A method for launching an aircraft and making a rapid turn

Abstract

A method for launching and quickly turning an aircraft, wherein a booster engine device (13) is sealed and connected to the tail of a guided aircraft (1) by means of explosive screws, and is characterized in that the method comprises the following steps: step 1, installing a turning attitude control device (14) at the front end of the guided aircraft (1), wherein the end of the guided aircraft (1) is inserted into the inner space of the turning attitude control device (14), so that the annular lower end portion of the turning attitude control device (14) and the upper outer wall of the guided aircraft (1) are sealed and installed together by means of explosive screws; the present invention is applicable to a variety of guided aircraft, and can meet the requirements of launching guided aircraft in vertical or inclined multiple modes from most modern roadbeds, surface ships, underwater submarines and other different vehicles, and realize the quick turning of the guided aircraft.

Description

Technical Field

[0001] The present invention discloses a method for launching and rapidly turning an aircraft, and relates to the field of aircraft engineering. Specifically, the method relates to a method for launching a guided power-propelled guided aircraft and a method for autonomously completing omnidirectional rapid turns in the air after takeoff. The method is widely applicable to anti-ship cruise guided aircraft and air defense guided aircraft with different launch modes. Background Art

[0002] The launch method for a guided aircraft refers to a launch plan that combines the launch base, launch power, launch attitude, and launch device. Due to differences in the combat mission, structure and appearance, mass, and guidance method of guided aircraft, the launch method and device type vary. Launch attitudes can be categorized as inclined, vertical, and horizontal launch.

[0003] For modern anti-ship cruise guided vehicles and air defense guided vehicles, adaptability to a wide range of launch methods is crucial. To adapt guided vehicles to different carriers, facilitate operation, and protect against adverse external factors, various transport launch tubes are commonly used. These numerous types of launch tubes result in high production costs and are difficult to deploy on technical positions and vehicles.

[0004] Another key technology for modern anti-ship cruise guided vehicles and air defense guided vehicles, particularly for low- and medium-altitude defense, near-shore and surface defense, or offensive operations, is rapid, all-around turns toward the target. This requires the guided vehicles to complete turns in the shortest possible time, with the smallest possible turning radius, and quickly enter the range interval to expand the minimum and maximum ranges. This necessitates crucial capabilities such as rapid reaction time, execution time, and minimum range. Currently, the primary vertical launch turning methods for guided vehicles, both domestically and internationally, include thrust vectoring and direct side force control. Direct side force control is further categorized as using a gas generator or an attitude control pulse engine. The gas generator method presents challenges such as complex structure, harsh rudder operating environment, complex rudder design, high thrust loss, and high cost. A control method based on an attitude control pulse engine, which operates independently of rudders, is a promising alternative. Summary of the Invention

[0005] The purpose of the present invention is to provide a method for launching and quickly turning a guided aircraft. The present invention is a completely universal method for launching and turning a guided aircraft, which can meet the working conditions of launching guided aircraft in various vertical or inclined modes from most modern roadbeds, surface ships, underwater submarines and other different vehicles.

[0006] A method for launching and quickly turning a guided aircraft, wherein a booster engine device 13 is sealed and connected to the tail of the guided aircraft 1 with explosive screws, and is characterized in that it includes the following steps:

[0007] Step 1: Install a turning attitude control device 14 at the front end of the guided aircraft 1. The end of the guided aircraft 1 is inserted into the interior space of the turning attitude control device 14, and the annular lower end of the turning attitude control device 14 is sealed to the upper outer wall of the guided aircraft 1 using explosive screws. The turning attitude control device 14 includes at least a pair of separate engines 23. The jet nozzles of the separate engines 23 are installed on the inner wall of the turning attitude control device 14 and are capable of ejecting air directly behind the direction of movement of the guided aircraft 1.

[0008] Specific launch process:

[0009] Step 2: Install the guided aircraft 1, equipped with the turning attitude control device 14 at its end, into the transport launch tube 2 in the launch device 3. During launch, the gunpowder accumulator 12 at the bottom of the transport launch tube 2 begins to operate, generating high-pressure gas in the bottom space of the transport launch tube 2. The high-pressure gas acts on the bottom of the guided aircraft 1, causing the guided aircraft 1 to begin moving inside the transport launch tube 2.

[0010] Step 3: After the guided aircraft 1 moves in the transport launch tube 2, the control system of the guided aircraft 1 determines the timing of starting the low-thrust mode of the booster engine device 13 according to different launch modes;

[0011] Step 4: When the guided aircraft 1 reaches the set altitude, the control system of the guided aircraft 1 decides whether to activate or deactivate the turning function of the turning attitude control device 14 according to different launch modes; the turning attitude control device 14 performs attitude control actions according to the direction specified by the flight mission until a rapid and large-angle turn is completed, or the turning attitude control device 14 remains inactive;

[0012] Step 5: After the guided aircraft 1 is adjusted to the direction specified by the flight mission, the separation motor 23 in the turning attitude control device 14 is activated. The separation motor 23 outputs impulse in the direction of movement of the guided aircraft 1, causing the turning attitude control device 14 to separate from the guided aircraft 1 and eject it forward and downward to its subsequent flight trajectory.

[0013] Step 6: After the turning attitude control device 14 is detached, the high-thrust mode of the booster engine device 13 is immediately turned on, and the guided aircraft 1 is rapidly accelerated and continues to fly along the programmed trajectory; after the guided aircraft 1 is accelerated to a speed capable of starting the ramjet engine, the explosive bolts connecting the guided aircraft 1 and the booster engine device 13 are detonated, the booster engine device 13 is thrown away, and then the ramjet engine is started to propel the guided aircraft to complete the cruise flight along the predetermined trajectory.

[0014] When the guided aircraft 1 is vertically launched from an underwater submarine, the launch hatch is opened before the guided aircraft 1 starts to move in the launch tube as described in step 2; after the tail of the guided aircraft 1 passes through the launch tube mouth as described in step 3, the booster engine device 13 is turned on to work in a low-thrust mode; at the same time, the guided aircraft 1 quickly opens the air rudder and the wing, and then enters step 4; when the guided aircraft 1 reaches the set altitude as described in step 4, the set altitude is above the water surface.

[0015] When the guided aircraft 1 is launched at a small horizontal angle of 10° to 30° from a surface ship, in step 3, after the guided aircraft 1 moves in the transport launch tube 2, the booster engine device 13 is immediately started to work in the low-thrust mode; the turning function of the turning attitude control device 14 described in step 4 is not started, and step 5 is directly entered; in step 5, after the guided aircraft 1 is adjusted to the direction specified by the flight mission, the adjustment to the direction specified by the flight mission is to implement a target course turn through the ship together with the canister bullet rigidly connected thereto, or the rotary launch device equipped with the canister bullet turns toward the target; the separation engine 23 in the turning attitude control device 14 described in step 5 is started when the guided aircraft is moving in the launch tube; after the high-thrust mode of the booster engine device 13 is started in step 6, the guided aircraft synchronously opens the air rudder and the missile wing to ensure stable movement of the guided aircraft on the subsequent trajectory.

[0016] When the guided aircraft 1 is launched vertically on land or water, in step 3, after the guided aircraft 1 moves in the transport launch tube 2, the booster engine device 13 is immediately started to work in the low-thrust mode; the turning attitude control device 14 described in step 4 performs attitude control until the guided aircraft 1 completes a rapid and large-angle turn, and then the air rudder and the wings of the guided aircraft 1 are opened to ensure that the guided aircraft 1 is subjected to less aerodynamic resistance during the rapid and large-angle turn.

[0017] When the guided aircraft 1 is launched at a large horizontal angle of 30° to 45° from a surface ship, in step 3, after the guided aircraft 1 moves in the transport launch tube 2, the booster engine device 13 is immediately started to work in the low-thrust mode; in step 4, when the turning attitude control device 14 performs attitude control, the guided aircraft 1 will not open the air rudder and the missile wing until the rapid and large-angle turn is completed, so as to ensure that the guided aircraft 1 is subjected to less aerodynamic resistance during the rapid and large-angle turn.

[0018] The turning attitude control device 14 further includes a yaw control engine 20 , a pitch control engine 21 and a roll control engine 22 .

[0019] The booster engine device 13 includes a low-thrust solid engine 16 and a high-thrust solid engine 17 .

[0020] Beneficial effects of the present invention:

[0021] 1. The turning attitude control device of the present invention can realize the rapid turning of the guided aircraft in all directions and at large angles towards the target after launch;

[0022] 2. The turning attitude control device of the present invention can protect the ramjet engine inlet at the nose of the guided vehicle (the ramjet engine inlet draws air from the annular gap at the nose of the guided vehicle, burns it, and provides propulsion power). If the first function is not used, the turning attitude control device will quickly and autonomously detach after the guided vehicle is launched, reducing the weight of the entire guided vehicle.

[0023] 3. The present invention is applicable to a variety of guided aircraft, and can meet the needs of most modern roadbeds, surface ships, underwater submarines and other different vehicles to launch guided aircraft in vertical or inclined multiple modes, and realize rapid turning of guided aircraft.

[0024] 4. The turning attitude control device and the booster engine device in the present invention are two independent devices, both of which are installed externally to the guided aircraft, greatly reducing the complexity of the guided aircraft design interface. They have a simple structure, are easy to install, and have wide adaptability, greatly reducing costs and assembly time.

[0025] 5. After the turning attitude control device in the present invention completes the rapid turning of the guided aircraft, it autonomously and controllably separates from the head of the guided aircraft, ensuring the safety of the launch platform. The removal of negative weight reduces the weight and volume of the entire guided aircraft. After the booster engine device (or main engine) of the guided aircraft in the air acceleration stage is ignited, the acceleration performance is greatly enhanced. The booster engine device can be selected according to the characteristics of the guided aircraft itself. After completing the boost acceleration function, it can separate from the tail of the guided aircraft during the flight of the guided aircraft without affecting the safety of the launch platform. This further reduces the weight and volume of the guided aircraft, comprehensively improves the maneuverability and range of the guided aircraft, and thereby enhances the strike or defense capability of the guided aircraft.

[0026] 6. The present invention provides a complete set of ideas for roll-pitch-yaw control and separation control during the ascent phase of a guided aircraft launched from the tube. It can completely replace the gas generator + air rudder control method, effectively improving the harsh working environment of the air rudder. After removing the gas generator and its accessories, the design complexity of the air rudder is reduced (for example, the internal flow channel of the rudder is removed, the thickness of the rudder root is thinned, etc.), and at the same time avoids the problem of large thrust loss in the gas generator + air rudder method. In addition, according to the characteristics of different guided aircraft, functional modules in the attitude control device can be selectively installed to achieve specific functions (for example, only the pulse engine for separation is installed), further reducing costs.

[0027] 7. The present invention can realize specific functions (effects) of different types of guided aircraft by using the same launch and turning system according to different launch methods and different types of guided aircraft, by selecting components in the system or only changing the working procedures and operating methods of the components in the system, thereby greatly reducing mass production costs and the difficulty of using the system in technical positions and vehicles. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 , a schematic diagram of the underwater vertical launch process of the present invention;

[0029] Figure 2 , a schematic diagram of the launching process at a small horizontal angle (10° to 30°) on the water surface of the present invention;

[0030] Figure 3 , a schematic diagram of the land-based vertical launch process of the present invention;

[0031] Figure 4 , a schematic diagram of the structure of the guided aircraft 1 of the present invention disposed in the transport launch tube 2;

[0032] (a) is a schematic diagram of the overall structure of the guided aircraft 1 of the present invention equipped with a turning attitude control device 14 and a booster engine device;

[0033] (b) Figure 4 The enlarged view of point II in (a);

[0034] (c) Figure 4 The enlarged view of point Ⅰ in (a);

[0035] (d) Figure 4 AA cross-sectional view in (c).

[0036] Among them, 1 is the guided aircraft, 2 is the transport launch tube, 3 is the launch device, 12 is the gunpowder accumulator, 13 is the booster engine device, 14 is the turn attitude control device, 18 is the detachable electrical socket, 19 is the shell, 20 is the yaw control engine, 21 is the pitch control engine, 22 is the roll control engine, and 23 is the separation engine. 15 is the surface ship launch device, 16 is the low-thrust solid engine, and 17 is the high-thrust solid engine.

[0037] T1: The moment when the gunpowder pressure accumulator 12 starts to work and high-pressure gas is generated in the bottom space of the transport launch tube 2; T2: The moment when the guided aircraft 1 starts to move in the launch tube; T3: The moment when the low-thrust mode of the booster engine device 13 is activated; T4: The moment when the turning attitude control device 14 is activated; T5: The moment when the separation engine is activated; T6: The moment when the high-thrust mode of the booster engine 13 is activated; T7: The moment when the explosive bolt of the booster engine is detonated; T8: The moment when the ramjet engine is activated; DETAILED DESCRIPTION

[0038] A method for launching an aircraft and making a rapid large-angle turn, wherein a booster engine device 13 is sealed and connected to the tail of a guided aircraft 1 with explosive screws, and is characterized in that it includes the following steps:

[0039] Step 1: Install a turning attitude control device 14 at the front end of the guided aircraft 1. The end of the guided aircraft 1 is inserted into the interior space of the turning attitude control device 14, and the annular lower end of the turning attitude control device 14 is sealed to the upper outer wall of the guided aircraft 1 using explosive screws. The turning attitude control device 14 includes at least a pair of separate engines 23. The jet nozzles of the separate engines 23 are installed on the inner wall of the turning attitude control device 14 and are capable of ejecting air directly behind the direction of movement of the guided aircraft 1.

[0040] Specific launch process:

[0041] Step 2: Install the guided aircraft 1, equipped with the turning attitude control device 14 at its end, into the transport launch tube 2 in the launch device 3. During launch, the gunpowder accumulator 12 at the bottom of the transport launch tube 2 begins to operate, generating high-pressure gas in the bottom space of the transport launch tube 2. The high-pressure gas acts on the bottom of the guided aircraft 1, causing the guided aircraft 1 to begin moving inside the transport launch tube 2.

[0042] Step 3: After the guided aircraft 1 moves in the transport launch tube 2, the control system of the guided aircraft 1 determines the timing of starting the low-thrust mode of the booster engine device 13 according to different launch modes;

[0043] Step 4: When the guided aircraft 1 reaches the set altitude, the control system of the guided aircraft 1 decides whether to activate or deactivate the turning function of the turning attitude control device 14 according to different launch modes; the turning attitude control device 14 performs attitude control actions according to the direction specified by the flight mission until a rapid and large-angle turn is completed, or the turning attitude control device 14 remains inactive;

[0044] Step 5: After the guided aircraft 1 is adjusted to the direction specified by the flight mission, the separation motor 23 in the turning attitude control device 14 is activated. The separation motor 23 outputs impulse in the direction of movement of the guided aircraft 1, causing the turning attitude control device 14 to separate from the guided aircraft 1 and eject it forward and downward to its subsequent flight trajectory.

[0045] Step 6: After the turning attitude control device 14 is detached, the high-thrust mode of the booster engine device 13 is immediately turned on, and the guided aircraft 1 is rapidly accelerated and continues to fly along the programmed trajectory; after the guided aircraft 1 is accelerated to a speed capable of starting the ramjet engine, the explosive bolts connecting the guided aircraft 1 and the booster engine device 13 are detonated, the booster engine device 13 is thrown away, and then the ramjet engine is started to propel the guided aircraft to complete the cruise flight along the predetermined trajectory.

[0046] When the guided aircraft 1 is vertically launched from an underwater submarine, the launch hatch is opened before the guided aircraft 1 starts to move in the launch tube as described in step 2; after the tail of the guided aircraft 1 passes through the launch tube mouth as described in step 3, the booster engine device 13 is turned on to work in a low-thrust mode; at the same time, the guided aircraft 1 quickly opens the air rudder and the wing, and then enters step 4; when the guided aircraft 1 reaches the set altitude as described in step 4, the set altitude is above the water surface.

[0047] When the guided aircraft 1 is launched at a small horizontal angle of 10° to 30° from a surface ship, in step 3, after the guided aircraft 1 moves in the transport launch tube 2, the booster engine device 13 is immediately started to work in the low-thrust mode; the turning function of the turning attitude control device 14 described in step 4 is not started, and step 5 is directly entered; in step 5, after the guided aircraft 1 is adjusted to the direction specified by the flight mission, the adjustment to the direction specified by the flight mission is to implement a target course turn through the ship together with the canister bullet rigidly connected thereto, or the rotary launch device equipped with the canister bullet turns toward the target; the separation engine 23 in the turning attitude control device 14 described in step 5 is started when the guided aircraft is moving in the launch tube; after the high-thrust mode of the booster engine device 13 is started in step 6, the guided aircraft synchronously opens the air rudder and the missile wing to ensure stable movement of the guided aircraft on the subsequent trajectory.

[0048] When the guided aircraft 1 is launched vertically on land or water, in step 3, after the guided aircraft 1 moves in the transport launch tube 2, the booster engine device 13 is immediately started to work in the low-thrust mode; the turning attitude control device 14 described in step 4 performs attitude control until the guided aircraft 1 completes a rapid and large-angle turn, and then the air rudder and the wings of the guided aircraft 1 are opened to ensure that the guided aircraft 1 is subjected to less aerodynamic resistance during the rapid and large-angle turn.

[0049] When the guided aircraft 1 is launched at a large horizontal angle of 30° to 45° from a surface ship, in step 3, after the guided aircraft 1 moves in the transport launch tube 2, the booster engine device 13 is immediately started to work in the low-thrust mode; in step 4, when the turning attitude control device 14 performs attitude control, the guided aircraft 1 will not open the air rudder and the missile wing until the rapid and large-angle turn is completed, so as to ensure that the guided aircraft 1 is subjected to less aerodynamic resistance during the rapid and large-angle turn.

[0050] The turning attitude control device 14 further includes a yaw control engine 20 , a pitch control engine 21 and a roll control engine 22 .

[0051] The booster engine device 13 includes a low-thrust solid engine 16 and a high-thrust solid engine 17 .

[0052] Example 1:

[0053] Underwater vertical launch:

[0054] The launching device 3 is vertically mounted on the submarine, and the guided aircraft 1 is launched from the transport launch tube 2 mounted on the launching device 3. The action sequence is as follows: Figure 1 .

[0055] The control system executes the pre-programmed underwater launch execution equipment control instructions in a corresponding order according to the "underwater vertical launch" launch mission type symbol marked on the surface of the guided aircraft 1. The gunpowder accumulator 12 operates, generating high-pressure gas in the bottom space of the transport launch tube 2 (time T1), which acts on the bottom of the guided aircraft 1, causing the guided aircraft 1 to begin moving within the launch tube (T2). When the tail of the guided aircraft 1 passes through the launch tube mouth, it is recorded by the sensor in the electrical equipment, and the booster engine device 13 is activated in a low-thrust mode (T3), propelling the guided aircraft to move at a medium, almost uniform speed in the water. The air rudder and wings are opened to ensure that the guided aircraft moves stably along the programmed underwater trajectory. After the guided aircraft emerges from the water and is recorded by the sensor, the turning attitude control device 14 is activated (T4). Based on data from the command system, it ensures that the guided aircraft 1 completes a rapid turn process in the direction specified by the flight mission (G1). Then, the separation engine in the turning attitude control device 14 is activated (T5), outputting an impulse in the direction of the guided aircraft's movement. The turning attitude control device 14 separates from the guided aircraft 1 and ejects it forward and downward onto its subsequent flight trajectory. After the turning attitude control device 14 is disengaged, the booster engine unit 13 is immediately activated in high-thrust mode (T6), causing the guided aircraft to accelerate rapidly and continue its flight along the programmed trajectory. After the guided aircraft 1 accelerates to a speed sufficient to activate the ramjet engine, the explosive bolts detonate (T7), jettisoning the passive mass of the booster engine unit 13. The ramjet engine is then activated (T8), propelling the guided aircraft 1 along the predetermined trajectory to complete its cruise flight. The operating method described above is designed for guided aircraft types with the highest workload and the most complex sequence of movements, such as a hypersonic anti-ship cruise guided aircraft with an internally installed ramjet engine launched from an underwater submarine.

[0056] Example 2:

[0057] Launching at a small horizontal angle (10°~30°) on the water surface:

[0058] The transport launch tube 2 configured on the surface ship launch device 15 launches the guided aircraft 1 at a small horizontal angle (10-30 degrees) to the deck. The action sequence is as follows: Figure 2 .

[0059] During the pre-launch preparation phase of the guided aircraft 1, the method for completing a rapid turn in the direction specified by the flight mission is to orient the transport launch tube 2 to the target without activating the turning attitude control device 14. Specifically, the ship and the tube-shaped missile rigidly connected to it (for example, an anti-ship guided aircraft deployed on a small-displacement ship) perform a heading turn, or the rotary launcher equipped with the tube-shaped missile is turned (for example, the launcher of a ship-borne air defense guided aircraft system). Similar to Figure 1During the initial launch phases T1 and T2 described above, the gunpowder accumulator 12 operates, generating high-pressure gas (T1) in the bottom space of the transport launch tube 2, which acts on the bottom of the guided aircraft 1. The guided aircraft 1 begins to move within the launch tube (T2). The control system activates the low-thrust mode of the booster engine device 13 (T3) at a specified time after T2, based on the "surface low-angle launch" mark on the surface of the guided aircraft 1. The guided aircraft 1 moves to the specified time T5, and the separation engine in the turning attitude control device 14 is started, outputting impulse in the direction of movement of the guided aircraft 1. The turning attitude control device 14 separates from the guided aircraft 1. When the guided aircraft 1 moves to the launch tube muzzle, the booster engine device 13 is turned on in high thrust mode (T6). The guided aircraft 1 accelerates rapidly and continues to fly along the programmed trajectory. After the guided aircraft 1 accelerates to a speed that can start the ramjet engine, the explosive bolt detonates (T7), the negative mass of the booster engine device 13 is thrown away, and then the ramjet engine is started (T8), pushing the guided aircraft to complete the cruise flight along the predetermined orbit. T7 and T8 are consistent with the Figure 1 The reason why T5 issues the separation command for the turning attitude control device 14 before the guided aircraft 1 completely leaves the transport launch tube 2 is that: first, it ensures that the turning attitude control device 14 obtains a large initial velocity, and the separated turning attitude control device 14 lands on the water surface at a safe distance from the vehicle after leaving the tube; second, it ensures that the high thrust mode (T6) of the booster engine device 13 is immediately turned on when the guided aircraft 1 moves to the launch tube muzzle. When the guided aircraft 1 leaves the launch tube muzzle, it begins to accelerate strongly. Since the negative mass of the turning attitude control device 14 is thrown away at the moment of leaving the tube, the acceleration performance of the guided aircraft 1 is greatly enhanced, thereby avoiding the post-launch "sinking" phenomenon of the guided aircraft 1 after launch, which is dangerous to the vehicle.

[0060] Example 3:

[0061] Land / surface vertical launch:

[0062] When launching from a surface ship or a land-based vertical launch system, the sequence of actions is as follows: Figure 3 The launch operation includes Figure 2In the low horizontal angle launch T1, T2, and T3 introduced, the gunpowder accumulator 12 works, and high-pressure gas (T1) is generated in the bottom space of the transport launch tube 2, which acts on the bottom of the guided aircraft 1, and the guided aircraft 1 begins to move in the launch tube (T2). The control system starts the booster engine device 13 in low thrust mode (T3) at a specified time after the start of T2 according to the "land / surface vertical launch" mark marked on the surface of the guided aircraft 1. After the guided aircraft leaves the tube and is recorded by the sensor, the turning attitude control device 14 is started (T4). According to the data of the command system, it is ensured that the guided aircraft 1 completes the rapid turning process (G1) in the direction specified by the flight mission. When executing this type of launch mission, T4 for starting the turning attitude control device 14 is carried out according to the program instructions formed within the specified time after the guided aircraft 1 starts to move 5. This time period is pre-calculated based on the condition of "not damaging" the superstructure of the launching ship (or land launch platform). The subsequent T5, T6, T7, T8 and Figure 1 The underwater vertical launch scheme described is identical. The separate engine in the turning attitude control unit 14 is activated (T5), delivering impulse in the direction of motion of the guided vehicle 1. The turning attitude control unit 14 separates from the guided vehicle 1 and is ejected forward and downward onto its subsequent flight trajectory. Immediately after the turning attitude control unit 14 detaches, the booster engine unit 13 is activated in high-thrust mode (T6), rapidly accelerating the guided vehicle and continuing along the programmed trajectory. After the guided vehicle 1 accelerates to a speed sufficient to activate the ramjet engine, the explosive bolt detonates (T7), jettisoning the passive mass of the booster engine unit 13. The ramjet then activates (T8), propelling the guided vehicle 1 along the planned trajectory for cruise flight. During the rapid turn (G1), the wings and air rudders of the guided vehicle 1 remain retracted, minimizing aerodynamic drag during the maneuver. Upon completion of T5, the wings and air rudders are instantly deployed.

[0063] The principle and method of executing a launch mission from a surface ship inclined (30-45 degrees) launcher is consistent with the land / surface vertical launch method.

[0064] The present invention also has the following effects:

[0065] When launching from the surface, the booster engine is activated while the guided vehicle is in the launch tube to increase the speed of the guided vehicle out of the tube. The purpose is:

[0066] 1) Alleviate the angular motion disturbance of the guided vehicle during launch (or during launch) caused by vehicle turbulence;

[0067] 2) Reduce the time required for the guided vehicle to reach a safe distance (for the vehicle) after leaving the canister and complete a quick turn, which is particularly important for vertical launch guided vehicles;

[0068] 3) When the guided aircraft is launched at a small angle, it is beneficial for the guided aircraft to accelerate strongly and avoid "sinking" after launch.

[0069] At the same time, before the guided aircraft starts to move in the launch tube, the large and small thrust modes of the booster engine device must not be started, because this can cause a sharp increase in pressure in the limited bottom space of the transport launch tube.

[0070] During underwater launch, the time delay before the guided vehicle passes through the launch tube is related to the resultant force acting on the guided vehicle during underwater launch and its distribution characteristics. The time delay is based on the following considerations:

[0071] 1) Under current circumstances, there is no incentive to increase the exit speed of guided vehicles;

[0072] 2) When the launch tube is "unsealed" (when the airtight device of the guided vehicle pops out of the muzzle of the transport launch tube), try to avoid the guided vehicle being subjected to residual load. Because of the almost complete incompressibility of water, the increased pressure acts not only on the bottom of the guided vehicle, but also on the sides of the guided vehicle.

[0073] During underwater launches, when the guided vehicle emerges from the water, or during surface launches, activating the attitude control device within a predetermined time after the guided vehicle begins moving, and then separating the negative mass of the attitude control device forward in the direction of the guided vehicle's flight, are extremely important for ensuring the safety of the vehicle under various launch conditions.

[0074] The appropriate moment to start the high-thrust mode of the booster engine device (after the negative mass of the attitude control device is separated) is to reduce the required separation impulse and increase the speed of the guided vehicle as quickly as possible. Otherwise, if the timing of starting is not chosen correctly, the inertial force and velocity head that prevent the separation of the negative mass will increase exponentially, and the acceleration of the guided vehicle will be lost.

[0075] Finally, the method of launching guided vehicles from the surface at low horizontal angles has several unique characteristics: First, this method is primarily suitable for anti-ship cruise guided vehicles or air defense guided vehicle weapons deployed on small-displacement ships of the "light guided vehicle destroyer or guided vehicle cruiser" class. Second, in most cases, when using these ships, the guided vehicle does not need to make large azimuth turns, as the ship itself can easily occupy a favorable firing position during the firing preparation period, with the launch tube carrying the guided vehicle facing the target. Considering these factors, as well as the strong acceleration required for guided vehicles launched at low horizontal angles, the method does not require the use of attitude control devices. The unused negative mass of attitude control devices will separate from the guided vehicle during its movement within the launch tube. This method facilitates the rapid activation of the booster engine unit's high thrust mode, thereby ensuring the high thrust-to-weight ratio required for subsequent guided vehicle acceleration.

[0076] The following is an example of a universal device for launching and turning a guided aircraft according to the method proposed above, with reference to the accompanying drawings. The example is only used to explain the present invention and is not intended to limit the scope of the present invention.

[0077] like Figure 4 As shown, a guided aircraft 1 with foldable wings is placed in a transport launch tube 2, which is a solid-bottomed cylindrical structure. The launch system for the guided aircraft 1 includes a propellant accumulator 12 for auxiliary launch, a universal launch and turning mechanism consisting of a booster engine 13 and a turning attitude control device 14, as well as electrical equipment (including sensors for the guided aircraft's water and tube exit). The propellant accumulator 12, mounted at the bottom of the transport launch tube 2, generates high-pressure combustion gas to propel the guided aircraft 1 within the tube.

[0078] The booster motor assembly 13 primarily consists of four low-thrust solid motors 16 and one high-thrust solid motor 17. The four low-thrust solid motors are evenly spaced around the nozzle of the high-thrust solid motor and are bundled in parallel. The entire assembly is designed as an integrated, independent module and is mounted to the tail of the guided vehicle 1 using explosive screws. After completing its mission, the booster motor assembly 13 separates from the guided vehicle 1 during flight, without compromising the safety of the launch platform. A detachable electrical socket 18 is also installed on the housing of the booster motor assembly 13, allowing communication between the onboard control system and the ship's weapon control system.

[0079] The turn attitude control system 14 primarily consists of a set of pulsed solid-state motors and electronic control equipment (including an inertial measurement unit, etc.). Each motor functions independently as an actuator, providing the thrust required for turn attitude adjustment and system separation. For example, there are a pair of yaw motors 20 responsible for yaw control, a pair of pitch motors 21 for pitch control, four roll motors 22 for roll control, and a pair of separation motors 23 for separation control. Each component is mounted on the housing 19. The system is an integrated, independent module designed to be installed on the nose of the guided vehicle 1 using shear screws or explosive screws, allowing it to be separated from the guided vehicle 1.

[0080] When launching the guided aircraft 1 according to the method recommended above, the working procedure is as follows:

[0081] The gunpowder accumulator 12 works, generating high-pressure gas in the bottom space of the transport launch tube 2, which acts on the bottom of the guided aircraft 1. When the pressure at the bottom of the guided aircraft reaches the calculated value, the connecting parts that assist the guided aircraft 1 in maintaining the initial state are destroyed, the guided aircraft 1 starts to move, and the bottom electrical socket 18 is disconnected. This event is recorded by the control system as the basis for the start of T2. It can also be used as the starting time for calculating the start of the booster engine device 13 and the turning attitude control device 14 when implementing surface launch.

[0082] As mentioned above, the subsequent launch sequence is determined by the launch type symbol specified by the vehicle's weapon control system. For example, the most demanding "underwater vertical launch" method: When the tail of the guided vehicle 1 passes through the mouth of the transport launch tube 2, it is registered by sensors in the electrical equipment, and the four low-thrust solid fuel engines 16 are activated, propelling the guided vehicle 1 through the water at a moderate, almost uniform speed. The air rudders are deployed to ensure stable movement along the programmed underwater trajectory. After the guided vehicle 1 emerges from the water and is registered by the sensors, the turn attitude control device 14 is activated. The control system verifies the real-time attitude of the guided vehicle 1 based on the estimated trajectory and issues an attitude adjustment command. Upon receiving the command, the turn attitude control device 14 operates individually or simultaneously, depending on the situation, to complete the guided vehicle 1's roll, pitch, or yaw movements, achieving a rapid turn toward the target. For example, to control the pitch of the guided aircraft 1, one of the pitch motors 21 is activated according to a control command. Under the action of the motor thrust, the angular velocity of the guided aircraft 1 in the pitch channel increases. The sensor transmits the attitude parameters of the guided aircraft 1 measured in real time to the control system. The control system calculates the activation time of the subsequent command based on the given inclination angle of the guided aircraft 1 and the attitude parameters measured by the sensor, and issues a command to activate the second pitch motor 21, thereby "suppressing" the angular velocity when the guided aircraft 1 reaches the desired attitude relative to the horizon. Similarly, the guided aircraft 1 uses similar control methods in the yaw channel and the roll channel. It should be noted that when controlling the guided aircraft 1 in the roll channel, a pair of roll motors 22 must be activated to generate positive and negative torques around the longitudinal axis of the guided aircraft 1. During the rapid turn process 8, the four low-thrust solid fuel engines 16 are continuously operating to offset the weight of the guided aircraft 1 and prevent it from "sinking" toward the water surface. After the turn is completed, the control system sends an instruction to start the separation engine 23, outputs an impulse to the turning attitude control device 14 along the flight direction of the guided aircraft 1, and the turning attitude control device 14 separates from the front of the guided aircraft 1, and then starts the high-thrust solid engine 17, and the guided aircraft 1 begins to accelerate rapidly. During this period, the stable movement of the guided aircraft 1 can be controlled by the gas rudder at the tail of the guided aircraft 1. When the flight speed is large enough, the attitude control of the guided aircraft 1 is completed by the air rudder.

[0083] Furthermore, according to the characteristics of different guided aircraft, functional modules in the turning attitude control device can be selectively installed to achieve specific functions. For example, in the water surface small horizontal angle (10-30 degrees) launch mode, target orientation is performed through a vehicle or launch platform. The guided aircraft does not need an attitude control device to perform large azimuth angle turns, and only the engine for separation is installed to further reduce costs.

[0084] According to the method recommended above, by adopting different action sequences and executing the equipment startup procedure of the launch system specified in the launch method recommended above, the guided aircraft is given the ability to be launched vertically or obliquely from different vehicles, as well as the ability to make a rapid turn after launch.

[0085] In summary, the present invention can guide the development of a fully universal guided aircraft that can meet the different requirements of modern conventional sea-based and land-based weapons, be widely adaptable to various types of vehicles, and fully demonstrate the advantages of universal weapons such as simple operation and low cost.

[0086] Beneficial effects brought by the technical solution of the present invention

[0087] The principles and methods of use of the universal guided aircraft launch and turning system proposed in this invention can guide the development of a fully universal guided aircraft that can meet the diverse requirements of launching guided aircraft in various vertical or tilted modes from most modern roadbeds, surface ships, underwater submarines, and other different vehicles, and can also achieve rapid turning of guided aircraft.

[0088] The present invention can guide the development of an integrated independent jettisonable device, realize external installation with a guided aircraft, greatly reduce the complexity of the interface design of the guided aircraft, and has a simple structure, convenient installation, and wide adaptability.

[0089] The present invention can realize specific functions (effects) of different types of guided aircraft by using the same launch and turning system according to different launch modes and different types of guided aircraft by selecting components in the system or simply changing the working procedures and operating methods of the components in the system, thereby greatly reducing mass production costs and reducing the difficulty of using the system in technical positions and vehicles.

[0090] In the present invention, the attitude control device autonomously and controllably separates from the head of the guided aircraft after completing a rapid turn of the guided aircraft, thereby ensuring the safety of the launch platform. The weight and volume of the entire guided aircraft are reduced by discarding the passive weight. The acceleration performance of the guided aircraft is greatly enhanced after the booster engine device (or main engine) is ignited during the air acceleration phase. The booster engine device can be optionally installed according to the characteristics of the guided aircraft. After completing the booster acceleration function, the booster engine device can separate from the tail of the guided aircraft during flight without affecting the safety of the launch platform. This further reduces the weight and volume of the guided aircraft, comprehensively improves the maneuverability and range of the guided aircraft, and thereby enhances the strike or defense capability of the guided aircraft.

[0091] The present invention provides a complete set of ideas for the roll-pitch-yaw control and separation control of the guided aircraft during the launch tube ascent phase, which can completely replace the gas generator + air rudder control method, effectively improve the harsh working environment of the air rudder, and after removing the gas generator and its accessories, the design complexity of the air rudder is reduced (for example, the internal flow channel of the rudder is removed, the thickness of the rudder root is thinned, etc.), while avoiding the problem of large thrust loss in the gas generator + air rudder method; and according to the characteristics of different guided aircraft, the functional modules in the attitude control device are selectively installed to achieve specific functions (for example, only the pulse engine for separation is installed), further reducing costs; the key points of the technical solution of the present invention are as follows:

[0092] This invention uses direct lateral force control technology based on attitude control engines to achieve rapid turns for guided aircraft, and innovates principles and methods such as working sequence and ignition timing. It can guide the development of a fully universal guided aircraft that can meet the diverse requirements of launching guided aircraft in various vertical or tilted modes from most modern roadbeds, surface ships, underwater submarines, and other different vehicles, and achieve rapid turns for guided aircraft.

[0093] The hardware device of the present invention adopts an integrated independent disposable module design and is installed externally with the guided aircraft, which greatly reduces the complexity of the guided aircraft design interface and has a simple structure, easy installation and wide adaptability.

[0094] The present invention can realize specific functions (effects) of different types of guided aircraft by using the same launch and turning system according to different launch modes and different types of guided aircraft by selecting components in the system or changing only the working procedures and operating methods of the components in the system, thereby greatly reducing mass production costs and reducing the difficulty of using the system in technical positions and vehicles.

[0095] In the present invention, the attitude control device autonomously and controllably separates from the head of the guided aircraft after completing a rapid turn of the guided aircraft, thereby reducing the weight and volume of the entire guided aircraft while ensuring the safety of the launch platform. After the booster engine device (or main engine) of the guided aircraft is ignited during the air acceleration phase, the acceleration performance is greatly enhanced. The booster engine device can be optionally installed according to the characteristics of the guided aircraft. After completing the booster acceleration function, it can separate from the tail of the guided aircraft during flight without affecting the safety of the launch platform. This further reduces the weight and volume of the guided aircraft, comprehensively improves the maneuverability and range of the guided aircraft, and thereby enhances the strike or defense capability of the guided aircraft.

[0096] The present invention provides a complete set of ideas for roll-pitch-yaw control and separation control during the ascent phase of a guided aircraft launch tube. It can completely replace the gas generator + air rudder control method, effectively improving the harsh working environment of the air rudder. After removing the gas generator and its accessories, the design complexity of the air rudder is reduced (for example, the internal flow channel of the rudder is removed and the thickness of the rudder root is thinned), while avoiding the problem of large thrust loss in the gas generator + air rudder method.

[0097] The technical problem to be solved by the present invention is:

[0098] A launching and turning principle and method for guided aircraft are proposed, which can meet the different requirements of launching guided aircraft in vertical or inclined modes from most modern roadbeds, surface ships, underwater submarines and other different vehicles, and realize the all-round rapid turning of the guided aircraft toward the target direction after launch, which can guide the development of a fully universal guided aircraft.

[0099] Guide the development of a universal and standardized launching and turning device to solve the problems of high mass production costs and the difficulty of using various traditional devices in technical positions and vehicles;

[0100] Solve the problem of safe and reliable separation of the device from the guided aircraft after use, reduce the weight and volume of the guided aircraft during flight, and improve the maneuverability and range of the guided aircraft;

[0101] The present invention can replace the traditional control method of gas generator + air rudder, and solve the problems of complex structure, harsh working environment of air rudder, high complexity of rudder design, large thrust loss, and high cost.

[0102] Main idea of the present invention

[0103] The present invention relies on a universal device for launching a guided aircraft from a transport launch tube. The device primarily includes a booster engine unit and a rapid turn attitude control unit (abbreviated as attitude control unit). The booster engine unit is mounted at the tail of the guided aircraft, while the attitude control unit is mounted at the nose of the guided aircraft.

[0104] The booster engine assembly has dual modes: high-thrust and low-thrust. The high-thrust mode can be achieved using a high-thrust solid engine, while the low-thrust mode can be achieved using multiple low-thrust solid engines bundled in parallel or in a gas generator + tail nozzle format. The potential of the booster engine assembly can be rationally utilized based on the actual needs of the guided aircraft. The low-thrust mode can reduce the load on the guided aircraft during underwater movement, while the high-thrust mode can provide the high thrust-to-weight ratio required for surface launches. After use, the booster engine assembly can be separated from the guided aircraft to reduce the flight weight of the guided aircraft. Alternatively, it can be omitted based on the characteristics of the guided aircraft. For example, a guided aircraft with a relatively small weight and a short range has a high initial velocity upon exiting the tube, and sufficient turning time during the ascent phase in the air, eliminating the need for additional thrust to keep the guided aircraft suspended in the air.

[0105] The attitude control device is based on the direct force control method of the pulse engine, which directly generates a large thrust on the guided aircraft in a short period of time, so that the guided aircraft can achieve a large maneuver turn instantly after launch and quickly enter the kinematic trajectory. After completing the turn, it can autonomously separate from the guided aircraft, reducing the flight weight of the guided aircraft, thereby achieving the purpose of improving the guided aircraft's maneuver combat (rapid response) effectiveness and survivability.

[0106] The present invention can achieve specific functions (effects) for different types of guided aircraft by varying the operating procedures and methods of operation of the components of the aforementioned universal device, depending on the launch method and the type of guided aircraft. The principles and methods of use of the present invention are described in detail below with reference to the accompanying drawings. The examples provided are intended only to illustrate the present invention and are not intended to limit its scope.

Claims

1. A method for launching and rapidly turning a guided aircraft, wherein a booster engine device (13) is sealed and connected to the tail of the guided aircraft (1) by explosive screws, characterized in that: The following steps are included: Step 1: Install a turning attitude control device (14) at the front end of the guided aircraft (1), wherein the end of the guided aircraft (1) is inserted into the internal space of the turning attitude control device (14), so that the annular lower end of the turning attitude control device (14) and the upper outer wall of the guided aircraft (1) are sealed and installed together with explosive screws; wherein the turning attitude control device (14) includes at least a pair of separate engines (23), and the jet ports of the separate engines (23) are installed on the inner wall of the turning attitude control device (14) and can jet directly behind the moving direction of the guided aircraft (1); Step 2: Install the guided aircraft (1) with the turning attitude control device (14) installed at the end into the transport launch tube (2) in the launch device (3); during launch: the gunpowder pressure accumulator (12) at the bottom of the transport launch tube (2) starts to work, and the gunpowder pressure accumulator (12) generates high-pressure gas in the bottom space of the transport launch tube (2). The high-pressure gas acts on the bottom of the guided aircraft (1), and the guided aircraft (1) starts to move in the transport launch tube (2); Step 3: After the guided aircraft (1) moves in the transport launch tube (2), the control system of the guided aircraft (1) determines the timing of starting the low-thrust mode of the booster engine device (13) according to different launch modes; Step 4: When the guided aircraft (1) reaches a set altitude, the control system of the guided aircraft (1) decides whether to activate or deactivate the turning function of the turning attitude control device (14) according to different launch modes; the turning attitude control device (14) performs attitude control actions according to the direction specified by the flight mission until a rapid large-angle turn is completed, or the turning attitude control device (14) remains inactive; Step 5: After the guided aircraft (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 aircraft (1), so that the turning attitude control device (14) is separated from the guided aircraft (1) and ejected forward and downward to its subsequent flight trajectory; Step 6: After the turning attitude control device (14) is separated, the high-thrust mode of the booster engine device (13) is immediately turned on, and the guided aircraft (1) is rapidly accelerated and continues to fly along the programmed trajectory; after the guided aircraft (1) is accelerated to a speed capable of starting the ramjet engine, the explosive bolts connecting the guided aircraft (1) and the booster engine device (13) are detonated, the booster engine device (13) is thrown away, and then the ramjet engine is started to propel the guided aircraft to complete the cruise flight along the predetermined trajectory.

2. A method for launching and rapidly turning a guided aircraft according to claim 1, characterized in that: When the guided aircraft (1) is vertically launched from an underwater submarine, the launch cabin cover is first opened before the guided aircraft (1) starts to move in the launch tube in step 2; In step 3, when the tail of the guided aircraft (1) passes through the launch tube, the booster engine device (13) is turned on to operate in a low-thrust mode; at the same time, the guided aircraft (1) quickly opens the air rudder and the bomb wing, and then enters step 4; When the guided aircraft (1) reaches the set altitude in step 4, the set altitude is above the water surface.

3. A method for launching and rapidly turning a guided aircraft according to claim 1, characterized in that: When the guided aircraft (1) is launched at a small horizontal angle of 10° to 30° from a surface ship, in step 3, after the guided aircraft (1) moves in the transport launch tube (2), the booster engine device (13) is immediately turned on to work in a low-thrust mode; the turning function of the turning attitude control device (14) described in step 4 is not started, and the process directly enters step 5; in step 5, after the guided aircraft (1) is adjusted to the direction specified by the flight mission, the adjustment to the direction specified by the flight mission is to implement a target course turn through the ship together with the canister bullet rigidly connected thereto, or the rotary launch device equipped with the canister bullet turns toward the target; the separation engine (23) in the turning attitude control device (14) described in step 5 is started when the guided aircraft is moving in the launch tube; after the booster engine device (13) is turned on in a high-thrust mode, the guided aircraft simultaneously opens the air rudder and the missile wing to ensure that the guided aircraft moves stably on the subsequent trajectory.

4. A method for launching and rapidly turning a guided aircraft according to claim 1, characterized in that: When the guided aircraft (1) is launched vertically on land or water, in step 3, after the guided aircraft (1) moves in the transport launch tube (2), the booster engine device (13) is immediately turned on to operate in a low-thrust mode; in step 4, the turning attitude control device (14) performs attitude control until the rapid and large-angle turn is completed, and then the air rudder and the wing of the guided aircraft (1) are opened to ensure that the guided aircraft (1) is subjected to less aerodynamic resistance during the rapid and large-angle turn.

5. A guided aircraft launching and rapid turning method according to claim 1, characterized in that: When the guided aircraft (1) is launched at a relatively large horizontal angle of 30° to 45° from a surface ship, in step 3, after the guided aircraft (1) moves in the transport launch tube (2), the booster engine device (13) is immediately turned on to operate in a low-thrust mode; the turning attitude control device (14) described in step 4 performs attitude control until the rapid large-angle turn is completed, and then the air rudder and the wing of the guided aircraft (1) are opened to ensure that the guided aircraft (1) is subjected to less aerodynamic resistance during the rapid large-angle turn.

6. A method for launching and rapidly turning a guided aircraft according to claim 1, characterized in that: The turning attitude control device (14) further comprises a yaw control engine (20), a pitch control engine (21) and a roll control engine (22).

7. A method for launching and rapidly turning a guided aircraft according to claim 1, characterized in that: The booster engine device (13) comprises a low-thrust solid engine (16) and a high-thrust solid engine (17).

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