DE2054877A1 - Arrangement for thrust generation and energy supply - Google Patents

Description

Arrangement for thrust generation and energy supply The invention relates on arrangements for thrust generation and energy supply, especially for Satellite launch systems with nuclear rocket propulsion.

A distinction is made between the flight mission of a satellite carrier system two flight phases: the thrust phase, during which the engine unit and the power supply Unit are switched on and the free flight phase, during which only the energy supply of the entire delivery system is maintained.

So far, separate units have been used for the respective flight phases Energy supply provided in the push and free flight phase.

The object of the present invention is to provide an arrangement for nuclear to develop propelled rockets that use a minimum of aggregates in the thrust and free flight phase.

According to the invention, this happens in that the on the power supply unit Acting reactor connected in the thrust phase between a tank and an exhaust nozzle is.

An advantageous embodiment of the invention is characterized in that that the reactor is connected to a turbine, a compressor and a generator is. Furthermore, an expedient arrangement is characterized in that a cooler is installed in the pipeline between the turbine and the compressor.

An improved arrangement is characterized in that the cooler is arranged as a jacket cooler around the tank.

The performance of the arrangement can be increased in that the jacket cooler is provided with a detachable outer insulation and an explosive device is, so that it is in the overrun phase as tank heating and in the free flight phase as The jet cooler works. Due to the double function of the power supply units Unit, a separate energy supply can be saved in the free flight phase.

The invention is based on the drawing of an exemplary embodiment explained. They show: FIG. 1 longitudinal section through an arrangement for generating thrust and power supply Figure 2 a, b cross section through a fuel tank in Figure 1, the reactor 1 and the thrust nozzle 4 are each equipped with a cooling jacket 12, 23 and connected to the tank 3 and the turbine 5 via pipes 14. turbine 5 and compressor 6 are mechanically coupled to a generator 9 via shaft 13 and connected to the cooler 7 by pipe 16.

The compressor 6 is still connected to the compressed gas cushion 2 via pipelines 17 and connected to the reactor 1 via pipes 18. A two-way valve 21 couples the pipes 17 and 18. For the closed gas process is between Cooling jacket 12 and turbine 5, a pipeline 22 installed.

FIG. 2a shows, in position A, a cross section through the tank 3, the outer insulation 9 with the explosive device 10 and the one consisting of cooling coils 19 Cooler 7.

In position B, the tank 3 with the cooler 7 is in the exploded state shown. In Figure 2b, inside mirror surfaces 11 are additionally attached.

Functional description: he pank 3 holds the propellant gas for the thrust generation, after firing the rocket from a compressed gas cushion 2 via pipeline 14 in the cooling jacket 23 of the thrust nozzle 4 and pressed into the cooling jacket 12 of the reactor 1 will.

This is the design according to a gas-cooled reactor, in which, however the propellant itself takes over the cooling.

Here, the larger partial flow is evaporated to the extent that it is in the REaktor 1 passed through pipeline 20 and after a further heating in the Nozzle 4 can be relaxed.

A small partial flow is used to drive the turbine 5, the releases its mechanical energy to the compressor 6 and the generator 8 via shaft 13. The remaining thermal energy of the partial flow is used for heating in the cooling jacket 7 of the tank 3 of fuel required. The propellant gas, which has now been greatly cooled, is over Pipeline 16 given to the compressor 6, the compressed propellant gas through Pipeline 17 lracks onto gas cushion 2.

After the end of the overrun phase, the tank 3 is only with pressureless propellant gas filled. The tank insulation 9 is destroyed by means of an explosive device 10 and at the same time the cooling jacket 7 burst open, so that the heat is now radiated into space can be. This is done particularly cheaply using the mirrors installed in the tank 11.

The thrust-generating and energy-supplying system is now closed gas turbine process switched to pure energy supply. After this the two-way valve 21 has been actuated, the compressor 6 can use the propellant gas Promote pipelines 17, 18 into reactor 1.

After heating, it enters the turbine through the pipe 22 5 and is relaxed. It is then in the cooler 7 after passing through the pipeline 16 cooled further until it reaches the compressor 6. This is a closed one Gas cycle produced in the usual way for generating mechanical or electrical energy, in the free-flight phase also for cooling the reactor 1 and the thrust nozzle 4 can be used.

To enable a second thrust phase after a free flight, can an additional tank with a pressurized gas cushion parallel to the main tank 7 in the pipeline system be switched.

- patent claims -

Claims (7)

Claims 1. arrangement for thrust generation and energy supply, bestexlerld especially for satellite carrier systems with naclear speed drive from a reactor, an engine unit and an energy supply unit, as a result, that the on the power supply unit (5, 6, 7) acting reactor (1) in the overrun phase between a tank (2, 3) and a thrust nozzle (4) is connected. 2. Arrangement according to claim 1, characterized in that g e k e n n -z e i c h n e t that the reactor (1) with a turbine (5), a compressor (6) and a generator (8) is connected. 3. Arrangement according to claim 1 or 2, characterized in that g e k e n n -z e i c h n e t that a sensor (7) in the pipe (16) between the turbine (5) and the compressor (6) is built in. 4. Arrangement according to claim 3, characterized in that g e k e n n -z e i c h n e t that the cooler (7) is arranged as a jacket cooler around the tank (2, 3). 5. Arrangement according to claim 4, characterized g e k e n n -z e i c h n e t that the jacket cooler (7) with a detachable outer insulation (9) and an explosive device (io) is provided. 6. Arrangement according to claim 5, characterized in that g e k e n n -z e i c h n e t that the jacket cooler (7) in the overrun phase as tank heating and in the free flight phase is designed as a radiation cooler. 7. Arrangement according to claim 6, characterized in that g e k e n n -z ei c h ne t, that in the tank (3) reflecting mirrors (11) are attached. L e r s e i t e