 14 is separated from the guided vehicle 1 and is thrown forward and downward to the subsequent flight trajectory. After the turning attitude control device 14 is disengaged, the booster engine device 13 is immediately started in a high thrust mode (T6), the guided vehicle is rapidly accelerated, and the guided vehicle continues to fly along a program trajectory. After the guided vehicle 1 accelerates to a speed at which the ramjet can be started, the blast bolt is detonated (T7), the passive mass of the booster engine device 13 is thrown away, and then the ramjet is started (T8), and the guided vehicle 1 is pushed to complete cruise flight along a predetermined trajectory. The working method described above is designed according to the type of guided aircraft with the greatest working strength and the most complex sequence of actions, such as the hypersonic carrier-reversing cruise guided aircraft with a ramjet mounted inside, launched from a submarine.
Example 2:
the small horizontal angle (10-30 DEG) of the water surface is transmitted:
The transport launching tube 2 arranged on the surface ship launching device 15 launches the guided vehicle 1 at a small horizontal angle (10-30 degrees) with the deck, and the action sequence is shown in figure 2.
In the preparatory phase before launching the guided vehicle 1, the method of performing a quick turn in the direction prescribed by the mission is to transport the launch canister 2 to orient the target without opening the turn attitude control device 14, in particular to effect a course turn by the ship with the canister (e.g., a reverse ship guided vehicle deployed on a small displacement ship) rigidly connected thereto, or a steering of a rotary launch device equipped with the canister (e.g., a launch device of a ship-based air defense guided vehicle system). Similar to the initial firing phases T1 and T2 described in fig. 1, the charge accumulator 12 operates to generate high pressure fuel gas (T1) in the bottom space of the transport firing drum 2, which acts on the bottom of the guided vehicle 1, the guided vehicle 1 starts to move in the firing drum (T2), the control system starts the boost motor device 13 in a low thrust mode (T3) at a prescribed time after the start of T2 according to the "low water angle firing" mark on the surface of the guided vehicle 1, the guided vehicle 1 moves to a prescribed T5, the separation motor starts in the turning attitude control device 14, the impulse is output in the direction of movement of the guided vehicle 1, and the turning attitude control device 14 is separated from the guided vehicle 1. When the guided vehicle 1 moves to the launching nozzle, a high thrust mode (T6) of the boosting engine device 13 is started, the guided vehicle 1 is rapidly accelerated, the guided vehicle continues to fly along a program trajectory, after the guided vehicle 1 is accelerated to a speed capable of starting the ramjet engine, the explosion bolt is detonated (T7), the negative mass of the boosting engine device 13 is thrown away, then the ramjet engine (T8) is started, the guided vehicle is pushed to complete cruising flight along a preset track, and the T7 and the T8 are consistent with the figure 1. The separation instruction of the turning attitude control device 14 is sent out before the guided vehicle 1 completely leaves the transport launching tube 2 at T5, and the separation instruction is firstly used for ensuring that the turning attitude control device 14 obtains a larger initial speed, the separated turning attitude control device 14 drops to a safe water surface position from the carrier after being discharged from the tube, secondly used for ensuring that the boosting engine device 13 is immediately started in a high thrust mode (T6) when the guided vehicle 1 moves to the launching tube opening, the guided vehicle 1 starts to strongly accelerate when leaving the launching tube opening, and the accelerating performance of the guided vehicle 1 is greatly enhanced due to the fact that the passive mass of the turning attitude control device 14 is thrown off at the moment of discharging the tube, thereby avoiding the dangerous post-emission sinking phenomenon for the carrier after the guided vehicle 1 is launched.
Example 3:
land/water vertical launch:
The sequence of actions is as shown in fig. 3 when the launching task is performed from a surface vessel or land vertical launching device. The launching operation comprises the steps of launching T1, T2 and T3 at a small horizontal angle as introduced in fig. 2, enabling a gunpowder accumulator 12 to work, generating high-pressure fuel gas (T1) in the bottom space of a transport launching cylinder 2 to act on the bottom of the guided vehicle 1, enabling the guided vehicle 1 to move in the launching cylinder (T2), enabling a boosting engine device 13 to start a small thrust mode (T3) at a specified time after the beginning of the T2 according to a mark of 'land/water surface vertical launching' on the surface of the guided vehicle 1 by a control system, enabling a turning gesture control device 14 to start (T4) after the guided vehicle leaves the cylinder and is recorded by a sensor, and guaranteeing the guided vehicle 1 to finish a quick turning process (G1) according to the specified direction of a flight task according to data of a command system. In performing such firing tasks, T4 of the turn attitude control device 14 is activated in accordance with program instructions formed within a prescribed time period after the start of movement 5 of the guided vehicle 1, the time period being pre-calculated in accordance with the condition of "not damaging" the firing vessel superstructure (or land firing platform). The following T5, T6, T7 and T8 are completely consistent with the underwater vertical launching scheme introduced in fig. 1, the separation engine in the turning attitude control device 14 is started (T5), impulse is output along the movement direction of the guided vehicle 1, and the turning attitude control device 14 is separated from the guided vehicle 1 and is thrown forward and downward to the subsequent flight trajectory. After the turning attitude control device 14 is disengaged, the booster engine device 13 is immediately started in a high thrust mode (T6), the guided vehicle is rapidly accelerated, and the guided vehicle continues to fly along a program trajectory. After the guided vehicle 1 accelerates to a speed at which the ramjet can be started, the blast bolt is detonated (T7), the passive mass of the booster engine device 13 is thrown away, and then the ramjet is started (T8), and the guided vehicle 1 is pushed to complete cruise flight along a predetermined trajectory. The missile wing and the air rudder of the guided vehicle 1 are kept in a folded state in the rapid turning process (G1), so that the guided vehicle receives smaller aerodynamic resistance in the maneuvering process, and the missile wing and the air rudder are opened instantly after T5 is completed.
The principle method of executing the launching task from the launching device inclined (30-45 degrees) on the surface of the ship is consistent with the land/water surface vertical launching mode.
The invention also has the following functions:
When the water surface launching is carried out, the guidance aircraft starts the boosting engine device in the process of moving in the launching cylinder so as to additionally improve the cylinder discharging speed of the guidance aircraft. The purpose is that:
1) Mitigating launch (mid) guided vehicle angular motion disturbances caused by vehicle pitch;
2) The time required for the guided vehicle to reach (for the vehicle) a safe distance after leaving the barrel and complete a quick turn is reduced, which is particularly important for vertical launch guided vehicles;
3) The small-angle launching of the guided vehicle is beneficial to the strong acceleration of the guided vehicle, and the sinking after the launching is avoided.
At the same time, the boost motor means has to be activated in a large thrust mode before the guided vehicle starts to move in the launch canister, as this can lead to a sharp rise in pressure in the limited bottom space of the transport launch canister.
The time delay before the guided vehicle passes through the launch nozzle during underwater launch is related to the resultant force acting on the guided vehicle during underwater launch and its profile, the time delay being taken into account by:
1) In the present case, there is no motivation to increase the exit speed of the guided vehicle;
2) When the launch canister is "unsealed" (when the guided vehicle airtight device is ejected from the transport launch canister port), the guided vehicle is largely prevented from being subjected to residual loads because of the almost complete incompressibility of the water, and the increased pressure acts not only on the bottom of the guided vehicle but also on the sides of the guided vehicle.
When launching underwater, when the guided vehicle is out of water or launching on the water surface, the attitude control device is started in a preset time after the guided vehicle starts to move, and then the negative quality of the attitude control device is separated forwards along the flight direction of the guided vehicle, so that the safety of the vehicle is very important under various launching conditions.
The reasonable moment for selecting to start the high thrust mode of the boosting engine device (after the passive mass of the attitude control device is separated) is to reduce the required separation impulse and improve the speed of the guided aircraft as soon as possible, otherwise, the moment for starting is not selected, the inertial force and the rapid pressure head for preventing the separation of the passive mass are multiplied, and the acceleration loss of the guided aircraft is avoided.
Finally, the method for launching the guided vehicle on the water surface at a small horizontal angle has the characteristics that firstly, the method is mainly suitable for a reverse ship cruising guided vehicle or an air defense guided vehicle weapon deployed on a 'light guided vehicle driving out ship or a guided vehicle cruiser' level small displacement ship, and secondly, when the ship of the level is used in most cases, the guided vehicle does not need to turn in a large azimuth angle, because the ship can easily occupy a favorable shooting position in a period for shooting preparation, and a launching barrel carrying the guided vehicle faces a target. In view of the above factors, and the aforementioned high acceleration required by guided vehicles launched at small horizontal angles, without the need to activate the attitude control device, the passive mass of the attitude control device that is not in use will be separated from the guided vehicle during its movement in the launch canister, which is advantageous in switching on the high thrust mode of the booster engine device as soon as possible, thus guaranteeing the high thrust-to-weight ratio required for the guided vehicle to accelerate thereafter.
The following describes a generalized apparatus for performing the launching and turning of a guided vehicle in accordance with the methods set forth hereinabove, with reference to the accompanying drawings, the examples set forth merely to illustrate the invention and are not intended to limit the scope of the invention.
As shown in fig. 4, a guided vehicle 1 with foldable missile wings is arranged in a transport launch canister 2, and the transport launch canister 2 is a solid cylinder. The launching system execution equipment of the guided aircraft 1 comprises a gunpowder accumulator 12 for auxiliary launching, a generalized launching and turning device consisting of a boosting engine device 13 and a turning attitude control device 14, electrical equipment and the like (comprising a guided aircraft water outlet sensor, a barrel outlet sensor and the like). The gunpowder accumulator 12 is arranged at the bottom of the transport launching tube 2 and can generate high-pressure fuel gas to push the guided aircraft 1 to move in the transport launching tube 2.
The boosting engine device 13 mainly comprises 4 small-thrust solid engines 16 and 1 large-thrust solid engine 17, wherein the 4 small-thrust solid engines are uniformly distributed around the nozzle of the large-thrust solid engine, and a parallel binding mode is adopted. The whole device is integrated with an independent module design and is installed at the tail part of the guided aircraft 1 through an explosion screw. After the service of the booster engine device 13 is completed, the booster engine device is separated from the guided aircraft 1 in the flight process of the guided aircraft 1, and the safety influence on the launching platform is avoided. A bottom separable electrical outlet 18 is also mounted on the booster engine assembly 13 housing for communication of the on-board control system with the on-board weapon control system.
The turning attitude control device 14 mainly comprises a group of pulse solid engines and electric control equipment (comprising an inertia measurement unit and the like), wherein each engine is functionally independent as an executing mechanism, and provides required thrust for turning attitude adjustment and device separation. For example, a pair of yaw motors 20 responsible for yaw control, a pair of pitch motors 21 for pitch control, 4 roll motors 22 for roll control, and a pair of split motors 23 for split control. The components are mounted on a housing 19, the device being of an integrated, independent modular design, which can be separated from the guided vehicle 1 by mounting on the head of the guided vehicle 1 with shear screws or explosive screws.
When launching the guided vehicle 1 according to the method recommended above, the working procedure is as follows:
The gunpowder accumulator 12 works, high-pressure fuel gas is generated in the bottom space of the transport launching tube 2 and acts on the bottom of the guided vehicle 1, when the bottom pressure of the guided vehicle reaches a calculated value, a connecting part for assisting the guided vehicle 1 to keep an initial state is destroyed, the guided vehicle 1 starts to move, the bottom electric socket 18 is disconnected, the event is recorded by the control system and used as a basis for starting T2, and the event can also be used as a calculation time for starting the boosting engine device 13 and the turning attitude control device 14 when water surface launching is implemented.
As described above, the subsequent action program of the launch is given according to the launch type symbol specified by the vehicle weapon control system, and is exemplified by the "underwater vertical launch" mode with the greatest working strength, when the tail of the guided vehicle 1 passes through the port of the transport launch canister 2, the 4 small thrust solid engines 16 are started by the sensors in the electrical equipment, the guided vehicle 1 is pushed to move in the water at a moderate and almost uniform speed, and the air rudders are opened, so as to ensure the stable movement of the guided vehicle along the trajectory of the underwater program. After the guided vehicle 1 discharges water and is recorded by a sensor, a turning attitude control device 14 is started, the control system checks the real-time attitude of the guided vehicle 1 according to the estimated trajectory, and sends out an attitude adjustment instruction, and after the turning attitude control device 14 receives the instruction, the guided vehicle 1 works individually or synchronously according to the situation, so that the actions of rolling, pitching, yawing and the like of the guided vehicle 1 are completed, and the rapid turning to a target is realized. For example, pitch control is performed on the guided aircraft 1, one of the pitch engines 21 is started according to a control instruction, the angular speed of the guided aircraft 1 in a pitch channel is improved under the action of engine thrust, a sensor transmits a real-time measured attitude parameter of the guided aircraft 1 to a control system, the control system calculates a subsequent instruction starting time according to a given inclination angle of the guided aircraft 1 and the guided aircraft attitude parameter measured by the sensor, and gives an instruction to start a second pitch engine 21, so that the angular speed is 'suppressed' at the moment when the guided aircraft 1 shifts to a required attitude relative to the horizon. Likewise, the guided vehicle 1 also employs a similar control method in yaw and roll paths. It should be noted that in the control of the guided vehicle 1 in the roll channel, it is necessary to activate a pair of roll motors 22, generating positive and negative moments around the longitudinal axis of the guided vehicle 1. The 4 low thrust solid engines 16 are operated all the time during the fast turning 8 and function to counteract the weight of the guided vehicle 1 and prevent the guided vehicle 1 from "sinking" into the water. After the turning is finished, the control system sends an instruction to start the separation engine 23, outputs impulse to the turning attitude control device 14 along the flight direction of the guided vehicle 1, the turning attitude control device 14 separates from the front part of the guided vehicle 1, then starts the high-thrust solid engine 17, the guided vehicle 1 starts to accelerate sharply, during which stable movement of the guided vehicle 1 can be controlled through the tail gas rudder of the guided vehicle 1, and when the flight speed is high enough, the attitude control of the guided vehicle 1 is completed by the air rudder.
Furthermore, according to the characteristics of different guided aircrafts, the functional modules in the turning attitude control device can be selectively installed to realize specific functions, such as target orientation through a carrier or an emission platform in a water surface small horizontal angle (10-30 degrees) emission mode, the guided aircrafts do not need the attitude control device to turn in a large azimuth angle, only the engine for installation and separation is selected, and the cost is further reduced.
According to the method recommended above, the ability of the guided vehicle to launch vertically or obliquely from different vehicles, and the ability to turn quickly after launch, is given by performing the equipment start-up procedure using different sequences of actions and launch systems specified by the launch method recommended above.
In conclusion, the invention can guide the development of the fully generalized guided aircraft, can meet different requirements of modern conventional weapons such as sea bases, roadbeds and the like, is widely suitable for various carriers, and can fully embody the advantages of simple operation and low use cost of the generalized weapons.
The technical proposal of the invention has the beneficial effects that
The universal guidance aircraft launching and turning system principle and the using method provided by the invention can guide the development of a completely universal guidance aircraft, can meet different requirements of most modern roadbeds, water-surface ships, underwater submarines and other different carriers for launching the guidance aircraft in a plurality of modes of vertical or inclined, and can realize rapid turning of the guidance aircraft;
The integrated independent jettisonable device can be guided and developed, the external installation of the integrated independent jettisonable device and the guided aircraft is realized, the design interface complexity of the guided aircraft is greatly reduced, the structure is simple, the installation is convenient, and the adaptability is wide;
according to different launching modes and different types of guided aircrafts, the invention has the advantages that the components in the launching and turning system are selected or the working procedures and the operation methods of the components in the system are only changed, so that the specific functions (effects) of the different types of guided aircrafts can be realized, the mass production cost is greatly reduced, and the use difficulty of the system on technical arrays and carriers is also reduced;
According to the invention, the attitude control device is independently and controllably separated from the head of the guided vehicle after the guided vehicle turns rapidly, so that the safety of the launching platform is ensured, the weight and the volume of the whole guided vehicle are reduced by throwing away the negative weight, the accelerating performance of the guided vehicle air accelerating section boosting engine device (or the main engine) after ignition is greatly enhanced, the boosting engine device can be selectively arranged according to the characteristics of the guided vehicle, and after the boosting accelerating action is completed, the boosting engine device can be separated from the tail of the guided vehicle in the flying process of the guided vehicle, so that the safety influence on the launching platform is avoided, the weight and the volume of the guided vehicle are further reduced, the maneuvering performance and the range of the guided vehicle are comprehensively improved, and the striking or defending capability of the guided vehicle is further improved;
The invention provides a complete set of thought for controlling the roll-pitch-yaw and separation of the ascending section of the launching tube of the guided aircraft, which can completely replace a control mode of a gas generator and an air rudder, effectively improve the severe working environment of the air rudder, reduce the design complexity of the air rudder (such as removing the internal flow passage of the rudder, reducing the thickness of the rudder root, and the like) after removing the gas generator and accessories thereof, simultaneously avoid the problem of large thrust loss of the gas generator and the air rudder mode, selectively install functional modules in the attitude control device according to the characteristics of different guided aircraft so as to realize specific functions (such as only selecting and installing a pulse engine for separation), further reduce the cost, and the key point of the technical scheme of the invention is that
The invention adopts a direct lateral force control technology based on a gesture control engine to realize the principle and method innovation of rapid turning, working sequence, ignition time sequence and the like of the guided aircraft. The guiding aircraft can be guided and developed to be completely universal, different requirements of most modern roadbeds, water-surface ships, underwater submarines and other different carriers for launching the guiding aircraft in a plurality of modes of being vertical or inclined can be met, and the guiding aircraft can rapidly turn;
the hardware device is designed by adopting an integrated independent jettisonable module, is externally arranged with the guided vehicle, greatly reduces the complexity of a design interface of the guided vehicle, and has the advantages of simple structure, convenient installation and wide adaptability;
According to different launching modes and different types of guided aircrafts, the invention has the same set of launching and turning systems, and the specific functions (effects) of the different types of guided aircrafts can be realized by selecting the components in the systems or only changing the working procedures and the operation methods of the components in the systems, so that the mass production cost is greatly reduced, and the use difficulty of the systems on technical arrays and carriers is also reduced;
According to the invention, the attitude control device is independently and controllably separated from the head of the guided vehicle after the guided vehicle turns rapidly, the weight and the volume of the whole guided vehicle are reduced on the premise of guaranteeing the safety of the launching platform, the accelerating performance of the guided vehicle air accelerating section booster engine device (or the main engine) after ignition is greatly enhanced, the booster engine device can be selectively arranged according to the characteristics of the guided vehicle, and after the boosting accelerating action is finished, the booster engine device can be separated from the tail of the guided vehicle in the flying process of the guided vehicle, so that the safety influence on the launching platform is avoided, the weight and the volume of the guided vehicle are further reduced, the maneuvering performance and the range of the guided vehicle are comprehensively improved, and the striking or defending capability of the guided vehicle is further improved;
The invention provides a complete set of thought for controlling the rolling, pitching and yawing of the ascending section of the launching tube of the guided aircraft and for controlling the separation, so that the method can completely replace a control mode of the gas generator and the air rudder, effectively improve the severe working environment of the air rudder, reduce the design complexity of the air rudder (such as removing an internal flow passage of the rudder, reducing the thickness of a rudder root and the like) after removing the gas generator and accessories thereof, and simultaneously avoid the problem of large thrust loss of the mode of the gas generator and the air rudder;
the technical problem to be solved by the invention is that,
The launching and turning principle and the using method of the guidance aircraft are provided, so that the launching and turning principle and the using method of the guidance aircraft can meet different requirements of most modern roadbeds, water-surface ships, underwater submarines and other different vehicles for launching the guidance aircraft in a plurality of modes of being vertical or inclined, realize the omnibearing rapid turning of the guidance aircraft towards the target direction after the launching, and can guide the development of a completely universal guidance aircraft.
The universal standardized transmitting and turning device is guided to be developed, so that the problems of high mass production cost and great use difficulty of various traditional devices on technical arrays and carriers can be solved;
The problem of safe and reliable separation between the device and the guided vehicle after the device is used is solved, the weight and the volume of the guided vehicle in the flight are reduced, and the maneuvering performance and the range of the guided vehicle are improved;
The invention can replace the traditional control mode of the gas generator and the air rudder, and solves the problems of complex structure, severe environment of air helmsman, high design complexity of the rudder, large thrust loss, high cost and the like.
The main idea of the invention
The invention aims to complete the task by means of a universal device for launching a guided aircraft from a transport launching tube, and mainly comprises a boosting engine device and a quick turning gesture control device (gesture control device for short). The boosting engine device is arranged at the tail part of the guided aircraft, and the attitude control device is arranged at the head part of the guided aircraft.
The boosting engine device is provided with a large thrust mode and a small thrust mode, wherein the large thrust mode can be realized by adopting a large thrust solid engine, the small thrust mode can be realized by adopting a plurality of small thrust solid engines to be bundled in parallel or adopting a gas generator and tail nozzle mode, the potential of the boosting engine device can be reasonably utilized according to the actual use requirement of the guided aircraft, the load of the guided aircraft during underwater movement can be lightened by the small thrust mode, and the large thrust mode can provide a required large thrust-weight ratio for water surface emission. The booster engine device can be separated from the guided vehicle after being used, so that the flight weight of the guided vehicle is reduced, the guided vehicle which is smaller in weight and shorter in range can be selected according to the characteristics of the guided vehicle, for example, the initial speed of a cylinder is higher, the turning time of an ascending section in the air is sufficient, and the guided vehicle is maintained to be suspended in the air without providing additional thrust.
The attitude control device directly generates larger thrust to act on the guided vehicle in a short time based on a direct force control mode of the pulse engine, so that the guided vehicle can realize large maneuvering turning in the moment after being launched, quickly enter a kinematic trajectory, and automatically separate from the guided vehicle after turning, and lighten the flight weight of the guided vehicle, thereby achieving the purpose of improving the maneuvering combat (quick response) efficiency and the viability of the guided vehicle.
According to the invention, specific functions (effects) of different types of guided vehicles can be realized by changing the working procedures and the operating methods of the components in the above-mentioned generalized device according to different launching modes and different types of guided vehicles. The principles and methods of use of the present invention are described in detail below with reference to the drawings, the examples being illustrative of the present invention and not intended to limit the scope of the invention.