RU2254265C9 - Method of injection of artificial satellites as main and accompanying payloads into geocentric orbit and device for realization of this method - Google Patents

Abstract

FIELD: rocketry and space engineering; scientific and commercial fields.

SUBSTANCE: proposed method includes placing payloads on injection facility, launching the launch vehicle, separation of injection facility from launch vehicle and injection of injection facility into geocentric orbit where said payloads are separated from injection facility. Main payload is placed on injection facility directly of body of accompanying payload; this body combines its functions with functions of main load-bearing member of adapter system for placing the main payload. After separation of injection facility from launch vehicle, additional acceleration of injection facility is performed and injection facility is injected into reference orbit and then it is shifted to geocentric orbit where main and accompanying payloads are separated. Accompanying payload is separated from injection facility after main payload is at safe distance without waiting for complete turn of main payload. Spacecraft in facility injecting the artificial satellites into geocentric orbit are placed in succession on injection facility beginning with lower one. Main payload in form of one or several spacecraft is placed on body of lower spacecraft through separation device. Body of lower spacecraft combines its functions with functions of adapter load-bearing member for placing the main payload.

EFFECT: increased mass ratio of launch vehicle and injection facility; extended functional capabilities.

3 cl, 2 dwg

Description

The invention relates to rocket and space technology and, in particular, to methods of launching several artificial satellites or spacecraft into geostationary orbit, and can be used in civil, scientific or commercial fields.

Known methods for introducing artificial satellites into geostationary orbit. In particular, for example, there is a known method of launching artificial satellites as the main and associated loads in the geostationary orbit, which consists in installing a payload including several artificial satellites on the launch vehicle, launching the space vehicle with the launch vehicle, and launching the launch vehicle payloads in stages into the geostationary orbit, where these payloads are then separated from it (see, for example, RF patent No. 2196080, B 64 G 1/10 dated 06/26/2001).

Also known are devices for launching spacecraft into a given orbit. In particular, for example, a device is known for launching artificial satellites as the main and associated payloads into the geostationary orbit, made in the form of a space-rocket system containing payload launch vehicles mounted on a launch vehicle as a space vehicle, and sequentially installed artificial satellites in the form of spacecraft along the longitudinal axis of the launch vehicle, starting from the bottom mounted on the launch vehicle with the detachment mechanism lenii from him (see, for example, RF patent No. 2109658, class B 64 G 1/00 dated 04/20/1990).

As the disadvantages of the known method and device, it is possible to note the insufficiently full and effective use of the vehicle and the means of removal according to its (their) power and conditions of removal. For example, for launching into space at a given, for example, geostationary orbit, Proton and Proton-M launch vehicles (LV) are often used as a vehicle with the upper stage of the Breeze-M launch vehicle. To make full use of the capabilities of the LV, RB, it makes sense to simultaneously display one (or several) main payload (LN), and if there is a reserve of weight, provide for the removal of an additional associated LN and at the same time provide ways to maximize its mass to ensure maximum efficiency (for example, if if we are talking about communication spacecraft, then an increase in the mass of the associated payload by 20-30 kg already significantly expands the functionality of communication spacecraft and its range).

Thus, the objective of these inventions is to develop such a launch scheme and create a device that would allow to achieve an improved technical and economic result in the form, in particular, of increased mass return of a spacecraft rocket vehicle and launch vehicle used to derive the main payload or several payloads and associated payloads.

And, in addition, the technical result here is also the expansion of the arsenal of technical means used in rocket and related fields of technology.

This problem is solved in that in the method of launching artificial satellites as the main and associated loads in the geostationary orbit, which consists in installing a payload on the launch vehicle, including several artificial satellites, launching the space vehicle with the launch vehicle, and launching the launch vehicle with payloads in stages into a geostationary orbit, where then these payloads are separated from it, in accordance with the invention, the main payload the narrow is installed on the means of removal directly to the body of the associated load, combining the functions of the body of the associated load and the main power element of the transition system to install the main payload, after separating the means of removal with the payload from the space vehicle, the impulse of the accelerator to the support means is given by the propulsion system of the removal means orbit, and then transfer it to a geostationary orbit, where the main payload is separated, and then separated from means of deriving the associated payload after leaving the main payload at a safe distance, without waiting for the full deployment of the main payload.

The problem is also solved by the fact that in the device for launching artificial satellites as the main and associated payloads into the geostationary orbit, made in the form of a space-rocket system containing payload launch vehicles mounted on a launch vehicle as a space vehicle, and sequentially artificial satellites installed along the longitudinal axis of the launch vehicle in the form of spacecraft, starting from the bottom mounted on the launch vehicle with the separation mechanism According to the invention, the main payload in the form of one or more spacecraft is mounted on the lower spacecraft body through a separation device from it, while the lower spacecraft body is capable of simultaneously realizing the spacecraft body functions and the transitional power element functions systems to set the top payload.

Further, the proposed method and device are explained in more detail using the attached graphic materials, where Fig. 1 shows a schematic diagram of a device for implementing the inventive method, and Fig. 2 shows a diagram of the launch of artificial satellites into geostationary orbit.

The device used to launch artificial satellites into geostationary orbit is made in the form of a space-rocket system containing the launch vehicle - item 1, which can be, for example, the Breeze-M upper stage unit and the Proton- M "as a space vehicle - item 2. Several payloads are installed sequentially on the launch vehicle, which can be either spacecraft - the lower (item 3) as the associated payload and the upper or upper (items 4 and 5), for example, Express-AM spacecraft - as the main payload. In this case, the lower spacecraft (or associated payload), which has its own separation device, is installed on the launch vehicle (RB) through the separation mechanism from it - pos.6, and the upper spacecraft (or upper spacecraft) as the main payload is installed with its own means compartments - item 7 directly to the lower spacecraft body, without any special transitional system (adapter), due to the special structural design of the body, lower or associated spacecraft. Those. the lower spacecraft’s hull is capable of simultaneously implementing the functions of the spacecraft’s hull and the functions of the power element of the adapter for installing the upper payload. Namely, the lower spacecraft body carries its direct functional (in spacecraft) load - it is a power structure and has panels for mounting spacecraft equipment in it and on it and the power load from the main spacecraft, i.e. performs the function of the transition element - the adapter - attaching the upper load to the output means, while in the prototype, such a transition element - the adapter, consisting of two parts, is available. There is it in the prototype according to the method - in the form of a capsule. However, the weight of the capsule or transition device (adapter) is a significant amount that reduces the total weight and volume of the output PN or spacecraft and increases the cost and complexity of the entire space-rocket system.

Thus, in accordance with the above graphic explanation, the implementation of the claimed method can be described as follows.

At the starting position, the payload, i.e., 1 (Fig. 1), sets the payload, i.e. first, along the longitudinal axis of the Republic of Belarus through the mechanism, compartments - pos.6, establish the lower associated payload - the lower spacecraft - pos.3, and then, directly on the lower SC body through the separation device from it - pos.7 - establish the main payload - one or more spacecraft - items 4, 5, for example. At the same time, the body of the associated load combines the functions of the body of the associated load and the main power element of the transition system to install the main payload.

After setting all the payloads, a space vehicle is launched with the RB docked to it and the payload on board. After passing through the dense layers of the atmosphere, the head fairing is separated (pos. 8, then the launch vehicle), the RB is supplied with its own propulsion system, the after-acceleration impulse - pos. 9 of Fig. 2 to the reference orbit, transfers it step by step to the geostationary orbit, to the separation point (pos. 10) where the main payload is separated (point - item 11). After separation of the upper payload, only the lower spacecraft remains on the launch vehicle and there is no additional element - the adapter, i.e. there is no separate additional means of attaching the upper spacecraft to the launch vehicle. Then, the associated payload (point - pos. 12) is separated from the launch vehicle after the main payload has gone to a safe distance, without waiting for the main payload to fully deploy. The period of departure of the main PN to a safe distance ensures the "non-impact" of the separated spacecraft and amounts to tens and hundreds of seconds. The deployment period of the main payload is necessary to bring the service and target systems of the main payload to the operational state of the spacecraft and reaches several days. Full deployment of the target systems is carried out at the "standing" point on the GSO, which does not coincide with the separation point. After leaving the main payload at a safe distance and after separation of the associated payload, the RB is removed (point 13) from the geostationary orbit (key 14). Office PN - pos. 10, 11, 12 in figure 2 are conditionally spaced.

Thus, the proposed method of launching artificial satellites as the main and associated payloads into the geostationary orbit and a device for its implementation allow:

1) increase the weight of the output payload; more effectively display additional two or more spacecraft;

2) make fuller use of the volume under the head fairing;

3) reduce startup costs.

Claims (2)

1. The method of launching artificial satellites as the main and associated payloads into the geostationary orbit, which consists in installing payloads including several artificial satellites on the launch vehicle, launching the space vehicle with the launch vehicle, and separating the launch vehicle from the space vehicle and launch the launch vehicle into the geostationary orbit in stages, where the indicated payloads are separated from it, characterized in that the main the payload is installed on the means of launching directly to the body of the associated payload, combining the functions of the body of the passing payload and the main power element of the transition system to set the main payload, after separating the launch vehicle from the space vehicle, this means of removing it by a propulsion system imparts an overdrive boost to reference orbit, then transfer the launch vehicle to the geostationary orbit, where the main payload is separated, and then passing, and the passing payload is separated from the means of removal after leaving the main payload at a safe distance, without waiting for the full deployment of the main payload. 2. A device for launching artificial satellites as the main and associated payloads into the geostationary orbit, made in the form of a space-rocket system containing means for launching payloads into the geostationary orbit, mounted on a space vehicle in the form of a launch vehicle, and sequentially installed along the longitudinal axis of the launch vehicle artificial satellites in the form of spacecraft, starting from the bottom mounted on the launch vehicle and equipped with a division of it, characterized in that the primary payload in the form of one or more spacecraft separation device is installed through the housing of said lower spacecraft configured compatibilizing function of the actuator body and transition system for setting the primary payload.