Engine unit for separation and removal of air space set from cryogenic stage of carrier

FIELD: space craft.

SUBSTANCE: proposed engine unit includes two equal-thrust solid propellant brake engines and system of their starting. Solid propellant brake engines are arranged diametrically opposite on cryogenic stage of carrier and are made with equal nozzles and equal diameter chambers. Sizes of grains for each brake engine are related by (D+d2)·L2=(D+d1)·L1 and 1.2·(D-d1)≤(D-d2)≤2.0·(D-d1) where D is outer diameter of grains; d1,d2 are diameters of channels of grains of 1st and 2nd engines, respectively;L1,L2 are lengths of grains of 1st and 2nd engines, respectively.

EFFECT: provision of minimum dynamic disturbances at separation of air space set from cryogenic stage of carrier by means of two brake engines.

2 dwg

 

The present technical solution is devoted to the issue of separation and withdrawal from the flight path booster carrier from aerospace unit.

A well-known system of separation of the payload from the launch vehicle and pull the last stage due to the switching brake motors (see, for example, U.S. Pat. U.S. No. 3534686, CL 102-49 .5). Here the payload after breaking the mechanical connection with the burnt out last stage of the carrier is separated by means of two brake motors (AP): the first involved one of them, which starts to slow down and to simultaneously expand the last stage of the carrier, with a time delay of 0.8 seconds turns on the second TD and spent the final stage is given trajectory of the payload. The first TD has enough fuel for simultaneous burning with the second AP. Brake motors are located symmetrically relative to the center of mass of the detachable object is diametrically opposed.

The disadvantage of this scheme is the following. When the start timing of the actuation of brake motors, an additional lateral dynamic load on the object branch, as the current residual thrust booster and pull one brake engine creates an unbalanced torque, which is in the form of lateral forces in acts on the end of the detachable object, that distorts the trajectory of further movement of the payload.

The essence of the proposed design aims to eliminate this disadvantage through the use of two brake motors, which are located on the upper stages of the media are diametrically opposed and have the system run the same pull, the same nozzle, the same size shell diameters DT, of the same diameter camera TD run simultaneously, but have different lengths of the combustion chambers and different good times TD.

These conditions satisfy the propellant charge end of combustion of the same diameter but different lengths. However, to ensure the desired modes of short-term work DT with such charges and with the desired pulses of thrust is not always possible.

In this regard, the proposed AP to use channel solid checkers comprehensive burning the same outer diameter in each TD, but with different diameters of the channels of checkers and different length.

When required equality of the magnitude of thrust of each of th respect to time of engine operation, ensuring the withdrawal of spent stages with the flight path, τ2for time-shared operation of both TD τ1almost should be

To rannatarvete two TD would be the as a minimum, the checkers must be made of one of the fuel mass.

For equality of the magnitude of thrust two TD on the site of the joint work pieces must have the same initial surface combustion. In addition, to reduce the variation of the thrust force of each of TD and to unify buildings engines outer diameter of the sticks (the tolerance on the size which gives the greatest scatter the burning surface and defines a geometric dimensions of the camera etc.) must be the same for both TD. This results in the following relations for the geometric dimensions of checkers two TD: (D+d2)·L2=(D+d1)·L1; (D-d2)=1,2-2,0(D-d1) or 1.2(D-d1)≤(D-d2)≤2,0(D-d1),

where D is the outer diameter of the sticks,

d1d2the diameter of the channel checkers 1st and 2nd TD, respectively,

L1, L2- length checkers 1st and 2nd TD, respectively.

The propulsion system for the separation and withdrawal of aerospace Assembly from the upper stages of the carrier illustrated by drawings:

figure 1 is a fragment of the booster vehicle with two brake motors

figure 2 is a longitudinal section of checkers for each TD.

The propulsion system includes installed on the booster carrier 1 two renotahoe solid model of the engine 3 and 4 (figure 1) with a channel checkers 5 (TD 4, figure 2) and channel the checkers 6 (TD 3, 2).

Simultaneous actuation of the motors 3 and 4 after a break of a mechanical connection between the unit and the upper stage stage 1 occurs the separation of stages in the axial direction. Then, when I worked the motor 4 continues to operate the motor 3 and takes the 1st step in the direction from the predetermined flight path. Residual thrust booster will not lead to that step will catch up separated aerospace unit.

In case of simultaneous activation of two engines with the same thrust dynamic perturbations on the detachable unit is minimal, and the trajectory of aerospace unit after separation from the booster carrier meets specified.

The propulsion system for the separation and withdrawal of aerospace Assembly from the upper stages of media containing located on the upper stages of media diametrically opposite two renotahoe solid brake motor with the sabres, with cameras of the same diameter and with the same nozzles and run the engine, characterized in that the size of the checkers for each brake motor connected by the relation (D+d2)·L2=(D+d1)·L1and 1.2·(D-d1)≤(D-d2)≤2,0·(D-d1), where D is the outer diameter of checkers; d1d2the diameter of the channel checkers 1st and 2nd number is LEU, respectively; L1, L2- length checkers 1st and 2nd motors, respectively.



 

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SUBSTANCE: proposed engine unit includes two equal-thrust solid propellant brake engines and system of their starting. Solid propellant brake engines are arranged diametrically opposite on cryogenic stage of carrier and are made with equal nozzles and equal diameter chambers. Sizes of grains for each brake engine are related by (D+d2)·L2=(D+d1)·L1 and 1.2·(D-d1)≤(D-d2)≤2.0·(D-d1) where D is outer diameter of grains; d1,d2 are diameters of channels of grains of 1st and 2nd engines, respectively;L1,L2 are lengths of grains of 1st and 2nd engines, respectively.

EFFECT: provision of minimum dynamic disturbances at separation of air space set from cryogenic stage of carrier by means of two brake engines.

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