German LFA Experimental F 22 Rocket .1941

[klem]

The project for the development of the experimental F 22 rocket started in May 1941 at the Luftfahrtforschungsanstalt Hermann Göring, Braunschweig (LFA), its project manager was Gerhard Braun. "This work proceeded in parallel to industrial developments that had partly been undertaken on their own initiative during the same year. W. Wernitz reports later that the LFA development had been performed to be able to compare windtunnel measurements with original high-speed test data.

With regard to the purpose of the LFA development, there were obviously discrepancies at the RLM. In a letter of February 2, 1943, the Research Directorate stated that the LFA did not have the task of developing an operational antiaircraft rocket . Rather questions of control were to be examined, and problems of flight mechanics were to be solved. At least the Rheinmetall-Borsig Company had accompanied this development and was later, also involved in the evaluation of the test results. It is not obvious from the report of G. Braun and P. Retert on which specifications the experimental rocket F 22 was based. The highest demands with regard to the speed represented the self target-seeking rocket. Supersonic speeds were demanded by such a rocket to be able to reach a target at the desired distance and altitude. It was, nevertheless, the wish of the LFA to venture with the projectile into the supersonic speed regime to be able to collect important data.

The layout of the F 22 (fuselage diameter 0.22 m) envisaged correspondingly a slender fuselage with a bullet-like nose. The nose formed an ogive with a 10-caliber curvature; it was copied off the long-range missile A4. It is likely that the missile "Hecht " which was at the time under development at the LFA , served as a further model. Basic investigations were to be carried out with the "Hecht" concerning the stabilization and control of glide bombs.

No reference to wings is found in the description of the F 22. Because however, large side forces were required to keep the F 22 on the guide beam, it may be assumed that Braun had also planned wings for the projectile. The relatively simple stabilizers at the tail were dimensioned so that the static stability was ensured within the entire speed range, For propulsion, a solid-fuel rocket of Rheinmetall-Borsig was to be employed. The takeoff was carried out vertically from a launch tower. The rocket was guided by a 20-m long ramp. When leaving the launch tower, the rocket was expected to reach a speed of 4 m/s, sufficient for an aerodynamic stabilization by stabilizer fins.

In 1941, further considerations and configuration studies led to the model F 25 with a fuselage diameter of 0.25 m and conventional wings. The name "Feuerlilie " was mentioned for the first time in the last quarterly report of the Institute of Aerodynamics that year. The work commenced in the fall of 1941 with wind-tunnel measurements. The determination of the main load cases and the design of an airworthy version were completed in the summer of 1942. The manufacture of the rocket was carried out at the Ardelt Works in Breslau. It was clear from the start that the selected configuration must reach supersonic speeds. Therefore, a swept wing with a 45 degree angle of inclination (at the level of the aircraft wing) was chosen".

Special Features of Antiaircraft Rockets with Swept or Low-Aspect-Ratio Wings-Bernd Krag https://arc.aiaa.org/doi/10.2514/5.9781600867552.0545.0614

 

[Scapaflow]

The project for the development of the experimental F 22 rocket started in May 1941 at the Luftfahrtforschungsanstalt Hermann Göring, Braunschweig (LFA), its project manager was Gerhard Braun. "This work proceeded in parallel to industrial developments that had partly been undertaken on their own initiative during the same year. W. Wernitz reports later that the LFA development had been performed to be able to compare windtunnel measurements with original high-speed test data.

With regard to the purpose of the LFA development, there were obviously discrepancies at the RLM. In a letter of February 2, 1943, the Research Directorate stated that the LFA did not have the task of developing an operational antiaircraft rocket . Rather questions of control were to be examined, and problems of flight mechanics were to be solved. At least the Rheinmetall-Borsig Company had accompanied this development and was later, also involved in the evaluation of the test results. It is not obvious from the report of G. Braun and P. Retert on which specifications the experimental rocket F 22 was based. The highest demands with regard to the speed represented the self target-seeking rocket. Supersonic speeds were demanded by such a rocket to be able to reach a target at the desired distance and altitude. It was, nevertheless, the wish of the LFA to venture with the projectile into the supersonic speed regime to be able to collect important data.

The layout of the F 22 (fuselage diameter 0.22 m) envisaged correspondingly a slender fuselage with a bullet-like nose. The nose formed an ogive with a 10-caliber curvature; it was copied off the long-range missile A4. It is likely that the missile "Hecht " which was at the time under development at the LFA , served as a further model. Basic investigations were to be carried out with the "Hecht" concerning the stabilization and control of glide bombs.

No reference to wings is found in the description of the F 22. Because however, large side forces were required to keep the F 22 on the guide beam, it may be assumed that Braun had also planned wings for the projectile. The relatively simple stabilizers at the tail were dimensioned so that the static stability was ensured within the entire speed range, For propulsion, a solid-fuel rocket of Rheinmetall-Borsig was to be employed. The takeoff was carried out vertically from a launch tower. The rocket was guided by a 20-m long ramp. When leaving the launch tower, the rocket was expected to reach a speed of 4 m/s, sufficient for an aerodynamic stabilization by stabilizer fins.

In 1941, further considerations and configuration studies led to the model F 25 with a fuselage diameter of 0.25 m and conventional wings. The name "Feuerlilie " was mentioned for the first time in the last quarterly report of the Institute of Aerodynamics that year. The work commenced in the fall of 1941 with wind-tunnel measurements. The determination of the main load cases and the design of an airworthy version were completed in the summer of 1942. The manufacture of the rocket was carried out at the Ardelt Works in Breslau. It was clear from the start that the selected configuration must reach supersonic speeds. Therefore, a swept wing with a 45 degree angle of inclination (at the level of the aircraft wing) was chosen".

Special Features of Antiaircraft Rockets with Swept or Low-Aspect-Ratio Wings-Bernd Krag https://arc.aiaa.org/doi/10.2514/5.9781600867552.0545.0614

Probably the basic work for the development of the f25.