RU1818285C - Ballistic recoverable capsule - Google Patents

Abstract

Usage: delivery of payload from a space object to Earth. SUMMARY OF THE INVENTION: A capsule comprises a housing provided with resettable thermal protection (TPP). The capsule is equipped with an inflatable airtight shell located e the gap between the housing and the TZP. Filling the shell with gas occurs when the capsule is separated from the space object, as a result of which the body and the pressure transformer are compressed by excessive pressure, which reduces the vibration load on the capsule during its descent in dense atmospheric layers. 5 ill.

Description

: The invention relates to spacecraft for returning to the atmosphere of the Earth, braking and landing.

The aim of the invention is to improve the performance of the capsule by reducing vibration loads during the descent of 8 dense atmospheric layers.

In FIG. 1 shows a general diagram of a device in its initial position; in FIG. 2 - nipple device; Fig. 3 is a capsule after applying pressure to the sealed enclosure; in FIG. 4 - the structure of the hermetic shell; in FIG. 5 is a general diagram of a capsule after pressure has been applied to the sealed sheath M of the heat-release coating.

The ballistic return capsule 1 (Fig. 1) includes a housing 2 with resettable thermal protection 3. The capsule 1 is made in the form of a cylinder 5 with a front cone 5 and a blunting over the sphere 6. The capsule 1 has a conical skirt 7.

A useful load 8 is placed inside the housing 2. The housing 2 is closed by a hermetic bottom 9. The thermal protection 3 is made in the form of an integral integral shell. Case 2 is made of two parts. The first of them (front) has a payload of 8, and the second (bottom) has an automation system 10, power supply 11, and capsule search 12. A braking propulsion system 13 is provided for descent from orbit, and stabilization motors 14 are used to stabilize the position of the capsule.

The parachute system 15 is also located in the bottom part in the parachute compartment 16, the separation device 17 of the brake and stabilization engines, which are mounted on the frame 18.

For mounting and interconnecting the compartments of the capsule body, frames 19,20.21,22 are provided. The pressure plate 9 is attached to the housing 2 by means of locks 23. The remaining locking devices are not shown in the drawings.

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If necessary, a balancer 25 can be installed in the nose 24 of the capsule 1. Under the thermal protection 3, a sealed shell 26 is placed along the entire length of the capsule 1, having at least one nipple device 27. placed in the bottom 28 of the capsule 1 and connected to the pressure source 29 through the automatic undocking device 30 (FIG. 2). The nipple device 27 of the airtight shell 26 is attached to the capsule body 2 by means of a nut 31. FIG. Figure 2 shows the position after disconnecting the communication with the power source.

In FIG. 3 shows a sealed enclosure 26 filled with compressed gas 32.

Resettable thermal protection 3 is made in a form structurally similar to the capsule body and placed with a clearance of concentric to the body 2 (Figs. 1 and 3). The heat shield 3 and the casing 2 are interconnected in the bottom 28, for example, by means of three power locking devices (not shown) which absorb all longitudinal loads. Taking into account that the descent of the capsule is carried out at small trajectory angles of entry into the Dense atmosphere (- 2.5 °), the loads acting on the capsule during descent in the dense layers of the atmosphere are relatively small and the forces acting on each of the power locking devices amounted to approximately 0.5 ... 1.0 t.

These loads are partially removed from the locking devices due to friction between the pressurized shell 26 filled with compressed gas 32, thermal protection 3 and capsule 1 body 2.

The sealed sheath 26 is internally divided in the longitudinal and transverse direction of the x-section 33 by partitions 34. The sections 33 are interconnected by at least two valves 35 and 36, for example, membrane-type, working in opposite directions, installed in the partitions 34 (Fig. , 4). Instead of valves, calibrated holes can be made.

Fig. 5 shows the ballistic return capsule 1 after the thermal protection 3 has been reset. Under the action of compressed gas 32, the sealed casing 26 is expanded to form a case around the capsule 1. The pressure source 29 has a actuating mechanism 37.

The device operates as follows.

The spacecraft control system issues a command to separate the ballistic return capsule 1 from it. The activation mechanism is triggered by this command 37

a pressure source 29 and compressed gas fills the sealed enclosure 26, compressing the heat shield 3 (from the inside) and the housing 2 (from the outside). After this, the capsule is separated from the spacecraft and

moves away from it to a safe distance, where the TDU is launched, ensuring the capsule leaves the orbit. At the stage of removal from the spacecraft and the operation of the TDU, stabilization engines work 14. providing a given orientation

0 longitudinal axis of the capsule in outer space.

After the operation of the TDU, the braking and stabilization engines, together with the frame 18 and the pressure source 29, are separated from

5 capsules. The capsule continues its autonomous flight along a ballistic descent trajectory in dense atmospheric layers up to an altitude of 20 km, where, by the command of the automation system 10 of capsule 1, the parachute compartment lid is shot and the parachute is put into the stream.

Further flight is carried out with a brake parachute to an altitude of 10 km, where the main

5 parachutes, activation of the capsule search system (ejection of dipole reflectors, activation of a radio beacon located on capsule 1), reset of thermal protection. After the heat shield 3 has been reset, the sealed sheath 26 straightens, assuming a working position to meet the surface of the earth. At the time of thermal protection reset 3 after undocking of the power locking devices connecting the thermal protection 3 with the housing 2

5 of the capsule 1, simultaneously with the opening of the main parachute, the pressure 32 of the hermetic shell 26 is in effect, contributing to the more rapid discharge of thermal protection 3 from the body 2.

0 At the moment of contact with the surface of the earth, at the signal of the piezoelectric transducer, the automation system shoots (cuts off) the parachute and the capsule with its airtight shell 26 begins to interact with the ground (water). In this case, the section 33 of the capsule, which, for example, first touched the ground, begins to be squeezed, pumping the compressed gas from this section to the neighboring sections through, for example, the valve 35. As the neighboring sections 33 are compressed, the same thing happens with them. The compressed gas is pumped into neighboring sections in accordance with the passage sizes and the number of, for example, valves 35. Theoretically and experimentally, it is possible to select the optimal characteristics of these valves or simply calibrated openings.

After the capsule’s speed is completely extinguished, the compressed gas from the sections that were uncompressed during the landing and which absorbed the compressed gas from

of the compressed sections begins to return to the initially compressed sections, but through other, for example, diaphragm valves 36. The characteristics of these valves are selected so as to prevent the capsule from jumping up.

Since the capsule is lowered by a parachute secured to the bottom of the capsule, the most probable first encounter with the ground is the nose of the capsule. After the parachute is fired, the capsule begins to tumble onto the side surface. In this case, the corresponding sections 33 of the airtight shell 26 will be crimped on the side surface and the tail skirt (Fig. 5) and the processes described above will similarly undergo.

: At the final stage of landing, the capsule will have a stable position on the ground, the pressure in sections 33 of the sealed shell 26 will equalize. Around the capsule there will be a thermo-insulating shell, which for some (estimated) time will protect it from excessive overheating in summer and overcooling in winter.

To reduce the heat-absorbing shell, its outer surface should be covered with a layer of material (spraying) with high reflective characteristics.

The gap A (Fig. 3) is selected (theoretically and experimentally) in such a way as to provide maximum damping of vibration loads when the capsule is lowered in dense atmospheric layers.

The proposed embodiment of the ballistic return capsule makes it possible to improve the performance of the capsule by reducing vibration loads during descent in dense atmospheric layers and accelerating the discharge of thermal protection from the capsule body.

Instead of several commonly used systems (soft landing systems, rescue systems during splashdown, additional thermal insulation on the ground), one sealed enclosure is proposed that functions as all of these systems. In this case, the pressure source used to fill this shell with compressed gas is separated from the capsule together with the brake and stabilization engines and occupies the minimum useful volume of the capsule.

Claims (1)

The claims A ballistic return capsule comprising a housing with a resettable heat-shielding coating installed on it, structurally similar to the housing and connected to it by means of separation elements, the heat-shielding coating being installed with a gap with respect to the housing, characterized in that, in order to improve the performance of the capsule by reducing vibration loads during descent in dense atmospheric layers, the capsule is equipped with an inflatable airtight shell located in the gap between the housing and protective coating. Fi g yudgg2127 twenty 22 u & 9Pf    iXJnL - i ff ft- j k: i 7t g fifQI # S8Z8181 Bj & Ј bpf Sz  i i ff ft- j k: i 7t gg f.  ch0 Fig 5 70D / 2