Method of control of travel of space liquid-fuelled rocket after command for disabling of mid-flight engine of burnt-out stage

FIELD: aircraft engineering.

SUBSTANCE: invention can be used for control of travel of space liquid-fuelled rocket (SLFR). After the command for disabling of the mid-flight engine (MFE) of the burnt-out stage MD is switched to the reduced-thrust stage and MD is completely disabled, the rolling travel of the rocket is controlled using two pairs of gas nozzles, the moment of MD final disabling is forecasted, one of pairs of gas nozzles is enabled before the forecasted moment of MD final disabling for creation of the control rolling moment, the pair of gas nozzles are disabled at forecasted moment, and the value of the period of work of pair of gas nozzles is determined before the flight depending on the moment of inertia of the rotating part of the turbo-pump unit with the allowance for attached mass of fuel components with reference to the axis of rotation, an absolute value of the roll moment, created by each pair of the gas nozzles at their enabling, an absolute value of angular speed of rotation of the turbo-pump unit rotor at the reduced-thrust stage, angle between the axis of rotation of the turbo-pump unit rotor and the longitudinal axis of the rocket.

EFFECT: invention allows to improve safety of SLFR flight.

1 dwg

 

The invention relates to rocket and space technology, namely to methods of motion control liquid space rocket (ILV) on the flight phase after the command on off switch mounted in the gimbal of the main engine (MD) spent the ILV stage and before the separation of that degree.

In rocket technology known selected as a prototype method of controlling liquid movement ILV after a shutdown command and the MD exhaust stage, consisting in the translation of the CBMs at reduced thrust, and the final shutdown of the CBMs by stopping delivery of the fuel components in the combustion chamber [1].

The disadvantage of this method is that its implementation operates on the ILV disturbing moment, which can lead to LV twist around its longitudinal axis. This point, due to the braking of the rotating parts of the turbopump Assembly (TNA) and carries their weight fuel components.

To parry disturbing moments on a roll at LV tandem layout mid-flight with one engine usually used for more steering motors or remote gas nozzle roll, which produces gas for the generator MD. However, the effectiveness of the gas nozzle is directly proportional to thrust sustainer engine and by the time that stops fridaysaturday TNA, and LV becomes the maximum angular velocity about the roll, the gas nozzle are already inefficient and not able to fend off the perturbations caused by the rotation of the LV around its longitudinal axis. Therefore, given the systematic nature of the disturbance, opposing him from the moment of the gas nozzle must be created in advance.

The object of the present invention to provide a method for motion control of LV after a shutdown command and the MD exhaust stage, providing counteracting the disturbing torque due to the braking of the rotating parts of TNA and thereby prevents undesirable twisting of the LV on the roll, which in combination with other adverse conditions may result in "folding" part of the gyrostabilized platform and emergency flight termination ILV.

The technical result of the invention is to increase the safety of the flight to LV.

Said technical result is achieved in that in the method of controlling the movement of liquid ILV after a shutdown command and the MD of spent stages, including the translation of CBMs for reduced thrust and the final shutdown of the CBMs by stopping delivery of the fuel components in the combustion chamber, in accordance with the invention, in the case where the motion control ILV roll OS�carried out using two pairs of gas nozzles, gas to the gasifier which produces MD, carried out at the beginning of the forecast time (t0final cutoff MD, in advance, a time interval (Δt) to the predicted point in time (t0final shutdown of the CBMs include one pair of gas nozzles, creating a control torque roll, the sign of which is opposite to the sign of the angular velocity of rotation of the rotor TNA, then turn off the specified pair of gas nozzles in the predicted time (t0), while the value of time interval (Δt) of the work of this pair of gas nozzles is determined before the beginning of the missile by the formulawhere IP- the moment of inertia of the rotating parts of the TNA with regard to added masses of propellant relative to the axis of rotation,MX- the absolute value of the roll moment created by each pair of gas nozzles at their inclusion, Ω is the absolute value of the angular velocity of rotation of the rotor turbopump on the reduced thrust, φ is the angle between the axis of rotation of the turbopump rotor and the longitudinal axis of the LV.

The essence of the invention is illustrated in Fig.1.

Fig.1 - typical dependence of the parameters of angular motion of the LV from time after a shutdown command and the MD.

As an example, consider a possible implementation of the proposed method of control of SR light class t�PA Korean missiles "KSLV-I". The combustion of the sustainer stage I engine this LV is installed in the gimbal. Motion control of LV in pitch and yaw is accomplished by deflection of the camera by means of two electro-hydraulic servos. To control the movement of the roll used 4 gas nozzle, which are included in pairs. At the end of stage I and the control system sends the command to shut down its MD, after which the engine is transferred to the reduced thrust (finite thrust - KCT), constituting 38% of nominal. In this mode, you can still control the movement of LV in pitch and yaw by turning the combustor MD. In the channel of the roll mode, the FTC used the gas nozzle, albeit with reduced efficiency. The turbopump rotor, feeding fuel components into the combustion chamber, on the mode of KST rotates with angular velocity Ω≈12600 rpm, the angle between the axis of rotation of the rotor and the longitudinal axis of the LV is φ=6°. Rotating turbopump possess angular momentum (kinetic), the projection of which on the longitudinal axis of SR is equal to K1=IPΩcosφ, where IP- the moment of inertia of the rotating parts of the turbopump relative to the axis of rotation with regard to added masses of propellant (mass components between the shoulder blades pump the fuel and oxidizer), approximately equal to the 0.375 kg·m2.

When finished�relatively off the MD stops supply of the fuel components in the combustion chamber. Angular velocity of rotation of the rotor turbopump approximately 0.9 to fall to zero. The law of conservation of angular momentum of a closed system of LV-turbopump rocket will acquire angular momentum relative to the longitudinal axis, is equal to K2=IXωX0where IX- moment of inertia of LV relative to the longitudinal axis of approximately $ 16500 kg·m2at the end of the sustainer stage I engine. While (K2=K1, ie, LV, begin to rotate around the longitudinal axis with an angular velocity

For the numeric values of the parameters of the angular velocity of rotation will be about 1.7 g/S. For the repayment of this angular velocity must include one of the two pairs of gas nozzles, namely, that which generates control torque roll, the sign of which is opposite to the sign of the angular rotation speed of the turbopump. This pair of gas nozzles should be fixed on time

where MX- the absolute value of the roll moment created by each pair of gas nozzles at their inclusion (MX≈114 kg·m when running MD on the reduced thrust). For these parameter values, the inclusion of a pair of nozzles will be Δt≈0,44 S.

Therefore, in accordance with the method of control to prevent unwanted rotation of LV on the roll, it is proposed p�ed the beginning of the flight by the formula (2) to determine the duration of the time interval Δt, during which should work a pair of gas nozzles. In flight, at the end of stage I is the forecast of time t0the final engine is turned off. This prediction can be done either on the basis of information coming into the control system from the sensors of the levels of the oxidant and fuel, installed in the tanks of the rocket and allows to determine the mass of the remaining fuel components, either on the basis of a comparison of the current values of the trajectory parameters (speed, altitude, etc.) with their program values (method of implementation of the prognosis depends on the accepted principles of the system of missile guidance). After the time t0final off the MD predicted, in advance, for the time interval Δt to the time t0in accordance with the method of administration includes one pair of gas nozzles, creating a control torque required sign (opposite sign to the angular rotation speed of the turbopump). Off this pair of gas nozzles at time t0.

Fig.1 presents the results of mathematical simulation of angular motion of the LV in the channel of the roll, since the inclusion of a pair of nozzles roll. Shown:

- the time dependence of the angular velocity of rotation of the rotor TNA Ω·0.001, rad/s;

- the time dependence of the angular velocity in�of Amenia ILV roll (longitudinal axis) ω Xg/C;

- the time dependence of the roll angle γ LV, g;

- the time dependence of the team on the inclusion of one of the pairs of gas nozzles u (u takes on the values -1, 0, +1. u=-1 means includes a pair of gas nozzles, creating a negative point on a roll, u=0 means that the gas nozzle off). From Fig.1 shows that the proposed control method is already using 1.4 with after turning the gas nozzle reduces the angular velocity ωXalmost to 0, the absolute value of the roll angle γ LV does not exceed 1,1°.

Thus, thanks to the implementation proposed in the invention of the technical solution solves the problem of parry disturbing torque due to the braking of the rotating parts of TNA, and achieved technical result of the invention - improving the safety of flight ILV.

Sources of information

1. V. I. Fedoseev. Basic techniques of rocket flight. M.: "Nauka", 1981, p. 139.

A method of controlling liquid movement of a space rocket after a shutdown command and the sustainer engine exhaust level which contains the translation of the main engine at reduced thrust, and the final shutdown of the main engine by stopping delivery of the fuel components in the combustion chamber, characterized in that in the case where the motion control of the missile roll OSU�applied using two pairs of gas nozzles, gas to the gasifier which produces sustainer engine, carried out at the beginning of the forecast time (t0final shutdown of the main engine, in advance, a time interval (Δt) to the predicted point in time (t0final shutdown of the main engine, include one pair of gas nozzles, creating a control torque roll, the sign of which is opposite to the sign of the angular velocity of rotation of the rotor of the turbopump unit, then turn off the specified pair of gas nozzles in the predicted time (t0), while the value of time interval (Δt) of the work of this pair of gas nozzles is determined before the beginning of the missile by the formulawhere IP- the moment of inertia of the rotating parts of the turbopump unit with regard to added masses of propellant relative to the axis of rotation, MX- the absolute value of the roll moment created by each pair of gas nozzles at their inclusion, Ω is the absolute value of the angular velocity of rotation of the rotor of the turbopump unit at reduced thrust, φ is the angle between the axis of rotation of the rotor of the turbopump unit and the longitudinal axis of the rocket.



 

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