Adapter for group launch of spacecraft

FIELD: rocketry and space engineering; adapters for group launch of spacecraft.

SUBSTANCE: proposed adapter has body consisting of two parts: one part is made in form of load-bearing body with platform for placing the spacecraft on one end and with attachment frame on other end; other part is made in form of load-bearing ring secured on payload frame and provided with attachment frame. Attachment frames of load-bearing body and load-bearing ring are interconnected by means of bolted joints fitted with two rubber washer shock absorbers each; one of them is mounted between surfaces of attachment frames to be coupled and other is mounted between opposite surface of attachment frame of load-bearing body and metal washer laid under bolt head. Diameter of metal washer exceeds diameter of rubber washer shock absorber; spacecraft attachment units are secured on platform of load-bearing body by means of bolted joints with rubber washer shock absorbers mounted between platform surfaces to be coupled and spacecraft attachment units.

EFFECT: reduction of dynamic vibration and impact loads due to extended range of varying dampening properties of adapter.

6 dwg, 1 tbl, 1 ex

 

The invention relates to rocket and space technology and relates to adapters for group space launch vehicles.

Known adapters for multiple spacecraft, comprising a housing connected with LV where by systems Department docked spacecraft (see “Device to host multiple satellites on booster”, patent No. 2156212 on the application 95103975/28).

Typically, the enclosure through a special docking frame is mounted on the power stud rod frame payload included in the instrument compartment of the rocket.

The main feature of such structures is that the dynamic loads acting on the spacecraft from the booster in the ascent phase, and pulse load from the systems Department of the spacecraft, significantly depend on the damping properties of the structure of the adapter. Reduce data loads to acceptable by selecting the desired damping properties of the structure of the adapter is a complex technical task.

The closest technical solution to the claimed is the adapter for the group space launch vehicles, comprising a housing mounted on the edge of the platform to install the spacecraft. The bottom end through founded the e adapter is installed on studs rod frame payload launch vehicle (see “Modern technologies to create products for military and civil purposes. Proceedings of the technology of Congress. Part II. Publishing house “Omsk state technical University”. 2001 ISBN 5-8149-0076-8. P.20. Fig. 6(a) Adapters for multiple SPACECRAFT”, a General view of the adapter shown in the Appendix.

As the experience of ground-based experimental testing dynamic strength spacecraft in similar adapters and their systems branch, dynamic and impulse loads acting on the spacecraft, are determined by the damping properties of the structure of the adapter and device docking spacecraft adapter.

In flight in the plane of the junction adapter with booster function on the three orthogonal axes of the quasi-stationary broadband random vibration. The maximum levels of airborne vibrations occur at the time of launch and during flight in the dense layers of the atmosphere in the transonic regime.

Vibro-impact acceleration in the plane of the junction adapter with booster occur at start-up and shutdown of the engines of the 1st and 2nd stages separation steps. Vibro-impact processes are transient decaying vibration. Low-frequency vibrocore occur during startup and shutdown of engines, propulsion stages. High fre is now vibrocore caused by the firing of pyrotechnic devices, used to separate steps and reset the head fairing.

The greatest shock load acting on the structural elements of the adapter and installed on spacecraft, occur when triggered ProCredit systems branch of the spacecraft. For example, table 1 shows the impact load from the pyrotechnic separation system for a spacecraft with a mass of about 90 kg

Table 1
Frequency, Hz200200010000
Spectrum shock, g6033004200

Usually, when developing an adapter for a group of spacecraft launch the task of reducing the dynamic vibration and shock loads. This is because the design and the devices launched spacecraft may not be able to withstand operating loads or booster, or from the systems Department.

In the technical solution according to the prototype of this task can be solved only by selection of the required damping properties of the structure of the adapter and the mounting position of the spacecraft, which is a complex technical task, even with the use of modern software and computer technology, and has the significant disadvantage of the known technical solutions.

In addition, in the practice of developing adapters there are occasions when the group launch small satellites (let's say two spacecraft with a mass of 90 kg each) it is necessary to develop such an adapter, which would provide the desired in terms of stability and controllability of the booster a lot headunit (adapter + satellites), as well as the desired location of the center of mass of the head unit (for this example a booster the minimum mass of the block should be 500 kg, and the center of mass of the head unit should be placed from the plane of the junction with the booster at a minimum distance in 1000 mm). In this case, the design of the adapter is developed not from the condition of minimum weight of the structure, and from the condition that requirements to ensure the stability and controllability of the booster in the ascent phase. Therefore, the design of the adapter in this case will be “parmagiana and to vary its damping properties is almost impossible.

The purpose of the proposed solutions is the reduction of dynamic vibration and shock loads on installed on the adapter spacecraft by expanding the range of variation of the damping properties of the structure of the adapter.

This objective is achieved in that the adapter for the group of the new space launch vehicles includes a housing, consisting of two parts, one of which is made in the form of the power chassis with a platform for installation of the spacecraft at one end and with a docking ring on the other end, and the other part - in the form of a power ring, mounted on the frame payload, the docking frame, thus connecting the frames of the power enclosure and power rings are interconnected by means of bolts, each of which has two Leibovich rubber shock absorber, and one of them is mounted between the abutting surfaces of the connecting ribs of the power enclosure and power ring, and the other between the opposite surface of the docking frame power housing and a metal washer under the bolt head, the diameter metal washers exceeds the diameter chyboveho rubber shock absorber and device mounting spacecraft mounted on the platform power chassis with bolt connections shibowei rubber shock absorbers mounted between the abutting surfaces of the platform and device mounting spacecraft.

The proposed solution is illustrated by the drawings, which depict:

figure 1 - General view of the adapter;

figure 2 is a top view of the adapter;

figure 3 - connection node of the power ring power enclosure adapter is;

figs.4, 5 - node connection device mounting spacecraft platform to install spacecraft;

figure 6 - levels of congestion on the spacecraft during testing adapter on random vibration in the direction of the transverse axis.

In addition, the Appendix contains a three-dimensional image of General view of the adapter and the connection node of the power ring power body of the adapter is received by the photo adapter, assigned for conducting ground-based experimental testing.

Adapter for group space launch vehicles consists of the power of the housing 1 with the platform 2 for attaching the spacecraft and the power of the ring 3. On the platform 2 are spacecraft and other payloads, such as satellites 4, 5 and detachable part of the measuring unit 6.

The adapter through the power of the ring 3 is fixed to the frame payload 7 booster. Spacecraft 4 is attached to the platform 2 through the ring 8 and the spacecraft 5 - through the spacer 9. The adapter with the spacecraft was installed under the head of aerodynamic fairing 10.

Power block 1 contains the connecting frame 11, and the power ring 3 - docking frame 12. The connecting frames 11, 12 are designed to connect power to the chassis 1 and the power ring 3 between the other.

The connecting frames 11, 12 are interconnected by means of bolts 13, each of which has two Leibovich rubber shock absorber 14, 15. Shibby rubber damper 14 is mounted between the abutting surfaces of the connecting frames 11, 12 of the casing and the power ring, and shibby rubber damper 15 is between the opposing surface of the connecting frame 11 of the power of the housing 1 and a metal washer 16 under the bolt head of the bolt connection 13. The diameter metal washers 16 exceeds the diameter chyboveho rubber shock absorber 15 and is selected so that in the compressed state, the diameter of the washer was not less than the diameter chyboveho rubber shock absorber.

The fastening device 8, 9 spacecraft 4, 5 mounted on the platform 2 of the power of the housing 1 by means of bolts 17, 19 shibowei rubber shock absorbers 18, 20 mounted between the abutting surfaces of the platform 2 and the device mounting space devices 8, 9.

The implementation of the adapter of the two parts connected by a double belt depreciation of Leibovich rubber grommets and install Leibovich rubber grommets in the mounting locations of the spacecraft platform adapter greatly enhances the damping properties of the adapter as a whole.

The inventive adapter with belt is mi depreciation compared with the core and shell adapters without data zones depreciation allows you to:

- significantly reduce the levels of random vibration acting on a spacecraft in the frequency range from 60 Hz to 2500 Hz;

- to reduce the RMS amplitude random vibration acting on a spacecraft in 2.5-3 times;

- reduces shock loads on installed on the adapter spacecraft, from actuation system Department of separated spacecraft 6-10 dB compared to adapters without belts depreciation.

The inventive adapter has passed the full cycle of dynamic vibration and shock tests proved the effectiveness of belts depreciation.

Figure 6 (figure 21) shows the results of the test adapter with belts depreciation on random vibration. For comparison 22 shows a graph obtained by calculating, for a truss adapter, in which the belt depreciation missing.

Impact test adapter showed that the maximum amplitude values of the response of structural elements under shock from the operation of the separation system of the spacecraft 4, mounted on the platform 2 through Shibuya rubber bumpers (range strike when the operation of the Department of space apparatus 4 shown in table 1), was on the platform 2 in the area of installation of the measuring unit 6-45g, and the spacer 9 to the installation space is on unit 5, mounted on the platform 2 through the absorbers, - 19g. Range of impact on the spacer 9 in the frequency range from 10 to 10000 Hz did not exceed 90g.

Adapter for group space launch vehicles, comprising a housing consisting of two parts, one of which is made in the form of the power chassis with a platform for installation of the spacecraft at one end and with a docking ring on the other end, and the other part - in the form of a power ring, mounted on the frame payload, the docking frame, thus connecting the frames of the power enclosure and power rings are interconnected by means of bolts, each of which has two Leibovich rubber shock absorber, and one of them is mounted between the abutting surfaces of the connecting ribs of the power housing and power ring, and the other between the opposite surface of the docking frame power housing and a metal washer under the bolt head, the diameter metal washers exceeds the diameter chyboveho rubber shock absorber and device mounting spacecraft mounted on the platform power chassis with bolt connections shibowei rubber shock absorbers mounted between the abutting surfaces of the platform and the device mounting space devices is impressive.



 

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