RU2544023C1 - Spacecraft rescue system - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to rocket-and-space engineering and can be used for spacecraft rescue in hazard situations. Emergency rescue system includes upper stage engines, pyrotechnic catapulting missile working stages separation subsystem based on device containing several shafts connected by synchronising ring-shaped gas channel with rods, pyro cartridges with electric detonators and substance providing smooth gradual detonation, shock absorbers for dynamic impact amortisation.

EFFECT: lower mass of missile.

6 dwg

Description

The invention relates to rescue systems of rocket and space technology and is intended to rescue spacecraft for various purposes (both manned and unmanned - cargo) in case of emergency situations.

The existing well-known emergency rescue systems (CAC) [http://ru.wikipedia.org/wiki/Emergency rescue system], [http: //www.e-reading-] are mainly intended for rescue 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 motor 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 a flight at a certain altitude. This is irrational from an economic position, 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 prototype of the claimed invention is an emergency rescue system US20070012821, publ. 01/18/2007, paragraphs [0013], [0018], [0027] of the description, which consists of engines, a pyrotechnic ejection system for separating from the working stages of the rocket and a parachute landing system. As engines of the system, the engines of the upper stage are located in the head of the rocket. The principle of operation of this system is that when a dangerous situation arises, the head part of the rocket (compartment with cargo or crew) is shot, then the engine of the booster block is turned on, which raises the head part to a considerable height to ensure the deployment of the parachute system, then the parachutes and the salvage are opened part gradually descends to the ground.

Advantage - the engine of the booster block is used, so there is no need to equip the launch vehicle with additional rescue engines, which facilitates the weight of the rocket and reduces its cost.

Disadvantages. In order for the parachute system to be able to fully open and provide a smooth descent of the heavy vehicle, it is necessary to have a sufficient height (3-5 km), therefore the engines of the booster block must have a sufficient fuel supply and significant power to provide such a lift. The use of a more powerful booster block increases the weight and cost of the launch vehicle. In addition, at the time of switching from the stage of lifting to the stage of using the parachute system, failures are possible, because uncontrolled flight occurs during this period of time. And if the parachute system did not open, it is impossible to use a "reserve parachute" due to the relatively low altitude. An uncontrolled parachute descent is also carried out, which can be blown away by the wind into a terrain unsuitable for landing (for example, into a forest, swamp, or water), which significantly reduces the reliability of rescue.

The advantages of the claimed invention compared to the prototype using a parachute system:

Firstly, there is no need to raise the salvage unit to a great height to ensure the opening of the parachute system, the evacuation of the salvage head of the rocket can be carried out along a gentle ballistic trajectory, sideways, by taking the salvage unit to a safe horizontal distance. Therefore, a less powerful booster engine can be used, which reduces the cost and weight of the launch vehicle. Secondly, the absence of a bulky parachute system significantly reduces the weight and cost of the rescue system. Thirdly, there is no danger of ignition of the parachute system in an emergency associated with an explosion or burning, which increases the reliability of the rescue. Fourth, there is no dangerous transitional period between turning off the engines and opening parachutes, as the booster block rescue engine runs continuously from the moment it is turned on until the moment it lands. Fifth, in contrast to the parachute descent of the prototype, the claimed method performs a controlled flight along a ballistic trajectory using the engine control system of the upper stage, which allows more precise control of the descent parameters and landing in the safest place.

The aim of the claimed invention is to eliminate the above disadvantages in the new design of the CAC and prototype.

The technical result of the claimed invention 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 unmanned aerial vehicles.

Additional advantages of the invention are that the system does not need a significant climb, and it does not use an outdated parachute system. To ensure the removal of the salvaged head of the rocket to a safe distance, a gentle ballistic trajectory is used, the flight is carried out at a low horizontal height. The missile does not need to be equipped with an overclocking unit of increased power, but you can use an ordinary overclocking unit in power. The possibility of fire or damage to the parachute system (due to flame or flying fragments) is excluded, which increases the reliability of rescue. In addition, a controlled descent is made with the possibility of choosing the safest landing place.

The specified technical result is achieved due to the fact that the emergency rescue system, consisting of engines, a pyrotechnic ejection system for separating from the booster modules of the rocket and the parachute landing system, in which the engines of the booster block of the head of the rocket are used as the engines of the system, is characterized in that the ejection system made on the basis of a device consisting of several barrels, each of which has a squib with an electric detonator, and in each barrel there are amortization tori to mitigate the dynamic shock generated by the operation of the squib; 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 invention is illustrated in the drawing.

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 accelerating engine is turned on 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 for 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).

The implementation of the invention

The emergency rescue system (CAC) operates as follows.

When an emergency occurs, the ejection device automatically detaches and throws the head of the launch vehicle to a small height of 10-50 m.

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 rescue 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.

Claims (1)

The emergency rescue system, consisting of engines, a pyrotechnic ejection system for separating the rocket from the working stages and a parachute landing system, as the engines of the system, the upper stage engines located in the head of the rocket are used, characterized in that the ejection system is based on a device consisting of several trunks, in each of which there is a pyro cartridge with an electric detonator, and shock absorbers are placed in each barrel to mitigate the dynamic shock generated when triggered by squibs; 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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