RU2649539C2 - Motor module of spacecraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: motor module of spacecraft (SC) has at least two rings and three fuel tanks with the upper pole elements, connected with the upper rings, and lower pole elements, that are the legs of the whole motor module, interacting with relevant SC supports, at least one high-pressure cylinder, rocket motors and control units. The lower pole elements are pivotally fixed on the supports of the motor module, and the upper pole elements are fixed to the upper ring with the ability to move, allowing rotation relative to the pivot fixing of the lower pole elements.

EFFECT: weight reduction and increased vibration resistance of the structure.

3 cl, 4 dwg

Description

The invention relates to rocket and space technology, namely, to the design of propulsion systems for space purposes, as well as to the design of upper stages, designed to bring the payload to the calculated orbit and correct this orbit.

Known rocket booster block containing the oxidizer tank, with a suspension rod truss, a toroidal fuel tank with a supporting rod truss for interfacing with a launch vehicle. The tanks are interconnected by a power structure, which is the upper frame with the oxidizer tank and the lower frame with the fuel tank. Both frames are interconnected by stringers. Moreover, the rod trusses of the oxidizer tank suspension and the payload are supported by the upper frame, and the lower frame interacts with the fuel tank arms and the support rod farm (RF patent No. 21553779, IPC B64G 1/00, 1/16, 1/40, publ. 20.04. 2001, bull. No. 11).

A disadvantage of the known design is that the frame of the propulsion system (DU) carries a power load from the total mass of all elements of the DU when exposed to linear accelerations of up to 10 g or more and shock - up to 1000 g. Therefore, the frame should ensure the integrity and performance of the entire structure, taking into account the full loads, while it will have a large mass and a large number of power elements: frames, stringers, stiffeners.

Known engine module (RF patent No. 23766216, IPC B64G 1/40, publ. 12/20/2009, bull. No. 35), consisting of at least two frames, fuel tanks with pole elements, high-pressure cylinders, rocket engines flight control, automation and control units, moreover, the upper pole elements are rigidly connected to the upper frame, and the lower pole elements are the supports of the entire propulsion module, interacting with the corresponding supports of the spacecraft, upper stage or stage.

This design is essentially a prototype of the proposed solution. This engine module has reduced weight, improved manufacturability and simplified design. However, this propulsion module has several disadvantages:

- adjusting the position of the center of mass when mounting the fuel tanks to the supports of the engine module requires special devices, complicates the assembly and reconfiguration, increases the complexity and reduces the maintainability of the entire module;

- the position of the axes of the tanks relative to the supports of the module and the corresponding supports of the spacecraft creates a moment of force from the component of the force directed along the axis of the tank on the shoulder equal to the distance from the center of the platform of the power support to the line of the force vector. This can lead to low-frequency fluctuations during the action of vibrational loads when the spacecraft is put into orbit, which significantly reduces the vibration strength margin, which means that it requires an increase in the mass of supporting and other power elements, and leads to structural complexity due to elements reinforcing structural rigidity.

The objective of the invention is to reduce weight, simplify the design and increase the reserves of vibration and vibration resistance, and therefore, the survivability of the structure.

The proposed propulsion module of a spacecraft consists of at least two frames and three tanks for fuel components with upper pole elements mounted on the upper frame and lower pole elements, which are the supports of the entire propulsion module, interacting with the corresponding supports of the spacecraft, at least one balloon high pressure rocket engines flight control, control units.

According to the invention, the lower pole elements are pivotally mounted on the supports of the motor module, and the upper pole elements are mounted on the upper frame with the possibility of movement, providing rotation relative to the hinge fastening of the lower pole elements.

To reduce or eliminate the moment of force in the supports of the engine module in order to prevent low-frequency resonance vibrations when exposed to vibroloads, increase the rigidity and vibration resistance of the structure, the axis of the tanks passes through the axis of the articulated joints and through the center of the power contact zone of the lower pole elements and supports of the spacecraft.

To reduce the mass and increase the reserves of vibration resistance by increasing the density of the arrangement in the area of the fuel tanks, in the inter-tank space and on the upper frame of the engine module, payload, additional fuel tanks or high-pressure cylinders can be located.

The proposed engine module is shown in the drawings. In FIG. 1 shows a section through a module. In FIG. 2 is a top view of this module (instead of toroidal balloons, ball-mounted, placed between the tanks for storing fuel components are shown). In FIG. Figure 3 shows a section through the attachment point of the upper pole element on the upper frame. In FIG. 4 - an option for placing additional tanks or cylinders.

The proposed engine module (Fig. 1 and Fig. 2) consists of a minimum of three tanks 1 for storing fuel components with a gas cavity 2 and a fuel cavity 3, at least one high-pressure cylinder 4 for storing pressurized gas, spacecraft flight control engines 5 , control and automation units 6, the upper frame 7 with grooves 8 (Fig. 3) for moving the upper pole elements 9 of the fuel tanks when the angle of inclination of their axes relative to the supports of the motor module, the lower frame 10, the lower poles x elements 11 with swivel joints 12 for connection with the supports 13 of the propulsion module, interacting with the respective supports 14 of the spacecraft. The tanks are evenly spaced around the longitudinal axis of the motor module and are fixed to the upper pole elements 9, for example the neck, in the grooves 8 on the upper frame 7, which is a power support, for example, for a payload (not shown).

The use of hinges for mounting the lower pole elements 11 in the supports 13 of the motor module allows for the least cost to assemble the entire motor module, as well as adjusting the position of its center of mass by simply turning the tanks in the hinge assembly by moving the upper pole element 9 in the grooves 8 of the frame 7 using for example, a micrometer screw 15. After adjustment, the upper pole elements 9 are fixed in the grooves 8 with fasteners or, for example, by welding.

To ensure strength and stability when exposed to dynamic loads, the axis of the tanks pass through the axis of the hinged joints 12 and the central zone of power contact of the connection of the supports 13 of the propulsion module and the supports 14 of the spacecraft. In this case, a geometric pyramid is obtained, fixed at the corners of its base, which eliminates the possibility of additional forces and torques in the attachment points and the occurrence of low-frequency vibrations in the structural elements of the module.

When forming the engine module, which requires an increased density of the arrangement, an additional fuel tank or balloon 16 may be located on the upper frame instead of the payload, toroidal fuel tanks or cylinders 17 may be located in the outer zone of the fuel tanks or in the inner zone between the fuel tanks additional tanks or cylinders 18 can be located (Fig. 4). Thus, there is no need for additional fastening elements for cylinders or fuel tanks, and the rigidity and quality of centering of the remote control are also increased. This, in turn, increases vibration resistance and reduces fuel costs for controlling the orientation and stabilization of the spacecraft, improves the overall mass characteristics of the propulsion module and the spacecraft as a whole, and also increases their reliability and survivability.

Claims (3)

1. The propulsion module of a spacecraft, consisting of at least two frames and three tanks for fuel components with upper pole elements connected to the upper frame and lower pole elements, which are the supports of the entire propulsion module, interacting with the corresponding supports of the spacecraft, at least one high pressure cylinder, missile flight control engines and control units, characterized in that the lower pole elements are pivotally mounted on and the supports of the motor module, and the upper pole elements are mounted on the upper frame with the possibility of movement, providing rotation relative to the hinge fastening of the lower pole elements. 2. The engine module according to claim 1, characterized in that the axis of the tanks of the fuel components pass through the axis of the articulated joints and through the center of the power contact zone of the lower pole elements and the supports of the spacecraft. 3. The engine module according to claim 1 or 2, characterized in that in the zone of the fuel tanks, in the inter-tank space and on the upper frame of the engine module, payload, additional fuel tanks or high-pressure cylinders can be located.

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