RU2000102687A

RU2000102687A - METHOD FOR INTRODUCING USE OF USEFUL LOAD OF A MULTIFUNCTIONAL ROCKET-CARRIER OF A COMBINED DIAGRAM WITH MARCHED LIQUID ROCKET MOTOR INSTALLATIONS (RUNNER)

Info

Publication number: RU2000102687A
Application number: RU2000102687/28A
Authority: RU
Inventors: Анатолий Иванович Киселев; Александр Алексеевич Медведев; Владимир Константинович Карраск; Геннадий Дмитриевич Дермичев; Игорь Сергеевич Радугин; Сергей Александрович Петроковский; Евгений Иванович Моторный; Василий Юрьевич Юрьев
Original assignee: Государственный космический научно-производственный центр им. М.В. Хруничева
Filing date: 2000-02-07
Publication date: 2001-11-27

Claims

1. A method of launching a payload into orbit with a multifunctional launch vehicle of a combined circuit with marching liquid propellant rocket propulsion systems (LRE), comprising connecting, in accordance with the launch program, tandemly located missile blocks and a head block with a payload to the central rocket block and forming a lower multi-block package rocket blocks by connecting to the central rocket block of the side rocket blocks, the inclusion of all marching rocket engines of the side and central th rocket blocks, the joint operation of mid-range rocket engines of the central and side rocket blocks until the side rocket blocks generate fuel, the marching rocket engines of the side rocket blocks and separation of the side rocket blocks from the central missile block while continuing the operation of the mid-range rocket engine of the central rocket block before fuel is generated from it, shutdown marching liquid propellant rocket engine of the central missile unit, separation from the central missile unit of the tandemly located missile units and the head unit and subsequent acceleration of the main about the block with the indicated rocket blocks up to its orbit, characterized in that for the formation of the lower multiblock package of rocket blocks the same rocket blocks are used, having adjustable marching rocket engines with the same nominal thrust, when the launch vehicle starts, the marching rocket launchers of the side rocket blocks to the nominal thrust, and the marching liquid propellant rocket engine of the central missile unit - for thrust equal to 90 ... 100% of the nominal value, and maintain the thrust of the liquid propellant rocket engine of the central missile block unchanged until the launch vehicle reaches longitudinally acceleration of 12.7 ... 16.7 m / s ² (1.3. . . 1.7 g), then reduce it to 0.3 ... 0.5 from the nominal thrust, and after disabling the marching rocket engine of the side rocket blocks, increase the thrust of the marching rocket engine of the central unit to the nominal value.

2. The method according to claim 1, characterized in that when the launch vehicle is operated with a reduced thrust level of the mid-range main propellant rocket engine when it reaches longitudinal acceleration of 39 ... 44 m / s ² (4 ... 4.5 g) uniformly reduce the thrust of marching rocket engine side rocket blocks, maintaining the specified longitudinal acceleration until the end of the rocket engine side rocket blocks.

3. The method according to claim 1, characterized in that. that on the atmospheric portion of the trajectory, the flight altitude of the launch vehicle and its speed are measured, which determine the velocity head of the incoming air flow at a standard atmosphere density at flight altitude, and when the carrier rocket reaches a speed at which aerodynamic forces from the velocity head of the air flow reach the maximum permissible values for the design of the launch vehicle, a further increase in the speed of the launch vehicle is carried out by adjusting the thrust of the marching rocket engine of the side rocket blocks in within 0.3 ... 1.0 of the nominal thrust from the condition of not exceeding the maximum permissible pressure head, maintaining the ratio

where V _i is the current speed of the launch vehicle;
k is a dynamic coefficient equal to 0.95 ... 1.05;
V ₁ - the speed of the launch vehicle at which the maximum permissible pressure head is reached;
ρ _l is the density of the standard atmosphere at which the maximum permissible pressure head is reached;
ρ _i is the current density of the standard atmosphere at flight altitude.

4. The method according to claim 3, characterized in that the thrust regulation of the marching rocket engines of the side rocket blocks is carried out on the condition that the maximum permissible speed pressure equal to 12000 ... 17000 Pa is not exceeded.

5. A multifunctional launch vehicle of a combined scheme with marching rocket engines, containing a lower multiblock package of rocket blocks with marching rocket engines, including a central and attached side rocket blocks and a transition compartment, booster rockets and a head block with a payload, tandemly mounted on the central block, head fairings of the side rocket blocks, and a system for attaching the side rocket blocks to the central block, characterized in that the lower multiblock package is composed of identical rocket blocks For example, having identical fuel tanks and identical marching rocket engines with adjustable traction, fixed in a gimbal, the side rocket blocks are mounted symmetrically on the central rocket block relative to its longitudinal axis in the sectors formed by the rocking planes of the main rocket rocket engine of the central rocket block, so that the rocking planes of the main rocket The rocket engine of each side rocket block is parallel to the corresponding rocking planes of the mid-flight rocket engine of the central rocket block.

6. The launch vehicle according to claim 5, characterized in that it is equipped with two lateral rocket blocks mounted on the central rocket block in one plane oriented at an angle of 45 ^o to one of the rocking planes of the mid-range rocket propelled rocket engine.

7. The launch vehicle according to claim 5, characterized in that it is equipped with four lateral rocket blocks mounted on the central rocket block in two mutually perpendicular planes oriented at an angle of 45 ^o to the rocking planes of the main rocket propelled rocket engine.

8. A method for testing a multifunctional launch vehicle of a combined scheme with mid-range rocket engines, including the selection of the overall mass characteristics of the central, side and booster rocket blocks and the traction characteristics of their mid-range rocket engines, the design and manufacture of these rocket blocks, the formation of the lower multi-block package of rocket blocks, ground and flight design tests to confirm the reliability of both individual missile units and the launch vehicle as a whole, characterized in that for the central and side new missile blocks are set to the same overall mass characteristics and thrust of marching liquid propellant rocket engines, which ensure the use of a central rocket block as part of a tandem launcher with a single-block lower stage, make the specified missile block and conduct its ground and flight design tests, including as part of the tandem launcher, confirm the reliability of the central missile block and use the central missile block worked out on the tandem launcher when forming lower multiblock package of missile blocks of the launch vehicle of the combined circuit with flight design tests with increased operating time of the mid-range main propellant rocket engine with respect to the main propellant rocket engines of the side rocket blocks.