Satellite carrier for integrated circuits. Carrier satellite for integrated circuits in flat packages with pins arranged around the perimeter
The Sputnik-3 launch vehicle (8A91) was the result of a modernization of the 8K71 rocket and was capable of solving the problem (unlike the 8K71 rocket of the second stage) of launching into orbit a payload weighing ~1300 kg (the mass of the third satellite was 1327 kg). The 8A91 launch vehicle had uprated engines; Also, the radio control system was removed from the standard rocket, the instrument compartment and the warhead separation system were simplified. Two launches of the Sputnik-3 (8A91) launch vehicle were carried out. During the first launch, due to the occurrence of self-oscillations, the rocket collapsed at 102 seconds of flight. The second launch of this rocket was successfully carried out this year. The D-1 satellite was launched into orbit.
Having completed its historic mission of launching the first three satellites, the Sputnik rocket itself did not fade into history, but continued to serve the cosmonautics as the basis for many other more powerful launch vehicles, remaining unsurpassed in power and sophistication for many years that marked the beginning of space age
In the second half of the fifties, Soviet science and technology gained biggest victory. Under the leadership of Sergei Pavlovich, the queen was developed, the first in the world space rocket, called Sputnik. For the first time in the history of mankind, it reached cosmic flight speed - on October 4, 1957, the rocket carried into space the world's first artificial earth satellite with a mass of 836 g. It was quite simple and was called PS 1. (The simplest satellite is the first). The creation of the Sputnik launch vehicle opened fundamentally new horizons scientific research noted.
The two-stage Sputnik launch vehicle consisted of 5 blocks: four side blocks (blocks B, C, g, D), which together constituted the first stage, and one central block (block A), which was the second stage of the rocket.
The mass of the first stage with a full fuel supply is 267 tons, the mass of the second stage is 58. The dry weight of Sputnik is 22 tons. These figures indicate the high design perfection of the rocket. In it, the fuel accounted for 93% of the mass of both stages and only 7% for all other structural elements, including engines.
The total length of the Sputnik is 29.167 m. The diameter along the air rudders is 10.3 m. The length of the side blocks is 19 m, the diameter is 3 m, the central block is 28 m and 2.95, respectively.
Sputnik was equipped with liquid rocket engines(LPRE), which had very high energy characteristics for that time. They were created by the GDL-OKB team under the leadership of V.P. Glushko. Each of the first stage blocks had an RD-107 engine. It had four main combustion chambers and two steering ones with one common turbo-pump unit (TNA). At rocket launch, each RD-107 engine developed a thrust of 99.5 tons. The total thrust of all engines of the four first-stage blocks was 398 tons.
The second stage of the rocket (i.e., the central block) had an RD-108 engine with a thrust of 93 tons near the Earth. Its 4 main and 4 steering combustion chambers were powered by one common turbo-pump unit. Both the main and steering engines ran on kerosene and liquid oxygen, and the TNA turbine ran on decomposition products of 82% hydrogen peroxide.
At launch, the engines of all 5 blocks, the first and second stages of the rocket were turned on immediately. In total, their total thrust was 491 tons. As you rise to altitude. As the layers of air became more and more rarefied, the thrust of the engines increased. In the “emptiness” the thrust of the RD-107 reached 102 tons, and the RD-108 - 96 tons. The specific thrust of the first stage engines on Earth was 250 s, and the thrust of the second stage engine RD-108 reached 308 s in the “emptiness”.
The Sputnik rocket was equipped with a reliable control system that met the most stringent requirements. It was developed by a group of specialists under the leadership of N. A. Pilyugin.
A month after the launch of the world's first artificial Earth satellite, which marked the beginning of the space age of mankind, on November 3, 1957, the second Sputnik launch vehicle launched into orbit the world's first biological artificial Earth satellite, in the pressurized cabin of which was the dog Laika. The total weight of the equipment, experimental animal and power supplies of the second satellite exceeded 500 kg. In May 1968, a rocket of the same type, Sputnik, lifted into space the third Soviet satellite, weighing 1327 kg. It was already a real multi-purpose automatic flying laboratory with a large number various scientific instruments, multi-channel telemetry system and other on-board equipment. The launch of these satellites marked the beginning of comprehensive research and exploration of outer space.
Developed in the late fifties space program Soviet Union provided, in particular, for the need to increase the energy capabilities of launch vehicles, and consequently, the possibility of increasing the mass of payload launched into outer space. In accordance with this task, the team headed by the Chief Designer of Rocket and Space Systems S. P. Korolev persistently improved the two-stage rocket and, on its basis, developed a three-stage and then a four-stage rocket. With a slight increase in launch weight, these rockets lifted a payload three and then more than four times greater than Sputnik.
(51) UNION OF SOVIET SOCIALIST REPUBLICS STATE PATENT OFFICE OF THE USSR (USSR STATE PATENT) DESCRIPTION OF THE INVENTION to the author's side (72) Makhaev V.G.; Ozherepeva L.D.; Malinova L.R. (56) Copyright certificate of the USSR No. 1380547, class. N 01 21/68, 1984. Author's certificate of the USSR I 361535, class. N 05 K 5/00, 1970.(54) CARRIER SATELLITE FOR INTEGRATED CIRCUITS IN FLAT PACKAGES WITH TERMS POSITIONED AROUND THE PERIMETER(57) The invention relates to a technological container for electronic products that provides orientation, automatic download, carrying out control and testing operations, marking, transportation of integrated circuits in the process of their manufacture, in particular to end-to-end technological containers for microelectronics products that provide protection from mechanical loads. The purpose of the invention is to improve operational capabilities by increasing the reliability of fixing the leads in the grooves, achieved by that the cover 5 of the carrier satellite is equipped with shaped clamps for the terminals of integrated circuits, located along the periphery of the grooves parallel to the wedge-shaped protrusions b and made in the form of jumpers with bevels along the entire length, the tops of which are directed to the edges of the base 1. 5 ill.1664082 along the periphery of the grooves and 55 oriented perpendicular The invention relates to technological packaging for electronic products, providing orientation, automatic loading, carrying out control and testing operations, marking and transportation of integrated circuits (ICs) during their manufacture, in particular to end-to-end technological packaging for microelectronics products, providing protection from mechanical loads. The purpose of the invention is improving operational capabilities by increasing the reliability of fixing the leads in the grooves. FIG. 1 shown general form in respect of; what the heck, 2 - section A-A in Fig, 1; in fig. 3 - satellite cover in axonometry; in fig. 4- the base of the satellite in axonometry; what the heck. 5 - shaped cover clamp. The carrier satellite for the IC contains a base 1 with support pads 2 and slots 3 for the IC leads, a window 4, a cover 5 installed with the possibility of fixing on the base 1 by means of wedge-shaped protrusions 6 with strips 7 for pressing the IC leads to the base 1. The cover 5 is equipped shaped clamps 8 IC pins, which are located along the periphery of the grooves parallel to the wedge-shaped protrusions and are made in the form of jumpers with nipples 9 along the entire length, the tops of which are directed to the edges of the base, as well as an elastic cross-shaped retainer 10 for the IC case with platform 11. Operation of the carrier satellite occurs as follows ,The IC housing fits into window 4 of the base 1 in accordance with GOST 20.39.40584 with the cover of the device housing downwards, the IC leads fall into the grooves of 3 support pads 2, Window 4 and grooves 3 protect the IC from moving in the horizontal plane. Then a cover 5 with a platform 11 is placed on top, which is adjacent to the bottom of the device body and protects the IC from vertical movements and protects the IC from accidental mechanical influences at the installation location of the crystal. When closing the cover 5, the shaped clamps 8 interact with the IC pins and press them against the support ones. AND NTEGRAL MICROCIRCUITS IN FLAT CASES WITH TERMINALS AROUND THE PERIMETER, containing a base with support pads and grooves for microcircuit leads, a cover with wedge-shaped protrusions that fix it and clamping strips with pins 5 10 15 20 25 30 35 40 45 50 base pads of 1 carrier satellite , The location of the bevels of 9 shaped clamps 8 at an acute angle to the IC terminals allows them to slide along the terminals in the direction from the center of the IC body to the periphery, without deforming them, but, on the contrary, further straightening them. Examples of a specific implementation are satellites in flat cases with the terminals located along the perimeter SN.IM/0.625 - 095 (ShchDM 4.118.371) and SN. IM/0.625-096 ShDM 4.118.390) with parameters: number of pins 132, 108 with a pitch of 0.625 and base platform 63 x 63 and 51 x 51, respectively, containing base 1 with support pads 2 and grooves 3 for IC pins, cover 5, installed with the possibility of fixation on the base 1 by means of clinoid protrusions 6 with strips 7 for clamping the IC leads to the base 1, placed along the periphery of the grooves 3 and located perpendicular to the wedge-shaped protrusions 6. The cover 5 is equipped with shaped clamps 8 IC leads, placed along the periphery of the grooves 3, parallel wedge-shaped protrusions 6, made in the form of jumpers, turning along the entire length of the clamps into bevels 9, located at an acute (30 - 450) angle to the center of the satellite. The shaped clamps 8 have spring properties that depend on the numerical value of the acute bevel angle. The optimal value of the angle is 30 - 450. In this case, it has been experimentally established that clamps 8 with a bevel of less than 30 do not provide reliable contact of the leads with the supporting platforms 2 of the base of 1 satellite, i.e., the springing properties of the clamps decrease, and with a bevel angle 9 of more than 45 it increases significantly the rigidity of the shaped clamps, i.e. with an increase in rigidity when opening the cover 5 of the satellite, the effects of a hard clamp on the IC terminals and, as a result, deformation of the terminals are possible. This design of the satellite carriers makes it possible to increase the reliability of contacting by increasing the reliability of fixing the IC terminals in the grooves, and the microcircuits to the base, placed with a wedge-shaped protrusion, characterized in that, in order to improve operational capabilities by increasing the reliability of fixation of the leads in the grooves, the cover is equipped with shaped clamps for the leads of integral micro-circuits and made in the form of jumpers of circuits, located along the periphery with bevels along the entire length, the top of the grooves is parallel to the wedge-shaped protrusions directed towards the edges of the base.
Application
4662402/21, 13.03.1989
Makhaev V. G., Ozhereleva L. D., Malinova L. R.
IPC / Tags
Link code
Carrier satellite for integrated circuits in flat packages with pins arranged around the perimeter
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