Space and missile system

FIELD: transport.

SUBSTANCE: invention relates to space and missile equipment and can be used for final carrier rocket stages. A space and missile system (SMS) includes a carrier rocket with a final stage with an outer housing compartment with an intermediate power support frame with outer and inner frames connected to each other by means of fastening elements; a space vehicle with the main fairing with an end frame. The outer diameter of the intermediate support power frame corresponds to the diameter of the end frame of the main fairing.

EFFECT: invention allows attachment of different standard sizes of main fairings with carrier rockets without increasing the time for assembly and preparation for SMS launching.

2 dwg

 

The invention relates to rocket and space technology, namely the means of removing devices for space applications at specified orbits.

In a recent application in rocket and space systems, spacecraft, large volume demanded the development of a nose cone with a larger diameter, resulting in a transition of a head fairing to the last stage of launch vehicles, having a smaller docking port diameter, is carried out using a reverse cone head fairing.

Known missile and space system according to the patent of the Russian Federation 2351510 consisting of a launch vehicle and spacecraft with nose fairing prototype.

To dock with the nose fairing on the last stage of the launch vehicle is mounted a removable compartment and an external diameter which mates with the nose fairing diameter greater than the diameter of the last stage of the carrier rocket and goes beyond the current restrictions, rail and air transport, which leads to the need of the removable compartment to transport to the launch site separately from the last stage of the carrier rocket, and then to carry out their Assembly. This increases Assembly time and preparation for launch rocket-space systems - the disadvantage of the prototype.

The object of the proposed invention is the creation of space-rocket system�eat which provides docking of various sizes nose cone of the launch vehicle, having at the last stage of smaller diameter of the connecting compared to the nose fairing, without increasing Assembly time and preparation for launch rocket-space systems.

The object is achieved in that in the missile and space system containing a booster, which includes the last stage with the outer hull compartment, spacecraft and fairing, the composition of the shell compartment of the last stage of the carrier rocket power introduced intermediate support frame is rigidly connected at its end with end frame payload fairings, forming a one-piece in-flight connection, and the outer diameter of the intermediate power of the reference frame corresponds to the diameter of the end frame payload fairings, with power intermediate support frame consists of outer and inner frames, coupled together with fasteners through the outer shell of the body compartment of the last stage of the carrier rocket

Fig.1 shows a space-rocket system, Fig.2 shows the connection of a head fairing with the last stage of the carrier rocket, where:

1. booster;

2. spacecraft;

3. fairing;

4. external Cabinet compartment of the last stage of the carrier rocket;

5. the last stage of the carrier rocket;

6. power intermediate support frame;

7. end frame payload fairings;

8. outer frame;

9. the inner frame;

10. sheath;

11. fasteners;

12. the separation device.

Proposed rocket-space system consisting of booster 1, which has produced the last step 5 with the outer housing compartment of the last stage of the carrier rocket 4, spacecraft 2 with nose fairing 3, the composition of the shell compartment of the last stage of the carrier rocket 4 power introduced intermediate support frame 6 is rigidly connected at its end with end frame head fairing 7, forming a one-piece in-flight connection, and the outer diameter of the power intermediate support frame 6 corresponds to the diameter of the end frame payload fairings, 7, at that power intermediate support frame 6 consists of 8 external and 9 internal frames, coupled together by means of fastening elements 11 through the outer shell 10 shell compartment of the last stage of the carrier rocket 4.

The introduction of power intermediate support frame 6 is provided dock operated launch vehicles 1 (with a diameter of last stupas�no booster 5 less than the diameter of the lower frame payload fairings 8) operated with the head fairing 3 different sizes, with outer diameter power intermediate support frame 6 corresponds to the diameter of the lower frame payload fairings 7 and is located within the existing dimensional constraints, railway and air transport.

In addition, unshared in flight, the power connection intermediate support frame 6 with a sufficiently powerful end frame payload fairings 7 provides reliable transfer of load from the head fairing 3 on the outer Cabinet compartment of the last stage of the carrier rocket 4.

Department head fairing 3 from booster 1 is manufactured on shared flight to the junction of the head fairing 3 with the end frame payload fairings 7.

The proposed space-rocket system operates as follows.

In the operation of rocket and space systems fairing 3 prior to his separation from the launch vehicle 1 transmits the load on the junction of the head fairing 3 with a force intermediate the supporting frame 6 of the last stage of the carrier rocket 5.

After passing the space rocket system dense layers of the atmosphere fairing 3 is divided in the longitudinal direction at two folds, production�tsya compartment folds of the head fairing 3 from end of frame payload fairings 7 using the separation device 12. End frame payload fairings 7 remains at the last stage of the booster 5, and after separation of the booster 1 from the last stage booster 5 is separated from her Cabinet compartment last stage of the rocket carrier 4 together with the end frame payload fairings 7.

The implementation of this proposal in missile and space system allows for the docking of various sizes fairings with 3 launchers 1 having at the last stage of the carrier rocket 5 with a smaller diameter nose fairing 3, without increasing Assembly time and preparation for launch rocket-space systems.

Rocket-space system containing a booster, which includes the last stage with the outer hull compartment of the last stage of the launch vehicle, spacecraft with nose fairing, characterized in that the composition of the shell compartment of the last stage of the carrier rocket power introduced intermediate support frame is rigidly connected at its end with end frame payload fairings, forming a one-piece in-flight connection, and the outer diameter of the intermediate power of the reference frame corresponds to the diameter of the end frame payload fairings, with power intermediate support frame consists of the outer and inner�th frames, coupled together with fasteners through the outer shell of the body compartment of the last stage of the carrier rocket.



 

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Settlement in space // 2264330

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