RU141797U1 - UNIVERSAL RESCUE SYSTEM OF THE SPACE VEHICLE ON THE START USING THE ACCELERATION UNIT ENGINE - Google Patents

Abstract

1. The emergency rescue system, consisting of engines, a pyrotechnic catapult system of separation from the working stages of the rocket and a parachute landing system, characterized in that the engines of the acceleration block located in the head of the rocket are used as system engines. The emergency rescue system according to claim 1, characterized in that the ejection system is made on the basis of a device consisting of several barrels, each of which has a squib with an electric detonator, and shock absorbers are placed in each barrel to mitigate the dynamic shock generated when the squibs fire; squibs consist of a substance that provides smooth gradual detonation; all trunks are connected by a synchronizing annular gas channel, the function of which is to equalize the pressure in the trunks; rods are inserted into the trunks, fixed on a detachable rocket stage.

Description

The utility model relates to rescue systems of rocket and space technology and is designed to rescue spacecraft for various purposes (both manned and unmanned - cargo) in case of emergency situations at the start.

Existing Emergency Rescue Systems (CACs) [http://en.wikipedia.org/wiki/CncTeMa_aBapnfiHoro_cnaceHHHasnas], [http://www.e-reading-lib.com/chapter.php/66469/46/Shuneiiko_-_Pilotirumye_poletu_na_na .html] are mainly designed to save the crews of manned launch vehicles. To save cargo, CACs are not used, because have significant weight and a very complex structure. Therefore, for technical and economic reasons, cargo missiles are not equipped with rescue systems.

Currently used SAS have the same scheme.

Typically, CACs are located in the head of the rocket in front of the head fairing, as shown in FIG. 1, where 1 is the SAS of the Soviet H1 launch vehicle, and 2 is the SAS of the American Saturn-5 launch vehicle, located identically and having similar structural elements.

For example, the emergency compartment system for the Saturn-5 rocket command compartment shown in FIG. 2, consists of a titanium truss 3, on which three powder rocket engines are mounted: one to separate the command compartment from the launch vehicle, another to control the orientation in the pitch plane, and the third to separate the emergency rescue system farm from the command compartment. The emergency rescue system 4 is equipped with two aerodynamic surfaces with a length of 0.61 m and a width of 0.46 m, orienting the separated command compartment with the bottom in the direction of flight. The entire emergency rescue system is located on the head fairing of the instrument compartment 5, mounted on the cargo compartment 6, and the transition module 7 of the launch vehicle. The mechanism of the separation system consists of four pyro-bolts with two ignition devices in each. The parachute landing system has 2 conical tape brake parachutes with a diameter of 4.2 m, 3 tape parachutes with a diameter of 2.2 m, 3 main parachutes with a diameter of 25.2 m.

The emergency rescue system has 3 operating modes in the altitude range 0 ... 9, 9 ... 30 and 30 ... 90 km. In the event of an emergency at the initial stage of the first stage, when the time factor is critical, the rescue system is automatically activated by the signal of the fault detection system. Such situations are a drop in traction in two or more first-stage rocket engines and a high angular velocity of the launch vehicle (more than 3 degrees per second in pitch and yaw and more than 20 degrees per second in roll), the appearance of which is usually associated with a serious engine malfunction.

In FIG. 3 shows the placement of the SAS 8 of the Soyuz launch vehicle in front of the cargo compartment 9, in front of the head fairing.

In all cases, the sequence of operation of the system for the first few seconds is the same.

1. Turn on the rescue system automatically or manually.

2. Fuel cut-off of the launch vehicle engines (only 30 seconds after the start).

3 Separation of command and service compartments.

4. The inclusion of the main solid propellant rocket motor and solid rocket orientation control

5. Release of aerodynamic surfaces 11 seconds after turning on the solid propellant rocket engine.

All existing emergency rescue systems (CAC) have a number of significant drawbacks, the most important of which are as follows:

1. SAS is located in the head of the launch vehicle (LV) in the form of a separate structure consisting of a solid propellant rocket engine and a very powerful attachment point. Therefore, such a device has a significant mass (weight). The use of CAC significantly complicates the design of the launch vehicle, which leads to a decrease in its effectiveness.

2. CAC is located in front of the head fairing of the rocket, which degrades the overall aerodynamic characteristics, and leads to additional fuel consumption.

3. After a successful start, the SAS is not used in any way, and is reset during the flight at a certain altitude. This is not rational from an economic point of view, because САС is quite expensive equipment that is simply thrown away.

4. The use of CAC reduces the weight of the payload that can be launched into space. Therefore, SAS is used only in manned missiles, where its use is extremely necessary.

5. Separation (shooting) of the SAS after the start is a very dangerous event, because detachable CAC design is located in the head of the rocket. In some cases, for example, if the separation program fails, the detachable part can hit and damage the main missile.

The purpose of the proposed solution is to eliminate the above disadvantages in the new design of the CAC.

The technical result is that for the declared SAS requires a minimum retrofit of the launch vehicle, which does not require a fundamental change in technology; CAC has the best aerodynamics; CAC does not increase rocket weight; the possibility of saving not only people, but also cargo, i.e. use in launches of unmanned vehicles.

The specified technical result is achieved due to the fact that the emergency rescue system, consisting of engines, a pyrotechnic ejection separation system from the booster modules of the rocket and the parachute landing system, characterized in that the engines of the booster head of the rocket are used as the engines of the system.

Preferably, the ejection system is made on the basis of a device consisting of several barrels, each of which has a pyro cartridge with an electric detonator, and shock absorbers are placed in each barrel to mitigate the dynamic shock generated when the pyro cartridge is triggered; squibs consist of a substance that provides a relatively smooth gradual detonation; all trunks are connected by a synchronizing annular gas channel, the function of which is to equalize the pressure in the trunks; rods are inserted into the trunks, fixed on a detachable rocket stage.

The utility model is illustrated by drawings.

In FIG. 4 shows the placement of the proposed emergency rescue system (CAC) under the head of the launch vehicle 10, in the rear of the cargo compartment 11, which is connected by a power frame to the ejection device 12, after which the head of the rocket is thrown to a small height, where the acceleration engine is turned on block 13, lifting the head to a safe height, from where a smooth descent is carried out using a parachute system. In FIG. 5 shows a device of a catapult system consisting of several shafts 14, each of which has a pyro cartridge 15 with an electric detonator, and shock absorbers having a shock mitigation function are placed in each barrel; squibs consist of a substance that provides smooth gradual detonation; all barrels are connected by a synchronizing annular gas channel located at the base of the head part 16 to equalize the pressure in the trunks after the activation of the squib; rods 17 are mounted in the trunks, fixed on a detachable stage 18. In FIG. 6 shows the location of the structural elements and the principle of operation of the emergency rescue system (CAC), where: 19 - the head of the rocket (cargo compartment or manned spacecraft), 20 - the upper stage, 21 - the ejection device, 22 - the second stage of the launch vehicle; (a - stage of bailout; b - stage of flight).

Utility Model Implementation

The emergency rescue system (CAC) works as follows:

At the time of the emergency at the start, the ejection device that automatically detaches and throws the head of the launch vehicle to a small height of 10-50 m automatically starts.

At the same time, the engine of the booster block is turned on, which smoothly leads (evacuates) the head of the rocket to a predetermined height of 3-6 km. To control the flight, the control engines of the upper stage are used.

After gaining maximum height, the salvaged object may have two options for landing:

After climbing, the booster block is reset (shoots back), and the saved structure is facilitated. Then the parachute system opens. Landing is done by parachute. This method is applicable, for example, to rescue the crews of manned launch vehicles, when the relief of the rescue unit (reset of the upper stage) is necessary to ensure a softer landing.

After climbing, the booster block does not separate. The parachute system is opened and the soft landing of the entire head is carried out. This saves the spacecraft (or valuable cargo), the electronic equipment of the warhead and the upper stage. This method of evacuation is advisable, for example, to save the warhead of transport-cargo missiles, when the rescue part of the rocket can be reused.

The location of the structural elements of emergency rescue systems (CAC) based on the Soyuz rocket carrier is shown in FIG. one.

The ejection device is necessary for quick separation of the head of the rocket and the creation of the necessary conditions for turning on the engine of the upper stage. The ejection device CAC (Fig. 2) can be performed, for example, on the basis of a device consisting of several shafts 7 with squibs 6, which are triggered by electric detonators. The alarm signal is supplied automatically from the alarm sensors via the control system. The explosion pressure in the barrel 7 pushes the piston 8. Thus, the base of the head part 5 is repelled (catapulted) from the base of the rocket stage 9 and takes the head part to a small height, where the relatively powerful engine of the acceleration block 2 is turned on. The engine of the acceleration block raises the head part to a predetermined the height where parachutes are deployed for a soft landing.

SAS requires minimal retrofitting of the carrier rocket, as basically, the basic components and assemblies are used - the booster block and its control system, which reduces the total weight of the rocket being launched into space and increases its reliability. Since the new CAC is located inside the rocket, its appearance and aerodynamics are improved. The new SAS does not make the rocket heavier, since its system mainly uses the basic structural elements of the launch vehicle, in which the head of the rocket is evacuated using the engine of the upper stage. This design has the following advantages:

Due to its advantages, the new SAS can find application not only in manned, but also in cargo-transport missiles. At present, there are no world analogues of the use of SAS for saving cargo of carrier rockets. In this invention uses the following technical solutions that do not have world analogues:

- for the first time, it was proposed to use the upper stage (or last stage) of the rocket as the main engine of the emergency rescue system (CAC);

- for the first time, as a CAS, not a separate device is used, but rocket design elements (a booster unit and its control system). This improves aerodynamic performance (the system is located inside the rocket), reduces the total weight of the launch vehicle, and reduces the cost of equipment. With a successful start, the elements of the CAC design are not thrown away (as before), but are used for their intended purpose. The ejection device is used as an interstage accelerator. A booster block is used to accurately bring the spacecraft to a given flight path.

- For the first time, the design of the SAS was developed, which can save not only a capsule with the crew of a manned ship, but also the entire head part of the rocket with cargo, electronic equipment and an accelerating unit. The salvaged portion of the equipment rocket can be reused.

A useful model of the emergency rescue system for the head of the rocket carrier is carried out using the engines of the booster block, the power of which allows the head of the rocket carrier to be lifted and evacuated to a safe distance, followed by lowering to the ground using a parachute system. If an existing booster block is used, then it is selected in such a way that its power is sufficient to evacuate the warhead of the launch vehicle. If the launch vehicle has a certain design and mass of the warhead, then the booster block is designed specifically for this rocket so that its power is sufficient to provide emergency rescue of the warhead at launch and work in outer space, to disperse the spacecraft during its launch into orbit .

Claims (2)

1. The emergency rescue system, consisting of engines, a pyrotechnic catapult system of separation from the working stages of the rocket and a parachute landing system, characterized in that the engines of the upper stage are the engines located in the head of the rocket. 2. The emergency rescue system according to claim 1, characterized in that the ejection system is made on the basis of a device consisting of several barrels, each of which has a squib with an electric detonator, and shock absorbers are placed in each barrel to mitigate the dynamic shock generated when the squibs fire ; squibs consist of a substance that provides smooth gradual detonation; all trunks are connected by a synchronizing annular gas channel, the function of which is to equalize the pressure in the trunks; rods are inserted into the trunks, fixed on a detachable rocket stage.

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