RU2584401C1 - Method of separating sustainer and device therefor - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: method of main propulsion stage SC separating includes mechanical retention in open state of start-up circuit igniter stage separation mechanism at start-up of aircraft on launch flight path segment. On board of aircraft in flight longitudinal acceleration and speed of its variation in time are measured, recording change of derivative sign longitudinal acceleration from negative to positive and close electric circuit of start stage separation mechanism electric igniter. Aircraft with separable engine comprises main propulsion stage and jointed to it engine with stage separation mechanism equipped with electric igniter. In main propulsion stage parallel to longitudinal axis of aircraft is actuator remote inertial action made in form of non-conducting housing with fixed contact group and conducting of inertial body locked power spring towards stage separation mechanism.

EFFECT: technical result is exclusion of improper separation of engine and main propulsion stage at preparation and checks of aircraft before start.

2 cl, 1 dwg

Description

The proposed group of inventions relates to military equipment, in particular to the field of rocket technology.

When you start the aircraft (LA) with a detachable engine, such as a rocket or rocket, it is necessary to ensure reliable separation of the engine from the sustainer stage after completion of its work. It is unacceptable both the early separation of the engine, when its fuel has not yet burned out and it is possible to catch up and hit the engine on the aft of the marching stage, and the late separation of the engine, in which the fuel is completely burned out, and there is no separation, which leads to a loss of aircraft speed due to drag caused by the presence of aerodynamic elements (engine) unnecessary for the further flight.

There is a method of separating the march stage of the projectile from the engine, in which when starting a rocket at the start of the flight path due to axial (longitudinal) acceleration of the projectile with the engine running, the start circuit of the electric igniter of the stage separation mechanism is mechanically held open, and at the end of the engine’s operation it is reset to zero and the longitudinal acceleration of the projectile reverses due to braking of the projectile by drag. At the same time, an electric circuit is formed, through which voltage is supplied to the electric igniter of the stage separation mechanism, which is triggered and the march stage is separated from the engine, RF patent No. 2167388, publication 05/20/2001, cl. IPC F42B 15/10 [1].

This method is implemented in an aircraft with a detachable engine containing a marching stage and an engine docked to it with a stage separation mechanism, in front of which a remote inertial action actuator is installed parallel to the longitudinal axis of the projectile, made in the form of a non-conductive housing with a fixed contact group, a conductive inertial body, lockable a power spring in the direction of the stage separation mechanism, while the inertial body is made in the form of a cylinder with an internal conical bore pation, passing into the cylinder, the inertial mass body and the spring force are calculated from the triggering conditions for the longitudinal acceleration determined by the formula

- продольное ускорение ЛА;Where $$\frac{F}{m}=d$$

- longitudinal acceleration of the aircraft;

F is the working force of the spring at the moment of closure;

m is the mass of the inertial body;

X _M is the drag force of the march stage at the time of engine separation;

G _M - mass march stage at the time of separation of the engine;

X _d is the drag force of the engine at the moment of separation of the march stage;

G _d - the mass of the engine at the time of separation of the marching stage [1].

Significant uncertainty of the initial data, drag forces X _M and X _d , technological dispersions of the masses of the march stage and the engine G _M and G _d do not allow establishing reasonable requirements for the elements of the actuator of inertial action, ensuring its reliable operation at the optimal time, which can lead to both to premature and delayed response.

, строго не обеспечивается соответствие момента выдачи сигнала на механизм разделения ступеней t_PC моменту окончания работы двигателя t_0дв, что может привести к раннему срабатыванию механизма разделения ступеней, догону и удару двигателем по корме маршевой ступени.In aircraft launches, the actuator of the remote inertial action will operate until the end of the engine t _0dv . The moment of operation of the actuator of the remote inertial action t _0im is the moment of issuing the signal to the stage separation mechanism t _PC , t _PC = t _0im . But since perhaps $$\left|t_{0\mathrm{and}m}-t_{0d\mathrm{at}}\right|>0$$

, the correspondence of the moment of signal output to the stage separation mechanism t _{PC to the} moment the engine _ends t _{0dv is} not _{strictly ensured} , which can lead to early operation of the stage separation mechanism, catch-up and engine blow to the aft of the march stage.

This situation can be eliminated if a signal to the stage separation mechanism is generated when the engine fuel is completely burned out and the engine thrust is finished falling, which corresponds to the lowest value of the longitudinal acceleration of the aircraft and the sign of the derivative of the longitudinal acceleration of the aircraft from negative to positive.

An abnormal situation is also possible when preparing and inspecting aircraft before launch. For example, from an accidental impact, a fall, the actuator of the remote inertial action will work, as a result of which the steps will be separated in preparation for launch at the moment of using power sources on board the aircraft.

Therefore, the objective of the proposed group of inventions is to eliminate the above disadvantages, namely: the elimination of abnormal separation of stages during pre-launch inspections and preparations of the aircraft, ensuring reliable operation of the mechanism of separation of the stages of the aircraft at the time of completion of the fall of the engine thrust, i.e. at the moment when the value of the longitudinal acceleration of the aircraft reaches its minimum value, the negative sign of the derivative of the longitudinal acceleration changes to positive and the march stage is separated from the engine without collision.

In the method of separating the marching stage of the aircraft from the engine, including mechanically keeping the start circuit of the electric igniter of the separation mechanism of the steps when starting the aircraft at the start of the flight path due to the longitudinal acceleration of the aircraft with the engine running, forming an electric start circuit of the electric igniter of the stage separation mechanism at the end of engine operation , applying voltage to the electric igniter of the stage separation mechanism, its operation and separation of the march stage from the engine At the same time, the task is achieved by measuring the longitudinal acceleration d on board the aircraft during the flight and determining its rate of change in time, fixing the moment t ₀ of the sign of the derivative of the longitudinal acceleration from negative to positive, at the moment t _0, closing the electric circuit for starting the electric igniter stage separation mechanism.

In an aircraft with a detachable engine containing a marching stage and an engine docked to it with a stage separation mechanism equipped with an electric igniter, an actuator of remote inertial action is installed in the marching stage parallel to the longitudinal axis of the aircraft, made in the form of a non-conductive housing with a fixed contact group and a conductive inertial body locked by a power spring in the direction of the stage separation mechanism, while the inertial body is made in the form of a cylinder with an internal With a conical hole passing into the cylinder, the task is achieved in that the marching stage is additionally equipped with a linear acceleration sensor in series, oriented by a sensitivity axis parallel to the aircraft’s longitudinal axis, an analog-to-digital converter and a computer, and to break an electric circuit between the remote inertial actuator and an electric igniter of the stage separation mechanism, a key controlled by the computer is installed, the first input of which is connected inen with the output of the calculator, the second input with the output of the actuator of the remote inertial action, and the output with the input of the electric igniter of the stage separation mechanism, while the mass of the inertial body and the power spring are calculated from the condition of operation of the inertial body at longitudinal acceleration

where d _hold is the longitudinal acceleration developed by the engine during its operation, minimally sufficient to mechanically hold the start circuit of the electric igniter of the stage separation mechanism.

The technical result is ensured by the fact that in the method of separating the marching stage of the aircraft from the engine on board the aircraft during the flight, the longitudinal acceleration d is measured and its rate of change in time is determined, the moment t ₀ of the sign of the derivative of the longitudinal acceleration is changed from negative to positive, in moment t ₀ closes the electric start circuit of the electric igniter of the stage separation mechanism.

For this, the march stage is additionally equipped with a linear acceleration sensor connected in series, oriented by the sensitivity axis parallel to the aircraft’s longitudinal axis, an analog-to-digital converter and a calculator, and a key controlled by the calculator is installed in the open circuit between the remote inertial actuator and the electric igniter of the stage separation mechanism, the first input which is connected to the output of the calculator, the second input to the output of the actuator dis antsionnogo inertial action, and output - with an input electric spark separation stages mechanism, wherein the inertial mass body and the spring force are calculated from the triggering conditions for the values of an inertial body longitudinal acceleration

0 <d <d _hold ,

where d _hold is the longitudinal acceleration developed by the engine during its operation, minimally sufficient to mechanically hold the start circuit of the electric igniter of the stage separation mechanism.

This technical solution is illustrated in the drawing.

The drawing schematically shows a block diagram of an aircraft with a detachable engine, where:

1 - aircraft;

2 - march stage;

3 - ADC;

4 - linear acceleration sensor;

5 - calculator;

6 - actuator remote inertial action;

7 - key;

8 - electric igniter;

9 - mechanism for the separation of steps;

10 - engine.

In the march stage (2) parallel to the longitudinal axis of the aircraft, an actuator of remote inertial action (6) is installed, the output of which is connected to the second input of the key (7), open in the initial state. When starting the aircraft (1) at the start of the flight path, the unit (6) monitors the amount of overload acting on the aircraft, and due to the longitudinal acceleration of the aircraft with the engine (10) in operation, mechanically keeps the circuit open, along which the voltage is generated at the output of the unit ( 6). The design of the block (6) is made in the form of a non-conductive housing with a fixed contact group, a conductive inertial body locked by a power spring towards the stage separation mechanism, while the inertial body is made in the form of a cylinder with an internal conical hole that passes into the cylinder.

Prior to the start and at the initial flight stage of the aircraft, the sequentially installed actuator of remote inertial action (6) and the key (7) reliably block the signal supply to the electric igniter (8) and the abnormal operation of the stage separation mechanism (9) on different physical principles. In addition, as shown above, the mass of the inertial body and its power spring cannot be unambiguously calculated by the formula (1). Therefore, the triggering condition of block (6) for calculating the mass of the inertial body and the force spring is determined by condition (2) in a rather wide range of longitudinal acceleration d, from 0 to d _hold .

At the end of engine operation (10), at the moment t _0dv, its thrust decreases and the longitudinal acceleration of the aircraft changes sign due to braking of the aircraft by drag. The most reliable and safe engine separation (10) should be carried out at time t _{0 of the} lowest value of the longitudinal acceleration of the aircraft and the negative sign of the derivative of the longitudinal acceleration of the aircraft to positive.

A linear acceleration sensor (4) is installed along the longitudinal axis of the aircraft in the march stage (2), which, during the flight of the aircraft, measures longitudinal acceleration and generates an analog signal proportional to longitudinal acceleration at the output. The output of block (4) is connected to the ADC (3), which for subsequent calculations converts the analog signal into a digital signal, which is fed to the computer (5). Block (5) at each current time step determines the value of the derivative of the longitudinal acceleration of the aircraft and compares it with the value of the derivative of longitudinal acceleration at the previous time step. At the same time, the output of the calculator (5) is connected to the first input (control input) of the key (7), at the second input of which there is voltage from the output of the actuator of the remote inertial action (6). Key (7) is open. According to condition (2), the mass of the inertial body and the power spring of the actuator of the remote inertial action (6) are calculated in such a way that the block (6) is activated and closed at a value of d> 0.

As the engine burns out and its thrust drops, the aircraft speed decreases, and the longitudinal acceleration becomes negative due to the braking of the aircraft by the incoming air flow.

At time t ₀ , when the engine fuel has completely burned out and the derivative of the longitudinal acceleration of the aircraft changes sign from negative to positive, block (5) generates a signal that arrives at the first input of the key (7), which closes. By this moment, the actuator of the remote inertial action (6) has already worked, voltage is present at the second input of the key (7) and an electric circuit is formed, through which the output of the key (7) is supplied with voltage to the electric igniter (8) of the stage separation mechanism (9). Block (9) is triggered, and the marching stage (2) is separated from the engine (10). This eliminates the supply of voltage to the block (8) until the end of the engine.

In the proposed device, the actuator remote inertial action (6), the separation mechanism of the steps (9), electric igniter (8), engine (10) can be performed, for example, similarly to the prototype blocks [1]. As a key (7) can be applied, for example, a field effect transistor SI4401.

As block (4), for example, the linear acceleration sensor ADXL150 from Analog Devises (USA) can be used.

The calculator (5) can be performed, for example, on the ATMEGA128 processor, ADC (3) - on the K1107 PV1 chip.

Thus, the use of the proposed method for separating the marching stage of the aircraft from the engine and device for its implementation allows you to:

- eliminate the abnormal separation of the engine and the march stage during the preparation and inspections of the aircraft before launch;

- to carry out the separation of the marching stage from the engine no earlier than the end of its operation and complete burnout of fuel without subsequent catching and hitting the stern of the marching stage.

Claims (2)

1. A method of separating the marching stage of an aircraft (LA), including mechanically keeping the start circuit of the electric igniter of the stage separation mechanism when starting the aircraft at the launch site of the flight path due to the longitudinal acceleration of the aircraft with the engine running, forming an electric start circuit of the electric igniter of the stage separation mechanism in the end of engine operation, applying voltage to the electric igniter of the stage separation mechanism, its operation and separation of the marching stupa neither from the engine, characterized in that the longitudinal acceleration d is measured on board the aircraft during the flight and its rate of change in time is determined, the moment t ₀ of the sign of the derivative of the longitudinal acceleration is changed from negative to positive, at the moment t _{0 the} electric igniter start circuit is closed stage separation mechanism. 2. An aircraft with a detachable engine, containing a marching stage and an engine docked to it with a stage separation mechanism equipped with an electric igniter, while in the marching stage, an inertial remote-action actuator mounted in the form of a non-conductive housing with a fixed contact group and a conductive one parallel to the longitudinal axis of the aircraft an inertial body locked by a power spring in the direction of the stage separation mechanism, while the inertial body is made in the form of a cylinder with an internal a lower conical hole passing into the cylinder, characterized in that the marching step is additionally equipped with a linearly accelerated linear acceleration sensor, oriented by a sensitivity axis parallel to the aircraft’s longitudinal axis, an analog-to-digital converter and a calculator, and into an open circuit between the remote inertial actuator and an electric igniter a stage separation mechanism has a calculator-controlled key, the first input of which is connected to the output of the subtract numerator, the second input - to the output of inertial actuator remote actions, and output - with an input electric spark separation stages mechanism, wherein the inertial mass body and the spring force are calculated from the triggering conditions for the values of an inertial body longitudinal acceleration
0 <d <d _hold ,
where d _hold is the minimum longitudinal acceleration developed by the engine during its operation, sufficient to mechanically hold the start circuit of the electric igniter of the stage separation mechanism.

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