RU2096721C1 - Method of ground or water surface launch of rocket with control system and device for its realization - Google Patents

Abstract

FIELD: rocket engineering. SUBSTANCE: for increase of mobility and combat invulnerability of rocket complexes with ground or water-surface launching it is proposed to carry out preliminary tossing up of launcher with rocket into air with subsequent stabilization, turn and control over them and over exit of rocket from launcher. For realization of proposed method there are provided system of deflection of launcher with rocket from carrier, system of stabilization, turn and control over launcher with rocket. Proposed method and device for its realization make it possible to ensure launching of rocket under any angle to plane of horizon at initial position of launcher with rocket and independent of condition of surface where launching position is located. EFFECT: increased mobility and invulnerability of rocket complexes. 2 cl, 6 dwg

Description

 The present proposal relates to the field of rocket technology and describes a new method for surface or surface launch of a rocket with a control system.

 Currently known methods of launching missiles with a control system are mainly based on the launch of missiles from the launcher, which is installed and mounted on the carrier. In the process of a rocket leaving the launcher, its mechanical connection with the carrier can either be maintained or modified, but it must exist.

The launcher can be in the transport position, and before the start of the rocket it can be transferred to the launch (for example, RK "Redut";RK-55; SAM "Krug"; SAM "Kub"; S-300V, etc.). [1, p. 51, 52, 89, 91, 95]
It is possible to permanently place the launcher on the carrier at a certain angle to the horizon (for example, most ship installations).

 The rocket launch methods used in all of the above options are based on the fact that the rocket starts from a launcher that is mechanically connected to the carrier or (and) to the surface on which it is located. Obviously, in this case, the possibility of launching a rocket is determined both by the state of the carrier (serviceability of the carrier, the swing-lifting mechanism, etc.) and the state of the surface on which it is located (ground strength, slope, etc. in the case of a ground launch , and in the case of a surface launch - a sea ball).

 These factors limit the scope of missile weapons and reduce its mobility and combat survivability.

 Consider, by way of example, the start method depicted in FIG. 1 and described in the book of B.I. Rodionov, N.N. Novichkov. Cruise missiles in a naval battle. M: Military Publishing House, 1987, p. 29.

 Rocket 1 starts from the launcher 2, rigidly mounted on the carrier 3 at an angle θ to the horizon plane. The media is on the surface 4. Start can occur when the media moves on the surface.

 The missile leaves the launcher launcher under the action of the thrust of the rocket engine, providing movement relative to the launcher located on the carrier.

 Due to the movement of the carrier on a non-smooth and unsteady surface at the moment of exit from the launcher, the rocket structure is loaded by reaction forces from the launcher moving together with the launcher, the values of which form the calculated case for the strength of the missile structure. As a rule, in order to reduce the weight of the rocket in this case, a restriction is imposed on the quality of the surface (for example, according to the semiteness of the sea) at the time of launch.

 In addition, to ensure the safe launch and non-splashdown of the rocket after exiting the launcher in stormy conditions, the angle q is forced to be made as large as possible, which, in turn, leads to a high location of the launcher's center of mass and reduces the stability of the carrier on a non-smooth and unsteady surface.

 Thus, the method of launching a rocket imposes restrictions on the quality of the surface on which the carrier is located and reduces the mobility and combat survivability of the missile system.

Known methods of launching a rocket from a launcher placed on a ship or land vehicle. Start can be carried out with the movement of the medium. The rocket leaves the launcher (launcher) under the influence of the thrust of the rocket engine, providing its movement relative to launcher located on the carrier [2]
Known launch methods reduce the scope of missile weapons due to restrictions imposed on this area by the state of the carrier and the surface on which it is located. The creation of promising missile systems requires continuous improvement of launch methods in order to ensure the largest possible area of application by eliminating as many restrictions as possible, provided that the missile has high flight and technical characteristics.

 The expansion of the scope increases the mobility and combat survivability of the missile system. It follows that the best way to launch a rocket will be one that will allow the effective use of missile weapons in all conditions of the carrier and the surface on which it will be.

 To achieve this, it is proposed to launch a rocket with a control system into three parts: separation of the launcher (launcher) from the carrier by tossing it into the air, stabilization, turning and controlling the launcher-launcher system during the toss, and the missile leaving the launcher located in the air by pushing them apart.

 This method of launching is reminiscent of a ball in sports games, when a player tosses the ball into the game, first throws him up and then strikes him.

 Considering the sports associations that arise when considering this method, and the fact that the launch of the rocket occurs from above, as well as considering that the proposal relates to the field of missile weapons, the proposed launch method can be called a Smash type method (destroy the enemy, strong hit from above).

 For example, we give a quantitative assessment of the required efforts for the free movement of launchers with a rocket in the direction opposite to the action of gravitational forces.

 Suppose that the weight of the launcher with a rocket is 4000 kg, length 8000 mm, diameter 700 mm.

 To ensure the safety of the carrier, we assume that the missile exit from the launcher in the air should occur at a distance of 15 m behind the carrier and at a height of 20 m

 Let us assume that from the moment of the launch of the launcher to the launch of the rocket from it, a time of about 2 s must pass.

 Based on the accepted conditions, the ejection force should be about 3000 kg in the horizontal and 8000 kg in the vertical direction. In this case, the velocity of the launcher at the time of the launch of the rocket will be about 25 m / s.

If we assume that a solid propellant jet engine will be used to create the force, then its required thrust should be 8500 kg, its vector is directed to the center of mass of the rocket launcher, and the nozzle installation angle relative to the vertical plane is 20 ^o .

где R тяга двигателя; t время его работы;
j -единичный импульс двигателя, с.The stock of solid fuel of such an engine will be:

where R is the engine thrust; t time of his work;
j is the unit impulse of the engine, sec.

где V_т плотность топлива, кг/м³; K_з коэффициент заполнения.Engine capacity will be:

where V _{t the} density of the fuel, kg / m ³ ; K _s fill factor.

 We assume that the diameter of the engine is 0.3 m, then its length will be about 0.85 m.

 The obtained estimate of the dimensions of the engine, taking into account the geometric characteristics of the launcher, shows the reality of achieving the specified parameters in range and height from the carrier at the time the rocket leaves the launcher.

 It should be noted that after the tossing of the launcher, perturbations will act on it, both caused by the spatial movement of the carrier (initial conditions), and acquired from the transmission error of the throwing force. For example, errors in the installation of outboard motors.

 To parry these disturbances in order to stabilize the launcher with the missile during the toss, it is proposed to use a system of autopilot and inertial navigation of the rocket.

 The angular velocities relative to the stabilization planes of the "PU rocket" system are recorded by the angular velocity sensors located in the instrument compartment of the rocket and enter the on-board computer.

 In addition, to ensure a given spatial position of the launcher at the time of the start relative to the movement of the rocket, a system of autopilot and inertial navigation of the rocket is also used. This problem is solved in conjunction with the task of stabilizing launchers with missiles.

 In the on-board computer, according to a special algorithm, a total control signal is generated based on the stabilization conditions of the "PU rocket" system and ensuring its spatial position specified before the start at the time the rocket starts to move relative to the PU.

 The total control signal is supplied to the control equipment for switching on devices located on the control panel.

 Devices create short-term impulses of forces, providing the necessary control moments of forces relative to the center of mass of the launcher with a rocket to parry these disturbances and ensure a given spatial position.

 Actuators can be, for example, jet engines.

 For example, we give a quantitative assessment of the mass characteristics of jet engines. To solve the problem of stabilization and reversal of launchers, we use the above example.

Let the moments of inertia of the launcher with the rocket relative to the central axes OY and OZ be equal, J _y J _z 16,000 kg • m ² , and the moment of inertia of the launcher with a rocket with respect to the central axis O _x , J _x 123 kg • m ² .

We assume that the error in installing the outboard motor relative to the center of mass along the roll is 2 mm, then
M _prob 8500 • 0.002 17 kgm
Then the thrust of the jet engine will be 50 kg.

 Suppose that the action of this force to compensate for roll disturbance will continue for one second, then the solid fuel supply will be 0.25 kg.

Suppose that a missile launcher with a missile is launched from the surface of a carrier having an angular velocity in the vertical plane of 1.4 s ^-1 . To counter this disturbance, it is necessary to have a control torque of 2300 kgm, and a draft of 575 kg. The stock of solid fuel will be 5.7 kg.

 Suppose that in the horizontal plane the perturbation is similar to the vertical one. Then the supply of solid fuel necessary to parry the disturbance in the horizontal plane will be 5.7 kg.

Assume that the required turn in the horizontal and vertical planes is 180 ^o . Then, the required supply of solid fuel for its implementation will be 6 kg for each of these planes.

Thus, summing up the required reserves of solid fuel for stabilization and reversal of launchers with a missile and, given the need to double this reserve due to the specifics of using jet engines of solid fuel, we obtain:
G _t 2 (0.25 + 5.7 + 5.7 + 6.0 + 6.0) 47.8 kg.

The required volume for the placement of this fuel will be 0.035 m ³ , which is about 1% of the volume of PU with a rocket.

 It should be noted that in the examples cited, the total weight of the withdrawal, reversal, and stabilization engine is about 200 kg, which is significantly less than the weight of the lifting and swinging mechanisms of modern PUs.

 The above examples show the reality of the proposed method of start.

 The proposed method for surface or surface launch of a rocket with a control system is shown in FIG. 2.

 The carrier 1 with PU 2 and rocket 3 is located on surface 4.

 At the “Start” command, the force F begins to act on the launcher from the rocket, ensuring the launcher’s free movement in the opposite direction to the gravitational forces G.

Having the given conditions of the spatial position of the launcher with the rocket at the moment the rocket begins to move relative to the launcher (for example, the angle θ), and also knowing the actual values of the angular velocities w _x , ω _y , ω _{z, the} on-board missile computer generates the total control signals for each stabilization plane YOZ, YOX, XOZ.

These signals cause the action of short-term pulses of forces F _y1 , F _y2 , F _x1 , F _x2 , F _z1 , F _z2 in such a way as to fend off perturbations acting on the rocket launcher, trying to ensure minimum angular velocities and achieve a given angle θ
When the desired orientation of the launcher with the missile is achieved, the on-board equipment of the missile generates a signal that starts the rocket engine and starts moving relative to the launcher.

 The proposed launch method allows the use of a missile system regardless of the state of the carrier and with any quality of the surface on which it is located.

 This becomes possible due to the absence of any PU bonds with the carrier after tossing it into the air.

It becomes possible to start from the transport horizontal position under conditions of carrier movement, both in combat condition and in a relocation state, while ensuring at the initial moment of flight any angle of rocket pitch, up to 90 ^o , regardless of the initial position of the launcher in space.

 This quality does not have any of the known methods of launch.

 When placing a missile system on a ship, this method allows implementing the below-deck placement of launchers in their horizontal position, which increases the combat survivability of the complex even when it is used on small missile ships.

 It becomes easier and safer to solve the problem of emergency missile ejection.

 Increased combat survivability is associated with the ability to use a missile system in conditions of damage to the ground carrier.

 Thus, a method of surface or surface launch of a rocket with a control system based on the use of moving the launcher to the starting position without mechanical connections with the carrier by means of a force (for example, engine traction), the direction of which is opposite to the action of gravitational forces, followed by the rocket leaving the launcher located in the air, allows you to increase the mobility and combat survivability of the missile system, as well as expand the capabilities of its combat use.

 PU missiles is one of the main elements of the missile weapons complex and determines such important parameters of the missile complex as mobility and combat survivability.

The development of technology has led to the creation of launchers in which the rocket is stored, transported, and from which it starts. The most common type of such PU devices has become a transport and launch container (TPK). It is a sealed cylindrical structure, inside which a rocket is placed on the guide surfaces. This type of launcher was used in many missile systems, both tactical and strategic, (Pioneer, Topol, Redut, RK-55, etc.) [1, p. 22, 25, 51, 52]
Many launchers of naval missile systems are made according to a similar scheme (P-15, P-35, Uranus, etc.) [1, p. 57, 60, 65]
All of these types of PU are TPK, mechanically associated with the carrier at the launch of the rocket.

 This circumstance limits the scope of the missile system due to the effect on the launching rocket of the quality of the surface where the carrier is located (slope of the launch pad, ground strength, sea level, etc.).

One of the successful design of PU today can be considered PU missile system S-300V [1, p. 95]
PU is placed on a caterpillar carrier 1 and contains TPK with a rocket 2, a lifting mechanism 3, a rotary truss 4, on which TPK is installed (see Fig. 3).

 In the transport state, the TPK is in a horizontal position. To transfer the TPK to the starting position, the lifting mechanism rotates the TPK with the rocket into a vertical position. In the launcher of the described type, it is possible that when the missile starts, the TPK freely moves in the vertical direction, settling on the soil 5. The transverse forces acting on the TPK are perceived by the attachment points and transferred to the carrier.

 The start can be carried out by starting the powder pressure accumulator 6 and increasing the pressure in a given space 7.

 This design of the launcher allows you to achieve a minimum launch impact on the carrier, and the vertical position at launch provides the ability to effectively use the missile system in any direction in azimuth when there is no rotary device in the horizontal plane on the launcher.

 This launcher does not allow rocket launch during carrier movement, with large slopes of the surface on which the launcher is located, from the transport position of the launcher. It has low stability against possible disturbances when the launcher with the missile is in the starting position due to the high location of the center of mass of the carrier-PU system.

 In case of damage to the carrier (for example, a failure of its engine), it is not possible to transfer the launcher from the transport position to the starting position. The use of the missile system is limited by the strength of the launch pad soil. The launch of the rocket is possible only with the vertical position of the launcher.

 These shortcomings limit the scope of use of weapons, reduce the mobility and combat survivability of the missile system, and also do not allow for the launch of a rocket at any angle to the horizontal plane at any initial launch position.

 In order to eliminate these shortcomings, a missile launcher launcher with a ground or surface launch is proposed, containing TPK, TPK with a missile removal system from the carrier, TPK deployment and stabilization system with a rocket in the air, TPK and missile separation system.

 On the TPK case, a system for removing its rocket from the carrier is fixed, made, for example, in the form of a jet engine, the nozzle axis of which is located at an angle to the longitudinal axis of the TPK, and a stabilization, rotation and control system for the TPK with a rocket in the air, made, for example, is fixed in the form of jet engines, the axis of the nozzles of which are transverse to the longitudinal axis of the TPK, and containing devices for turning on these engines.

The proposed PU is based on the use and integration of scientific and technical backlog available in the following similar directions:
the solution of the problem of withdrawal or separation of the various stages of the rocket with their parallel arrangement;
solving the problem of the turn and stabilization of a vertical take-off and landing aircraft in the air in the absence of wing lift and the inefficiency of aerodynamic controls;
the solution of the problem of separation of the rocket with the capsule in the air in the case of placement and storage on the carrier of the rocket in the capsule and their joint launch.

 The proposed PU is shown in FIG. 4, 5, 6.

On carrier 1 (car, ship) is PU, which includes:
TPK 2 with support rails in the form of a cylindrical surface;
a TPK removal system with a rocket from the carrier in the form of a jet engine 3 fixed to the TPK;
the rotation and stabilization system of the TPK with a rocket in the air, which is a set of jet engines 4, 5, 6 fixed to the TPK, the axis of the nozzles of which are directed across the longitudinal axis of the TPK, and also containing control equipment 7 for turning on these engines;
separation systems TPK and rockets in the form of a powder pressure accumulator 8, mounted inside the TPK between the rear end of the rocket 9 and the bottom 10.

 At the command "Start" the jet engine of the withdrawal is started. Under the influence of traction TPK begins to move freely in the air, having no connection with the carrier.

 The perturbations acting on the TPK and obtained due to the error in installing the withdrawal engine and determining the center of mass 11 are countered by the operation of the rotation and stabilization engines according to bank 4, pitch 5, and heading 6. These engines provide the specified conditions for the spatial position of the TPK with a rocket at the time the rocket starts moving relative to the TPK.

 The start of these engines is carried out with the help of equipment for their inclusion, which is connected via electrical harnesses 12, on the one hand, to the engines and, on the other hand, to the onboard equipment of the rocket control system.

 The reversal and stabilization system can be built on inkjet control devices.

 After moving to a safe distance from the carrier, reaching the desired angle between the axis of the TPK and the horizon plane and the specified azimuth of firing, the powder pressure accumulator is activated. In the bottom space of the TPK, the pressure rises, there is a force that separates the TPK from the rocket. The rocket engine starts and its flight begins.

 The proposed PU is devoid of those disadvantages that are inherent in PU of the considered type.

The proposed PU allows you to start:
when the carrier moves;
at any slopes of the surface on which the carrier is located;
from the transport state of the medium;
at any angle to the horizon plane at any initial position of PU;
in case of damage to the media;
at any strength of the soil;
from direct starting positions.

 The use of the proposed PU in the ship version is safer than vertically installed PU. In addition, at the start there are no restrictions on the severity of the sea. The task of ensuring a safe emergency release of missiles is much simpler.

 Taking into account the indicated advantages of such a method of launching a rocket, as well as a device for its implementation, it can be assumed that in the future this method will become a widespread method of launching missiles at ground and sea based carriers and will open up possibilities for further improving the effectiveness of missile systems.

Claims (2)

 1. A method of surface or surface launch of a rocket with a control system, comprising launching the rocket from the launcher, for example, under the influence of engine thrust, characterized in that the launcher is pre-selected with a missile in the air with subsequent stabilization, rotation and control, for example pulsed motors, the thrust of which is directed across the axis of the launcher with a rocket.  2. A device for implementing the method of surface or surface launch of a rocket with a control system, including a transport and launch container with a missile, mounted in a horizontal position on the carrier, characterized in that on the body of the transport and launch container is fixed a system for removing it from the carrier from the carrier, made , for example, in the form of a jet engine, the axis of the nozzle of which is located at an angle to the longitudinal axis of the transport and launch container, and a stabilization, reversal and control system for the trans Taylor and launch container with a rocket in air, made, e.g., in the form of jet fuel, which nozzle axis disposed transversely to the longitudinal axis of the transport and launch container, and comprising a device incorporating these engines.

Images